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
2004052600055	20040526	00055	NE  	2004	5	26	00141            	2	20040524	G	7200		ENGINE          			LEAR  	24    	24F         	5170317	CE  	GE    	CJ610 	CJ6106      	30006	NE  					LEFT	FLAMED OUT      	E			HAEA	O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			SW	05	444TW	15995	10363			24F348	241C050A			AIRCRAFT ENCOUNTERED TURBULENCE AT FL390K. LT ENGINE FLAMED OUT. ENGINE RELIGHT NORMAL.						2	L	7	2 	4J	4	J	 	A10CE   	1E16
2005031000028	20050310	00028	NM  	2005	3	10	0041005          	1	20041005	G	3097		WIRE            			BOEING	727   	727100      	1384036	NM  										DRAIN HEATER	SHORTED         	C			U1IM	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	23	727VJ					19318				AFTER TAKEOFF AT 1000 FT, A BURNING ODOR NOTED, NO OBVIOUS PROBLEM WITH GEN LOADS, APPROX 3000 FT VISIBLE SMOKE EMINATIN	G BEHIND FE TABLE. NO CB'S POPPED, NO VISIBLE SYS TROUBLE. TROUBLE CEASED & SMOKE CLEARED. ENGINEER DETERMINED ALL SYSTE	MS OPERATIONAL. AS IT WAS A DAY TIME FLIGHT AND VMC EXISTED WE ELECTED TO CONTINUE FOR OUR SCHEDULED MX. UPON IVESTIGATI	ON DRAIN MAST "AIR" CB DID NOT POP, WIRING FROM CB TO DRAIN MAST BURNED EXPOSING BARE WIRES. TROUBLE TRACED TO FWD DRAIN	 MAST, FOUND LOOSE INSIDE MAST FAIRING. MAST HEATER WIRE SHORTED TO MAST STRUCTURE. RUN OF WIRE REPLACED, CB'S REPLACED 	(AIR & GRD) EXERCISED ALL CB'S IN COCKPIT, REPLACED FORWARD DRAIN MAST, MLG ACCESSORY BOX REPLACED DUE TO DAMAGED WIRES.	2	L	7	3 	4F			RT	A3WE
2004022300078	20040223	00078	NM  	2004	2	23	01070422H        	1	20040107	G	5743		SPAR CAP        			UNIVAR	415   	415D        	0420306	NM  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25						3647				FOUND A POCKET OF EXFOLIATION ON TOP OF BOTTOM SPAR CAP EXTRUSION, AT AREA DIRECTLY BELOW MAIN LANDING GEAR ATTACH BOLT.	  ALSO FOUND AREA OF EXFOLIATION IN STIFFENER 31107 ON LT SIDE BEHIND WING FILLET.					1	L	7	1 	3O			 	A787
2004022500086	20040225	00086	CE  	2004	2	25	01222004         	1	20040122	G	5210	07110381	HINGE PIN       			CESSNA	182   	182H        	2072718	CE  										LWR RT DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2084X					18256184				DURING ANNUAL INSPECTION LOWER RT DOOR HINGE PIN WAS FOUND BROKEN IN 3 PLACES. THIS ITEM IS SIMPLE TO DETECT BY JUST OPE	NING AND CLOSING THE DOOR SLOWLY AND WATCH FOR EQUAL ROTATION OF PIN.  IF ONLY ONE END TURNS THEN THE PIN MUST BE BROKEN	.  PART INFO: HINGE PIN  P/N 0711038-1, AFFECTING LOWER HINGE (P/N 0711037-20) OF RT DOOR.				1	H	7	1 	3O			NT	3A13
2004110200127	20041102	00127	SW  	2004	11	2	031283           	1	20040901	G	5310		TUBE            			SPARTN	7W    	7W          	8430302	SW  	PWA   	R985  	R985*       	52008	NE  					FUSELAGE	BENT            	B			W2OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	17662					28				DURING SCHEDULED INSPECTION, FOUND AFT FUSELAGE TUBES BENT AND CRACKED. THIS AREA HAD BEEN PREVIOUSLY REPAIRED FOR SIMIL	AR CONDITION.  DAMAGE WAS APPARENTLY CAUSED BY TAIL WHEEL LINK STRIKING TUBES AS A RESULT OF UNDER INFLATION OR COLLAPSE	 OF TAIL WHEEL STRUT.  THERE IS NO EXTERNAL STOP ON THE TAIL WHEEL ASSEMBLY TO PREVENT THE LINK FROM CONTACTING THE TUBE	S DUE TO COLLAPSE OR UNDER INFLATION OF TAIL WHEEL STRUT.  RECOMMEND ALL MFG OWNERS CAREFULLY INSPECT THIS AREA DURING I	NSPECTIONS AND MAINTAIN THE PROPER SERVICING IN THE TAIL WHEEL STRUT.		1	L	7	1 	3R	3	R	 	TC628   	5E1
2004042900095	20040429	00095	EA  	2004	4	29	033104           	2	20040324	G	7230	MS9714XX	BOLT            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					COMPRESSOR	BACKED OUT      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	30HF		370  			LJ506	PCE22520			PILOT REPORTS (GRINDING) SOUND WHEN PROPELLER IS SPUN BY HAND. THE ENGINE WAS SPLIT AT THE (C) FLANGE WHERE DEBRIS WAS N	OTED AT THE 6 O'CLOCK AREA BETWEEN THE COMPRESSOR TURBINE BLADES AND SHROUD SEGMENTS. AFTER REMOVAL OF THE CT DISK, IT W	AS NOTED THAT FOUR BOLTS HOLDING THE INNER EXIT DUCT TO THE ENGINE WERE MISSING. THE DEBRIS WERE THE REMAINS OF THE FOUR	 BOLTS.  SAFETY WIRE WAS NOT PRESENT IN THE REMAINING FOUR BOLTS. 370 HOURS SINCE ENGINE O/H.			1	L	7	2 	3T	3	T	 	3A20    	E4EA
2004111900036	20041119	00036	SO  	2004	11	19	040103119        	1	20040723	G	2913	1159SCH20041	PUMP            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					HYD SYSTEM	FAILED          	B			Y3PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	35	7800					1098				ENGINE DRIVEN HYDRAULIC PUMP INTERNAL FAILURE.  LARGE ACCUMULATION OF METAL SHAVINGS FOUND IN HYDARULIC FILTER AND CANIS	TER, CAUSING THE BYPASS INDICATION BUTTON TO POP.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE
2004051200092	20040512	00092	EA  	2004	5	12	040505           	2	20040504	G	8530	68795	ROCKER COVER    	LYC         		HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  					ENGINE	WORN            	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	62JA		370  			1443				ROCKER BOX, PN 68795 WAS WORN BY THE VALVE ROCKER SHAFT UNTIL THE SHAFT CUT THROUGH THE SHAFT RETAINER WHICH IS SPOT WEL	DED TO THE VALVE COVER.  THREE OF SIX COVERS WERE SEVERELY WORN.  A FOURTH COVER'S BRACKET WAS WORN THROUGH AND THE RESU	LTING SLUG OF METAL (ROCKER SHAFT WAS WORKING LIKE A WAD CUTTER) WAS FOUND LYING IN THE VALVE ROCKER BOX.  REPLACED FOUR	 VALVE COVERS WITH SERVICEABLE PARTS.			1	H	7	1 	3O	3	O	 	1A8     	E275
2004050300143	20040503	00143	CE  	2004	5	3	040604           	1	20040406	G	1430	MS9714XX	BOLT            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	30HF					LJ506	PCE22543			THE ENGINE WAS SPLIT AT THE (C) FLANGE.  AFTER REMOVAL OF THE C.T. DISC, IT WAS NOTED THAT 2 BOLTS HOLDING THE INNER EXI	T DUCT TO THE ENGINE HAD SHEARED OFF AND WERE LODGED IN THE AREA, WITH THE REMAINDER OF THE BOLT SHANKS LEFT IN THE BOLT	 HOLES.  DAMAGE WAS NOTED ON THE C.T. DISC.  SAFETY WIRE WAS PRESENT IN ALL THE BOLTS INCLUDING THE SHEARED BOLT HEADS.				1	L	7	2 	3T	3	T	 	3A20    	E4EA
2004091500091	20040915	00091	SO  	2004	9	15	040624           	2	20040624	G	8520	646520646521	CRANKCASE       			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			EVGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	33		5704 					4A9388			IT HAD PROP STRIKE WHICH IS WHEN THE DAMAGE PROBABLY OCCURRED. OVERHAULED AND RAN FULL LIFE BUT OIL LEAKS DEVELOPED AT T	HE MOST FORWARD THROUGH BOLTS.  BECAUSE OF THE OIL LEAK AT BOLT HOLE DURING RUNUP AFTER OVERHAUL THAT WAS JUST COMPLETED	.  CRACK IS IN FRONT MAIN LOWER THRU BOLT HOLE IN LEFT CASE HALF.  CRACK IS ABOUT 2.5 IN. LONG, STARTS INSIDE HOLE ABOUT	 AN INCH FROM PARTING SURFACE AT ABOUT 9 O'CLOCK AS VIEWED FROM THE OUTSIDE CASE, SPIRALS SLIGHTLY TO ALMOST 11 O'CLOCK 	POSITION.  CRACK CAN BE VIEWED WITH THROUGH BOLT REMOVED AND BY USING A BORESCOPE.  SINCE CRACK IS ON FORWARD SIDE OF HO	LE, IT COMMUNICATES WITH OIL PASSAGE THAT IS JUST FORWARD OF THROUGH BOLT HOLE, THUS CAUSING THE LEAK.	1	H	7	1 	3O	3	O	 	A4CE    	E5CE
2004030100130	20040301	00130	CE  	2004	3	1	041332           	1	20040212	G	2823	CCA1550	DRAIN           	CESSNA      		CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300*       	17022	SO  					FUEL VALVE	CRACKED         	B			W2OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	6341E					46441				PILOT REPORT OF FUEL LEAK FROM SELECTOR. FOUND LEAKAGE PAST SHAFT SEAL. REMOVED SELECTOR VALVE FOR REPAIR. CCA-1550 DRAI	N VALVE WAS INSTALLED IN BOTTOM OF SELECTOR VALVE. WHEN DRAIN VALVE WAS REMOVED, ORING RETAINING WASHER AT END OF DRAIN 	VALVE WAS OBSERVED TO BE CRACKED IN NUMEROUS PLACES AND IN IMMINENT DANGER OF FAILURE. HAD THE WASHER BROKEN OFF, AN UNC	ONTROLLABLE LOSS OF FUEL THROUGH THE DRAIN VALVE WOULD HAVE OCCURRED. THE ONLY WAY TO PREVENT FUEL LEAKAGE WOULD HAVE BE	EN TO SHUT OFF THE FUEL SELECTOR, WHICH RESULTS IN ENGINE STOPPAGE.		1	H	7	1 	3O	3	O	NT	3A12    	E253
2004101300088	20041013	00088	CE  	2004	10	13	041403           	1	20041005	G	7160	BA5710	AIR FILTER      			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	WRONG PART      	B			W2OR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	117MM					17700872	L2119627			DURING TROUBLESHOOTING FOR EXCESSIVE MAGNETO DROP, FOUND FACE OF AIR FILTER ELEMENT DETERIORATED. THE INSTALLATION IS FO	R A BRACKETT FILTER. REMOVED ELEMENT AND FOUND THAT ELEMENT WAS AN UNAPPROVED PART. THE (FILTER) WAS HAND CUT FROM A PIE	CE OF GREEN FOAM .6250 INCH THICK. IT APPEARS THE FACE OF THE FOAM WAS PAINTED BLACK SO AS TO LOOK LIKE A GENUINE BRACKE	TT FILTER. HAD THE FILTER DETERIORATED, INGESTION IN THE CARBURETOR COULD HAVE CAUSED A LOSS OF ENGINE POWER WITH POTENT	IAL FATAL RESULTS. THIS PRESENTS A SERIOUS SAFETY PROBLEM AND REPRESENTS A LACK OF REGARD FOR SAFETY.  NO LOGBOOK ENTRY 	COULD BE FOUND FOR RECENT INSTALLATION OF FILTER. ANNUAL INSPECTION WAS SIGNED OFF IN AUGUST OF 2004.	1	H	7	1 	3O	3	O	NT	A13CE   	E274
2004101300089	20041013	00089	EA  	2004	10	13	041403A          	2	20041005	G	7414	10357586	GEAR            	BENDIX      	S4LN21      	CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320E2D     	41508	EA  					MAGNETO	BROKEN          	B			W2OR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			GL	09	117MM				A13623	17700872	L2119627			LOST POWER ON TAKEOFF. VERIFIED PROBLEM OF LT MAGNETO INOPERATIVE.  INSPECTED AND FOUND MAGNETO DISTRIBUTOR GEAR MISSING	 SEVERAL TEETH. GEAR WAS LOOSE ON SHAFT WHICH PROBABLY CONTRIBUTED TO BREAKAGE. SUSPECT CAUSE WAS LACK OF PROPER MAINTEN	ANCE OVER LIFE OF MAGNETO.  ANNUAL INSPECTION WAS SIGNED OFF IN AUGUST 2004.				1	H	7	1 	3O	3	O	NT	A13CE   	E274
2004051000042	20040510	00042	CE  	2004	5	10	0423JKW          	1	20040424	G	2742	2A9200H	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZONTAL STAB	INOPERATIVE     	C				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	09	45HF	258  	172  			121				CREW REPORTED (PRIMARY TRIM FAULT) WHITE EICAS MESSAGE, WHICH CHANGED TO (PRIMARY AND SECONDARY TRIM FAIL EICAS) AMBER M	ESSAGE ON APPROACH TO LANDING.  HORIZONTAL STAB SYSTEM LOCKED OUT ALL MOVEMENT FOR REMAINDER OF THE FLIGHT.  CREW RESET 	SYSTEM POST LANDING, ALL FAULTS CLEARED, AND THE SYSTEM RETURNED TO NORMAL OPERATION.  NO FAULTS REOCCURED ON NEXT FLIGH	T TO HOME STATION.  REMOVED ACTURATOR PN662740100-007 SN H0053, INSTALLED ACTUATOR PN 662740100-007 SN H0113. (MFG PN 2A	9200H).  COMPLIED WITH AD. (CE09200403217)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004091500117	20040915	00117	CE  	2004	9	15	06282004         	1	20040628	G	3232	MS166251068	RETAINING RING  			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	IO520L      	17032	SO  					MLG DOOR	WORN            	G				O				OTHER                   				K	S		FLUID LOSS                	AFFECT SYSTEMS            		AP	APPROACH       	1			WP	27	121JR	4503 	11   			21061726	511992			A RETAINING RING SEPERATED FROM THE LT MAIN LANDING GEAR DOOR HYDRAULIC ACTUATOR. THIS LEAD TO A LOSS OF HYDRAULIC FLUID	 AND FAILURE OF THE LANDING GEAR SYSTEM.  AIRCRAFT WAS FORCED TO LAND WITH THE NOSE GEAR EXTENDED AND NO MAIN WHEELS.  P	ILOT REPORTED THAT THE ACTUATOR HAD JUST UNDERGONE REPLACEMENT OF INTERNAL PACKINGS A WEEK AND HALF PRIOR TO THE REPORTE	D FAILURE.  PILOT COMMENTED THAT THE ACTUATOR FAILED AFTER ABOUT 6 GEAR CYCLES.			1	H	7	1 	3O	3	O	 	3A21    	E5CE
2004091500097	20040915	00097	SW  	2004	9	15	07092004         	1	20040709	G	3210	4196001C	LANDING GEAR    			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	AEIO360*    	 	EA  					MAINS	COLLAPSED       	G				E				ENGINE SHUTDOWN         				G			MULTIPLE FAILURE          			LD	LANDING        	1			SO	17	6817V	4956 	5    							LANDING GEAR CIRCUIT BREAKER POPPED, ATTEMPTED TO RESET IT AND SAW SPARKS.  PILOT ATTEMPTED  MANUAL EXTENSION OF GEAR BU	T WAS UNABLE TO GET DOWN AND LOCKED INDICATION.  PILOT REPORTED GEAR PROBLEM TO TOWER.  GEAR APPEARED TO BE DOWN AND THE	 PILOT FLEW BY TOWER AND THE CONTROLLER ALSO STATED THAT GEAR APPEARED TO BE DOWN.  LANDING WAS MADE AND LANDING GEAR CO	LLAPSED CAUSING MINOR DAMAGE TO FUSELAGE AND PROPELLER.  MECHANIC IDENTIFIED STRIPPED SPLINES ON EMERGENCY EXTENSION SHA	FT WHICH WOULD NOT ALLOW THE GEAR TO FULLY EXTEND MANUALLY.  IT IS UNCLEAR WHEN THE SPLINE WAS DAMAGED AND WHY.  THE MEC	HANIC DID PERFORM A SUCCESSFUL MANUAL EXTENSION DURING THE ANNUAL INSPECTION LAST JULY.	1	L	7	1 	3O	3	O	 	2A3     	1E10
2004050300116	20040503	00116	EU  	2004	5	3	109041504        	1	20040414	G	6720	1090130117	SPIDER          			AGUSTA	A109  	A109        	0260109	EU  										T/R PITCH	WORN            	B			JBZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	24RX					7185				MECHANIC PERFORMING ROUTINE DAILY INSPECTION NOTICED EXCESSIVE ROTATIONAL PLAY IN THE TAILROTOR PITCH CHANGE SPIDER ASSE	MBLY.  THIS COMPONENT IS INTERNALLY SPLINED TO THE TAIL ROTOR OUTPUT SHAFT.  EXCESSIVE WEAR ON THE SPLINES WILL ULTIMATE	LY RESULT IN THE PITCH CHANGE ASSEMBLY TO SKIP OUT OF ITS PROPER POSITION.				1	G	7	2 	3U			 	H7EU
2004060100133	20040601	00133	EU  	2004	6	1	109052704        	1	20040527	G	2910	MS24166D	RELAY           			AGUSTA	A109  	A109        	0260109	EU  										HYD SYSTEM	FAILED          	B			JBZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	23RX					7205				DURING ROUTINE SCHEDULED MAINTENANCE, IT WAS NOTED THAT THE HYDRAULIC UTILITY POWER PACK WOULD NOT SHUT OFF AFTER REACHI	NG OPERATING PRESSURE.  THE PROBLEM WAS TRACED TO AN ELECTRICAL RELAY.  THE CONTACT POINTS WERE WORN AND HAD INDICATIONS	 OF METAL TRANSFER.  THE RELAY WAS REPLACED AND SUBSEQUENT FUNCTIONAL TESTS OF THE SYSTEM WERE WITHOUT FAULT.  AS A PREC	AUTIONARY MEASURE, WE ARE TAKING STEPS TO REPLACE THIS RELAY THROUGHOUT OUR FLEET.			1	G	7	2 	3U			 	H7EU
2005030800054	20050308	00054	EU  	2005	3	8	11072110704      	1	20041107	G	6410	109813201111	BLADE           			AGUSTA	A109  	A109E       	0260119	EU  	PWC   	PW206C	PW206C      		NE  					TAIL ROTOR	CRACKED         	B			DT1R	O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			EA	17	200BK	620  				11072				PILOT FELT VIBRATION IN TAIL ROTOR PEDALS DURING APPROACH.  POST FLIGHT INSPECTION REVEALED THAT 1 TAIL ROTOR BLADE HAD 	A CHORD WISE CRACK BEGINNING AFT OF THE SPAR AND EXTENDING THROUGH THE TRAILING EDGE OF THE BLADE.  THE CRACK WAS THROUG	H BOTH SKINS AND THE HONEYCOMB CORE. SB109EP-30 REV B AND AD 02-25-51 PROVIDE INSPECTION CRITERIA FOR RECURRING INSPECTI	ONS IN THIS AREA.			1	G	7	2 	3U	3	U	RT	H7EU    	E42NE
2004092300062	20040923	00062	SW  	2004	9	23	121JW            	1	20040622	G	5412	6600011112	FIREWALL        			GULSTM	690TP 	690A        	0141722	SW  										ZONE 400	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	121JW	5674 				11299				THE LT AND RT ENGINE ALUMINUM FIREWALLS (P/N 660001-11 / -12 CHANNEL) HAVE DEVELOPED VERTICAL CRACK INDICATIONS AT THE L	OWER SHEAR CLIP ATTACHMENT TAB.  BOTH THE LT AND RT ENGINE IB LOWER TABS ARE COMPLETELY SHEARED AT THE FLANGE RADIUS.					1	H	7	2 	3T			 	2A4
2005031000043	20050310	00043	EU  	2005	3	10	122004           	1	20041220	G	3233	D52177	HOLDER          	MESSIER     		AMD   	FALC20	FALCON200   	2730150	EU  										PACKING	CRACKED         	B			GQRR	O				OTHER                   				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	05		5100 								THE PACKING HOLDER P/N D52177 INSIDE OF THE MAIN GEAR ACTUATOR P/N A 23721 HAS BEEN FOUND CRACKED ON TWO OCCASIONS.  A S	ERVIE BULLETIN F200-110 IS TO MODIFY THE PART TO PREVENT CRACKING. WE HAVE TWO PACKING HOLDERS THAT ARE CRACKED, ONE MOD	IFIED AND ONE NOT. WE HAVE NOTIFIED FALCON JET ABOUT THE PROBLEM				2	L	7	2 	4F			RT	A7EU
2005020200143	20050202	00143	CE  	2005	2	2	1538T001         	1	20041126	G	2520	863422	TABLE           			CESSNA	421   	421B        	2076014	CE  										CABIN	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	11	1538T	4704 				421B0308				INSPECTED RIGHT HAND CABIN EXECUTIVE TABLE AT THE RECOMMENDATION OF ANOTHER MAINTENANCE FACILITY MAINTAINING SAME TYPE O	F AIRCRAFT.  FOUND A LEFT HAND TABLE INSTALLED.  FORWARD CUP HOLDER WAS SCREWED TO THE TABLE MAKING EMERGENCY EXIT REMOV	AL DIFFICULT.  EMERGENCY EXIT CHECKED AT LAST TWO ANNUAL INSPECTIONS WITH THE INTERIOR REMOVED.				1	L	7	2 	3O				A7CE
2005033000145	20050330	00145	SO  	2005	3	30	1624112304       	1	20041201	G	3244	H34X92518	TIRE            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					NR 4 POSITION	DAMAGED         	B			VZXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	1624	3653 				1318				NR 4 TIRE WAS FOUND TO BE DAMAGED FOR SOME UNKNOWN REASON.  THE DAMAGE WAS SUCH THAT IT APPEARED TO BE A FAILURE OF THE 	TREAD AREA.  A SECTION LOCATED ON THE TIRE TREAD APPEARED TO HAVE BEEN RIPPED AWAY BY SOME UNKNOWN FORCE.  NONE OF THE O	THER 3 TIRES DISPLAYED ANY VISIBLE DEFECTS, TRAUMA, OR DAMAGE.  WEATHER AT THE LOCATION WAS FREEZING RAIN FOLLOWED BY SN	OW AND ICE CONDITION.  CAN NOT DETERMINE IF THE WEATHER HAD ANY EFFECT ON THE MALFUNCTION.   (K)			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE
2004091500096	20040915	00096	GL  	2004	9	15	16970704         	1	20040719	G	7810	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	CRACKED         	B			YD5R	E				ENGINE SHUTDOWN         				O			OTHER                     			UK	UNKNOWN        	1			GL	15	558CD	26   	26   			0942				THIS AIRCRAFT HAD THE NR 1,NR 3,NR 5 HEADERS REPLACED WITH NEW PARTS AT 154.0 HRS.  THE AIRCRAFT THEN EXPERIENCED A CRAC	K IN THE NR 5 HEADER AT 180.0 HRS. THERE DOES NOT SEEM TO BE ANY ABNORMAL STRESS ON THE PART/INSTALLATION. AIRCRAFT EXHA	UST SYSTEM WILL BE MONITORED TO INSURE INTEGRITY.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2004031900013	20040319	00013	NM  	2004	3	19	18069            	1	20040303	G	5710		STRUCTURE       			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				THE CRACK/CORROSION IS LOCATED ON THE AFT VERTICAL SIDE OF STRINGER (HAT SECTION) NR 18.  IT IS LOCATED IN THE LEFT HAND	 OUTER WING AT WING STATION 284.  THE CRACK/CORROSION IS 1.25 INCH LONG AND RUNS SPAN WISE.  THE CORROSION WAS REMOVED C	OMPLETELY AT .024 OF GRIND OUT.  THE CRACK IS STILL EVIDENT AND APPEARS TO GO ALL THE WAY THRU THE MATERIAL.  THE MATERI	AL THICKNESS OF THE HAT SECTION IS .120.			2	M	7	2 	4R	4	R	RT	A1RM    	E272
2004072000002	20040720	00002	NE  	2004	7	20	198M2004         	2	20040709	G	7310		FILTER          								GARRTT	TFE731	TFE73140    	29001	NE  					ENGINE FUEL	CONTAMINATED    	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99	198M									AIRCRAFT EXPERINCED A SERIES OF FUEL BY-PASS INDICATIONS. DURING THE TROUBLESHOOTING WE DISCOVERED THE FILTERS TO HAVE B	EEN CONTAMINATED WITH DIEGME AS A RESULT OF USING AN ANTI-ICE ADDITIVE. I FOLLOWED THE OEM M/M AND REMOVED ALL FUEL PART	S ON ALL THREE ENGINES/APU AND FLUSHED THE AIRFRAME FUEL SYSTEM PER THE OEM TO REMOVE THE CONTAMINATION.									4	F			E1NM
2004030400046	20040304	00046	CE  	2004	3	4	2004001          	1	20040211	G	8000	MHB6016	STARTER         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	97811	163  	136  			17276232	L1550339A			RECEIVED AN OVERHAULED ENGINE FROM MFG ON 5 DEC 2003 AND INSTALLED ON THE AIRCRAFT.  STARTER BENDIX DRIVE GEAR SHATTERED	 AGAINST ENGINE RING GEAR ON A START ATTEMPT.					1	H	7	1 	3O	3	O	NT	3A12    	E274
2004030400048	20040304	00048	CE  	2004	3	4	2004002          	1	20040220	G	8011	MHB6016	STARTER         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	DISENGAGED      	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	97811					17276232	L1550339A			STARTER WAS INSTALLED AFTER ORIGINAL STARTER FAILED ON 2/11/2004 (SDR FILED) FOR A SHATTERED BENDIX DRIVE GEAR.  ENGINE 	WAS SUCCESSFULLY STARTED TWICE AND RETURNED TO SERVICE.  ON FIRST FLIGHT ATTEMPT AFTER STARTER WAS INSTALLED THE BENDIX 	DRIVE GEAR WOULD NOT ENGAGE THE ENGINE STARTER RING GEAR, THE STARTER MOTOR WOULD SPIN BUT THE GEAR WOULD NOT COME FORWA	RD TO ENGAGE THE ENGINE GEAR. THIS UNIT HAD ZERO HOURS SINCE NEW.			1	H	7	1 	3O	3	O	NT	3A12    	E274
2004071900080	20040719	00080	CE  	2004	7	19	200401           	1	20040330	G	2720	GTX330TXP	TRANSPONDER     			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RUDDER CONTROL	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	692JM					525A0004				INSTALLED VARIOUS RADIOS IN THIS AIRCRAFT INCLUDING THE GTX 330 TRANSPONDER INTO THE LOWER SECTION OF THE CAPTAINS INSTR	UMENT PANEL.  MONTHS LATER, WHILE THE AIRCRAFT WAS UNDERGOING A PHASE 5 INSPECTION AT THE MFG, IT WAS DISCOVERED THAT TH	E NEWLY INSTALLED TRANSPONDER WAS INTERFERING WITH THE RUDDER BELLCRANK ABOVE THE PILOTS RUDDER PEDALS AND PREVENTING TH	E RUDDER FROM ACHIEVING FULL TRAVEL TO THE LEFT.  THE LOSS OF TRAVEL WAS IDENTIFIED AS BEING 6 DEGREES DURING A FLIGHT C	ONTROL (THROW) CHECK.  REMANUFACTURED THE PANEL AND RELOCATED THE NR TRANSPONDER TO A MORE APPROPRIATE LOCATION WITH ADE	QUATE CLEARANCE.	1	L	7	1 	4F	4	F	RT	A1WI    	E3GL
2004060100148	20040601	00148	EU  	2004	6	1	20040209         	1	20040526	G	3251	CA248003	SELECTOR VALVE  			CASA  	C212  	C212CC      	2410204	EU  	GARRTT	TPE331	TPE33110R   	0517	WP  	HARTZL	HCB4M	HCB4M       	GL  	NLG	FAILED          	M				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	28	00177					336				DURING LANDING ROLL-OUT AC VEERED LT.  PC WAS STILL ON FLT CNTRLS (CONTROL YOKE, POWER LEVERS, AND RUDDERS) WITH FULL RT	 RUDDER INPUT AND PWR LEVERS IN FULL REVERSE. PC WAS APPLYING BRAKES.  GO-AROUND WAS NOT AN OPTION AS THERE WAS NOT ENOU	GH RUNWAY, NOR TIME TO SPOOL UP ENG. GLANCED AT TILLER WHEEL AND IT INDICATED NOSE WHEEL WAS CENTERED. AC DEPARTED RUNWA	Y, AND AFTER GOING OVER A SMALL RISE, STOPPED IN SAND BETWEEN RUNWAY AND PARALLEL TAXIWAY.  WHEN INSPECTED NOSE-WHEEL ST	EERING SYS, FOUND HYD FLUID AROUND STEERING SEL VALVE, INDICATING INTERNAL FAILURE. REPLACED STEERING SEL VALVE. AC WAS 	TEST-FLOWN AND RELEASED FOR FLIGHT. TEARDOWN REVEALED CENTERING SPRING TENSION WAS LESS THAN SPECIFIED BY CMM 30-50-02.	2	H	7	2 	4T	4	T	 	A43EU   	E4WE	6	C	P56GL
2004110300114	20041103	00114	CE  	2004	11	3	20040720         	1	20040720	G	2810	6225544	HOUSING         			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480B      	41527	EA  					CHECK VALVE	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	61JA					1286				MFG PN 6-2255-44 CHECK VALVE IN FUEL LINE WAS LEAKING.  THE HOUSING OF THE CHECK VALVE WAS CRACKED.						1	H	7	1 	3O	3	O	 	1A8     	E275
2004120200211	20041202	00211	EA  	2004	12	2	20040816         	2	20040813	G	8520	AEL11021M003	BEARING         			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  					ENGINE	FLAKING         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33							RL53137			ASSEMBLED THE ENGINE ACCORDING TO THE LYCOMING OVERHAUL MANUAL AND STANDARD PRACTICES.  THE ENGINE WAS PREOILED AND RUN 	IN A TEST STAND USING AEROSHELL 100W OIL.  AFTER A TWO HOUR BREAK-IN RUN WHERE ALL TEMPS AND PRESSURES WERE NORMAL THE O	IL FILTER WAS CUT OPEN AND INSPECTED.  ABOVE NORMAL AMOUNT OF METAL FLAKES WERE FOUND. IT WAS RUN ANOTHER HOUR TO CHECK 	OIL CONSUMPTION AND THE FILTER INSPECTED AGAIN. THERE WAS LESS METAL BUT STILL OF CONCERN. NORMALLY THAT IS ALL THE TEST	 CELL RUNNING WE DO IF ALL LOOKS NORMAL, BUT SINCE WE WERE STILL SEEING METAL, WE PUT IN NEW OIL AND RAN IT ANOTHER TWO 	HOURS. SINCE STILL SEEING METAL WHICH LOOKED LIKE BEARING MATERIAL WE DISASSEMBLED THE ENGINE TO FIND THE PROB.	1	H	7	1 	3O	3	O	 	1A8     	E275
2004083000098	20040830	00098	CE  	2004	8	30	20040820         	1	20040720	G	2820	6225544	CHECK VALVE     			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480*      	41527	EA  					FUEL SYSTEM	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	61JA					1286				FUEL SYSTEM CHECK VALVE PN 6-2255-44, HOUSING WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	 	1A8     	E275
2004083000131	20040830	00131	EA  	2004	8	30	20040823         	2	20040820	G	8520	77134	CAMSHAFT        			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  					ENGINE	MAKING METAL    	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33							RL53137			AFTER ENGINE O/H, THE ENGINE WAS TEST RUN 5 HOURS ON THE TEST STAND AND THEN DISASSEMBLED BECAUSE OF METAL IN OIL.  AS P	ART OF INSPECTION NOTED THAT NR 4 EXHAUST CAM LOBE APPEARED TO BE WEARING ABNORMALLY.  HAS A ROUGH SURFACE WITH SOME PIT	TING AND APPEARANCE OF METAL SMEARING. CAM FOLLOWER SHOWED BEGINNING OF DISTRESS BELIEVED TO BE CAUSED BY CAM.  THE CAMS	HAFT WAS NEW.			1	H	7	1 	3O	3	O	 	1A8     	E275
2004091700095	20040917	00095	CE  	2004	9	17	20040915         	1	20040915	G	2520	169534024601	SEAT            			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1A    	41514	EA  					CABIN	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	7638R	2908 				MA349				LOWER SEAT DEVELOPED CRACKS WHERE UPPER SEAT BACK CONTACTS.						1	L	7	1 	3O	3	O	 	A1CE    	1E10
2004110300128	20041103	00128	SO  	2004	11	3	20041024         	1	20040922	G	2410	76028	BRACKET         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ZONE 400	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	69JA					274555				ALTERNATOR BELT ADJUSTMENT BRACKET CRACKED AT THE SLOTTED END.						1	L	7	2 	3O	3	O	 	1A10    	1E4
2004050600061	20040506	00061	EA  	2004	5	6	2004F00085       	2	20040227	G	7310	LW120980100	TUBE            			BEECH 	36    	36BEECH     	1151602	CE  	LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL SYSTEM	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	7886L					E10	1719461A			THIS IS THE TUBE THAT ATTACHES FROM THE FLOW DIVIDER TO THE INJECTOR.  THE TUBE BROKE AT THE WELD ON THE END ATTACHED TO	T THE FLOW DIVIDER.  THE LACK OF SUPPORT CLAMPS ON THE LINE MAY HAVE CAUSED THE LINE TO VIBRATE AND BREAK.					1	L	7	1 	3O	3	O	 	3A15    	E14EA
2004050300226	20040503	00226	EU  	2004	5	3	2004F00101       	1	20040310	G	3340	017601	HOUSING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					SPOT LIGHT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	232LA	502  				3356				CRACKED AT DRIVE FLANGE WELD.  POSSIBLE CAUSE- AERODYNAMIC AND MECHANICAL FORCES AT DRIVE FLANGE.  RECOMMENDATION-USE OF	 STRONGER BASE MATERIAL AND STRICTER CONTROL OF WELDING PROCESS.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004051400125	20040514	00125	CE  	2004	5	14	2004F00104       	1	20040322	G	2701	100524119	CONTROL COLUMN  			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	552TP	1753 				FL281	PK301			DURING A PHASE INSPECTION A SQUEAK WAS NOTED DURING MOVEMENT OF FLIGHT CONTROL COLUMN.  INVESTIGATION REVEALED.  LOOSE R	IVETS BETWEEN THE CONTROL T COLUMN AND BEARING PLATES AT THE POINT WHERE THE CONTROL COLUMN ATTACHES TO THE AIR FRAME AN	D PIVOTS.  MFG ISSUED SB.  AC WAS INSPECTED AT THAT TIME AND FOUND AIRWORTHY.  THIS PROBLEM OCCURRED 12 HOURS AFTER COMP	LETION OF SB.  WOULD SUGGEST MFG THIS ITEM TO ALL PHASE INSP.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2004052500028	20040525	00028	SW  	2004	5	25	2004F00121       	1	20040326	G	3230	71404	LEG ASSY        			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	31276					40772				UPON LANDING, GEAR RT MLG, BROKE FLUSH AT FUSELAGE.  AIRCRAFT HAD SADDLE BLOCKS INSTALLED BY STC437SWP.  THE LANDING GEA	R BREAK, SHOW SIGNS OF INTERGRANULAR CORROSION.					1	H	7	1 	3O	3	O	NC	A759    	E274	5	N	P88614
2004063000141	20040630	00141	EA  	2004	6	30	2004F00146       	2	20040517	G	7414	M3637	POINTS          	SLICK       		PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					LT MAGNETO	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8127K				03060080	327940268				INVESTIGATION OF MAGNETO FAILURE FOUND THAT THE CONTACT ARM OF THE PRIMARY POINT SET HAD SNAPPED OFF.  THE BREAK OCCURED	 AT THE AREA WHERE THE STIFFENER FLANGES FLATEN OUT.  JUST AT THE EDGE OF THE NYLON BLOCK.  UNABLE TO DETERMINE CAUSE OF	 FAILURE. (AL05200402443)				1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004091400183	20040914	00183	EU  	2004	9	14	2004F00147       	1	20040524	G	2435		BEARING         			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					STARTER GEN	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	2QG				5834	NA0467	P91528			PILOTS NOTICED VIBRATION ASSOCIATED WITH THE NR 1 ENGINE.  TECHNICIAN LOCATED SOURCE OF VIBRATION AS NR 1 STARTER/GENERA	TOR.  THIS UNIT HAD BEEN REMOVED AND REINSTALLED TWO WEEKS PRIOR TO VIBRATION AFTER REBRUSHING BY AN OUTSIDE FACILITY.  	UNIT ACCUMULATED 70 HOURS AFTER REBRUSHING PRIOR TO FAILURE.  TECHNICIAN SUSPECTS FAILED BEARING DUE TO THE SEVERE SIDE 	PLAY IN THE STARTER/GENERATOR SHAFT, WHICH SET UP SUFFICIENT VIBRATION TO CAUSE COMPLETE FAILURE AND SEPARATION OF THE G	EARBOX TO ENGINE SUPPORT BRACKET FITTINGS ON THE GEARBOX.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
2004071200019	20040712	00019	GL  	2004	7	12	2004F00149       	1	20040522	G	3230	RGSYS1B	CONTROL SYSTEM  			AMTR  	VELITY	VELOCITYXL  	05604JM	GL  	LYC   	O540  	IO540*      	41532	EA  					MLG	MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	787SB					3RX097				DURING A NORMAL FLIGHT AND LANDING PROCEDURE, PLACED THE GEAR SWITCH IN THE DOWN POSITION WITH NO RESPONSE.  TRIED THIS 	SEVERAL TIMES STILL NO RESPONSE.  DID A MANUAL DROP OF THE GEAR AND RECEIVED GREEN GEAR DOWN AND LOCKED LIGHTS.   SET TH	E UNIT BACK TO COMPOSITE DESIGN.  COMPOSITE DESIGN FOUND A FAILED RELAY REASON NOT KNOWN.  (EA17200407757)				1	M	7	1 	3O	3	O	RT	EXPA1M71	1E4
2004071300088	20040713	00088	CE  	2004	7	13	2004F00153       	1	20040520	G	2460		ELECTRICAL SYS  			LEAR  	60    	60LEAR      	5170707	CE  										DC SYSTEM	FAILED          	A				B	A			EMER. DESCENT           	UNSCHED LANDING         			H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SW	21	54					009				TOTAL AIRCRAFT ELECTRICAL FAILURE IN FLIGHT.  PILOT DECLARED IN FLIGHT EMEGENCY AND LANDED AIRCRAFT ON DIMINISHING DC PO	WER.  (M)					2	L	7	2 	4F			RT	A10CE
2004071300142	20040713	00142	CE  	2004	7	13	2004F00154       	1	20040223	G	3260		UPLOCK          			LEAR  	60    	60LEAR      	5170707	CE  										MLG	OUT OF ADJUST   	A				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			SW	21	56					033				RAISED GEAR AND HEARD 6-10 LOUD THUMPS, AIRCRAFT YAWED RUDDER PEDALS BACK AND FORTH.  BOTH MAIN RED LIGHTS ON, THEN LIGH	TS WENT OUT AND ALL WAS NORMAL.  LOWERED GEAR, BURNED FUEL DOWN AND LANDED.  REMOVED, ADJUSTED AND REINSTALLED LT MLG UP	LOCK STRIKER PLATE.  (M)				2	L	7	2 	4F			RT	A10CE
2004091400150	20040914	00150	NM  	2004	9	14	2004F00155       	1	20040406	G	2435		BRUSHES         			GULSTM	200   	200         	4500308	NM  	PWA   	306   	PW306B      	 	NE  					STARTER GEN	WORN            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	707QS				Y20083	066				CREW REPORTED APU INOPERATIVE TROUBLESHOT SYSTEM AND FOUND VOLTAGE AVAILABLE AT STARTER GEN.  REMOVED STARTER GEN AND BR	USH COVER.  FOUND 2 OUT OF 4 BUSHES WELDED IN BRUSH HOLDERS AND BUSH WIRES BROKEN OFF.  INSULATION STRIP ON INSIDE OF BR	USH COVER WORN BURNED THROUGH.  INSTALLED REPAIRED STARTER GEN OF SAME PN IAW GAC G200 MM., CH 49-40-05, OPERATIONAL CHE	CKS GOOD.			2	L	7	2 	4F	4	F	RT	A53NM   	E35NE
2004071300152	20040713	00152	CE  	2004	7	13	2004F00156       	1	20040131	G	3233	7003974731	ACTUATOR        			CESSNA	650   	650         	2076802	CE  										NLG	FAILED          	A				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	5117					6507064				MCO - GEAR UNLOCK FLIGHT STAYED ON FAFTER TAKEOFF FROM NAPLES.  TOOK AIRPLANE TO ORLANDO FOR REPAIR.  FGC 'B' FAILED EN 	ROUTE TO ORLANDE.  NOSE LANDING GEAR ACTUATOR OUT OF ADJUSTMENT.  NR 2 FLIGHT GUIDANCE COMPUTER FAULTY.  ADUSTED NLG ACT	UATOR, PERFORMED L/G SWING PER CESSNA M/M OPS NORMAL.  REPLACED NR 2 FGC, OPS CHECK PER 650 MM 34/21/01 IS GOOD.  (M)				2	L	7	2 	4F			 	A9NM
2004092000099	20040920	00099	SO  	2004	9	20	2004F00235       	1	20040803	G	3230		DOWNLOCK        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	DIRTY           	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	87MA	12690				31444				THE RT MAIN LANDING GEAR COLLAPSED AFTER TOUCH DOWN, SUSPECT DIRTY GEARS WITH GRIT ON DOWNLOCK.  ALSO AIRCRAFT HAD BEEN 	OUT OF SERVICE FOR 5 WEEKS AND RUST HAD ACCUMULATED ON DOWN LOCK.  (EA05200405925)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004083000019	20040830	00019		2004	8	30	2004F00238       	4	20040721	G	2562	45350000999	TRANSMITTER     			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ELT	MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	21	47WP	648  				5605317				THE ELT TRANSMITTER WOULD ACTIVATE ITSELF WHILE THE AIRCRAFT WAS STATIC IN THE HANGAR.  THE UNIT WOULD ALSO SELF ACTIVAT	E WHILE SITTING ON THE BENCH.  THE ON/OFF SWITCH ON THE ELT COULD BE TURNED ON THEN BACK TO OFF AND THE ELT WOULD REACTI	VATE WITHIN A FEW MINUTES.  THERE WERE NO VISUAL DISCREPANCIES NOTED ON THE ELT UNIT.  REPLACED ELT UNIT WITH A NEW ONE.	  CONTACTED REGISTERED OWNER FOR ADDITIONAL INFORMATION.  DISCOVERED THAT THE EMERGENCY LOCATOR TRANSMITTER IS ONE OF TH	E NEW TYPE: C4062AF (AUTOMATIC FIXED) WHICH WAS PART OF THE ORIGINAL FACTORY INSTALLATION.  INDIVIDUAL STATED THAT THEY 	DID NOT TRY REPLACING THE BATTERIES, BUT OPTED FOR A COMPLETE REPLACEMENT OF THE UNIT.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004092000068	20040920	00068	EU  	2004	9	20	2004F00241       	1	20040615	G	5220	80161101	SEAL            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A6       	52043	EA  					EMERGENCY EXIT	SEPARATED       	D				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			WP	11	106SL					1070				AC CLIMBED THRU 25,000 FT,  VERY LOUD HOWL, EMANATING FROM EMERG EXIT BEHIND COPILOT SEAT.  COMMUNICATION IN AC WAS NEAR	LY IMPOSSIBLE AND AC WAS FORCED TO RETURN TO BASE.  AT 15,000 FT NOISE SUBSIDED AND AC RETURNED TO DEPARTURE.  UPON EXAM	 OF EMERGENCY EXIT, DOOR SEAL, PN 80-161101, WAS FOUND TO BE SEPARATED AT SPLICE, WHICH IS HELD TOGETHER BY SILICONE ADH	ESIVE IN BUTT END SPLICE FASHION.  WHEN EMERG EXIT IS REMOVED AND INSTALLED DURING PERIODIC INSP, SEAL SPLICE IS FORCED 	OVER LOCK PIN PAD ON LWR WINDOW FRAME, IS DEFORMED AS IT PASSES OVER PAD.  THIS TENDS TO LOOSEN SPLICE CAUSING A PRESSUR	IZATION LEAK THAT CAN BE VERY AUDIBLE.  INSTALL SEAL WITH SPLICE AT TOP OF DOOR, ELIMINATING ABUSE OF DOOR SEAL SPLICE.	1	H	7	2 	3O	3	T	RT	A59EU   	E4EA
2004083000181	20040830	00181	NE  	2004	8	30	2004F00269       	2	20040524	G	7320	8061633	FMU             			AIRBUS	320   	A320233     	3930329	EU  	IAE   	V2527 	V2527EA5    	 	NE  					NR 2 ENGINE	ERRATIC         	A				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SO	23	991LR					561	V10860			DURING TAKEOFF, AN ECAM WARNING MESSAGE, ENGINE NR 2 OVERSPEED PROTECTION FAULT CAME ON, AT LOW SPEED.  WHEN MOVING TRUS	T LEVERS TO FLX MCT POSITION ENGINE NR 1 RESPONDED NORMAL, WHILE ENGINE NR 2 REMAINED AT LOW POWER.  THE PLANE YAW TO TH	E RT AND THE TAKEOFF WAS ABORTED.  AT TGU STATION, TECHNICIANS, PERFORMED TEST ON BOTH ENGINES IAW AMM 71-00-00.  FOUND 	THE FMU NR 2 WORKING ERRATIC AND GIVING TOO MUCH FUEL FLOW.  IT WAS REPLACED AND TESTED IAW AMM 7322-52.  ALL PARAMETERS	 WERE FOUND NORMAL, AND AIRCRAFT RETURNED TO NORMAL OPERATION.  (M)		2	L	7	2 	4F	4	F	RT	A28NM   	E40NE
2004090300034	20040903	00034		2004	9	3	2004F00279       	4	20040709	G	3416	962830A1	ADC             			CESSNA	208   	208B        	2073701	CE  										NR 1	FAULTY          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	331AK					208B0739				UNIT WAS REPORTING 400 PLUS FEET OFF FROM ACTUAL.  PROGRESSIVE REPORTING ERROR OVER ONE MONTH TIME FRAME.  (M)						1	H	7	1 	3T			 	A37CE
2004091000014	20040910	00014	EA  	2004	9	10	2004F00282       	1	20040804	G	2420		DRIVE ASSY      			CNDAIR	CL600 	CL6002B16   	1900305	EA  										NR 2 ENGINE	FAILED          	H				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NE	03	601VH	2086 				5043				NR 2 GENERATOR CAME OFF LINE ON TO ROLL OUT OF SBM.  TAKEOFF WAS ABORTED BETWEEN 65-75 KTS.  GENERATOR RESET WAS SUCCESS	FUL ON TAXI BACK.  PROCEEDED TO TAKEOFF AND WAS UNEVENTFUL.  AFTER REACHING CRUISE GEN NR 2 CAME OFF LINE AGAIN.  GENERA	TOR REMAINED OFF.  CONTINUED FLIGHT TO TEB WITHOUT FURTHER INCIDENT.  REMOVED AND REPLACED INTEGRATED DRIVE GEN.  O2GA (	M)			2	L	7	2 	4F			RT	A21EA
2004091000015	20040910	00015	CE  	2004	9	10	2004F00283       	1	20040813	G	5710	622126161	FAIRING         			CESSNA	650   	650         	2076802	CE  										LT WING	DEPARTED        	A				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			SW	09	651CV					6500036				LEFT CENTER WING FAIRING PANEL DEPARTED AIRCRAFT WHILE DESCENDING THROUGH FL13 EN ROUTE FROM SAT-HOU.  NO PASSENGERS ON 	BOARD.  PILOTS REDUCED SPPED ON DESCENT PRIOR TO LANDING WHEN LOUD NOISE WAS HEARD.  (M)					2	L	7	2 	4F			 	A9NM
2004091000020	20040910	00020	NE  	2004	9	10	2004F00286       	2	20040713	G	7230	769251	DUCT            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					DIFFUSER CASE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	CFCRN		2693 			64061				DURING DISASSEMBLY OF N1 SECTION, IT WAS NOTICED THAT THERE WAS A LARGE PIECE OF MATERIAL WEDGED IN BETWEEN TWO 1ST STAG	E BLADES.  UPON FURTHER DISASSEMBLY/INVESTIGATION THE OUTLET DUCT ASSEMBLY WAS FOUND TO BE MISSING A LARGE SECTION OF TH	E OUTER DUCT APPROXIMATELY 1.5 INCHES DIAMETER WHICH WAS DETERMINED TO BE THE PIECE LODGED IN THE BLADES.  E8KL (M)TONY 	CHECK THIS			2	G	7	2 	4U	4	U	 	H4EA    	E15EA
2004091000062	20040910	00062	EU  	2004	9	10	2004F00288       	1	20040205	G	3260		SQUAT SWITCH    			BRAERO	DH125 	HS125700A   	4230170	EU  										MLG	FAILED          	A				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	11	727TA					NA0202				UPON TAKEOFF, CREW WAS UNABLE TO ENGAGE GEAR SELECT HANDLE TO RETRACT UP POSITION.  INITIAL INSPECTION OF LANDING GEAR S	YSTEM INDICATED THAT GEAR SELECT SAFETY LEVER LOCK WAS ENGAGED, INDICATING A LANDING GEAR SYSTEM MALFUNCTION. FURTHER IN	SPECTION REVEALED THE LEFT SQUAT SWITCH WAS INTERMITTENT.  REPLACED SQUAT SWITCH.  GEAR SYSTEM SWING CHECKS ACCOMPLISHED	 WITH NO PROBLEMS NOTED.  AIRCRAFT WAS RETURNED TO SERVICE.  (M)			2	L	7	2 	4F			 	A3EU
2004092800070	20040928	00070	CE  	2004	9	28	2004F00391       	1	20040826	G	3246	4040A	WHEEL           			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	SEPARATED       	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CE	07	678JS					414A0090				ON TAKEOFF, LT OB HALF OF WHEEL, TIRE AND TUBE SEPARATED FROM AC.  THE IB HALF OF WHEEL STAYED ON THE AXLE AS WELL AS TH	E AXLE NUT, BEARING CONE AND INNER RACE FOR OUTER HALF.  DUE TO HIGH SPEED AT THE TIME OF INCIDENT THE TIRE AND TUBE HAV	E NOT BEEN LOCATED.  THE OUTER WHEEEL HALF WAS LOCATED.  THE WHEEL HALVES AND REMAINING HARDWARE WERE INSPECTED.  NO EVI	DENCE WAS FOUND TO INDICATE IMPROPER ASSY.  IMPROPER INSTALLATION, OR IMPROPER HARDWARE INSTALLATION.  AT THIS TIME CAUS	E OF WHEEL SEPARATION IS UNKNOWN.  (CE07200416204)		1	L	7	2 	3O	3	O	 	A7CE    	E8CE
2004102600159	20041026	00159	CE  	2004	10	26	2004F00415       	1	20040507	G	5730	65223053	SKIN            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT WING	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	962J	7106 				5500453	PCE71393			AFTER REMOVAL OF THE LT WING DEICE BOOT, CORROSION ON THE IB WING SKIN WAS FOUND.  THE DAMAGE WAS MEASURED AND FOUND TO 	EXCEED THE MANUFACTURERS LIMITS REQUIRING WING SKIN REPLACEMENT.  THE DAMAGE WAS LIMITED TO CORROSION PITTING, NONE HAD 	PENETRATED THOUGH THE SKIN.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004022300017	20040223	00017	EA  	2004	2	23	2004FA0000013    	2	20040101	G	8520	A8268	ROD             			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  	HARTZL	HC82V	HC82V*      	GL  	PISTON ASSY	BROKEN          	B			HPFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	8242P					243496		8386		APPEARS THAT ROD (PN A8268) BROKE JUST ABOVE A921-1 ROD FORK.  SUBSEQUENT INVESTIGATION BY PROP REPAIR STATION DID NOT F	IND ANY MISALIGNMENT OF GUIDE COLLAR RODS DO NOT APPEAR TO BE BENT OR DAMAGED.  COULD NOT FIND ANY REASON FOR ROD TO FAI	L.				1	L	7	1 	3O	3	O	 	1A15    	E295	5	C	P23EA
2004020400017	20040204	00017	NE  	2004	2	4	2004FA0000020    	2	20040106	G	7314	238006015	PUMP            			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					FUEL SYSTEM	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	23			85   			180				INSTALLED OVERHAULED FUEL PUMP FROM MFG ON 4NOV03.  DURING AIRCRAFT INSPECTION 22DEC04 HAD FUEL SEEP FROM WIRES ON PUMP.						2	L	7	2 	4J	4	J	 	A10CE   	1E16
2004021700190	20040217	00190	CE  	2004	2	17	2004FA0000031    	1	20040102	G	2434		STUD            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A103	1A103TCM    	GL  	ALTERNATOR	MELTED          	D				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			SO	15	5169F				A160568	172S9152				POSITIVE TERMINAL ON ALTERNATOR MELTED. INSPECTED ALTERNATOR WIRING HARNESS FOR CORRECT ROUTING AND DAMAGE. PROBABLE CAU	SE FOR THIS MALFUNCTION OCCURRED IN THE ALTERNATOR ITSELF, AS THE POSITIVE STUD AND NUT WERE RECOVERED WITH THE NUT IN T	HE TORQUED POSITION.  ALSO THERE WAS NO EVIDENCE OF ARCING BETWEEN THE ALTERNATOR AND ADJACENT GROUNDS, (BAFFLES,ENGINE 	CASE, ECT.) REPAIRED POSITIVE WIRE, INSTALLED OVERHAULED ALTERNATOR PN 9910591-11RX, SN A-174533, AND NEW NOISE FILTER P	N S1915-3. RUNUP AND OPERATIONAL CHECK OK.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P50GL
2004021700084	20040217	00084	SO  	2004	2	17	2004FA0000032    	2	20040107	G	8520	633189	PLUG            	CONT        		CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	OIL TRANSFR	LOOSE           	D				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	23	HCBXB		73   			04322	532202			SENT CRANKSHAFT  FOR ULTRASONIC AND MAGNAFLUX INSP.  REMOVED OIL TRANSFER PLUG FROM CRANKSHAFT AS PART OF INSP.  PLUG WA	S REINSTALLED INTO CRANKSHAFT BEFORE RETURNING.  APPROX. 70 HRS AFTER REPAIR, PROP WOULD NOT CYCLE AT NORMAL RUN-UP.  WH	EN PILOT APPLIED POWER AFTER STALL, ENG OVERSPED AND GOVERNOR DID NOT CONTROL RPM.  AT TEARDOWN OIL TRANSFER PLUG WAS MI	SSING FROM CRANKSHAFT.  ONLY EXPLANATION IS THAT A LOOSE PLUG FROM CRANKSHAFT.  THIS PLUG MOVED AROUND DURING THE APPROX	. 70 HRS OF OPERATION LEAKING OIL AND CAUSING THE SLOW, LESS RESPONSIVE PROP CONTROL UNTIL IT FINALLY MOVED FAR ENOUGH O	UT OF POSITION TO NOT ROUTE ANY OIL TO THE PROP.  PLUG THEN FELL OUT AND WAS LOST IN SHIPPING ENGINE BACK.	1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL
2004022300077	20040223	00077		2004	2	23	2004FA0000033    	4	20040105	G	2562	E01	ELT             			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360A1D     	41514	EA  					CABIN	CORRODED        	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	40HU					1315				OPERATIONAL TEST OF ELT ON PRE-FLIGHT AT THE REMOTE SWITCH SHOWED THE ELT WAS NOT WORKING.  MANUALLY TURNED THE ELT ON A	T THE UNIT, STILL NOT WORKING.  REMOVED ELT AND OPENED UP THE UNIT TO DISCOVER CONDENSATION AND ELECTROLYSIS CORROSION H	AD COMPLETELY RENDERED THE UNIT USELESS. THE O-RINGS APPEARED TO BE IN GOOD SHAPE. THE ELT HAD BEEN INSPECTED AND NEW BA	TTERIES INSTALLED DURING THE 100 HR. INSPECTION ON 9/2003.  TEMPERATURES OUTSIDE HAVE BEEN IN THE -30 DEG. F RANGE AND T	HE PLANE HAD BEEN PUT INTO THE HANGAR TO WARM UP.		1	H	7	1 	3O	3	O	NC	A22NM   	E286
2004020400010	20040204	00010	SO  	2004	2	4	2004FA0000050    	1	20040110	G	3233	SAF2323	ACTUATOR        			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG	LEAKING         	E				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			GL	21	13AG	7433 	81   			347770115				DURING FLIGHT, THE LANDING GEAR WOUND NOT EXTEND, CYCLED THE GEAR SEVERAL TIMES THEN PERFORMED AN EMERGENCY EXTENSION AN	D LANDED.  THE RT MAIN GEAR ACTUATOR END CAP O-RING FAILED AND RESULTED IN THE LOSS OF ALL HYDRAULIC FLUID.					1	L	7	2 	3O			 	A7SO
2004022300097	20040223	00097	SO  	2004	2	23	2004FA0000051    	1	20040109	G	7120	824872	FASTENER        			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE MOUNT	LOOSE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	119CP	5527 				468508041				DURING A RECENT INSPECTION IT WAS NOTED THAT ALL OF THE LOCK FASTENERS THAT SECURE THE STEEL ATTACH FITTINGS TO THE AIRF	RAME FOR THE ENGINE MOUNT LOWER ATTACH POINTS WERE VERY LOOSE (COULD BE TURNED BY HAND).  ACCESS TO THE AREA MAKES IT DI	FFICULT TO INSPECT.  PROBLEM WAS CORRECTED BY INSTALLING THE NEXT SIZE UP LOCK FASTENERS.				1	L	7	1 	3O	3	O	RT	A25SO   	E8CE
2004022300098	20040223	00098	SO  	2004	2	23	2004FA0000052    	1	20040109	G	7120	824872	FITTING         			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O550  	TSIO550C    		SO  					ENGINE MOUNT	LOOSE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	135US	2751 				4608078				DURING A RECENT INSPECTION IT WAS NOTED THAT THE LOCK FASTENERS SECURING THE STEEL LOWER ENGINE MOUNT ATTACH FITTINGS, I	NBOARD AND OUTBOARD, TO THE FUSELAGE WERE EXTREMELY LOOSE. ALL OF THE LOCK FASTENERS WERE CHANGED TO THE NEXT SIZE UP. A	CCESS TO AREA MAKES IT DIFFICULT TO INSPECT.				1	L	7	1 	3O	3	O	RT	A25SO   	E5SO
2004022300084	20040223	00084	SO  	2004	2	23	2004FA0000053    	1	20040106	G	7603		THROTTLE        			PIPER 	PA28  	PA28140     	7102802	SO  										ENGINE	STUCK           	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			EA	21	32285					287525043				THE STUDENT PILOT AND FLIGHT INSTRUCTOR WERE PRACTICING POWER-OFFS STALLS WHEN THE THROTTLE BECAME STUCK AT THE IDLE POS	ITION.  DUE TO THE MECHANICAL PROBLEM, THE FLIGHT INSTRUCTOR LANDED THE AIRCRAFT IN A VACANT FIELD.  THERE WERE NO INJUR	IES TO THE PILOT OR FLIGHT INSTRUCTOR, AND THE AIRCRAFT WAS NOT DAMAGED.				1	L	7	1 	3O			 	2A13
2004022300100	20040223	00100	SO  	2004	2	23	2004FA0000054    	2	20040109	G	8530		CYLINDER        			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	39HW	65   	50   			290215	679455			ENGINE INTAKE TUBE P/N 646207 FOR THE NR 6 CYLINDER CRACKS OUT AT ITS CYLINDER FLANGE.  THIS ENGINE HAS CRACKED 3 INTAKE	 TUBES.  THE CRACKS HAVE BEEN FOUND FROM .5000 INCH LONG TO OVER 3 INCHES LONG.  THIS CAUSES AN INTAKE FUEL LEAK AND FIR	E HAZARD.  THE INTAKE MANIFOLD DOES NOT HAVE ANY SUPPORT EXCEPT FOR THE INTAKE TUBES TO THE CYLINDERS.  BELIEVE VIBRATIO	N CAUSES THE CRACKS.			1	L	7	1 	3O	3	O	RT	2A3     	E3SO
2004022300124	20040223	00124	SO  	2004	2	23	2004FA0000055    	2	20040109	G	8520	AEC648029	PISTON          	CONT        		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 2 CYLINDER	BROKEN          	C				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	23	4810N	260  			273185R	18267384	273185R			REBARRELED CYL, ECI PISTONS.  LOSS OF OIL PRESSURE, 260 STOH, 1043 SMOH.  CAUSE, BROKEN NR 2 PISTON, PARTS BLOCKING OIL 	PICKUP SCREEN.   POSSIBLE CAUSES. DEFECTIVE PISTON CASTING, DROPPED PISTON OR IMPROPERLY MACHINED NR 4 RING GROOVE, SQUA	RE CUT BOTTOM OF GROOVE.  50 PERCENT OF BOTTOM SKIRT BROKE OFF PISTON. PISTON RING BROKE INTO ABOUT 20 PIECES.				1	H	7	1 	3O	3	O	NT	3A13    	E273
2004022300125	20040223	00125	SO  	2004	2	23	2004FA0000057    	2	20040109	G	8520	AEC648029	PISTON          	CONT        		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 2 CYLINDER	BROKEN          	C				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	23	4810N	783  			273185R	18267384	273185R			ENGINE OVERHAULED.  REBARRELED CYL, ECI PISTONS.  LOSS OF OIL PRESSURE, 260 STOH, 1043 SMOH.  CAUSE, BROKEN NR 2 PISTON,	 PARTS BLOCKING OIL PICKUP SCREEN.   POSSIBLE CAUSES. DEFECTIVE PISTON CASTING, DROPPED PISTON OR IMPROPERLY MACHINED NR	 4 RING GROOVE, SQUARE CUT BOTTOM OF GROOVE.  50 PERCENT OF BOTTOM SKIRT BROKE OFF PISTON. PISTON RING BROKE INTO ABOUT 	20 PIECES.			1	H	7	1 	3O	3	O	NT	3A13    	E273
2004022300126	20040223	00126	CE  	2004	2	23	2004FA0000058    	1	20040110	G	7921	TCM639171	OIL COOLER      			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	LOOSE           	C				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			WP	23	4810N	206  	206  			18267384	273185R			8/22/2002, OIL COOLER TCM 639171.  TACH TIME NOT LOGGED. APPROX 830 SMOH.  12/1/2003 A MAJOR OIL LEAK DEVELOPED AROUND T	HE OIL COOLER AND THE NR 5 CYL PUSH ROD TUBES.  ISOLATED LEAK TO OIL COOLER GASKETS. 1036 SMOH.  DURING REMOVAL OF OIL C	OOLER BASE PLATE, IT WAS DETERMINED THAT THE ATTACHING BOLTS WERE IMPROPERLY TORQUED.  NEW GASKETS WERE INSTALLED AND CO	OLER ATTACHING BOLTS PROPERLY TORQUED.  PROBLEM CAUSED BY IMPROPERLY TORQUED ATTACHING BOLTS.			1	H	7	1 	3O	3	O	NT	3A13    	E273
2004022300130	20040223	00130	EA  	2004	2	23	2004FA0000059    	2	20040112	G	7324	2524321	FLOW DIVIDER    	BENDIX      		PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL SYSTEM	BYPASSING       	G				O				OTHER                   				G	R	J	MULTIPLE FAILURE          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			SO	07	4658J	4947 				28R30553	L481751A	7666A2		FUEL FLOW DIVIDER, TEARDOWN AND TEST OF DIVIDER SHOWED UNIT WAS BY-PASSING FUEL , WHICH INTERRUPTED FLOW OF FUEL TO ENG 	UNDER HIGH POWER SETTINGS, LEADING TO INTERRUPTION OF ENG POWER AND/OR TOTAL LOSS OF ENG POWER.  FURTHER TEAR DOWN, REVE	ALED DIAPHRAGM WAS STIFF, AN INDICATION OF LONG TIME IN SERVICE.  CONNECTING SCREW WHICH ATTACHES DIAPHRAGM TO SHAFT WAS	 LOSE, NOT TORQUED.  ESTIMATED DIAPHRAM WAS MANUFACTURED IN 1967.  AFTER TIGHTENING  ATTACHMENT SCREW TO ITS PROPER TORQ	UE, DIVIDER WAS TESTED AGAIN.  AT 2.5 POUNDS OF FUEL PRESSURE APPLIED, NO INDICATION OF FUEL DIVIDER FLOWING UNTIL 3.750	0 POUNDS OF FUEL PRESS WAS APPLIED.   1 POUND OF PRESSURE DIFFERENCE FOR FUEL FLOW WAS DUE TO STIFFNESS OF DIAPHRAGM.	1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920
2004022300159	20040223	00159	CE  	2004	2	23	2004FA0000068    	1	20040105	G	7160	AM107635FP	AIR FILTER      			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  					ENGINE	MISMANUFACTURED 	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	01	30695					17701409	L1470036A			FACTORY NEW PART- SCREEN ATTACH TABS ARE BENT 90, AND SPOT WELDED ON TO SCREEN FRAME.  WELDS DO NOT PENETRATE BASE MATER	IAL.  ATTACH TABS WORK LOOSE.  HAVE FOUND THIS CONDITION 3 TIMES.  SOME HAVE BEEN REPAIRED WITH SHEET METAL SCREWS.  TAB	S SHOULD BE RIVETED ON OR, BETTER WELDS.				1	H	7	1 	3O	3	O	 	A13CE   	E286
2004022300168	20040223	00168	EU  	2004	2	23	2004FA0000073    	1	20040113	G	1430	5321012077	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	454PS					454	PCEPR0323	HJ1674		UPON ARRIVAL OF AIRCRAFT FOR INSPECTION, IT WAS DISCOVERED THAT THE LT MLG TO GEAR ACTUATOR ATTACH BOLT WAS BROKEN OFF. 	 BOLT WAS REMOVED AND REPLACED WITH NEW BOLT SAME P/N 532.10.12.077. DEFECTIVE BOLT WAS SENT TO MFG FOR ANALYSIS.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004022300192	20040223	00192	SO  	2004	2	23	2004FA0000076    	1	20040114	G	5510	510229616	STIFFENER       			AMRGEN	AA5   	AA5B        	3960105	SO  										HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	875L	2540 				AA5B0672				CRACKS IN TWO STIFFENERS AT HORIZONTAL STABILIZER SPAR, ONE RT SIDE OF FUSELAGE ABOVE THE SPAR.  THE OTHER IN HORIZONTAL	 STIFFENER LOWER LEFT SIDE.  FOUND WHILE INSPECTING IAW SPECIAL AIRWORTHINESS INFORMATION BULLETIN NR CE-04-34.					1	L	7	1 	3O			 	A16EA
2004022300108	20040223	00108	EU  	2004	2	23	2004FA0000077    	1	20040104	G	7697	30709341	WIRE HARNESS    			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					RT ENGINE	DETERIORATED    	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CE	03	120JC	6970 	6970 			NA0247	P80195C			WHILE EN ROUTE, NOTED RT ENGINE COMPUTER AMBER WARNING LAMP BECAME ANNUNCIATED.  ALSO NOTED, INDICATED LOSS OF POWER RT 	ENGINE.  CONSULTED AND COMPLIED WITH EMERGENCY PROCEDURES WHICH INSTRUCTED TO SWITCH TO MANUAL CONTROL AND MONITOR ALL A	PPLICABLE ENGINE PARAMETERS.  IMMEDIATE NOTIFICATION TO ATC REQUESTS TO DIVERT TO DAL FOR INSPECTION AND REPAIRS.  FOLLO	WING TROUBLESHOOTING AND INSPECTION TO DETERMINE SOURCE OF DEFECT, IT WAS NOTED THAT THE RT ENGINE PT2 HARNESS WAS DEFEC	TIVE.  PARTS WERE REPLACED, ENGINE AND COMPUTER FUNCTIONS WERE TESTED, AND NO RECURRING DEFECTS WERE NOTED.		2	L	7	2 	4F	4	F	 	A3EU    	E6WE
2004022500030	20040225	00030	CE  	2004	2	25	2004FA0000079    	1	20040119	G	5544	05331341	BALANCE WEIGHT  			CESSNA	172   	172RG       	2072438	CE  										RUDDER	MISSING         	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	03	4726V	8222 				172RG0370				IT WAS NOTED THAT RUDDER BALANCE WEIGHT WAS MISSING FROM LOCATION IN TOP LE OF RUDDER. UPON INSP OF RAMP AREA, IT WAS RE	COVERED FROM TAXIWAY. RUDDER TAB AND AC WERE UNDAMAGED FROM IT DEPARTING AC, WEIGHT ASSY WAS INSPECTED TO DETERMINE CAUS	E OF DEFECT. SCREW INSERTS WERE FULLY FUNCTIONAL AND IN SERVICEABLE CONDITION. ASSY WAS RE-INSTALLED AND CHECKED FOR SEC	URITY OF ATTACHMENT.  RUDDER ASSY WAS CHECKED FOR BALANCE AND DETERMINED TO BE IN AN IMBALANCE CONDITION. DETERMINATION 	IS THAT INCORRECT HARDWARE WAS INSTALLED IN BALANCE WEIGHT ASSY OVER LONG TIME WORKED OUT. NO EXCESSIVE VIBRATION WAS NO	TED PRIOR TO OR FOLLOWING REMOVAL AND NO RECENT WORK HAD BEEN PERFORMED ON THE RUDDER, OR WEIGHT ASSY FOR SOME TIME.	1	H	7	1 	3O			 	3A17
2004022500032	20040225	00032	NM  	2004	2	25	2004FA0000080    	1	20040119	G	5711		SPAR            			UNIVAR	415   	415C        	0420302	NM  	CONT  	C85   	C8512F      	17008	SO  	MCAULY	1A90	1A90CF      	GL  	CENTER WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	93517					840	28872712	598		AD 2002-26-02 CORROSION INSPECTION: REMOVED BOTH WINGS AND BOTH FUEL TANKS. INSPECTED ENTIRE CENTER SECTION AND FOUND FO	UR QUARTER SIZED AREAS OF LIGHT CORROSION ON FWD SIDE OF FRONT CENTER SECTION SPAR. CORROSION AREAS WERE SANDED WITH 240	 GRIT SANDPAPER AND THE ENTIRE CENTER SECTION WAS CLEANED AND SPRAYED WITH CORROSION PREVENTIVE. CLEANED AND INSPECTED E	XTERIOR OF BOTH GAS TANKS AND FOUND NO CORROSION. REPLACED ONE RIVET IN TOP EDGE OF RIGHT FRONT CENTER SECTION SPAR CAP 	WITH AN OVERSIZE RIVET.  REINSTALLED BOTH WING PANELS AND BOTH FUEL TANKS. WORK PERFORMED IAW AC 43.13-1B, SB-31 REVISIO	N 1, AC 43-4A AND PATIENCE.	1	L	7	1 	3O	3	O	 	A718    	E233	5	N	P842
2004022500025	20040225	00025	EU  	2004	2	25	2004FA0000081    	1	20040104	G	7697	30709341	WIRE HARNESS    			BRAERO	DH125 	HS125700A   	4230170	EU  										RT ENGINE	DETERIORATED    	E				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CE	03	120JC	6970 				NA0247				WHILE ENROUTE, NOTED RT ENGINE AMBER WARNING LAMP BECAME ANNUNCIATED, ALSO NOTED INDICATED LOSS OF POWER RT ENGINE. CONS	ULTED OPERATORS MANUAL AND COMPLIED WITH EMERGENCY PROCEDURES WHICH INCLUDED TO SWITCH TO MANUAL CONTROL AND MONITOR ALL	 ENGINE PARAMETERS. IMMEDIATE NOTIFICATION TO ATC AND REQUESTED TO DIVERTED FOR INSPECTION. INSPECTION WAS PERFORMED AND	 FOLLOWING TROUBLESHOOTING AND INSPECTION THAT THE SOURCE OF THE DEFECTS WAS THE RT ENGINE PT2 HARNESS. PARTS WERE REPLA	CED AND PN 3070934-1 HARNESS. SYSTEM WAS OPERATIONALLY TESTED WITH NO FURTHER DEFECTS NOTED.		2	L	7	2 	4F			 	A3EU
2004022500041	20040225	00041	NM  	2004	2	25	2004FA0000088    	1	20040112	G	2720	ABC10800318	CONTROL CABLE   			AMBLP 	A150  	A150        	3850110	NM  	LYC   	O360  	IO360A1A    	41514	EA  					RUDDER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	154ZP					104				NICOPRESS FITTING FAILED ON THIS PARTICULAR CABLE.						1	B	7	2 	3O	3	O	0	SOOOO2SE	1E10
2004022300086	20040223	00086	NM  	2004	2	23	2004FA0000095    	1	20040108	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	3PD	435  	435  		0099990080	9000085				DURING ACCOMPLISHMENT OF A.D. 2002-10-05(MAIN ROTOR UPPER HUB INSPECTION)FOUND (6) OUT OF (10) UPPER FLANGE BOLT HOLES T	O BE CRACKED.  CRACKS RUN RADIALLY FROM BOLT HOLE TO INNER EDGE AS DEPICTED IN SB 900-072.  PART TOTAL TIME: 435 HRS SIN	CE NEW.  REPLACED UPPER HUB ASSY WITH NEW IAW MM.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004022500071	20040225	00071	EU  	2004	2	25	2004FA0000097    	1	20040109	G	3230	1090512431	SELECTOR VALVE  			AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20      	03013	GL  					MLG	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	1PJ					7262				LANDING GEAR WOULD NOT EXTEND.  FINALLY FORCE LANDING GEAR HANDLE DOWN GEAR EXTENDED AND LOCKED BUT STILL HAD TRANSITION	 LIGHT.  PART FAILED PRIMARILY DUE TO AGE AND USE (WEAR).					1	G	7	2 	3U	3	U	 	H7EU    	E4CE
2004012300070	20040123	00070	EU  	2004	1	23	2004FA0000101    	1	20040101	G	7920	C792A1030802	LINE            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENGINE	MISMANUFACTURED 	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	277SD	1470 				1134				DURING ROUTINE MAINTENANCE, OIL LINE B-NUT WAS LOOSENED, IT WAS NOTED THAT LINE MOVED AWAY FROM MATING CONNECTOR APPROX 	.2500 INCH.  A SPRING SCALE WAS USED TO PULL THE LINE BACK INTO PLACE, IT REQUIRED 45 LBS OF FORCE TO DO SO.  THE MFG WA	S CONTACTED, PRINT OF PART WAS OBTAINED AND PART WAS MEASURED.  (PRINT DIM: 26.1 CM, PART DIM: 25.7 CM) NEW LINES WERE O	RDERED, 2 NEW LINES WERE ALSO TOO SHORT.  THESE ARE ENGINE OIL LINES TO THE THERMAL BYPASS VALVE.			1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2004012300072	20040123	00072	EU  	2004	1	23	2004FA0000102    	1	20040101	G	7920	C792A1030802	LINE            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENG OIL	MISMANUFACTURED 	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	266SD	1470 				1133				DURING ROUTINE MAINTENANCE, OIL LINE (B NUT) WAS LOOSENED, IT WAS NOTED THAT LINE MOVED AWAY FROM MATING CONNECTOR APPRO	X. .2500 INCH.  A SPRING SCALE WAS USED TO PULL THE LINE BACK INTO PLACE, IT REQUIRED 45 LBS OF FORCE TO DO SO.  THE MAN	UFACTURER WAS CONTACTED, A PRINT OF THE PART WAS OBTAINED AND THE PART WAS MEASURED.  (PRINT DIM: 26.1 CM, PART DIM: 25.	7 CM)  NEW LINES WERE ORDERED, 2 NEW LINES WERE ALSO TOO SHORT.  THESE ARE ENGINE OIL LINES TO THE THERMAL BYPASS VALVE.			1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2004022300209	20040223	00209	CE  	2004	2	23	2004FA0000116    	1	20040115	G	3233	5201KD	BEARING         	BEECH       		BEECH 	55    	T42A        	       	CE  										MLG GEARBOX	GALLED          	G				O				OTHER                   				F	B	S	FLT CONT AFFECTED         	SMOKE/FUMES/ODORS/SPARKS  	AFFECT SYSTEMS            	LD	LANDING        	1			GL	15	221Q	6342 	2137 			TC804				DURING TRAINING FLIGHT, LANDING GEAR WOULD NOT EXTEND ELECTRICALLY OR MANUALLY (EMERGENCY EXTENSION).  AIRCRAFT LANDED G	EAR UP.  DURING INVESTIGATION, FOUND BEARING ON ACTUATOR WORM GEAR GALLED AND IN MANY PIECES.  WORM GEAR WAS THUS ALLOWE	D TO MOVE RADIALLY AND BIND THE SECTOR GEAR.  MM SECTION 15 INDICATES THAT THIS PART IS TO BE REPLACED OR OVERHAULED EVE	RY 2000 HOURS.			1	L	7	2 	3O			 	3A16
2004022300012	20040223	00012	CE  	2004	2	23	2004FA0000117    	1	20040106	G	3233	5201KD	BEARING         	BEECH       		BEECH 	55    	T42A        	       	CE  										MLG GEARBOX	GALLED          	G				O				OTHER                   				F	B		FLT CONT AFFECTED         	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			GL	15	221Q	6342 	2137 			TC804				DURING TRAINING FLIGHT, LANDING GEAR WOULD NOT EXTEND ELECTRICALLY OR MANUALLY(EMERGENCY EXTENSION).  AIRCRAFT LANDED GE	AR UP.  DURING INVESTIGATION, FOUND BEARING ON ACTUATOR WORM GEAR IN MANY PIECES THUS ALLOWING THE WORM GEAR TO BIND THE	 SECTOR GEAR AGAINST THE LANDING GEAR GEAR BOX HOUSING.  MM SECTION 15 INDICATES THAT THIS PART IS TO BE REPLACED OR OVE	RHAULED EVERY 2000 HOURS.  THIS ACTUATOR ASSEMBLY HAS 2137 HOURS ON IT SINCE LAST OVERHAUL. 6342 HOURS TOTAL TIME OVER A	 40 YEAR SPAN. 		1	L	7	2 	3O			 	3A16
2004022300118	20040223	00118	CE  	2004	2	23	2004FA0000118    	1	20040108	G	3243	05411383	MASTER CYLINDER 			CESSNA	195   	195B        	2073112	CE  										BRAKES	LEAKING         	C				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			SW	13	6850D	2420 				16026				LT MASTER CYLINDER LEAKING WHERE BRAKE PLUNGER INTERFACES WITH MASTER CYLINDER, THERE IS NO O RING SEAL AT THIS LOCATION	, FLUID LEAKS OUT DUE TO WEAR, THIS CAUSES GRADUAL LOSS OF FLUID.  ALSO LEAKAGE AT HOSE ATTACH FITTING P/N AN922-4D. HOS	E P/N AN6262-40-10 ALSO LEAKING WHERE HOSE ATTACHES TO FITTING ON MASTER CYLINDER. GRADUAL LOSS OF FLUID CAUSES BRAKE SY	STEM FAILURE. AIRCRAFT HAD SATISFACTORY BRAKE PERFORMANCE DURING PRE TAKEOFF RUN UP, AFTER APPROX ONE HOUR FLIGHT AIRCRA	FT RETURNED TO LAND AND HAD NO BRAKE ON LT SIDE, AIRCRAFT GROUND LOOPED ON LANDING.		1	H	7	1 	3R			 	A790
2004022500060	20040225	00060	CE  	2004	2	25	2004FA0000120    	1	20040119	G	5544	05331341	BALANCE WEIGHT  			CESSNA	172   	172RG       	2072438	CE  										RUDDER	MISSING         	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	03	4726V	8222 				172RG0370				RUDDER BALANCE WEIGHT WAS MISSING FROM IT'S LOCATION. UPON INSP OF RAMP AREA, MISSING WEIGHT ASSY WAS FOUND FROM TAXIWAY	. RUDDER TAB, AC WERE DETERMINED TO NOT BE DAMAGED FROM PART DEPARTING ITS LOCATION. WEIGHT ASSY WAS INSP, CAUSE OF PART	 COMING OFF AC WAS RESEARCHED. SCREW INSERTS WERE FULLY FUNCTIONAL AND IN SERVICEABLE CONDITION. ASSY WAS RE-INSTALLED A	ND INSP FOR SECURITY OF ATTACHMENT. RUDDER ASSY WAS CHECKED FOR BALANCE, DETERMINED TO BE IN A BALANCED CONDITION. POSSI	BLY INCORRECT HARDWARE WAS INSTALLED TO MOUNT WEIGHT ASSY AND WORKED LOOSE OVER TIME. NO EXCESSIVE VIBRATION WAS NOTED P	RIOR TO OR FOLLOWING THE WEIGHT ASSY BEING REMOVED FROM RUDDER, NO RECENT WORK TO THAT PART OF AC WAS PERFORMED.	1	H	7	1 	3O			 	3A17
2004022300076	20040223	00076		2004	2	23	2004FA0000122    	4	20040105	G	2562	E01	ELT             			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360A1D     	41514	EA  					CABIN	CORRODED        	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	40HU					1315				OPERATIONAL TEST OF ELT ON PRE-FLIGHT AT THE REMOTE SWITCH SHOWED THE ELT WAS NOT WORKING.  MANUALLY TURNED THE ELT ON A	T THE UNIT, STILL NOT WORKING.  REMOVED ELT AND OPENED UP THE UNIT TO DISCOVER CONDENSATION AND ELECTROLYSIS CORROSION H	AD COMPLETELY RENDERED THE UNIT USELESS. THE O-RINGS APPEARED TO BE IN GOOD SHAPE. THE ELT HAD BEEN INSPECTED AND NEW BA	TTERIES INSTALLED DURING THE 100 HR. INSPECTION ON 9/2003.  TEMPERATURES OUTSIDE HAVE BEEN IN THE -30 DEG. F RANGE AND T	HE PLANE HAD BEEN PUT INTO THE HANGAR TO WARM UP.		1	H	7	1 	3O	3	O	NC	A22NM   	E286
2004021700191	20040217	00191		2004	2	17	2004FA0000126    	4	20040102	G	2562	EBCG7	HOUSING         	EBC         																G SWITCH	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					53442G					DURING ANNUAL INSPECTION, WHILE REMOVING UNIT FROM ITS MOUNTING TRAY, THE IMPACT ACTIVATOR EBC G7 HOUSING BROKE FREE FRO	M THE BATTERY/TRANSMITTER HOUSING.  THESE TWO HOUSINGS APPEARED TO BE EPOXIED TOGETHER.  THE UNIT IS 20+ YEARS OLD, ACCO	RDING TO THE OWNER.  THE EPOXY JOINT FAILED, PERHAPS DUE TO AGE, OR PERHAPS DUE TO BEING DROPPED.  ACTUAL REASON UNKNOWN	.  THIS SUBMITTER'S OPINION IS THAT THE JOINT CONNECTION BETWEEN THE TWO HOUSINGS WITH EPOXY IS OF POOR DESIGN.  THIS SU	BMITTER BELIEVES A MECHANICAL CONNECTION WOULD BE FAR SUPERIOR.  THIS IS THE SECOND DEFECT OF THIS TYPE KNOWN TO THE SUB	MITTER.  THIS PARTICULAR UNIT REPLACED ANOTHER UNIT OF THE SAME MODEL WHICH HAD THE SAME DEFECT, ACCORDING TO THE OWNER.
2004022500087	20040225	00087	SW  	2004	2	25	2004FA0000129    	1	20040122	G	5541		SPAR            			NAMER 	T28C  	T28C        	6402509	SW  										RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	1064	2100 				610649				CRACKS FOUND ADJACENT TO UPPER HINGE BRACKET ATTACH HOLES ON RUDDER SPAR. FOUR CRACKS FOUND, EACH BETWEEN .7500 INCH AND	 1 INCH LONG. ONE WAS VISIBLE, OTHERS FOUND USING DYE PENTRANT. CRACKS CANNOT BE SEEN WITHOUT REMOVAL OF THE HINGE BRACK	ET.				1	L	7	1 	4R			RT	EXPA1L71
2004022500088	20040225	00088	SW  	2004	2	25	2004FA0000130    	1	20040122	G	5541		SPAR            			GULSTM	112   	112         	0144701	SW  										RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	1064	2100 				64				CRACKS FOUND ADJACENT TO UPPER HINGE BRACKET ATTACH HOLES ON RUDDER SPAR. FOUR CRACKS FOUND, EACH BETWEEN .7500 INCH AND	 1 INCH LONG. ONE WAS VISIBLE, OTHERS FOUND USING DYE PENTRANT. CRACKS CANNOT BE SEEN WITHOUT REMOVAL OF THE HINGE BRACK	ET.				1	L	7	1 	3O			 	A12SO
2004022500097	20040225	00097		2004	2	25	2004FA0000132    	4	20040116	G	3424	303770	INDICATOR       			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	TURN COORDINATOR	FAILED          	G				O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			WP	17	8227V		236  			28R8018085	62208651A	931655PC085		TURN COORDINATOR UNIT FAILED DURING IFR CONDITIONS.  PROBLEM SEEMS TO BE INTERMITTENT BECAUSE AFTER LANDING, UNIT WORKED	 AND CONTINUED FOR DURATION OF FLIGHT (VFR) FROM FCH TO FYI (FAT).  (WP17200402720)					1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA
2004022500120	20040225	00120		2004	2	25	2004FA0000133    	4	20040119	G	2561	KSD35PO723107	LIFE VEST       																	CELL	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE PRESERVER FAILED MFG RECOMMENDED CELL PSI TEST IAW MANUAL 25-60-7.  DOM: MARCH 1985.
2004022500121	20040225	00121		2004	2	25	2004FA0000134    	4	20040120	G	2561	KSD35PO723105	LIFE VEST       																	CELL	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE PRESERVER FAILED MFG RECOMMENDED CELL PRESSURE TEST: LIFE PRESERVER DOM: APRIL 1985.
2004021700178	20040217	00178	EA  	2004	2	17	2004FA0000137    	2	20040128	G	8530	17C21191	KEEPER          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	NR 2&3 CYLS	WORN            	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	479ER		721  			172S8942	L2709951A	UC037		DURING A ROUTINE INSPECTION, AND WHILE ACCOMPLISHING SB 388, IT WAS DISCOVERED THAT THE VALVE KEY RETAINERS (P/N-17C2119	1) ON THE EXHAUST VALVE, WERE WORN WHERE THEY CONTACT THE ROTOR CAP. THE WEAR WAS RADIAL, AND THE DEPTH WAS ESTIMATED AP	PROXIMATELY .020 INCH TO .030 INCH.  THERE WAS NO STRONG INDICATION OF WEAR ON THE ROTATOR CAP OR THE GROOVE IN THE VALV	E STEM. THESE PARTS WERE REPLACED WITH NEW PARTS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2004022500125	20040225	00125	EA  	2004	2	25	2004FA0000138    	2	20040128	G	8530	17C21191	KEEPER          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	NR 4 CYLINDER	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	930ER	5358 	981  			4496154	L54971A	AU7685		DURING A ROUTINE INSPECTION, AND WHILE ACCOMPLISHING SB 388, IT WAS DISCOVERED THAT THE VALVE KEY RETAINERS (P/N-17C2119	1) ON THE EXHAUST VALVE, WERE WORN WHERE THEY CONTACT THE ROTATOR CAP. THE WEAR WAS RADICALLY ORIENTED, AND DEPTH WAS ES	TIMATED APPROXIMATELY .020 INCH TO .030 INCH. THERE WAS NO STRONG INDICATION OF WEAR ON THE ROTATOR CAP OR THE GROOVE IN	 THE VALVE STEM. THESE PARTS WERE REPLACED WITH NEW PARTS.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004022700002	20040227	00002	SO  	2004	2	27	2004FA0000139    	1	20040109	G	2810	39824804	CAP             			PIPER 	PA34  	PA34220T    	7103420	SO  										LT FUEL CELL	LOOSE           	G				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NE	01	4142R					3449140				PILOT ENCOUNTERED LOSS OF POWER ON LT ENGINE AND MADE PRECAUTIONARY (UNSCHEDULED) LANDING.  WATER WAS FOUND IN LT TANK A	ND LT FUEL LINES. WATER WAS SUMPED OUT, ENGINE TEST RUN, AND AIRCRAFT RETURNED TO HOMEBASE.  AT HOMEBASE LT SIDE FUEL CA	P WAS FOUND TO BE A LOUSY FIT, WHICH PROBABLY ALLOWED WATER TO ENTER.  AIRCRAFT HAS LOCKING CAPS SWAPPING RT FUEL CAP TO	 LT WING MADE A SLIGHT IMPROVEMENT, BUT NOT MUCH. CAPS CA  NOT BE ADJUSTED LIKE SOME OTHERS CAN. THIS AIRCRAFT IS KEPT I	N A HEATED HANGAR.  THE CAPS APPEAR TO BE THE PROBLEM NOT THE GASKETS.		1	L	7	2 	3O			 	A7SO
2004042700047	20040427	00047		2004	4	27	2004FA0000140    	4	20040128	G	6113		SPINNER         			AMTR  	RV4   	RV4         	       	GL  	LYC   	O320  	O320E2C     	41508	EA  	SNSNCH	70C	70CM6       	EA  	PROPELLER	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	227MJ							33609K		PROPELLER DAMAGED BEYOND REPAIR DUE TO IMPROPER SPINNER INSTALLATION.						1	L	7	1 	3O	3	O	NC	EXPA1L71	E274	5	N	P28NE
2004022700082	20040227	00082	SW  	2004	2	27	2004FA0000142    	1	20040123	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A75   	A75*        	17005	SO  					WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	83899					7AC2580				AD 200-25-02-R1, INSPECTION OF WING SPARS WAS SIGNED OFF AS COMPLIANCE WITH, ON 19 AUG O1 AS A NON-REOCCURRING INSP.  DU	RING ANNUAL INSPECTION IN JAN 04, BOTH MAIN SPARS WERE FOUND TO BE CRACKED AT THE ROOT END.					1	H	7	1 	3O	3	O	 	A759    	E213
2004021700102	20040217	00102	CE  	2004	2	17	2004FA0000143    	1	20040202	G	5210	07110381	PIN             			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470*       	17026	SO  					DOOR HINGE	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	2084X	3600 				18256184				DURING ANNUAL INSPECTION.  THIS LOWER RT DOOR HINGE PIN WAS FOUND BROKEN IN 3 PLACES.  IT IS VERY SIMPLE TO DETECT, THIS	 JUST TO OPEN AND CLOSE DOOR SLOWLY AND WATCH FOR EQUAL ROTATION OF PIN.  IF ONLY ONE END TURNS THEN THE PIN MUST BE BRO	KEN.				1	H	7	1 	3O	3	O	NT	3A13    	E273
2004022700099	20040227	00099	SO  	2004	2	27	2004FA0000144    	1	20040112	G	3220	67054003	TRUNNION        			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG	CRACKED         	D			CDHS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	9253M	71   				32R8513010				NOSE TRUNNION FOUND CRACKED AT ASSIST SPRING ATTACH BOSS.  THIS WAS A NEW MFG TRUNNION WITH 16 MONTH AND 71 HOURS IN SER	VICE.  THE CRACK OCCURRED AT A POINT THAT IS NOT SUBJECT TO OPERATING STRESS.					1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004021700128	20040217	00128	CE  	2004	2	17	2004FA0000146    	1	20040201	G	5200	125083912	HINGE           			CESSNA	210   	T210J       	2073440	CE  	CONT  	O520  	IO520*      	17032	SO  					ALT AIR DOOR	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	2271R	2230 				T2100421				THE ORIGINAL HINGE MFG OF ALUMINUM WORE OUT AND DROPPED PIECES IN THE INTAKE, CAUSING DAMAGE TO THE TURBOCHARGER.  SERIO	US DAMAGE WAS AVOIDED BY A TIMELY INSPECTION.  THE NEW SUPPLIED PART IS STAINLESS STEEL WITH A HINGE PIN SECURED BY CRIM	PING.  THIS AREA IS DIFFICULT TO INSPECT ROUTINELY, AND ALL HINGES SHOULD BE CHANGED TO STEEL.				1	H	7	1 	3O	3	O	 	3A21    	E5CE
2004021700155	20040217	00155	SW  	2004	2	17	2004FA0000148    	1	20040109	G	7120	204060031015	FITTING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	4750R					30009	LEO7587			UPON OPENING PACKED FOR FITTING ASSEMBLY FOUND THREADS ON LONG SIDE OF FITTING PULLED LOOSE.  PART REJECTED BEFORE INSTA	LLATION.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA
2004021100149	20040211	00149	GL  	2004	2	11	2004FA0000149    	3	20040120	G	6110	D4170	COUNTERWEIGHT   			CESSNA	310   	310         	2074202	CE  						MCAULY	2AF34C	D2AF34C52   	GL  	PROPELLER	CRACKED         	B			L2PR	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	13	1312J				810739					PART HAD APPROX 700.00 HOURS SINCE OVERHAUL, FATIGUE CRACK APPEARS TO HAVE  ORIGINATED AT FORWARD BOLT HOLE.  PROPELLER/	ENGINE BEGAN VIBRATING IN FLIGHT DUE TO COUNTER WEIGHT SHIFTING ON FERRULE.  AIRCRAFT REDUCED POWER, LANDED AND WAS REPA	IRED BEFORE FURTHER FLIGHT.  (K)				1	L	7	2 	3O			RT	3A10    		5	C	P5EA
2004021700077	20040217	00077	NM  	2004	2	17	2004FA0000163    	1	20040204	G	6320	51003400	LINE            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					XMSN OIL	CRACKED         	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	13	902PD	1261 			0062190056	9000084				AIRCRAFT EXPERIENCED LOW TRANSMISSION OIL PRESSURE.  DURING RUN-UP AND LEAK CHECK FOUND TRANSMISSION OIL COOLER LINE P/N	 900D3409526105 TO BE LEAKING FROM UNDER STEEL BRADE.  REPLACED OIL COOLER LINE, OPS AND LEAK CHECK WERE GOOD.  CUT BACK	 STEEL BRADE ON OLD LINE TO FURTHER INVESTIGATE CAUSE AND FOUND LINE TO BE CRACKED BELLOWS.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004022700108	20040227	00108	CE  	2004	2	27	2004FA0000164    	1	20040204	G	2810	125932	FUEL CAP        			BBAVIA	8     	8KCAB       	2110612	CE  										FUEL CELL	MISINSTALLED    	B				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			WP	28	561ER	66   				9342003				FUEL TANK CAPS ARE VERY DIFFICULT TO SECURE PROPERLY.  IT IS EASY TO PUT THE CAP ON PARTIALLY.  THE FACTORY RECOMMENDS T	HE CAP GASKETS BE LUBED WITH SILICONE SPRAY.  WE ARE ALSO PUTTING ALIGNMENT MARKS ON THE CAP AND WING FOR POSITIVE ENGAG	EMENT INDICATION.				1	H	7	1 	3O			 	A21CE
2004030100071	20040301	00071	SO  	2004	3	1	2004FA0000171    	1	20040122	G	5310	45467016017	RIB             			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG WW	CORRODED        	B			C85R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	131PJ	5052 				317912030				REPORTED OCCASIONAL GEAR CYCLING PROBLEM.  INSPECTED LANDING GEAR AND FOUND RIBS (WHICH ARE IN THE LT AND RT MAIN GEAR W	HEEL WELLS) TO BE SEVERELY CORRODED.  MOUNTED ON THIS RIBS IS THE BRACKET FOR THE  UPLOCK LATCH SWITCH.  THERE WAS ENOUG	H MOVEMENT IN THE RIBS THAT SWITCH CONTACT BECAME AN ISSUE.  BOTH RIBS WERE REPLACED .  SOME OF PROBLEMS MIGHT BE CORREC	TED BY INSTALLING KIT, WHICH C/W AND CHANGED THE GEAR PUSH-PULL TUBES TO CABLES INSTEAD.  THIS WAS ALSO DONE.  REMOVED O	LD PUSH-PULL TUBES, WHICH WERE CORRODED. (NE01200402913)		1	L	7	1 	3O	3	O	RT	A20SO   	E14EA
2004021700180	20040217	00180	SO  	2004	2	17	2004FA0000172    	1	20040112	G	2810	34824804	FUEL CAP        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					LT WING	LOOSE           	B			C85R	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NE	01	4142R	620  				3449140				PILOT ENCOUNTERED LOSS OF POWER ON LT ENGINE AND MADE AN UNSCHEDULED LANDING.   WATER WAS FOUND IN LT TANK AND LT FUEL L	INES.  WATER WAS SUMPED OUT, ENG TEST RUN,  AC RETURNED TO HOMEBASE.  LT SIDE CAP WAS FOUND TO BE LOUSY FIT, PROBABLY AL	LOWED WATER TO ENTER.  SWAPPING RT FUEL CAP TO LT WING MADE A SLIGHT IMPROVEMENT, NOT MUCH.  (CAPS CAN NOT BE ADJUSTED) 	CAPS APPEAR TO BE THE PROBLEM, NOT THE GASKETS.  AC IS KEPT IN HEATED HANGAR.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004030100076	20040301	00076	CE  	2004	3	1	2004FA0000173    	1	20040122	G	3260		DOWNLOCK SWITCH 			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	17	356D					340A0745				LANDING GEAR WOULD NOT EXTEND, FOUND LANDING GEAR ACTUATOR DOWN LIMIT SWITCH STUCK IN GEAR DOWN POSITION.  PERIODIC REPL	ACEMENT OF SWITCH WOULD BE THE ONLY WAY TO PREVENT REOCURRENCE.  THE SWITCH IS A SEALED UNIT AND CANNOT BE INSPECTED INT	ERNALLY.  (GL17200402312)				1	L	7	2 	3O	3	O	 	3A25    	E8CE
2004030100116	20040301	00116	EA  	2004	3	1	2004FA0000178    	2	20040109	G	8550	LW13792	SEAL            			AMRGEN	AA1   	AA1B        	0631206	SO  	LYC   	O235  	O235C2C     	41505	EA  					ENGINE	WORN            	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	25	6291L	1446 				AA1B0091	L1121615			FOUND CRANKSHAFT SEAL PUSHED FREE FROM ITS MOUNTING AREA.  SEAL APPEARED DRY ROTTED  AND INSTALLED WITH INSUFFICIENT SEA	LANT.  INSTALLED NEW SEAS IAW SRM.  INSPECTED OIL SCREEN AND TOOK OIL SAMPLE.  NO METAL FOUND SEAL SHOULD BE INSPECTED F	OR PROPER MOUNTING EVERY 100 HOURS.				1	L	7	1 	3O	3	O	 	A11EA   	E223
2004021700105	20040217	00105	EU  	2004	2	17	2004FA0000181    	1	20040110	G	5330	1022704	SKIN PANEL      			LET   	L13   	L13BLANIK   	1360306	EU  										AFT FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6288	3076 				025520				ON INSPECTION, FOUND CRACKS .50 INCH LONG ON BOTH RT AND LT SIDES, ON BOTTOM OF STABILIZER, HOLE CUTOUTS ONE INCH AFT BU	LKHEAD N 14.  STOP DRILLED AND REPAIR WITH PLATS OF 2024T3 .050 ALUM. IAW AC.					1	K	0	0 	  			 	G24EU
2004030100121	20040301	00121	CE  	2004	3	1	2004FA0000182    	1	20040204	G	2133	40117	CHECK VALVE     			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN PRESSURE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	600JD					6500236				WHILE TROUBLESHOOTING A PRESSURIZATION PROBLEM, A CRACKED CHECK VALVE AT THE RT PRESSURE REGULATING AND CHECK VALVE ASSE	MBLY WAS FOUND.  A PIECE OF THE CHECK VALVE WAS MISSING.  THE LT SIDE WAS THEN CHECKED AND AN IDENTICAL CHECK VALVE COND	ITION WAS FOUND.  A SEARCH FOR THE MISSING PIECE WAS UNSUCCESSFUL.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004021700106	20040217	00106	CE  	2004	2	17	2004FA0000183    	1	20040204	G	2133	40117	CHECK VALVE     			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN PRESSURE	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	600JD					6500236				WHILE TROUBLESHOOTING A PRESSURIZATION PROBLEM, A CRACKED CHECK VALVE AT THE RT PRESSURE REGULATING AND CHECK VALVE ASSE	MBLY WAS FOUND.  A PIECE OF THE CHECK VALVE WAS MISSING.  THE LT SIDE WAS THEN CHECKED AND AN IDENTICAL CHECK VALVE COND	ITION WAS FOUND.  A SEARCH FOR THE MISSING PIECE WAS UNSUCCESSFUL.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004030100122	20040301	00122	CE  	2004	3	1	2004FA0000184    	1	20040204	G	2133	40117	CHECK VALVE     			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN PRESSURE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	900JD	4923 				6500213				WHILE TROUBLESHOOTING A PRESSURIZATION PROBLEM, A CRACKED CHECK VALVE AT THE RT PRESSURE REGULATING AND CHECK VALVE ASSE	MBLY WAS FOUND.  A PIECE OF THE CHECK VALVE WAS MISSING.  THE LT SIDE WAS THEN CHECKED AND AN IDENTICAL CHECK VALVE COND	ITION WAS FOUND.  A SEARCH FOR THE MISSING PIECE WAS UNSUCCESSFUL.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004030100123	20040301	00123	CE  	2004	3	1	2004FA0000185    	1	20040204	G	2133	40117	CHECK VALVE     			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN PRESSURE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	900JD	4923 				6500213				WHILE TROUBLESHOOTING A PRESSURIZATION PROBLEM, A CRACKED CHECK VALVE AT THE RT PRESSURE REGULATING AND CHECK VALVE ASSE	MBLY WAS FOUND.  A PIECE OF THE CHECK VALVE WAS MISSING.  THE LT SIDE WAS THEN CHECK AND AN IDENTICAL CHECK VALVE CONDIT	ION WAS FOUND.  A SEARCH FOR THE MISSING PIECE WAS UNSUCCESSFUL.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004030100127	20040301	00127	EA  	2004	3	1	2004FA0000186    	2	20040114	G	7414	4347	MAGNETO         			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6784V	665  				700083	L1506136A			ROUGH ENGINE ON RUNUP.  MAGNETO REMOVED AND DISASSEMBLED.  BEARING CAP ASSEMBLY NOT HELD STATIONARY IN FRAME.  RETAINING	 SCREWS AND TABS WERE FOUND TIGHT BUT NOT TIGHT ON BEARING CAP.  BEARINGS FOUND TO BE OK.  BELIEVE THAT CAP ON HOUSING W	AS MACHINED INCORRECTLY AND WAS NEVER TIGHT FROM DAY ONE.				1	L	7	1 	3O	3	O	 	2A3     	1E10
2004021700096	20040217	00096	CE  	2004	2	17	2004FA0000187    	1	20040206	G	2820	652635537	TUBE            			CESSNA	500   	550         	2076604	CE  										FUEL SYSTEM	CHAFED          	I				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	792MA	11000				5500302				COMPLETING CESSNA SB,  WE FOUND BOOST PUMP WIRING CHAFING INTO FUEL TUBE. THE TUBE WAS CHAFED BEYOND LIMITS IAW SB.  THE	RE IS POTENTIAL OF SPARKING IN THE FUEL BAY AREA IF THE BOOST PUMP WIRES SHORTED TO THE TUBE CAUSING A FIRE. THE BOOST P	UMP WIRING HAD SOME CHAFFING ON OUTSIDE SHIELDING BUT WAS IN LIMITS IAW SB.  THIS SB SHOULD BECOME AN AD TO PREVENT ANY 	CHAFFING OF BOOST PUMP WIRES IN THE FUEL BAY AREA.			1	L	7	2 	4F			 	A22CE
2004030100047	20040301	00047	SO  	2004	3	1	2004FA0000188    	1	20040206	G	2823		SELECTOR VALVE  			PIPER 	PA18  	PA18150     	7101828	SO  										FUEL SYSTEM	BROKEN          	P				D				RETURN TO BLOCK         				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			AL	03						188109055				PILOT TURNED FUEL VALVE TO CHECK FOR SMOOTH OPERATION AND DETENTS ON THE FUEL SELECTOR VALVE AS DIRECTED BY FLIGHT INSTR	UCTOR.  INSTRUCTOR HEARD (FUNNY SOUND) COMING FROM VALVE AND THE VALVE WAS SUBSEQUENTLY DETERMINED TO BE BROKEN. WHEN TH	E VALVE BROKE IT WAS STUCK BETWEEN NORMAL POSITIONS.  MAINTENANCE REMOVED THE VALVE FROM THE AIRCRAFT.  THE VALVE HAS A 	PLASTIC/SYNTHETIC INSERT THAT FUNCTIONS LIKE A BALL VALVE.  THE PLASTIC PART IS BROKEN NEAR THE TOP WHERE THE HANDLE ENG	AGES THE CONE.  THE INSTRUCTOR PILOT HAD FLOWN THE 2 PREVIOUS FLIGHTS WITHOUT ANY INDICATION OF A VALVE PROBLEM.  THIS C	OMPONENT FAILURE COULD HAVE CAUSED AN AIRCRAFT ACCIDENT IF IT HAD FAILED UNDER POWER (IN FLIGHT).	1	H	7	1 	3O			 	1A2
2004030100050	20040301	00050	CE  	2004	3	1	2004FA0000189    	1	20040206	G	5313		STRINGER        			BEECH 	200   	200BEECH    	1152920	CE  										PRESS BULKHEAD	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	553R	9597 				BB589				STRINGERS NR 8,9 ON THE RIGHT SIDE OF THE AFT PRESSURE BULKHEAD WERE FOUND CRACKED DURING COMPLIANCE OF AD 93-25-07.  CR	ACKS WERE FOUND AT THE FWD RIVET.  REPAIR KITS WERE INSTALLED IAW MANDATORY SB.					1	L	7	2 	4T			 	A24CE
2004030100083	20040301	00083	CE  	2004	3	1	2004FA0000190    	1	20040211	G	5512	04121761	SKIN            			CESSNA	150   	150B        	2071806	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100*      	GL  	HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	1163Y	3548 				15059563	30082A	36505		REMOVED HORIZONTAL STABILIZER FOR TAILCONE REPAIR.  FOUND TWO 1.5 INCH CRACKS RADIATING FROM LOWER FORWARD CORNER OF TAI	L CONE SKIN WHERE BOTTOM OF HORIZONTAL LEADING EDGE RESTS.  CRACKS PROGRESSING TOWARDS FORWARD HORIZONTAL STABILIZER MOU	NT BOLT HOLES.  APPEARS INTERFERENCE FIT BETWEEN HORIZONTAL AND TAIL CONE WAS A CONTRIBUTING FACTOR.  AREA HAD TO BE CLE	ANED TO FIND CRACK DUE TO THE ACCUMULATION OF DEBRIS AND WEAR MATERIAL.			1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918
2004030100084	20040301	00084	CE  	2004	3	1	2004FA0000191    	1	20040211	G	5512	04121761	SKIN            			CESSNA	150   	150B        	2071806	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100*      	GL  	ZONE 300	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	1163Y	3548 				15059563	30082A	36505		REMOVED HORIZONTAL STABILIZER FOR TAILCONE REPAIR.  FOUND TWO 1.5 INCH CRACKS RADIATING FROM LOWER FORWARD CORNER OF TAI	L CONE SKIN WHERE BOTTOM OF HORIZONTAL LEADING EDGE RESTS.  CRACKS PROGRESSING TOWARDS FORWARD HORIZONTAL STABILIZER MOU	NT BOLT HOLES.  APPEARS INTERFERENCE FIT BETWEEN HORIZONTAL AND TAIL CONE WAS A CONTRIBUTING FACTOR.  AREA HAD TO BE CLE	ANED TO FIND CRACK DUE TO THE ACCUMULATION OF DEBRIS AND WEAR MATERIAL.			1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918
2004030100093	20040301	00093	CE  	2004	3	1	2004FA0000192    	1	20040211	G	5521	0732000153	SPAR            	CESSNA      		CESSNA	182   	182         	2072702	CE  										LEFT ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	6465A	3053 				33265				DURING ANNUAL INSPECTION WHAT APPEARED TO BE A DENT WAS FOUND ON THE LOWER LEADING EDGE SKIN OF THE LT ELEVATOR. THIS (D	ENT) WAS CROSSED BY A CRACK. EXCESSIVE MOVEMENT OF THE ELEVATOR HORN WAS NOTED WHEN THE ELEVATOR WAS FLEXED. FURTHER INS	PECTION REVEALED A CRACK ACROSS THE SPAR 1.5 INCH OUTBOARD OF THE OUTBOARD HINGE BRACKET. THERE IS EVIDENCE ON THE TIP O	F THE ELEVATOR OF (HANGAR RASH), THAT CONTACT EVIDENTLY WAS SEVERE ENOUGH TO BUCKLE THE ELEVATOR AT THE HINGE CAUSING TH	E SPAR TO FAIL.		1	H	7	1 	3O			NT	3A13
2004030100094	20040301	00094	CE  	2004	3	1	2004FA0000193    	1	20040211	G	5521	0732000153	SPAR            	CESSNA      		CESSNA	182   	182         	2072702	CE  										LEFT ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	6465A	3053 				33265				DURING ANNUAL INSPECTION WHAT APPEARED TO BE A DENT WAS FOUND ON THE LOWER LEADING EDGE SKIN OF THE LEFT ELEVATOR. THIS 	(DENT) WAS CROSSED BY A CRACK.  EXCESSIVE MOVEMENT OF THE ELEVATOR HORN WAS NOTED WHEN THE ELEVATOR WAS FLEXED. FURTHER 	INSPECTION REVEALED A CRACK ACROSS THE SPAR 1.5 INCH OB OF THE OB HINGE BRACKET. THERE IS EVIDENCE ON THE TIP OF THE ELE	VATOR OF (HANGAR RASH), THAT CONTACT EVIDENTLY WAS SEVERE ENOUGH TO BUCKLE THE ELEVATOR AT THE HINGE CAUSING THE SPAR TO	 FAIL.		1	H	7	1 	3O			NT	3A13
2004030100003	20040301	00003	EA  	2004	3	1	2004FA0000195    	2	20040204	G	8520	61510	PLUG            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					CRANKSHAFT	LOOSE           	B				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			WP	07	35G	1144 	1144 			R18201785				DURING CLIMB OUT ENGINE RPM WOULD START CLIMBING AND THE PROP CONTROL HAD NO EFFECT ON REDUCING RPM.  DURING TROUBLESHOO	TING FOUND THE REAR CRANKSHAFT PLUG HAD COME LOOSE IN THE CRANKSHAFT ALLOWING OIL TO BYPASS BACK TO THE ENGINE SUMP.  UN	ABLE TO DETERMINE THE CAUSE FOR LOOSE PLUG.  PLUG REPLACED.				1	H	7	1 	3O	3	O	RT	3A13    	E295
2004030100049	20040301	00049	SO  	2004	3	1	2004FA0000197    	2	20040206	G	7414	641742	GEAR            								CONT  	O550  	IO550B      	 	SO  					MAGNETO DRIVE	GALLED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		500  	500  				684070			DURING ENGINE DISASSEMBLY FOR CYLINDER REPLACEMENT FOUND RT MAGNETO DRIVE GEAR DISCOLORED AND THRUST SURFACE GALLED.  MA	GNETO/ACCESSORY DRIVE ADAPTER BUSHING GALLED AND HEAT DAMAGED.										3	O			E3SO
2004030300081	20040303	00081	CE  	2004	3	3	2004FA0000198    	1	20040204	G	7921	654585	OIL COOLER      			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	732HN	465  	367  			21061527	821036R			LOWER OB FLANGE OF ENGINE OIL COOLER IS CRACKED AND LEAKING.						1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300089	20040303	00089	CE  	2004	3	3	2004FA0000199    	1	20040202	G	8120	K1250860M105	INLET           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					TURBO EXH SYS	MISMANUFACTURED 	B			CVDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	111VF					21064005	2935795			UPON INSPECTION OF NEW PARTS DEFECTS WERE FOUND WITH THE TURBO INLET COMPONENT.  DAMAGE WAS NOTED ON THE TURBOCHARGER MO	UNTING FLANGE AND THE WELDING HAD VERY POOR PENETRATION.  PART REJECTED AND SENT BACK TO O/H FACILITY.  UPON RECEIVING P	ARTS, FACILITY WAS NOT ABLE TO IDENTIFY IF PART WERE NEW OR REPAIRED DUE TO INSUFFICIENT PAPER WORK.  W/O AND INVOICE IS	 ONE AND SAME FOR NEW PARTS AND OVERHAULED PARTS.			1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300165	20040303	00165	CE  	2004	3	3	2004FA0000202    	1	20040203	G	2497		WIRE            			CESSNA	210   	210M        	2073450	CE  										ALTERNATOR	BROKEN          	B				B				EMER. DESCENT           				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			GL	15	732PY					21061677				AIRCRAFT LANDED WITH NO ELECTRICAL POWER.  REPAIRED DAMAGED ALTERNATOR PRIMARY WIRE AND RESOLDERED CAPACITOR WIRE. TOP C	HARGED BATTERY.  OPS CHECKED GOOD IAW MFG C210 AMM AND AC43-1B/2A CHAPTER 11-7.					1	H	7	1 	3O			 	3A21
2004050600017	20040506	00017	CE  	2004	5	6	2004FA0000203    	1	20040219	G	7120		BEAM            			CESSNA	421   	421C        	2076016	CE  										LT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	HBLMR					421C0111				DURING AN INSPECTION, FOUND A LOT OF LOOSE RIVETS ON THE LT ENGINE BEAM ON THE RT WING. THE DISTANCE BETWEEN SHEET METAL	 AND THE BEAM-WEBCAPS IS APPROXIMATELY 1.5 TO 2 MM.					1	L	7	2 	3O			 	A7CE
2004030300187	20040303	00187		2004	3	3	2004FA0000204    	4	20040220	G	2210	ST566	AUTOPILOT SYS   			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	COCKPIT	MALFUNCTIONED   	C				H				DEACTIVATE SYST/CIRCUITS				S			AFFECT SYSTEMS            			CR	CRUISE         	1			WP	03	210MT	201  				21064165	291649R	FP235A		ONCE ESTABLISHED IN CRUISE FLIGHT WITH ALTITUDE HOLD ENGAGED, THE S-TEC SYSTEM 55X AUTOPILOT FREQUENTLY BEGINS TO GENTLY	 PORPOISE IN PITCH.  THIS GETS PROGRESSIVELY WORSE UNTIL THE AUTOPILOT CAUSES SERIOUS PITCH EXCURSIONS OF SEVERAL HUNDRE	D FEET PER MINUTE UP AND DOWN.  THE ONLY SOLUTION FOUND IS TO DISENGAGE THE ALTITUDE HOLD MODE AND SELECT VERTICAL SPEED	 EQUALS  ZERO.  THE OTHER MAJOR PROBLEM NOTICED WITH SYSTEM 55X IS THAT DURING THE APPROACH TO LANDING, THE AUTOPILOT WI	LL PITCH DOWN ABRUPTLY WHEN THE FLAPS AND/OR GEAR ARE DEPLOYED.  THIS CAN BE ALARMING, ESPECIALLY DURING AN INSTRUMENT A	PPROACH IN INSTRUMENT METEOROLOGICAL CONDITIONS.	1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P36EA
2004030300189	20040303	00189	SO  	2004	3	3	2004FA0000205    	2	20040210	G	8530	AEC631397SN712B	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE DID NOT MEET MINIMUM SIZE DIMENSIONS AN	D VALVE SEAT MACHINING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004050600043	20040506	00043	CE  	2004	5	6	2004FA0000206    	1	20040219	G	5411		SPAR CAP        			CESSNA	421   	421C        	2076016	CE  										RT NACELLE	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	HBLMR					421C0111				DURING AN INSPECTION FOUND A LOT OF CORROSION IN THE REGION OF RT FIREWALL NACELLE AND THE THE UPPER FWD SPARCAP.  BECAU	SE OF THIS FACT HE TOOK OUT THE WING LOCKER TANK.   IN THIS REGION HE FOUND A LOT OF HEAVY CORROSION.					1	L	7	2 	3O			 	A7CE
2004030300190	20040303	00190	SO  	2004	3	3	2004FA0000207    	2	20040203	G	8530	AEC631397SN712B	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY TISN 71.2BCA AS RECEIVED.  FOUND VALVE SEAT MACHINING NOT CONCENTRIC AND EXHAUST VALVE SEAT 	DIAMETER CUT TO APPX. 1.847 INCH WHEN IT SHOULD BE APPX. 1.781 INCH ACCORDING TO PRINT DIMENSIONS IN OVERHAUL MANUAL.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300191	20040303	00191	SO  	2004	3	3	2004FA0000208    	2	20040211	G	8530	AEC631397SN712B	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER AS RECEIVED. FOUND EXHAUST VALVE GUIDE INSIDE DIAMETER TO BE BELOW MINIMUM SPECIFICATIONS, AND VA	LVE SEAT MACHINING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300196	20040303	00196	SO  	2004	3	3	2004FA0000209    	2	20040202	G	8530	AEC631397SN712	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY. AS RECEIVED.  FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG. SPECS. 	AND VALVE SEAT MACHING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300192	20040303	00192	SO  	2004	3	3	2004FA0000210    	2	20040202	G	8530	AEC631397SN712B	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY AS RECEIVED.  FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE DID NOT MEET MINIMUM MFG. DIMENSI	ONS, AND VALVE SEAT MACHINING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300193	20040303	00193	SO  	2004	3	3	2004FA0000211    	2	20040202	G	8530	AEC631397SN712	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY AS RECEIVED.  FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG SPECS., A	ND VALVE SEAT MACHINING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300194	20040303	00194	SO  	2004	3	3	2004FA0000212    	2	20040202	G	8530	AEC631397SN712	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY. AS RECEIVED.  FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG. SPECS. 	 AND VALVE SEAT MACHINING NOT CONCENTRIC.  PRE-SIZED GUIDES ARE USED ON THIS UNIT AND 5 OTHERS IN THIS BATCH INSPECTED. 	ALL UNAIRWORTHY. ALL BALL SIZED.  ALL BELL MOUTHED.				1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300195	20040303	00195	SO  	2004	3	3	2004FA0000213    	2	20040202	G	8530	AEC631397SN712	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY. AS RECEIVED.  FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MFG. MINIMUM SPECS. 	AND VALVE SEAT MACHINING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300197	20040303	00197	SO  	2004	3	3	2004FA0000214    	2	20040202	G	8530	AEC631397SN712	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							517404			INSPECTED NEW CYLINDER ASSY. AS RECEIVED.  FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG. SPECS. 	AND VALVE SEAT MACHINING NOT CONCENTRIC.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004030300093	20040303	00093	SO  	2004	3	3	2004FA0000215    	2	20040218	G	8530	655166	VALVE GUIDE     	CONT        							CONT  	O520  	IO520D      	17032	SO  					CYLINDER	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		109  	109  		Q226		293450			MFG CYLINDER (109.9HRS) DISASSEMBLED FOR REASONS NOT RELATED TO THIS REPORT. INTAKE VALVE GUIDE FOUND TO BE ONLY FINGER 	TIGHT, NO INTERFERENCE FIT. P005 FOUND STAMPED NEXT TO GUIDE.										3	O			E5CE
2004030300203	20040303	00203	SW  	2004	3	3	2004FA0000216    	1	20040217	G	3210	P1912506252M	ROLL PIN        	MOONEY      		MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  	MCAULY	3A32C	3A32C418G   	GL  	LT MLG TUBE	SHEARED         	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			DE	DESCENT        	1			GL	09	909WM	1923 			182352	290152	679307	010286		SHEAR PINS ON LT MLG TUBE ASSEMBLY FAILED.  AFT INSERT SEPARATED FROM TUBE ASSEMBLY.   LT MAIN GEAR SUBSEQUENTLY REMAINE	D UNSAFE AND RETRACTED UPON CONTACT WITH RUNWAY.  RT MLG AND NOSE GEAR WERE IN THE DOWN AND LOCKED AT TIME OF LT MLG FAI	LURE.				1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P21EA
2004030400021	20040304	00021	CE  	2004	3	4	2004FA0000217    	1	20040124	G	1430	NAS679A4	NUT             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					HORIZONTAL STAB	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	4423A	7200 				TH28				NUTS ON SEVERAL HORIZONTAL STABILIZER REAR SPAR BOLTS WERE CRACKED OR BROKEN.  NUT INSTALLED, NO NUTS HAD COME OFF AND B	OLTS WERE NOT LOOSE IN SPAR.  REPLACED NUTS AND NEW BOLTS WITH CURRENT HARDWARE.					1	L	7	2 	3O	3	O	 	3A16    	E5CE
2004030400024	20040304	00024	NE  	2004	3	4	2004FA0000218    	3	20040201	G	6110	C4784	PISTON          			PIPER 	PA 24 	PA24180     	7102402	CE  						MCAULY	C3D36C	C3D36C41582 	NE  	PROPELLER	SEIZED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03								912230		PISTON SEIZED IN HIGH PITCH POSITION TO PISTON ROD TUBE (HAD TO BE REMOVED AND PRESSED OUT OF PISTON PROP) WOULD NOT CYC	LE ON AIRCRAFT.  PISTON TUBE AND PISTON SENT TO MFG TECH REP.  SUSPECT THAT PROP GOV WORN PARTS ALLOWED METAL INTO PROP 	AND SEIZED PISTON TUBE.  MARKED AND GROOVED PARTS.				1	L	7	1 	3O			NT	1A15    		5	N	SA645NE
2004030400025	20040304	00025	WP  	2004	3	4	2004FA0000219    	1	20040113	G	6120	6873725012	O-RING          	AEROPRODTSXX		CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					TRANSFER TUBE	CUT             	B			MV1R	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	17	49	33437	603  		R242	479				AT CRUISE FLIGHT NR 1 PROP EXPERIENCED RPM FLUCTUATIONS.  AS A PRECAUTIONARY MEASURE, PROP WAS FEATHERED.  PILOT LANDED 	UNEVENTFULLY.  FOUND REGULATOR TO PROP, OIL TRANSFER TUBE, O-RING CUT.  INSTALLED NEW O-RING.  GROUND RUN FUNCTIONAL AND	 LEAK CHECKS GOOD.				2	L	7	2 	4R	4	T	 	6A6     	E282
2004030400034	20040304	00034	GL  	2004	3	4	2004FA0000221    	2	20040128	G	7323	252469211	GOVERNOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	124AE		645  			51591	CAE890804			SUSPECT HIGH END GOVERNOR FAILURE.  OVERSPEED OF N2.  (SW11200403763)						1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004030400035	20040304	00035	GL  	2004	3	4	2004FA0000222    	1	20040107	G	7160	BA111	CAGE            			CIRRUS	SR    	SR22        	2130001	GL  										AIR FILTER	FAILED          	B			NF2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03		547  								WELDS FAILED ON AIR FILTER CAGE END THAT ATTACHES END RING.						1	L	7	1 	3O			NT	A00009CH
2004030400041	20040304	00041	EA  	2004	3	4	2004FA0000223    	2	20040130	G	8520	LW16812	LIFTER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	WORN            	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	73827	1033 				17267703	L23476T			DURING A ROUTINE OIL CHANGE, WHILE COMPLYING WITH AD.  MINUTE METAL PARTICLES WERE FOUND IN THE OIL FILTER WHEN IT WAS C	UT OPEN FOR INSPECTION.  HYDRAULIC LIFTERS WERE REMOVED FOR A MORE DETAILED INSP.  THE ONE CAM LOBE FOR NR 3 AND NR 4 CY	LINDERS HAD PLATING SEVERELY WORN OFF THE TOP OF THE LOBE AND THE BASE OF THOSE TWO LIFTERS HAD SEVERE DAMAGE.  THIS ENG	INE GETS FREQUENT OIL CHANGES.  THIS ENGINE HAS THE 76T MOD INSTALLED INFORMATION WAS FORWARDED TO CERTIFICATION OFFICE.	  THIS ENGINE HAS BEEN REMOVED AND SENT FOR OVERHAUL. (NE05200404276)		1	H	7	1 	3O	3	O	NT	3A12    	E274
2004030400047	20040304	00047	SO  	2004	3	4	2004FA0000224    	1	20040210	G	5542	63396802	SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					RUDDER	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4166H	4759 	4759 			2843119				DURING PREFLIGHT, FLIGHT INSTRUCTOR FOUND THE RUDDER SKIN CRACKED.  PROBABLE CAUSE AIR FLOW OVER THE SKIN.  NO RECOMMEND	ATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	 	2A13    	E286
2004030400049	20040304	00049	SO  	2004	3	4	2004FA0000225    	1	20040206	G	2420		HOUSING         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ALTERNATOR	BROKEN          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4130W	99   			D071998	2843204	L2847836A			DURING ROUTINE INSPECTION, LOWER FRONT ATTACHMENT EAR FOR ALTERNATOR WAS FOUND TO BE CRACKED THROUGH AND BROKEN.  PROBAB	LE CAUSE IS VIBRATION, POOR MFG OR MATERIAL FAILURE.  NO RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	 	2A13    	E286
2004030400050	20040304	00050	SO  	2004	3	4	2004FA0000226    	2	20040210	G	7310	631526	DIAPHRAGM       			BEECH 	35    	M35         	1151526	CE  	CONT  	O470  	IO470C      	17026	SO  					FUEL MANIFOLD	CRACKED         	D			ET9T	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	762AA	3600 				D6168	718869C			FUEL DIAPHRAGM ON THE FUEL MANIFOLD VALVE SHOWED DETERIORATION DUE TO AGEING.  FUEL LEAKED OUT OF THE AIR BLEED HOLE ON 	THE FUEL MANIFOLD VALVE, CAUSING ENGINE FUEL FLOW PROBLEMS.  ADDITIONAL INSPECTIONS AFTER PROLONGED STORAGE.					1	L	7	1 	3O	3	O	 	3A15    	E273
2004030400044	20040304	00044		2004	3	4	2004FA0000227    	4	20040224	G	2562	AK450	ELT             			CESSNA	310   	310N        	2074234	CE  										CABIN	FAILED          	P				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	53	310VD	60   				310N0123				FAILED ANNUAL TEST ON FIRST TEST. THIS IS THE SECOND FAILURE OF THIS ELT MODEL. THE FIRST ONE FAILED AFTER FIRST YEAR AL	SO. THAT ONE WAS SERIAL NUMBER 50035. IN THIS FAILURE, BATTERIES ARE FINE, BUT THE UNIT IS DEAD ELECTRONICALLY.					1	L	7	2 	3O			 	3A10
2004030400055	20040304	00055	EU  	2004	3	4	2004FA0000229    	1	20040217	G	5330		DOPE FILM       			AVIAT 	S2B   	PITTSS2B    	2210308	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					SKIN FABRIC	DELAMINATED     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	79D	560  				5260				ALL OF THE DOPE FILM DELAMINATED FROM THE CECONITE 102 FABRIC.  AFTER SEVERAL PHONE CALLS, IT WAS DETERMINED THAT IMPROP	ER APPLICATION METHOD WAS USED.  THE RANDOLPH DOPE PROCESS REQUIRES THE USE OF RANDO PROOF PRIMER FOR THE FIRST TWO COAT	S ON CECONITE FABRIC AND THE FIBERS OF THE FABRIC MUST BE COMPLETELY ENCAPSULATED.  AFTER ADDITIONAL CALLS, IT WAS DETER	MINED THAT THE FACTORY OMMITED THE RANDO PROOF PRIMER STEP AND FAILED TO ENCAPSULATE THE FABRIC FIBERS RESULTING IN THE 	DELAMINATION OF THE DOPE FILM.  (EA17200405558)		1	Q	7	1 	3O	3	O	NC	A8SO    	1E4
2004030400070	20040304	00070	GL  	2004	3	4	2004FA0000230    	1	20040220	G	5550	2055300099	SLEEVE          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					RUDDER HINGE PIN	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	922AF					C0179				THE SLEEVE ON THE RUDDER HINGE PIN CAME LOOSE FROM ITS LOCTITED POSITION ON THE PIN AND WORKED UP INTO THE CAVITY ABOVE 	THE BEARING ON THE FIN. RUDDER HAD CONSIDERABLE PLAY AT THE TOP.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO
2004030400080	20040304	00080	GL  	2004	3	4	2004FA0000234    	3	20040206	G	6110	C50462	PLATE           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  	MCAULY	2D34C	B2D34C218   	GL  	PROP BULKHEAD	CRACKED         	D			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	35G	144  				R18201785		776893		DURING AN INSPECTION, THE BULKHEAD MOUNTING PLATES WERE FOUND CRACKED AND BROKEN AROUND THE HOLES THROUGH WHICH THE PROP	ELLER MOUNTING STUDS PASS.  THIS CONDITION IS FOUND VERY OFTEN AND THE PLATES REALLY NEED TO BE REDESIGNED TO NOT CRACK 	AS EASILY AS THEY DO NOW.  SHOULD THE CRACKS GO UNDETECTED, FAILURE OF THE SPINNER ASSEMBLY AND DAMAGE TO THE PROPELLER 	AND COWLING WILL RESULT. (WP07200403102)			1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA
2004030400081	20040304	00081	GL  	2004	3	4	2004FA0000235    	1	20040206	G	2700		STRUCTURE       			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					STABILATOR	CHAFED          	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM	28   				201023				STABILATOR RUBS AGAINST FUSELAGE SCREW.  .5 INCH GAP ON LT SIDE, .2500 INCH GAP ON RT SIDE.  (GL13200405339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400082	20040304	00082	GL  	2004	3	4	2004FA0000236    	1	20040206	G	1430		FASTENER        			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					LT AILERONS	CHAFED          	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM	28   				201023				DEFLECTION OF LT AILERON UP CAUSES IT TO RUB AGAINST AN EXPOSED RIVET.  DEFLECTION OF RT AILERON UP CAUSES IT TO RUB AGA	INST TWO EXPOSED RIVETS POSSIBLY HINDERING TRAVEL.  (GL13200405339)					1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400085	20040304	00085		2004	3	4	2004FA0000237    	4	20040206	G	6113		SPINNER         			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					PROPELLER	CHAFED          	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM					201023				PROP SPINNER RUBS AGAINST COWL, INCH LONG AND GOING THOUGH FIBERGLASS COWL.  (GL13200405339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400086	20040304	00086	GL  	2004	3	4	2004FA0000238    	1	20040206	G	5540		RUDDER          			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					VERTICAL STAB	MISINSTALLED    	B			KC5R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	13	622AM					201023				RUDDER CONTACTS FUSELAGE BEFORE REACHING STOPS.  (GL13200405339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400087	20040304	00087	GL  	2004	3	4	2004FA0000239    	1	20040206	G	3250		BUNGEE CYLINDER 			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					NLG STEERING	STIFF           	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM					201023				NOSE WHEEL STEERING BUNGEES ARE EXTREMELY STIFF, CAUSES THE RUDDER TO REQUIRE EXTREMELY HIGH RUDDER INPUTS IN FLIGHT.  P	ILOT CAN FEEL A BREAKOVER POINT.  (GL13200405339)					1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400090	20040304	00090		2004	3	4	2004FA0000240    	4	20040206	G	3454		INDICATOR       			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					VOR SYSTEM	INACCURATE      	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM	28   				201023				NEWLY INSTALLED VORS INDICATORS 6-10 DEGREES DIFFERENCE.  NAV 1 G430 W G5, NAV 2 BK W G5 KX 155.   (GL13200405339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400092	20040304	00092	GL  	2004	3	4	2004FA0000241    	1	20040206	G	5260		STEP            			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					PAX DOOR	LOOSE           	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM					201023				RT ENTRANCE STEP IS EXTREMELY LOOSE.  (GL200305339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400094	20040304	00094	GL  	2004	3	4	2004FA0000242    	1	20040206	G	2810		FUEL TANK       			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					LT WING	LEAKING         	B			KC5R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	13	622AM					201023				WITH FULL FUEL TANKS AND THE AIRCRAFT ON THE GROUND AN AMOUNT OF FUEL (.5 GALLON +) WILL DRAIN FROM THE VENT OF THE LT F	UEL TANK AFTER A FORWARD OR AFT MOVEMENT OF THE AIRCRAFT.  (GL13200305339)					1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400095	20040304	00095	GL  	2004	3	4	2004FA0000243    	1	20040206	G	5320		BRACKET         			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					CARB HEAT	BROKEN          	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM	21   				201023				CARB HEAT BRACKET BROKE LOOSE IN FLIGHT.						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400096	20040304	00096		2004	3	4	2004FA0000244    	4	20040206	G	2300		AUDIO PANEL     			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					COCKPIT	INOPERATIVE     	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM	13   				201023				STEREO INPUT INTO AIRCRAFT DOES NOT WORK.  (GL13200405339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400097	20040304	00097	GL  	2004	3	4	2004FA0000245    	1	20040206	G	1100		PLACARD         			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  					TRIM CNTRL WHEEL	MISSING         	B			KC5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	622AM	13   				201023				DOES NOT INDICATE TAKEOFF POSITION, PLACARD MISSING.  (GL13200405339)						1	L	7	1 	  	3	O		EXPA1L71	E223
2004030400089	20040304	00089	SO  	2004	3	4	2004FA0000246    	1	20040227	G	3210	400885	BOLT            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG DOWNLOCK	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	15143					28R7335027				LANDING GEAR (IN-TRANSIT) LIGHT CAME ON INTERMITTENTLY.  DURING TROUBLESHOOTING, FOUND NLG DOWNLOCK BOLT MISSING (GOES I	N METAL BLOCK ON RT LOWER ENG MOUNT STRUCTURE). THIS IS THE BOLT THE DOWNLOCK HOOK ENGAGES IF THE NLG COLLAPSES. ORDERED	 REPLACEMENT BOLT AND INSTALLED IAW MM. RETRACTION CHECK OK.  ENGINE MOUNT HAD BEEN REMOVED FOR REPAIR. WHEN IT WAS REIN	STALLED, THE PART WAS PROBABLY NOT PUT BACK ON (UP LIMIT STOP BOLT WAS ALSO MISSING). THERE IS NO WAY THE GEAR RIG CHECK	 WAS GOOD AFTER REINSTALLATION OF MOUNT.  RECOMMEND MAINTENANCE ACTIONS ON MAJOR ACFT SYSTEMS BE STRICTLY BY THE BOOK. L	UCKILY THERE WAS NOT A HARD NOSE LANDING ON THIS ACFT WHILE THE BOLT WAS MISSING.	1	L	7	1 	3O	3	O	 	2A13    	1E10
2004030400091	20040304	00091	SO  	2004	3	4	2004FA0000247    	1	20040227	G	3210	453199	BOLT            			PIPER 	PA28  	PA28R200    	7102811	SO  										NLG UPLOCK	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	15143					28R7335027				LANDING GEAR (IN-TRANSIT) LIGHT CAME ON INTERMITTENTLY.  DURING TROUBLESHOOTING, FOUND NLG UP LIMIT BOLT MISSING.  ORDER	ED REPLACEMENT BOLT AND INSTALLED IAW MM. RETRACTION CHECK OK.  ENGINE MOUNT HAD BEEN REMOVED FOR REPAIR. WHEN IT WAS RE	INSTALLED, THE PART WAS PROBABLY NOT PUT BACK ON. THERE IS NO WAY THE GEAR RIG CHECK WAS GOOD AFTER REINSTALLATION OF MO	UNT.			1	L	7	1 	3O			 	2A13
2004030400093	20040304	00093	SO  	2004	3	4	2004FA0000248    	1	20040227	G	3230	67502000	RETAINER        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					RT MLG	LOOSE           	D				E	H			ENGINE SHUTDOWN         	DEACTIVATE SYST/CIRCUITS			W			INADEQUATE Q C            			LD	LANDING        	1			SO	05	15412					347350060				ON LANDING ROLL-OUT, RIGHT MLG COLLAPSED AFT AND CAME TO REST AGAINST AFT PORTION OF WHEEL WELL.RETAINING PIN HAD SLIPPE	D OUT OF TRUNNION, ALLOWING GEAR TO COLLAPSE. THIS GEAR WAS PREVIOUSLY REMOVED FOR SPAR REPAIR. THE RETAINER BOLT WAS EI	THER LEFT OUT OR WAS NOT INSTALLED CORRECTLY. OVER A PERIOD OF TIME, THE RETAINER SLID OUT OF THE TRUNNION.  RECOMMEND P	OST MAINTENANCE INSPECTIONS BE MORE COMPLETE. THIS INCIDENT, IF IT HAD HAPPENED 20 SECONDS EARLIER, WOULD HAVE CAUSED MA	JOR STRUCTURAL DAMAGE AND POSSIBLY PERSONAL INJURY.		1	L	7	2 	3O	3	O	 	A7SO    	1E10
2004030400088	20040304	00088	SO  	2004	3	4	2004FA0000249    	1	20040227	G	2810	63901038	HOSE            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SYSTEM	MISROUTED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	15143					28R7335027				LANDING GEAR (IN-TRANSIT) LIGHT CAME ON INTERMITTENTLY.  DURING TROUBLESHOOTING, FOUND FUEL FEED LINE FROM ELECTRIC PUMP	 TO ENGINE DRIVEN PUMP MISROUTED.  HOSE WAS BEING JAMMED BETWEEN NLG TIRE AND ENGINE MOUNT WHEN GEAR IS RETRACTED.  THIS	 CAUSED NLG TO INCOMPLETELY RETRACT, CAUSING UP-LIMIT SWITCH TO BE INTERMITTENT. REROUTED HOSE AND RIGGED GEAR PER MM. O	PS CK OK.ENGINE MOUNT HAD BEEN REMOVED FOR REPAIR. WHEN IT WAS REINSTALLED, THE PART WAS PROBABLY NOT PUT BACK ON CORREC	TLY AND NOT FOUND DURING POST MAINTENANCE INSPECTION. THERE IS NO WAY THE GEAR RIG CHECK WAS GOOD AFTER REINSTALLATION O	F MOUNT.	1	L	7	1 	3O	3	O	 	2A13    	1E10
2004050600037	20040506	00037		2004	5	6	2004FA0000250    	4	20040227	G	3416	AK350	ENCODER         																	ALTITUDE	FALSE INDICATION	B			QEDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17										ENCODER TESTED AND FOUND ALTITUDE OFF. CORRECTED AND RETEST THE NEXT DAY.  RETURNED AIRCRAFT TO SERVICE. SAME DAY OF RTS	 THE MODE (C) WAS OFF. READJUSTED AND COULD NOT KEEP ENCODER FROM WANDERING AROUND.
2004050600038	20040506	00038		2004	5	6	2004FA0000251    	4	20040227	G	3416	AK350	ENCODER         																	ALTITUDE	FALSE INDICATION	B			QEDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17										ENCODER TESTED AND FOUND ALTITUDE OFF. CORREECTED AND RETEAST THE NEXT DAY.  RETURNED AIRCRAFT TO SERVICE. SAME DAY OF R	TS THE MODE (C) WAS OFF.  READJUSTED AND COULD NOT KEEP ENCODER FROM WANDERING AROUND.
2004040100160	20040401	00160		2004	4	1	2004FA0000255    	4	20040105	G	3418		STALL WARNING   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  						FROZEN          	B			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	102U	319  				C0205				WE HAVE FOUND THAT THE STALL WARNING SYSTEM ON THIS TYPE OF AIRCRAFT IS PRONE TO FREEZE UP.  MOISTURE IS INTRODUCED TO T	HE SYSTEM THROUGH THE SENSORY HOLE IN THE LEFT WING.  MOISTURE TRAVELS TO THE LOW POINT IN THE SYSTEM LOCATED IN THE AIR	CRAFT BELLY AD FREEZES UP CAUSING THE STALL WARNING SYSTEM TO NOT FUNCTION.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO
2004040100163	20040401	00163	SO  	2004	4	1	2004FA0000256    	1	20040116	G	5720	62371008	HINGE           			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					IB RT AILERON	WORN            	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	01	56264					28R7535212				RECEIVED 2 NEW HINGES FROM API WITH EXCESSIVE PLAY BETWEEN PIN AND HINGE HALFES.  DATE CODES:  12/23/03 AND 01/16/04.  H	INGES ARE MADE BY AC MFG.					1	L	7	1 	3O	3	O	 	2A13    	1E10
2004040100164	20040401	00164	EA  	2004	4	1	2004FA0000257    	2	20040101	G	8550	LW13388	GASKET          			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					OIL FILTER	FAILED          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	21	589Q					32R7780492				OIL FILTER CONVERTER PLATE GASKET (PN LW13388) PROTRUDED OUT OF THE PLATE CAUSING LOSS OF OIL AND SUBSEQUENT ENGINE SEIZ	URE.  RECOMMENDATION:  CURRENT AD ALONG WIGH LYC SI CAN LEAD INTO MECHANIC TRAP.  IF THE OIL FLITER CONVERTER PLATE KIT 	(PN LW-13904, THIS PROBLEM WOULD BE RESOLVED.  (WP21200402668)				1	L	7	1 	3O	3	O	 	A3SO    	E14EA
2004040100165	20040401	00165		2004	4	1	2004FA0000258    	4	20040105	G	6113		BULKHEAD        			CESSNA	172   	172S        	2072439	CE  						MCAULY	1A170	1A170E      	GL  	PROP SPINNER	CRACKED         	B			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	35339	162  				172S8891				DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED A .7500 INCH CRACK IN THE SPINNER BULKHEAD.  THIS CRACK WAS IN THE CORNER	 NEXT TO THE SPINNER MOUNT NUTPLATE.  SEVERAL PREVIOUS M OR D ON THIS SAME PART.					1	H	7	1 	3O			NT	3A12    		5	N	P857
2004040100166	20040401	00166	SO  	2004	4	1	2004FA0000259    	2	20040207	G	8530	SA10200A1	CYLINDER        			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4	BROKEN          	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	15	8745S		841  			15062045				AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING A FORCED LANDING AFTER TOTAL LOSS OF ENGINE POWER.  INVESTIGATION SHOWED THE C	YLINDER HAD COMPLETELY SEPARATED IN THE MIDDLE WHILE IN FLIGHT, CAUSING THE TOTAL LOSS OF POWER.					1	H	7	1 	3O	3	O	 	3A19    	E252
2004040100169	20040401	00169	CE  	2004	4	1	2004FA0000261    	1	20040201	G	3243	988200104	MASTER CYLINDER 			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LT BRAKE	INOPERATIVE     	B			EHHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	641SP	679  				172S8049				PILOT REPORTED NO RESPONSE FROM LT BRAKE PEDAL, FOUND THAT BOTTOM LT BRAKE MASTER CYLINDER ATTACHMENT CLEVIS PIN MISSING	.  LOCATED CLEVIS PIN ON UPPERSIDE OF BELLY SKIN AND COTTER PIN.  FOUND THAT COTTER PIN WAS BARELY BENT AND APPEARENTLY 	FELL OUT O F CLEVIS PIN HOLE THUS ALLOWING CLEVIS PIN TO FALL OUT OF BRAKE MASTER CYLINDER ATTACHMENT.				1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004040100170	20040401	00170	SW  	2004	4	1	2004FA0000262    	1	20040213	G	5753	190151	HINGE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C1E     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	TE FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	5060M					32679	L2722636A	CH24256		CONDUCTED ANNUAL INSPECTION ON AIRCRAFT.  FOUND BOTH LEFT AND RIGHT WING FLAP CONTROL ROD ATTACH POINTS TO CONTROL SURFA	CES TO BE CRACKED.  SPECULATE DAMAGE MAY HAVE BEEN INDUCED BY WIND ACTION AND LACK OF USE OF CONTROL SURFACE LOCK.					1	H	7	1 	3O	3	O	 	A21CE   	E286	5	C	P920
2004040100171	20040401	00171	EA  	2004	4	1	2004FA0000263    	2	20040213	G	7414		IMPULSE COUPLING			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MAGNETO	CRACKED         	B			NF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	9210H	1936 			95120132	17266017	L4305327A			ONE OF THE MAGNETO IMPULSE COUPLING PAWLS OR PAWL ATTACH RIVETS FAILED DURING TOUCH AND GO OPERATION.  THE PAWL BROKE TH	E MAGNETO MOUNTING CASTING AND DEPARTED THE AIRCRAFT.  MAGNETO WAS HANGING FROM THE ACCESSORY HOUSING WITH THE HELP OF T	HE IGNITION HARNESS.  PILOT REPORTED ONLY A SLIGHT BACKFIRE DURING CLIMB OUT WITH A LITTLE LOSS OF POWER.  MAGNETO HAD R	ECEIVED A 500 HOUR INSPECTION 260 HOURS PRIOR TO FAILURE.  IF FAILURE HAD OCCURRED DURING A LONG CROSS COUNTRY FLIGHT, T	OTAL LOSS OF OIL MAY HAVE OCCURRED.  (PILOT WOULD HAVE PROBABLY ADVANCED THROTTLE SLIGHTLY TO MAKE UP FOR ONE MAGNETO FA	ILING AND DROPPING RPM SLIGHTLY).	1	H	7	1 	3O	3	O	NT	3A12    	E274
2004040100172	20040401	00172	CE  	2004	4	1	2004FA0000264    	1	20040213	G	3244		TIRE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					NLG	OUT OF BALANCE  	D				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SW	13	64107					17265023				PILOT REPORTED NOSE WHEEL SHIMMY AFTER TOUCH DOWN AND HIGH SPEED TAXI.  INSPECTED NOSE GEAR AND NOTED SHIMMY DAMPENER AN	D STEERING COLLAR BEARING A LITTLE MORE THAN NORMAL AXIAL MOVEMENT,  TIRE STILL HAD 65 PERCENT TREAD AND SAW NO OBVIOUS 	TIRE DEFECTS.  REMOVED NOSE STRUT TO INSPECT AND RESHIM STEERING COLLAR AND SERVICE/SHIM SHIMMY DAMPENER.  WHEN THE NOSE	 STRUT LOWER FRONT HALF CLAMP WAS REMOVED, THE NOSE STRUT TUBE SPRUNG FORWARD .120 OUT OF ALIGNMENT WITH THE TOP STRUT M	OUNT.  FOUND NO DAMAGE TO AIRFRAME OR NO NOSE GEAR HISTORY.  POSSIBLE LEAVING FACTORY LIKE THIS.  INSPECTED AND RESHIMED	 NOSE GEAR ASSEMBLY AND LOWER STRUT CLAMP UP TO RELIEVE STRESS.  MOUNTED NEW TIRE, DIFFERENT BRAND.  NO SHIMMY DETECTED.	1	H	7	1 	3O	3	O	NT	3A12    	E274
2004040100174	20040401	00174	EA  	2004	4	1	2004FA0000265    	2	20040129	G	7322	30768	FLOAT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					CARBURETOR	SATURATED       	B			WIWR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	923RS				75132505	447995196	RL70177T			PILOTS REPORTED THAT UPON LANDING THE LEFT ENGINE DIED AND THAT FUEL WAS DRIPPING FROM THE COWLING.  MAINTENANCE INSPECT	ED LEFT ENGINE AND COULD NOT FIND FUEL LEAKAGE.  AIRCRAFT WAS GROUND RUN AND OPERATIVE NORMALLY EXCEPT AT IDLE.  AT IDLE	 AIRCRAFT RAN SMOOTHLY FOR ABOUT 15 TO 20 SECONDS AND THEN WOULD BEGIN TO DIE AS IF THE ENGINE WAS EXCESSIVELY RICH.  MI	XTURE WAS LEANED TO ICO AND ENGINE CONTINUED TO RUN AND THERE WAS FUEL DRIPPING FROM THE AIRBOX.  CARBURETOR WAS REMOVED	 FROM THE AIRCRAFT AND THE TOP OPENED.  THE FLOAT INSIDE THE CARBURETOR WAS FOUND TO BE HALF FILLED WITH FUEL.  MFG TO M	ONITOR PRODUCTION OF FLOATS. (WP07200410619)	1	L	7	2 	3O	3	O	 	A19S0   	E286
2004040100175	20040401	00175	CE  	2004	4	1	2004FA0000266    	1	20040218	G	3260	12700344	SAFETY SWITCH   			CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360GB     	17025	SO  	MCAULY	2AF34C	D2AF34C*    	GL  	NLG	DAMAGED         	B			LX5R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	19	1244S	5920 				33701892	236691R	780550		AFTER TAKE OFF PILOT WAS UNABLE TO RETRACT THE LANDING GEAR, THE GEAR DID SHOW DOWN AND LOCKED.  THE PLANE LANDED WITHOU	T INCIDENT.  FOUND NOSE GEAR SAFETY SWITCH BAD INTERNALLY NOT ALLOWING NOSE GEAR TO RETRACT, (SENSING STILL ON GROUND). 	IT IS SUSPECTED THAT THIS WAS NORMAL WEAR OF SWITCH.  THERE WAS NO EVIDENCE OF EXTERNAL DAMAGE.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA
2004040100176	20040401	00176	CE  	2004	4	1	2004FA0000267    	1	20040212	G	3297	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					CE1331	825800R			PILOT REPORTED THAT LANDING GEAR WOULD NOT EXTEND.  AFTER GEAR HANDLE CYCLED SIX TIMES GEAR CAME DOWN.  UPON TROUBLESHOO	TING 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
2004042700003	20040427	00003	WP  	2004	4	27	2004FA0000269    	1	20040214	G	7712	6510043	GAUGE           			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20R2    	 	GL  					TORQUE	INACCURATE      	D				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			WP	05	1726B	2231 	829  			0551E				PILOT REPORTED OPERATIONAL EXCEEDANCE DURING FLIGHT RETURNED AC TO HELIPORT.  UPON FURTHER INSPECTION AND EVALUATION IT 	WAS DETERMINED THAT THE DIAMOND J. TORQUE GAUGE WAS READING APPROX 15 LBS. LOW.  AT 60 KNOTS AIRSPEED TORQUE READING 26-	27 LBS. NORMAL READING 42 LBS.  HOVERING BEFORE TAKEOFF, FIFTY POUND RANGE NORMAL IS 65 LBS.  GROUNDED AIRCRAFT, REMOVAL	 INSTRUMENT AND TRANSDUCER SENT TO MANUFACTURE FOR TESTING AND EVALUATION.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004042300011	20040423	00011	SO  	2004	4	23	2004FA0000270    	1	20040205	G	2822		BEARING         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	BOOST PUMP	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	200HM				2AV3	32R7680025	RL2471148A	CH34707		CIRCUIT BREAKER POPPED DUE TO FUEL PUMP ELECTRICAL DRAW ON SYSTEM HIGH RESISTANCE.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920
2004042300012	20040423	00012	SW  	2004	4	23	2004FA0000271    	1	20040219	G	6720	407340334101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					T/R CONTROL	SEIZED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	601MT	843  				53428				BEARING SEIZED DURING TRAINING FLIGHT, RESULTING IN D/S FAILURE AND LOSS OF T/R CONTROL ALLOWING THE TAIL ROTOR BLADES T	O STRIKE TAILBOOM.  (WP17200403114)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004042700007	20040427	00007	NE  	2004	4	27	2004FA0000272    	2	20040213	G	7310	0301007710	PIPE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					LT FUEL INJECTOR	CRACKED         	D				O				OTHER                   				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			SW	15	448AE	704  				3210	9639			DURING ENGINE START AFTER CHANGING THE START DRAIN VALVE, LT FUEL INJECTOR PIPE WAS SPRAYING FUEL AT INJECTOR FITTING.  	INSPECTION OF PIPE REVEALED A CACK AT THE TOP OF THE FLARE ON THE PIPE.  CAUSE OF CRACK APPEARS TO BE FROM THE FLARE NOT	 BEING CENTERED ON THE LINE DURING MANUFACTURE.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004042700008	20040427	00008	CE  	2004	4	27	2004FA0000274    	1	20040217	G	3220	5082020517	DRAG BRACE      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3A     	NE  	NLG	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	842E					UE336				THE LOWER BOLT WAS SEVERELY CORRODED IN PLACE REQUIRING IT TO BE DRIVEN OUT FOR REPLACEMENT.  THIS BOLT, CENTER DRAG BRA	CE ASSY PIVOT, IS LUBRICATED ON BOTH ENDS VIA THRU BOLT GREASE PROVISIONS.  THE CENTER PORTION HAS NO PROVISION FOR GREA	SE SINCE THIS AREA IS NON ROTATING.  THERE IS NO REQUIREMENT TO REMOVE THIS BOLT UNTIL THE 5 YEAR OVERHAUL BY WHICH TIME	 THE BOLT AND DRAG BRACE HAVE CORRODED TO THE POINT OF REQUIRING REPLACEMENT.			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE
2004042700011	20040427	00011	SO  	2004	4	27	2004FA0000275    	1	20040227	G	3240	D2113	BRAKE ASSY      			PIPER 	J3    	J3C65       	7100510	SO  	CONT  	A65   	A65*        	17003	SO  					RT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	25WF					5671				AFTER DISASSEMBLY OF THE RT WHEEL AND BRAKE COMPONENTS FOR INSPECTION, ONE OF SIX BRAKE BLOCK (NR B27-59-D) WAS FOUND TO	 BE BROKEN, AND ONE OF SIX SPRING RETAINERS (NR R21-35) WAS FOUND TO BE BROKEN, AND LOOSE.  THIS CLIP (RETAINER) MAY HAV	E JAMMED UNDER A BRAKE BLOCK AND CAUSED THE RT WHEEL TO DRAG EXCESSIVELY ENOUGH TO CAUSE LOSS OF CONTROL DURING THE LAND	ING ROLLOUT.  ACTUAL TIME OF SERVICE FOR COMPONENTS ARE UNKNOWN.			1	H	7	1 	3O	3	O	 	A691    	E205
2004042700012	20040427	00012	SO  	2004	4	27	2004FA0000276    	1	20040224	G	2424	68804007	VOLT REGULATOR  			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360C1F     	41514	EA  					LT KICK PANEL	FAILED          	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	07	4188T	1    				2843124				ALTERNATOR INOPERATIVE LIGHT CAME ON DURING GROUND RUN UP.  TROUBLESHOOT SYSTEM AND FOUND NO OUTPUT VOLTAGE TO THE FIELD	 WIRE.  PROBABLE CAUSE REGULATOR FAILED INTERNALLY, NO RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	 	2A13    	E286
2004042300016	20040423	00016	SO  	2004	4	23	2004FA0000277    	2	20040224	G	8530		CYLINDER        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					ENGINE	LEAKING         	B			FFKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	1063X	1058 	394  			347570198	807611R			VALVE COVER GASKETS ON RT ENGINE WERE SEEPING.  PROCEEDED TO CHANGE GASKETS ON NR 1 CYLINDER AND DISCOVERED THE LOCKING 	SAFETY FOR THE NUTS ON THE VALVE ROCKER ARM WERE NOT BENT TO SECURE THE NUT FROM BACKING OFF.  INSPECTED ALL 6 CYLINDERS	 AND FOUND ALL SIX TO BE IN THE SAME CONDITION.  CHECKED TORQUE ON THE NUTS AND BENT LOCK TANGS.  NO FURTHER ACTION WAS 	REQUIRED.  AFTER REVIEW OF ENGINE LOG BOOK, THIS ENGINE WAS DISASSEMBLED IN APRIL OF 2003 FOR A PROP STRIKE.  SUSPECT TH	IS TO BE AN ISOLATED INCIDENT.		1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004042700043	20040427	00043	EA  	2004	4	27	2004FA0000278    	2	20040223	G	8520	LW11750	CONNECTING ROD  			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					ENGINE	BROKEN          	G				A				UNSCHED LANDING         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CR	CRUISE         	1			GL	03	3370W	6526 	1381 			32216	L1034040			WHILE IN CRUISE FLIGHT, ENGINE STARTED TO RUN ROUGH, CATASTROPHIC ENGINE FAILURE OCCURED.  PILOT MADE AN EMERGENCY LANDI	NG, MINOR DAMAGE TO AIRCRAFT.  INSPECTION  OF FAILED ENGINE REVIELD A BROKEN NR 1, (ONE) CONNECTING ROD.					1	L	7	1 	3O	3	O	 	A3SO    	E295
2004042200133	20040422	00133	EU  	2004	4	22	2004FA0000280    	1	20040226	G	6320	7052A3652038	PLUG            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					GEARBOX	LOOSE           	D				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SW	17	1240W					1240				PILOT STARTED ENGINE, COMPLETED CHECKLIST AND (BEEPS) IN HEADSET AND VISUAL WARNING ON CAUTION PANEL OF MAIN GEAR BOX (L	OW OIL PRESSURE).  SHUT DOWN ENGINE AND OPENED COWL, TRANSMISSION FILLED WAS COVERING BOTH ENGINE DECK AND TRANSMISSION 	DECK.  DISCOVERED THAT THE BLANKING PLUG HAD COME LOOSE FROM TRANS INPUT FLANGE CAUSING LOSS OF TRANS FLUID.  THIS (LOOS	E BLANKING PLUG) ADDRESSED IN ALERT SB 63-003, WHEN THIS EVENT HAPPENS IT IS NOT JUST A SMALL LEAK WITH MINOR CONSEQUENC	ES, BUT A MAJOR LEAK, EMPTYING THE TRANSMISSION WITHIN A SHORT PERIOD CAUSING A POWER REDUCTION IAW FLIGHT MANUAL, A RUN	 ON LANDING, OR POSSIBLE CRASH.	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2004032200111	20040322	00111	CE  	2004	3	22	2004FA0000282    	1	20040315	G	3244	178K235	TIRE            			LEAR  	35    	35A         	5170602	CE  										MLG	FAILED          	C				O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			SO	07	35SM					419				TREAD ON RIGHT MAIN LANDING GEAR OUTBOARD TIRE SEPARATED ON TAKEOFF.  THE TIRE WAS INSTALLED ON FEBRUARY 8, 2002.  AT TH	AT TIME THE AIRCRAFT TOTAL TIME WAS 3683.3  ON MARCH 7, 2004 THE TREAD SEPARATED, AT THE TIME OF SEPARATION THE AIRCRAFT	 TOTAL TIME WAS 3889.				2	L	7	2 	4F			 	A10CE
2004050300203	20040503	00203	CE  	2004	5	3	2004FA0000284    	1	20040303	G	3230	0541153	U BOLT          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300*       	17022	SO  					LT GEAR LEG	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	5705R	3600 				17253359				FOUND U BOLT ON LT MAIN GEAR SHEARED IN THREAD AREA UNDER NUT.  PROBABLY NUT WAS OVERTORQUED.						1	H	7	1 	3O	3	O	NT	3A12    	E253
2004050400051	20040504	00051		2004	5	4	2004FA0000285    	4	20040316	G	2561	GA12P0201	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED.  MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-13.  DOM: JULY 1980.
2004050300204	20040503	00204	EU  	2004	5	3	2004FA0000286    	1	20040128	G	6321	3637GR85	ROD END         			AGUSTA	A109  	A109E       	0260119	EU  										ROTOR BRAKE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	109DU					11503				ON SHUTDOWN A BUMP WAS FELT WHEN ENGINES WERE SET TO IDLE, SHUTDOWN AND WHEN ROTOR BRAKE WAS APPLIED.  ON POST FLIGHT BR	OKEN DAMPER ROD END WAS FOUND.  PROBABLE CAUSE WAS POSSIBLE MATERIAL DEFECT.  AD2003-26-04 DAMPER ROD END INSPECTION ADD	RESSES THIS PROBLEM.				1	G	7	2 	3U			RT	H7EU
2004051000043	20040510	00043	SO  	2004	5	10	2004FA0000287    	1	20040219	G	2701	20965	CONTROL WHEEL   			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					PILOT	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	35	752CF	5839 				30592				A CRACK WAS FOUND IN THE CO-PILOT CONTROL WHEEL WHEN IT WAS REMOVED.  THE BOTTOM OF THE WHEEL FROM FRONT TO REAR THROUGH	 THE PIN HOLE.  THIS CRACK IS NOT VISABLE FROM THE OUTSIDE.					1	L	7	2 	3O	3	O	 	A1EA    	1E12
2004050600057	20040506	00057	EA  	2004	5	6	2004FA0000289    	2	20040301	G	7324	2526388	DIAPHRAGM       								LYC   	O540  	IO540*      	41532	EA  					FUEL DIVIDER	IMPROPER        	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										MATERIAL TOO THIN OR TOO SOFT.  WHEN TORQUING RETAINING SCREW MATERIAL SQUEEZES OUT WITH NR 5 TORQUE.  FUEL FLOW DIVIDER	, BENDIX.										3	O			1E4
2004042200186	20040422	00186	EA  	2004	4	22	2004FA0000290    	2	20040315	G	7414		COIL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MAGNETO	INOPERATIVE     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	712MA				G03JA028R	317405217	L55868A	DJ8171A		WEAK COIL, SUSPECT BREAK DOWN IN COIL.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004050600078	20040506	00078	CE  	2004	5	6	2004FA0000291    	1	20040318	G	5312	05530315	FIREWALL        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	FUSELAGE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	98528	500  				17280605	L769436A	R1152		LOWER FIREWALL NUMEROUS CRACKS IN LOWER LEFT SIDE ZONE, 124, RADIATING FROM LOWER BATTERY MOUNT AND COWL MOUNT BRACKETS.	  THIS IS THE THIRD FIREWALL THAT DEVELOPED CRACKS IN THE SAME AREA.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004050300169	20040503	00169	SO  	2004	5	3	2004FA0000292    	2	20040305	G	8530	24077	RETAINER        			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					CYLINDER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	2650U					17250250	2513770R			FOUND UPPER VALVE RETAINER ABOUT 09 PERCENT WORN THROUGH BY OUTER SPRING (PN 625958) BUT HAD NOT FAILED YET.  PN 24077 U	PPER VALVE SPRING RETAINER.					1	H	7	1 	3O	3	O	NT	3A12    	E253
2004050600080	20040506	00080	SO  	2004	5	6	2004FA0000293    	2	20040305	G	8530		RETAINER        			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	WORN            	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	08	2650U					17250250	2513770R			FOUND PN 24077, UPPER VALVE SPRING RETAINER WORN OUT ALLOWING VALVE SPRING TO BYPASS IT.  CAUSED LOSS OF STATIC RPM AND 	SOME ROUGHNESS OCCASIONALLY.					1	H	7	1 	3O	3	O	NT	3A12    	E253
2004050600062	20040506	00062	CE  	2004	5	6	2004FA0000295    	1	20040127	G	2842	58380019	SENSOR          			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520*      	17032	SO  					FUEL TANK	FAULTY          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	4000W					TE1004				FLOAT DOES NOT BRING ARM TO FULL UP STOP WHEN SUBMERGED.  IT WILL COME UP TO APPROX .7500 TO .8750 OF ITS TRAVEL.  TAPPI	NG ON THE HOUSING WILL EVENTUALLY BRING IT TO THE UP STOP.  THIS, IAW MFG, DOES NOT MEET THEIR SPECIFICATIONS.  THE FLOA	T APPEARS TO NOT HAVE ENOUGH BUOYANCY.  FOUR (4) OF THESE TRANSMITTERS WERE TRIED, WITH NO FAVORABLE RESULTS.				1	L	7	2 	3O	3	O	 	3A16    	E5CE
2004042200125	20040422	00125	CE  	2004	4	22	2004FA0000296    	1	20040325	G	5523	1695240761	ROD             			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360*       	41514	EA  					TRIM TAB	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	24652					M1430				DURING ANNUAL INSPECTION THE TRIM TAB ROD WAS FOUND TO HAVE RUST ON IT.  WHILE CLEANING THE PART, A HOLE WAS FOUND AT TH	E MID POINT OF THE ROD AND MOISTURE(WATER) WAS FOUND INSIDE.  IT APPEARS THIS ROD IS RUSTING FORM THE INSIDE OUT.  THIS 	UNIT SHOULD BE TAKEN APART, INSPECTED, CLEANED, PAINTED INSIDE AND OUT AND REASSEMBLED TO ASURE THE AIRCRAFT HAS A SERVI	CEABLE PART.  (GL092004040017)			1	L	7	1 	3O	3	O	 	A1CE    	E286
2004050600068	20040506	00068		2004	5	6	2004FA0000297    	4	20040206	G	3418		DETECTOR        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					STALL WARNING	INOPERATIVE     	D				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	27	421ZM					421C1058				THIS NEWLY OVERHAULED DETECTOR WAS INSTALLED AND OPS CHECKED AFTER A COUPLE OF CHECKS THE STALL HORN WILL STAY ON.  RETU	RNED UNIT FOR ANOTHER O/HED DETECTOR.  THIS ABOUT SECOND AIRCRAFT I WENT THROUGH THIS WITH (ORDERING DETECTORS UNTIL I G	ET ONE THAT WORKED.  NEED BETTER QC).				1	L	7	2 	3O	3	O	 	A7CE    	E7CE
2004042200148	20040422	00148	CE  	2004	4	22	2004FA0000298    	1	20040315	G	5312	07126167	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					AFT FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	20844	2890 				18261251				DURING COMPLIANCE WITH AD72-07-09 REFERENCED BUKHEAD WAS FOUND CRACKED PART REPLACED WITH NEW.  SUSPECT FAILURE OCCURRED	 DUE TO AGE.					1	H	7	1 	3O	3	O	NT	TA13    	E273
2004042200181	20040422	00181		2004	4	22	2004FA0000300    	4	20040308	G	2210		BRIDAL CABLE    			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360B1E    	41514	EA  					ROLL SERVO	WORN            	B			EHHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	642SP	462  				172S8050				ROLL SERVO BRIDLE CABLE WAS IMPROPERLY INSTALLED.  TOP PORTION OF CABLE WAS WRAPPED AROUND PRIMARY AILERON CABLE, CAUSIN	G BRIDLE CABLE TO CHAFE AGAINST A PULLEY FLANGE.  INSTALLATION OF CABLE ASSEMBLY OCCURRED AT THE FACTORY AND HAS NOT BEE	N REPLACED SINCE AIRCRAFT WAS MANUFACTURED.  REPAIRED BY REMOVING BRIDLE CABLE AND INSTALLING CABLE CORRECTLY.  (EA17200	405907)			1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004050300141	20040503	00141	NM  	2004	5	3	2004FA0000301    	1	20040326	G	2530	BS0063	COUPLER         			BOEING	717   	717200      	1383700	NM  										COFFEEMAKER	INOPERATIVE     	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	15					02120207					OPTO COUPLER (MOD-16) INSTALLED BY MFG IS MISWIRED, CAUSING OVER TEMP PROTECTION CIRCUIT TO BECOME INOPERATIVE.						2	L	7	2 	4F			TR	A6WE
2004050600042	20040506	00042	CE  	2004	5	6	2004FA0000302    	1	20040325	G	3210	101810505	STOP            			BEECH 	B300  	B300B350C   	       	CE  										DRAG LEG STOP	MISINSTALLED    	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	07										FOUND DRAG LEG STOPS INSTALLED UPSIDE DOWN. STOPS CAUSED DAMAGE TO THE UPPER DRAG LEG. UPPER DRAG LEG CANNOT HAVE ANY DA	MAGE IAW THE COMPONENT MM.   NO PREVIOUS MAINTENANCE PERFORMED ON THE LANDING GEAR. SUSPECT AIRCRAFT WERE DELIVERED WITH	 THIS PROBLEM.				2	L	7	2 	4T			RT	A24CE
2004051000040	20040510	00040	EA  	2004	5	10	2004FA0000303    	2	20040402	G	7314	200F5003	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	350PC					318152006				DURING ENGINE 100 HOUR INSPECTION AND SERVICE FOUND THAT THE ENGINE DRIVEN FUEL PUMP LEAKING FUEL FROM THE REGULATOR HOU	SING.  (SO05200407947)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004042200160	20040422	00160	GL  	2004	4	22	2004FA0000304    	3	20040322	G	6114	D4883	HUB             	MCAULY      												MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER	CRACKED         	B			L2PR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	13					740453					PROPELLER WAS LEAKING RED DYE FROM HUB, PROP WAS DISASSEMBLED FOR RESEAL AND INSPECTION, CRACK WAS NOTED DURING VISUAL I	NSPECTION AND CONFIRMED BY EDDY CURRENT.  PROBABLE CAUSE FOR CRACK IS FATIGUE FAILURE, RED DYE/ OIL IS PLACED INSIDE HUB	 TO DETECT POSSIBLE CRACKS BEFORE CATASTROPHIC FAILURE (AD 91-15-04), MANY OWNER/OPERATORS ARE NOT AWARE OF THE SIGNIFIC	ANCES OF THESE LEAKS AND IGNORE THEM.													5	C	P5EA
2004050300209	20040503	00209	EA  	2004	5	3	2004FA0000305    	2	20040407	G	8520	SL13521	ROD BEARING     			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					NR 6 POSITION	DELAMINATED     	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03							L1034040			ENGINE EXPERIENCED FAILURE OF CONNECTING ROD BOLT, PN 74644 OR  DELAMINATION OF CONNECTING ROD BEARING, PN SL 13521 IN N	R 6 CONNECTING ROD POSITION.  NOT SURE WHICH CAUSED THE FAILURE OF THE ENGINE.  A ROD BEARING HALF WAS FOUND IN THE SUMP	, MANGLED BUT INTACT;  ITS MATE HAD DISINTEGRATED AND WAS SCATTERED THROUGHOUT THE ENGINE.  THE ROD BOLT IN QUESTION WAS	 MISSING THREADS, AND WAS BLUE IN COLOR FROM EXCESSIVE HEAT.  THE ROD NUT AND BOLT HEAD WERE NOT FOUND IN THE ENGINE AND	 SUSPECTED THAT THEY EXITED THE CRANKCASE THROUGH THE HOLE CREATED BY THE CONNECTING ROD BEING THROWN OFF THE CRANKSHAFT	.  THE ENGINE DID NOT SHOW SIGNS OF OIL STARVATION OR PROBLEMS WITH ANY OF THE OTHER CONNECTING ROD BEARINGS OR BOLTS.	1	L	7	1 	3O	3	O	 	A3SO    	E295
2004050600076	20040506	00076	CE  	2004	5	6	2004FA0000306    	1	20040409	G	2720	S100343A	BEARING         			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					RUDDER BAR	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	182TA					18280062				DURING THE ANNUAL INSPECTION, IT WAS DETERMINED THAT THE BEARING FOR THE CO-PILOT RT RUDDER BAR TO BRAKE BELLCRANK WAS M	ISSING.  THE FACTORY TORQUE SEAL ON THE ATTACHING HARDWARE WAS UNDISTURBED.					1	H	7	1 	3O	3	O	NT	3A13    	1E4
2004050600025	20040506	00025	CE  	2004	5	6	2004FA0000307    	1	20040409	G	2497	103003	WIRE            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					ALTERNATOR	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	54589		383  			17275007				THE 3 WIRES COMING FROM THE STATOR WERE SHORTED OUT ON THE CASE, THIS IS THE 4TH ALTERNATOR OVERHAULED WITH THE SAME FAI	LURE.  WITH LESS THAN 390.0 HOURS SINCE OVERHAUL.  WIRES NOT INSULATED PROPERLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274
2004050700031	20040507	00031	SW  	2004	5	7	2004FA0000308    	1	20040413	G	6220	206010450113	SWASHPLATE      			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	INCORRECT       	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	01	383SH	12050				51073				RECEIVED SWASHPLATE ASSY FROM VENDOR OVERHAUL SHOP.  DURING INSTALLATION  FOUND LEVER (PN 206-010-467-001)  WAS INSTALLE	D UP-SIDE-DOWN.  ALSO FOUND SHIMS (PN 206-010-463-005) WERE NET STACKED EVENLY.  PROBABLE CAUSE: WORKMANSHIP AND QA PROB	LEM.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004042200124	20040422	00124	NE  	2004	4	22	2004FA0000309    	2	20040401	G	7250	557501	TURBINE WHEEL   								PWA   	JT8   	JT8D7B      	52053	NE  					ENGINE	WORN            	B			ZAVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07		7381 	4723 				649049			T-1 DISC RUB ON INNER TURBINE NOZZLE CASE SEAL.  SEAL COMPLETELY RUBBED OFF.											4	F			E2EA
2004042300001	20040423	00001	GL  	2004	4	23	2004FA0000310    	3	20040322	G	6114		HUB             													MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER	FATIGUED        	B			L2PR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13								714499		PROPELLER WAS LEAKING RED DYE FROM HUB, PROPELLER WAS DISASSEMBLED FOR RESEAL AND INSPECTION, CRACK WAS NOTED DURING VIS	UAL INSPECTION AND CONFIRMED BY EDDY CURRENT.  PROBABLE CAUSE FOR CRACK IS FATIGUE FAILURE, RED DYE/ OIL IS PLACED INSID	E HUB TO DETECT POSSIBLE CRACKS BEFORE CATASTROPHIC FAILURE (AD 91-15-04), MANY OWNER/ OPERATORS ARE NOT AWARE OF THE SI	GNIFICANCES OF THESE LEAKS AND IGNORE THEM.													5	C	P5EA
2004050600047	20040506	00047	CE  	2004	5	6	2004FA0000311    	1	20040108	G	5280	245000615	BUMPER BLOCK    			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					LT NLG DOOR	WORN            	B			CMXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	9084F					172RG0352				NG DOOR OB EDGE CAUGHT ON GEAR WELL BUMPERS AND PREVENTED NG DOORS FROM OPENING WHEN GEAR SELECTED DOWN.  IT IS CAUSED B	Y DOORS BEING RIGGED WITH TOO LITTLE CLEARANCE, BUMPERS WEAR THIN AND ALLOW GEAR DOORS TO RAISE ON TOP OF BUMPER AND WED	GE DOORS.  NOSE GEAR WOULD NOT EXTEND BECAUSE DOORS WERE WEDGED AND COULD NOT OPEN CAUSING A LANDING WITHOUT NOSE GEAR D	EPLOYED, CAUSING DAMAGE TO THE PROPELLER AND NOSE GEAR DOORS.  CLEARANCE IS .160 MAX AND .100 MIN.  BUMPER IS .375 IN WI	DTH AND IF BUMPER WEARS THIN OR EVEN AWAY THEN THERE IS AN EDGE THAT DOOR CAN WEDGE ON.  CHECK GEAR DOOR OB EDGES TO INS	URE SPOT WELDS ARE INTACT AND DOOR SKINS HAVE NOT SEPARATED ALLOWING ONE SKIN TO CATCH ON BUMPERS.	1	H	7	1 	3O	3	O	 	3A17    	E286
2004050300105	20040503	00105	CE  	2004	5	3	2004FA0000312    	1	20040108	G	5320	245000616	BUMPER BLOCK    			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					RT NLG WW	WORN            	B			CMXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	9084F					172RG0352				NG DOOR OB EDGE CAUGHT ON GEAR WELL BUMPERS AND PREVENTED NG DOORS FROM OPENING WHEN GEAR SELECTED DOWN.  IT IS CAUSED B	Y DOORS BEING RIGGED WITH TOO LITTLE CLEARANCE, BUMPERS WEAR THIN AND ALLOW GEAR DOORS TO RAISE ON TOP OF BUMPER AND WED	GE DOORS.  NOSE GEAR WOULD NOT EXTEND BECAUSE DOORS WERE WEDGED AND COULD NOT OPEN CAUSING A LANDING WITHOUT NOSE GEAR D	EPLOYED, CAUSING DAMAGE TO THE PROPELLER AND NOSE GEAR DOORS.  CLEARANCE IS .160 MAX AND .100 MIN BUMPER IS .375 IN WIDT	H AND IF BUMPER WEARS THIN OR EVEN AWAY THEN THERE IS AN EDGE THAT DOOR CAN WEDGE ON.  CHECK GEAR DOOR OB EDGES TO INSUR	E SPOT WELDS ARE INTACT AND DOOR SKINS HAVE NOT SEPARATED ALLOWING ONE SKIN TO CATCH ON BUMPERS.	1	H	7	1 	3O	3	O	 	3A17    	E286
2004050300157	20040503	00157	CE  	2004	5	3	2004FA0000313    	1	20040108	G	5280	24130832	DOOR            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NOSE GEAR	OUT OF RIG      	B			CMXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	9084F					172RG0352				NOSE GEAR OB EDGE CAUGHT ON GEAR WELL BUMPERS AND PREVENTED NG DOORS FROM OPENING WHEN GEAR SELECTED DOWN.  IT IS CAUSED	 BY DOORS BEING RIGGED WITH TOO LITTLE CLEARANCE, BUMPER WEAR THIN AND ALLOW GEAR DOORS TO RAISE ON TOP OF BUMPER AND WE	DGE DOORS.  NOSE GEAR WOULD NOT EXTEND BECAUSE DOORS WERE WEDGED AND COULD NOT OPEN CAUSING A LANDING WITHOUT NOSE GEAR 	DEPLOYED, CAUSING DAMAGE TO THE PROPELLER AND NOSE GEAR DOORS.  CLEARANCE IS .160 MAX AND .100 MIN.  BUMPER IS .375 IN W	IDTH AND IF BUMPER WEARS THIN OR EVEN AWAY THEN THERE IS AN EDGE THAT DOOR CAN WEDGE ON.  CHECK GEAR DOOR OB EDGES TO IN	SURE SPOT WELDS ARE INTACT AND DOOR SKINS HAVE NOT SEPARATED ALLOWING ONE SKIN TO CATCH ON BUMPERS.	1	H	7	1 	3O	3	O	 	3A17    	E286
2004050600074	20040506	00074	CE  	2004	5	6	2004FA0000314    	1	20040108	G	5280	24130831	DOOR            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NLG	OUT OF RIG      	B			CMXR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	05	9084F					172RG0352				NG DOOR OB EDGE CAUGHT ON GEAR  WELL BUMPERS AND PREVENTED NG DOORS FROM OPENING WHEN GEAR SELECTED DOWN.  IT IS CAUSED 	BY DOORS BEING RIGGED WITH TOO LITTLE CLEARANCE, BUMPERS WEAR THIN AND ALLOW GEAR DOORS TO RAISE ON TOP OF BUMPER AND WE	DGE DOORS.  NOSE GEAR WOULD NOT EXTEND BECAUSE DOORS WERE WEDGED AND COULD NOT OPEN CAUSING A LANDING WITHOUT NOSE GEAR 	DEPLOYED, CAUSING DAMAGE TO THE PROPELLER AND NOSE GEAR DOORS.  CLEARANCE IS .160 MAX AND .100 MIN.  BUMPER IS .375 IN W	IDTH AND IF BUMPER WEARS THIN OR EVEN AWAY THEN THERE IS AN EDGE THAT DOOR CAN WEDGE ON.  CHECK GEAR DOOR OB EDGES TO IN	SURE SPOT WELDS ARE INTACT AND DOOR SKINS HAVE NOT SEPARATED ALLOWING ONE SKIN TO CATCH ON BUMPERS.	1	H	7	1 	3O	3	O	 	3A17    	E286
2004050700002	20040507	00002	EA  	2004	5	7	2004FA0000315    	2	20040313	G	8520		PISTON          			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	NR 3 CYLINDER	MELTED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	8364N	7226 	1760 			28R8118060	L1544651A	805737		NR 3 PISTON/ CYLINDER MELTED.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA
2004050600075	20040506	00075	CE  	2004	5	6	2004FA0000316    	1	20040408	G	2434	DOFF10300BR	WIRE            			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520*      	17032	SO  					ALTERNATOR	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	761SP					21062483				THE 3 WIRES COMING FROM THE STATOR ARE SHORTED OUT ON THE CASE.  THIS IS 4TH ALTERNATOR OVERHAUL BY FACILITY WITH THE SA	ME FAILURE, ALL 4 ALTERNATORS HAD LESS THAN 390 HOURS SINCE OVERHAUL.  THERE NEED TO BE MORE INSULATION ON THE 3 WIRES.					1	H	7	1 	3O	3	O	 	3A21    	E5CE
2004050300165	20040503	00165	CE  	2004	5	3	2004FA0000317    	1	20040408	G	2497		WIRE            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					ALTERNATOR	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	65045		237  		A155851	17275674				THE 3 WIRES COMING FROM THE STATOR ARE SHORTED OUT ON THE CASE.  THIS IS THE 4TH ALTERNATOR OVERHAULED BY FACILITY WITH 	THE SAME FAILURE.  ALL 4 ALTERNATORS HAD LESS THAN 390 HOURS SINCE OVERHAUL.  THERE NEEDS TO BE MORE INSULLATION ON THE 	3 WIRES.				1	H	7	1 	3O	3	O	NT	3A12    	E274
2004050300158	20040503	00158	EA  	2004	5	3	2004FA0000318    	1	20040316	G	3520	STCSA8082NMD	OXYGEN SYSTEM   			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					PAX	FAILED          	B			TJ4R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	11	316FX					5387				DURING A 12 MONTH OXYGEN SYS OPERATIONAL TEST, FOUND NO OXYGEN FLOW TO LT SIDE CABIN MASKS (6 EA) LOCATED IN LT CABIN OV	ERHEAD PASSENGER SERVICE UNIT. (PSU) 6 MASKS SUPPLY EMERGENCY OXYGEN FOR 4 LT CABIN SEATS.  THERE WAS SUFFICIENT PRESSUR	E IN THE SYSTEM FOR THE MASKS TO DEPLOY FROM THE DEPLOYMENT CONTAINERS LOCATED IN THE PSU, BUT WHEN THE MASK LANYARDS WE	RE PULLED TO ENABLE OXYGEN FLOW TO THE MASKS THERE WAS NO FLOW OF OXYGEN TO THE MASKS.  DISCOVERED THE OXYGEN SUPPLY HOS	E (PN17341024) FOR THE LT SIDE OF THE CABIN WAS PINCHED BETWEEN THE OVERHEAD PSU AND THE INTERIOR SHELL PANEL DUE TO MIS	ALIGNMENT OF THE HOSE PASS-THROUGH HOLES AT FS364.  HOSE WAS REPLACED WITH NEW, AND PASS-THROUGH CLEARANCE PROVIDED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004051000039	20040510	00039		2004	5	10	2004FA0000320    	4	20040415	G	8300		GEAR            			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					ACCESSORY G/B	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	78940					1974	1635236A			REMOVED OIL PUMP TO CHECK ON TYPE OF GEARS, FOUND SINTERED IRON IMPELLERS.  REPLACED WITH HARDEN GEAR KIT.						1	L	7	1 	3O	3	O	 	2A3     	E286
2004050500044	20040505	00044	SO  	2004	5	5	2004FA0000321    	2	20040323	G	8530	654959A1	CYLINDER        			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	DAMAGED         	B			UGZR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			AL	03	8924X					18253324				COULD NOT GET ENGINE TO RUN PROPERLY.  COMPRESSION GOOD ON NR 6, FINALLY DETERMINED NR 6 WAS NOT OPERATING PROPERLY.  RE	MOVED CYLINDER, SENT FOR OVERHAUL.  FOUND HOLE IN EXHAUST VALVE PORT.  (VOID IN THE CYLINDER CASTING) CYLINDER REJECTED 	AND RETURNED WITH LETTER.				1	H	7	1 	3O	3	O	NT	3A13    	E273
2004050300102	20040503	00102	NM  	2004	5	3	2004FA0000322    	1	20040413	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					UPPER HUB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	102  			0099990080	9000085				DURING ACCOMPLISHMENT OF AD2002-10-05 (MAIN ROTOR UPPER HUB INSP.) FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED 	IN MFG SERVICE BULLETIN 900-072.  CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004050300103	20040503	00103	NM  	2004	5	3	2004FA0000323    	1	20040413	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					UPPER HUB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	102  			0099990080	9000085				DURING ACCOMPLISHMENT OF AD2002-10-05 (MAINROTOR UPPER HUB INSP.) FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED I	N MFG SERVICE BULLETIN 900-072.  CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004050300106	20040503	00106	NM  	2004	5	3	2004FA0000324    	1	20040421	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					UPPER HUB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	102  			0099990080					DURING ACCOMPLISHMENT OF AD 2002-10-05 (MAIN ROTOR UPPER HUB INSPECTION), FOUND (3) OUT OF (10) BOLT HOLES TO BE CRACKED	 AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0HOURS. REMOVED AN	D REPLACED UPPER HUB WITH NEW.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004050300123	20040503	00123	EA  	2004	5	3	2004FA0000325    	2	20040329	G	8530		PUSHROD         			ROBSIN	R22   	R22MARINER  	7640115	NM  	LYC   	O360  	O360J2A     	41514	EA  					NR 2 CYLINDER	BENT            	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	03	203CP					2659M	L3525336A			NUMBER 2 CYLINDER EXHAUST VALVE STUCK AND BENT PUSHROD CAUSING ENGINE POWER LOSS.  PILOT THEN EXECUTED A PRECAUTIONARY L	ANDING.					1	G	7	1 	3O	3	O	 	H10WE   	E286
2004050300145	20040503	00145	EA  	2004	5	3	2004FA0000329    	2	20040329	G	8530		PUSHROD         			ROBSIN	R22   	R22MARINER  	7640115	NM  	LYC   	O360  	O360J2A     	41514	EA  					ENGINE	BENT            	C				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	03	203CP					2659M	L3525336A			NR 2 CYLINDER EXHAUST VALVE STUCK AND BENT PUSHROD CAUSING ENGINE POWER LOSS.  PILOT THEN EXECUTED A PRECAUTIONARY LANDI	NG.					1	G	7	1 	3O	3	O	 	H10WE   	E286
2004042900028	20040429	00028	NM  	2004	4	29	2004FA0000330    	1	20040303	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	15	902PD	399  	106  		0099990078					DURING ACCOMPLISHMENT OF AD 2002-10-05 INSP. (MAIN ROTOR UPPER HUB INSP.) FOUND (2) OUT OF (10) FLANGE BOLT HOLES WITH C	RACKS AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS RUN RADIALLY FROM BOLT HOLE INWARD TO FLANGE EDGE. PART TOTAL 	TIME WAS 399.65 HRS. UPPER HUB WAS FLOWN 106 HRS WITH MFG SERVICE BULLETIN 900-093 (INCREASED BOLT TORQUE) INCORPORATED.	 REMOVED AND REPLACED HUB WITH SERVICEABLE PART IAW MFG MM.			1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004050300161	20040503	00161	NM  	2004	5	3	2004FA0000331    	1	20040413	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					UPPER HUB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	102  	102  		0099990080					DURING ACCOMPLISHMENT OF AD 2002-10-05 (MAIN ROTOR UPPER HUB INSP.)  FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTE	D IN SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102 HRS.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004050300183	20040503	00183	NM  	2004	5	3	2004FA0000332    	1	20040413	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					UPPER HUB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	102  			0099990080	9000085				DURING ACCOMPLISHMENT OF AD2002-10-05 (MAINROTOR UPPER HUB INSP.)   FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED	 IN MFG SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004042900037	20040429	00037	SW  	2004	4	29	2004FA0000333    	1	20040325	G	6220	2040121127	STRAP           	BELL        		BELL  	204   	UH1H        	1181407	SW  	LYC   	T53   	T53L13B     	41549	NE  					M/R HEAD	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	667HP	4815 	131  		ARA0638	659952	22986B			AIRCRAFT WAS EXPERIENCING VIBRATIONS DURING FLIGHT, MAINTENANCE WAS UNABLE TO REMOVE THE VIBRATION THROUGH TRACK AND BAL	ANCE PROCEDURES. THE MAIN ROTOR ASSEMBLY WAS REMOVED FOR INSPECTION. DURING THE INSPECTION A TENSION-TORSION STRAP WAS F	OUND CRACKED AT BOTH ENDS WHERE THE PINS HOLD THE STRAPS IN PLACE. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE	 STRAPS INSTALLED WERE NOT THE PROPER STRAPS FOR THIS M/R HEAD CONFIGURATION.			1	G	7	1 	4U	4	U	 	EXPA1G71	E17EA
2004050600046	20040506	00046	GL  	2004	5	6	2004FA0000334    	1	20040303	G	1410		HOSE            			AMTR  	VORTEX	VORTEX      	05603FA	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					VACUUM SYSTEM	IMPROPER PART   	G				C				ABORTED TAKEOFF         				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			WP	25	96XV	12   					5437430			THE VACUUM LINE GOING TO THE FUEL PNEUMATIC PUMP HAD AN IRREGULAR PART INSTALLED. THE MM REQUIRES A HARD, NON-COLLAPSIBL	E, FUEL RESISTANT LINE. THE LINE INSTALLED WAS FLEXIBLE/COLLAPSABLE AND HAD A 45 DEGREE KINK ON THE VACUUM SIDE. THIS MA	Y LEAD TO LESS VACUUM TO THE FUEL PUMP LOWERING THE CAPABILITY OF THE PUMP. RECOMMEND FOLLOW THE MFG PROCEDURES WHEN INS	TALLING THE ENGINE.			1	G	7	1 	3I	3	I	NT	EXPA1G71	EXPE3I
2004050300104	20040503	00104	CE  	2004	5	3	2004FA0000336    	1	20040305	G	5712	08522350	RIB             			CESSNA	402   	402B        	207590P	CE  										LT WING	CRACKED         	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	707H	11745				402B0117				FOUND OIL CANNING IN LT WING OF HIGH TIME WHEN LIFTING AFT END OF TIP TANK.  WING WAS INSPECTED AND ONLY DEFECT WAS LWR 	FLANGE ON 4 OF INTERSPAR RIBS WERE CRACKED, STRINGER PASS-THROUGH.  CRACK WAS .5-.75 INCHES LONG, EXTENDED PAST FIRST RI	VET. AFTER REPAIRING, OIL CANNING WAS STILL EVIDENT.  OIL CANNING SKIN IS NOT RESULT OF RIB CRACKS BUT CRACKS ARE DIRECT	 RESULT OF OIL CANNING SKIN. IF LEFT UNDETECTED COULD LEAD TO STRUCTURAL FAILURE OF RIB. OIL CANNING WHEN GENTLE LIFTING	 FORCE IS PLACED ON AFT END OF TIP TANK (CAUSE OF DAMAGE) AND POSSIBLY SOME LOOSE OR SMOKING RIVETS ON RIB LINE (RESULT 	OF THE DAMAGE)  IF RIVETS ARE LOOSE OR SMOKING BE SURE TO INSPECT INNER STRUCTURE BEFORE PUTTING BLIND FASTENER IN.	1	L	7	2 	3O			 	A7CE
2004042900039	20040429	00039	EU  	2004	4	29	2004FA0000337    	1	20040329	G	8097	52621	CABLE           			AIMM  	AMT200	AMT200S     	0160001	EU  										STARTER	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	139XS	178  				200139				STARTER CABLE PN 52621 BROKE AT THE LUG CONNECTED TO THE STARTER.						1	L	7	1 	3I			NC	TG0004A
2004050300115	20040503	00115	CE  	2004	5	3	2004FA0000338    	1	20040422	G	2710	63610027	CONTROL CABLE   			CESSNA	525   	525A        	2076615	CE  										WING AILERON	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	630TF	1061 				525A0022				DURING ACCOMPLISHMENT OF THE AIRCRAFT'S FIRST PHASE 5 INSPECTION, FOUND ALL FOUR AILERON WING CABLES TO BE HEAVILY FLAT 	SPOTTED AT THE FAIRLEADS LOCATED AT WS 58.00, 103.43 AND 149.18.  THE RT UPPER CABLE (P/N 6361002-7) HAD ONE BROKEN STRA	ND.  THESE CABLES NORMALLY LAST MUCH LONGER THAN 1061 HRS.  SUSPECT A HEAVIER THAN NORMAL CONTACT BETWEEN THESE WING AIL	ERON CABLES AND THE NOTED FAIRLEADS WHILE IN FLIGHT.  RECOMMEND CLOSE INSPECTION OF THE AILERON WING CABLES IN THE FAIRL	EAD AREAS AT THE NEXT AVAILABLE INSPECTION.		1	L	7	1 	4F			RT	A1WI
2004042900036	20040429	00036	SO  	2004	4	29	2004FA0000339    	1	20040323	G	8120	60051004	HOUSING         			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					TURBOCHARGER	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8177C	1119 			CGR0706	28R8231065				REMOVED TURBO FOR OTHER WORK, INSPECTED HOUSING PN 600510-04 AND FOUND IT TO BE CRACKED AS SHOWN IN AD 82-27-03 FIGURE 2	, AD 82-27-03 DOES NOT APPLY TO THIS HOUSING NUMBER, RECOMMEND INSPECTING ALL TURBOS REGARDLESS OF AD.					1	L	7	1 	3O	3	O	 	2A13    	E9CE
2004050500155	20040505	00155	SO  	2004	5	5	2004FA0000340    	2	20040331	G	8530	631996	ROCKER          			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  					ENGINE	BROKEN          	B			H00R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	736DU					R1722452	288641			FOUND HOLE IN ROCKER COVER CAUSED BY ROCKER ARM ON EXHAUST SIDE.  FOUND FWD STUD ASSY BROKEN OFF FLUSH WITH CYLINDER HEA	D.  STUD (PN 401852).  ROCKER RETAINER (PN 631996) WAS BROKEN AND HALF MISSING (GONE OUT OF HOLE IN COVER) IB STUD HOLD 	DOWN NUT WAS 4 TO 5 THREADS FROM COMING OFF.  SUSPECT NUTS WERE NOT PROPERLY TORQUED.				1	H	7	1 	3O	3	O	 	3A17    	E1CE
2004050400054	20040504	00054		2004	5	4	2004FA0000341    	4	20040315	G	2561	KS9P0101125NC	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										LIFE PRESERVER FAILED.  MFG RECOMMENDED CELL PRESSURE CHECK IAW 25-60-1.  DOM: MAY 1984.
2004050400053	20040504	00053		2004	5	4	2004FA0000342    	4	20040315	G	2561	GA12P0201	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-13.  DOM: AUG 1981.
2004050300208	20040503	00208	SO  	2004	5	3	2004FA0000343    	2	20040331	G	7414	10160844	BRUSHES         		S6RH1225    	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					MAG DIST GEAR	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	99	PKMAR				F02HA216	U20606231	523210			UPON COMPLETING THE FIRST 500 HOUR INSPECTION ON THE MAGNETO, IT WAS DISCOVERED THAT THE CARBON BRUSH AND SPRING ASSY (P	N 10160844) WERE NOT INSTALLED.  THE BUSHING IN THE DISTRIBUTOR GEAR HAD BEEN MAKING CONTACT WITH THE TAB ON THE COIL SO	 THE MAGNETO APPEARED TO BE FUNCTIONING NORMALLY.  ADDITIONALLY, THE WEDGES (PN 10349219) THAT SECURE THE COIL ASSEMBLY 	INTO THE CASE WERE OVER-DRIVEN, BENT AND MALFORMED SEVERELY BY THE INSTALLATION PROCESS WHEN MANUFACTURED.			1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004050300132	20040503	00132	CE  	2004	5	3	2004FA0000344    	1	20040312	G	5541		SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	68329					15282261				FOUND RUDDER SPAR CRACKED AT LIGHTENING HOLE JUST UNDER TOP RUDDER MOUNTING HINGE.  4 CRACKS WERE PRESENT, THE LONGEST W	AS .5 INCH.  RECOMMEND INSPECTION EVERY 100 HOURS, REPLACE WITH NEW SPAR MISSING LIGHTENING HOLE IF DEFECTIVE.					1	H	7	1 	3O	3	O	NT	3A19    	E223
2004050300135	20040503	00135	CE  	2004	5	3	2004FA0000345    	1	20040426	G	3010	632242014	PICCOLO TUBE    			CESSNA	525   	525A        	2076615	CE  										ANTI-ICE	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	630TF	1061 				525A0022				DURING THE PHASE 5 INSPECTION THE RT WING ANTI-ICE PICCOLO TUBE WAS FOUND BROKEN AT THE ANIT-ROTATION TAB.  THE TUBE WOR	KED ITS WAY INBOARD APPROXIMATELY 4 INCHES.  THE FLEX COUPLING KEPT IT FROM TRAVELING INBOARD ANY FURTHER.  NEW PART WAS	 ORDERED AND INSTALLED.  THIS SAME CONDITION WAS FOUND ON ANOTHER 525 AND 525A.				1	L	7	1 	4F			RT	A1WI
2004050300137	20040503	00137	CE  	2004	5	3	2004FA0000346    	1	20040403	G	5320	20430129	RUB STRIP       	CESSNA      		CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NLG DOOR ACT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	8828Y		100  			177RG1289				DURING ANNUAL INSPECTION LANDING GEAR RETRACTION TEST WAS PERFORMED AND THE NOSE GEAR DOORS WOULD NOT FULLY CLOSE. INVES	TIGATION FOUND THE TEFLON RUB STRIP ON THE NOSE LANDING GEAR DOOR ACTUATOR MISSING.					1	H	7	1 	3O	3	O	 	A20CE   	1E10
2004050300139	20040503	00139	CE  	2004	5	3	2004FA0000347    	1	20040331	G	2434	646843	ALTERNATOR      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	C				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			SO	11	42RK	24   	24   			CE934	813981			OVERHAULED GEAR DRIVEN ALTERNATOR REPEATED FAILURE. ALTERNATOR P/N 646843 S/N D022878 WENT TO TWO TIMES FOR REPAIR OR OV	ERHAUL AND FAILED VERY SOON AFTERWARDS EACH TIME. 25 HOURS FIRST TIME AND .5 HOURS SECOND TIME. FIRST TIME WO NR MW25590	 SECOND TIME WO NR MW29610.				1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004050300144	20040503	00144	CE  	2004	5	3	2004FA0000348    	1	20040318	G	3230	3A0500002	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	LEAKING         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	185TH					18503456				LEAKING CYLINDER CAUSED GEAR NOT TO LOCK, GEAR COLLAPSED DURING TAXI.						1	H	7	1 	3O	3	O	 	3A24    	E5CE
2004050300147	20040503	00147	SO  	2004	5	3	2004FA0000349    	1	20040401	G	8097	A02855688499	SWITCH          			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					AUTO START SYS	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	77Y	531  				4697035				AUTO START SYSTEM WOULD NOT DISENGAGE AUTOMATICALLY AT 56 PERCENT NG. FOUND ELECTRONIC CONTROL MODULE 1012 (P/N 688-499)	 INTERNALLY SHORTED CAUSING POWER TO CONSTANTLY FLOW REGARDLESS OF COMMANDS.					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA
2004050300149	20040503	00149	EU  	2004	5	3	2004FA0000350    	1	20040405	G	3411		LINE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6*        	52043	EA  					PITOT SYSTEM	SEPARATED       	B				O				OTHER                   				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CR	CRUISE         	1			SO	11	529PB	188  				529				PILOT EXPERIENCED AN ALTITUDE PORPOISE WITH AUTOPILOT ENGAGED.  AIRSPEED IND INDICATED THAT AIRSPEED WAS DECREASING, ALT	HOUGH AIRSPEED REMAINED SAME. BOTH PITOT SYS WERE CHECKED, OK.  RT STATIC SYS WAS CHECKED, FOUND TO BE OK.  THE LT STATI	C SYS WOULD NOT PRESSURIZE AT ALL.  ISOLATED THE STATIC SYS LEAK TO FITTING AT AFT PRESSURE BULKHEAD (FRAME 36, STATION 	380.7).  STATIC LINE TUBING ON INSIDE OF PRESSURE BULKHEAD HAD PULLED OUT OF THE FITTING, IT HAD BEEN CUT TOO SHORT AT T	HE FACTORY.  WHEN THIS LINE PULLED OUT, IT EXPOSED THE PILOT SIDE STATIC SYS TO CABIN PRESSURE. MAKE THE STATIC LINES SL	IGHTLY LONGER DURING THE MFG PROCESS, THUS PREVENTING THEM PULLING OUT OF THE FITTINGS AS THE AC STRETCHES.	1	L	7	1 	3T	3	T	RT	A78EU   	E2NE
2004050300152	20040503	00152	EU  	2004	5	3	2004FA0000351    	1	20040315	G	2823	SF2601314611	ROD             			MRCHTI	SF260 	SF260       	8121206	EU  	LYC   	O540  	O540*       	41532	EA  					FUEL VALVE	BROKEN          	G				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			GL	07	260MN	5342 				121				PILOT WAS MOVING FUEL SELECTOR KNOB FROM WING TIP TANKS TO WING TANKS AND THE FUEL SELECTOR ROD BROKE AT THE FUEL SELECT	OR VALVE WITH THE FUEL SELECTOR VALVE IN BETWEEN TANK POSITIONS.  THE ENGINE STOPPED AND AN EMERGENCY LANDING WAS ACCOMP	LISHED.  INVESTIGATION REVEALED THE FUEL SELECTOR ROD BROKE WERE IT WAS DRILLED FOR THE TAPERED PIN, P/N AN385H40-7. INF	O ON MFG'S PART BOOK AT PAGE 8-22-01, FIGURE 1.			1	L	7	1 	3O	3	O	 	A10EU   	E295
2004050300154	20040503	00154		2004	5	3	2004FA0000352    	4	20040312	G	2210	55X	AUTOPILOT SYS   			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					COCKPIT	INOPERATIVE     	C				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	19	738QV	300  	10   			R18200955				IN APR AND NAV MODE, AUTOPILOT WILL NOT PROPERLY INTERCEPT AND TRACK LOCALIZER AND/OR VOR SIGNAL. AUTOPILOT WILL SCALLOP	 ACROSS COURSE. AUTOPILOT HAS BEEN SENT IN FOR EVALUATION.  WE HAVE EVALUATED OUR PN-101 HSI TO DETERMINE IF THEY ARE TH	E SOURCE. AFTER EVALUATIONS THE AUTOPILOT IS SOURCE OF THE PROBLEM.  ALSO, WHEN FLAPS AND GEAR ARE EXTENDED ON APPROACH,	 AUTOPILOT WILL PITCH UP AND DOWN WILDLY. THIS PROBLEM HAS PERSISTED SINCE INSTALLATION AND ON-SITE EVALUATION.  AWARE O	F SEVERAL OTHER AIRCRAFT THAT HAVE THIS PROBLEM.  AUTOPILOT NEEDS TO BE FULLY RE-EVALUATED BY THE FAA AND MANUFACTURER.		1	H	7	1 	3O	3	O	 	3A13    	E295
2004050300166	20040503	00166	CE  	2004	5	3	2004FA0000353    	1	20040311	G	2720	22601145	TORQUE TUBE     			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					ZONE 100	DETACHED        	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	09	736ZX	5075 				R18200813				LT RUDDER BAR TORQUE TUBE ASSEMBLY, PN 2260114-5 FAILURE. FAILURE OCCURRED IN FLIGHT RESULTING IN LT SIDE PILOT'S TOTAL 	LOSS OF LT RUDDER AND STEERING CONTROL.  NATURE OF FAILURE; LT OB RUDDER PEDAL SOCKET ON TORQUE TUBE BROKE AWAY FROM THE	 TORQUE TUBE. THERE IS NO OBVIOUS REASON WHY THIS MIGHT HAVE HAPPENED. THERE ARE NO BENT OR DAMAGED COMPONENTS WITHIN TH	E SAME SYSTEM, AND THE STEEL TORQUE TUBE HAS ONLY VERY LIGHT INTERNAL CORROSION.			1	H	7	1 	3O	3	O	RT	3A13    	E295
2004050300178	20040503	00178	CE  	2004	5	3	2004FA0000354    	1	20040427	G	2750	99141873	CONTROLLER      			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					TE FLAP	DEFECTIVE       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	934H					6500172				FLAP CONTROLLER FAILED TO INDICATE PROPERLY ON SYSTEM TEST.						2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004050300179	20040503	00179	SO  	2004	5	3	2004FA0000355    	2	20040427	G	8530		CYLINDER HEAD   			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					ENGINE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	5988M					421B0231				AIRCRAFT NDT SERVICE WAS CONTRACTED TO VERIFY CRACKS IN THE ENGINE CYLINDER HEADS BETWEEN THE SPARK PLUG AND FUEL INJECT	OR MOUNTING BOSS.  AN EDDY CURRENT EXAMINATION DETERMINED THAT ALL TWELVE CYLINDER HEADS WERE CRACKED. THE OPERATOR REPL	ACED ALL TWELVE CYLINDER HEADS WITH FRESH OVERHAULED HEADS. AN EDDY CURRENT EXAMINATION DETERMINED THAT FIVE OF THE TWEL	VE OVERHAULED HEADS WERE CRACKED IN THE SAME LOCATION.			1	L	7	2 	3O	3	O	 	A7CE    	E7CE
2004050300186	20040503	00186	GL  	2004	5	3	2004FA0000357    	1	20040307	G	3350	D4125609000	BATTERY PACK    			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					INSTRUMENT PNL	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	338MA	207  				40298				EMERGENCY BATTERY PACK SHORTED DUE TO SET SCREW FALLING THROUGH HOLE IN BOTTOM OF INSTRUMENT PANEL DIRECTLY ABOVE BATTER	Y PACK TERMINALS.  HOLE IS FOR WIRES FROM BATTERY PACK, HAS A RECESS IN AREA OF ELECTRICAL TERMINALS.  WHEN SET SCREW FE	LL THROUGH HOLE, LODGED BETWEEN TERMINAL CONNECTIONS IN RECESS, COMPLETELY DRAINING EMERGENCY BATTERY PACK.  BATTERIES R	EACHED HIGH ENOUGH TEMP DURING SHORT/DISCHARGE CYCLE THAT INDIVIDUAL BATTERY JACKETS WERE DEFORMED OR ACTUALLY  MELTED, 	SOME OF BATTERY CASES SPLIT, SPILLING CONTENTS.  ANYTHING THAT FALLS THROUGH THIS HOLE IN THE INSTRUMENT PANEL (INCLUDIN	G WATER) WILL NATURALLY BE TRAPPED IN RECESS IN TOP OF EMERGENCY BATTERY PACK.	1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2004050600020	20040506	00020	GL  	2004	5	6	2004FA0000358    	1	20040307	G	3350	D4125609000	BATTERY PACK    			DIAMON	DA40  	DA40        	2990002	GL  										INSTRUMENT PANEL	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	338MA	207  				40298				EMERGENCY BATTERY PACK SHORTED DUE TO A SET SCREW FALLING THROUGH HOLE IN BOTTOM OF INSTRUMENT PANEL DIRECTLY ABOVE BATT	ERY PACK TERMINALS.  HOLE IS FOR WIRES FROM BATTERY PACK.  BATTERY PACK ITSELF HAS A  RECESS IN AREA OF THE ELECTRICAL T	ERMINALS.  WHEN SET SCREW FELL THROUGH HOLE, IT LODGED BETWEEN TERMINAL CONNECTIONS IN RECESS, COMPLETELY DRAINING EMERG	ENCY BATTERY PACK.  BATTERIES THEMSELVES REACHED HIGH ENOUGH TEMPERATURE DURING SHORT/DISCHARGE CYCLE THAT INDIVIDUAL BA	TTERY JACKETS WERE DEFORMED OR ACTUALLY  MELTED.  SOME OF BATTERY CASES SPLIT, SPILLING CONTENTS. ANYTHING THAT FALLS TH	ROUGH THIS HOLE IN THE INSTRUMENT PANEL (INCLUDING WATER) WILL NATURALLY BE TRAPPED IN THE RECESS.	1	L	7	1 	3O			NT	A47CE
2004050300187	20040503	00187	CE  	2004	5	3	2004FA0000359    	1	20040312	G	3040	1295428	REGULATOR VALVE 			CESSNA	441   	441         	2076020	CE  										BLEED AIR	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03						ALL				WINDSHIELD BLEED AIR TEMP SENSOR/REGULATOR WHICH ARE REQUIRED TO BE FUNCTIONALLY TESTED AND REPLACED IF NECESSARY EVERY 	PHASE 13 (3 YRS) ARE NO LONGER AVAILABLE FROM MANUFACTURE.					1	L	7	2 	3T			RT	A28CE
2004050500094	20040505	00094	EA  	2004	5	5	2004FA0000360    	2	20040420	G	8550	73772	COOLING JET     			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					CRANKCASE	MISSING         	B			NX42	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	703ER	2079 				2844057	L3013951A			UPON DISASSEMBLY FOR ITS FIRST OVERHAUL, THE TECH FOUND TAPERED PIPE PLUGS WERE INSTALLED IN CRANKCASE INSTEAD OF THE RE	QUIRED PISTON COOLING JETS.  PISTONS AND CYLINDERS SHOWED SIGNS OF OVERHEATING ALTHOUGH NO MALFUNCTION OCCURRED.  ENGINE	 RECORDS INDICATE THE ENGINE WAS BUILT FACTORY NEW, INSTALLED ON AC AND HAS HAD NO HISTORY OF CYLINDER REMOVAL OR REPLAC	EMENT.			1	L	7	1 	3O	3	O	 	2A13    	1E10
2004050600019	20040506	00019	SO  	2004	5	6	2004FA0000361    	2	20040429	G	8530		CYLINDER        			GULSTM	680   	685         	0141612	SW  	CONT  	O520  	GTSIO520K   	17032	SO  					NR 3	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	414C					12021				NR 3 CYLINDER ON LT ENGINE HOLD DOWN STUDS BROKE OFF ON UPPER FWD AND LOWER FWD. ONLY ONE NUT WAS TIGHT ENOUGH TO USE A 	WRENCH. THE OTHER NUTS WERE LOOSE.  AFTER CYLINDER REMOVAL A PIECE OF THE CASE HALF CAME OFF WITH THE CYLINDER APPROX.  	6 INCHES ACROSS ALONG THE TOP OF THE CYLINDER. EXHAUST PIPE FOR THE NR3 CYLINDER BROKE OFF AT THE FLANGE.				1	H	7	2 	3O	3	O	 	2A4     	E7CE
2004050600026	20040506	00026	CE  	2004	5	6	2004FA0000362    	1	20040325	G	1430	AN824A	BOLT            			CESSNA	150   	150M        	2071830	CE  										WING ATTACHING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	66062	4681 				15075807				WHEN PERFORMING MAINT. ON A/C, NOTED RUST ON HEADS OF MAIN SPAR WING ATTACHING BOLTS. REMOVED BOLTS FINDING THEM BADLY C	ORRODED AND RUSTED. INSPECTED FUSELAGE BEARING BORE AND SPAR BOAR AND INSTALLED NEW AN8-24A BOLTS. AGE AND ENVIRONMENT M	AY BE PROBLEM, RECOMMEND COATING BOLTS AND BORE WITH EPOXY PRIMER AND INSTALLING WET.				1	H	7	1 	3O			 	3A19
2004050600029	20040506	00029	CE  	2004	5	6	2004FA0000363    	1	20040413	G	5210	551123514	HINGE           	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN DOOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	92B	6678 				5500471				WHEN PILOT OPENED CABIN DOOR, A GUST OF WIND CAUGHT DOOR AND SLAMMED IT INTO STOP. PILOT REPORTED A LOUD (POP) AND PAINT	 FELL FROM DOOR HINGE.  INSPECTION REVEALED LOWER LEG OF DOOR HINGE HAD BROKEN.  DISASSEMBLY REVEALED EVIDENCE OF A PRE 	EXISTING SUBSURFACE CRACK IN CASTING, 3 INCH AFT OF HINGE BEARING. A SURFACE CRACK 1INCH LONG 1.5 INCH AFT OF HINGE BEAR	ING WAS HIDDEN BY HEAVY PAINT COATING. THESE CRACKS WOULD NOT BE VISIBLE WITHOUT PAINT REMOVAL.  RECOMMEND PAINT BE REMO	VED AND CAST PORTION OF HINGE INSPECTED UNDER MAGNIFICATION AT 500 HR INTERVALS.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004050600039	20040506	00039	EA  	2004	5	6	2004FA0000364    	2	20040315	G	7320		FUEL CONTROL    			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	MISMARKED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23										AS MANUFACTURED, THE FUEL VALVE SELECTOR HANDLE CONSISTS OF A SMALL POINTER AND A SILVER HANDLE OPPOSITE OF EACH OTHER O	N THE LT INTERIOR WALL BY THE FRONT SEAT.  OPPOSITE BOTH FUEL VALVE SELECTIONS OF (LT) AND (RT) IS AN (OFF) POSITION.  T	HE POINTER IS OFTEN PAINTED THE SAME COLOR AS THE BACKGROUND COLOR OF THE INTERIOR, USUALLY DARK RED.  THIS LEADS TO THE	 POSSIBILITY OF SOMEONE INADVERTENTLY USING THE SILVER HANDLE TO MAKE THE VALVE SELECTION INSTEAD OF THE POINTER, PERHAP	S TURNING THE VALVE (OFF) INSTEAD OF SELECTING A FUEL TANK.  THE POINTER SHOULD BE PAINTED A DISTINCTIVE COLOR AND PERHA	PS THE VALVE SELECTOR SHOULD BE PLACARDED: (USE POINTER NOT SILVER HANDLE TO MAKE VALVE SELECTION).	1	H	7	1 	3O	3	O	 	1A2     	E274
2004050600044	20040506	00044	CE  	2004	5	6	2004FA0000365    	1	20040329	G	1420	52621	CABLE           			BEECH 	35    	M35         	1151526	CE  										STARTER	BROKEN          	B				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	03	136X	318  				D6215				STARTER CABLE PN 52621 BROKEN AT THE LUG CONNECTED TO THE STARTER.						1	L	7	1 	3O			 	3A15
2004050600045	20040506	00045	CE  	2004	5	6	2004FA0000366    	1	20040324	G	1430	AN823A	BOLT            			CESSNA	172   	172K        	2072430	CE  										SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	78203	3400 				17257525				WHILE REMOVING WING BOLTS, FOUND BOLTS RUSTED AND CORRODED.  RECOMMENDED BOLTS BE INSPECTED AND COATED WITH EPOXY PRIMER	, INSTALLING NEW BOLTS.					1	H	7	1 	3O			NT	3A12
2004051400114	20040514	00114	EU  	2004	5	14	2004FA0000368    	1	20040329	G	8097	52621	CABLE           			AIMM  	AMT200	AMT200S     	0160001	EU  										STARTER	BROKEN          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	136XS	318  				200136				STARTER CABLE PN 52621 BROKE AT THE LUG CONNECTED TO THE STARTER.						1	L	7	1 	3I			NC	TG0004A
2004050600079	20040506	00079	SO  	2004	5	6	2004FA0000369    	2	20040429	G	8520	SA627246	MAIN BEARING    			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200*       	17020	SO  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2586J	2385 				15061086	605994A			AFT THRUST FACES OF BOTH FRONT MAIN BEARING HALVES WERE SEPARATED FROM BEARING.  THIS IS A ONE PIECE STYLE THRUST/MAIN B	EARING.  PROBLEM FOUND DURING OVERHAUL, NO INDICATIONS OF FAILURE NOTED BEFORE DISASSEMBLY.  NO DAMAGE TO CASE OR CRANKS	HAFT.				1	H	7	1 	3O	3	O	 	3A19    	E252
2004050600070	20040506	00070	SO  	2004	5	6	2004FA0000370    	2	20040426	G	8530	AEC626820ST2J	CYLINDER        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 1	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	97660					18267161	466461			NR 1 CYLINDER HEAD SEPARATED FROM CYLINDER BASE IN FLIGHT.  (SO09200406841)						1	H	7	1 	3O	3	O	NT	3A13    	E273
2004051000034	20040510	00034	SO  	2004	5	10	2004FA0000371    	1	20040423	G	3245		TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					TIRE	BLEW OUT        	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	17	102WM	250  				318152112				NOSE TIRE BLEW ON LANDING.  NO CAUSE COULD BE DETERMINED BY MAINT.  THEY SUSPECTED LOW TIRE PRESSURE.  TUBE VALVE SHEARE	D OFF.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004051300035	20040513	00035		2004	5	13	2004FA0000372    	4	20040420	G	2561	AV2AS2000	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										LIFE PRESERVER FAILED MFG RECOMMENDED CELL PRESSURE TEST.  DOM: JULY 1979
2004051200016	20040512	00016	SO  	2004	5	12	2004FA0000373    	2	20040506	G	7310	6561511A5M	MANIFOLD        			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE FUEL	MALFUNCTIONED   	C				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			NM	03		491  				C0208	806463	AF0823		ENGINE DIED ON DOWNWIND. PILOT LANDED SAFELY. ENGINE STARTED ON GROUND, BUT WAS IDLING AT 750 HAS BEEN SET AT 900. ALSO,	 HAD NO MIXTURE RISE. DURING SETUP FOR FUEL PRESSURE TESTS THE LINE FROM THE THROTTLE BODY TO THE FUEL MANIFOLD HAD RESI	DUAL PRESSURE. THE FUEL MANIFOLD WAS CHANGED AND ENGINE BEHAVED NORMALLY.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004051200023	20040512	00023	SO  	2004	5	12	2004FA0000374    	1	20040511	G	5341	6676200	ATTACH FITTING  			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	FUSELAGE	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	703ER	2155 				2844057	L2983151A	010001		DURING A ROUTINE INSPECTION, THE LT AFT WING ATTACHMENT FITTING WAS FOUND TO HAVE A LOOSE ATTACHING BOLT. THIS PROBLEM H	AS BEEN TYPICAL ON A FLEET OF 6 AIRCRAFT OF THIS MODEL. THE PARTS IN QUESTION ARE: P/N-401-187 BOLT (AN5-7A), P/N-66762-	00 (PLATE-AFT SPAR) AND P/N-62448-02 (FITTING-LWR LT FUSELAGE). ONLY THE LT SIDE FITTING HAS BEEN FOUND LOOSE ON ANY OF 	THESE AIRCRAFT. THE MANUFACTURER HAS BEEN ADVISED OF THIS PROBLEM AND HAS INSPECTED THE SUBJECT AIRCRAFT. THE ONLY PREVE	NTIVE MAINTENANCE AT THIS TIME IS REPETITIVE TORQUING OF THE BOLT, VERY OFTEN.		1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA
2004051200026	20040512	00026	SO  	2004	5	12	2004FA0000375    	1	20040504	G	1430	400873	BOLT            	PIPER       		PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	NLG	SHEARED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	15	708ER	1692 	35   			2844067	L3023651A	011204		DURING FLIGHT, THE PILOT REPORTED THAT THE GEAR UNSAFE LIGHT WAS ILLUMINATED DURING GEAR RETRACTION. THE GEAR WAS EXTEND	ED AND 3 GREEN LIGHTS WERE OBSERVED. DURING THE SUBSEQUENT INSPECTION, THE BOLT IDENTIFIED BELOW WAS FOUND SHEARED AND T	HE PORTION OF THE BOLT WITH THE HEX ON IT WAS NOT FOUND. THE THREADED PORTION, WITH THE NUT AND WASHER STILL ATTACHED, W	AS FOUND TO BE THE ONLY ATTACHING ITEM CONNECTING THE ACTUATOR ROD END TO THE OVER CENTER DEVICE. NO OTHER DAMAGE WAS FO	UND AND THE HARDWARE WAS REPLACED WITH NEW.		1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA
2004051200029	20040512	00029	SO  	2004	5	12	2004FA0000376    	1	20040504	G	3220	400873	BOLT            	PIPER       		PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	ZONE 700	SHEARED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	15	708ER	1692 	35   			2844067	L3023651A	011204		DURING FLIGHT, THE PILOT REPORTED THAT THE GEAR UNSAFE LIGHT WAS ILLUMINATED DURING GEAR RETRACTION. THE GEAR WAS EXTEND	ED AND 3 GREEN LIGHTS WERE OBSERVED. DURING THE SUBSEQUENT INSPECTION, THE BOLT IDENTIFIED BELOW WAS FOUND SHEARED AND T	HE PORTION OF THE BOLT WITH THE HEX ON IT WAS NOT FOUND. THE THREADED PORTION, WITH THE NUT AND WASHER STILL ATTACHED, W	AS FOUND TO BE THE ONLY ATTACHING ITEM CONNECTING THE ACTUATOR ROD END TO THE OVER CENTER DEVICE. NO OTHER DAMAGE WAS FO	UND AND THE HARDWARE WAS REPLACED WITH NEW.		1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA
2004051400024	20040514	00024	GL  	2004	5	14	2004FA0000377    	2	20040510	G	8500		BEARING         			AMTR  	VANS  	RV8A        	05608J0	GL  	AMTR  	CHEVY6	CHEVYV6     		GL  					ENGINE	SEIZED          	G				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CL	CLIMB          	1			SW	13	82LS	5    				81013				THIS WAS SECOND FLIGHT ON THE AIRCRAFT, AIRCRAFT DEPARTED, AND UPON CLIMB OUT ENGINE EXPERIENCED HIGH OIL TEMPERATURE AN	D REDUCED RPM, PILOT RETURNED TO RUNWAY AND LANDED SHORT OF RUNWAY THRESHOLD. EXAMINATION OF ENGINE BY THE PILOT REVEALE	D THAT MAIN BEARINGS AND ROD BEARING CLEARANCES WERE TOO TIGHT AND ENGINE PARTIALLY SEIZED. ENGINE INSTALLED IN THIS EXP	ERIMENTAL AIRCRAFT IS CONVERTED FOR AIRCRAFT USE. TOTAL RUN TIME ON ENGINE IS APPROXIMATELY FIVE HOURS.			1	L	7	1 	3O	3	V	NC	EXPA1L71	EXPE3V
2004051200051	20040512	00051		2004	5	12	2004FA0000378    	4	20040510	G	3416	5934P1	ALTIMETER       																	COCKPIT	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17										MOUNTING POST ON DIAPHRAGM ASSEMBLY P/N 2644-452101 SEPARATED FROM DIAPHRAGM, CAUSING COMPLETE FAILURE OF OPERATION.
2004051300019	20040513	00019	CE  	2004	5	13	2004FA0000379    	1	20040415	G	2720		CONTROL CABLE   			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  					RUDDER	FRAYED          	B			OACR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	9873E	2357 				18268459				WHILE INSTALLING THE BATTERY AFTER SERVING, IT WAS NOTICED THAT THE FORWARD RT RUDDER CABLE WAS FRAYED IN TWO SPOTS.  IT	 WAS DETERMINED THAT, AT SOMETIME, DURING BATTERY REMOVAL OR REINSTALLATION THE RUDDER CABLE ARCED ON BOTH POSITIVE AND 	NEGATIVE POSTS.  THE FORWARD SPOT WAS ARCED THROUGH MORE THAN HALF THE DIAMETER OF THE CABLE.  AFTER REMOVING THE CABLE 	IT WAS NOTICED THAT ONLY TWO STRANDS OF THE CABLE HELD IT TOGETHER.  THE CABLE WAS REPLACED WITH FACTORY NEW.  THE BATTE	RY REMOVAL AND REINSTALLATION ON THIS MODEL AC REQUIRES GOING THROUGH A PANEL IN THE AFT SIDE FUSELAGE.		1	L	7	1 	3O	3	O	NT	3A13    	E273
2004051400122	20040514	00122	CE  	2004	5	14	2004FA0000380    	1	20040511	G	5730		WING ROOT       			CESSNA	310   	310H        	2074220	CE  										LT & RT	BUCKLED         	C				O				OTHER                   				O			OTHER                     			AB	AEROBATIC      	1			NM	07		5000 				N1091Q				AIRCRAFT WAS LOOPED, SPUN, AND BARREL ROLLED.  INFORMED, BUT NOTHING WAS DONE.  PILOT WAS/IS STILL FLYING CLUB PLANES AN	D ANOTHER VISUAL. A RECENT LOOK AT THE AIRCRAFT INDICATES POSSIBLE STRUCTURAL DAMAGE AT THE WING ROOTS. GETTING INDICATI	ONS FROM OTHER PILOTS THAT THIS WAS NOT AN ISOLATED INCIDENT.  OTHER PILOTS ARE USING THE AIRCRAFT NOT KNOWING OF IT'S P	AST HISTORY. THERE ARE OTHER AIRCRAFT AT THIS CLUB THAT WERE ALSO SPUN/LOOPED BUT HAVE NO FIRST HAND KNOWLEDGE OF THIS (	OTHER THAN WHAT OTHER MEMBERS HAVE SAID)		1	L	7	2 	3O			 	3A10
2004051400124	20040514	00124	CE  	2004	5	14	2004FA0000381    	1	20040511	G	5730		WING            			CESSNA	310   	310H        	2074220	CE  										ZONE 600	BUCKLED         	C				O				OTHER                   				O			OTHER                     			AB	AEROBATIC      	1			NM	07		5000 				N1091Q				AIRCRAFT WAS LOOPED, SPUN, AND BARREL ROLLED.  PILOT WAS/IS STILL FLYING CLUB PLANES AND ANOTHER VISUAL. A RECENT LOOK A	T THE AIRCRAFT INDICATES POSSIBLE STRUCTURAL DAMAGE AT THE WING ROOTS.  GETTING INDICATIONS FROM OTHER PILOTS THAT THIS 	WAS NOT AN ISOLATED INCIDENT.  OTHER PILOTS ARE USING THE AIRCRAFT NOT KNOWING OF IT'S PAST HISTORY. THERE ARE OTHER AIR	CRAFT AT THIS CLUB THAT WERE ALSO SPUN/LOOPED BUT HAVE NO FIRST HAND KNOWLEDGE OF THIS (OTHER THAN WHAT OTHER MEMBERS HA	VE SAID).		1	L	7	2 	3O			 	3A10
2004051400115	20040514	00115	EU  	2004	5	14	2004FA0000382    	1	20040329	G	8097	52621	CABLE           			AIMM  	AMT200	AMT200S     	0160001	EU  										STARTER	BROKEN          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	140XS					200140				STARTER CABLE PN 52621 BROKE AT THE LUG CONNECTED TO THE STARTER.						1	L	7	1 	3I			NC	TG0004A
2004051300022	20040513	00022	EA  	2004	5	13	2004FA0000383    	2	20040329	G	8500	IO360L2A	ENGINE          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	52531	776  				172S9172	L3045551A			DURING A PHASE INSPECTION, SOME METAL WAS FOUND IN THE FILTER, TOOK OIL SAMPLE FROM OIL COOLER, REMOVED SUCTION SCREEN, 	MORE METAL WAS FOUND, SENT FILTER AND OIL TO LAB FOR ANALYSIS,  SENT METAL FROM SCREEN, WAS ADVISED THAT THE SCREEN MATE	RIAL WAS FROM BEARINGS, REMOVED ENGINE FROM SERVICE.  THIS IS THE 2ND ENGINE FROM THIS AREA WITH THIS PROBLEM. THIS AIRC	RAFT HAS BEEN ON A PHASE INSPECTION PROGRAM SINCE NEW, WITH OIL CHANGES EVERY 50 HRS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004051300023	20040513	00023	EU  	2004	5	13	2004FA0000384    	1	20040421	G	1430	5PA108	NUT             			AIMM  	AMT200	AMT200S     	0160001	EU  										LANDING GEAR	MISSING         	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	136XS	318  				200136				UPON LANDING AIRCRAFT VEERED OFF THE RUNWAY. UPON INSPECTION IT WAS FOUND THAT THE NUT, (PN 5PA-108) HAD FALLEN OFF ALLO	WING THE LINK (PN 32358) TO SEPARATE.					1	L	7	1 	3I			NC	TG0004A
2004051300024	20040513	00024	SO  	2004	5	13	2004FA0000385    	2	20040426	G	8530	AEC626820ST2J	CYLINDER HEAD   			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				B	E	K	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	FLUID LOSS                	CL	CLIMB          	1			SO	09	97660	404  				18267161	466461	804513		NR 1 CYLINDER HEAD SEPARATED FROM CYLINDER BASE IN FLT. MAY NEED TO BE ADDED TO AD 2004-08-10.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
2004051900111	20040519	00111	CE  	2004	5	19	2004FA0000386    	1	20040405	G	7810	22540122	EXHAUST STACK   			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					ENGINE	FRACTURED       	C				B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	09	738QV	1200 	1200 			R18200955				DURING CRUISE FLT AT 7,500 FT. VFR, AIRCRAFT WOULD NOT MAINTAIN 25 INCHES MP. MP DROPPED TO 23 INCHES AFTER APPROX. 15 M	IN. MP DROPPED ABRUPTLY TO 18.5 INCHES MP MADE EMERGENCY DESCENT & UNSCHEDULING LANDING AT VNX WITHIN 3 MINUTES OF POWER	 LOSS. UPON EXAMINATION, FOUND EXHAUST STACK ASSY COMPLETELY FRACTURED, FULL CIRCUMFERANCE OF PIPE AROUND BASE OF FLANGE	. ADDITIONALLY, FOUND COMPLETE CIRCUMFERAL FRACTURE OF CROSSOVER AT THE WYE INTERSECTION DOWNSTREAM OF WASTEGATE. ADDITI	ONAL HEAT DAMAGE TO EGT PROBE AND WIRING, & LANDING LIGHT & WIRING.  DUE TO THE DESIGN OF THIS SYSTEM, & AFTER READING N	TSB REPORT CHI02LA218.  RECOMMEND AN AD BE ISSUED.	1	H	7	1 	3O	3	O	 	3A13    	E295
2004051300026	20040513	00026	SO  	2004	5	13	2004FA0000387    	2	20040507	G	7313	TITAN	ADAPTER         			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  					FUEL NOZZLE	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	3310D	45   				310Q0630				2 FUEL INJECTION NOZZLE ADAPTERS BACKED OUT WITH FUEL NOZZLES.						1	L	7	2 	3O	3	O	 	3A10    	3E1
2004051300033	20040513	00033	SO  	2004	5	13	2004FA0000388    	1	20040316	G	1430	NAS464P427	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  										DRAG BRACE	SHEARED         	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	575ER	1350 				4496151				ON LANDING ROLLOUT THE NOSEGEAR COLLAPSED.  INSPECTION REVEALED THE DRAG BRACE CENTER PIVOT BOLT (PN NAS464P4-27) HAD SH	EARED.  THESE SAME BOLTS WERE REMOVED AND REPLACED WITH NEW BOLTS ON THE REST OF THE FLEET.  ALL BOLTS WERE FOUND TO BE 	WORN IN A SHEAR TO SOME DEGREE.  ALL BOLTS SHOWED SOME EVIDENCE OF CORROSION SUGGESTING INADEQUATE LUBRICATION.  THIS OP	ERATOR WILL BE FOLLOWING MORE AGGRESSIVE LUBRICATION AND REMOVAL OF THE BOLTS AT 1000 HOURS FOR DETAILED INSPECTION.			1	L	7	2 	3O			 	A19S0
2004051300034	20040513	00034	SW  	2004	5	13	2004FA0000389    	1	20040417	G	7810	6414185	EXHAUST DUCT    			GULSTM	680   	685         	0141612	SW  	CONT  	O520  	GTSIO520K   	17032	SO  					NR 3 CYLINDER	BROKEN          	B				A				UNSCHED LANDING         				A			FLAME/FIRE                			CR	CRUISE         	1			SO	35	414C					12021	226116			IB EXHAUST ON LT ENGINE BROKE AT THE WELD BELOW NR 3 CYLINDER. BURNED HOLE IN LOWER ENGINE COWLING. BURNED WIRE BUNDLE O	N THE FIREWALL AFT OF NR 1 CYLINDER. SCORCHED FIRE SLEEVE ON THREE FUEL HOSES.					1	H	7	2 	3O	3	O	 	2A4     	E7CE
2004051300037	20040513	00037	CE  	2004	5	13	2004FA0000391    	1	20040405	G	5712	08522350	RIB             			CESSNA	402   	402B        	207590P	CE  										LT WING	CRACKED         	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	4167G	11745				402B1214				RAMP INSP FOUND OIL CANNING IN LT WING OF HIGH TIME.  WING WAS INSPECTED AND ONLY DEFECT FOUND WAS LWR FLANGE ON 4 OF IN	TERSPAR RIBS WERE CRACKED AT STRINGER PASS-THROUGH.  CRACK WAS .5-.75 INCHES LONG AND USUALLY EXTENDED PAST FIRST RIVET.	 AFTER REPAIRING IAW SRM THE OIL CANNING WAS STILL EVIDENT. CONCLUSION THAT OIL CANNING SKIN IS NOT RESULT OF RIB CRACKS	 BUT CRACKS ARE DIRECT RESULT OF OIL CANNING SKIN.  OIL CANNING WHEN A GENTLE LIFTING FORCE IS PLACED ON AFT END OF TIP 	TANK (CAUSE OF DAMAGE) AND POSSIBLY SOME LOOSE OR SMOKING RIVETS ON RIB LINE (RESULT OF THE DAMAGE)  IF RIVETS ARE LOOSE	 OR SMOKING BE SURE TO INSPECT INNER STRUCTURE BEFORE PUTTING A BLIND FASTENER IN.	1	L	7	2 	3O			 	A7CE
2004051300039	20040513	00039	NM  	2004	5	13	2004FA0000392    	1	20040429	G	2597	BS0063	CONNECTOR       			BOEING	717   	717200      	1383700	NM  										COFFEEMAKER	MISMANUFACTURED 	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	15										MOD 16 INSTALLED BY OEM MISWIRED. THIS IS CAUSING THE OVER TEMP PROTECTION CIRCUIT TO BECOME INOPERATIVE.						2	L	7	2 	4F			TR	A6WE
2004051400071	20040514	00071	EA  	2004	5	14	2004FA0000394    	2	20040414	G	7320	70210301	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	FUEL SYSTEM	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	665SP	1    				172S8069	L1699851A	S4101		ENGINE HAD VERY ROUGH AND RICH IDLE, COULD NOT ADJUST IDLE MIXTURE IAW AD.  FUEL SERVO WAS INSTALLED ON A FRESH O/H ENGI	NE AND FUEL SERVO WAS ALSO FRESH FROM O/H.  ENGINE WAS OPERATED AND LEAK CHECKED.  AFTER .2 HOURS OF ENGINE OPERATION.  	FUEL SERVO BECOME ROUGH AND RICH.  IDLER MIXTURE COULD NOT BE ADJUSTED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2004051400100	20040514	00100	CE  	2004	5	14	2004FA0000395    	1	20040318	G	2820	RSA5AD1	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	O320  	IO320*      	41508	EA  	MCAULY	1A170	1A170E      	GL  	FUEL SYSTEM	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	974SP	2195 				172S8178	L2893651A	TB007		FUEL MIXTURE CONTROL ARM WILL NOT ROTATE TO (IDLE CUT-OFF) POSITION.						1	H	7	1 	3O	3	O	NT	3A12    	1E12	5	N	P857
2004051400094	20040514	00094	SO  	2004	5	14	2004FA0000396    	1	20040413	G	3340	6041H202	RELAY           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					STROBE LIGHT	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	312AJ					3449188				DURING A RAIN STORM FLIGHT PERSONNEL REPORTED TO RAMP 66 MAINTENANCE DEPT THAT AC.  WINGS AND TAIL STROBE LIGHTS CAME ON	.  MAINT MECH CHECKED BATTERY SWITCH.  SWITCH WAS TURNED OFF.  DURING TROUBLESHOOT AFT COMPARTMENT FLOORING WAS REMOVED 	BEHIND PASSENGER SEATS.  WATER WAS STANDING 2 INCHES IN BELLY OF AC.  BATTERY RELAY WAS STANDING IN WATER.  AFTER REMOVI	NG, WATER WAS FOUND INSIDE OF THE RELAY.  RELAY HAD LARGE PITTING HOLE AND SHOWED SIGNS OF ARCING.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004051400092	20040514	00092	SO  	2004	5	14	2004FA0000397    	2	20040501	G	7414	10400316	IMPULSE COUPLING			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  					MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	8AH	36   				P3370030	824766			PILOT REPORTED REAR ENGINE WAS HARD TO START.  AFTER TROUBLESHOOTING, THE LT MAGNETO WAS REMOVED.  UPON INSPECTION THE I	MPULSE COUPLING WOULD NOT ROTATE IN THE CORRECT DIRECTION.  THE MECH WAS NOT SURE IF WRONG IMPULSE COUPLING OR SPRING TU	RN BACKWARD.  DUE TO ONLY 36 HRS AND 1 YR 10 MO. SINCE ENGINE WAS REBUILT BY MFG.  MFG INSPECTED IMPULSE COUPLING AND DI	SCOVERED IMPULSE SPRING BROKEN.			1	H	7	2 	3O	3	O	 	A6CE    	E9CE
2004051400095	20040514	00095	SO  	2004	5	14	2004FA0000398    	1	20040317	G	5720		STRAP           			MICCO 	145A  	MAC145A     	5660000	SO  	LYC   	O540  	IO540T4B5   	41532	EA  					WING	CRACKED         	D			LM8S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	969WC	188  				260010				DURING AN ANNUAL INSPECTION THE BUTT WELDS IN THE LOWER MAIN SPAR REINFORCEMENT STRAP, APPROX 3.25 INCHES IB FROM EACH E	ND OF THE REINFORCEMENT STRAP, DO NOT HAVE PROPER PENETRATION AND ARE CRACKED THRU THE WELD.  MFG WAS CONTACTED AND REPA	IR INSTRUCTIONS WERE PROVIDED.  THE WELDS WERE PROPERLY PREPARED AND REWELDED IAW THE MFG INSTRUCTIONS BY A CERTIFIED WE	LDING REPAIRMAN.			1	L	7	1 	3O	3	O	RC	        	1E4
2004051400096	20040514	00096	SO  	2004	5	14	2004FA0000399    	1	20040317	G	5720		STRAP           			MICCO 	145A  	MAC145A     	5660000	SO  	LYC   	O540  	IO540*      	41532	EA  					WING	CRACKED         	D			LM8S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	969WC					260010	L2797148A			DURING AN ANNUAL INSPECTION THE BUTT WELDS IN THE LOWER MAIN SPAR REINFORCEMENT STRAP. APPROX 6.50 INCHES IB FROM EACH E	ND OF THE REINFORCEMENT STRAP.  DO NOT HAVE PROPER PENETRATION AND ARE CRACKED THRU THE WELD.  MFG WAS CONTACTED AND REP	AIR INSTRUCTIONS WERE PROVIDED.  THE WELDS WERE PROPERLY PREPARED AND REWELDED IAW MFG.				1	L	7	1 	3O	3	O	RC	        	1E4
2004051400067	20040514	00067	SO  	2004	5	14	2004FA0000400    	1	20040317	G	5740		ATTACH BRACKET  			MICCO 	145A  	MAC145A     	5660000	SO  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	LT WING	CRACKED         	D			LM8S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	969WC					260010	L2797148A	DY4978B		DURING AN ANNUAL INSPECTION THE WELD JOINT THAT ATTACHES THE UPPER WING SKIN ATTACH BRACKET TO THE UPPER MAIN WING SPAR 	CENTER SECTION JUST ABOVE THE UPPER LT WING ATTACHMENT FITTING WAS CRACKED.  MANUFACTURER WAS CONTACTED AND REPAIR INSTR	UCTIONS WERE PROVIDED.  THE LT WING WAS REMOVED FOR ACCESS.  THE LT WING WELD AREA WAS PROPERLY PREPARED AND REWELDED IA	W MM.			1	L	7	1 	3O	3	O	RC	        	1E4	5	C	P25EA
2005022200002	20050222	00002	GL  	2005	2	22	2004FA0000401    	1	20040513	G	3242	DP600	PAD             			AMTR  	VM1   	VM1         	05601TD	GL  										BRAKES	BINDING         	G				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			GL	07	626EA	133  				E180032				PILOT WAS IN PROCESS OF TAKEOFF ROLL, PILOT REPORTED A/C VEERED TO LT HITTING A RUNWAY LIGHT, WENT OVER SOME TERRAIN AND	 ENDED PARTIALLY SUBMERGED IN A BODY OF WATER. AN EXAMINATION OF THE A/C WAS CONDUCTED. THE A/C CONFIG INCLUDES A FREE C	ASTORING NOSE WHEEL AND BRAKES ARE OF A MOTO-GUZZI MOTORCYCLE. LT BRAKE FOUND TO BE DRAGGING SUBSTANTIALLY, AFFECTING TH	E SMOOTH ROTATION OF THE LT MAIN GEAR WHEEL. THE RT WHEEL AND BRAKE WERE SATISFACTORY. THE BRAKE WAS REMOVED. IT WAS FOU	ND THE DESIGN OF WIRE LOOP USED AS A MEANS TO HOLD BRAKE PADS ALIGNED, APPLIES CONSTANT RESISTANCE ON THE BRAKE PADS. TH	IS CONSTANT RESISTANCE PREVENTS THE BRAKE PADS FROM FLOATING AT ALL, THERE IS MINIMAL CLEARANCE,  FROM THE BRAKE DISC.	1	L	7	1 	3O			NT	EXPA1L71
2004051400116	20040514	00116	CE  	2004	5	14	2004FA0000402    	1	20040310	G	2752	1015210161R	ACTUATOR        			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TE FLAPS	SEPARATED       	D				D				RETURN TO BLOCK         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			WP	23	200ET		3753 			BC73				CREW RETRACTED FLAPS, FLAPS STOPPED .5000 WAY UP.  SPLIT FLAP SAFETY CIRCUIT STOPPED FLAP RETRACTION.  REVEALED THAT LT 	IB FLAP ACTUATOR HAD FAILED.  90 DEGREE DRIVE (P/N 50-380153-3) HAD COMPLETELY SEPARATED FROM MAIN BODY (SCREW DRIVE) OF	 ACTUATOR.  FAILURE WAS CAUSED BY LOCKING PIN IN 90 DEG. DRIVE WHICH HAD NOT BEEN PROPERLY ENGAGED INTO GROOVE IN MAIN B	ODY AT LAST O/H.  WEAR EVIDENCE SHOWS, PIN WAS IMPROPERLY ENGAGED IN MAIN BODY, DID NOT ENGAGE GROOVE APPROPRIATELY.  GR	OOVE AND PIN WORE UNTIL IT ALLOWED THE 90 DEGREE DRIVE TO DISENGAGE FROM MAIN BODY, 3352 LANDINGS AND 3753 HOURS SINCE A	CTUATOR ASSY WAS LAST OVERHAULED. THERE IS NO PRESCRIBED OVERHAUL TIME OR CYCLE LIMIT REQUIREMENT FOR THIS ACTUATOR.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA
2004051400117	20040514	00117	NM  	2004	5	14	2004FA0000403    	1	20040513	G	5310	41513128	SPAR CAP        	UNIVAR      		UNIVAR	415   	A2AALON     	0540104	NM  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	224PW	3798 				B253				DURING INSPECTION REQUIRED BY AD-2003-21-01, INTERGRANULAR AND EXFOLIATION CORROSION WAS DISCOVERED ON THE MAIN SPAR LOW	ER CAP. THE CENTER SECTION FRONT SPAR WILL REQUIRE REPLACEMENT.					1	L	7	1 	3O			 	A787
2004052000078	20040520	00078	CE  	2004	5	20	2004FA0000404    	1	20040517	G	3040	66004047	WINDSHIELD      			LEAR  	55    	55LEAR      	5170702	CE  										COCKPIT	CRACKED         	B				K				NONE                    				G			MULTIPLE FAILURE          			IN	INSP/MAINT     	1			CE	03	345RJ	6711 				078				SEVERE DELAMINATION OF OUTER PLY ON LT WINDSHIELD UNDER BLEED AIR DUCT AND ANTI-ICE SPRAY NOZZLE. SUSPECT SEALER FAILED 	AND ALLOWED METHYL ALCOHOL TO MIGRATE THROUGH SEALER AND SETTLE BETWEEN LAYERS AND DETERIORATED THE WINDSHIELD.					2	L	7	2 	4F			 	A10CE
2004052400059	20040524	00059	CE  	2004	5	24	2004FA0000406    	1	20040518	G	2520		SEAT            			LEAR  	35    	31A         	5170531	CE  										CABIN	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	766AJ					103				FOUND WIDTH BETWEEN CABIN SEATS WAS 8.5 INCHES IN AREA FROM FLOOR UP TO TWENTY FIVE INCHES ABOVE FLOOR. ARMRESTS WERE SO	URCE OF THIS DISCREPANCY.  IAW TYPE CERTIFICATE THIS AIRCRAFT MODEL IS SPECIFICALLY EXCLUDED FROM THE SERIES 24/25 AND 3	5/36 EQUIVALENT LEVEL OF SAFETY FINDING FOR 14CFR, PART 2, SECTION 25.815 ALLOWING LESS THAN NINE INCH AISLE WIDTH. TECH	 SUPPORT CONFIRMED THAT AISLE WIDTH ON THIS MODEL AIRCRAFT MUST BE AT LEAST NINE INCHES MEASURED FROM FLOOR UP TO TWENTY	 FIVE INCHES ABOVE FLOOR.  DETERMINED THAT CHAIRS HAD EXCESS FOAM PADDING ON LOWER SHROUD BASE. REMOVED FOAM PADDING FRO	M LOWER SHROUD BASE, THUS ALLOWING ARMREST TO MOVE FARTHER OB. THIS ENABLED A NINE INCH AISLE WIDTH TO BE OBTAINED.	2	L	7	2 	4F			RT	A10CE
2004052400055	20040524	00055	SO  	2004	5	24	2004FA0000407    	2	20040520	G	7322	45A10396512	CARBURETOR      			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	180C	4000 				32312				CARBURETOR STICKING AT FULL THROTTLE DUE TO WEAR OF THE FULL THROTTLE STOP.  IT WAS ACTUALLY GOING PAST FULL THROTTLE.  	THE PUMP LEVER ASSEMBLY WOULD TURN PAST THE AIR METERING PIN AND HANG UP THE THROTTLE SHAFT IN WIDE OPEN POSITION.					1	H	7	1 	3O	3	O	NC	5A6     	E273
2004052500031	20040525	00031	CE  	2004	5	25	2004FA0000408    	1	20040430	G	2110	45AS63019009	SHUTOFF VALVE   			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					AIR CONDITIONER	INOPERATIVE     	B			E81R	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	03	453CW					RK53				PILOT REPORTED EMERGENCY PRESSURIZATION SYSTEM CAME ON DURING TAKEOFF WITH AIR CONDITIONING FAIL ANNUNCIATOR LIGHT ILLUM	INATED.  TROUBLESHOT SYS IAW MM21-00-00.  FOUND RT PRESSURE REGULATING/SHUT-OFF VALVE (PRSOV) HAD FAILED, ALLOWING FULL 	BLEED AIR VOLUME THROUGH AT ALL THROTTLE SETTINGS.  REPLACED PRSOV WITH OVERHAULED VALVE IAW MM21-10-00.  ENVIRONMENTAL 	SYS OPERATIONAL CHECKS NORMAL ON GROUND RUN-UP.  MAINTENANCE RECORDS UNAVAILABLE.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA
2004052600056	20040526	00056	WP  	2004	5	26	2004FA0000409    	2	20040524	G	7250	8687466	GASKET          								GARRTT	TPE331	TPE33110    	01514	WP  					PLENUM	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25							P36043C			PLENUM FUEL NOZZLE BOSS BLANK-OFF COVER GASKET PN 868746-6 (BLEW OUT) ON 5 OF 5 BOSSES.  GASKET FAILURE ALLOWS HOT COMPR	ESSOR GAS LEAKING.  GASKETS WERE ALL REPLACED AND ENGINE WAS TEST RUN.  3 OF 5 NEW GASKETS (BLEW OUT) DURING TEST RUN.										4	T			E4WE
2004052600068	20040526	00068	WP  	2004	5	26	2004FA0000410    	2	20040524	G	7250	8687466	GASKET          								GARRTT	TPE331	TPE33110    	01514	WP  					PLENUM	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25							P36043C			PLENUM FUEL NOZZLE BOSS BLANK-OFF COVER GASKET PN 868746-6 (BLEW OUT) ON 5 OF 5 BOSSES.  GASKET FAILURE ALLOWS HOT COMPR	ESSOR GAS LEAKING.  GASKETS WERE ALL REPLACED AND ENGINE WAS TEST RUN.  3 OF 5 NEW GASKETS (BLEW OUT) DURING TEST RUN.										4	T			E4WE
2004052600070	20040526	00070	NM  	2004	5	26	2004FA0000411    	1	20040525	G	2910	280411	FUSE            			BOEING	737   	737300      	1384610	NM  										HYD SYSTEM	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05										INSIDE THE HYDRAULIC FUSE P/N 2-8041-1 IS A MATCHED SET OF PARTS P/N 7-2500-6 SEPARATED BY A FORMED WASHER.  UPON DISASS	EMBLY OF THESE PART THE FORMED WASHER HAS BEEN FOUND TO BE BROKEN.   THESE UNITS ARE SUPPLIED TO US FROM AN AIRLINE TO I	NSPECT, MANY OF THESE APPEAR TO SHOWING UP IN OUR SYSTEM.  HOURS ARE UNKNOWN. SERIAL NUMBERS RANDOM.				2	L	7	2 	4F			RT	A16WE
2004052600126	20040526	00126	CE  	2004	5	26	2004FA0000413    	1	20040506	G	7921	53E22144	VALVE           			CESSNA	150   	150J        	2071820	CE  	LYC   	O720  	IO720A1B    	41546	EA  					OIL COOLER	INOPERATIVE     	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	15	50786	12   				15069552	RL146754A			PILOT REPORTED HIGH OIL TEMPERATURE 220-225 DEGREES, REMOVED VALVE AND TESTED SIDE BY SIDE WITH NEW VALVE, OLD VALVE DID	 NOT CLOSE AT THE SAME RATE AS NEW VALVE, INSTALLED NEW VALVE AND OIL TEMP DECREASED TOO.					1	H	7	1 	3O	3	O	 	3A19    	1E15
2004052600130	20040526	00130	SO  	2004	5	26	2004FA0000414    	1	20040514	G	2197		WIRE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					FAN	BURNED          	C				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SO	15	661SC	5694 			010316	278054052				COCKPIT BEGAN TO FILL WITH SMOKE WHILE TAXIING FOR TAKE-OFF.  AIRCRAFT WAS SHUTDOWN AND UPON INSPECTION FOUND AVIONIOCS 	FAN TO BE BURNT ON CORNER WHERE WIRES ENTER FAN ASSEMBLY.  THE DATE STAMPED ON FAN IS NOV. 1979.  SUSPECT THE AGE AND TI	ME IN SERVICE WOULD BE THE CAUSE OF DEFECT.  THESE ELECTRICAL PARTS SHOULD BE INSPECTED CLOSELY FOR ANY SIGNS OF MELTING	 OR DISCOLORED PLASTIC.			1	L	7	2 	3O	3	O	 	1A10    	1E4
2004052600127	20040526	00127		2004	5	26	2004FA0000415    	4	20040422	G	2561	KSE35L8PO723E105	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										LIFE PRESERVER FAILED MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-12.  DOM:  DEC 1990.
2004052600128	20040526	00128		2004	5	26	2004FA0000416    	4	20040422	G	2561	AV35S211506300	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED MFG RECOMMENDED CELL PRESSURE TEST IAW MM 25-60-200.  LIFE PRESERVER MFG, DATE: AUSUST 1989.
2004052600129	20040526	00129	CE  	2004	5	26	2004FA0000417    	1	20040504	G	5511	053200196	SPAR            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					HORIZONTAL STAB	DAMAGED         	B			LC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	24787					172S8804				WHILE PERFORMING THE INSPECTIONS REQUIRED BY MFG SB04-55-01, FOUND THE RT SIDE HOLE IN THE HORIZONTAL STABILIZER AFT SPA	R ELONGATED.  THIS ELONGATION OPENED THE HOLE APPROX. .040 TO .050 INCHES IN THE 5 O`CLOCK DIRECTION (VIEWING THE HOLE F	ROM THE ACCESS IN THE TIO STABILIZER SKIN, LOOKING AFT).  ELONGATION DID NOT APPEAR TO EXTEND INTO THE PN 0531006-113 HO	RSESHOE FITTING ON THE VERTICAL STABILIZER OR INTO THE PN 05121595 AFT BULKHEAD.  ADDITIONALLY, THE BOLT DID NOT APPEAR 	TO BE WORN.  IAW MFG TECH SUPPORT, HOLE WILL BE ENLARGED TO NEXT BOLT SIZE AND APPROPRIATE SIZE BOLT WILL BE INSTALLED. 	 CONDITION SB IS INSPECTING FOR WAS NOT FOUND.	1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004052800057	20040528	00057	GL  	2004	5	28	2004FA0000418    	1	20040503	G	2720		CONTROL CABLE   			YAKLEV	YAK983	YAK50       	9830220	GL  										RUDDER	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07	150YK					822308				UPON CONDITIONAL INSPECTION, WHILE AIRCRAFT PARKED ON RAMP.  FOUND AFT RT RUDDER CABLE PULLEY OUT OF TERMINAL END.  SENT	 TO REPAIR SHOP AND WAS TOLD TERMINAL END WAS NOT SWAGED PROPERLY DURING ASSY.  INSPECTED AND REPLACED ALL CABLE CONTROL	S AS PRECAUTIONARY MEASURES.				1	L	7	1 	3R			RT	EXPA1L71
2004060100006	20040601	00006	SO  	2004	6	1	2004FA0000419    	2	20040406	G	8530	655474	CYLINDER        								CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	CRACKED         	B			VA1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										RAM AIRCRAFT HAS FOUND NUMEROUS CYLINDERS WITH LOW HOURS CRACKED IN AN AREA EXTENDING FROM FUEL INJECTOR BOSS AREA TO TH	E SPARK PLUG HOLE.  IN THIS AREA IS A MACHINED AREA WITHOUT SUFFICIENT RADIUS.  SUGGEST RADIUS OF THIS AREA TO PREVENT C	RACKING.									3	O			E7CE
2004060100008	20040601	00008	CE  	2004	6	1	2004FA0000421    	1	20040421	G	3610	99144022	PRECOOLER       			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					RT PYLON	SPLIT           	D				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CE	01	195ME	4395 				5250110				PILOTS NOTICED SLIGHT TEMP RISE IN RT ENGINE, AND AN UNUSUAL VIBRATION ALL ENGINE INDICATIONS IN NORMAL RANGES POSTFLIGH	T WALK AROUND NOTICED A SPLIT IN THE PRESSURIZATION (BLEED AIR) PRE-COOLER IN THE RT PYLON.  PAINT DISCOLORATION WAS NOT	ED NO DAMAGE TO ADJACENT STRUCTURES.  NO EVIDENCE OF IMPACT DAMAGE.  IT SHOULD BE NOTED THAT THIS PRE-COOLER IS UP-STREA	M OF THE BLEED AIR SHUT OFF VALVES.  INCLUDE INSPECTION AT PRE-POST FLIGHT.			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL
2004060100009	20040601	00009	SO  	2004	6	1	2004FA0000422    	1	20040301	G	7120	5501111501	MOUNT           			AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	74608	4700 				AA5B0282				DURING ANNUAL INSP, A CRACK WAS NOTED IN THE LOWER HORIZONTAL CROSSPIECE OF THE ENGINE MOUNT.  THE CRACK IS APPROX .5000	 INCH AWAY FROM THE PILOT SIDE END OF THIS TUBE, NEAR THE WELD THAT ATTACHES THIS TUBE TO THE DIAGONAL TUBE THAT ATTACHE	S TO THE FIREWALL LOWER PILOT SIDE SUPPORT BRACKET.  THIS SAME CRACK LOCATION HAS BEEN SEEN IN SEVERAL AIRCRAFT.  APPEAR	S TO BE A POINT OF HIGH VIBRATION INDUCED STRESS, AS THERE IS LITTLE LOAD ON THE PART DURING OPERATION.			1	L	7	1 	3O	3	O	 	A16EA   	E286
2004052700078	20040527	00078	SW  	2004	5	27	2004FA0000423    	1	20040325	G	6220	K910005007	PIN             			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					LT ROTOR HUB	UNSERVICEABLE   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	358KA	269  				A940029				THE LEADING EDGE OF THE LT SIDE TEETER PIN WAS DAMAGED (MUSHROOMED).  FURTHER INSPECTION SHOWED THAT THE HEAD SIDE OF TH	E INSIDE DIAMETER OF THE LINER THAT THE TEETER PIN SITS IN IS ALSO DAMAGED.  THE LINER IS DEFORMED AND PROTRUDES IN AN I	RREGULAR MANNER ON THE LEADING EDGE.  THE TEETER PIN SHOWS CROSS-CORNER WEAR.  THE TEETER THRUST WASHER ON THE HEAD SIDE	 WAS ALSO MISSING.  THERE WAS RESIDUE OF THE COATING ON THE ID OF THE LINER.  THE DAMAGES EXCEED THE INSPECT LIMITS ON T	HE TEETER PIN NON-CRITICAL AREA IAW THE CRITERIA ON THE ROTOR HUB ASSY INSP.  RESIDUE WAS FOUND ON THE HEAD SIDE OF THE 	RIGHT TEETER PIN.  PLAY GREATER THAN .015 ON THE TEETER PIN ALLOWABLE PLAY LIMITS WAS ALSO NOTED.	1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA
2004060100102	20040601	00102	CE  	2004	6	1	2004FA0000424    	1	20040529	G	5412	05131092956	DOUBLER         			CESSNA	172   	172N        	2072434	CE  										FIREWALL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	734BZ	3695 				17268738				DURING ANNUAL INSPECTION FOUND POPPED RIVET HEADS IN FIREWALL DOUBLERS, REMOVED DOUBLERS FOUND EXFOLIATION EXCEEDING 40 	PERCENT THICKNESS ON BACK SIDE OF DOUBLERS, REPLACED DOUBLER, RECOMMEND CLOSE INSPECTION OF RIVET HEADS IN THIS AREA.					1	H	7	1 	3O			NT	3A12
2004071200182	20040712	00182	CE  	2004	7	12	2004FA0000425    	1	20040601	G	5751	6524010810	SKIN            			CESSNA	500   	560CESSNA   	2076750	CE  										AILERON	DELAMINATED     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		5511 								AILERON TRAILING EDGE DELAMINATED WITH LOSS OF MATERIAL.						2	L	7	2 	4F			RT	A22CE
2004061400212	20040614	00212	CE  	2004	6	14	2004FA0000427    	1	20040506	G	2421	643840	BEARING         			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					ALTERNATOR	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	59292					21060196	294956			BEARING AT PULLEY END, PN 643840, FAILED, ALLOWING BELT TO BECOME OUT OF ALIGNMENT.  BELT CAME OFF OF PULLEY CAUSING ALT	ERNATOR TO BECOME INOPERATIVE.					1	H	7	1 	3O	3	O	 	3A21    	E5CE
2004061400220	20040614	00220	SO  	2004	6	14	2004FA0000428    	1	20040428	G	2820	231311	LINE            			BALWKS	FIREFY	FIREFLY11   	1050125	SO  										FUEL DIST	INADEQUATE      	B			B24R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	2192Y	159  				F112004				UPON INSPECTION OF VALVE LINE SEVERAL LOCATIONS WERE FOUND WHERE THE INNER KEVLAR LINE HAS BUNCHED UP AND BECAME EXPOSED	 THROUGH THE OUTER PROTECTIVE NYLON COVER.  THIS WAS FOUND IN VARIOUS PLACES ALONG LENGTH OF LINE.  EACH OF THE PEA SIZE	D EXPOSED AREAS HAVE ABRASION ON THE EXPOSED KEVLAR.  THIS LINE WAS REMOVED FROM SERVICE.				1	B	0	0 	  			 	A14SO
2004061400265	20040614	00265	CE  	2004	6	14	2004FA0000429    	1	20040527	G	2730	0510105291	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					ELEVATOR	BROKEN          	B			KH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	4366R					17263117				ANNUAL INSPECTION FOUND UPPER ELEVATOR CABLE WITH SOME BROKEN STRANDS.  REPLACED BOTH CABLES BOTH AIRCRAFT HAVE A LITTLE	 OVER 5000.0 HOURS ON THEM.					1	H	7	1 	3O	3	O	NT	3A12    	E274
2004061400202	20040614	00202	CE  	2004	6	14	2004FA0000430    	1	20040527	G	2730	0510105291	CONTROL CABLE   			CESSNA	172   	172P        	2072436	CE  										ELEVATOR	BROKEN          	B			KH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	53373					17274734				ANNUAL INSPECTION FOUND UPPER ELEVATOR CABLE WITH SOME BROKEN STRANDS.  REPLACED BOTH CABLES.  AIRCRAFT HAS A LITTLE OVE	R 5000.0 HOURS.					1	H	7	1 	3O			NT	3A12
2004061400203	20040614	00203		2004	6	14	2004FA0000431    	4	20040511	G	2561	D21343153	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE PRESERVER FAILED, MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-05.
2004061400269	20040614	00269	SO  	2004	6	14	2004FA0000432    	2	20040521	G	7314	6467682	PUMP            			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	93379		3    			21060383	506168			ENGINE DRIVEN FUEL PUMP NO METERED OR UN METERED FUEL PRESSURE WHILE ENGINE RUNNING.  FUEL PUMP RECENTLY INSTALLED HAD 2	.7 HOURS ON IT, AFTER OVERHAUL.  INSTALLED NEWLY OVERHAULD PUMP.  OPS CHECK GOOD.  PROBABLE CAUSE OF PUMP FAILURE, UNKNO	WN.				1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004061400264	20040614	00264	CE  	2004	6	14	2004FA0000433    	1	20040514	G	2130	26011	VALVE           			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					EMER PRESS	FAILED          	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	03	900JD		556  			6500213				DURING CLIMBOUT FROM MLI, THE RT EMERGENCY PRESSURIZATION VALVE OPENED ALLOWING HIGH PRESSURE BLEED AIR TO ENTER THE CAB	IN.  THIS CAUSED THE CABIN TEMP TO RISE AND A LOUD AUDIBLE RUSH OF AIR TO BE HEARD IN THE CABIN.  THE FLIGHT CREW ELECTE	D TO RETURN TO POINT OF DEPARTURE (MLI).  MAINTENANCE CONFIRMED THE FAILURE AND REPLACED THE VALVE.  GROUND TESTS CONCLU	DED THAT THE NEW VALVE WAS WORKING PROPERLY.  A FLIGHT WAS INITIATED WITHOUT PASSENGERS TO CONFIRM THAT THERE WERE NO MO	RE ANOMALIES WITH THE EMERGENCY PRESSURIZATION SYSTEM.		2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004062100144	20040621	00144	CE  	2004	6	21	2004FA0000434    	1	20040609	G	5753		FLAP TRACK      			CESSNA	206   	T206H       	2073303	CE  										WING	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	2378X					T20608023				MECHANIC HEARD (POPPING) NOISE WHEN FLAPS WERE EXTENDED OR RETRACTED.  FOUND THE UPPER FLAP TRACK HARDWARE WAS HITTING T	HE FLAP WELL CUT OUTS.  THE BOLTS WERE INSTALLED FACING OB AT THE FACTORY.  REVERSED HARDWARE AND PROBLEM WENT AWAY.					1	H	7	1 	3O			RT	A4CE
2004062100168	20040621	00168	CE  	2004	6	21	2004FA0000435    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	4352V					7261				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	)  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	TC121
2004062100124	20040621	00124	CE  	2004	6	21	2004FA0000436    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBS	R755  	R7557       	35003	EA  					AILERON	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	1030D					7643				INSPECTED ORIGINAL MAGENSIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	5E11
2004062200210	20040622	00210	CE  	2004	6	22	2004FA0000437    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9836A					7529				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESES BRACKET	S).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			NC	A790
2004062200156	20040622	00156	CE  	2004	6	22	2004FA0000438    	1	20040525	G	5751	03227091	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4426C					16011				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORHTY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			NC	A790
2004062200149	20040622	00149	CE  	2004	6	22	2004FA0000439    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	R7557       	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9331A					7410				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR AL OF THE FOLLOWING CONDITIONS:  SEVERELY CORRO	DED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEET	.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESES BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	 	A790    	5E11
2004062300039	20040623	00039	CE  	2004	6	23	2004FA0000440    	1	20040525	G	5751	0322790	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1508D					7730				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			NC	A790
2004062300040	20040623	00040	CE  	2004	6	23	2004FA0000441    	1	20040525	G	5751	03227091	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4345V					7272				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			NC	A790
2004062200155	20040622	00155	CE  	2004	6	22	2004FA0000442    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195AC					7907				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300041	20040623	00041	CE  	2004	6	23	2004FA0000443    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	41X					7775				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERLY CORRO	DED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEET	.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS.  (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKET	S).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			 	A790
2004062200150	20040622	00150	CE  	2004	6	22	2004FA0000444    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2194C					16179				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			 	A790
2004062300042	20040623	00042	CE  	2004	6	23	2004FA0000445    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	PWA   	R985  	R985*       	52008	NE  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4383V					7305				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	5E1
2004062200209	20040622	00209	CE  	2004	6	22	2004FA0000446    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2152C					16137				INSPECTED ORIGINAL MAGNESIUM INBOARD AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY	 CORRODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTIN	G FEET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS ( THIS CONDITION FOUND ON TWO DIFFERENT  SETS OF THESE B	RACKETS).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			 	A790
2004062200152	20040622	00152	CE  	2004	6	22	2004FA0000447    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195EL					7794				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			NC	A790
2004062200207	20040622	00207	CE  	2004	6	22	2004FA0000448    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3050B					7933				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	)  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R			 	A790
2004062200151	20040622	00151	CE  	2004	6	22	2004FA0000449    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4381V					7303				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING AND/OR MOUNTING FEET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS	 (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNA	IRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062200153	20040622	00153	CE  	2004	6	22	2004FA0000450    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4331N					7078				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	)  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062200208	20040622	00208	CE  	2004	6	22	2004FA0000451    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195SC					7402				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062200154	20040622	00154	CE  	2004	6	22	2004FA0000452    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9810A					7489				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300104	20040623	00104	CE  	2004	6	23	2004FA0000453    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3006B					7889				INSPECTED ORIGINAL MAGNESIUM INBOARD AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY	 CORRODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTIN	G FEET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRA	CKETS).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062200193	20040622	00193	CE  	2004	6	22	2004FA0000454    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	CONT  	R670  	W670*       	17016	SO  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3089B					7974				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	)  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	NC	A790    	E162
2004062200176	20040622	00176	CE  	2004	6	22	2004FA0000455    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	R7557       	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1LE					7729				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).  WE ARE FINDING 85 PERCENT OF THE ORIGINAL BRACKETS UNAIRWORTHY DUE TO CORROSION, 35 PERCENT ARE CRACKED.			1	H	7	1 	3R	3	R	 	A790    	5E11
2004062200195	20040622	00195	CE  	2004	6	22	2004FA0000456    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2158C					16143				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING AND/OR MOUNTING FEET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS	 (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS).				1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200203	20040622	00203	CE  	2004	6	22	2004FA0000457    	1	20040525	G	5751		HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	90K					7439				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200211	20040622	00211	CE  	2004	6	22	2004FA0000458    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	10N					7657				INSPECTED ORIGINAL MAGNESIUM INBOARD AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY	 CORRODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTIN	G FEET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRA	CKETS).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300028	20040623	00028	CE  	2004	6	23	2004FA0000459    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  	CONT  	R670  	W670*       	17016	SO  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1551D					7773				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS CRACKING AND/OR MOU	NTING FEET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE	 BRACKETS).			1	H	7	1 	3R	3	R	NC	A790    	E162
2004062300061	20040623	00061	CE  	2004	6	23	2004FA0000460    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4372N					7034				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKEST AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ONTWO DIFFERENT SETS OF THESE BRACKETS)	.			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062300055	20040623	00055	CE  	2004	6	23	2004FA0000461    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2112C					16097				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	)			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200157	20040622	00157	CE  	2004	6	22	2004FA0000462    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  	CONT  	R670  	W670*       	17016	SO  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9359A					7522				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	E162
2004062300044	20040623	00044	CE  	2004	6	23	2004FA0000463    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4332V					7238				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC121
2004062300037	20040623	00037	CE  	2004	6	23	2004FA0000464    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	6857D					7848				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS: SEVERELY CORRO	DED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEET	.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS)	.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300035	20040623	00035	CE  	2004	6	23	2004FA0000465    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2139C					16124				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300038	20040623	00038	CE  	2004	6	23	2004FA0000466    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4462C					16047				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	.			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300062	20040623	00062	CE  	2004	6	23	2004FA0000467    	1	20040525	G	5751		HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3042B					7925				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300049	20040623	00049	CE  	2004	6	23	2004FA0000468    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195WG					7926				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062200158	20040622	00158	CE  	2004	6	22	2004FA0000469    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9334A					7413				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING  BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FE	ET.  PRIMER AND/OR BODY FILLER TO HIDE SETS OF THESE BRACKETS).				1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062200192	20040622	00192	CE  	2004	6	22	2004FA0000470    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195H					7200				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/ OR MOUNTING FE	ET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKET	S).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300022	20040623	00022	CE  	2004	6	23	2004FA0000471    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4448C					16033				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200159	20040622	00159	CE  	2004	6	22	2004FA0000472    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9339A					7419				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T. PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS)	.			1	H	7	1 	3R			NC	A790
2004062300023	20040623	00023	CE  	2004	6	23	2004FA0000473    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2193C					16178				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200162	20040622	00162	CE  	2004	6	22	2004FA0000474    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	8266R					7550				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESES BRACKET	S).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300090	20040623	00090	CE  	2004	6	23	2004FA0000475    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	4468C					16053				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300045	20040623	00045	CE  	2004	6	23	2004FA0000476    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  	JACOBS	R915  	L6          	35005	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1525D					7747				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC195
2004062300048	20040623	00048	CE  	2004	6	23	2004FA0000477    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195TG					7341				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/ OR MOUNTING FE	ET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKET	S).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062200160	20040622	00160	CE  	2004	6	22	2004FA0000478    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4494C					16078				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300024	20040623	00024	CE  	2004	6	23	2004FA0000479    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3869V					7330				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300050	20040623	00050	CE  	2004	6	23	2004FA0000480    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1524D					7746				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062200161	20040622	00161	CE  	2004	6	22	2004FA0000481    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3035B					7918				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200163	20040622	00163	CE  	2004	6	22	2004FA0000482    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195BT					16176				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300025	20040623	00025	CE  	2004	6	23	2004FA0000483    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195ST					7527				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKES SPANNING COMPLETELY ACROSS THE BEARING BOSS AND OR MOUNTING FE	ET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKET	S).			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062300091	20040623	00091	CE  	2004	6	23	2004FA0000484    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	4301V					7205				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300026	20040623	00026	CE  	2004	6	23	2004FA0000485    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1022D					7630				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200206	20040622	00206	CE  	2004	6	22	2004FA0000486    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2141C					16126				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062200169	20040622	00169	CE  	2004	6	22	2004FA0000487    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	RROYCE	VIPER 	VIPER522    	54552	EU  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4408C					7993				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	4	J	NC	A790    	E3EU
2004062300013	20040623	00013	CE  	2004	6	23	2004FA0000488    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	60W					7385				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING  BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FE	ET.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKET	S).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300064	20040623	00064	CE  	2004	6	23	2004FA0000489    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R915  	L6          	35005	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9855A					7548				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC195
2004062300014	20040623	00014	CE  	2004	6	23	2004FA0000490    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R915  	L6          	35005	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9855A					7548				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC195
2004062300001	20040623	00001	CE  	2004	6	23	2004FA0000491    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1075D					7687				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062300015	20040623	00015	CE  	2004	6	23	2004FA0000492    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	47KL					7053				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS ( THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKET	S).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300008	20040623	00008	CE  	2004	6	23	2004FA0000493    	1	20040525	G	5751		HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	5N					7356				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO  DIFFERENT SETS OF THESE BRACKET	S).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300009	20040623	00009	CE  	2004	6	23	2004FA0000494    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4666T					7802				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC121
2004062300010	20040623	00010	CE  	2004	6	23	2004FA0000495    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3890V					7361				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITION:  SEVERELY CORRO	DED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEET	.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS)	.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300004	20040623	00004	CE  	2004	6	23	2004FA0000496    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195VF					7268				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300075	20040623	00075	CE  	2004	6	23	2004FA0000497    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4347V					7256				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS. CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEET	.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS)	.			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300016	20040623	00016	CE  	2004	6	23	2004FA0000498    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9303A					7382				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300011	20040623	00011	CE  	2004	6	23	2004FA0000499    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9818A					7497				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300002	20040623	00002	CE  	2004	6	23	2004FA0000500    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195P					7218				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC121
2004062300076	20040623	00076	CE  	2004	6	23	2004FA0000501    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3083B					7968				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062300005	20040623	00005	CE  	2004	6	23	2004FA0000502    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3443V					7133				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC121
2004062300077	20040623	00077	CE  	2004	6	23	2004FA0000503    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  	JACOBP	R755  	R755B1      	35007	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4418C					16003				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC237
2004062300006	20040623	00006	CE  	2004	6	23	2004FA0000504    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A1      	35006	SW  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1566D					7788				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	NC	A790    	TC237
2004062300017	20040623	00017	CE  	2004	6	23	2004FA0000505    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195         	2073102	CE  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4051A					7318				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R			NC	A790
2004062300003	20040623	00003	CE  	2004	6	23	2004FA0000506    	1	20040525	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195KR					7160				INSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS:  SEVERELY CORR	ODED BRACKET BODY AROUND MOUNT AND BEARING BOSS.  CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEE	T.  PRIMER AND/OR BODY FILLER TO HIDE CRACKING OF BRACKETS (THIS CONDITION FOUND ON TWO DIFFERENT SETS OF THESE BRACKETS	).			1	H	7	1 	3R	3	R	 	A790    	TC121
2004062300074	20040623	00074	EA  	2004	6	23	2004FA0000507    	2	20040413	G	8530	5015	STUD            			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A2B    	41514	EA  					CYLINDER	BROKEN          	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	7987L	2702 	849  			MA148	L299351A			NR 4 DECK STUD BROKEN AT 8 OCLOCK POSITION.						1	L	7	1 	3O	3	O	 	A1CE    	1E10
2004062300012	20040623	00012	EA  	2004	6	23	2004FA0000508    	2	20040504	G	8530		STUD            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					NR 4 CYLINDER	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	174PC					287425187				PILOT REPORTS EXHAUST PIPE LOOSE ON NR 4 CYLINDER.  FOUND 4 STUDS SHEARED ON CYLINDER HOLD DOWN FLANGE.  THIS CAUSED EXH	AUST TO VIBRATE LOOSE.  CHECK NUTS ON ANNUAL OR ANYTIME EXHAUST STUDS DROP OUT.					1	L	7	1 	3O	3	O	 	2A13    	E274
2004063000113	20040630	00113	SO  	2004	6	30	2004FA0000509    	1	20040504	G	3240		BRAKE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					LANDING GEAR	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2382M					287890250				DURING ANNUAL, SPONGY BRAKE FOUND.  UNABLE TO BLEED.  FOUND (AGED) HYD OIL LEAD TO DETERIORATION OF SEALS IN 4 TOE BRAKE	S AND PARKING BRAKE.  NO RECORD OF ANY PREVIOUS REPAIR.  SUGGEST AC OVER 10 YEAR OLD HAVE SYSTEM FLUSH AND SEAL REPLACEM	ENT.				1	L	7	1 	3O	3	O	 	2A13    	E286
2004063000125	20040630	00125	CE  	2004	6	30	2004FA0000510    	1	20040602	G	2420	DOFF10300BR	ALTERNATOR      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O540  	O540*       	41532	EA  					ENGINE	DETACHED        	D			BLVR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	17	5301R					172RG0050				PILOT REPORTED HE THOUGHT ALTERNATOR THREW THE BELT.  REMOVED THE COWLING, FOUND ALTERNATOR LYING IN ENGINE COMPARTMENT,	 WIRING INTACT, COOLING FINS TORN OFF BELT PULLEY, BELT SHREDDD.  AN7-40A MOUNTING BOLT NOT FOUND.  BELT ADJUSTMENT BRAC	KET AN5 ATTACH BOLT FOUND IN COWLING WITH SAFETY WIRE, BOLT HOLE THREADS IN ENGINE CASE STRIPPED/WORN.  INSTALLED HELI-C	OIL IN BOLT HOLE.  INSTALLED EXCHANGE ALTERNATOR WITH NEW ATTACH HARDWARE AND BELT. RUN-UP CHECK NORMAL.  PROBABLE CAUSE	 IS FAILURE OF AN7 BOLT OR NUT, ALLOWING ALTERNATOR TO BECOME UN-ATTACHED.		1	H	7	1 	3O	3	O	 	3A17    	E295
2004063000005	20040630	00005	SO  	2004	6	30	2004FA0000511    	1	20040528	G	3260	7642603	DRAG BRACE      			PIPER 	PA28  	PA28R201T   	7102813	SO  										NLG	CRACKED         	B			TUDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	2919Q	4273 				28R7703079				PILOT REPORTED A LOUD SOUND SIMILAR TO A RIFLE SHOT WHILE IN CRUISE FLIGHT AT 7500 FEET MSL.  IMMEDIATELY, THE LANDING G	EAR UNSAFE LIGHT ILLUMINATED.  PRIOR TO LANDING, HE LOWERED THE GEAR NORMALLY AND GOT DOWN AND LOCKED INDICATIONS FOR AL	L THREE LANDING GEAR.  LANDING WAS NORMAL.  THE UPPER DRAG BRACE WAS CRACKED JUST FORWARD OF THE AREA WHERE THE LANDING 	ACTUATOR ATTACHES TO THE BRACE.  THERE DID NOT APPEAR TO BE ANY OTHER DAMAGE IN THE AREA.  A POSSIBLE CAUSE OF FAILURE I	S FATIGUE DUE TO THE NR OF HOURS OR CYCLES ON THE PART. (SW13200404055)		1	L	7	1 	3O			 	2A13
2004063000134	20040630	00134	GL  	2004	6	30	2004FA0000512    	3	20040303	G	6110	B24521	CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HC83X	HC83X*      	GL  	PROPELLER	DAMAGED         	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17					BP9634					CYLINDER (PN B2452-1) SEPARATED FROM PROPELLER ON GROUND RUN.  INSPECTION SHOWED THREAD DAMAGE OF CYLINDER.  AFTER DISCU	SSION WITH MANUFACTURER THE LIKELY CAUSE IS DUE TO HIGH PRESSURE FROM GOVERNOR, USUALLY CAUSED BY STICKING PRESSURE RELI	EF VALVE.				1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P884
2004063000010	20040630	00010	SO  	2004	6	30	2004FA0000513    	1	20040519	G	7160	67775000	DOOR            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					HEAT BOX	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	07	2495M					28R7837090				PARTIAL LOSS OF ENGINE POWER OCCURRED JUST AFTER TAKEOFF.  THE MANIFOLD PRESSURE DROPPED TO 15 INCHES HG, RPM DROPPED TO	 1900.  PRE TAKEOFF ENGINE RUN UP,  ALTERNATE AIR CHECK WAS REPORTED AS NORMAL.  A POST FLIGHT INSPECTION REVEALED THAT 	ALTERNATE AIR (HEAT BOX) DOOR HAD SEPARATED FROM ALTERNATE AIR BOX ASSY, WAS INGESTED INTO FUEL SERVO INTAKE, PARTIALLY 	BLOCKED ENGINE INDUCTION AIR FLOW AND RESULTED IN A PARTIAL LOSS OF POWER.  MS20470AD3 RIVETS (3EA) THAT SECURE DOOR TO 	AIR BOX ASSY HAD FAILED.  IMPROPERLY BUCKED RIVETS DUE TO EXCESSIVE SPRING TENSION DURING ASSY AND/OR TOO MUCH SPRING TE	NSION FOR THE RIVETS TO BEAR.	1	L	7	1 	3O	3	O	 	2A13    	1E10
2004063000023	20040630	00023	SO  	2004	6	30	2004FA0000514    	1	20040524	G	2622		FIRE BOTTLE     			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					LEFT	MISMARKED       	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	05	3PG	4366 				1260				DURING THE LT FIRE BOTTLE WEIGHT CHECK, THE INSPECTOR NOTICED THE COLOR OF THE CABLE MARKER TIES AND THE HEAT SHRINK SLE	EVES FOR THE LT BOTTLE, DID NOT MATCH THE COLOR OF THE DECALS ON THE PLUMBING, EVEN THOUGH THE NOMENCLATURE ON THE TIES 	IS CORRECT.  ASC WAS INSTALLED IN PRODUCTION IN 1995.  AD WAS ISSUED TO ENSURE ASC146A IS INCORPORATED.  ORDERED REPLACE	MENT TIES, SHRINK SLEEVES, AND TERMINALS TO CORRECT THE PROBLEM.  NOTIFIED THE MFG AND RECOMMENDED THEY CHECK OTHER GIV`	S IN THIS SN RANGE.		2	L	7	2 	4F	4	F	RT	A12EA   	E25NE
2004063000054	20040630	00054	EA  	2004	6	30	2004FA0000515    	2	20040603	G	7414	LC100101	REGULATOR       			AMTR  	MURPHY	MURPHYREBEL 	05623QL	GL  	LYC   	O320  	O320E2D     	41508	EA  					SPARK ADVANCE	INOPERATIVE     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	7229N					422REB				AC IN FOR NO SPARK DURING START-UP.  REMOVED LT AND RT MAGNETOS AND SPARK ADVANCED REGULATOR.   OWNER INSTALLED BUSH KIT	 MODIFICATION, LT MAG WITH IMPULSE COUPLING.  MAG, NR 4755, SN 04030730.  MAGS TIMING SET WITH T-300 IGNITION TIMING TOO	L.  PERFORMED GROUND OP CHK.  MAG CHECKS AT 1700 RPM 50 FOR BOTH MAGS SMOOTH.  BOTH MAGS CHECKED AT FULL POWER. ENG CK G	OOD.  BEFORE FLIGHT MAG CK WAS GOOD.  FIRST TAKE-OFF NO PROBLEMS NOTED.  SECOND TAKE-OFF, ENG LOST POWER, RAN VERY ROUGH	.  POST FLIGHT, BOTH MAGS CHK NORMAL.  ON FULL PWR, OPS NORMAL FOR 1 MINUTE, WITHOUT WARNING, SUDDEN POWER LOSS.  ENG BA	CKFIRING, RUNNING ROUGH.  RPM DROPPED FROM 2450 TO 2100 RPM.  REDUCED TO 1900 RPM, ENG SMOOTHED OUT WITH NORMAL MAG CK.	1	H	7	1 	3O	3	O	NC	EXPA1H71	E274
2004063000041	20040630	00041	CE  	2004	6	30	2004FA0000516    	1	20040519	G	3231		ARM             			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  					NLG DOOR	INOPERATIVE     	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	07	4916U					21058616	112609R			NOSE GEAR ON THIS AC WOULD NOT EXTEND DURING NORMAL, SUBSEQUENT EMERG L/G EXTEND PROCEDURE.  UPON JACKING AC, FREEING NO	SE GEAR, IT WAS DISCOVERED NOSE L/G DOOR ACTUATION ARM AND ROLLER ASSY WAS POSITIONED ON AFT SIDE OF NOSE GEAR FORK.  WH	EN WEIGHT OF AC WAS ONCE AGAIN ON NOSE GEAR, NOSE L/G STRUT WAS COMPLETELY COLLAPSED.  IT IS POSSIBLE THAT AT THE TAKE-O	FF PRIOR TO THIS INCIDENT, THAT NOSE GEAR DID NOT EXTEND FULLY,  DOOR ACTUATION ARM WAS ABLE TO ROLL TO  AFT SIDE OF NOS	E L/G FORK.  AC WAS PREVIOUSLY MODIFIED.  STC NR SA 3612SW, WHICH ELIMINATES MAIN GEAR DOORS AND MODIFIES NOSE GEAR DOOR	 ACTUATION METHOD BY INSTALLING MECHANICAL ARM, ROLLER ASSY AGAINST NOSE GEAR FORK ARE MISSING ON THIS INSTALLATION.	1	H	7	1 	3O	3	O	 	3A21    	E5CE
2004063000099	20040630	00099	GL  	2004	6	30	2004FA0000517    	1	20040526	G	3220		BRACE           			AMTR  	GAIR  	GLASAIRIII  	05691HK	GL  	LYC   	O540  	IO540*      	41532	EA  					NLG	INOPERATIVE     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	27001					3045				IN FLIGHT, AC LOST HYDR PRESSURE FOR UNRELATED CAUSE.  HYDR PRESSURE NORMALLY ASSISTS L/G TO REMAIN IN DOWN AND LOCKED P	OSITION.  ON LANDING, AC TOUCHED DOWN NORMALLY.  ON ROLLOUT, NOSE LANDING COLLAPSED.  LANDING GEAR SYS IS DESIGNED TO RE	MAIN DOWN AND LOCKED WITHOUT AID OF HYDR PRESSURE BY USE OF SPRINGS THAT SHOULD APPLY TENSION TO OVERCENTER DESIGN OF LA	NDING GEAR BRACES.  NOSE LANDING GEAR BRACE ONLY GOES OVER CENTER A SMALL AMOUNT, JUST A COUPLE OF DEGREES.  LOW OVERCEN	TER ASSIST SPRING TENSION COUPLED WITH A SMALL AMOUNT OF OVERCENTER TRAVEL ALLOWED NOSE GEAR TO COLLAPSE IN ABSENCE OF H	YDR PRESSURE.  ON JACKS N/G COULD BE MADE TO UNLOCK WITH A MODEST KICK TO THE NOSEWHEEL. (SW17200407156)	1	L	7	1 	3O	3	O	RT	EXPA1L71	1E4
2004063000100	20040630	00100	GL  	2004	6	30	2004FA0000518    	1	20040608	G	5330		FABRIC          			AMTR  	SKYBLT	SKYBOLT     	       	GL  	LYC   	O540  	IO540*      	41532	EA  					RT WING	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	25BM	116  				SBM001				5 FEET OF THE TOP RT WING FABRIC FAILED.  POLYFIBER AC COATINGS TB 89-1D.  STATES FABRIC WEIGHING LESS THAN 2.4 OZ SHOUL	D BE USED ON AC WITH ENGINES UP TO 145 HORSEPOWER THIS AC HAD A 300 HP ENGINE INSTALLED LT WING HAD BROKEN RIB STITCHING	 BUT FABRIC HAD NOT FAILED YET.  (SW15200410524)				1	Q	7	1 	3O	3	O	 	EXPA1Q71	1E4
2004063000098	20040630	00098	NE  	2004	6	30	2004FA0000520    	2	20040423	G	7250	3020159	RETAINING RING  								PWA   	PT6   	PT6A34AG    	52053	NE  					TURBINE SECTION	DAMAGED         	B			CP2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15							PH0094			DISASSEMBLY OF THE HOT SECTION, SMALL EXIT DUCT REVEALED THE SEGMENT RETAINING RING ENDS STACKED AND APPROXIMATELY 4-4.5	 INCHES OF THE RING OUT OF PLACE.  SEGMENTS IN THE AFFECTED AREA WERE BEGINNING TO MOVE OUT OF OPERATING POSITION.  THE 	HOT SECTION WAS BEING INSPECTED AS PART OF A LIGHT OVERHAUL OF THE UNSERVICEABLE CONDITIONS RELATING TO THE ENGINE.  THE	 HOT SECTION WAS IN OTHERWISE SERVICEABLE CONDITION.  UNCONTAINED SEGMENTS CAN MOVE INTO THE PATH OF THE COMPRESSOR TURB	INE BLADES DESTROYING HOT SECTION SEALING, RESULTING IN LOSS OF POWER.							4	T			E4EA
2004063000081	20040630	00081	SO  	2004	6	30	2004FA0000521    	1	20040415	G	8012	9937711	SWITCH          			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	103JH					347570087				WATER FROM WASHING THE AIRCRAFT WENT DOWN LEFT SIDE WINDOW INTO SWITCH PANEL CAUSING MASTER SWITCH TO ACTIVATE MASTER SO	LENOID (WHEN IN OFF POSITION).  THE WATER FROM WASHING ALSO CAUSED LT ENGINE STARTER SWITCH TO ACTIVATE STARTER SPINNING	 PROPELLER (WHEN IN OFF POSITION)  NOTE:  PROP STARTED TO SPIN ABOUT 1 HOUR AFTER WASHING.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004063000124	20040630	00124	SO  	2004	6	30	2004FA0000522    	1	20040415	G	2400	9937713	MASTER SWITCH   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					COCKPIT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	103JH					347570087				WATER FROM WASHING THE AIRCRAFT WENT DOWN LEFT SIDE WINDOW INTO SWITCH PANEL CAUSING MASTER SWITCH TO ACTIVATE MASTER SO	LENOID (WHEN IN OFF POSITION).  THE WATER FROM WASHING ALSO CAUSED LT ENGINE STARTER SWITCH TO ACTIVATE STARTER SPINNING	 PROPELLER (WHEN IN OFF POSITION).  NOTE:  PROP STARTED TO SPIN ABOUT 1 HOUR AFTER WASHING.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004063000118	20040630	00118	CE  	2004	6	30	2004FA0000523    	1	20040601	G	5520	1016100198	TORQUE TUBE     			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ELEVATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	7232R	8067 				BL69				DURING PHASE INSPECTION, THE RT ELEVATOR CONTROL TORQUE TUBE THAT ATTACHES TO THE IB END RIB OF THE RT ELEVATOR WAS FOUN	D TO HAVE PLAY BETWEEN THE COLLAR WITH THE FLANGE THAT BOLTS TO THE END RIB AND THE TORQUE TUBE ITSELF.  THE 4 MOUNTING 	BOLTS WERE TIGHT TO THE END RIB, BUT THE RIVETS ATTACHING THE COLLAR TO THE TUBE HAD BECOME LOOSE ALLOWING FOR POTENTIAL	 UNCOMANDED MOVEMENT (FLUTTER) OF THE ELEVATOR.  (WP19200405628)			1	L	7	2 	4T	4	T	 	A24CE   	E4EA
2004071200043	20040712	00043	CE  	2004	7	12	2004FA0000524    	1	20040701	G	2730	1016100197	TORQUE TUBE     			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ELEVATOR	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	7232R	8067 				BL69				DURING AN INSPECTION, THE LT ELEVATOR CORNTOL TORQUE TUBE THAT ATTACHES TO IB END RIB OF THE LT ELEVATOR WAS FOUND TO HA	VE PLAY BETWEEN THE ACTUATING HORN AND THE TORQUE TUBE ITSELF.  THE COLLAR WITH THE FLANGE AND THE 4 MOUNTING BOLTS ATTA	CHING THE TORQUE TUBE TO THE END RIB WERE TIGHT, BUT THE 8 RIVETS ATTACHING THE ACTUATING HORN TO THE TUBE HAD BECOME LO	OSE ALLOWING FOR POTENTIAL UNCOMMANDED MOVEMENT (FLUTTER) OF THE ELEVATOR.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA
2004071200051	20040712	00051	EU  	2004	7	12	2004FA0000525    	1	20040517	G	3260	JKL6839	BULB            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					MLG INDICATOR	FAILED          	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	05	41HF					NA0208				ON APPROACH CREW SELECTED THE GEAR HANDLE DOWN, THE NOSE DOWNLOCK ANNUNCIATOR DID NOT ILLUMINATE WITH GEAR HANDLE IN DOW	N POSITION.  CREW ATTEMPTED TO CHANGE THE NOSE DOWNLOCK ANNUNCIATOR BULBS, BUT COULD NOT REMOVE THE ANNUNCIATOR.  WHEN T	HE AIRCRAFT ARRIVED AT THE HANGAR, REMOVED THE NOSE GEAR DOWN LOCK ANUNCIATOR, THE ANNUNCIATOR HOUSES FOUR BULBS, TWO FO	R GEAR UP ANNUNCIATION, TWO FOR THE DOWN AND LOCKED ANNUNCIATION.  THE TWO BULBS FOR THE DOWN AND LOCKED ANNUNCIATION WE	RE BURNED OUT.  REPLACED THE DOWNLOCK BULBS AND ANNUNCIATORS TEST GOOD.  INSTALLED A SCREW DRIVER ON THE AC TO ASSIST IN	 REMOVING THE ANNUNCIATOR.  (GL05200405284)	2	L	7	2 	4F	4	F	 	A3EU    	E6WE
2004091500118	20040915	00118	CE  	2004	9	15	2004FA0000527    	1	20040325	G	5340	101620000638	FITTING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					HORIZONTAL STAB	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	70AJ					BB206				DURING A PHASE 2 AIRFRAME INSPECTION, EXFOLIATION CORROSION WAS FOUND ON THE HORIZONTAL STABILIZER UPPER ATTACH FITTING 	IN TWO PLACES.  ALSO EXFOLIATION CORROSION WAS FOUND ON THE RT UPPER SPAR CAP OF THE HORIZONTAL STABALIZER.  BOTH ARTICL	ES ARE BEING REPLACED WITH MANUFACTURERS NEW PARTS.				1	L	7	2 	4T	3	T	 	A24CE   	E2NE
2004071200020	20040712	00020	SO  	2004	7	12	2004FA0000529    	2	20040426	G	8530	SA10200A20	CYLINDER        			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	09	1050C	1211 	509  			15074893	647526A			PILOT REPORTED ENG RUNNING ROUGH AND SMELLED OIL IN COCKPIT SHORTLY AFTER TAKE OFF, MANAGED TO MAKE EMERGENCY LANDING ON	 DEPARTURE AIRPORT, DETERMINED CYLINDER NR 2 BARREL CRACKED ALMOST ALL THE WAY AROUND 2.8750 INCHES UP FROM BASE CAUSE U	NKNOWN EXCEPT POSSIBLE DEFECTIVE PART.  SOLUTION SHOULD BE TO CHECK OUT CYLINDER BARRELS AT ANNUAL INSPECTION OR 100 HOU	R AND EACH TIME COWL REMOVED FOR LEAKS AND CRACKS AND IF LEAKS OIL OR SEE CRACK IN BARREL SHOULD BE EASIER TO FOLLOW.  S	N ON HEAD IS F20056.		1	H	7	1 	3O	3	O	 	3A19    	E252
2004070800210	20040708	00210	CE  	2004	7	8	2004FA0000530    	1	20040510	G	5541	12310345	SPAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	6207Z	3619 				U20606188				LT SKIN CRACKED 6 INCHES AFT OF LOWER RUDDER HINGE POINT.  RT SKIN WRINKLED 6 INCHES AFT OF LOWER HINGE POINT.  LOWER RI	B CRACKED 5 INCHES AFT OF SECURING POINT TO FORWARD RUDDER SPAR, CRACKED ON LT SIDE.  PROBABLE CAUSE UNNECESSARY ROUGHNE	SS.  (WP25200406045)				1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004070900001	20040709	00001	CE  	2004	7	9	2004FA0000531    	1	20040510	G	5541	12310372	SPAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	6207Z	3619 				U20606188				LT SKIN CRACKED 6 INCHES AFT OF LOWER RUDDER HINGE POINT.  RT SKIN WRINKLED 6 INCHES AFT OF LOWER HINGE POINT.  LOWER RI	B CRACKED 5 INCHES AFT OF SECURING POINT TO FORWARD RUDDER SPAR, CRACKED ON LT SIDE.  PROBABLE CAUSE UNNECESSARY ROUGHNE	SS.  (WP25200406045)				1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004070900002	20040709	00002	CE  	2004	7	9	2004FA0000532    	1	20040510	G	5541	12310346	SPAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	6207Z	3619 				U20606188				LT SKIN CRACKED 6 INCHES AFT OF LOWER RUDDER HINGE POINT.  RT SKIN WRINKLED 6 INCHES AFT OF LOWER HINGE POINT.  LOWER RI	B CRACKED 5 INCHES AFT OF SECURING POINT TO FORWARD RUDDER SPAR, CRACKED ON LT SIDE.  PROBABLE CAUSE UNNECESSARY ROUGHNE	SS.  (WP25200404045)				1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004071200053	20040712	00053	CE  	2004	7	12	2004FA0000534    	1	20040427	G	7603	22500531	NUT             			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540*       	41532	EA  					THROTTLE	MISSING         	B			PAIR	O				OTHER                   				F	D		FLT CONT AFFECTED         	INFLIGHT SEPARATION       		AP	APPROACH       	1			SO	05	738PK	1642 				R18200950				JUST TURNED FINAL AND WENT TO PULL POWER BACK AND FOUND NO THROTTLE RESPONSE.  PILOT WAS ABLE TO LAND USING MAG SWITCH T	O ADD AND REDUCE POWER.  UPON INSPECTION FOUND LOCK NUT MISSING FROM THROTTLE CONNECTION AND BOLT LAYING HALF OUT OF THR	OTTLE /TURBO ACTUATOR.  (MS203651032C AND 22500531).  INSPECTED BOLT FOUND NO DEFECTS.  INSTALLED NEW BOLT, NUT, BEARING	, AND WASHERS.  OPS NORMAL.			1	H	7	1 	3O	3	O	 	3A13    	E295
2004071200158	20040712	00158	EA  	2004	7	12	2004FA0000535    	1	20040623	G	1430	MS20008H20	BOLT            			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	MLG	SHEARED         	G				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	6567	11006				706	19315	76343		AIRCRAFT WAS LOADED WITH 1600LBS OF FERTILIZER AND WAS TAKING OFF TO THE SOUTH ON A DIRT RUNWAY.  PILOT WAS APPROACHING 	65 MPH, WHEN THE RT MAIN WHEEL AND TIRE SEPARATED FROM THE AIRCRAFT.  PROPELLER STRUCK THE GROUND SEVERAL TIMES, CAUSING	 THE AIRCRAFT TO FLIP OVER AND CAME TO REST FACING NORTH.  INSPECTORS FOUND BRAKE ATTACHMENT CLIP APPROX 270 FEET FROM A	IRCRAFT WRECKAGE ON THE RUNWAY.  RT WHEEL AND TIRE ASSY. STILL HAD THE AIRCRAFT AXLE ATTACHED.  THREE ATTACHMENT BOLTS T	HAT SECURE THE AXLE SHAFT TO THE RT SPRING GEAR HAD SHEARED OFF.  TWO OF THE THREE BOLTS SHOWED SIGNS OF CORROSION, BEFO	RE SHEARING.	1	Q	7	1 	3R	3	R	 	1A16    	5E2	5	C	P257
2004071200162	20040712	00162	CE  	2004	7	12	2004FA0000536    	1	20040701	G	2497		WIRE            			CESSNA	210   	T210N       	2073456	CE  										VERTICAL STAB	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06		2077 								FOUND BEACON CIRCUIT WIRING RUNNING UP THROUGH THE VERTICAL STABILIZER CHAFED IN 3 PLACES WHERE THE WIRES WERE ROUTED TH	ROUGH 3 RIBS. REPLACED THE WIRES AND INSTALLED THE NEW WIRES IN A FIBERGLASS LOOM TO PREVENT FURTHER CHAFING.  OPERATOR 	STATED THE BEACON CIRCUIT BREAKER WOULD POP IN TURBULENCE.				1	H	7	1 	3O			 	3A21
2004071200063	20040712	00063	CE  	2004	7	12	2004FA0000537    	1	20040505	G	5711		SPAR            			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					RT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	1182E	945  				31677				SPAR INSPECTED IAW 00-25-02R1.  FOUND 2 CRACKS IN BUTT END,  DOUBLER PLATES APPEAR TO BE LOOSENING.  CRACKS ARE HORIZONT	AL ACROSS THE END GRAIN.					1	H	7	1 	3O	3	O	 	A21CE   	1E10
2004092000096	20040920	00096	SO  	2004	9	20	2004FA0000538    	2	20040220	G	8530	10351002	RISER           			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					NR 5 EXHAUST	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	7329Y					1394	357644			NR 5 EXHAUST RISER BROKEN COMPLETELY OFF AT MOUNTING FLANGE.  POSSIBLE DEFECTIVE WELDING.						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE
2004091400177	20040914	00177	CE  	2004	9	14	2004FA0000539    	1	20040525	G	5343	24130023	MOUNT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					ACTUATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	6098V					172RG0579				NOSE GEAR COLLAPSED DUE TO PART FAILURE ON LANDING ROLL OUT.  (NM07200406705)						1	H	7	1 	3O	3	O	 	3A17    	E286
2004092300109	20040923	00109	NM  	2004	9	23	2004FA0000540    	1	20040103	G	5751		ATTACH FITTING  			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					AILERON	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	94107	1289 				1430				FOUND SEVERE GALVANIC CORROSION BETWEEN THE AILERON ATTACH BRACKETS AND REAR SPAR IN SEVERAL LOCATIONS.  STEEL HAD ORIGI	NALLY BEEN CADIMUM PLATED.  THIS WAS CRITICAL AS IT COULD ALLOW THE AILERON TO DEPART THE AIRPLANE.  COULD NOT FIND A PN	 IN THE CATALOG AS THIS IS CALLED THE REAR BEAM ASSEMBLY.  THE REAR AILERON ATTACH POINTS ARE REINFORCED WITH STEEL PLAT	ES.  THE CORROSION WAS LOCATED BETWEEN THE PLATES AND THE ALUMINUM BEAM.  (GL19200404422)			1	L	7	1 	3O	3	O	 	A718    	E213
2004070900003	20040709	00003	NM  	2004	7	9	2004FA0000541    	1	20040117	G	5320		SUPPORT         			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					BATTERY BOX	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	94107					1430				THE SUPPORT ASSY THAT SUPPORTS THE BATTERY BOX AND BATTERY IS SEVERLY CORRODED.  NO PART NUMBER FOUND IN MFG PARTS CATAL	OG.					1	L	7	1 	3O	3	O	 	A718    	E213
2004092300058	20040923	00058	CE  	2004	9	23	2004FA0000542    	1	20040603	G	2400	S199411	MASTER SWITCH   			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					INSTRUMENT PANEL	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	4918H					15284020				LOWER CONNECTION ON MASTER SWITCH CONTAINS TWO TERMINALS, ONE THAT IS NOT USED.  THIS CONTACT THAT IS NOT USED IS THE LO	WEST ONE ON THE SWITCH AND CAN COM INTO CONTACT WITH THE INSTRUMENT PANEL CAUSING SEVERE ARCING AND POTENTIAL FIRE HAZAR	D IF HIT WITH NEE OR OTHER MEANS OF CONTACT UNDER THE PANEL.  RECOMMENDED CORRECTION:  CHECK FOR SATISFACTORY CLEARANCE 	AT INSTRUMENT PANEL AND INSULATE TERMINAL END FROM CONTACT.  POSSIBLE INSPECTION RECURRING AD DUE TO CLOSE PROXIMITY TO 	FULL PRIMER AND LINE.		1	H	7	1 	3O	3	O	NT	3A19    	E223
2004092300074	20040923	00074	EA  	2004	9	23	2004FA0000543    	2	20040606	G	7322		FLOAT           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CARBURETOR	STICKING        	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			GL	03	63012				CK36716	17275372	RL707939A			ON SHORT FINAL THE ENGINE LOST POWER.  A DECISION WAS MAKE TO MAKE AN OFF FIELD LANDING IN A CORNFIELD.  FOLLOW-UP STATI	C RUN SHOW NO PROBLEMS AND TEST FLIGHT WAS SCHEDULED.  DURING THE TEST FLIGHT ENGINE POWER LOSS TOOK PLACE ON SHORT FINA	L.  CARBURETOR WAS REMOVED AND INSPECTED FINDING MARKS ON THE FLOAT AND CARBURETOR BODY INDICATING THE FLOAT WAS STICKIN	G CAUSING FUEL STARVATION.  RECOMMEND SPECIAL EMPHASIS BE PLACE ON CENTERING THESE FLOATS IN THE CARBURETOR BODY TO PREV	ENT STICKING AND POSSIBLE FUEL STARVATION.  (GL03200409863)		1	H	7	1 	3O	3	O	NT	3A12    	E274
2004071200031	20040712	00031	SW  	2004	7	12	2004FA0000544    	1	20040520	G	5711		SPAR            			BBAVIA	7     	7BCM        	2110106	SW  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A105	1A105*      	GL  	RT WING	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	59Z	3887 				7BCM93	6416R	3167		A LONGITUDINAL CRACK WAS FOUND AT OB AILERON ATTACH FITTING OF THE REAR WOOD SPAR.  THE CRACK IS LOCATED ON RT WING REAR	 SPAR, OB AILERON ATTACH POINT EMANATING FROM LOWER BOLT HOLE ON FORWARD SIDE OF SPAR.  THE CRACK WAS FOUND DURING ANNUA	L INSP WHILE COMPLING WITH AD.  THE CRACK EXTENDS IB FROM THE BOLT APPROXIMATELY FOUR INCHES AND OB APPROX 5.5 INCHES.  	THE REAR SPAR IS A TWO PIECE SPRUCE LAMINATE, AND THE CRACK IS ONLY VISIBLE ON FWD FACE, IT DOES NOT APPEAR ON OPPOSITE 	SIDE.  CRACK WAS POSSIBLY CAUSED OVER TIME BY AILERON ATTACH BOLTS BEING OVER TORQUED.  THIS AC HAS NO KNOWN DAMAGE HIST	ORY.	1	H	7	1 	3O	3	O	 	A759    	E252	5	N	P918
2004092000115	20040920	00115	CE  	2004	9	20	2004FA0000545    	1	20040616	G	3230	24411003	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					LANDING GEAR	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	6623Z	737  				172RG0240				WHILE REPLACING A BROKEN GEAR ACTUATOR THE PIVOT WAS REMOVED AND INSPECTED.  A CRACK WAS FOUND IN THE LOWER RADIUS AT TH	E BOTTOM OF THE GEAR SPLINES.  TO PREVENT THIS PROBLEM IT IS SUGGESTED THAT THE MLG 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.				1	H	7	1 	3O	3	O	 	3A17    	E286
2004092000088	20040920	00088	CE  	2004	9	20	2004FA0000546    	1	20040616	G	3233	12810013	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					RT MLG	MALFUNCTIONED   	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	6623Z					172RG0240				DURING A FLIGHT, THE PILOT REPORTED HEARING A LOUD POP WHEN THE GEAR WAS CYCLED DOWN.  UPON INSPECTION OF THE LANDING GE	AR, THE LT MLG ACTUATOR WAS FOUND TO BE CRACKED ALL THE WAY ACROSS THE LARGE BORE AT THE FORWARD BOLT HOLE AND THERE WER	E TWO OTHER SMALL CRACKS IN THE LARGE BORE.  THE LOWER BOLT FOR THE ACTUATOR WAS FOUND BROKEN OFF IN THE IB GEAR CASTING	, THE SECTOR GEAR WAS DAMAGED AND THE MLG PIVOT WAS CRACKED.  THE MANUFACTURER SHOULD REDESIGN THE ACTUATOR AND GEAR PIV	OT ASSEMBLIES, MAKING THEM OUT OF STEEL OR SOME OTHER MATERIAL THAT WILL WITH STAND THE REPEATED STRESS THAT ARE PUT ON 	THESE PARTS.  THIS IS A RECURRING PROBLEM WITH THIS TYPE OF LANDING GEAR.	1	H	7	1 	3O	3	O	 	3A17    	E286
2004071200045	20040712	00045	CE  	2004	7	12	2004FA0000547    	1	20040526	G	2720		RUDDER PEDAL    			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	COCKPIT	DAMAGED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	6623Z	3300 				172RG0240	RL3382736A	820229		PILOTS REPORTED AFTER PERFORMING A SIMULATED WING FIRE MANUVER (A STEEP TURN TO THE LEFT) THEY HEARD A LOUD BANG AND THE	N LOST CONTROL OF THE RUDDER.  THE AIRCRAFT LANDED SAFELY.  MAINTENANCE INSPECTED THE RUDDER SYSTEM AND FOUND THE WELD A	SSEMBLY GEARS HAD (JUMPED) A TOOTH AND REDUCED RUDDER TRAVEL TO APPROX .3333 OF NORMAL TRAVEL.  AFTER REMOVAL OF THE WEL	D ASSEMBLIES MAINTENANCE FOUND THE BULKHEADS THAT THE OUTBOARD RUDDER BEARINGS MOUNTED TO HAD ELONGATED HOLES THAT WOULD	 ALLOW THE BEARING TO SHIFT FORWARD WHEN EXCESSIVE PRESSURE WAS APPLIED TO THE OB RUDDER PEDALS ON EITHER SIDE OF THE CO	CKPIT.  THE RUDDER BEARINGS SHOWED NO ABNORMAL WEAR FOR THIS TYPE OF AIRCRAFT.  ONE TIME OCCURANCE BEFORE SB 98-3.	1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA
2004071200161	20040712	00161	EU  	2004	7	12	2004FA0000548    	1	20040709	G	2550	23509600	CARGO HOOK      			AEROSP	AS355 	AS355*      	       	EU  											INSTALLED       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	HBZET	228  								DURING A MAINTENANCE CHECK, IAW ONBOARD SYSTEMS SB NO. 159-013-00,  FOUND CRACKS IN THE WELD PART OF SWING ASSY.						1	G	7	2 	3U			 	H11EU
2004071200155	20040712	00155	SW  	2004	7	12	2004FA0000549    	1	20040710	G	7120	600429503	HEAT SHIELD     	MOONEY      	M20R        	MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  	MCAULY	2A34C	2A34C*      	GL  	ISOLATOR	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	242M	250  				290292				HEAT SHIELD WAS FOUND TO BE MAKING CONTACT WITH TUBULAR ENGINE MOUNT. THIS CONTACT CREATED A GOUGE APPROXIMATELY .200 IN	CH IN LENGTH AND APPROXIMATELY .045 INCH DEEP.					1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P3EA
2004071200200	20040712	00200	EA  	2004	7	12	2004FA0000550    	2	20040707	G	8530	73111	EXHAUST VALVE   			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	BROKEN          	G				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			GL	07	9SA	1884 	1884 			32R7780530	L1493248			THE PILOT REPORTED A LOSS OF POWER AND LOSING ALTITUDE TO AIR TRAFFIC. AN EMERGENCY LANDING WAS ACCOMPLISHED AT A PUBIC 	AIRPORT. MAINTENANCE PERSONNEL FOUND THE NR 2 CYLINDER HAD A BROKEN EXHAUST VALVE, WITH THE PISTON AND CYLINDER DAMAGED 	DUE TO THE HEAD OF THE VALVE IN THE CYLINDER. THE STEM OF THE VALVE WAS STILL ON THE ENGINE. THE ENGINES WAS LAST OVERHA	ULED ON 08/24/1983.			1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004071200205	20040712	00205	WP  	2004	7	12	2004FA0000551    	2	20040606	G	7250		STATOR          			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	DAMAGED         	B			DSCR	E				ENGINE SHUTDOWN         				B	K	J	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	WARNING INDICATION        	NR	NOT REPORTED   	1			GL	25	600CM					15020	P38327			DURING ENGINE START THE OPERATOR OBSERVED SMOKE EXITING THE ENGINE EXHAUST DUCT.  THE OPERATOR SHUT THE ENGINE DOWN.  VI	SUAL INSPECTION REVEALED OIL AND IMPACT DAMAGE IN THE EXHAUST PATH.  THIRD STAGE TURBINE WHEEL BLADES WERE FRACTURED.  F	RAGMENTS FROM THE FRACTURED BLADES ENTERED THE GAS FLOW PATH RESULTING IN SECONDARY IMPACT DAMAGE TO THE THIRD STAGE STA	TOR, AFT SCAVENGE PUMP OIL TRANSFER TUBE AND SHIELD, AFT SCAVENGE PUMP COVER, EGT HARNESS, ENGINE EXHAUST DUCT AND AIRFR	AME EXHAUST PIPE.  THE THIRD STAGE STATOR SEAL ASSEMBLY LOWER RETAINER SEGMENT WAS SEPARATED FROM THE RETAINER RIVETS AN	D EXITED THE ENGINE THROUGH THE EXHAUST.  THE RETAINER RIVETS AND SPACERS REMAINED IN THE STATOR SEAL.	1	H	7	2 	4T	4	T	 	2A4     	E4WE
2004072100062	20040721	00062	EA  	2004	7	21	2004FA0000553    	2	20040701	G	8550	LW14784	DIPSTICK        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	DESTROYED       	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			NM	03	733RL	6118 	45   			17268489	RL529976T			PILOT CHKD OIL DURING PREFLIGHT, REINSERTED DIPSTICK, TURNED C/W UNTIL SNUG. INSTRUCTOR PILOT CHECKED DIPSTICK AND FOUND	 SNUG.  AFTER T/O OIL BEGAN STREAMING FROM COWL. PILOT RETURNED TO BASE AND MADE UNEVENTFUL LANDING. AMT OPENED COWL AND	 FOUND THAT DIPSTICK WAS MISSING. REMOVED AND CUT OIL FILTER, FOUND MASSIVE AMTS OF ALUMINUM SUBSTANCE IN FILTER ELEMENT	. REMOVAL OF SUMP SCREEN REVEALED PIECES OF ALUMINUM ROD IN BOTTOM OF SUMP.  WITH CYLINDER NR 4 NEAR TDC, DIPSTICK COULD	 BE FULLY INSERTED INTO CRANKCASE ALONG CRANKSHAFT, AND CROSS-THREADED UNTIL SNUG WHEN TILTED SLIGHTLY AFT. LOCATION OF 	SMALL ACCESS DOOR ON THE TOP OF COWL OF AC IT IS DIFFICULT TO VISUALLY INSPECT DIPSTICK FOR PROPER THREAD ENGAGEMENT.	1	H	7	1 	3O	3	O	NT	3A12    	E274
2004091300120	20040913	00120	CE  	2004	9	13	2004FA0000554    	1	20040625	G	2510	MM201057	LOCK            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					SEAT BACK	BROKEN          	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	07	516ER	2886 				172S8620				PILOT SEAT BACK CYL LOCK ASSY ROD BROKE AT SWAGED ROD END. AC RETURNED TO AIRPORT.  MFG RESCINDED SB DUE TO PROBLEMS WIT	H CYL LOCK ASSY.  ANOTHER SB04-25-02 WHICH IS SUPPOSED TO TAKE CARE OF ANY PROBLEMS.  ELECTED TO REMOVE ALL CYL LOCK ASS	Y, INSTALL SOLID RODS IAW SB04-25-02 UNTIL SUCH TIME AS ALL NEW CYL LOCK ASSY ARE RECEIVED FROM MFG, SEATS ARE RETURNED 	TO ORIGINAL CONFIGURATION.  OFFSET ATTACHMENT AT BACK OF SEAT CONTRIBUTES TO BENDING MOMENT BEING APPLIED TO ROD END AND	 SIDE LOADS CYL LOCK ASSY.  IT IS IMPOSSIBLE TO OBSERVE ROD CRACKING AT SWAGED END PRIOR TO FAILURE DUE TO PLASTIC COVER	 OVER END THAT IS NOT REMOVABLE. THIS IS SECOND CYL LOCK ASSY ROD END TO BREAK SINCE SB04-25-01 WAS INCORPORATED.	1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004071900055	20040719	00055	SO  	2004	7	19	2004FA0000555    	2	20040629	G	7322	1048941	CARBURETOR      								CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	BROKEN          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			SO	15		1214 	1214 				254630A48	K20557		AC ENTERED A POWER ON STALL, DURING RECOVERY THE ENGINE BEGAN LOOSING POWER.  INSTRUCTOR TRIED TO MAINTAIN POWER BY MANE	UVERING THROTTLE IN AND OUT BUT WAS ONLY ABLE TO MAINTAIN ABOUT 1100 RPM MAXIMUM CONTINUES.  MECHANICS QUICKLY IDENTIFIE	D THE PROBLEM AS THE CARBURETOR.  UPON REMOVAL AND EXTERNAL INSPECTION OF THE CARBURETOR, FOUND THE NOZZLE ASSEMBLY PIN 	47-799 TO BE CRACKED, ABOUT HALF INCH FROM THE END OF THE NOZZLE AND JUST ABOUT ALL THE WAY AROUND.  CARBURETOR WAS OVER	HAULED ON 7/31/2002 WO NR M992180.							3	O			E252	5	N	P918
2004071900056	20040719	00056	GL  	2004	7	19	2004FA0000556    	1	20040616	G	2823	EFS20X2	SELECTOR        			DIAMON	DA40  	DA40        	2990002	GL  										FUEL	MISPINNED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	801ER	378  	75   			40305				THIS FLEET OPERATOR OPERATES 10 DA40 AIRCRAFT.  THERE WAS A PILOT REPORT OF THE FUEL SELECTOR NOT FUNCTIONING PROPERLY, 	AND NOT ALLOWING THE PILOT TO SELECT THE OTHER TANK.  A FLEET INSPECTION WAS INITIATED, AND THIS AIRCRAFT WAS FOUND TO H	AVE THE SELECTOR SHAFT UNIVERSAL JOINTS WITH LOOSE OR MISSING ATTACH PINS.				1	L	7	1 	3O			NT	A47CE
2004071900075	20040719	00075	WP  	2004	7	19	2004FA0000557    	2	20040606	G	7250	31022471	RETAINER        								GARRTT	TPE331	TPE33110    	01514	WP  					TURBINE SECTION	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	600CM						P38327			SECOND STAGE STATOR AIR SEAL RETAINING RIVETS FOUND LOOSE DURING INSPECTION/REPAIR FOR TURBINE SECTION DAMAGE.  RETAINER	 PLATE RIVET HOLE DIAMETER(S) WERE ENLARGED BEYOND MAX RIVET MANUFACTURER SPECIFICATIONS.  ENGINE MANUFACTURER MANUALS L	ACK ANY INSPECTION CRITERIA FOR RETAINER PLATE RIVET HOLE DIAMETER.  ENLARGED RETAINER PLATE RIVET HOLE DIAMETER MAY RES	ULT IN LOOSE RETAINER AND/OR AIR SEAL CONTACTING TURBINE ROTOR HUB DURING ENGINE OPERATION.								4	T			E4WE
2004071900060	20040719	00060	CE  	2004	7	19	2004FA0000558    	1	20040503	G	5510	12320412	ATTACH BRACKET  			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					HORIZONTAL STAB	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	4631C					21063582				WHEN PN 1232041 ARE INSTALLED, INCORRECT FIT UNLESS SK210-125 ALSO INSTALLED ON STA 209.0 BULKHEAD.  NO CORRELATING REFE	RENCE IN MFG PARTS OR SERVICE.  TOOK 2 WEEKS WITH MFG TECH TO WORK OUT.  IMPROPER FIT CAUSES STRESS AND BINDING ON PARTS	 THAT COULD LEAD TO FAILURE AND LOSS OF AIRCRAFT.  OLD STYLE FITTING CLEAR RIVETS IN BULKHEAD BUT NEW PART KITS, SHOP RI	VET LEAVING APPROX .075 GAP UNLESS 210-125 DONE TO CHANGE TO COUNTERSINK RIVETS.			1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004071900061	20040719	00061	CE  	2004	7	19	2004FA0000560    	1	20040415	G	5230		LATCH           			CESSNA	208   	208B        	2073701	CE  										CARGO DOOR	INOPERATIVE     	D			Q03E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	303PW					208B0985				CARGO DOOR OPENED IN FLIGHT.  INSPECTED DOOR AND ADT LATCH.						1	H	7	1 	3T			 	A37CE
2004071900058	20040719	00058	EU  	2004	7	19	2004FA0000561    	1	20040429	G	5520	A730201N	ROCKER          			LET   	L23   	L23         	1360308	EU  										ELEVATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	251BA					917817				NDT ELEVATOR ROCKER IAW ASTM E-1444.  CLEANED AND MAGNETIC PARTICLE INSPECTED IAW ASTM E-1444 AND NDT MT-001.  CRACKS FO	UND IN SEVERAL PLACES.  LACK OF PENETRATION AROUND MANY WELDS.  RED TAGGED PART.					1	K	0	0 	  			RC	G24EU
2004092000116	20040920	00116	CE  	2004	9	20	2004FA0000562    	1	20040713	G	5711		SPAR            			BBAVIA	11    	11AC        	0191102	CE  	CONT  	A65   	A65*        	17003	SO  					LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	9628E					11AC1266				LT AFT WING SPAR HAD A VERTICAL COMPRESSION CRACK AT THE OB EDGE OF THE LIFT STRUT PLATE.  ALSO, IT WAS CRACKED HORIZONT	ALLY FROM THE COMPRESSION CRACK TO THE OB LIFT STRUT ATTACHMENT POINT.  ALSO, ALL FOUR SPARS WERE CRACKED AT THE IB WING	 ATTACHMENT BOLT HOLES TO THE END OF THE SPAR.  SPAR WAS PROBABLY CRACKED AS THE RESULT OF A HARD LANDING WHICH VISIBLY 	DAMAGED THE RT WING.  AFTER HARD LANDINGS RESULTING IN WING DAMAGE, THE INTERIOR WING ATTACHMENT POINTS, INCLUDING LIFT 	STRUT ATTACHMENT POINTS, SHOULD BE INSPECTED FOR CRACKS.		1	H	7	1 	3O	3	O	 	A761    	E205
2004092300090	20040923	00090	CE  	2004	9	23	2004FA0000563    	1	20040504	G	7603	RA1039C	CLIP            			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470*      	17026	SO  					THROTTLE CONTROL	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	102FA					TC483				LT THROTTLE CONTROL LEVER FAILED TO CHANGE POWER DURING CHANGE FROM TAKE-OFF TO CRUISE POWER SETTING.  IT WAS DISCOVERED	 THT THE CRIMPING HAS FAILED ON THE CLIP THROTTLE CONTROL PN RA1039C WHICH IS PART OF THE THROTTLE CABLE ASSY PN 50-3890	12-15.  THIS CLIP IS LOCATED ON THE ENGINE SIDE OF THE CONTROL CABLE AND IS ATTACHED TO BRAKE THROTTLE CONTROL PN 96-940	021.			1	L	7	2 	3O	3	O	 	3A16    	E1CE
2004071900009	20040719	00009	CE  	2004	7	19	2004FA0000564    	1	20040712	G	5210	CJ1028	HANDLE          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PAX DOOR	OUT OF ADJUST   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	9528W	2600 				17280467				CABIN DOOR LATCH ASSEMBLY, TWO IN FLEET.  THE DOOR LATCH ASSEMBLIES CONTINUALLY GET OUT OF ADJUSTMENT CAUSING THE INSIDE	 DOOR HANDLE TO FALL TO THE CLOSED POSITION WHEN THE DOOR IS CLOSED FROM THE OUTSIDE.  THIS CAUSES THE DOOR TO LOCK AND 	BE UNABLE TO OPEN FROM THE OUTSIDE.  PROPER TEACHING OF DOOR CLOSING PROCEDURES HELPS, BUT ON A FLIGHT SCHOOL / RENTAL A	IRCRAFT IT IS NOT ALWAYS POSSIBLE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004071900010	20040719	00010	CE  	2004	7	19	2004FA0000565    	1	20040712	G	5210	CJ1028	HANDLE          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PAX DOOR	OUT OF ADJUST   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	9528W	2600 				17280467				CABIN DOOR LATCH ASSEMBLY, TWO IN FLEET.  THE DOOR LATCH ASSEMBLIES CONTINUALLY GET OUT OF ADJUSTMENT CAUSING THE INSIDE	 DOOR HANDLE TO FALL TO THE CLOSED POSITION WHEN THE DOOR IS CLOSED FROM THE OUTSIDE.  THIS CAUSES THE DOOR TO LOCK AND 	BE UNABLE TO OPEN FROM THE OUTSIDE.  PROPER TEACHING OF DOOR CLOSING PROCEDURES HELPS, BUT ON A FLIGHT SCHOOL / RENTAL A	IRCRAFT IT IS NOT ALWAYS POSSIBLE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004092300064	20040923	00064	GL  	2004	9	23	2004FA0000566    	1	20040524	G	7603		CONTROL CABLE   			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					MIXTURE CONTROL	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	6000C	769  				1037				MIXTURE CONTROL AND ALTERNATOR BATTERY AND CABLE ARE TIED TOGETHER.  CONTROL AND CABLE CHAFED INSULATION OFF CABLE AND S	HORTED TO MIXTURE CABLE, CAUSING MIXTURE CABLE TO FREEZE UP AT ITS CURRENT SETTING.  WHEN TYING WIRES AND CABLE AND LINE	S OR HOSE TOGETHER USE A STAND OFF FOR SEPARATION BETWEEN THEM.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE
2004071900006	20040719	00006	CE  	2004	7	19	2004FA0000567    	1	20040601	G	5740	24130023	MOUNT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NLG ACTUATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	9795B					172RG1042				FOUND AT 100 HOUR INSPECTION.  NOSE GEAR ACTUATOR MOUNT, CRACKED AFT OF NOSE GEAR ACTUATOR.						1	H	7	1 	3O	3	O	 	3A17    	E286
2004071900078	20040719	00078	SO  	2004	7	19	2004FA0000568    	1	20040226	G	5310	62522000	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					WINDSHIELD FRAME	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	157BJ					347570282				BOTH LOWER AFT WINDSHIELD FRAME STEEL FITTING VERY CORRODED.  WINDSHIELD LEAK AND INSULATION HOLDING MOISTURE ON FITTING	.  NEED TO BE INSPECTED MORE OFTEN AND CLEANED AND TREATED.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004071900012	20040719	00012	SO  	2004	7	19	2004FA0000569    	1	20040226	G	5340	6852700	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					WINDSHIELD FRAME	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	157BJ					347570282				BOTH LOWER AFT WINDSHIELD FRAME STEEL FITTING VERY CORRODED.  WINDSHIELD LEAK AND INSULATION HOLDING MOISTURE ON FITTING	.  NEED TO BE INSPECTED MORE OFTEN AND CLEANED AND TREATED.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004071900013	20040719	00013	EU  	2004	7	19	2004FA0000570    	1	20040615	G	3610	275503	SHUTOFF VALVE   			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					OXYGEN	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	79KP	39   				262				THIS VALVE INSTALLED PREVIOUSLY TO COMPLY WITH REQURIEMENTS OF AD 2003-11-07.  FOUND DURING INSPECTION THAT VALVE WILL N	OT SHUT OFF OXYGEN FLOW WHEN TURNED TO CLOSED.  REPLACED VALVE WITH NEW PN 27550-3, THIS CORRECTED PROBLEM.					2	M	7	2 	4F	4	F	 	A2SW    	E6WE
2004071900014	20040719	00014	EA  	2004	7	19	2004FA0000571    	2	20040610	G	7310	25765361	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE FUEL	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	974SP					172S8178	L2893651A	TB007		AIRCRAFT WAS REPORTED, ENGINE DIES ON IDLE SPEED, EXCESSIVE RICH MIXTURE, BLACK SMOKE EMITTED FROM EXHAUST.  IDLE SPEED 	AND MIXTURE COULD NOT BE ADJUSTED IAW AD 2001-06-17 INSTRUCTIONS REF D, L, I, THRU 2, 1.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2004071900011	20040719	00011	SO  	2004	7	19	2004FA0000572    	1	20040510	G	1430	AN546	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					DOWNLOCK SWITCH	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	615SN	3334 				318052094				PILOT DECLARED AN EMERGENCY WHEN HE HAD A GEAR UNSAFE LIGHT AFTER THE GEAR EXTENDED.  (AC EVENTUALLY LANDED SAFELY).  GE	AR DOWNLOCK DID NOT GO ALL THE WAY TO THE LOCK POSITION AND ACTIVATE THE SWITCH.  (DOWNLOCK WAS FOUND CORRODED TO THE BO	LT) MM , PUT A FEW DROPS OF OIL ON THE BOLT AT ANNUAL/100 HOUR.  THE PROBLEM IS THE OIL DOES NOT WICK INTO THE AREA WHER	E IT PIVOTS.  ALSO, HOT ENGINE EXHAUST BLOWING ACROSS THE BOLT EVENTUALLY NEGATES ANY LUBRICATION ACTION.  RECOMMEND BOL	T, GET CHANGED PERIODICALLY AND PUT NEVER SEIZE ON THE BOLT WHEN INSTALLING.  IF NOTHING ELSE, THE (NEVER SEIZE) WOULD K	EEP THINGS MOVING!	1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004071900030	20040719	00030	SO  	2004	7	19	2004FA0000573    	2	20040602	G	7310	CK002	CLAMP           			LANCAR	LC40  	LC40550FG   	5150000	NM  	CONT  	O550  	IO550N      	17042	SO  					FUEL PRESS TRANS	CRACKED         	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	03	419JK	7    				40020				AD WAS COMPLIED WITH AT 250 HOURS BY INSP AND INSTALLATION OF MFG SERVICE KIT (PN CK-002) (WORM TYPE CLAMP) INSTALLED ON	 THE FUEL PRESSURE TRANSDUCER.  THE CLAMP WAS TORQUED TO THE EXACT TORQUE AS CALLED.  6/2/04-DURING AN OIL CHANGE THE CL	AMP SUPPLIED IN KIT CK0002 WAS FOUND CRACKED IN TWO, NO LONGER SECURING THE TRANSDUCER.  THE PROBLEM IS CAUSED BY COMMON	 TYPE STAINLESS HOSE CLAP BEING TIGHTENED AROUND A SQUARE TRANSDUCER BRACKET.  THE BRACKET PUTS VERY SHARP STRESS MARKS 	IN FOUR SPOTS OF THE CLAMP CAUSING IT TO CRACK.  RECOMMEND PROMPT REVISION TO AD NOTE.		1	L	7	1 	3O	3	O	RT	A00003SA	E3SO
2004071900004	20040719	00004	SW  	2004	7	19	2004FA0000574    	1	20040611	G	5711		SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					WING	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	50338					107279				TWO SPARS SPLIT AT WING ROOT WING ATTACH FITTINGS, ONE SPAR SPLIT AT WING LIFT STRUT ATTACH FITTING.  SPLITS FOUND DURIN	G ANNUAL INSPECTION.  PROBABLE CAUSE:  DRYING AND SHRINKAGE.					1	H	7	1 	3O	3	O	NC	A759    	E274
2004071900024	20040719	00024	SO  	2004	7	19	2004FA0000575    	2	20040624	G	7497	M1740R	WIRE HARNESS    			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	NR 4 CYLINDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	9139Q	1093 				E249	1214317BA	EE557		THE SHIELDING ON THE IGN LEAD ON 4 CYLINDERS AT THE PLUG ENDS FRAYED AND BROKEN ALLOWING IGN NOISE TO BE HEARD OVER AIRC	RAFT RADIO.  PREVENTS PILOT FROM UNDERSTANDING ATC SHIELDING BROKE RT AT (B) ASSEMBLY.  THIS IS THE RED SLICK IGN HARNES	S.				1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P25EA
2004071900008	20040719	00008	CE  	2004	7	19	2004FA0000576    	1	20040621	G	8010	637817	BEARING         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					STARTER ADAPTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	8190G	1453 				E2658	297163R			UPON RETURN FROM A TRAINING FLIGHT A LARGE QUANTITY OF OIL WAS FOUND IN THE ENGINE COWL AND ON THE GROUND UNDER THE AIRC	RAFT.  AFTER WASHING THE ENGINE DOWN, AND AN ENGINE RUN, IT WAS DETERMINED THAT THE OIL WAS COMING FROM THE AIR CONDITIO	NING DRIVE SHAFT SEAL IN THE STARTER ADAPTER ASSEMBLY.  FURTHER DISASSEMBLY AND INSPECTION REVELED THAT THE BALL BEARING	, JUST BEHIND THE SEAL, HAD COME APART.  NO METAL WAS FOUND IN THE OIL FILTER OR THE STRAINED ENGINE OIL.  INSPECT SEAL 	AT PREFLIGHT TO DETECT EXCESSIVE LEAKAGE.		1	L	7	1 	3O	3	O	 	3A15    	E3SO
2004071900005	20040719	00005	CE  	2004	7	19	2004FA0000577    	1	20040714	G	7160		SEALANT         		STCSA4428S  	CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  					AIR BOX	SEPARATED       	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	05	738GV					17269974	L3633336A			ACFT HAD LOW POWER DURING TAKE OFF, DURING THE FOLLOW-UP INSPECTION THE MECH. FOUND PIECES OF SILICON MISSING AROUND THE	 CARB INTAKE SUSPECTED THAT IT WAS INGESTED THROUGH THE CARB DURING TAKE OFF.  THIS ACFT HAD STC NR SA4428SW INSTALLED O	N 9-16-98 PART OF THIS INSTALLATION WAS TO MOD THE AIR BOX AND INSTALL AN ADAPTER PLATE WITH SILICON SEALANT BETWEEN THE	 PLATE AND THE AIR BOX A PIECE OF THIS SEALANT WAS MISSING.			1	H	7	1 	3O	3	O	NT	3A12    	E286
2004072100061	20040721	00061	NM  	2004	7	21	2004FA0000578    	1	20040719	G	6220	900R2101006107	HUB             	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	91   	91   		0099990080	9000085				DURING ACCOMPLISHMENT OF A.D. 2002-10-05, (MAIN ROTOR UPPER HUB INSP.) FOUND (2) OUT OF (10) HOLES CRACKED IN UPPER HUB 	FLANGE AS DEPICTED IN MFG SERVICE BULLETIN 900-072.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004072100063	20040721	00063	CE  	2004	7	21	2004FA0000580    	1	20040714	G	1430	AN37	BOLT            			CESSNA	210   	T210J       	2073440	CE  	CONT  	O520  	TSIO520H    	17040	SO  					THROTTLE	MISSING         	G				L				ABORTED APPROACH        				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			NM	04	2KD		58   			T2100436	501200			WHILE MAKING A APPROACH TO THE AIRPORT FOR LANDING, THE PILOT ADDED POWER WITH NO ENGINE RESPONSE. THE THROTTLE CABLE DI	SCONNECTED FROM THE ENGINE CONTROL ARM DUE TO THE THROTTLE ATTACHING BOLT MISSING ALONG WITH THE WASHER, NUT AND COTTER 	PIN. THROTTLE WORKED FIND WHEN MOVED FROM THE COCKPIT.  AIRCRAFT HAD THE ENGINE REMOVED APRIL 04 FOR METAL CONTAMINATION	 AND REINSTALLED.			1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004091500110	20040915	00110	NM  	2004	9	15	2004FA0000585    	1	20040621	G	5210	AE40142Z006	ACTUATOR        			AMD   	FALC50	FALCON2000  	2730170	NM  										PAX DOOR	DELAMINATED     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		2895 								MAIN CABIN DOOR ACTUATOR (WISHBONE) DELAMINATING.						2	K	7	3 	4F			RT	A50NM
2004091500112	20040915	00112	NM  	2004	9	15	2004FA0000586    	1	20040621	G	5210	AE40142Z006	ACTUATOR        			AMD   	FALC50	FALCON2000  	2730170	NM  										PAX DOOR	DELAMINATED     	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		2810 				034				MAIN CABIN DOOR ACTUATOR DELAMINATED.						2	K	7	3 	4F			RT	A50NM
2004091500114	20040915	00114	SO  	2004	9	15	2004FA0000587    	1	20040708	G	2701		CLAMP           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					CONTROL COLLUMN	OUT OF POSITION 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	81892					288090286				FULL DOWN ELEVATOR WAS NOT ACHIEVED DUE TO THE FACT THAT TEMPORARY YOKE ATTACHMENTS WERE IMPEDING THE MOVEMENT OF THE FO	RWARD TRAVEL OF THE YOKE.  AFTER A THOROUGH INSPECTION OF THE STABALATOR CONTROL SYSTEM IT WAS FOUND THAT THE CLAMP ON A	TTACHMENTS WERE IMPEDING THE TRAVEL. OF COURSE THIS CARRY MUCH POTENTIAL DANGER.				1	L	7	1 	3O	3	O	 	2A13    	E286
2004092000087	20040920	00087	GL  	2004	9	20	2004FA0000588    	1	20040605	G	2823	3F20M	SELECTOR VALVE  			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ZONE 100	SEPARATED       	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	807ER	282  	86   			40318	L3114451A	CH37371B		DURING FLIGHT, THE FLIGHT CREW MADE A FUEL TANK SELECTION CHANGE AND NOTICED THE FUEL WAS BURNING FROM THE PREVIOUS TANK	 EVEN THOUGH THE SELECTOR HAD BEEN MOVED TO THE NEW TANK.  AFTER LANDING, MAINTENANCE PERSONNEL FOUND THE FUEL SELECTOR 	SHAFT HAD BECOME SEPARATED FROM THE SELECTOR AT THE UNIVERSAL JOINT.  THE UNIVERSAL JOINT RETAINING PINS ARE PRESSED INT	O THE UNIVERSAL JOINT BODY AND HAD BECOME LOOSE ALLOWING THEM TO FALL OUT.  THIS SHAFT IS PART OF THE FUEL SELECTOR ASSE	MBLY AND HAS NO UNIQUE P/N.		1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920
2004092000103	20040920	00103	GL  	2004	9	20	2004FA0000590    	1	20040605	G	2823	3F20M	SELECTOR VALVE  			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	FUEL SYS	SEPARATED       	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	807ER	282  	86   			40318	L3114451A	CH37371B		DURING FLIGHT, THE FLIGHT CREW MADE A FUEL TANK SELECTION CHANGE AND NOTICED THE FUEL WAS BURNING FROM THE PREVIOUS TANK	 EVEN THOUGH THE SELECTOR HAD BEEN MOVED TO THE NEW TANK.   AFTER LANDING, MAINTENANCE PERSONNEL FOUND THE FUEL SELECTOR	 SHAFT HAD BECOME SEPARATED FROM THE SELECTOR AT THE UNIVERSAL JOINT.  THE UNIVERSAL JOINT RETAINING PINS ARE PRESSED IN	TO THE UNIVERSAL JOINT BODY AND HAD BECOME LOOSE ALLOWING THEM TO FALL OUT.  THIS SHAFT IS PART OF THE FUEL SELECTOR ASS	EMBLY AND HAS NO UNIQUE P/N.		1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920
2004092000104	20040920	00104	GL  	2004	9	20	2004FA0000591    	1	20040605	G	2823	3F20M	SELECTOR VALVE  			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ZONE 100	SEPARATED       	B				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SO	15	807ER	282  	86   			40318	L3114451A	CH37371B		DURING FLIGHT, THE FLT CREW MADE A FUEL TANK SELECTION CHANGE AND NOTICED THE FUEL WAS BURNING FROM THE PREVIOUS TANK EV	EN THOUGH THE SELECTOR HAD BEEN MOVED TO THE NEW TANK. AFTER LANDING, MAINTENANCE PERSONNEL FOUND THE FUEL SELECTOR SHAF	T HAD BECOME SEPARATED FROM THE SELECTOR AT THE UNIVERSAL JOINT. THE UNIVERSAL JOINT RETAINING PINS ARE PRESSED INTO THE	 UNIVERSAL JOINT BODY AND HAD BECOME LOOSE ALLOWING THEM TO FALL OUT.  THIS SHAFT IS PART OF THE FUEL SELECTOR ASSEMBLY 	AND HAS NO UNIQUE P/N.		1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920
2004092300055	20040923	00055	GL  	2004	9	23	2004FA0000596    	1	20040616	G	2823	EA2UJD	SHAFT           			DIAMON	DA40  	DA40        	2990002	GL  										FUEL SELECTOR	MISPINNED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	807ER	282  	86   			40318				THIS FLEET OPERATOR OPERATES AIRCRAFT. THERE WAS A PILOT REPORT OF THE FUEL SELECTOR NOT FUNCTIONING PROPERLY, AND NOT A	LLOWING THE PILOT TO SELECT THE OTHER TANK.  A FLEET INSPECTION WAS INITIATED, AND THIS AIRCRAFT WAS FOUND TO HAVE THE S	ELECTOR SHAFT UNIVERSAL JOINTS WITH LOOSE OR MISSING ATTACH PINS.				1	L	7	1 	3O			NT	A47CE
2004092300057	20040923	00057	GL  	2004	9	23	2004FA0000597    	1	20040616	G	2823	EA2UJD	SHAFT           			DIAMON	DA40  	DA40        	2990002	GL  										FUEL SELECTOR	MISPINNED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	810ER	291  	99   			40320				THERE WAS A PILOT REPORT OF THE FUEL SELECTOR NOT FUNCTIONING PROPERLY, AND NOT ALLOWING THE PILOT TO SELECT THE OTHER T	ANK.  A FLEET INSPECTION WAS INITIATED, AND THIS AIRCRAFT WAS FOUND TO HAVE THE SELECTOR SHAFT UNIVERSAL JOINTS WITH LOO	SE OR MISSING ATTACH PINS.				1	L	7	1 	3O			NT	A47CE
2004092300059	20040923	00059	GL  	2004	9	23	2004FA0000598    	1	20040616	G	2823	EFS20X2	SHAFT           			DIAMON	DA40  	DA40        	2990002	GL  										FUEL SELECTOR	MISPINNED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	802ER	346  	48   			40306				THERE WAS A PILOT REPORT OF THE FUEL SELECTOR NOT FUNCTIONING PROPERLY, AND NOT ALLOWING THE PILOT TO SELECT THE OTHER T	ANK. A FLEET INSPECTION WAS INITIATED, AND THIS AIRCRAFT WAS FOUND TO HAVE THE SELECTOR SHAFT UNIVERSAL JOINTS WITH LOOS	E OR MISSING ATTACH PINS.				1	L	7	1 	3O			NT	A47CE
2004092300060	20040923	00060	GL  	2004	9	23	2004FA0000599    	1	20040616	G	2823	EFS20X2	SHAFT           			DIAMON	DA40  	DA40        	2990002	GL  										FUEL SELECTOR	MISPINNED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	805ER		9    			40316				THERE WAS A PILOT REPORT OF THE FUEL SELECTOR NOT FUNCTIONING PROPERLY, AND NOT ALLOWING THE PILOT TO SELECT THE OTHER T	ANK. A FLEET INSPECTION WAS INITIATED, AND THIS AIRCRAFT WAS FOUND TO HAVE THE SELECTOR SHAFT UNIVERSAL JOINTS WITH LOOS	E OR MISSING ATTACH PINS.				1	L	7	1 	3O			NT	A47CE
2005022200010	20050222	00010	GL  	2005	2	22	2004FA0000600    	1	20040614	G	3222		FORK            			AMTR  	AEROST	AEROSTARBIRD	0560582	GL  										NLG	BROKEN          	G				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	07	7022X	70   				AS1020				THE PILOT REPORTED THAT WHILE TAXING AFTER A LANDING, THE NOSE GEAR GAVE WAY AND THE AIRCRAFT CAME TO REST ON THE PROPEL	LER SPINNER.  THIS IS AN AMATEUR BUILT AIRCRAFT. THE AIRCRAFT BUILDER MADE THE NOSE WHEEL FORK THAT BROKE. THEREBY LOSIN	G THE NOSE WHEEL AND CAUSING THE NOSE GEAR LEG TO FOLD BACK AND PUTTING THE PROPELLER SPINNER ON THE PAVEMENT.  SINCE TH	IS PART IS INSTALLED ON AN EXPERIMENTAL AIRCRAFT THERE ARE NO STANDARDS  FOR THE AIRCRAFT OR ANY OF THE PARTS.  PREVENTI	ON/SOLUTION, THE PRESENT OWNER HAS RELATED THE OLD PART WAS MADE UP OF ONE QUARTER INCH 2024 T3 ALUMINUM AND THE NEW PAR	T WILL BE ONE EIGHTH INCH 4130 STEEL, BENT TO SHAPE AND THEN HARDENED TO A HARDNESS OF 135-145.	1	M	7	1 	  				EXPA1M71
2004081300055	20040813	00055	GL  	2004	8	13	2004FA0000601    	1	20040727	G	2844		TEE FITTING     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360LYC*   	41514	EA  					ENGINE SERVO	DAMAGED         	B				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SO	15	809ER		50   			40321	L3104651A			DURING MANEUVERS, THE FUEL PRESSURE GAUGE AND ENUNCIATOR SYSTEM WARN OF A LOW FUEL PRESSURE PROBLEM.  ALL ENGINE INDICAT	IONS HOWEVER, SHOW THAT FUEL FLOW AND PRESSURE ARE NORMAL. THIS PROBLEM HAS BEEN EVIDENT IN OTHER AIRCRAFT IN THE FLEET 	OF 10 DA40 AIRCRAFT. THE MOST SUCCESSFUL METHOD OF ELIMINATING THIS INDICATION PROBLEM IS TO BLEED THE AIR THAT SEEMS TO	 HAVE ACCUMULATED IN THE TRANSDUCER LINES AND FITTINGS.			1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2004082300097	20040823	00097	EA  	2004	8	23	2004FA0000602    	2	20040726	G	8530	3116	STUD            	LYC         		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 3 CYL ROCKER	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	04	7610F	2345 	2345 		15317	17273268	L699076			NR 3 CYLINDER INTAKE VALVE ROCKER ARM STUD BACKED OUT CAUSING PUSHROD TO BEND AND HYDRAULIC LIFTER FAILURE.						1	H	7	1 	3O	3	O	NT	3A12    	E274
2004083100023	20040831	00023	SW  	2004	8	31	2004FA0000603    	1	20040729	G	3220		NUT             			SLINDS	100   	10AVOLAIRE  	9550104	SW  	LYC   	O320  	O320*       	41508	EA  					NLG	LOOSE           	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	25	6665D					10A028				SAFETY WIRE BROKE FROM THE NUT THAT RETAINS THE NOSE LANDING GEAR PISTON/PISTON ROD ASSEMBLY INTO THE NOSE STRUT CYLINDE	R TUBE ASSEMBLY. THE PISTON/PISTON ROD ASSEMBLY SEPARATED FROM THE STRUT CYLINDER TUBE ASSEMBLY UPON LANDING.  SUBSEQUEN	TLY THE NOSE GEAR/PISTON ROD ASSEMBLY AND WHEEL ASSEMBLY FOLDED BACK ON IMPACT CAUSING THE AIRCRAFT ROLL OUT TO BE SUPPO	RTED BY THE STRUT CYLINDER TUBE ASSEMBLY. THE STRUT CYLINDER TUBE ASSEMBLY LOWER LEADING EDGE WAS GROUND DOWN DURING THE	 LANDING ROLL OUT.		1	H	7	1 	3O	3	O	 	1A21    	E274
2004091400084	20040914	00084		2004	9	14	2004FA0000604    	4	20040630	G	2397	S2899L50	CIRCUIT BREAKER 			CESSNA	525   	525A        	2076615	CE  										NAV/COMM SYS	ARCED           	B				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CL	CLIMB          	1			CE	07	692JM	1229 				525A0004				THE FOLLOWING SYS FAILED IN FLIGHT:  NR 1 NAV/COMM/XPDR, CO-PILOTS AUDIO PANEL, RT PITOT HEAT, STANDBY HSI, NR 2 ATTITUD	E/HEADING, AUTOPILOT DISENGAGED, LANDING GEAR HYDRAULIC, SYS PRESSURE, LANDING GEAR DOWN AND LOCK INDICATOR LIGHTS, FLIG	HT CREW UTILIZED THE EMERGENCY EXTENSION SYSTEM TO EXTEND THE LANDING GEAR. A LOOSE TERMINAL SCREW WAS FOUND ON BUS SIDE	 OF CB (HC068) LOCATED IN THE LT COCKPIT CB PANEL. TERMINAL SCREW BACKED OUT AND SHORTED TO ADJACENT STRUCTURE.  THIS CA	USED EMERGENCY POWER CB (HC102) IN AFT JUNCTION BOX TO DISENGAGE.  DAMAGED TERMINALS AND CIRCUIT BREAKER (HC068) WERE RE	PLACED.  ALL WIRING AND TERMINALS IN BOTH COCKPIT CB PANELS WERE INSPECTED FOR LOOSE SCREWS AND CHAFING WIRES.	1	L	7	1 	4F			RT	A1WI
2004091500108	20040915	00108	SO  	2004	9	15	2004FA0000605    	1	20040729	G	1430	NAS464P427	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  										NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2163N					447995222				DURING INSPECTION FOUND NOSE GEAR TORQUE LINK BOLT PN NAS464P4-27 SHEARED MID SPAN OF BOLT SHANK. NO SIGN OF EXCESSIVE C	ORROSION.					1	L	7	2 	3O			 	A19S0
2004092300082	20040923	00082	GL  	2004	9	23	2004FA0000606    	1	20040616	G	2823	EA2UJD	SHAFT           			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SELECTOR	MISPINNED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	809ER	296  	99   			40321				THIS FLEET OPERATOR OPERATES 10 DA40 AIRCRAFT. THERE WAS A PILOT REPORT OF THE FUEL SELECTOR NOT FUNCTIONING PROPERLY, A	ND NOT ALLOWING THE PILOT TO SELECT THE OTHER TANK. A FLEET INSPECTION WAS INITIATED, AND THIS AIRCRAFT WAS FOUND TO HAV	E THE SELECTOR SHAFT UNIVERSAL JOINTS WITH LOOSE OR MISSING ATTACH PINS.				1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2004092300069	20040923	00069	CE  	2004	9	23	2004FA0000607    	1	20040721	G	1430	FN22A524	NUT             	DUNLOP      		RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 4 WHEEL	SPLIT           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	91HK	1418 			ZT111	258578				WHILE CLEANING AIRCRAFT DISCOVERED NR 4 MAIN WHEEL 1 EACH TIE-BOLT NUT SPLIT IN HALF. REPLACED ALL WHEEL TIE BOLTS P/N: 	EWB22-5-16 AND NUTS P/N: FN22A524 WITH NEW PARTS.  TIME ON PART SINCE REPAIR UNKNOWN.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
2004092300094	20040923	00094	SO  	2004	9	23	2004FA0000608    	1	20040625	G	1410		LINE            			GULSTM	GV    	GV          	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					SENSE LINE	LOOSE           	C				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			GL	23	300K					587				AT FL 410 RECEIVED A CABIN PRESSURE LOW (RED) MESSAGE ON YTHE CAS. AIRCRAFT INITIATED EDM APPROX. FL 380 CAS MESSAGE EXT	INGUISHED LEVELED OFF AT FL 200. UNDECLARED AN EMERGENCY. APPROX.  10 MIN LATER RECEIVED ANOTHER CABIN PRESSURE LOW MESS	AGE, DECLARED AN EMERGENCY DIVERTED, LANDED WITHOUT INCIDENT. INSPECTED AIRCRAFT IAW MFG M/M. FOUND PRESSURE REFERENCE S	ENSE LINE (B) NUT AND FITTING LOOSE. REMOVED AND REPLACED CPCS IAW M/M 21-31-01.			2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN
2004090800173	20040908	00173	SO  	2004	9	8	2004FA0000614    	1	20040326	G	1430		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	7192Y					30216				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 TOT THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING B	OLTS:  AN24-46A (400-932), AN174-22A (402-321). TT 4542			1	L	7	2 	3O	3	O	 	A1EA    	1E12
2004090800166	20040908	00166	SO  	2004	9	8	2004FA0000619    	1	20040326	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	O320*       	41508	EA  					STABILATOR	CORRODED        	D			Q76E	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	14A	3681 				301208				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)..  THE BOLTS ATTACHING THE STABILATOR TO THE TORQUE TUBE WERE ALSO CORRODE	D SEVERELY.  THE BOLTS HAD TO BE REMOVED BY AN IMPACT TOOL.  THESE WERE TO BE REPLACED OR INSPECTED IAW AD 74-13-03.  TT	 3681.	1	L	7	2 	3O	3	O	 	A1EA    	E274
2004091400118	20040914	00118	SO  	2004	9	14	2004FA0000628    	1	20040809	G	2840	602501	FLOAT SWITCH    			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					FUEL SYSTEM	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	901DM	413  				4697051				OWNER COMPLAINED RT FUEL PUMP WAS INOPERATIVE. TROUBLESHOOT SYSTEM TO A HEAVY FUEL FLOAT SWITCH P/N 602-501. HEAVY FLOAT	 CAUSED FUEL PUMP TO BE INOPERABLE WHEN SELECTED IN MANUAL OR AUTOMATIC.					1	L	7	1 	3O	3	T	RT	A25SO   	E2NE
2004091300193	20040913	00193	SO  	2004	9	13	2004FA0000630    	1	20040709	G	3213	6531903	STRUT           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					MLG	DAMAGED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	01	98151					2826076				LANDING ON GRASS STRIP WHICH WAS NOT AS SMOOTH AS THE USUAL PAVEMENT.  THE STRUT APPEARED TO BE OVER EXTENDED.  UPON CLO	SER LOOK IT WAS NOTED THAT BOTH ON THE EARS WHICH CONNECT THE TORQUE LINK, HAD BROKEN OFF THE STRUT.  CHECKING THE OTHER	 LANDING GEAR SHOWED CRACKS ALSO IN THE SAME AREA.				1	L	7	1 	3O	3	O	 	2A13    	E274
2004092000070	20040920	00070	CE  	2004	9	20	2004FA0000631    	1	20040623	G	7810	NH100089770	CLAMP           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					TURBO TO EXHAUST	CRACKED         	B			W6NR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	346FS					340A0790				WHILE DOING THE EXHAUST AD2000-01-16, THE ONE PIECE V CLAMP THAT HOLDS THE EXHAUST TO THE TURBO WAS FOUND CRACKED APPROX	 50 PERCENT AROUND, REPLACED CLAMP AND LEAK CHECKED OK.  THE CRACKED CLAMP DID NOT APPEAR TO BE OVER TORQUED.					1	L	7	2 	3O	3	O	 	3A25    	E8CE
2004091500100	20040915	00100	SO  	2004	9	15	2004FA0000632    	2	20040615	G	7310	641481	LINE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					INJECTOR	CRACKED         	B			J7BR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	421GF		98   			421C1110	608045			PILOT EXPERIENCED EGT FLUXUATIONS, MADE PRECAUTIONARY LANDING.  INSPECTION REVEALED CYLINDER NR 4 INJECTOR LINE WAS CRAC	KED AND LEAKING FUEL AT THE BASE OF THE BRAZED ON SLEEVE BETWEEN THE SLEEVE AND THE BALL END.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE
2004091500094	20040915	00094	SO  	2004	9	15	2004FA0000633    	1	20040719	G	2730	51757005	CONTROL CABLE   			PIPER 	PA31T 	PA31T2      	7103127	SO  										ELEVATOR	DISCONNECTED    	B			GW1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	31JZ					31T8166062				DURING A ROUTINE EVENT NR 1 AIRFRAME INSPECTION, IT WAS DISCOVERED THE (ELEVATOR) PRIMARY TOP CONTROL CABLE (ELEVATOR CA	BLE) WAS NOT CONNECTED TO THE ELEVATOR BELLCRANK.  THE ELEVATOR CABLE IS SHROUDED BY A CABLE TENSIONER TUBE ASSY.  THE E	LEVATOR CABLE RETAINING BOLT (PN 400-052) WAS POSITIONED THROUGH THE CABLE TENSIONER TUBE (PN 81950-002) AND THE BELLCRA	NK (PN 40307-000), HOWEVER, THE ELEVATOR CABLE (PN 51757-005) WAS NOT SECURED TO THE BELLCRANK, THE ELEVATOR CABLE CLEVI	S DISCONNECTED WITHIN THE CABLE TENSIONER.  A RETAINING CLIP WITHIN THE SPRING TUBE ASSY. WAS THE ONLY DEVICE PREVENTING	 LOSS OF ELEVATOR CONTROL.  (EA03200405977)	1	L	7	2 	3T			RT	A8EA
2004091500078	20040915	00078	CE  	2004	9	15	2004FA0000635    	1	20040707	G	5210	05170392	HANDLE          			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  					PILOTS DOOR	FAILED          	E			SSCA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4736U					U20605072				INTERIOR DOOR HANDLE FELL OFF.  THE INSERT WHICH HAS THE SPLINE REMAINED ON DOOR.  THE DOOR HANDLE IS A NEW STYLE WHICH 	HAS THE PIN WHICH STOPS THE SPLINE INSERT FROM SPINNING INSIDE THE HANDLE.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE
2004091500111	20040915	00111	EA  	2004	9	15	2004FA0000636    	2	20040811	G	8500	O320H2AD	ENGINE          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  						MAKING METAL    	B			VJ0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	75704					17267886	RL122676T			FACTORY OVERHAUL FOUND FERROUS METAL FLAKES (SEVERAL HUNDRED) IN OIL FILTER.  ENGINE REMOVED AND RETURNED TO MFG.						1	H	7	1 	3O	3	O	NT	3A12    	E274
2004091500079	20040915	00079	CE  	2004	9	15	2004FA0000637    	1	20040811	G	3230	2400021	BUSHING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360A1D     	41514	EA  					MLG	SPLIT           	D			VJ0R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	16ED					172RG1189				DURING 100 HR INSPECTION, FOUND BOTH LT AND RT MLG PIVOT BUSHINGS SPLIT AND LEAKING GREASE.  THESE BUSHINGS ARE REQUIRED	 TO BE INSTALLED IAW AD2001-06-06, SB 90-1, SK 172-151.  THE SRM HAS NOT BEEN UPDATED TO SHOW ANY DETAIL OF THIS STYLE B	USHING.  NO INSPECTION PROCEDURES FOR THIS STYLE BUSHING.  PARTS MANUAL ALSO HAS NOT BEE UPDATED.  MUCH CONFUSION ABOUND	S CONCERNING THESE BUSHINGS.  (NM09200412026)			1	H	7	1 	3O	3	O	 	3A17    	E286
2004091400140	20040914	00140	CE  	2004	9	14	2004FA0000638    	1	20040713	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BRAKE	INTERMITTENT    	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	07	1570A	272  				CE1333				DURING FLIGHT, CREW SELECTED (GEAR UP) AND GEAR FAILED TO RETRACT.  AFTER ABOUT ONE MINUTE, THE GEAR RETRACTED.  THE DYN	AMIC BRAKE RELAY WAS FOUND TO BE OPERATING INTERMITTENTLY.  RECOMMEND REPLACEMENT OF RELAY WITH SOLID STATE CIRCUIT BOAR	D.				1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004112400113	20041124	00113		2004	11	24	2004FA0000639    	4	20040606	G	2561	KS9P0101	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										LIFE PRESERVER FAILED MFG.  RECOMMMENDED CELL PRESSURE TEST IAW MM. DOM: OCT 1981.
2004112400135	20041124	00135	NM  	2004	11	24	2004FA0000640    	1	20040630	G	2435	03600923	BEARING         			DHAV  	DHC8  	DHC8202     	2809007	NM  										STARTER GEN	FAILED          	B			OL3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27			1053 		97090					STARTER GENERATOR HAD A BEARING FAILURE.						2	H	7	2 	4T			RT	A13NM
2004091400132	20040914	00132	SO  	2004	9	14	2004FA0000641    	2	20040615	G	8530		CYLINDER        			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					NR 1	FAILED          	B			CRJR	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			CE	01	6329B	157  				34229	069972R			DURING ANNUAL INSP, CYLINDERS NR 1 AND NR 2 WERE FOUND TO HAVE A LOW COMPRESSION AND LEAKAGE PAST THE EXHAUST VALVE.  EN	GINE WAS STILL UNDER WARRANTY AND MFG WAS CONTACTED.  MFG REP SUGGESTED TO READ SB03-3 WHICH SUPERSEDES SB84-15.  SB03-3	 SAYS ANY CYLINDER THAT PASSES COMPRESSION VALUE FOUND WHEN USING THE MASTER ORIFICE CAN BE RETURNED TO SERVICE REGARDLE	SS OF WHERE THE LEAKS WERE.  SB84-15 SAID LEAKAGE PAST ANY VALVE WAS AN UNACCEPTABLE CONDITION.  NR 1 AND NR 2 CYLINDERS	 WERE REMOVED, CLEANED AND MEASURED.  NR 1 EXHAUST VALVE AND GUIDE WERE FOUND TO BE BEYOND SERVICEABLE LIMITS AND WERE R	EPLACED WITH NEW PARTS.  THE GUIDE AND SEAT WERE FOUND NOT TO BE CONCENTRIC. GUIDE AND SEAT WERE GROUND CONCENTRIC.	1	H	7	1 	3O	3	O	NT	3A13    	E273
2004091400176	20040914	00176	EA  	2004	9	14	2004FA0000642    	2	20040601	G	7414		IMPULSE COUPLING			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  					MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	4355F	12113			98060008	287610097	L1299140C			IMPULSE COUPLING FAILED LOCKING MAGNETO, RESULTING IN FAILURE OF GEARS IN ACCESSORY CASE, PN 13S18647, 71652 AND LW-1909	6 GEARS.  FAILURE OCCURRED WHILE FLYING IN PATTERN.  (EA23200400620)					1	L	7	1 	3O	3	O	 	2A13    	E295
2004091400185	20040914	00185		2004	9	14	2004FA0000643    	4	20040624	G	3457	TNL200A	GPS             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C*       	 	GL  					COCKPIT	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	09	656TL					656				ON A PILOT TRAINING FLIGHT, SMOKE WAS OBSERVED COMING OUT OF GPS FACE-PLATE AND THE DISPLAY WENT BLANK.  CB WAS PULLED A	ND AIRCRAFT RETURNED TO BASE.  AFTER SHUTDOWN, POWER WAS APPLIED TO GPS, OPERATION APPEARED NORMAL, BUT SELF DIAGNOSIS D	ISPLAYED A (DATA BASE FAILED) WARNING.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004092000098	20040920	00098	SO  	2004	9	20	2004FA0000644    	2	20040701	G	7414	ES10357426	DISTRIBUTOR BLK 	BENDIX      		CESSNA	172   	172M        	2072418	CE  	CONT  	O360  	IO360GB     	17025	SO  					MAGNETO	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	12585	137  			A081296	17262094	352806			REPLACED WORN POINTS IN MAGNETO.  ON RUN UP FOUND 500 RPM DROP.  REMOVED MAGNETO AND FOUND DISTRIBUTOR BLOCK CONTACT TOW	ERS AND DISTRIBUTOR FINGER OIL SOAKED FROM EXCESS LUBRICANT.  WHILE INSPECTING FOUND DISTRIBUTOR GEAR BUSHING LOOSE IN D	ISTRIBUTOR BLOCK.  OVERHAUL SHOULD FOLLOW MANUAL.				1	H	7	1 	3O	3	O	NT	3A12    	E1CE
2004092000074	20040920	00074	EA  	2004	9	20	2004FA0000645    	2	20040602	G	7314		HOUSING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					EDP	LEAKING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	350PC	207  			GLN005FP	318152006				DURING ENGINE REMOVAL FOR OVERHAUL, FOUND THE ENGINE DRIVEN FUEL PUMP LEAKING FROM AROUND HOUSING ASSY.  (SO05200407947)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004092000100	20040920	00100	EA  	2004	9	20	2004FA0000646    	2	20040713	G	7414		BEARING         			HUGHES	269   	269B        	4470502	WP  	LYC   	O360  	IO360A1A    	41514	EA  					MAGNETO	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	9442F		352  			1150213				MAGNETO OVERHAULED, WAS FOUND TO HAVE A LOOSE ROTOR TAB THAT CHEWED UP THE DISTRIBUTOR BLOCK TERMINALS.  ALSO AN INNER B	EARING RACE WAS LOOSE AND SCORED THE SHAFT AND AN OUTER BEARING RACE WAS LOOSE IN THE CASE AND THE CASE WAS THEREFORE JU	NK.				1	G	7	1 	3O	3	O	 	4H12    	1E10
2004082300059	20040823	00059	SO  	2004	8	23	2004FA0000648    	1	20040819	G	3220	6715003	DOWNLOCK        			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	CRACKED         	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	01	8991E	6854 				28R7635220				DURING INSPECTION FOR AN INTERMITTENT IN TRANSIT LIGHT, DISCOVERED CRACKED NLG DOWNLOCK ASSY.  HALF OF THE IB PERIMETER 	AROUND ACTUATOR ROD ATTACH POINT WAS BROKEN OFF.  REMAINING HALF HAS SEVERAL CRACKS EMANATING FROM BOLT HOLE.  SEVERAL M	ORE GEAR ACTUATIONS WOULD HAVE RESULTED IN COMPLETE SEPARATION.  REPLACED ASSY WITH NEW MFG PART WHICH WAS BEEFIER THAN 	ORIGINAL.  PAY ADDED ATTENTION TO THIS AREA (INCLUDING DRAG BRACE ATTACH AREA) AND DO NOT IGNORE FLICKERING LANDING GEAR	 INDICATION LIGHTS, INVESTIGATE.		1	L	7	1 	3O	3	O	 	2A13    	1E10
2004082300034	20040823	00034	EA  	2004	8	23	2004FA0000649    	2	20040819	G	8550		SUMP            			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					ENGINE OIL SYS	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	05	242ME					20608112	L2724248A			DURING AN ANNUAL INSPECTION THE ENGINE OIL SUMP WAS FOUND CRACKED IN THE LT REAR STUD BOSS WHERE THE STUD US THREADED IN	TO THE SUMP.					1	H	7	1 	3O	3	O	RT	A4CE    	1E4
2004083000065	20040830	00065	WP  	2004	8	30	2004FA0000650    	2	20040819	G	8520		CONNECTING ROD  			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1C	20004	WP  					NR 3 CYLINDER	BROKEN          	G				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			GL	11	7110S		30   			83015				NR 3 CYLINDER CONNECTING ROD BROKE DURING TAKE OFF CAUSING ENGINE DAMAGE. GIPSY MAJOR 1C ENGINE MODEL INSTALLED IN A VIN	TAGE EXPERIMENTAL EXHIBITION AIRCRAFT.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU
2004083000026	20040830	00026	CE  	2004	8	30	2004FA0000652    	1	20040510	G	2810	121640753	RESERVOIR       			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	FUEL SYSTEM	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	72635	950  				20608065	L2710448A	000187		RESERVOIR FUEL TANKS BELOW FUEL SELECTOR WAS LEAKING FUEL FROM A SEEM WELD THAT HAD CRACKED.  FOUND DURING ROUTINE WALK 	AROUND INSPECTION.  THE LEAK WHEN FIRST NOTICED WILL INDICATE THE FUEL PEDCOK IS LEAKING UNDER THE BELLY OF THE AIRCRAFT	 FURTHER INSPECTION LEAD YOU TO INSPECT THE TANK BY REMOVING THE FLOOR PANEL ABOVE THE RESERVOIR.  THERE ARE TWO RESERVO	IR RT/ LT.  ADVISE:  CLOSER INSPECTION DURING 100 HOURS OR ANNUAL INSPECTION USING A MIRROR AND FLASH LIGHT YOU CAN INSP	ECT MOST OF THE RESERVOIR.		1	H	7	1 	3O	3	O	RT	A4CE    	1E4	5	C	P58GL
2004083000109	20040830	00109	SO  	2004	8	30	2004FA0000653    	2	20040420	G	7261	530010816	LINE            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					OIL PRESSURE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	68245	1930 				340A1204				OIL PRESSURE HARD LINES LEAKING OIL UNDER CABIN FLOOR AFT OF PILOTS AND COPILOTS SEATS.  LINES MAKE A 90 DEGREE TURN FOR	WARD AND CONTACT CABIN DUCTWORK.  LINE CORRODED AND APPROXIMATELY 2-3 QUARTS OF OIL DISCOVERED IN CABIN BELOW FLOOR.					1	L	7	2 	3O	3	O	 	3A25    	E8CE
2004083000130	20040830	00130	SO  	2004	8	30	2004FA0000654    	1	20040712	G	3213	486604	STRUT           			PIPER 	PA25  	PA25260     	7102508	SO  	LYC   	O540  	O540*       	41532	EA  					LT MLG	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	4339Y					254833				ON MAKING A SLIP TO A LANDING, THE LT GEAR COLLAPSED.  IT WAS FOUND THAT THE (VEE ASSEMBLY) PULLED OUT OF THE FITTING AS	SEMBLY OF THE SHOCK STRUT.  I RECOMMEND THAT THIS BECOME AN INSPECTION POINT FOR POSSIBLE CRACKS.  THESE AIRCRAFT MAKE H	UNDREDS OF LANDINGS THAT PLACE HIGH SIDE LOADS AT THIS POINT.				1	L	7	1 	3O	3	O	 	2A10    	E295
2004083000128	20040830	00128	CE  	2004	8	30	2004FA0000655    	1	20040607	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DAMAGED         	B			V9MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	5359K					172S9447	L3100251A			STARTER BENDIX FAILED CAUSING DAMAGE TO THE STARTER RING GEAR.  THIS IS THE 6TH STARTER BENDIX FAILURE ON THIS AIRCRAFT.						1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004083000110	20040830	00110	CE  	2004	8	30	2004FA0000656    	1	20040513	G	5322		SUPPORT         			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					BATTERY	CRACKED         	B			WXHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	7267H	2998 				18280591				OB BATTERY SUPPORT ANGLE CRACKED AT BOTH ENDS.  THIS IS THE THIRD INSTANCE IN FLEET.  THE BATTERY SUPPORT STRUCTURE NEED	S TO STRENGTHENED WITH ADDITIONAL STRUCTURE TO PREVENT THIS.  (NM01200410074)					1	H	7	1 	3O	3	O	NT	3A13    	1E4
2004091300104	20040913	00104	CE  	2004	9	13	2004FA0000659    	1	20040630	G	2821	7560052	FUEL STRAINER   			CESSNA	210   	T210M       	2073451	CE  										FUEL SYSTEM	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	8159M	3667 				21062032				AD 2000-06-01 HAS STAND PIPE MEASUREMENT AT 1.68 INCHES.  FOUND STAND PIPE LONG AT 1.75.6.  REPLACED WITH NEW FUEL STRAI	NER WITH STAND PIPE AT 1.68 (AT FLIGHT ICE FOUND STAND PIPE LOOSE ON OTHER AND LIKE AIRCRAFT.  AC; 8159 TT 3667.					1	H	7	1 	3O			 	3A21
2004091300180	20040913	00180	SO  	2004	9	13	2004FA0000660    	1	20040519	G	7160	67775000	DOOR            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					HEAT BOX ASSY	INGESTED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	2495M	68   				28R7837090	L1110451A			PARTIAL LOSS OF ENG PWR OCCURRED JUST AFTER T/O.  MANIFOLD PRESS DROPPED TO 15 INCHES HG AND RPM DROPPED TO 1900.  PRE T	/O ENG RUN UP, ALTERN AIR CHECK WAS REPORTED AS (NORMAL).  POST FLT INSP REVEALED THAT ALTERN AIR (HEAT BOX) DOOR HAD SE	PARATED FROM ALTERNATE AIR BOX ASSY, WAS INGESTED INTO FUEL SERVO INTAKE, PARTIALLY BLOCKED ENG INDUCT AIR FLOW, RESULTE	D IN PARTIAL LOSS OF PWR.  MS20470AD3 RIVETS (3EA) THAT SECURE DOOR TO AIR BOX HAD FAILED.  IMPROPERLY BUCKED RIVETS DUE	 TO EXCESS SPRING TENSION DURING ASSY AND/OR TOO MUCH SPRING TENSION FOR RIVETS TO BEAR.  HEAT BOX DOOR SHOULD BE TETHER	ED IN SUCH WAY, IF HINGE ATTACHMENTS SHOULD FAIL DOOR WON`T BE INGESTED AND/OR SECURED WITH STRONGER FAIL SAFE HDWR.	1	L	7	1 	3O	3	O	 	2A13    	1E10
2004083000085	20040830	00085	SO  	2004	8	30	2004FA0000661    	1	20040819	G	8011		GEAR            	ELECTROSYS  		PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	STARTER	STRIPPED        	B			FFKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	8209C	203  	203  		D123607	32R7680082	L732348A	CH34426C		BENDIX DRIVE GEAR TEETH STRIPPED OUT AFTER ENGAGING STARTER.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920
2004083000122	20040830	00122	CE  	2004	8	30	2004FA0000662    	1	20040820	G	8011	MMU6001	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	STICKING        	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			WP	05	714TW	17   	17   			15279429	L1338615	R774530		STARTER BENDIX ENGAGED RING GEAR DURING FLIGHT. ENGINE RPM LOSS APPROXIMATELY 300 RPM. AIRCRAFT WOULD NOT IDLE WITHOUT A	PPLICATION OF POWER AFTER LANDING.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2004083000067	20040830	00067	GL  	2004	8	30	2004FA0000663    	2	20040228	G	8520		CRANKSHAFT      			AMTR  	SF2A  	SF2A        	       	GL  	AMTR  	AMTR  	4AR1200VOLKS	99999	GL  					ENGINE	FAILED          	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	07	219GK	517  				303				DURING CRUISE PHASE OF FLIGHT, WHILE DEPARTING TRAFFIC PATTERN, AIRCRAFT EXPERIENCED SEPARATION FAILURE OF CRANKSHAFT WI	TH RESULTING LOSS OF PROPELLER, LOSS OF OIL AND SUBSEQUENT ENGINE FAILURE.  ENGINE SPEED APPROX.  3100 RPM, 3700 FT MSL,	 AIRSPEED APPROX 104 MPH.  FAILURE OCCURRED APPROXIMATELY 10 INCHES BEHIND PROPELLER AND AFT OF THE FRONT BEARING.  CRAN	KSHAFT FAILED DIAGONALLY WITH APPROXIMATE 45 DEGREE BREAK.  PROPELLER AND CRANKSHAFT STUB DEPARTED CLEANLY WITH NO RESUL	TING DAMAGE TO AIRFRAME.		1	H	7	1 	3O	3	O	NC	EXPA1H71	EXP3O
2004112900153	20041129	00153	NE  	2004	11	29	2004FA0000668    	2	20040617	G	8520	126209	BOLT            	PWA         							PWA   	R1340 	R1340*      	52016	NE  					CRANKSHAFT	CRACKED         	B			CP2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15		6450 	609  		20497		4214943			THE CRANKSHAFT THRU BOLT APPEARS TO HAVE FRACTURED IN THE AREA JUST BELOW THE THREADS IN THE NECKED DOWN AREA.  THE HEAD	 OF THE COTTER PIN THAT SAFETY LOCKS THE BOLT WAS FOUND IN THE OIL SUMP.  THE ENGINE WAS THEN REMOVED AND DISASSEMBLED. 	 UNKNOWN PROBABLE CAUSE, OTHER THAN POSSIBLE FATIGUE FAILURE AND RESULTED IN FRACTURE OF THE CRANKSHAFT IN THE MATING SP	LINES.								3	R			5E2
2004083000069	20040830	00069	NM  	2004	8	30	2004FA0000669    	1	20040414	G	2912	271N20421	BOWL            	BOEING      		BOEING	757   	757         	UTILUSE	NM  										FILTER	CRACKED         	B			IU6R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01					0187A					FILTER BOWL IS CRACKED AND SEVERED AT THE BOTTOM OF THE THREADED AEA.  THIS IS THE THIRD INCIDENT OF THIS PART FOUND IN 	THE LAST SIX MONTHS.  INADEQUATE DESIGN OR MATERIAL TYPE.  DESIGN AN NEW FILTER BOWL FROM A BETTER MATERIAL.  (JOB NR 18	4025)				2	L	7	2 	4F			RT	A2NM
2004083000073	20040830	00073	SO  	2004	8	30	2004FA0000671    	2	20040311	G	8520		CRANKSHAFT      								CONT  	O300  	O300D       	17022	SO  					ENGINE	MAKING METAL    	C			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03							25171D7D			ENGINE WAS DISASSEMBLED AND INSPECTED.  INSP REVEALED METAL CONTAM OF CRANKSHAFT MAIN, CONNECT ROD BRG INSERTS.  ENGINE 	WAS REASSEMBLE WITH NEW BRG INSERTS AND REPLACEMENT STARTER ADAPTER, WHICH WAS DISASSEMBLED AND INSP BEFORE INSTALLATION	 ON ENGINE.  DISCREPANCIES FOUND DURING INSP OF STARTER ADAPTER THAT CAUSED METAL CONTAM OF ENGINE DURING TEST RUN.  BRA	SS SHAVINGS IN WINDINGS OF THE STARTER ADAPTER CLUTCH SPRING.  STEEL BURRS ON THE CLUTCH SHAFT GEAR SERRATIONS.  CLUTCH 	SHAFT SIZE OF 1.899 WITH A TAPER OF .006.  SPRING HAS PREMATURE WEAR PATTERN.  NR 1  CONNECT ROD BRG WAS DAMAGED DUE TO 	METAL CONTAM, CORRESPONDING CONNECT ROD JOURNAL. MATERIAL FOUND IN OIL FEED CHANNEL OF SHAFT GEAR, MORE BRASS AND STEEL.						3	O			E253
2004092000069	20040920	00069	NM  	2004	9	20	2004FA0000672    	1	20040210	G	7120	1692M35P03	BUSHING         			BOEING	777   	777*        	UTILUSE	NM  	GE    	GE90  	GE9090B     	 	NE  					FWD MNT ASSY	MISSING         	D			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35		27182	17303				900143			DURING SHOP VISIT, IT WAS OBSERVED THAT BUSH CMM REF 71-21-03 FIG 3, ITEM 170 WAS MISSING FROM THE ASSEMBLY OF THE FWD M	OUNT.  THE LOAD BEARING SHOULDER BOLT WAS SUBJECTED TO A SINGLE SHEAR LOAD AS OPPOSED TO A DOUBLE SHEAR IAW DESIGN INTEN	T.  SIMILARLY, ONLY ONE HALF OF THE CLEVIS WAS SUPPORTING THE LOAD.  THE PLATFORM ITEMS, LT LINK ITEM 145, NUT ITEM 160,	 AND RETAINER EXHIBITED FRETTAGE ASSOCIATED WITH EXCESSIVE RADIAL MOVEMENT OF THE END OF THE SHOULDER BOLT.  IT IS NOTED	 THAT THE FORWARD MOUNT ASSY OR SUBASSY DID NOT FAIL AND IT FULFILLED ITS FUNCTION OF SUPPORTING THE ENGINE.  ALL FWD MO	UNT ASSY ON SITE HAVE BEEN INSPECTED WITH NO DEFECTS FOUND.  INDICATES ASSY HAS NOT BEEN DISASSEMBLED SINCE NEW.	2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN
2004091500098	20040915	00098	CE  	2004	9	15	2004FA0000673    	1	20040810	G	2510	05142132	CYLINDER        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					SEAT BACK	DETACHED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	437ER	3047 	10   			172S8653	L2994351A			THE CREW REPORTED A SEAT BACK WHICH WOULD NOT RECLINE PROPERLY. THE MAINTENANCE TECHNICIAN INSPECTED THE SEAT MECHANISM 	AND FOUND THE SEAT RECLINING ACTUATOR WAS BROKEN AT THE AFT ATTACH POINT. THE BREAKAGE WAS AT THE USAGE POINT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004092000077	20040920	00077	CE  	2004	9	20	2004FA0000674    	1	20040719	G	2897		WIRE            			CESSNA	501   	551         	2076605	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BOOST PUMP	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	828SS	6824 				5510205				WHILE PERFORMING, SB550-28-14, THE FUEL BOOST PUMP WIRING INSIDE THE LT AND RT WING TANKS WAS FOUND TO HAVE RUBBED HOLES	 IN THE FUEL TRANSFER LINES INSIDE THE TANKS AND DAMAGED THE WIRING. THE ABOVE BULLETIN ADDRESSES THIS CONCERN AND PROVI	DES INSTRUCTIONS FOR SECURING THE BOOST PUMP WIRING,  THIS IS A MANDATORY BULLETIN ONLY.  WE HAVE HEARD OF OPERATORS WHO	 HAVE BEEN UNWILLING TO DO THIS BULLETIN BECAUSE IT IS NOT ASSOCIATED WITH AN AD AT THIS TIME. WE HAVE DIGITAL PICTURES 	AVAILABLE.		1	L	7	2 	4F	4	F	 	A27CE   	E1NE
2004092000095	20040920	00095	SO  	2004	9	20	2004FA0000675    	2	20040720	G	8520	631716	CRANKSHAFT      			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520T    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	BROKEN          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			NM	04	7736K	1776 	1776 			P21000420	278513R	90DSA10		TSIO-520-T CRANKSHAFT BROKE AT 1776 HOURS SINCE FACTORY REMANUFACTURE. OPERATED BEYOND RECOMMENDED OVERHAUL, CRANK FAILE	D CAUSING UNSCHEDULED LANDING THAT RESULTED IN AN AIRCRAFT ACCIDENT.					1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL
2004092000128	20040920	00128	CE  	2004	9	20	2004FA0000676    	1	20040806	G	2432	G6381	BATTERY         			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					EQUIPMENT BAY	EXPLODED        	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	999AM	86   				5000232				WHILE ATTEMPTING TO PERFORM AN ENGINE START A LOUD NOISE WAS HEARD AND THE START WAS ABORTED.  AN INVESTIGATION REVEALED	 THE MAIN BATTERY HAD EXPLODED.  SEVEN OF THE TWELVE CELL CAPS WERE BLOWN OFF AND THE TOP COVER WAS BROKEN AND BLOWN OFF	.  BATTERY ELECTROLYTE HAD TO CLEANED FROM THE REAR EQUIPMENT BAY.  A LOCAL BATTERY SHOP INFORMED US THEY HAD SEEN THE S	AME PROBLEM WITH THIS TYPE BATTERY SEVERAL TIMES AND THE PROBLEM IS CAUSED BY INTERNAL ARCING IN THE BATTERY CAUSING FUM	ES TO BE IGNITED.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004092300086	20040923	00086	SO  	2004	9	23	2004FA0000677    	2	20040731	G	8530	64680A7	CYLINDER        			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	NR 3	CRACKED         	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	03	73C		183  			51251	670866L	723440		NR 3 CYLINDER CRACKED CIRCUMFERENTIALLY APPROXIMATELY 4 INCHES BELOW THE HEAD.  THE RESULTANT VIBRATION MADE A PRECAUTIO	NARY LANDING PRUDENT.  UPON REMOVAL AND INSPECTION, THE CRACK APPEARED TO VARY BETWEEN 0.060 INCH AND 0.030 INCH (APPROX	IMATE) AS IT PROPAGATED AROUND THE CYLINDER.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
2004092300061	20040923	00061	WP  	2004	9	23	2004FA0000678    	1	20040806	G	2782		FUSE PIN        	DOUG        		DOUG  	DC10  	DC1030F     	3023504	WP  	GE    	CF6   	CF650C2     	30018	NE  					DROOP MECHANISM	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	322FE					47908				RT WING OB SLAT CONTROL MECHANISM HAS ANTI-DROOP FUSE PIN SHEARED.  REFERENCE NON-ROUTINE 39501.						2	L	7	3 	4F	4	F	RT	A22WE   	E23EA
2004092300071	20040923	00071	WP  	2004	9	23	2004FA0000679    	1	20040806	G	5341	ANB73111	ATTACH FITTING  			DOUG  	DC10  	DC1030F     	3023504	WP  	GE    	CF6   	CF650C2     	30018	NE  					WING ROOT	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	322FE					47908				LOWER AFT WING TO CENTER BOX ATTACH SKATE FITTING IS EXFOLIATED, LT WHEEL WELL, FUSELAGE STATION 1366 TO 1381.  REFERENC	E NON-ROUTINE NR 39431.					2	L	7	3 	4F	4	F	RT	A22WE   	E23EA
2004090800048	20040908	00048	EA  	2004	9	8	2004FA0000680    	2	20040802	G	8597	P610072P610113	CONDUIT         			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CHAFED          	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	441CA					17280441				FOUND DURING AN ENGINE CHANGE WHILE INSPECTING THE WIRES IN THE ENGINE COMPARTMENT THE CONVOLUTED TUBING USED TO PROTECT	 THE WIRES WAS CHAFING INTO THE WIRES.  IF LEFT UNATTENDED COULD CAUSE AN OPEN IN WIRES FOR OIL PRESSURE, VACUUM MP AND 	VARIOUS OTHER WIRES OR COULD CAUSE IMPROPER INDICATION OR NO INDICATION OF SYSTEMS.  CORRECTED AS REQUIRED.  (CE07200415	499)			1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004090800049	20040908	00049	CE  	2004	9	8	2004FA0000681    	1	20040802	G	8011	PM2401	STARTER         			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	465CA					17280465				DURING THE ENGINE START THE STARTER BENDIX STAYED ENGAGE.  THIS SHREDDED THE GEARS ON THE STARTER AND DAMAGED THE ENGINE	 FLYWHEEL, GEARS TO THE POINT WHERE THE FLYWHEEL HAD TO BE REPLACED.  ACCORDING TO THE POH THEIR IS NOT REQUIREMENT TO L	OOK AT THE AMP GAUGE LIKE THE OLDER MODELS.  THIS WOULD HAVE SHOWED AN EXCESSIVE AMP DRAW.  THE PILOT REPORTED HE NEVER 	NOTICED ANY PROBLEMS.  NOTE: PIECES OF GEAR FROM THE STARTER AND FLYWHEEL WAS FOUND IN THE ENGINE COWLING AREA.  (CE0720	0415498)		1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004090800053	20040908	00053	CE  	2004	9	8	2004FA0000682    	1	20040802	G	1430		BOLT            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					STARTER	SHEARED         	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	7275R				85044305	172S8026				DURING AN INSPECTION, FOUND 2 OF THE 3 THROUGH BOLTS SHEARED OFF AT THE THREADS, REPLACED THE STARTER.  IF LT UNATTENDED	 WOULD CAUSE THE BACKPLATE OF THE STARTER TO COME OFF.					1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004090800056	20040908	00056	EA  	2004	9	8	2004FA0000683    	2	20040706	G	8530		EXHAUST VALVE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NR 2 CYLINDER	STUCK           	B			RL8R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	738FZ	3248 	1237 			17269955	L493076T			AIRCRAFT EXPERIENCED POWER LOSS DURING CLIMBOUT.  AIRCRAFT CIRCLED AND LANDED AND DEPARTED END OF RUNWAY, ROLLED OUT THR	U RUNWAY LIGHTS.  PROPELLER STRIKE OF ONE LIGHT.  FOUND NR 2 CYLINDER EXHAUST VALVE STUCK AND VALVE GUIDE LOOSE .  FURTH	ER INSPECTION ALSO FOUND EXHAUST PUSH ROD DAMAGED AND PISTON SLIGHTLY CONTACTED EXHAUST VALVE.  REMOVED AND REPLACED CYL	INDER ASSY, PUSH RODS, INTAKE AND EXHAUST ROCKERS, AND PUSH ROD TUBES WITH NEW PARTS.  RECOMMENDED COMPLIANCE WITH MFG M	SB PROP STRIKE INSPECTION BEFORE NEXT FLIGHT.  (GL15200412166) (GL15200412587)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004092000046	20040920	00046	GL  	2004	9	20	2004FA0000684    	2	20040830	G	7230	60483	DIFFUSER        								WILINT	FJ44  	FJ44        	66000	GL  					FLANGE WELD SEAM	CRACKED         	B			WI5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23							1003			A CRACK APPROXIMATELY 12 INCHES IN LENGTH WAS FOUND ALONG THE AFT FLANGE WELD SEAM OF THE DIFFUSER ASSY.											4	F			E3GL
2004090800057	20040908	00057	SO  	2004	9	8	2004FA0000685    	2	20040609	G	8530	712ACA	CYLINDER HEAD   								CONT  	O520  	IO520A      	17032	SO  					ENGINE	CRACKED         	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03							240774R			HOLE THROUGH HEAD OR EXHAUST SIDE, NR7707-14, NR 7707-5 CRACKED HEAD.  EST 500 HOURS SINCE NEW.											3	O			E5CE
2004090800058	20040908	00058	EA  	2004	9	8	2004FA0000686    	2	20040708	G	8550	8526250	OIL COOLER      			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	FAILED          	B			QB2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	82667		1    			187909028	L4855127A	A46232		INSTALLED OVERHAULED OIL COOLER, TO AIRCRAFT ON 4/30/04, TACH 2028.5.  NO LEAKS AT RUN UP.  AFTER INSTALL AND NO LEAKS N	OTICED AFTER TAXI TO HANGER.  AIRCRAFT WAS FLOWN.  OIL COOLER FAILED IN FLIGHT WITH LESS THAN AN HOUR OF FLIGHT TIME.  C	AUSING TOTAL LOSS OF ENGINE OIL.  AIRCRAFT MADE AN EMERGENCY LANDING AT FLYING CLOUD FIELD.  ENGINE HAD TO BE DISASSEMBL	ED AND INSPECTED.  ADDITIONAL INFORMATION WILL BE PROVIDED UPON REQUEST.			1	H	7	1 	3O	3	O	 	1A2     	E274	5	N	P88614
2004083100004	20040831	00004		2004	8	31	2004FA0000687    	4	20040722	G	3442	AV200	RECEIVER        			CESSNA	337   	337         	2075702	CE  	CONT  	IO360 	IO360*      	17025	CE  					WX RADAR SYS	INTERFERENCE    	B			LN7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	2131X					3370031				WSI WEATHER RECEIVER CAUSES INTERFERENCE WITH COMS ON FREQS.  126.425 AND 126.450.  THIS CONDITION MAY EXIST IN OTHER IN	STALLATIONS AND SHOULD BE ADDRESSED IN THE MANUFACTURERS INSTALLATION MANUAL.  (EA13200405796)					1	H	7	2 	3O	3	O	 	A6CE    	E1CE
2004092000064	20040920	00064	SO  	2004	9	20	2004FA0000688    	2	20040724	G	8530	AEC631397	CYLINDER HEAD   			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  	MCAULY	3A32C	D3A32C*     	GL  	NR 4 CYLINDER	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	117HB		154  			E1316	249196R	881193		PILOT LANDED AIRCRAFT AT LT AFTER EXPERIENCING A ROUGH RUNNING ENGINE.  UPON FURTHER INVESTIGATION FOUND THE NR 4 CYLIND	ER HEAD SEPARATED FROM THE BARREL.  FOUND ALL CYLINDERS TO BE ECI CYLINDERS HAVING ONLY 154.73 HOURS IN SERVICE, ALL CYL	INDER REQUIRE REPLACEMENT IAW AD 2004-08-10 AND ECI SB 04-1.  OWNER REPORTS THAT SINCE MAY 5, 2004 THE EFFECTIVE DATE OF	 THE AD, THE AIRCRAFT HAS ONLY FLOWN 21.7 HOURS OF THE 50 THAT THE AD GIVES YOU.			1	L	7	1 	3O	3	O	 	3A15    	E3SO	5	C	P21EA
2004091500089	20040915	00089	SW  	2004	9	15	2004FA0000689    	1	20040623	G	6520	24910	SHAFT           			HYNES 	B2    	B2B         	1440506	SW  	LYC   	O360  	O360A1A     	41514	EA  					T/R GEARBOX	FAILED          	D			WHSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	9023Z	352  				2021				TAIL ROTOR DRIVE FROM 90 GEARBOX TO TAIL ROTOR GEARBOX FAIL AT ATTACHING POINT IN TAIL ROTOR GEARBOX.  BY THE DISCOLORAT	ION OF THE BREAK IT APPEARS THAT IT HAD PARTIALLY CRACKED PRIOR TO TOTAL FAILURE.  THIS CAUSED LOST OF DIRECTIONAL CONTR	OL OF AIRCRAFT.  THE INSTALLATION WAS INSTALL BY THE FACTORY AND HAD NOT BEEN WORK ON BY ANY OTHER MAINTENANCE PERSONAL.	  THIS DID NOT FAIL AT THE ATTACHING BOLT HOLE, WHICH WOULD INDICATE AN ALIGNMENT PROBLEM.  WOULD SUGGEST A FLEX COUPLIN	G INSTALLATION TO ALLOW FOR MISALIGNMENT AND FLEXING OF THE TAIL BOOM PYLON.		1	G	7	1 	3O	3	O	 	2H2     	E286
2004090800020	20040908	00020	SO  	2004	9	8	2004FA0000690    	2	20040701	G	7414	ESIO357174	POINTS          	BENDIX      		CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360GB     	17025	SO  					MAGNETO	WORN            	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NE	01	1258S	137  			A081296	33701894	352806			PILOT REPORTED REAR ENGINE LT MAGNETO INOPERABLE ON RUN-UP.  TROUBLESHOT AND FOUND CONTACT POINTS NOT OPENING FAR ENOUGH	.  NYLON CAM FOLLOWER FOUND MELTED AT CONTACT POINT ARM.  CONTACT COMPARTMENT COVER HAS VENT HOLES THAT ARE COVERED BY I	NSTRUCTIONS IN MASTER SM X40000 S20/S200 .  SUSPECT THAT LACK OF VENTILATION CONTRIBUTED TO SOFTENING OF CAM FOLLOWER EI	THER THROUGH IONIZATION AND OR EXCESS HEAT.  RECOMMEND OPENING VENT HOLES.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE
2004090800042	20040908	00042	SO  	2004	9	8	2004FA0000691    	1	20040611	G	5511	6357102	RIB             			PIPER 	PA32  	PA32R301T   	7103220	SO  										STAB	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	SE12M	5349 				32R8129093				A/C IS IN ANNUAL FOR USA CERT.  DURING INSPECTION FOUND STAB LT OUTTER RIB CRACKING AT BALANCE WEIGHT ATTACHMENT POINTS.	  RIB HAS 3 CRACKS WORKING AFT FROM FORWARD END OF RIB.  CRACKS RANGED FROM 12 MM TO 23 MM IN LENGTH.  LARGEST TRACKING 	THROUGH LOWER FORWARD RIVET/NUT FOR BALANCE WEIGHT ATTACHMENT.				1	L	7	1 	3O			 	A3SO
2004100100061	20041001	00061	EU  	2004	10	1	2004FA0000692    	1	20040826	G	2720	A740255N	CONTROL CABLE   			LET   	L23   	L23SUPERBLAN	1360308	EU  										RUDDER	FRAYED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25										NEW RUDDER CABLE ASSEMBLY, PURCHASED THRU US IMPORTER/DISTRIBUTOR, FOUND TO HAVE BROKEN AND/OR DISTORTED STRANDS IN NUME	ROUS PLACES.					1	K	0	0 	  			 	G60EU
2004090300005	20040903	00005	NM  	2004	9	3	2004FA0000693    	1	20040729	G	5753	65B155351	BRACE           			BOEING	747   	747228F     	1384895	NM  										NR 4 CANOE FAIR	CRACKED         	D			UIEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	15	809MC					20887				DURING A-CHECK ACCOMPLISHING ATLAS AIR ROUTINE WORK CARD 11FM15002 INSPECTION OF LEFT WING FOUND NR 4 FLAP CANOE FAIRING	 TO TRACK FORWARD OUTBOARD FITTING CRACKED IN HALF.  JETIIIB WORK ORDER 1063 NON-ROUTINE NR 132.					2	L	7	4 	4F			 	A20WE
2004090800061	20040908	00061	GL  	2004	9	8	2004FA0000694    	1	20040831	G	7921	P010904	OIL COOLER      			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235N2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	CRACKED         	D				A				UNSCHED LANDING         				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		CR	CRUISE         	1			SO	13	669AM	18   				201025	L2575915	K8593		AIRCRAFT 10 MILES FROM AIRPORT, TRAINING FLIGHT, PRACTICING FLIGHT MANEUVERS.  SMELLED SOMETHING WRONG, SCANNED ENGINE G	AUGES.  NO OIL PRESSURE, BUT OIL TEMPERATURE WAS IN THE GREEN.  DECIDED TO RETURN TO THE AIRPORT AND LANDED UNEVENTFULLY	.  POST FLIGHT INSPECTION - OIL COVERING THE BELLY, WING ROOT AREA, INSIDE THE COCKPIT ON THE FIREWALL, FRONT CARPET, PI	LOT'S SHOES.  NO OIL SHOWING ON DIPSTICK.  REMOVED COWLING.  LEAK APPEARED TO ORIGINATE AT THE OIL COOLER.  REMOVED OIL 	COOLER (MOUNTED TO FIREWALL) AND PRESSURE CHECKED.  FOUND CRACK (APPROX 1 INCH LONG) IN END CAP, ALONG THE MIDDLE OF THE	 BEND RADIUS.	1	L	7	1 	  	3	O		EXPA1L71	E223	5	N	P9045
2004091700073	20040917	00073	SO  	2004	9	17	2004FA0000696    	1	20040909	G	3246	40131	WHEEL           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	15FG					277554112				DURING AN ANNUAL INSPECTION, WAS UNABLE TO LOOSEN LT MAIN WHEEL AXLE NUT.  TIRE PRESSURE WAS FOUND TO BE ABOUT 90 PSI IN	STEAD OF RECOMMENDED 32 PSI.  TIRE WAS DEFLATED AND AXLE NUT WAS ABLE TO BE REMOVED EASILY.  WHEEL DISASSEMBLED AND INSP	ECTED.  FOUND TO BE CRACKED IN TWO PLACES AROUND ADJACENT NUT PLATES.  CRACKS WERE PROBABLY DUE TO OVER INFLATION OF TIR	E.  RT TIRE PRESSURE FOUND TO BE ABOUT 90 PSI ALSO.  BOTH WHEEL ASSEEMBLIES REPLACED WITH NEW.			1	L	7	2 	3O	3	O	 	1A10    	E14EA
2004091700077	20040917	00077	SO  	2004	9	17	2004FA0000697    	2	20040914	G	8550	CH481091	OIL FILTER      			BEECH 	45    	A45         	1152006	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	BLOCKED         	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	09	41W					G127				THE OIL FILTER WAS REPLACED AT THE NORMAL OIL CHANGE INTERVAL. THE ENGINE WAS STARTED TO VERIFY OIL PRESSURE AND LEAK CH	ECK. NO LEAKS NOTED BUT OIL PRESSURE WOULD NOT RISE ABOVE 20 PSI. ( THIS IS THE MINIMUM OIL PRESSURE FOR IDLE POWER ). O	IL FILTER WAS REMOVED FOR INSPECTION AND COMPARED WITH ANOTHER NEW OIL FILTER. THE RUBBER FLAP INSIDE THE FILTER APPEARE	D INSTALLED INCORRECTLY WHEN THE FILTER WAS MANUFACTURED. THE LOW OIL PRESSURE WAS CAUSED BY BLOCKAGE OF THE OIL FLOW IN	 THE FILTER. ANOTHER FILTER WAS INSTALLED AN THE OIL PRESSURE RETUNED TO NORMAL (50 PSI ).		1	L	7	1 	3O	3	O	 	5A3     	E273
2004092000050	20040920	00050	SO  	2004	9	20	2004FA0000698    	1	20040903	G	3233	455987	ACTUATOR        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	855ND	6808 				4495009				FOUND TWO CRACKS IN HOUSING AT PISTON SHAFT END RETAINING CLIP GROOVE AREA.						1	L	7	2 	3O	3	O	 	A19S0   	E286
2004092000051	20040920	00051	SO  	2004	9	20	2004FA0000699    	1	20040903	G	3233	455987	ACTUATOR        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	855ND	6808 				4495009				FOUND TWO CRACKS IN HOUSING AT PISTON SHAFT END RETAINING CLIP GROOVE AREA.						1	L	7	2 	3O	3	O	 	A19S0   	E286
2004092000052	20040920	00052	EU  	2004	9	20	2004FA0000700    	1	20040908	G	3350	F5053136501	SIGN            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					EMERGENCY LIGHT	BURNED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	450K					186				SMOKE WAS OBSERVED IN THE CABIN AFTER START OF TAXI TO ACTIVE RUNWAY. THE CREW SHUT DOWN ENGINES,  SHUTOFF ALL POWER AND	 DISCONNECTED BATTERIES.  FOUND SOURCE OF SMOKE TO BE FROM A NO SMOKING/SEATBELT SIGN LOCATED IN THE LT SIDE OF CABIN AT	 FRAME 20.  THE AIRCRAFT WAS SECURED AND FERRIED TO A MAINTENANCE BASE AND UPON FURTHER INVESTIGATION WE FOUND NO CONCLU	SIVE EVIDENCE BUT SUSPECT THAT THE PROBLEM ORIGINATED AT THE INTERFACE OF THE WIRING TO THE NO SMOKING/SEATBELT SIGN.			2	L	7	3 	4F	4	F	 	A46EU   	E6WE
2004092000057	20040920	00057	GL  	2004	9	20	2004FA0000701    	1	20040907	G	7810	DA403REVB	EXHAUST HEADER  			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	858PA	454  				40258	L3071651A			ON 100 HR INSPECTION FOUND EXHAUST RISER CRACKED AND NEARLY BROKEN AT NR 4 EXHAUST OB MOUNTING BOLT EXTENDING INTO THE W	ELD AROUND THE PIPE.					1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2004092000058	20040920	00058	GL  	2004	9	20	2004FA0000702    	1	20040907	G	7810	DA403REVB	EXHAUST HEADER  			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	858PA	454  				40258	L3071651A			ON INSTALLATION OF NEW NR 4 EXHAUST PIPE, THE FLANGE WELD BEGAN TO CRACK.  THIS WAS WITH LITTLE TORQUE APPLIED THE FLANG	E.  SUBMITTED REPORT TO MFG AND DISCUSSED WHAT MAY POSSIBLY BE CAUSING THIS PROBLEM.  THEY SEEMED TO THINK IT WAS THE US	E OF MFG EXHAUST GASKET WITH THE ASBESTOS CENTER CAUSING THE PROBLEMS, THIS IS THE SAME GASKET THAT IS CALLED FOR IN THE	IR PARTS MANUAL.  THEY RECOMMENDED USING TWO THIN COPPER GASKETS INSTEAD OF THE SINGLE THICKER ASBESTOS/COPPER GASKET.			1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2004092000062	20040920	00062	GL  	2004	9	20	2004FA0000703    	1	20040804	G	7810	DA403REVB	EXHAUST HEADER  			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	858PA	399  				40258	L3071651A			ON 100 HOUR INSPECTION FOUND EXHAUST RISER BROKEN AT NR 2 EXHAUST IB MOUNTING BOLT.  SUBMITTED REPORT TO MFG.						1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2004092000063	20040920	00063	CE  	2004	9	20	2004FA0000704    	1	20040908	G	2910		HYDRAULIC SYSTEM			BEECH 	B300  	B300        	1159232	CE  											CONTAMINATED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	74TF	56   				FL370				DURING THE INITIAL PHASE 1 AND 2 INSPECTION BEING COMPLETED ON AC, ROUTINE INSPECTION OF HYDRAULIC SYS COMPONENTS REVEAL	ED THAT THE HYDRAULIC SYS FILTER HAD RETAINED A LARGE AMOUNT OF RED PLASTIC MATERIAL AND THE (GEAR DOWN) PORT SCREEN WAS	 FOUND TO BE ALMOST COMPLETELY BLOCKED WITH LARGE PORTIONS OF SAME MATERIAL.  PORT SCREEN WAS ITSELF DETACH FROM HOUSING	 ASSY. PLASTIC MATERIAL APPEARED TO BE CONSISTENT WITH MATERIAL THAT LINE CAPS AND PLUGS ARE MADE OF. REVIEW OF MAINTENA	NCE LOG REVEALED THAT NO MAINTENANCE HAD BEEN ACCOMPLISHED ON THE HYDRAULIC SYSTEM SINCE THE AIRCRAFT WAS NEW. THE FOD W	AS LIKELY INTRODUCED INTO THE SYSTEM DURING PRODUCTION ASSEMBLY OF THE HYDRAULIC LINES FOR THE LANDING GEAR SYSTEM.	2	L	7	2 	4T			RT	A24CE
2004092000066	20040920	00066	SO  	2004	9	20	2004FA0000705    	2	20040830	G	8530	ACEC642068SNA	CYLINDER        			UNIVAR	108   	1083        	9230408	NM  	CONT  	O470  	O470R       	17026	SO  					ENGINE	DEBONDED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		114  	114  			1083716	831281R			NICKEL COATING OF INSIDE CYLINDER BARREL PEELING OFF.						1	H	7	1 	3O	3	O	 	A767    	E273
2004092000067	20040920	00067	NM  	2004	9	20	2004FA0000706    	1	20040830	G	8011		SPRING          	CONT        	O470        	UNIVAR	108   	1083        	9230408	NM  	CONT  	O470  	O470R       	17026	SO  					STARTER ADAPTER	SLIPPED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		114  			CAS1458	1083716	831281R			EXCESSIVE WEAR BETWEEN STARTER ADAPTER SPRING AND DRUM.  STARTER DOES NOT ALLOW STARTER ADAPTER TO RELEASE AFTER ENGINE 	START.					1	H	7	1 	3O	3	O	 	A767    	E273
2004092000107	20040920	00107	NE  	2004	9	20	2004FA0000707    	2	20040726	G	7200	8063042	FCU             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					DIAPHRAGM	FAILED          	H				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			NE	03	523JL	515  				523	PCEPRO0394			LOSS OF ENGINE POWER AND LOW TORQUE INDICATION.  ENGINE SHUT DOWN, PROP FEATHERED, EMERGENCY LANDING EXECUTED.  (M)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
2004092000108	20040920	00108	EA  	2004	9	20	2004FA0000708    	2	20040827	G	8530	CL4P10N	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	4295N	55   				288316051	L1345039A			DURING FLIGHT ENGINE STARTED RUNNING ROUGH AND WOULD ONLY DEVELOP 1800 RPM.  PILOT LANDED WITHOUT INCIDENT.  UPON INSPEC	TION FOUND NR 3 CYLINER ROCKER SHAFT BOSS BROKEN AND SHAFT AND ROCKERS LAYING LOOSE IN THE ROCKER BOX COVER.  THE PUSH R	ODS WERE STRAIGHT AND THE VALVES WERE NOT STUCK.  (M)				1	L	7	1 	3O	3	O	 	2A13    	E274
2004092000109	20040920	00109	CE  	2004	9	20	2004FA0000709    	1	20040801	G	5320		PANEL           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUSELAGE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	53CK					BB329				CLOSE OUT PANEL ON AFT SIDE OF REAR SPAR CARRY THROUGH.  TWO CRACKS IN LOWER BEND RADIUS.  FIRST CRACK AT END OF CENTER 	STRINGER AND LOWER END OF ANGLE STRIP ATTACHED TO PANEL SKIN.  SECOND CRACK IS FORWARD OF LEFT OF CENTER STRINGER IN BEN	D RADIUS OF PANEL.  BOTH CRACKS WERE COVERED BY PRESSURE VESSEL SEALANT.  (M)				1	L	7	2 	4T	4	T	 	A24CE   	E4EA
2004092000111	20040920	00111	CE  	2004	9	20	2004FA0000710    	1	20040609	G	2120	AN737TW107	CLAMP           			CESSNA	500   	S550        	2076607	CE  										ACM	LOOSE           	H				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NE	03	999HC					S5500030				CLIMBING THROUGH FL27, A POP WAS HEARD FROM THE REAR COMPARTMENT OF AC.  INSTANTLY CABIN RATE OF CLIMB WENT TO 4K FPM UP	.  CLEARED BY ATC, AC DESCENDED TO FL10 AND CONTINUED ON TO LAND AT ITS INTENDED DESTINATION.  INVESTIGATION FOUND CLAMP	 THAT SECURES COUPLING P/N 65153165-202 TO THE PRESSURE SIDE OF AIR CYCLE MACHINE WAS INCORRECTLY PLACED, TORQUED AND IN	SPECTED DURING JUST COMPLETED INSPECTION, ALLOWING DUCT TO PART, CAUSING CABIN TO VENT TO ATMOSPHERE.  AC WAS REPAIRED A	ND RETURNED TO SERVICE WITH NO FURTHER COMPLICATIONS.  A REVIEW OF INCIDENT HAS RESULTED IN A MORE AGGRESSIVE INSPECTION	 AND TRAINING PROGRAM FOCUSING ON SELF INSPECTION AND MORE THROUGH INSPECTION BY TECHNICIANS AND INSPECTORS.  (M)	1	L	7	2 	4F			RT	A22CE
2004092000121	20040920	00121		2004	9	20	2004FA0000711    	4	20040721	G	2562	450017	ANTENNA         			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					ELT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8900P					244355				DURING AN ANNUAL INSPECTION, THE ELT ANTENNA ON AIRCRAFT WAS DISCOVERED TO HAVE FAILED.  THE ANTENNA FAILED AT THE BULKH	EAD FITTING.  IT APPEARS TO BE SIMPLY GLUED INTO THE FITTING.  THIS ANTENNA P/N 450017 HAS BEEN RECENTLY UP GRADED INDIC	ATING THE MANUFACTURER KNOWS ABOUT THIS DEFECT.  PN 450017 SUPPLIED PRIOR TO JUNE 2004 ARE SUSPECT.  A PULL TEST WILL DE	TERMINE INTEGRITY.  (M)			1	L	7	1 	3O	3	O	 	1A15    	E14EA
2004092300054	20040923	00054	CE  	2004	9	23	2004FA0000712    	1	20040609	G	2120	AN737TW107	CLAMP           			CESSNA	500   	S550        	2076607	CE  										ACM	INCORRECT       	H				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			NE	03	999HC					S5500030				CLIMBING THROUGH FL27, POP WAS HEARD FROM REAR COMPARTMENT OF AIRCRAFT.  INSTANTLY CABIN RATE OF CLIMB WENT TO 4K FPM UP	.  CLEARED,  AIRCRAFT DESCENDED TO FL10 AND CONTINUED ON TO LAND AT ITS INTENDED DESTINATION.  INVESTIGATION FOUND THAT 	CLAMP THAT SECURES COUPLING P/N 65153165-202 TO PRESSURE SIDE OF AIR CYCLE MACHINE WAS INCORRECTLY PLACED, TORQUED AND I	NSPECTED DURING JUST COMPLETED INSPECTION, ALLOWING DUCT TO PART, CAUSING CABIN TO VENT TO ATMOSPHERE.  AIRCRAFT WAS REP	AIRED AND RETURNED TO SERVICE WITH NO FURTHER COMPLICATIONS.  A REVIEW OF THIS INCIDENT HAS RESULTED IN A MORE AGGRESSIV	E INSPECTION AND TRAINING PROGRAM FOCUSING ON SELF INSPECTION, MORE THROUGH INSPECTION BY THE TECH AND INSPECTORS. (M)	1	L	7	2 	4F			RT	A22CE
2004092300016	20040923	00016	EA  	2004	9	23	2004FA0000713    	2	20040916	G	7322	HA6	CARBURETOR      			AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	BINDS           	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			WP	07	959TE	50   	50   			10238				ON FINAL APPROACH TO THE AIRPORT, REDUCED POWER AND LOWERED THE FLAPS. TRIED TO ADD POWER, THE THROTTLE BOUND.  REMOVED 	THE THROTTLE CABLE AND IT'S MOVEMENT WAS FREE. THEN ACTUATED THE THROTTLE ARM ON THE CARBURETOR AND BINDING COULD BE FEL	T ON THE LAST .333 OF THE MOVEMENT.  CALLED THE FACTORY AND THEY SAID THERE WERE OTHER OCCURRENCES OF THIS PROBLEM WITH 	THIS MODEL CARBURETOR. THIS IS A NEW AIRPLANE WITH A NEW CARBURETOR.			1	L	7	1 	3O	3	O	 	A16EA   	E286
2004092300051	20040923	00051	CE  	2004	9	23	2004FA0000715    	1	20040826	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5599P	228  				CE1344				LANDING GEAR WOULD NOT RETRACT IN FLIGHT.  AIRCRAFT WAS PLACED ON JACKS AND THE LANDING GEAR CYCLED IAW MM.  INSPECTION 	OF THE SYSTEM FOUND THAT THE DYNAMIC RELAY WOULD STICK IN THE DOWN POSITION.  A NEW DYNAMIC RELAY WAS INSTALLED AND THE 	SYSTEM CHECKED NORMAL.  SUGGEST REPLACING RELAY WITH SOLID STATE BOARD.				1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004092300049	20040923	00049	EU  	2004	9	23	2004FA0000717    	1	20040727	G	7430	103570101	IGNITION SWITCH 			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					CABIN	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF					85004				AFTER INSTALLING IGNITION SWITCH, THE MECHANIC NOTICE THE SWITCH WAS HARD TO PUSH IN AND INTERMITTENT AT THE START POSIT	ION.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4
2004092300038	20040923	00038	CE  	2004	9	23	2004FA0000718    	1	20040727	G	8011	65556624V	STARTER         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	5540P	252  				CE1335				DURING ATTEMPTING TO START THE ENGINE, THE STARTER WOULD NOT TURN ENGINE TO START.  MAINTENANCE TECHNICIAN FOUND THAT TH	E STARTER WOULD NOT START THE ENGINE.  REPLACED STARTER AND ENGINE STARTED.					1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004092300046	20040923	00046	SO  	2004	9	23	2004FA0000719    	2	20040728	G	7261	ES48109	OIL FILTER      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	TORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1563A	50   				CE1320				WHILE THE MECHANIC WAS INSPECTING THE FILTER ELEMENT FOR METAL PARTICLES, NOTICED THE FILTER WAS TEARING AT THE SEAMS.  	PROBABLE CAUSE UNKNOWN, MFG HAS BEEN NOTIFIED.					1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004092300039	20040923	00039	EU  	2004	9	23	2004FA0000720    	1	20040727	G	8011	31B22101	STARTER         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					ENGINE	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	40   				85004				PILOT REPORTED STARTER WOULD NOT ENGAGE, PROBABLE CAUSE AT THIS TIME UNKNOWN.						1	L	7	1 	3O	3	O	RT	A49CE   	1E4
2004112900118	20041129	00118	SW  	2004	11	29	2004FA0000721    	1	20040715	G	6700		MOUNT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20      	03013	GL  					NOTAR FAN	OUT OF POSITION 	C			PO7M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	529FB					LN0098				AIRCRAFT FOUND TO HAVE CONTACT WITH FAN CONTROL ROD AND FAN DRIVESHAFT, WHICH MAY HAVE BEEN THE CAUSE OF HIGH VIBRATION 	IN AIRFRAME.  MFG CALLED TO CHECK THE ALIGNMENT OF THE FAN MOUNT.  SECOND TIME, HAD RUB WITH DRIVESHAFT SINCE AIRCRAFT W	AS NEW.				1	G	7	1 	3U	3	U	NC	H3WE    	E4CE
2004092800062	20040928	00062	SW  	2004	9	28	2004FA0000722    	1	20040715	G	5302		MOUNT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20      	03013	GL  					NOTAR FAN G/B	OUT OF ADJUST   	C			PO7M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	528FB					LN0097				AIRCRAFT OVERCOME WITH SEVERE VIBRATION ON THROTTLE ROLL UP FROM GROUND IDLE TO FLIGHT IDLE.  FOUND FAN CONTROL ROD MADE	 CONTACT INSIDE FAN DRIVESHAFT.  UPON FURTHER INSPECTION FOUND FAN TRANSMISSION MOUNT AT STATION 150 OUT OF ALIGNMENT.  	SENDING AIRCRAFT BACK TO MFG FOR REPAIR SECOND TIME WE HAD RUB WITH DRIVESHAFT SINCE AIRCRAFT WAS NEW.				1	G	7	1 	3U	3	U	NC	H3WE    	E4CE
2004092300041	20040923	00041	CE  	2004	9	23	2004FA0000724    	1	20040830	G	2710		BEARING         			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320*       	41508	EA  					AILERON CONTROL	DISLODGED       	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	07	3202T	2598 				17700502				IN FLIGHT, NOTICED THAT LOSS OF AILERON CONTROL INPUT HAD OCCURRED, AND UPON ADDED FORCE TO CONTROL YOKE, DETERMINED THA	T TOTAL SEIZURE OF THE AILERONS HAD OCCURRED.  LANDED WITH RUDDER CONTROL ONLY.  REMOVED TUBE ASSY FROM FIREWALL AND FOU	ND SHAFT AND BEARING TO BE SEVERELY WORN, APPARENT NEEDLE BEARING DISLODGING CAUSED INABILITY TO ROTATE YOKE FOR AILERON	 CONTROL INPUT.			1	H	7	1 	3O	3	O	NT	A13CE   	E274
2004092300036	20040923	00036	CE  	2004	9	23	2004FA0000725    	1	20040921	G	3230	24411001	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	B			HBKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	9572B					172RG0889				IN FLIGHT THE LT LANDING GEAR WOULD NOT COME DOWN.  THE PILOT WAS ABLE TO MANUALLY GET THE GEAR DOWN AND LOCKED FOR LAND	ING.  UPON INVESTIGATION IT WAS DISCOVERED THAT THE LT MAIN LANDING  GEAR PIVOT ASSEMBLY SHAFT WHERE THE ACTUATOR ATTACH	ES HAD BROKEN AND WHEN THE GEAR WAS SELECTED TO THE DOWN POSITION THE ACTUATOR COULD NOT MOVE THE LT GEAR.  IT APPEARS T	HAT THE SHAFT TO CRACK HALF WAY AROUND THE CIRCUMFERENCE OF THE SHAFT OVERTIME WHICH CAUSED THE FINAL FAILURE OF THE SHA	FT.  AT SOME POINT AND TIME THERE SHOULD BE A REQUIREMENT FOR THE GEAR TO BE REMOVED FOR A DETAILED INSPECTION.  THE ARE	A IN WHICH THE FAILURE OCCURRED ON THIS PIVOT ASSY COULD ONLY HAVE BEEN SEEN WITH LANDING GEAR REMOVED.	1	H	7	1 	3O	3	O	 	3A17    	E286
2004092300042	20040923	00042	GL  	2004	9	23	2004FA0000726    	3	20040826	G	6111	84334	BLADE           													HARTZL	HCA3V	HCA3VF4     	GL  	PROPELLER	CRACKED         	B			NWOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05								BL290		BLADE CRACKED .7500 AROUND RETENTION AREA.  PROP IS BEING USED ON S OR V MODEL.																5	C	P6EA5
2004112900041	20041129	00041	GL  	2004	11	29	2004FA0000727    	3	20040812	G	6114	D2A34C98	HUB             													MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B			NWOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05								744998		CRACKED THRU RETENTION THREADS AT CRANK FLANGE SIDE H1 SOCKET.  THIS FAILURE INDICATES THAT THE AD REQUIRING OIL FILLING	 OF THE HUB IS WORKING.  PROP WAS SENT TO PROP SHOP DUE TO RED DYE LEAK.  PROP WAS PREVIOUSLY OIL FILLED IAW AD.															5	C	P3EA
2004112400154	20041124	00154	GL  	2004	11	24	2004FA0000728    	3	20040812	G	6114	D2A34C98	HUB             													MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05								780317		CRACKED THRU RETENTION THREADS AT CRANK FLANGE SIDE, NR 2 SOCKET.  THIS FAILURE INDICATES THAT THE AD REQUIRING OIL FILL	ING OF HUB IS WORKING.  PROP WAS SENT TO PROP SHOP DUE TO RED DYE LEAK.  PROP WAS PREVIOUSLY OIL FILLED IAW AD.															5	C	P3EA
2004112400155	20041124	00155	GL  	2004	11	24	2004FA0000729    	3	20040812	G	6114	D2A34C98	HUB             													MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B			NWOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05								767342		CRACKED THRU RETENTION THREADS AT CRANK FLANGE SIDE OF NR 1 SOCKET.  THIS FAILURE INDICATES THAT THE AD REQUIRING OIL FI	LLING OF THE HUB IS WORKING.  PROP WAS SENT TO PROP SHOP DUE TO RED DYE LEAK.  PROP WAS SENT TO PROP SHOP DUE TO RED DYE	 LEAK.  PROP WAS PREVIOUSLY OIL FILLED IAW AD.														5	C	P3EA
2004092300045	20040923	00045	EA  	2004	9	23	2004FA0000732    	2	20040803	G	7322	MA4105217	CARBURETOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	BURNED          	G			FJPS	O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			SO	03	1307H	281  				287716015				THIS AIRCRAFT ENGINE HAS EXPERIENCED TWO FIRES.  BOTH OF WHICH WERE CARBURETOR FAILURE.  THIS WAS CAUSED BY A SPLIT FLOA	T THAT A PREVIOUS AD SHOULD HAVE SOLVED.  THE NEW FLOAT SPLIT AND THE FLOAT FILLED WITH FUEL THIS CAUSED THE ENGINE TO Q	UIT.  THE AIRCRAFT WAS BEING USED AS A INSTRUCTIONAL FLIGHT WITH TWO PILOTS ON BOARD.  AT RESTART PROCEDURES WERE BEING 	CONDUCTED ON THE ACTIVE RUNWAY THE AIRCRAFT CAUGHT FIRE. (SO03200402575)			1	L	7	1 	3O	3	O	 	2A13    	E274
2004092800056	20040928	00056	SW  	2004	9	28	2004FA0000733    	1	20040811	G	5302		MOUNT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20      	03013	GL  					NOTAR FAN	OUT OF POSITION 	B			PO7M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	529FB	1543 				LN0098				AIRCRAFT FOUND TO HAVE CONTACT WITH FAN CONTROL ROD AND FAN DRIVESHAFT.  WHICH MAY HAVE BEEN THE CAUSE OF HIGH VIBRATION	 IN AIRFRAME.  MFG CALLED TO CHECK THE ALIGNMENT OF THE FAN MOUNT.  SECOND TIME WE HAD RUB WITH DRIVESHAFT SINCE AIRCRAF	T WAS NEW.  UPON REMOVAL FOUND PAINT INSIDE MAST BLISTERED AND FALLING DOWN INSIDE M/R GEARBOX.  WE HAVE THIS PROBLEM NI	NE OTHER TIMES IN LAST 4 YEARS.			1	G	7	1 	3U	3	U	NC	H3WE    	E4CE
2004101500098	20041015	00098	GL  	2004	10	15	2004FA0000734    	1	20040922	G	5730		PANEL           			AMTR  	LANCAR	LANCAIRLEGAY	056141X	GL  	CONT  	O550  	IO550*      	 	SO  					WING	MISSING         	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	07	103LL	44   	44   			L2K182				DURING A LT TURN IN A PLEASURE FLIGHT; THE TOP LT IB PANEL FLEW OFF AND THERE WAS LOSS OF LIFT IN LT WING. IN TRYING TO 	LAND, HAD TO MAINTAIN HIGH AIRSPEED, MADE A HARD LANDING.  NOSE WHEEL BROKE OFF, PROPELLER WAS DAMAGED.  MISSING PANEL I	S JUST OB OF THE FUSELAGE, APPROX. 3 FEET BY 3 FEET, JUST ABOVE THE LT MAIN LANDING GEAR. PANEL IS A CARBON PILE MATERIA	L ATTACHED TO STRUCTURE BY THE BONDING OF EPOXY GLUE.  PILOT/ BUILDER/ OWNER REPORTED EPOXY WAS A JEFFCO EPOXY, 3176, 30	 MINUTES.  PANEL ON RT WING WAS FINISHED WITHIN A COUPLE WEEKS OF THE LT WING.  IAW OWNER, NO REPAIRS WILL BE STARTED UN	TIL LANCAIR HAS INSPECTED THE AIRCRAFT. AS OF THIS DATE THE MISSING PANEL HAS NOT BEEN LOCATED.	1	L	7	1 	3O	3	O	RT	EXPA1L71	E3SO
2004100400074	20041004	00074	CE  	2004	10	4	2004FA0000735    	1	20040907	G	3246	40170A	WHEEL           			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	77HE					LJ969				INNER WHEEL HALF OF WHEEL ASSEMBLY PN 40-170A, SN 10, HEAT LOT NR 283 WAS REJECTED DURING EDDY CURRENT INSPECTION FOR CR	ACKS IN EXCESS OF 0.010 INCH.  INDICATIONS WERE FOUND IN THE AREA OF BEAD SEAT OF THE INNER HALF OF THE WHEEL ASSEMBLY O	NLY, NO INDICATIONS WERE FOUND ON THE OUTER WHEEL HALF OF THE ASSEMBLY.				1	L	7	2 	3T	3	T	 	3A20    	E2NE
2004100400077	20041004	00077	EU  	2004	10	4	2004FA0000736    	1	20040913	G	2720	792200200N7134	FORK            			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A6       	52043	EA  					RUDDER PEDAL	BENT            	B			JULR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	220MA					248				LT RUDDER PEDAL WENT TO FLOOR ON TAXI OUT.  FOUND FORK END SHEARED AT JAM NUT.  WHEN BOLT AND CASTLE NUT WERE REMOVED, C	ASTLE NUT WAS EXTREMELY TIGHT AND BOLT COULD NOT ROTATE.  THIS COULD BE CAUSE OF THE PROBLEM.  RUDDER PEDAL NUT AND BOLT	 ON OTHER RUDDER PEDAL WAS LOOSE ENOUGH TO ROTATE.  OTHER CAUSE COULD BE MFG DEFECT OR FOR SOME REASON THE ROD ON FORK E	ND WAS POSSIBLY BENT.			1	L	7	1 	3T	3	T	RT	A60EU   	E4EA
2004100100119	20041001	00119	SO  	2004	10	1	2004FA0000737    	1	20040816	G	2497		BATTERY CABLE   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					BATTERY BAY	OVERHEATED      	D			F6FS	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	19	467TC	8126 				347870006				LT ENGINE HARD STARTING.  EXCESSIVE AMPERAGE DRAW THROUGH BATTERY CABLES CAUSING HOT CABLES AND SUBSEQUENT BATTERY FIRE.	  REPLACED BATTERY POSITIVE AND NEGATIVE CABLES, RT AND LT STARTER CABLES, ENGINE (STARTER) TO GROUND CABLES, MASTER SOL	ENOID TO TERMINAL CABLE, AND TERMINAL TO STARTER SOLENOID CABLES.  CABLE KIT IS A COMPLETE STC AND CONVERTS FROM ALUMINU	M TO COPPER WIRE.  OPERATIONAL CHECK AFTER CABLE REPLACEMENT SHOWS ENGINES TURN OVER MUCH FASTER THAN BEFORE.  (SO192004	18338)		1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004100400078	20041004	00078	EA  	2004	10	4	2004FA0000738    	2	20040909	G	7250	3053094	TURBINE         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					HOT SECTION	SHIFTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	40PT	258  			5032895	BB1291				NEW STYLE PN SEGMENT INSTALLED AT HSI 258 HOURS PRIOR.  THIS NEW STYLE SEGMENT SHIFTS AFT RESULTING IN HOT SECTION FAILU	RE.  VERY COMMON WITH THIS PN SEGMENT, MFG NEEDS TO CHANGE DESIGN.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA
2004092800060	20040928	00060	CE  	2004	9	28	2004FA0000739    	1	20040812	G	2450	AC2101	CONTROLLER      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALTERNATOR	FAILED          	B			MYNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	45EF	1765 				172S8982				ALTERNATOR VOLTAGE WENT OVER VOLT.  OV PROTECTION FAILED AND BUSS VOLTAGE WENT WAY HIGH BURNING UP EVERTHING THAT WAS TU	RNED ON INCLUDING NAV LIGHTS, LANDING AND TAXI LIGHTS, ALL RADIOS, MOST INSTRUMENT LIGHTS AND ALL ELEC INSTRUMENTS, ANNU	NCIATOR PANEL, INTERCOM.  (GL11200413843)				1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004111000070	20041110	00070	CE  	2004	11	10	2004FA0000740    	1	20040910	G	1430	MS2000626	BOLT            			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  					MLG WHEEL	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	598JL				MAY8538	RJ19				RT MAIN TIRE SIDEWALL AND TREAD DEPARTED AIRCRAFT ON LANDING ROLLOUT.  DETERMINED BROKEN WHEEL THROUGH BOLT DISLODGED IN	SIDE WHEEL HALF CAUSED BREAKAGE OF FUSIBLE PLUG AND EVENTUAL DEFLATION OF TIRE DURING FLIGHT.  AIRCRAFT LANDED ON DEFLAT	ED TIRE.  (CE09200404725)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA
2004100400094	20041004	00094	CE  	2004	10	4	2004FA0000741    	1	20040816	G	2701	805241051	BEARING         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					CONROL YOKE	STICKING        	D			X76R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	729P	210  				E3489	685975			PILOT REPORTS THAT THE AILERON CONTROL LOCKS UP AND WILL NOT TURN IN EITHER DIRECTION AND THEN RELEASES AND RETURNS TO N	ORMAL.  UPON INSPECTION OF AILERON SYSTEM, IT WAS FOUND THAT THE CONTROL YOKE CONNECTION BEARING WAS STICKING AND WOULD 	NOT RELEASE UNTIL THE YOKE WAS MOVED EITHER FORWARD OR AFT.  MFG TECH SUPPORT, WHO STATED THAT THE BEARING IS A 100 HOUR	 LUBRICATION ITEM AND THAT LUBRICATION SHOULD CLEAR UP THE PROBLEM.  THE PART WAS LUBRICATED AND NO BINDING OF THE CONTR	OL COLUMN WAS FOUND.  AC RETURNED FOR REPLACEMENT OF BEARING.		1	L	7	1 	3O	3	O	 	3A15    	E3SO
2004100400097	20041004	00097	SO  	2004	10	4	2004FA0000743    	2	20040827	G	8530	654650	CYLINDER        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 6	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	735UL	1043 				18265694	465734			ON TAKEOFF AT CLIMB OUT, PILOT HEARD LOUD BANG FOLLOWED BY ROUGH ENGINE, DECLARED EMERGENCY AND LANDED WITHOUT FURTHER P	ROBLEMS.  WITH OIL LEAKING FROM COWL, VISUAL INSPECTION NOTED HEAD SEPARATED FROM NR 6 CYLINDER.  WITH COWL REMOVED AND 	CYLINDER OFF, IT WAS OBVIOUS THE CYLINDER HAD BEEN PARTIALLY CRACKED FOR SOME TIME.  (SO05200410648)				1	H	7	1 	3O	3	O	NT	3A13    	E273
2004100100073	20041001	00073	CE  	2004	10	1	2004FA0000744    	1	20040923	G	2810	C1560030101	CAP             	CESSNA      		CESSNA	172   	172         	2072402	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL TANK	CLOGGED         	B			EHHR	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			EA	17	8214X					17248714	L2561736A	F766A2		PILOT EXPERIENCED FUEL INTERUPTION.  MADE EMERGENCY LANDING IN SOYBEAN FIELD. NO INJURIES OR DAMAGE TO AC.  REMOVED AC F	ROM FIELD TO LOCAL AIRPORT. DRAINED ALL FUEL FROM WING TANKS. FOUND WHILE DRAINING FUEL WITH FUEL CAPS ON THAT DRAINING 	FUEL WAS SLOW. REMOVED FUEL CAP, QUICKENED FLOW RATE AT FUEL DRAIN. AFTER CLOSE INSP, FOUND VENT HOLES CLOGGED WITH HARD	 MUD TYPE SUBSTANCE. ALSO FOUND THE VENT TUBE IN THE LT WING WAS RESTRICTED. BLOWING NITROGEN THROUGH TUBE FREED BLOCKAG	E. FRESH FUEL WAS INSTALLED, FUEL CAPS WERE REPLACED WITH NEW. LENGHTY RUNUP WAS PERFORMED WITH NO DEFECTS NOTED. FLIGHT	 WAS MADE WITHOUT INCIDENT.  AFTER ARRIVING, OWNER REQUESTED TO REPLACE THE FUEL SELECTOR AS PRECAUTIONARY MEASURE.	1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P920
2004100400088	20041004	00088	CE  	2004	10	4	2004FA0000745    	1	20040424	G	7160	05521644	AIR BOX         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CARBURETOR	DAMAGED         	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			NM	03	5048E	7993 				17271699	L217076T			DURING RUN-UP, BEFORE DEPARTURE, THE CARBURETOR HEAT WAS CHECKED AT 1000 AND 1700 RPM WITH ABOUT 75 RPM DROP.  DURING TH	E FLIGHT BACK, IN CRUISE FLIGHT, THE CARB HEAT WAS CHECKED AGAIN AT VARIOUS POWER SETTINGS, WORKING NORMALLY WITH ABOUT 	A 100 RPM DROP.  AFTER ARRIVAL, THE CARBURETOR AIR BOX WAS REMOVED FOR INSPECTION.  UPON INSPECTION, 2 EA .7500 IN PIECE	S OF THE FLAPPER VALVE SEAL WERE FOUND MISSING ON TWO CORNERS OF THE FLAPPER VALVE.  OTHERWISE, THE CARBURETOR AIR BOX A	SSY WAS INTACT.		1	H	7	1 	3O	3	O	NT	3A12    	E274
2004092800054	20040928	00054	CE  	2004	9	28	2004FA0000746    	1	20040802	G	5511	24320004	SPAR            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					HORIZONTAL STAB	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	4190V	3164 				17280626				DURING INSP, HORIZONTAL STABILIZER WAS FOUND TO BE LOOSE AT BOTH FORWARD SPAR MOUNT HOLES.  ENTIRE EMPENNAGE WAS REMOVED	 FROM AIRFRAME FOR DETAILED INSP.  BOTH HOLES AT STABILIZER SPAR AND FORWARD BULKHEAD WERE FOUND TO BE ELONGATED .316 IN	CH TO .319 INCH.  BOTH SHIMS BETWEEN STAB AND BULKHEAD WERE EXTREMELY ELONGATED AND APPEAR TO HAVE BEEN COUNTERSUNK PRIO	R TO INSTALLATION AT FACTORY.  BOTH SHIMS REMOVED WERE A THICKNESS OF .080 INCH.  BOLTS REMOVED FROM FWD SPAR MOUNTS WER	E AN5-6A, WHICH IS CORRECT HARDWARE IAW MM.  BOLTS INSTALLED FROM MFG DID NOT HAVE SUFFICIENT GRIP LENGTH TO SUPPORT TOT	AL MATERIAL THICKNESS.  RECOMMEND REAMING ALL 4 HOLES TO .371 IN TO .374 IN AND INSTALLING AN6-10A BOLTS.	1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004100400076	20041004	00076	EA  	2004	10	4	2004FA0000747    	2	20040628	G	8550	75141	SUMP            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					OIL SYSTEM	CORRODED        	D			T56R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	05	2850T	2853 				28R7235146	L2208551A			OWNER HAD OIL LEAK, UPON INSPECTION, FOUND OIL DRIPPING FROM OIL SUMP FWD OF RT INTAKE PORT.  REMOVED OIL SUMP, FOUND AR	EA APPROX. 2.5 INCHES IN DIA.  PITTED AND CORRODED.  ONE AREA HAD PITTED THROUGH AND LEAKED.  ENTIRE AREA WAS CLOSE TO P	ITTING THROUGH.  IAW MFG TECH, WAS CAUSED BY TOO MUCH TIME ON OIL AND AIRCRAFT NOT FLOWN ENOUGH TO KEEP MOISTURE OUT OF 	OIL.			1	L	7	1 	3O	3	O	 	2A13    	1E10
2004092800059	20040928	00059	EU  	2004	9	28	2004FA0000748    	1	20040803	G	3340	032452032470	MOUNT           			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					SPOT LIGHT	DAMAGED         	B			EH1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	172P	433  				14027				AT 25 HR INSPECTION, MECH HEARD A RATTLING NOISE WHEN INSPECTING NIGHTSUN II.  LENS WAS REMOVED, REFLECTION WAS REMOVED.	  FOUND BOTH MOUNTING PLATES (PN032452, PN 032470) REV X1 BROKEN COMPLETELY OFF AT REFLECTOR BUT STILL SCREWED TO MOUNT.	  ALSO, BULB SET SCREWS MISSING AND GOUND WIRE TO BULB LOOSE AT ATTACHMENT SCREW.  AIRCRAFT IS IN TRACK AND BALANCE, BUT	 AIR FRAME STILL HAS HIGH LEVEL OF 4 IAW VIBRATION.  (EA13200406110)			1	G	7	2 	3U	3	T	 	H7EU    	E2NE
2004100400093	20041004	00093	CE  	2004	10	4	2004FA0000749    	1	20040728	G	8120		DUCT            			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520C    	17040	SO  					TURBOCHARGER	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	1002V					U20602387	501091			SCAT 16 NOSE FROM AIRBOX TO TURBOCHARGER AIR INLET, WIRE INSIDE SCAT 16 NOSE WAS 1 INCH FROM TURBOCHARGER COMPRESSOR WHE	EL.  WIRE MUST BE SECURED TO OUTSIDE OF AIR DUCTS WITH OEM CLAMPS.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004100400092	20041004	00092	CE  	2004	10	4	2004FA0000750    	1	20040803	G	1430		BOLT            			BEECH 	36    	A36TC       	1151603	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT WING	INCORRECT       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	444FC					EA257				AFT UPPER LT WING ATTACH BOLT FOUND INSTALLED AND PRESUMABLY TORQUED WITHOUT CHAMFERED WASHER UNDER HEAD.  DAMAGE TO BAT	HTUB FITTING UNKNOWN AT THIS TIME.					1	L	7	1 	3O	3	O	 	3A15    	E8CE
2004100100113	20041001	00113	CE  	2004	10	1	2004FA0000751    	1	20040803	G	5610	0413419200	WINDSHIELD      			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					COCKPIT	DEPARTED        	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	23	4760X					15064810				SECTION OF WINDSHIELD DEPARTED AIRCRAFT IN FLIGHT.  WINDSHIELD HAD BEEN REPAIRED 7/15/00 IAW AC43.131B CHAPTER 3 SECTION	 4, BUT NO REINFORCEMENT WAS EVIDENT ON PART REMAINING IN AIRCRAFT.  HOW WINDSHIELD INSTALLED.  THIS COULD HAVE BEEN PRE	VENTED IF NEW WINDSHIELD WAS INSTALLED IAW AC 43.13 .				1	H	7	1 	3O	3	O	 	3A19    	E252
2004100100117	20041001	00117	CE  	2004	10	1	2004FA0000752    	1	20040903	G	7120	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  	LYC   	O360  	O360A1D     	41514	EA  					ENGINE MOUNT	CRACKED         	D			J7BR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	7487M	3951 				55787	L665436			THE FUSELAGE UPPER ENGINE MOUNT BRACKETS WERE DISCOVERED TO BE CRACKED AT MOUNTING HOLES.  PN 0513132-11 FOR UPPER LT AN	D UPPER RT.  NEW REPLACEMENT PARTS WERE NOTED TO BE SLIGHTLY THICKER AND MADE FROM SAME MATERIAL.  SUGGEST ENGINE MOUNT 	REMOVAL FOR INSPECTION PERIODICALLY.				1	H	7	1 	3O	3	O	NT	3A17    	E286
2004100100118	20041001	00118	SO  	2004	10	1	2004FA0000753    	2	20040723	G	7414	10357487242	VIBRATOR        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	MAGNETO	BURNED          	C				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	11	88CS	4704 				TC723	CS9152146	EB1190557		JUST AFTER DEPARTURE A BURNING ODOR WAS NOTICED FROM THE FRONT OF THE AIRCRAFT.  A STANDARD FLIGHT PATTERN BACK TO RUNWA	Y WAS EXPEDITED.  LATER FINDING THE IGN VIBRATOR HAD STARTED A FIRE IN THE FRONT PILOTS LOWER FIREWALL PANEL.  A GEAR UP	 LANDING BECAME THE RESULT OF THE ELECTRICAL BURN UP.  THE FINAL PART OF THE FLIGHT WAS CONDUCTED AS AN EMERGENCY. (WP11	200403343)			1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P25EA
2004100100121	20041001	00121	NM  	2004	10	1	2004FA0000754    	1	20040806	G	7160		DOOR            			PROPJT	200   	200D        	0140312	NM  	CONT  	O520  	IO520*      	17032	SO  					ALTERNATE AIR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	49J					352				PILOT COMPLAINED OF STUCK THROTTLE ON GROUND.  FOUND ALTERNATE AIR DOOR BROKEN OFF AND WEDGED IN THROTTLE BODY.  HINGE A	PPEARED TO HAVE WORN COMPLETELY THROUGH.					1	L	7	1 	3O	3	O	 	3A18    	E5CE
2004100100122	20041001	00122	SO  	2004	10	1	2004FA0000755    	1	20040809	G	7120		MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										ENGINE	BROKEN          	D			VKPS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	53395					4496076				ENGINE MOUNT TUBE BROKEN BELOW TOP RT ISOLATOR.  DISCOVERED DURING 100 HR INSPECTION.  (WP07200420174)						1	L	7	2 	3O			 	A19S0
2004100100123	20041001	00123	SO  	2004	10	1	2004FA0000756    	2	20040719	G	8520		GEAR            			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  					CAMSHAFT	FAILED          	D				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	01	7714A					32611	474576K			THIS ENGINE HAD A COMPLETE FAILURE IN FLIGHT, PILOT WAS ABLE TO GLIDE TO AIRPORT.  INITIAL INSPECTION FOUND DAMAGE TO CR	ANKSHAFT AND CAMSHAFT DRIVE GEARS INSIDE ACCESSORY GEARBOX.  INSPECTION WAS NOT COMPLETE TO FIND OUT WHY THIS HAPPENED, 	DUE TO THE TIME AND AGE OF ENGINE.  DECISION MADE TO JUST REPLACE ENGINE.  LAST OVERHAULED APRIL 1968.  (WO M8766)				1	H	7	1 	3O	3	O	NC	5A6     	E273
2004111000072	20041110	00072	EU  	2004	11	10	2004FA0000757    	1	20040818	G	2910	95G50	PRESSURE SWITCH 			AMD   	FALC90	FALCON900B  	2730171	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 2 HYD SYSTEM	LEAKING         	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			EA	03	25MB	2773 				163				APPROX 5-10 MINUTES AFTER TAKEOFF, PILOTS NOTED NR 2 HYDRAULIC SYSTEM LOSING FLUID.  SYSTEM CONTINUED TO LOSE FLUID SO N	R 2 ENGINE WAS SHUT DOWN AND AIRCRAFT LANDED.  MAINTENANCE FOUND NR 2 HYDRAULIC SYSTEM PRESSURE SWITCH LEAKING.  INSTALL	ED NEW PRESSURE SWITCH CLEANED AIRCRAFT AFT COMPARTMENT AND TESTED SYSTEM FOR OPERATION AND LEAKS.  AIRCRAFT RETURNED TO	 SERVICE. NEW SWITCH WAS A LATER GENERATION SWITCH (PN 906229).			2	L	7	3 	4F	4	F	RT	        	E6WE
2004100100065	20041001	00065	CE  	2004	10	1	2004FA0000758    	1	20040827	G	5540	07126167	BULKHEAD        			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470*       	17026	SO  					RT RUDDER STOP	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	9078G	4095 				18260618				BULKHEAD FOUND CRACKED DURING ANNUAL INSPECTION AT RT RUDDER STOP BOLT.  THIS BULKHEAD REQUIRES 1000 HR INSPECTIONS IAW 	AD72-07-09, WHICH WAS NOT DUE AT THIS TIME.  SUSPECT WIND DAMAGE FROM REPEATEDLY STRIKING STOP.  (SO05200410568)					1	H	7	1 	3O	3	O	NT	3A13    	E273
2004100100070	20041001	00070	SW  	2004	10	1	2004FA0000759    	1	20040820	G	2820	18586	LINE            			AIRPTS	A     	A9B         	0144206	SW  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	1A200	1A200*      	GL  	FUEL SYSTEM	LEAKING         	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	07	7798V	4340 				1551	L763148	103239		IT APPEARS THAT THE FUEL LINE WAS LEAKING FUEL AT THE ATTACH POINT OF THE STEEL BRAIDED LINE TO THE FITTING.  THE FUEL L	INE IS ATTACHED AT THE FIRE WALL AND GOES TO THE INLET SIDE OF THE ENGINE DRIVEN FUEL PUMP.  (CE07200416055)					1	L	7	1 	3O	3	O	 	A758    	1E4	5	N	P874
2004100100056	20041001	00056	EA  	2004	10	1	2004FA0000760    	2	20040811	G	8530	7580213	CYLINDER HEAD   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	B			MW2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	96507	1163 				17276082	L1437139A			CYLINDER CRACKED FROM LOWER SPARK PLUG HOLE AROUND OUTSIDE OF EX SEAT TO TOP SPARK PLUG HOLE.  JUST LIKE ALL THE OTHER O	NES.					1	H	7	1 	3O	3	O	NT	3A12    	E274
2004100100057	20041001	00057	EA  	2004	10	1	2004FA0000761    	2	20040811	G	8530		STUD            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					NR2 CYLINDER	FAILED          	B			MW2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4509X		1000 			28R7635067	L705051A			NR 2 CYLINDER STUD, 8 O CLOCK POSITION, FAILED.						1	L	7	1 	3O	3	O	 	2A13    	1E10
2004100100053	20041001	00053	EA  	2004	10	1	2004FA0000762    	2	20040922	G	8530	LW13870	CYLINDER        			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540B1A5   	41532	EA  					NR 1 POSITION	SEIZED          	B			G6NR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	6154X					500B98324	RL976248			NR CYLINDER ON LT ENGINE SEPARATED BETWEEN CYLINDER BASE AND FIRST SET OF STEEL COOLING FINS.  THE CONNECTING ROD WAS TO	RN FROM THE CRANKSHAFT.  THE SEPARATION ALLOWED THE CYLINDER TO MIGRATE OUTWARD ABOUT 2 INCHES.  THE FUEL INJECTION LINE	 WAS TORN OFF AT FUEL INJECTOR.  BOTH PUSH ROD TUBES FELL OUT AND INTAKE TUBE WAS PULLED OUT.  PROBABLE CAUSE IS CYLINDE	R AND PISTON SEIZED TOGETHER.			1	H	7	2 	3O	3	O	 	6A1     	1E4
2004100100068	20041001	00068	EA  	2004	10	1	2004FA0000763    	2	20040811	G	8530		STUD            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 3 CYLINDER	FAILED          	B			MW2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4228T		500  			327240046	L472948			NR 3 CYLINDER DECK STUDS FAILED AND CYLINDER DEPARTED ENGINE.						1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004100100108	20041001	00108	NE  	2004	10	1	2004FA0000764    	2	20040702	G	8540		BUSHING         			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340*      	52016	NE  					ENGINE	OBSTRUCTED      	G			MWRG	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	17	915X					434	4210213			ENGINE LOST POWER ON TAKE-OFF.  PILOT LANDED IN BOG AND FLIPPED OVER.  PRELIMINARY INSPECTION SHOWED DAMAGE TO INDUCTION	 IMPELLER.  TEARDOWN REVEALED IMPELLER SHAFT SUPPORTED BY TWO BRONZE BUSHINGS WHICH ARE LUBRICATED BY AN .1250 INCH HOLE	 ON BOTH BUSHINGS AND BY A .0625 INCH HOLE ON BOTH BUSHINGS AND BY A .0625 INCH HOLE ON ONE BUSHING.  THE .0625 INCH HOL	E WAS BLOCKED, UNABLE TO DETERMINE IF BLOCKAGE WAS CAUSE OR CONSEQUENCE OF THE FAILURE, ATTRIBUTED TO LACK OF LUBRICATIO	N.		1	Q	7	1 	3R	3	R	 	1A16    	5E2
2004100100034	20041001	00034	SO  	2004	10	1	2004FA0000765    	1	20040802	G	5102	F9B15	VALVE           			BALWKS	FIREFY	FIREFLY9    	1050124	SO  										BALLOON	DESTROYED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	2189K					F9B2004				DURING FLIGHT, 3 OF 4 VALVE WINDOWS FAILED BY SEPARATING AT SEAMS.  UPON SEPARATION, REMAINING WINDOW MATERIAL MELTED AW	AY, THUS CREATING 3 LARGE HOLES IN THE TOP OF THE BALLOON, WHICH RAISED INTERNAL TEMP, AND CAUS HIGH (EXTREME) FUEL CONS	UMPTION AND RENDERED THE AIRCRAFT UNCONTROLABLE AND UNAIRWORTHY.  ALL ABOVE WITHIN 42 MINUTES OF FLIGHT.				1	B	0	0 	  			 	A14SO
2004100100127	20041001	00127	SO  	2004	10	1	2004FA0000766    	1	20040808	G	5102	F8B15	VALVE           			BALWKS	FIREFY	FIREFLY8B15 	1050111	SO  										VALVE WINDOWS	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05					B820243	F8B2024				NOTICED DURING PREFLIGHT INSPECTION 2 OF 4 VALVE WINDOWS SHOWED CRACKING ON EDGES AND CRACKS.  TRANSVERSE PASSED SEAMS I	NTO FLIGHT LOAD AREA.  FLIGHT ABORTED.					1	B	0	0 	  			 	A14SO
2004100400072	20041004	00072	SO  	2004	10	4	2004FA0000767    	1	20040625	G	2741	67201104	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STAB TRIM	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	5903V	5340 				287790511				TRIM CABLE BROKEN (STABILIZER TRIM). FRAYED AND BROKEN AT 2ND PULLEY FROM FRONT.  (CLOSER INSPECTION UNDER BAGGAGE AREA)	.					1	L	7	1 	3O			 	2A13
2004100400064	20041004	00064	SO  	2004	10	4	2004FA0000768    	2	20040723	G	7413	10357487242	VIBRATOR        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					LT CTR FIREWALL	BURNED          	D				A				UNSCHED LANDING         				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		NR	NOT REPORTED   	1			WP	11	88CS	4704 				TC723				PILOT DEPARTED ON MAINT TEST FLIGHT ON CROSS WIND.  PILOT NOTICED BURNING ODOR AS PILOT TURNED BASE LEG TO LAND ON DEPAR	TURE RUNWAY, AC HAS SMOKE IN COCKPIT.  AC WAS LANDED GEAR UP.  AFTER AREA OF PILOT SIDE RUDDER PEDALS WAS NOTICED AND PU	T OUT.  ON FURTHER INVESTIGATION IT WAS FOUND THAT  IGNITION VIBRATOR (10-357487-242) HAD SHORTED OUT AND CAUSED FIRE TH	AT BURNED BEHIND INSTRUMENT PANEL.  BEEN DETERMINED FROM AC SRM THAT SN TC1 THRU TC1028 HAVE NO CIRCUIT PROTECTION IN IG	NITION CIRCUIT.  IGNITION VIBRATOR HAS 28V ON IT AT ACC TIMES AND SWITCH PROVIDES GROUND TO COMPLETE CIRCUIT.  ANY MALFU	NCTION OF SWITCH OR SHORT IN WIRING WOULD CAUSE POINTS TO CLOSE AND IGNITION VIBRATOR TO BE ENGAGED. (WP11200403343)	1	L	7	2 	3O	3	O	RT	3A16    	3E1
2004100100038	20041001	00038	EA  	2004	10	1	2004FA0000769    	2	20040727	G	7314	200F5003	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	05	350PC	10   				318152006				INSTALLED AN O/H ENGINE ONTO THE RT POSITION.  UPON PERFORMING AN OIL FILTER CHECK THE VERY NEXT DAY, AFTER AIRCAFT RUNS	 ON 7/27/04.  FOUND THAT THE ENGINE DRIVEN FUEL PUMP HAD BLUE STAINS AROUND BODY HOUSING AND ALSO NOTICED FUEL LEAKING F	ROM DRAIN END OF THE DRIVE SECTION OF THIS FUEL PUMP.  (SO05200410029)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004100100039	20041001	00039	CE  	2004	10	1	2004FA0000770    	1	20040603	G	7160		PLATE           			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ALT AIR DOOR	SEPARATED       	B			NF2R	O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			GL	03	732WP					21061835	512178	776652		ENGINE ALTERNATE AIR DOOR IS HELD CLOSED WITH A MAGNETIC LATCH ORIGINAL PN 1250938-8.  THE MAGNETIC LATCH HAS 2 STEEL SM	ALL PLATES BONDED TO THE MAGNET THAT MAKE CONTACT WITH THE ALTERNATE AIR DOOR.  ONE STEEL PLATE CAME DEBONDED FROM AGE V	IBRATION.  PLATE WAS INJESTED INTO THE TURBOCHARGER.  THE TURBO WAS DESTROYED IN SECONDS CAUSING TOTAL BOOST LOSS AND A 	RETURN LANDING.  THE METAL FROM THE TURBO WAS PASSED THRU THE INDUCTION SYSTEM AND OIL SYSTEM CAUSING MAJOR DAMAGE.  HAV	E FOUND 2 ADDITIONAL AC WITH THE LATCH ALMOST READY TO FAIL.  MFG HAS NEW IMPROVED LATCH THAT WILL NOT ALLOW ANY PARTS T	O FALL INTO THE INDUCTION.	1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL
2004100100126	20041001	00126	EA  	2004	10	1	2004FA0000771    	2	20040716	G	8530	AEL65102ST041	CYLINDER HEAD   			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	05	19674	820  				17260657	L3253127A	VJ44025		STUDENT AND INSTRUCTOR WERE FLYING, HEARD LOUD BANG.  AC SHUTTERED, OIL PRESSURE STABLE, RPM DROPPED TO BOTTOM OF GREEN 	ARC, OIL PRESSURE STARTED DROPPING ON A PRECAUTIONARY APPROACH.  NORMAL LANDING, SHUT ENGINE DOWN AT SOUTH BAY AVIATION.	  UPON INSP OF ENG IT WAS DETERMINED.  NR3 CYLINDER HEAD SEPARATED FROM CYLINDER.  REPLACED NR 3 CYLINDER ASSY.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004100100124	20041001	00124	SO  	2004	10	1	2004FA0000772    	1	20040714	G	8011	MZ6222	STARTER         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	BURNED          	D			GM8T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1594X	270  				32R7680004	L2313648A			STARTER WAS INSTALLED BY FACTORY DURING ENGINE OVERHAUL.  STARTER HAS STEADILY WEAKENED SINCE INSTALLATION OF THE ENGINE	 ON THE AIRCRAFT.  OPENED STARTER AND FOUND BRUSHES AND COMMUTATOR SEVERELY BURNED.  IT IS THE SUBMITTERS OPINION THAT T	HIS PERMANENT MAGNET STARTER IS UNDER DESIGNED TO TURN AN ENGINE WITH 12 VOLTS.				1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004100100125	20041001	00125	SW  	2004	10	1	2004FA0000773    	1	20040627	G	2820		LINE            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					FUEL SYSTEM	CHAFED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	11	86727					65674				IN COMPLIANCE WITH MFG SL NR 419.  FOUND FUEL LINE CHAFED OVER .5000 WAY THROUGH TUBE WALL.  CAUSED BY FLAP ACTUATOR.  C	HAFE WAS NOT VISIBLE.  FOUND BY FEELING.  RECOMMEND MFG RUN LINE STRAIGHT THROUGH FUSELAGE WALL THEN ROUTE AFT.  ALSO RE	COMMEND MAKING INTO AN AD.				1	H	7	1 	3O	3	O	NC	A759    	E274
2004100100114	20041001	00114	SO  	2004	10	1	2004FA0000774    	2	20040629	G	7261	640756	HOUSING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					SCAVANGE PUMP	BROKEN          	B			R2JR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	21	2190K	400  				347970096				DURING SEARCH FOR OIL LEAK ONTO ALTERNATOR FOUND.  OIL SCAVENGE PUMP HOUSING HAD BROKEN MOUNT LUG.  REPLACED WITH NEW PA	RT.  CAUSE OF FAILURE BELIEVED TO BE WEAK CONSTRUCTION.  AIRCRAFT FREON COMPRESSOR MOUNTS HERE.  AIRCRAFT HAS HAD DYNAMI	C PROP BALANCES.  SECOND FAILURE THIS ENGINE WITHIN 400 HOURS.  EXTRA WEIGHT OF FREON COMPRESSOR COULD BE FACTOR.  THE R	T ENGINE WITHOUT COMPRESSOR HAD NO FAILURES YET.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2004100400081	20041004	00081	EA  	2004	10	4	2004FA0000775    	2	20040714	G	8520	IO540	CRANKCASE       			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	8374T		800  			328106058	11379248A			CRANK IN CRANKCASE JUST BELOW CYLINDER NR 3 BETWEEN THE BOTTOM CYLINDER HOLD DOWN STUDS AND ROCKER DRAIN NIPPLES.  CRACK	 IS APPROX 2.5 INCHES LONG.  (AL03200418212)					1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004100100062	20041001	00062	SO  	2004	10	1	2004FA0000776    	2	20040713	G	7414	M3050	IMPULSE COUPLING			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					LT MAGNETO	BROKEN          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5599P	1383 	153  			CE1344	825882R			PILOT REPORTED EXCESSIVE DROP ON LT MAGNETO ON ENGINE RUN UP.  ON FURTHER INVESTIGATION THE MECHANIC FOUND THE IMPULSE C	OUPLING SPRING BROKEN.  PROBABLE CAUSE AT THIS TIME IN UNKNOWN, AND THERE IS NO RECOMMENDATIONS AT THIS TIME EITHER.					1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004100100110	20041001	00110	EA  	2004	10	1	2004FA0000777    	2	20040914	G	8530	LW19001	VALVE           			CESSNA	150   	150K        	2071822	CE  	LYC   	O320  	O320E2D     	41508	EA  					CYLINDER HEAD	STUCK           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	6103G					15071603	L4889027A			POWER LOSS ON TAKE OFF.  UPON  INSPECTION, FOUND PUSHROD TUBE BENT.  INDICATES STUCK VALVE.  DEVELOPMENT NEEDED TO AVOID	 EXHAUST AND/OR INTAKE VALVES FROM STICKING.  (WP07200421112)					1	H	7	1 	3O	3	O	 	3A19    	E274
2004100400066	20041004	00066	EA  	2004	10	4	2004FA0000778    	2	20040923	G	7322		FLOAT           	PREAIR      		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					CARBURATOR	LEAKING         	C				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			SW	99										ENGINE STARTED FALTERING DURING POWER REDUCTION FOR DESCENT.  ENGINE RAN FINE AT CRUISE POWER.  UPON INSPECTION OF CARB,	 ONE OF THE PLASTIC FLOAT CELLS IS FULL OF FUEL.  CARB LESS THAN 100 HOURS OUT OF OVERHAUL.					1	L	7	1 	3O	3	O	 	2A13    	E274
2004100400067	20041004	00067	EA  	2004	10	4	2004FA0000779    	2	20040923	G	7322		FLOAT           	PREAIR      		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					CARBURATOR	LEAKING         	C				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			SW	99										ENGINE STARTED FALTERING DURING POWER REDUCTION FOR DESCENT.  ENGINE RAN FINE AT CRUISE POWER.  UPON INSPECTION OF CARB,	 ONE OF THE PLASTIC FLOAT CELLS IS FULL OF FUEL.  CARB LESS THAN 100 HOURS OUT OF OVERHAUL.					1	L	7	1 	3O	3	O	 	2A13    	E274
2004100400082	20041004	00082	EA  	2004	10	4	2004FA0000780    	2	20040923	G	7322	MA4SPA	CARBURETOR      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	56098					287325571				OVERHAULED ENGINE INSTALLED ON AIRFRAME APPROXMIATELY 75 HRS AND 4 MONTHS AGO,CARBURETOR SET AND ADJUSTED TO SPECS AT IN	STALLATION.  ENGINE BECAME ERRATIC AND NEAR STALL OUT CONDITION WITHIN THE LAST 1 HOURS.  ATTEMPTED TO ADJUST RICH/LEAN 	SETTING AND IDLE.  ENGINE WOULD NOT RESPOND AS NORMAL.  REMOVED CARB, DISASSEMBLED, INSPECTED.  ONE HALF OF FLOAT NEARLY	 FULL OF AV 100LL FUEL, SLIGHT SPLIT NOTED AT FLOAT BOND JOINT.  FLOAT IS MADE FROM A PLASTIC MATERIAL, CARB SENT FOR RE	PAIRS.		1	L	7	1 	3O	3	O	 	2A13    	E274
2004100400102	20041004	00102	CE  	2004	10	4	2004FA0000781    	1	20040923	G	3000	33CB15	CIRCUIT BREAKER 			RAYTHN	390   	390         	7150030	CE  										WING ICE LIGHT	WRONG PART      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	567T	464  				RB37				REPORTED THAT THE WING ICE LIGHT C/B SWITCH TRIPS AFTER BEING IN (ON) POSITION FOR 3-4 MINUTES. TROUBLESHOOTING REVEALED	 THAT A 3 AMP C/B HAD BEEN INSTALLED IN A 7 AMP CIRCUIT AT POSITION 33CB15. INSPECTING THE OTHER C/B SWITCHES REVEALED T	HAT POSITION 33CB6, 33CB11 AND 33CB32 WERE ALL WRONG AMPERAGE C/B. THE C/B WERE REMOVED AND REPLACED IN THEIR CORRECT RE	SPECTIVE CIRCUITS AND THE SYSTEMS OPERATIONAL CHECKED. RESEARCH OF RECORDS REVEALED NO WORK HAD BEEN ACCOMPLISHED ON THE	 AFFECTED CIRCUITS AT ANY TIME SINCE THE AIRCRAFT WAS NEW. LEADING TO THE CONCLUSION THAT THE C/B WERE INCORRECTLY INSTA	LLED DURING PRODUCTION. MFG TECHNICAL SUPPORT WAS NOTIFIED AND IS CONDUCTING AND INVESTIGATION AT THIS TIME.	1	7		2 	3F			RT	A00010WI
2004102700102	20041027	00102	SO  	2004	10	27	2004FA0000782    	1	20040923	G	2810	C1560030101	CAP             	CESSNA      		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL TANK	CLOGGED         	B				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	17	8214Y					288090362	L2561736A	F766A2		PILOT EXPERIENCED FUEL INTERRUPTION TO ENGINE WHILE ENROUTE. SWITCHED FUEL TANKS AND ENGINE QUIT. MADE EMERGENCY LANDING	.  REMOVED AC FROM FIELD TO LOCAL AIRPORT (N75). DRAINED ALL FUEL FROM WING TANKS. FOUND WHILE DRAINING FUEL WITH FUEL C	APS ON THAT DRAINING FUEL WAS SLOW. REMOVING FUEL CAP QUICKENED FLOW RATE AT FUEL DRAIN.  AFTER CLOSE INSP FOUND VENT HO	LES CLOGGED WITH MUD.   FOUND THE VENT TUBE IN LT WING WAS RESTRICTED. BLOWING NITROGEN THROUGH TUBE FREED UP BLOCKAGE. 	FRESH FUEL WAS INSTALLED IN EACH TANK AND FUEL CAPS WERE REPLACED WITH NEW UNITS. A LENGTHY RUNUP WAS PERFORMED WITH NO 	DEFECTS NOTED.  AFTER ARRIVING, OWNER REQUEST WE REPLACE THE FUEL SELECTOR AS A PRECAUTIONARY MEASURE	1	L	7	1 	3O	3	O	 	2A13    	E286	5	C	P920
2004102700103	20041027	00103	CE  	2004	10	27	2004FA0000783    	1	20040923	G	2810	C1560030101	CAP             	CESSNA      		CESSNA	172   	172         	2072402	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL TANK	CLOGGED         	B				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	17	8214Y					17248714	L2561736A	F766A2		PILOT EXPERIENCED FUEL INTERRUPTION TO ENGINE WHILE ENROUTE. SWITCHED FUEL TANKS AND ENGINE QUIT.  MADE EMERGENCY LANDIN	G. NO INJURIES OR DAMAGE TO AIRCRAFT. REMOVED AC FROM FIELD TO LOCAL AIRPORT (N75). DRAINED ALL FUEL FROM WING TANKS. FO	UND WHILE DRAINING FUEL WITH FUEL CAPS ON THAT DRAINING FUEL WAS SLOW. REMOVING FUEL CAP QUICKENED FLOW RATE AT FUEL DRA	IN.  AFTER CLOSE INSP FOUND VENT HOLES CLOGGED WITH MUD.  FOUND VENT TUBE IN LT WING WAS RESTRICTED. BLOWING NITROGEN TH	ROUGH TUBE FREED UP BLOCKAGE. FRESH FUEL WAS INSTALLED IN EACH TANK AND FUEL CAPS WERE REPLACED WITH NEW UNITS. A  FLIGH	T WAS MADE WITHOUT INCIDENT. AFTER ARRIVING, THE OWNER REQUEST WE REPLACE THE FUEL SELECTOR AS A PRECAUTIONARY MEASURE.	1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P920
2004101500089	20041015	00089	NE  	2004	10	15	2004FA0000784    	2	20040515	G	8520	270458	CRANKSHAFT      			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	ENGIEN	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8561S					3010145	CP513333			AC WAS ON FERRY FLIGHT, PILOT REPORTED GETTING OIL ON WINDSHIELD.  OIL BEGAN TO GET WORSE; REDUCED POWER, AC STARTED VIB	RATING SEVERELY.  POWER WAS REDUCED FURTHER AND VIBRATION ALSO REDUCED.  PILOT LANDED AC IN UNPLANTED FIELD.  AC SKIPPED	 OVER TERRACE AS SLOWED TO STOP.  TAIL CAME UP AND AC WENT OVER ON NOSE.  PROP STRUCK GROUND AND SEPARATED FROM ENGINE. 	CRANKSHAFT HAD BROKEN  IN PROP THRUST BEARING AREA.  EXAM OF CRANKSHAFT SHOWS FATIGUE CRACKING.  BLADES DAMAGED APPROX 2	5 INCHES FROM TIPS.  PROP WAS INSTALLED AFTER BEING O/H.  ENGINE RUN AND GROUND CHECKS COMPLETED.  PROP WAS IN SERVICE .	5 HOUR BEFORE FAILURE OF CRANKSHAFT. (CE07200414081)	1	L	7	1 	3R	3	R	 	A9SW    	5E2	5	C	P257
2004101800127	20041018	00127	CE  	2004	10	18	2004FA0000785    	1	20040827	G	6120	C299506B0104	PCU             			CESSNA	172   	R172K       	2072431	CE  	CONT  	IO360 	IO360*      	17025	CE  					PROPELLER	FROZEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	218H	1    				R1722840				NEW PROP CONTROL INSTALLED IAW SRM, CONTROL OPERATED FINE, AIRCRAFT WAS FLOWN ONCE AFTER COOL DOWN.  PROP CONTROL WAS FR	OZEN, WAS ABLE TO BREAK FREE, INSTALLATION AND RIGGING CHECKED, PROP GOVERNOR CHECKED, AIRCRAFT FLOWN AGAIN, PROP CONTRO	L FROZEN AGAIN AFTER COOL DOWN, WAS ABLE TO BREAK  CONTROL FREE, INSTALLED SECOND NEW CONTROL FROM MFG, THE SAME ABOVE O	CCURRED WITH THE SECOND NEW CONTROL.  CONTROL SENT TO MFG FOR INSPECTION, CUSTOM CONTROL WAS PURCHASED, FIELD APPROVAL I	N PROGRESS.		1	H	7	1 	3O	3	O	 	3A17    	E1CE
2004101800182	20041018	00182	EA  	2004	10	18	2004FA0000786    	2	20040816	G	7414	10382971	BEARING         	BENDIX      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	OVERHEATED      	D			S43S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	2246E		382  		GO1AA069	17271203	L647276T			DURING FLIGHT, ENGINE BEGAN TO LOOSE POWER, AND AIRCRAFT EXPERIENCED AN OFF-FIELD LANDING.  UPON INVESTIGATION INTO THE 	FAULT, IT WAS DISCOVERED THAT THE MAGNETO BREAKER POINTS WERE NOT OPENING.  DISASSEMBLY OF THE MAGNETO REVEALED THAT BEA	RING PN 1038297 INSTALLED IN BENDIX MAGNETO PN 10-682555-14, HAD OVERHEATED DUE TO APPARENT INSUFFICENT LUBRICATION CAUS	ING RAPID WEAR OF THE BREAKER POINTS CAM FOLLOWERS. (CE03200402198)			1	H	7	1 	3O	3	O	NT	3A12    	E274
2004101800181	20041018	00181	SO  	2004	10	18	2004FA0000787    	2	20040812	G	8520	648014	VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					CYLINDER HEAD	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5823J					18263557				ON DOING A COMPRESSION CHECK, 3 OUT OF 6 CYLINDERS HAD VALVES LEAKING.  WHEN REMOVED FOR REPAIR, DISCOVERED GUIDES WORN 	BEYOND MAX SERVICE LIMIT.  (NM09200412745)					1	H	7	1 	3O	3	O	NT	TA13    	E273
2004101800103	20041018	00103	SO  	2004	10	18	2004FA0000788    	1	20040501	G	5102		PULLEY          			BALWKS	FIREFY	FIREFLY11   	1050125	SO  										ENVELOPE	STICKING        	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	70535					F11005				DEFLATION CWE PULLEY CATCHES ON ENVELOPE THROAT WEBBING AND NOMEX SKIRT CAUSING DEFLATION PANEL TO REMAIN OVEN DURING DE	SCENTS AND CAUSES DIFFICULTY RETURNING TO LEVEL FLIGHT WHEN HEATING ENVELOPE.  THE PULLEY EVENTUALLY FREES ITSELF WHEN E	NOUGH HEAT IS APPLIED AND MORE TENTION IS ADDED TO THE LINE.  THE PULLEY RELEASES WITH A SNAP WHICH ALSO JOLTS THE AIRCR	AFT AND PASSENGERS.			1	B	0	0 	  			 	A14SO
2004101800184	20041018	00184	EA  	2004	10	18	2004FA0000789    	2	20040428	G	7314	62D22569	PUMP            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					FUEL SYSTEM	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	54MV	3    				277654043	RL1057961A			FUEL LEAKING INTO MANIFOLD REFERENCE LINE.  PILOT EXPERIENCED INFLIGHT ROUGH ENGINE WHEN AUXILIARY FUEL PUMP WAS TURNED 	ON.  FUEL CONTINUED TO RUN ONTO THE GROUND AFTER ENGINE SHUTDOWN.					1	L	7	2 	3O	3	O	 	1A10    	E14EA
2004101800192	20041018	00192	EA  	2004	10	18	2004FA0000790    	2	20040428	G	7314	RG17980JM	PUMP            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	54MV	20   				277654043	RL723861A			FUEL LEAKING INTO MANIFOLD REFERENCE LINE.  PILOT EXPERIENCED INFLIGHT ROUGH ENGINE WHEN AUXILIARY FUEL PUMP TURNED ON. 	 FUEL CONTINUED TO RUN ON GROUND AFTER ENGINE SHUTDOWN.  PROBABLE CAUSE: MFG DEFECT: LEAKING DIAPHRAGM.					1	L	7	2 	3O	3	O	 	1A10    	E14EA
2004101500093	20041015	00093	CE  	2004	10	15	2004FA0000791    	1	20041001	G	5522	96610006617	SKIN            	BEECH       		BEECH 	58    	58          	1152740	CE  										ELEVATOR	CRACKED         	B			U5LR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15										ELEVATOR SKIN CRACKED WHERE CENTER RIB AND TRIM TAB HINGE BRACKET INTERSECT.  THESE SKINS ARE MADE FROM MAGNESIUM AND AR	E PRONE TO CRACKING IN THIS AREA. THIS REPAIR STATION HAS REPLACED NUMEROUS SKINS DUE TO THIS DEFECT.					1	L	7	2 	3O			 	3A16
2004101800046	20041018	00046	NM  	2004	10	18	2004FA0000792    	1	20040930	G	2497		WIRE            			LANCAR	LC42  	LC42550FG   	5150002	NM  	CONT  	O550  	IO550*      	 	SO  					ALTERNATOR	BROKEN          	B				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	05	65035	136  			E022966	42052				PILOT REPORTED LT ALTERNATOR INOPERATIVE.  FOUND TERMINAL FOR B+ WIRE BROKEN OFF, WHICH RESULTED IN INTERMITTENT CONTACT	 CAUSING SEVERE ELECTRICAL ARCING BETWEEN ALTERNATOR AND WIRE TERMINAL END.					1	L	7	1 	3O	3	O	RT	A00003SE	E3SO
2004101800120	20041018	00120	NM  	2004	10	18	2004FA0000793    	1	20041006	G	3220		STRUT           			LANCAR	LC42  	LC42550FG   	5150002	NM  	CONT  	O520  	IO520*      	17032	SO  					NLG	LOOSE           	B				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SO	05	244SC	100  				42047				DURING INSPECTION FOUND THE TWO BOLTS/NUTS THAT ATTACH NOSE STRUT TO THE ENGINE MOUNT VERY LOOSE.  NOSE STRUT WOBBLES WI	TH AIRCRAFT ON JACKS.  FOUND SIMILAR SITUATION ON TWO OTHER AIRCRAFT WITH LESS THAN 100 HOURS SINCE NEW.					1	L	7	1 	3O	3	O	RT	A00003SE	E5CE
2004101800039	20041018	00039		2004	10	18	2004FA0000794    	4	20041008	G	3422	ST3400	INDICATOR       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					TAWS/RMI	MALFUNCTIONED   	B			FE6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	2328E					BB1608				THE TAWS/RMI SHOWS SIGNIFICANT BEARING ERRORS ON HEADINGS GREATER THAN 350 DEGREES OR LESS THAN 0 DEGREES.  THIS PROBLEM	 WAS DISCOVERED IN FLIGHT AND VALIDATED THROUGH GROUND TESTING OF NUMEROUS UNITS.  PROBABLE CAUSE OF MALFUNCTION IS SOFT	WARE.  THE ST3400 TAWS/RMI IS NOT RECOMMENDED FOR NAVIGATION AT THIS TIME.				1	L	7	2 	4T	3	T	 	A24CE   	E2NE
2004102700080	20041027	00080	CE  	2004	10	27	2004FA0000796    	1	20040815	G	1430		BOLT            			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6*        	52043	EA  					WING	LOOSE           	G				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	07	148Z					LJ472				INSPECTION AFTER TURBULENT AIR, DISCOVERED BOTH UPPER FWD WING BOLTS AND NUTS WERE ONLY INSTALLED HAND TIGHT.  REVEALED 	THAT WING BOLT INSP HAD BEEN COMPLETED 116.8 HOURS BEFORE.  WING BOLT RETORQUE CHECK HAD BEEN COMPLIED WITH 72.8 HOURS A	FTER THAT.  AIRCRAFT HAS WING STRAP INSTALLED.  THE STC ICA AND SB ONLY MENTIONS PROCEDURES FOR TORQUEING THE LWR FWD BO	LTS.  PROCEDURE FOR TORQUEING REMAINDER BOLTS IS LEFT TO MFG SIRM.  WING BOLT MAINT, SIRM STATES TO CHK TORQUE IAW FIGUR	ES SHOWN.  IT APPEARS THAT REQUIRED TORQUE COULD BE MET, EVEN THOUGH NUTS WERE NOT FULLY ENGAGED, OR CORRECTLY TORQUED T	O BEGIN WITH, DUE TO DOWNWARD PRESSURE EXERTED ON WING.  SIRM STATES (ENSURE WING IS PROPERLY SUPPORTED FOR MAINT).	1	L	7	2 	3T	3	T	 	3A20    	E2NE
2004102000201	20041020	00201	EA  	2004	10	20	2004FA0000797    	2	20040723	G	8520	60009	VALVE           	LYC         		BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					CYLINDER	BROKEN          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	131MC					P392				WITHIN THE LAST 3 TO 3.5 HOURS OF FLIGHT, THE PILOT NOTED THE ENGINES WERE RUNNING ROUGH AND FLEW TO OUR FACILITY FOR DI	SCOVERED THAT THE INTAKE VALVE KEEPER KEYS WERE BROKEN, THE NR 6 CYLINDER HAD A STUCK EXHAUST VALVE.  THE PILOT REPORTED	 HAVE THE NR 6 CYLINDER REPLACED WITH A REMANUFACTURED UNIT AT ANOTHER FACILITY FAIRLY RECENTLY.  ON THE LT ENGINE, THE 	NR 4 INTAKE VALVE STEM WAS DISCOVERED TO BE BROKEN.			1	L	7	2 	3O	3	O	 	A12CE   	E10EA
2004102000198	20041020	00198	SO  	2004	10	20	2004FA0000798    	2	20040901	G	8530		CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	CRACKED         	B			PAIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	23NY					E2359	675303R			PERFORMED ROUTINE ENGINE CYLINDER COMPRESSION CHECKS AS REQUIRED IAW ANNUAL INSPECTION PROCEDURES.  FOUND NR 1 AND 3 CYL	INDERS PASSED COMPRESSION MINIMUMS IAW MFG SPEC, IE: NR1 66/80, NR3 51/80.  DURING COMPRESSION CK, THE TECH OBSERVED AIR	 ESCAPING FROM CYL AT AREA OF FUEL INJECTORS AT EACH CYLINDER.  UPON FURTHER INSP THE TECH VISUALLY FOUND CRACKS BETWEEN	 THE BARREL AND THE HEAD OF THE CYLINDERS BETWEEN TWO COOLING FINS.  COMPRESSION CHECKS FOR ALL OTHER CYLINDERS PASSED A	ND NO EXTERNAL LEAKS NOTED.  RESEARCH BY INSPECTION FOUND THAT THIS ENGINE SN WAS NOT COVERED BY AD, WHICH CONTAINS FAIL	URES VERY SIMILAR TO THIS FAILURE.  AD COVERS SN UP TO 675278, WHICH DOES NOT INCLUDE THIS SN OF 675303.	1	L	7	1 	3O	3	O	 	3A15    	E3SO
2004110300129	20041103	00129	GL  	2004	11	3	2004FA0000799    	1	20040609	G	2810		GASKET          			AIMM  	AMT300	AMT300      	05607RA	GL  	ROTAX 	914   	ROTAX914    	 	EU  					FUEL TANK	DETERIORATED    	B			L1MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	117MQ	365  				300106				FUEL TANK GASKETS MAY NOT BE COMPATABLE WITH AUTO FUEL.  ENGINE IS APPROVED FOR AUTO FUEL.  GASKETS WERE FOUND SEVERELY 	DETERIORATED.  (WP11200403100)					1	K	7	1 	3I	3	O	RT	TG00004A	EXPE3I
2004102000202	20041020	00202	CE  	2004	10	20	2004FA0000800    	1	20040603	G	7160	12509388	LATCH           			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ALT AIR DOOR/BOX	FAILED          	B			NF2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	7568M	22667				21062021				DURING THE ANNUAL INSPECTION, FOUND THE PN 1250938-8, MAGNET LATCH ON THE ALTERNATE AIR DOOR WITH ONE OF ITS STEEL BONDE	D PLATES LOOSE AND READY TO FALL INTO THE TURBO, COULD CAUSE INFLIGHT FAILURE.  INSTALLED THE NEW IMPROVED CATCH PN C100	200.  RECOMMEND MANDITORY REPLACEMENT OF THE OLD TYPE MAGNETIC LATCH IF TT IS ABOVE 1500 HOURS.				1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004101400004	20041014	00004	NM  	2004	10	14	2004FA0000801    	1	20040413	G	6220	900R2101006107	HUB             			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	102  	102  			9000085				DURING ACCOMPLISHMENT OF AD 2002-10-05, MAIN ROTOR UPPER HUB INSP. FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED 	IN SB 900-072.  CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004101400005	20041014	00005	NM  	2004	10	14	2004FA0000802    	1	20041012	G	6230	900D2436530101	DRIVE SHAFT     			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	1478 	300  			9000085				DURING ACCOMPLISHMENT OF A 300 HR INSPECTION FOUND MAIN ROTOR DRIVE SHAFT UPPER DRIVE SPLINES WORN BEYOND MAINTENANCE MA	NUAL LIMITS.  PART TOTAL TIME: 1478.9 HRS. REPLACED DRIVE SHAFT WITH NEW PART.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2004101500078	20041015	00078		2004	10	15	2004FA0000803    	4	20040928	G	6113	TCB35323011	BULKHEAD        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					SPINNER	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	8938C	521  				287625136				UPON ANNUAL INSPECTION, FOUND AFT SPINNER BULKHEAD (PN TCB36323011) TO BE CHAFFING AGAINST PROPELLER BLADES.  ONCE REMOV	ED, IT WAS ALSO EVIDENT THAT CORROSION HAD FORMED ON THE PROPELLER TUB.  ALSO DISCOVERED WAS MATERIAL FROM THE BULKHEAD 	HAD TRANSFERRED TO THE PROPELLER.  INSPECTION OF THE AFT SPINNER BULKHEAD SHOWED THAT THE BULKHEAD HAD BEEN COMPRESSED, 	WHICH HAD REDUCED THE TORQUE ON THE MOUNTING BOLTS. (WP27200407907)			1	L	7	1 	3O	3	O	 	2A13    	E274
2004101400003	20041014	00003		2004	10	14	2004FA0000804    	4	20041013	G	2350	KMA260201	AUDIO PANEL     			CESSNA	172   	172S        	2072439	CE  										COCKPIT	SMOKE           	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	13	106RA	500  				172S8241				THE AUDIO CONTROL PANEL EMITTED SMOKE AND STOPPED OPERATING DURING TAXI PRIOR TO FLIGHT.  AIRCRAFT RETURNED TO BASE, MAI	NTENANCE REMOVED THE UNIT FROM AIRCRAFT AND VERIFIED AIRCRAFT BUS BAR VOLTAGE WITH  ALTERNATOR OPERATING.  A WORKING KMA	-26 WAS INSTALLED, OPERATION WAS VERIFIED IAW MM AND AIRCRAFT WAS RETURNED TO SERVICE.  THE AIRCRAFT/AUDIO CONTROL PANEL	 HAD NOT COMPLIED RECOMMEND MFG SB03-23-01 AND SB KMA26-5.  THE BULLETINS REQUIRE THAT POWER MODULE INSIDE THE KMA-26 BY	 REPLACED WITH A UPDATED PART NUMBER.  THE KMA-26 HAD BOARD TRACE DAMAGE, BELIEVED TO BE CAUSED BY POWER MODULE FAILURE.		1	H	7	1 	3O			NT	3A12
2004102000197	20041020	00197	CE  	2004	10	20	2004FA0000805    	1	20041001	G	2121	903840311	BLOWER          			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A60      	52043	NE  					CABIN AIR	OVERHEATED      	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	314P					LA170				SMOKE COMING FROM UNDER PILOTS FLOORBOARDS.  UPON INVESTIGATION FOUND ENVIRONMENTAL BLOWER MOTOR TOO HOT TO TOUCH.  AIRC	RAFT LANDED SAFE WITH FIRE DEPARTMENT FOLLOWING.  INSPECTION FOUND NO TIME LIMIT ON BLOWER OR MOTOR.  (EA23200410155)					1	L	7	2 	4T	4	T	 	A31CE   	E4EA
2004110300127	20041103	00127	CE  	2004	11	3	2004FA0000806    	1	20040930	G	2497	024081000	WIRE HARNESS    	SAFT        		LEAR  	45    	45LEAR      	5170805	CE  										BATTERY	MISPINNED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25					117972	450150				WHILE PERFORMING THE OPERATIONAL CHECKS ON BATTERY, BOTH THE T1 (140 DEGREE) SWITCH AND T2 (160 DEGREE) SWITCH WERE IMPR	OPERLY WIRED. TEMP SWITCH T1 WAS WIRED TO PINS C AND D INSTEAD OF PINS C AND E AND SWITCH T2 WAS WIRED TO PINS E AND F I	NSTEAD OF PINS D AND F.  IN EVENT OF THERMAL RUNAWAY ON THE AC, 160 DEGREE SWITCH NOT ONLY PROVIDES A RED CAS AND CREW M	WP BATT OVHT INDICATION BUT ALSO REMOVES THE BATTERY FROM CHARGING CIRCUIT, WITH THIS DEFECTIVE SWITCH HARNESS INSTALLED	 NOT ONLY WOULD A THERMALLY UNSTABLE BATTERY BE ALLOWED TO CONTINUE TO CHARGE AND RUNAWAY BUT CREW WOULD NOT HAVE INDICA	TION THAT EVENT IS TAKING PLACE.IF THEY HAD EICAS CONFIGURED TO VIEW A PAGE OTHER THAN THE SUMMARY OR ELECTRICAL PAGES.	2	L	7	2 	4F			RT	T00008WI
2004102000180	20041020	00180	SO  	2004	10	20	2004FA0000807    	2	20041017	G	8520	6557718	EXHAUST VALVE   			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	BURNED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	732YK	830  	830  			21061879	294273R			EXHAUST VALVE LEAKAGE ON COMPRESSION CHECK.  BURNED VALVE VERIFIED BORESCOPE INSPECTION.  VALVE STEM AND GUIDE WORN BEYO	ND SERVICE LIMITS.					1	H	7	1 	3O	3	O	 	3A21    	E8CE
2004102000181	20041020	00181	EA  	2004	10	20	2004FA0000808    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NR2  CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT, AT A POINT ABOUT 3 MILES NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800 FT (1300 FT AGL), HEA	RD AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING TOWER OF EMER	GENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD VISIBILITY.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004102000182	20041020	00182	EA  	2004	10	20	2004FA0000809    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NR 2 CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT, AT A POINT ABOUT 3 MILES NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800 FT (1300 FT AGL), HEA	RD AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING TOWER OF EMER	GENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD VISIBILITY.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004102000183	20041020	00183	EA  	2004	10	20	2004FA0000810    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	2 CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT (0715 LOCAL TIME), AT A POINT ABOUT 3 MILE NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800' (13	00' AGL), HEARD AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING 	TOWER OF EMERGENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD	 VISIBILITY.			1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004102000184	20041020	00184	EA  	2004	10	20	2004FA0000811    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	NR2 CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT, AT A POINT ABOUT 3 MILES NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800 FT (1300 FT AGL), HEA	RD AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING TOWER OF EMER	GENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD VISIBILITY.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004102000185	20041020	00185	EA  	2004	10	20	2004FA0000812    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NR 2 CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT, AT A POINT ABOUT 3 MILE NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800 FT (1300 FT AGL), HEAR	D AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING TOWER OF EMERG	ENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD VISIBILITY.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004102000186	20041020	00186	EA  	2004	10	20	2004FA0000813    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NR 2 CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT, AT A POINT ABOUT 3 MILES NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800 FT (1300 FT AGL), HEA	RD AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING TOWER OF EMER	GENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD VISIBILITY.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004102000188	20041020	00188	EA  	2004	10	20	2004FA0000814    	2	20041016	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NR 2 CYLINDER	DETACHED        	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	07	4544X	300  	300  			287615027	L2033236A	35407K		WHILE ON CLIMB-OUT, AT A POINT ABOUT 3 MILES NORTH OF THE AIRPORT AND AT AN ALTITUDE OF ABOUT 2800 FT (1300 FT AGL), HEA	RD AND FELT LOUD BANG WITH RESULTING POWER LOSS.  INITIATED 180 DEGREE TURN BACK TO AIRPORT WHILE ALERTING TOWER OF EMER	GENCY.  LANDED WITHOUT FURTHER INCIDENT ALTHOUGH WIND SCREEN WAS TOTALLY COATED WITH OIL PREVENTING FORWARD VISIBILITY.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA
2004110300115	20041103	00115	NE  	2004	11	3	2004FA0000815    	2	20040730	G	7250	30606944	TRANSITION DUCT 			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					HP TURBINE	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	38WP	2475 				292	P115204			FLIGHT CREW MADE 3 ATTEMPTS TO START NR 3 ENGINE.  COCKPIT INDICATION ON N1 AND N2 SHOWED NO ROTATION.  4TH ATTEMPT SHOW	ED ROTATION WITH A NORMAL START.  DURING FLIGHT BACK, CREW NOTED N2 APPROX 2 PERCENT LOWER AT CRUISE.  ITT WAS APPROX 10	0 DEGREES HIGHTER.  ALL OTHER PARAMETERS INDICATED NORMAL.  MAINTENANCE CARRIED OUT GROUND MOTORING RUNS THAT INDICATED 	HARD RUB INSIDE ENGINE.  COMPUTER DOWNLOAD COMPLIED WITH AND ANALYZED BY MFG AND ECTM CONFIRMING HIGH PRESSURE TURBINE A	ND SHROUD FAILURE ENGINE NR 3 REMOVED AND SENT FOR REPAIR.  BANK ENGINE INSTALLED AND AC RELEASED FOR SERVICE.  (NM12004	11360)	2	L	7	3 	4F	4	F	 	A46EU   	E1NM
2004102700091	20041027	00091	CE  	2004	10	27	2004FA0000816    	1	20040902	G	5412	07536007	STIFFENER       			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					FIREWALL	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	7267H	3334 				18280591				2 INCH LONG CRACK IN LT AREA OF FIREWALL STIFFENER IN AREA OF THE PARKING BRAKE BRACKET MOUNTING.  BELIEVED TO BE CAUSED	 BY FLEXING OF FIREWALL BY APPLICATION OF PARKING BRAKE.  THIS IS THE SECOND AC IN FLEET WITH THIS PROBLEM.  THIS AREA N	EEDS ADDITIONAL REINFORCEMENT TO MINIMIZE FLEXING IN THIS AREA.				1	H	7	1 	3O	3	O	NT	3A13    	1E4
2004102700045	20041027	00045	EU  	2004	10	27	2004FA0000817    	1	20040923	G	3221	G1092805	MOUNT BRACKET   			GROB  	109   	G109        	1660204	EU  										TAIL WHEEL	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	909G	700  				6134				BRACKET WAS CRACKED AND BROKEN, ALLOWING THE BRACKET TO BECOME LOOSE.  THE TAIL WHEEL ATTACH STUD CONTACTOR TO ELEVATION	 TORQUE TUBE DAMAGING THE TUB.  RECOMMEND A FLEET WIDE VISUAL INSPECTION FOR CRACKS/ DAMAGE OF BRACKETS/ TORQUE FUSER.					1	K	7	1 	3O			NC	G43EU
2004102700027	20041027	00027	CE  	2004	10	27	2004FA0000818    	1	20040918	G	2820	S116760180	HOSE            			CESSNA	175   	175C        	2072508	CE  	CONT  	O300  	GO300E      	17022	SO  					CARBURETOR	LOOSE           	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	8323T					17557023	260431E			LOST POWER ON TAKE OFF, APPROXIMATELY 100 FT IN THE AIR AT 100 MPH, HALFWAY DOWN RUNWAY.  LANDED AT 10 FEET AT END OF RU	NWAY.  AIRCRAFT TAKEN BACK TO HANGER, REMOVED ENGINE COWL (TOP).  NOTE:  ENGINE PRIMER LINE TO LEFT AFT CYLINDER BROKEN.	  HOSE ASSEMBLY (CARBURETOR TO STRAINER) LOOSE AT CARBURETOR SIDE.  (SW11200408528)				1	H	7	1 	3O	3	O	 	3A17    	E298
2004102700028	20041027	00028	CE  	2004	10	27	2004FA0000819    	1	20040312	G	5510	12326232	REINFORCEMENT   			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	LT HORZ STAB	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	6546N	2597 				21063102	293534R	775725		FOUND REINFORCEMENT BROKEN AT ANNUAL INSPECTION.  BREAK IS AT LOWER OB BOLT HOLE.  PROBABLE CAUSE UNKNOWN.  RECOMMEND CA	REFUL INSPECTION OF AFT HORIZONTAL STABILIZER SPAR REINFORCEMENTS AT EACH 100 HOUR/ ANNUAL INSP.					1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL
2004102700093	20041027	00093		2004	10	27	2004FA0000820    	4	20040903	G	2200	1C7501668P	SERVO           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					PITCH	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	1854N					CE975				ONE SIDE OF BRIDLE CABLE BROKE AT CAPSTAN PIN.  OTHER SIDE O BRIDLE CABLE BACKLASHED AND TANGLED IN CAPSTAN BRIDLE CABLE	 GUARD PINS CAUSING RESTRICTION OF UP ELEVATOR CONTROL.  CENTURY FLIGHT SYSTEMS SB CSB-2003-01 EXISTS FOR THIS TYPE OF C	ONDITION.  POSSIBLY AD WOULD ENSURE COMPLIANCE.  (WP17200405843)				1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004102700072	20041027	00072	SW  	2004	10	27	2004FA0000821    	1	20040908	G	3233		SHAFT           			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540*     	41532	EA  					MLG ACTUATOR	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	2231X					270296				GEAR ACTUATOR (CHATTERED) DURING LANDING GEAR RETRACTION CYCLES.  FOUND APPROX .020 INCH END PLAY ON DRIVE GEAR ASSY SHA	FT.  INSPECTION OF RELATED PARTS REVEALED NO EXCESSIVE WEAR.  IT APPEARS THAT WITH ONLY 632 HRS TSI ON THE ACTUATOR (WHI	CH HAS NEVER BEEN PREVIOUSLY DISASSEMBLED) THAT IT MUST HAVE BEEN IMPROPERLY SHIMMED FROM THE FACTORY.  (EA07200405963)				1	L	7	1 	3O	3	O	RT	2A3     	E14EA
2004102700073	20041027	00073	SW  	2004	10	27	2004FA0000822    	1	20040908	G	3233		CLUTCH SPRING   			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540*     	41532	EA  					MLG ACTUATOR	MISSING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	2231X	632  				270296				AFTER COMPLIANCE WITH SB M20-282 AND THE CORRESPONDING SI 102000-1901 REV 2 THE NO-BACK CLUTCH SPRING MECHANISM WAS ALLO	WING THE ACTUATOR TO (BACK UP) UNDER NORMAL LOADS.  IT WAS FOUND THAT EXCESSIVE FRICTION BETWEEN THE INPUT/DRIVE GEAR AS	SY AND THE OUTPUT/DRIVEN GEAR ASSY CAUSES THEM TO (LOCK) TOGETHER AND THEREFORE ROTATE SIMULTANEOUSLY.  UNDER THIS CONDI	TION THE NO-BACK CLUTCH SPRING WILL SLIP AND NOT LOCK PROPERLY.  TWO CAUSES OF THE EXCESSIVE FRICTION WERE NOTED.  IF TH	E POINT OF CONTACT IS A THE LARGER DIAMETER HUBS INSTEAD OF THE SMALLER DIAMETER GEAR SHAFTS.  IF GEAR SHAFT ASSY IS PRE	LOADED TO THE MAX ACCEPTABLE LIMIT AS DEFINED IN THE ABOVE TWO BULLETINS.	1	L	7	1 	3O	3	O	RT	2A3     	E14EA
2004102700069	20041027	00069	SW  	2004	10	27	2004FA0000823    	1	20040908	G	3230		CLUTCH SPRING   	EATON       		MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540*     	41532	EA  					GEAR ACTUATOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	716PR	145  				270305				LANDING GEAR ACT CYCLED ON AND OFF AT 5-10 SECOND INTERVALS IN DOWN POSITION.  FOUND NO-BACK CLUTCH SPRING (SLIPPING) WH	EN GEAR WAS UNDER PRELOAD IN DOWN OR UP POSITION.  SB M20-282 AND SI 102000-1-901 REV2 , INSTALLING NEW NO-BACK CLUTCH S	PRING, MECHANISM WAS STILL ALLOWING ACT TO (BACK UP) UNDER NORMAL LOADS.  IT WAS FOUND THAT EXCESS FRICTION BETWEEN INPU	T/DRIVE GEAR ASSY, OUTPUT/DRIVEN GEAR ASSY CAUSES THEM TO (LOCK) TOGETHER AND ROTATE.  NO-BACK CLUTCH SPRING WILL SLIP A	ND NOT LOCK PROPERLY.  TWO CAUSES WERE NOTED: IF POINT OF CONTACT BETWEEN TWO DRIVE GEAR ASSY IS AT LARGER DIAMETER HUBS	 INSTEAD OF SMALLER DIAMETER GEAR SHAFTS.  IF GEAR SHAFT IS PRELOADED TO MAX ACCEPT LIMIT AS IN ABOVE BULLETINS.	1	L	7	1 	3O	3	O	RT	2A3     	E14EA
2004102700097	20041027	00097	CE  	2004	10	27	2004FA0000824    	1	20040902	G	5340	07326015	FITTING         			CESSNA	210   	T210G       	2073432	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	TAILCONE	DETACHED        	D			ESER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	6864R	2473 				T2100264	512265	030258		DURING COMPLIANCE WITH SEB88-3 TO REPLACE FORWARD STABILIZER ATTACH FITTINGS PN 0732601-5, IT WAS DISCOVERED THAT THE TO	P TWO RIVETS OF BOTH FITTINGS HAD FAILED LEAVING ONLY THE THREE RIVETS IN THE LOWER PORTION OF EACH FITTING.  ALL FOUR R	IVETS FAILED IN BETWEEN THE STABILIZER AND THE FITTINGS, APPARENTLY IN TENSION, LEAVING THE HEAD AND TAIL OF THE RIVET I	N PLACE.  THERE WAS NO EVIDENCE OF ANY PROBLEM UNTIL THE FITTINGS WERE DRILLED OFF OF THE STABILIZER.  A SUBSTANTIAL AMO	UNT OF BLACK ALUMINUM RESIDUE WAS SANDWICHED BETWEEN THE PARTS INDICATING THE PROBLEM HAD BEEN THERE FOR A WHILE.		1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL
2004102700098	20041027	00098	CE  	2004	10	27	2004FA0000825    	1	20040923	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5519A					CE1337				PILOT SELECTED GEAR DOWN AND NOTHING HAPPENED, SELECTED GEAR DOWN AGAIN AND GEAR CAME DOWN.  UP ON FURTHER TROUBLESHOOTI	NG FOUND RELAY WAS INTERMITTENT, PROBABLE CAUSE AT TIME, UNKNOWN, THIS IS SUPPOSE TO BE AN IMPROVED RELAY SO THERE IS NO	 RECOMMENDATIONS AT THIS TIME.				1	L	7	1 	3O	3	O	 	3A15    	E5CE
2004102600139	20041026	00139	EA  	2004	10	26	2004FA0000827    	2	20040823	G	8550	ES48110	OIL FILTER      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	53215					2842170	L1969739A	A59565		THIS DEFECT WAS FOUND ON 100 HR INSP.  HAD RUN AC TO ENSURE CORRECT OPER OF ENG AND AVIONICS, ENABLE OIL TO WARM UP.  DR	AINED OIL AND WENT TO REMOVE OIL FILTER.  AS OIL FILTER CAME OFF, NOTICED THAT OIL FILTER THREADED STUD WAS STILL ENGAGE	D AND TIGHT IN ENG SIDE OF OIL FILTER ADAPTOR.  IT WAS NOT DIFFICULT TO REMOVE THREADED STUD FROM ENG.  ONCE THREADED PO	RTION HAD BEEN REMOVED, DRAINED OIL FILTER.  OPENED OIL FILTER IN ORDER TO INSPECT FILTER ELEMENT.  UPON REMOVAL OF FILT	ER HSG, NOTED A DELAMINATION, SEPARATION OF FILTER ELEMENT AT CONNECTING POINT.  NOTED THAT THERE WAS EXCESS POTTING COM	POUND WITHIN OIL FILTER TO SECURE ELEMENT TO ELEMENT HSG.  THIS COMPOUND WAS GOOPY/SOFT.	1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004110200108	20041102	00108	CE  	2004	11	2	2004FA0000828    	1	20040622	G	3246	31571299124879	WHEEL           			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					MLG	DAMAGED         	L				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	OEGPA	4876 				5605265	LDB545			AC WAS TOWED, WITH BRAKES RELEASED, WITHOUT ANY BRAKING ACTIVITIES BY PILOT,  SHEARING NOISE WAS NOTED, TOWING PROCESS W	AS STOPPED.  HYD FLUID WAS SPILLED OUT FROM LT BRAKE UNIT.  FIRST INVESTIGATION OF  INSTALLED LT CARBON BRAKE UNIT DID S	HOW, THAT ATTACHING SCREW FOR ONE INSERT ON WHEEL ASSY WAS SHEARED OFF, THEN LOOSE INSERT DAMAGED BRAKE UNIT.  BRAKE FLU	ID SPILLED FROM DAMAGED ACTUATING CYLINDERS, PISTONS.  AS EACH INSERT IS ONLY FIXED BY ONE SCREW, INCASE OF A LOOSEN SCR	EW CORRESPONDING INSERT WILL SHEAR OFF THIS SCREW.  INSERT THEN MOVES OUT OF WHEEL AGAINST BRAKE UNIT.  IN CASE OF THIS 	OCCURRENCE DURING TAKE OFF ROLL, AFTER TOUCH DOWN OR TAXI, UNCONTROLLED AND EVENTFUL BRAKE OUT WOULD BE FORSEEABLE.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004102600142	20041026	00142	GL  	2004	10	26	2004FA0000830    	2	20040812	G	7230	230397911	ADAPTER         	ALLSN       		AGUSTA	A109  	A109        	0260109	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 2 COMPRESSOR	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	109WF	2961 			CAC39323	7298	CAE834720			DURING FLIGHT PILOT HEARD MUFFLED BANG AND EXPERIENCED YAWING OF FUSELAGE WITH RELATED HIGH TOT INDICATION OF NR 2 ENG. 	 ENGINE SHUT DOWN AND EMERGENCY LANDING CARRIED OUT.  AC RECOVERED BY ROAD TO MAINT FACILITY.  INVESTIGATION REVEALED MI	NOR DEBRIS ON ACCESSORY GB, CHIP DETECTOR AND COMPRESSOR/ POWER TURBINE SPINS FREELY BY HAND BUT, WITH COMPRESSOR TURNIN	G ACCESSORY DRIVES DO NOT ROTATE.  ENG MODULES SEPARATED AND COMPRESSOR ADAPTOR FOUND SHEARED.  ALERT BULLETIN HAS NOT B	EEN COMPLIED WITH ON THIS ENGINE AND MFG MAY SET AN OPER TIME LIMIT.		1	G	7	2 	3U	3	U	 	H7EU    	E4CE
2004102600133	20041026	00133	SO  	2004	10	26	2004FA0000831    	1	20040923	G	2520	51023306	PLATE           			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360A1D     	41514	EA  					SEAT BELT	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	400LM					10061				WHILE REPLACING REAR PASSENGER SEAT BELTS, IT WAS DISCOVERED THAT PN 51023306 REINFORCEMENT PLATE HAD BEEN INSTALLED ON 	FWD SIDE OF AFT SEAT BULKHEAD UNDER SEATBELT ATTACH BRACKET.  THE -6 PLATE SHOULD HAVE BEEN INSTALLED ON AFT SIDE OF THE	 BULKHEAD IAW AGAG DRAWING 5102299.  MS20364-1032 (THIN SHEER NUT) WAS USED TO SECURE THE AN3-5A RETAINING BOLTS.  MS203	65-1032 OR MS21042-3 NUTS SHOULD HAVE BEEN INSTALLED AS CALLED OUT ON THE DRAWING.  THIS RESULTS IN REDUCED SEATBELT ATT	ACHMENT STRENGTH WHEN COMPARED WITH THE DESIGN CONFIGURATION.  THIS AC APPEARED TO HAVE THE ORIGINAL SEATBELTS INSTALLED	 SO IT IS LIKELY THAT THIS IMPROPER INSTALLATION WAS ACCOMPLISHED DURING ASSEMBLY.  (EA07200406183)	1	L	7	1 	3O	3	O	NT	1L71    	E286
2004102600135	20041026	00135		2004	10	26	2004FA0000832    	4	20040324	G	3461	4010455000101	DISPLAY         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985*       	52008	NE  					INSTRUMT PANEL	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	62355					1045				FOLLOWING THE INSTALLATION OF THE EFIS-SV SYSTEM, THE SOFTWARE WAS LOADED ONTO A SMART MEDIA CARD AND THE SMART MEDIA CA	RD WAS INSERTED INTO THE INTEGRATED DISPLAY UNIT (IDU).  SEVERAL ATTEMPTS WERE MADE TO UPLOAD THE INFORMATION INTO THE S	YSTEM.  IT WAS DETERMINED THAT THE IDU WOULD NOT READ THE DATA FROM THE CARD, SO THE IDU WAS REPLACED AND THE SOFTWARE U	PLOAD WAS COMPLETED SUCCESSFULLY.  IDU SN 36244, MFG DATE CODE: 03328			1	H	7	1 	3R	3	R		A806    	5E1
2004102700063	20041027	00063	SO  	2004	10	27	2004FA0000833    	1	20040331	G	3010	4010455000101	DISPLAY         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					INSTRUMENT PANEL	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	15950					327340075				DURING THE INITIAL GROUND CALIBRATION FOR THE EFIS-SV, THE RT CONTROL KNOB OF THE INTEGRATED DISPLAY UNIT (IDU) WOULD NO	T ENTER THE CORRECT DATA WHEN PUSHED.  THE IDU WAS REPLACED AND THE CALIBRATION PROCEEDED NORMALLY.  IDU SN 34410.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA
2004102600161	20041026	00161	SO  	2004	10	26	2004FA0000834    	1	20040320	G	2497		CIRCUIT CARD    	CHELTON     		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					IDU	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	3590N					318052148				OPERATOR WAS IN PROCESS OF UPGRADING SOFTWARE FOR EFIS-SV SYSTEM IAW SB WSB IDU-III-6.  THE NEW DATA WAS LOADED ONTO THE	 SMART MEDIA CARDS AND THE CARDS WERE THEN INSTALLED IN THE INTEGRATED DISPLAY UNITS (2EA).  UPON INITIALIZATION OF THE 	SOFTWARE UPLOAD, THE ENTIRE SYSTEM MALFUNCTIONED AND COULD NOT BE REINITIALIZED.  THE AC WAS GROUNDED.  AFTER SEVERAL UN	SUCCESSFUL ATTEMPTS TO RELOAD THE UPGRADE ONTO THE CARDS AND THEN UPLOAD THE INFORMATION INTO THE SYSTEM, THE SMART MEDI	A CARDS WERE REPLACED WITH NEW, THE INFORMATION DOWN LOADED ONTO THE CARDS, AND THE SYSTEM SUCCESSFULLY REBOOTED AND FUN	CTIONED PROPERLY.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004110300135	20041103	00135		2004	11	3	2004FA0000835    	4	20040314	G	2330		CIRCUIT CARD    			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	IO470*      	17026	SO  					DISPLAY	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	7687K					18052703				THE OPERATOR WAS IN THE PROCESS OF UPGRADING THE SOFTWARE FOR THE EFIS-SV SYSTEM IAW SB WSB IDU-III-6.  THE NEW DATA WAS	 LOADED ONTO THE SMART MEDIA CARDS AND THE CARDS WERE THEN INSTALLED IN THE INTEGRATED DISPLAY UNITS (2 EA.)  UPON INITI	ALIZATION OF THE  SOFTWARE UPLOAD, THE ENTIRE SYSTEM MALFUNCTIONED AND COULD NOT BE REINITIALIZED.  THE AIRCRAFT WAS GRO	UNDED.  AFTER SEVERAL UNSUCCESSFUL ATTEMPTS TO RELOAD THE UPGRADE ONTO THE CARDS AND THEN UPLOAD THE INFORMATION INTO TH	E SYSTEM, THE SMART MEDIA CARDS WERE REPLACED WITH NEW, THE INFORMATION DOWNLOADED ONTO THE CARDS, AND THE SYSTEM SUCCES	SFULLY REBOOTED AND FUNCTIONED PROPERLY.	1	H	7	1 	3O	3	O	 	5A6     	E1CE
2004102700062	20041027	00062		2004	10	27	2004FA0000836    	4	20040329	G	3457	84100020301	RECEIVER        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					GPS/WAAS	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8127K	30   				327940268				THIS RECEIVER WAS INSTALLED AS PART OF THE EFIS-SV SYSTEM.  AFTER APPROXIMATELY 30 HOURS OF OPERATION FOLLOWING THE INST	ALLATION, AN LOI MESSAGE DISPLAYED ON THE INTEGRATED DISPLAY UNIT (IDU).  THE RECEIVER WAS REPLACED, AND THE ERROR MESSA	GE WAS NO LONGER DISPLAYED, AND THE SYSTEM FUNCTIONED NORMALLY.  GPS/WAAS RECEIVER, SN 4048218.				1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004102700085	20041027	00085	EA  	2004	10	27	2004FA0000837    	2	20040916	G	7322	30804	FLOAT           			AMRGEN	AA1   	AA1A        	0630710	SO  	LYC   	O235  	O235K2C     	41505	EA  					CARBURETOR	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	9253L	200  				AA1A0153	L1051215			ENGINE STALLED WHILE AIRCRAFT WAS ON FINAL APPROACH.  DURING TEST RUN, ENGINE PERFORMED NORMALLY DURING RUN UP CHECK, ID	LE CHECK AND MIXTURE CHECK AT 1000 RPM.  HOWEVER, WHEN THE ENGINE LT AT IDLE (650 RPM) THE ENGINE WOULD BEGIN TO RUN RIC	H, LOPE AND QUIT RUNNING AFTER ABOUT 1 TO 2 MINUTES.  THE CARBURETOR WAS REMOVED AND INSPECTED.  ONE HALF OF THE FLOAT, 	WHICH IS MADE OF HOLLOW PLASTIC, WAS FILLED WITH FUEL.			1	L	7	1 	3O	3	O	 	A11EA   	E223
2004102700086	20041027	00086	CE  	2004	10	27	2004FA0000838    	1	20041014	G	5711	58221661	SPAR CAP        			CESSNA	404   	404         	2075901	CE  										WING	CORRODED        	B			AK6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	677MF	8000 				4040421				DURING OUR INITIAL INSPECTION OF THIS AIRCRAFT, DISCOVERED SEVERE INTERGARNULAR CORROSION ON UPPER AND LOWER REAR SPAR C	APS.  THE AREA OF CORROSION IS LOCATED INSIDE THE MAIN GEAR WELL ON BOTH LEFT AND RIGHT WINGS.  NOTE:  AIRCRAFT IS OPERA	TED IN A SALT AIR ENVIRONMENT FOR THE LAST YEAR.				1	L	7	2 	3O			RT	A25CE
2004102700088	20041027	00088	CE  	2004	10	27	2004FA0000839    	1	20041014	G	5711	58221664	SPAR CAP        			CESSNA	404   	404         	2075901	CE  										WING	CORRODED        	B			AK6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	677MF	8000 				4040421				DURING OUR INITIAL INSPECTION OF THIS AIRCRAFT, DISCOVERED SEVERE INTERGRANULAR CORROSION ON UPPER AND LOWER REAR SPAR C	APS.  THE AREA OF CORROSION IS LOCATED INSIDE THE MAIN GEAR WELL ON BOTH LEFT AND RT WINGS.  NOTE:  THIS AIRCRAFT IS OPE	RATED IN A SALT AIR ENVIRONMENT FOR THE LAST YEAR.				1	L	7	2 	3O			RT	A25CE
2004102700087	20041027	00087	SO  	2004	10	27	2004FA0000840    	2	20040707	G	7414		DISTRIBUTOR BLK 			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					MAGNETO	BURNED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	24FG				01062608	18504207				ON 5/20/2004 THIS MAGNETO WAS REMOVED, PILOT REPORTED ROUGH ENGINE OPERATION AT ALTITUDES OF 8,000 FT OR HIGHER.  PILOT 	ISOLATED MISFIRING MAGNETO.  MAGNETO APPEARED TO BE FUNCTIONING NORMALLY ON GROUND AT SEA LEVEL AND INFLIGHT AT LOWER AL	TITUDES.  MAGNETO DISASSEMBLED.  DIST BLOCK AND GEAR ASSY WERE SEVERELY BURNED AND MELTED.  THE CARBON BRUSH WAS GONE, A	N THE HIGH TENSION LEAD AREA OF THE COIL WAS BURNED.  DUE TO SEVERAL FACTORS: INTERNAL ROUGHNESS OF HOLE IN SHAFT WERE C	ARBON BRUSH RIDES, CARBON BRUSHES MFG OF TOO SOFT COMPOUND AND CARBON BUILDUP WHICH CAUSES SHORT.		1	H	7	1 	3O	3	O	 	3A24    	E5CE
2004102600144	20041026	00144	SW  	2004	10	26	2004FA0000841    	1	20041021	G	7603	269A84601	BRACKET         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360*      	41514	EA  					THROTTLE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	614TV	2658 	35   			0035				A STUDENT NOTICED ON PRE-FLIGHT, A CRACK ON THE THROTTLE BELLCRANK SUPPORT BRACKET, (PN 269A8460-1) MOUNTED TO THE CARBU	RETOR. THE CRACK WAS LOCATED JUST BELOW THE THROTTLE CONTROL BELLCRANK ATTACH LUG AND WAS NOTICEABLE UPON APPLYING LATER	AL PRESSURE TO A LINKAGE TO WHICH THE THROTTLE BELLCRANK IS ATTACHED. THE CRACK WAS APPROX. AROUND 75 PERCENT OF THE WEB	.			1	G	7	1 	3O	3	O	O	4H12    	E286
2004102700078	20041027	00078	SW  	2004	10	27	2004FA0000842    	1	20041021	G	7603	269A84601	BRACKET         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360*      	41514	EA  					THROTTLE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	614TV	2658 	35   			0035				A STUDENT NOTICED ON PRE-FLIGHT A CRACK ON THE THROTTLE BELLCRANK SUPPORT BRACKET, (PN 269A8460-1)MOUNTED TO THE CARBURE	TOR. THE CRACK WAS LOCATED JUST BELOW THE THROTTLE CONTROL BELLCRANK ATTACH LUG AND WAS NOTICEABLE UPON APPLYING LATERAL	 PRESSURE TO A LINKAGE TO WHICH THE THROTTLE BELLCRANK IS ATTACHED. THE CRACK WAS APPROX. AROUND 75 PERCENT OF THE WEB.				1	G	7	1 	3O	3	O	O	4H12    	E286
2004102700079	20041027	00079	CE  	2004	10	27	2004FA0000843    	1	20041022	G	1410	62402312D0463	HOSE            			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A28      	 	EA  					OIL COOLER	DETERIORATED    	G				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	15	3741M	7    				LW342				DURING CLIMB OUT, OIL PRESSURE ON BOTH ENGINES DROPPED TO APPROXIMATELY 50 PSI WITH SLIGHT SURGING.  AUTOFEATHER WAS ENG	AGED AT THE TIME.  MAINTENANCE FACILITY DISCOVERED THAT BOTH OIL COOLER LONG LINES WERE DETERIORATING INTERNALLY. THE HO	SES ARE AEROQUIP HOSES PART NUMBER 033 624023-12D0463.  THIS BATCH OF HOSE WAS PRODUCED IN THE 3RD QUARTER OF 2004 AS IN	DICATED ON THE DATA TAG.  THE HOSES HAD APPROXIMATELY 7 HOURS USE PRIOR TO FAILURE.			1	L	7	2 	3T	4	T	 	3A20    	E4EA
2004102700083	20041027	00083		2004	10	27	2004FA0000844    	4	20041020	G	2562		ELT             			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					CAIBN	INCORRECT       	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	05	521JL					0877				DURING A RECENT INSPECTION OF A NEW AC IT WAS NOTED THAT THE ELT SWITCH WAS IN THE OFF POSITION FROM THE MANUFACTURE, UP	ON FURTHER INVESTIGATION THE PILOT RECEIVED THE AIRCRAFT FROM THE FACTORY AND WAS NOT INFORMED THAT THE SWITCH WAS OFF D	URING HIS FLY-OFF FROM THE FACTORY.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2004111000083	20041110	00083	SO  	2004	11	10	2004FA0000845    	1	20041018	G	2701	6271607	SHAFT           	PIPER       		PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  					CONTROL COLUMN	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	43761	6806 				28R7703310				DURING 100 HOUR INSP AT 1V5, LT CONTROL COLUMN, P/N 62834-02, WAS REMOVED FOR REPLACEMENT DUE TO EXCESS PLAY. UPON REMOV	AL, CONTROL COLUMN SHAFT, P/N 62716-02, WAS FOUND TO BE DRILLED (FOR AN-386-1-6A TAPER PIN) LESS THAN 0.025 INCH FROM AF	T END OF SHAFT.  HOLE IS SO CLOSE TO END THAT SHAFT WAS DEFORMED APPROX. .125 INCH BY TAPER PIN. FWD END OF SHAFT WAS IN	SERTED APPROX 0.20 INCH BEYOND THE END OF SPROCKET, P/N 62839-00, AND TAPER PIN HOLE IS APPROX. 0.35 INCH FROM FWD END O	F SHAFT.  REPLACEMENT UNIVERSAL, PMA, P/N CA62834-802, HAS A WITNESS HOLE TO ENSURE SHAFT IS FULLY INSERTED BEFORE DRILL	ING.  INSPECT SHAFT TO DETERMINE AMOUNT OF PENETRATION, THROUGH SPROCKET,  REPLACE SHAFT IF IT PROJECTS BEYOND SPROCKET.	1	L	7	1 	3O	3	O	 	2A13    	E9CE
2004111000084	20041110	00084	SO  	2004	11	10	2004FA0000846    	1	20041018	G	2701	6271607	SHAFT           	PIPER       		PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  					CONTROL COLUMN	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	43761	6806 				28R7703310				DURING 100 HR INSP AT 1V5, LT CONTOL COLUMN UNIVERSAL,P/N 62834-02, WAS REMOVED FOR REPLACEMENT DUE TO EXCESS PLAY.  CON	TROL COLUMN SHAFT, P/N 62716-02, WAS FOUND TO BE DRILLED (FOR THE AN-386-1-6A TAPER PIN) LESS THAN 0.025 INCH FROM AFT E	ND OF SHAFT.  HOLE IS SO CLOSE TO END THAT SHAFT WAS DEFORMED APPROX .125 INCH BY TAPER PIN.  FWD END OF SHAFT WAS INSER	TED APPROX 0.20 INCH BEYOND END OF SPROCKET, P/N 62839-00, TAPER PIN HOLE IS APPROX. 0.35 INCH FROM FWD END OF SHAFT.  R	EPLACEMENT UNIVERSAL, PMA PRODUCTS P/N CA62834-802, HAS A WITNESS HOLE TO ENSURE SHAFT IS FULLY INSERTED BEFORE DRILLING	.  OPS INSPECT SHAFT TO DETERMINE AMT OF PENETRATION, THROUGH SPROCKET, REPLACE SHAFT IF IT PROJECTS BEYOND SPROCKET.	1	L	7	1 	3O	3	O	 	2A13    	E9CE
2004110300005	20041103	00005	SO  	2004	11	3	2004FA0000847    	1	20040826	G	2750	82905003	BELLCRANK       			PIPER 	PA46  	PA46350P    	7104602	SO  										TE FLAP	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	77PK	2538 				4622089				RT IB FLAP BELLCRANK SHAFT SHEARED ON APPROACH FOR LANDING CAUSING ASYMMETRICAL FLAP CONDITION.  BELLCRANK SHOWED SIGNS 	OF BEING CRACKED FOR A LONG TIME.  FLAP SYSTEM WAS WAY OUT OF RIG.  OUT OF RIG PROBLEM CAUSED BY TWISTING OF BELLCRANK S	HAFT AND FURTHER ADJUSTMENTS OF ROD END CAUSING UNDUE LOAD.				1	L	7	1 	3O			RT	A25SO
2004110300033	20041103	00033	CE  	2004	11	3	2004FA0000848    	1	20040916	G	3222	67420861	CAP             			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					STRUT	UNSCREWED       	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CE	07	953QS	3350 				7500153				AT FLIGHT LEVEL 390, THE AIRCRAFT EXPERIENCED A JOLT AND THE LANDING GEAR UNLOCK LIGHT ILLUMINATED.  THE PROBLEM WAS CAU	SED BY THE NOSE LANDING GEAR DROPPING OUT OF THE UPLOCK HOOK.  IT WAS DETERMINED THAT THE NOSE GEAR STRUT WAS OVER EXTEN	DED.  THE NOSE GEAR WAS DISASSEMBLED AND THE LOWER ORIFICE CAP WAS FOUND TO BE PARTIALLY UNSCREWED.  THE SAME PROBLEM HA	S OCCURRED ON OTHER AIRCRAFT OF THIS MODEL.			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH
2004110300109	20041103	00109	GL  	2004	11	3	2004FA0000849    	2	20041018	G	7250	689967	TURBINE WHEEL   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				T	J		ENGINE CASE PENETRATION   	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	09	54GL	490  				4068	CAE270452			DURING GROUND RUN, AFTER SCHEDULED TURBINE REPLACEMENT, LEAK CHECKS HAD BEEN COMPLETED AT IDLE POWER.  WHILE ADDING POWE	R, AT ABOUT 85 PERCENT N2 THE NR 3 TURBINE WHEEL EXPERIENCED AN UNCONTAINED FAILUE DESTROYING THE ENGINE AS WELL AS DAMA	GING THE COWLING, ROTOR BLADES, AND ENGINE PAN AND STRUCTURE. THE CAUSE IS UNDER INVESTIGATION BY MFG.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004110300110	20041103	00110	GL  	2004	11	3	2004FA0000850    	2	20041018	G	7250	689967	TURBINE WHEEL   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				T	J		ENGINE CASE PENETRATION   	WARNING INDICATION        		IN	INSP/MAINT     	1			SW	09	54GL	490  				4068	CAE270452			DURING GROUND RUN, AFTER SCHEDULED TURBINE REPLACEMENT, LEAK CHECKS HAD BEEN COMPLETED AT IDLE POWER.  WHILE ADDING POWE	R, AT ABOUT 85 PERCENT N2 THE NR3 TURBINE WHEEL EXPERIENCED AN UNCONTAINED FAILURE DESTROYING THE ENGINE AS WELL AS DAMA	GING THE COWLING, ROTOR BLADES, AND ENGINE PAN AND STRUCTURE. THE CAUSE IS UNDER INVESTIGATION BY MFG.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004111000077	20041110	00077	CE  	2004	11	10	2004FA0000851    	1	20040923	G	5610		WINDSCREEN      			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					COCKPIT	DISTORTED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99						5368				ON DELIVERY OF A NEW AIRCRAFT, DAY ACCEPTANCE CHECK CARRIED OUT AND AIRCRAFT ACCEPTED. DURING NIGHT FLYING LT WINDSCREEN	 OBSERVED TO HAVE PARALLAX DISTORTION ERROR. DAY TESTS CARRIED OUT OF GRID TEST AND WATER TEST.  WINDSCREEN CERTIFIED SE	RVICEABLE BY VENDOR AND MFG ENGINEERS. PILOTS INSISTED CHECK BE CARRIED OUT AT NIGHT BY TEST PILOT WHO CONFIRMED DEFECT.	  WINDSCREEN CHANGED.  PRESENT DAY TESTS ONLY FOR WINDSCREEN PARALLAX AND DISTORTIONS INADEQUATE TO DETECT THESE FLAWS W	HICH CAN ONLY BE DETECTED AT NIGHT. MFG INDICATES THIS IS THE FIRST CASE DETECTED. SINCE THE PRESENT DAY TESTS ONLY CANN	OT DETECT THIS FLAW/DEFECT MANY AIRCRAFT MUST BE FLYING WITH THIS DEFECT.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004120700173	20041207	00173	CE  	2004	12	7	2004FA0000852    	1	20040923	G	5610		WINDSCREEN      			CESSNA	560   	560XL       	2076702	CE  										COCKPIT	DISTORTED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		10   				5368				ON DELIVERY OF NEW A/C, DAY ACCEPTANCE CHECK CARRIED OUT AND A/C ACCEPTED. DURING NIGHT FLYING LT WINDSCREEN OBSERVED TO	 HAVE PARALLAX DISTORTION ERROR.  DAY TESTS CARRIED OUT OF GRID TEST AND WATER TEST. WINDSCREEN CERTIFIED SERVICEABLE BY	 VENDOR & MANUFACTURERS ENGINEERS. PILOTS INSISTED CHECK BE CARRIED OUT AT NIGHT BY TEST PILOT, OVERRIDING INSISTENCE BY	 ENGINEERS ON WINDSCREEN HAVING NO DEFECT & BEING SERVICEABLE. TEST PILOT CONFIRMED DEFECT. WINDSCREEN CHANGED.PRESENT D	AY TESTS ONLY  FOR WINDSCREEN PARALLAX & DISTORTIONS INADEQUATE TO DETECT THESE FLAWS WHICH CAN ONLY BE DETECTED AT NIGH	T. CESSNA INDICATES THIS IS THE FIRST CASE DETECTED. SINCE THE PRESENT DAY TESTS ONLY CANNOT DETECT THIS FLAW/DE	2	L	7	2 	4F			RT	A22CE
2004111000082	20041110	00082	CE  	2004	11	10	2004FA0000853    	1	20040709	G	3220	08421211	ROD END         			CESSNA	310   	T310Q       	2074244	CE  										NLG	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	27KC					310Q1134				THE AIRCRAFT DEPARTED.  A LARGE NOISE WAS HEARD, COULD NOT EXTEND NOSE GEAR.  LANDED WITH AN UNSAFE NOSE GEAR UP, NOSE G	EAR COLLAPSED ON LANDING CAUSING DAMAGE.  THE ROD END FAILED ON TUBE ASSY.  NOTE:  THIS IS A COMMON PROBLEM ON THE AK.  	(SW05200408481)				1	L	7	2 	3O			 	3A10
2004111000076	20041110	00076	NE  	2004	11	10	2004FA0000855    	1	20041029	G	2910		LINE            			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HYD SYSTEM	CRACKED         	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	25	6691L					454	L747351A			DURING FLT, HYD PUMP STARTED TO CYCLE ABNORMALLY.  IDENTIFIED HYDRAULIC PRESSURE LOSS TO LANDING GEAR RETRACT CIRCUIT AN	D ISOLATED WITH LDG GEAR SELECTOR. GEAR EXTENDED FOR LANDING NORMALLY. DURING POST INSPECTION FOR LEAK, LOCATED HYD TUBE	 AT AFT BULKHEAD STATION 126, CRACKED .5 INCHES FROM FITTING. LINES WERE BUNDLED TOGETHER WITHOUT PROPER SUPPORT OR SEPA	RATION AT FITTINGS. REMOVED FLOOR BOARDS AND ALSO FOUND BROKEN AND INADEQUATE SUPPORT ALLOWING LINES TO VIBRATE AND CHAF	E.  SECURED ALL LINES AND PROVIDED SEPARATION AT FITTINGS. LOGBOOK INDICATED PREVIOUS HYD TUBE FAILURE ON RT SIDE OF AIR	CRAFT.	1	H	7	1 	3O	3	O	 	1A13    	1E10	5	C	P920
2005030800113	20050308	00113	SW  	2005	3	8	2004FA0000858    	1	20040827	G	5320	35011007	ANGLE           			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					FUSELAGE	CORRODED        	B			MYNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	6832V	7144 				201162				CROSS MEMBER AT STA 103, SUPPORT RUDDER, ELEVATOR PUSH ROD HANGER AND SUPPORTS A HANGER FOR TAIL TRIM TUBE.  (GL11200413	706)					1	L	7	1 	3O	3	O		2A3     	E286
2005030800114	20050308	00114	CE  	2005	3	8	2004FA0000859    	1	20040827	G	2460		CIRCUIT BREAKER 			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					ELECTRICAL SYS	MISINSTALLED    	B			RSUR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	5107Y					T18208099				GPS CIRCUIT BREAKER IS PROVIDING POWER TO MULTIPLE UNITS WHICH IS CONTRARY TO AC20-138A.  AC20-138 STATES THAT GPS CIRCU	IT BREAKER CAN ONLY POWER GPS.  REFERENCE ATTACHED DRAWINGS FROM MFG WIRING DIAGRAM MANUAL.  PAGES 34-20-00-01 AND 34-52	-03-01.				1	H	7	1 	3O	3	O	NT	3A13    	E14EA
2004112900164	20041129	00164		2004	11	29	2004FA0000860    	4	20040928	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										PROP SPINNER	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	3512T					172S8883				PILOTS REPORTED AFT SPINNER BULKHEAD CRACKED AND SPINNER DOME BENT UP SLIGHTLY.  UPON INSPECTION CORNER NUTPLATE FOUND C	OMPLETELY BROKEN OFF BULKHEAD.					1	H	7	1 	3O			NT	3A12
2004111000057	20041110	00057	CE  	2004	11	10	2004FA0000861    	1	20041031	G	2497		WIRE            	CESSNA      		CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					ALTERNATOR	BURNED          	D				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CE	03	21076	332  			A173381	20608213				PILOT REPORTED AN ALTERNATOR FAILURE.  REMOVED ENGINE COWLING AND FOUND THE POWER WIRE AND THE GROUND WIRE FOR THE ALTER	NATOR WERE BROKEN IN HALF ABOUT 3 INCHES FROM THE TERMINALS ON THE ALTERNATOR.  THE ENDS OF BOTH WIRES WERE MELTED, SUSP	ECTED FROM ARCING.  UPON FURTHER INSPECTION, FOUND THE GROUND WIRE TERMINAL STUD WAS BROKEN OFF THE BACK OF THE ALTERNAT	OR.  WE SUSPECT THE WIRES BROKE BECAUSE OF THE SHARP BEND RADIUS THE WIRES ARE SUBJECTED TO BETWEEN THE ENGINE BAFFLING 	AND THE ALTERNATOR.		1	H	7	1 	3O	3	O	RT	A4CE    	1E4
2004112900037	20041129	00037	NE  	2004	11	29	2004FA0000862    	2	20040913	G	7320	660526AS	TRANSDUCER      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL FLOW	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	37756	634  			2679	1456	2679			REMOVED FUEL FLOW TRANSDUCER PN 660526AS INSTALLED UNDER STC NR SA809GL.  UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AN	D CAUSING THE AIR DATA COMPUTER (ADC) ALSO INSTALLED IN THE AIRCRAFT TO FUNCTION IMPROPERLY.  AIR DATA COMPUTER INSTALLE	D UNDER FLIGHT SYSTEMS EFIS-SV SYSTEM IAW STC NR SA02203AK.				1	H	7	1 	3R	3	R	 	A806    	5E1
2004112900059	20041129	00059	NE  	2004	11	29	2004FA0000863    	2	20040913	G	7320	660526AS	TRANSDUCER      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL FLOW	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	67676	601  			2680	809	2680			REMOVED FUEL FLOW TRANSDUCER INSTALLED UNDER STC NR SA809GL.  UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AND CAUSING TH	E AIR DATA COMPUTER (ADC) ALSO INSTALLED IN THE AIRCRAFT TO FUNCTION IMPROPERLY.  AIR DATA COMPUTER INSTALLED, EFIS-SV S	YSTEM IAW STC NR SA02206AK.				1	H	7	1 	3R	3	R	 	A806    	5E1
2004112900079	20041129	00079	NE  	2004	11	29	2004FA0000864    	2	20040913	G	7320	660526AS	TRANSDUCER      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL FLOW	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	68010	362  			2681	1243	2681			REMOVED FUEL FLOW TRANSDUCER, INSTALLED UNDER STC NR SA809GL.  UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AND CAUSING T	HE AIR DATA COMPUTER (ADC) ALSO INSTALLED INT THE AIRCRAFT TO FUNCTION IMPROPERLY.  AIR DATA COMPURTER (ADC) INSTALLED, 	EFIS-SV SYSTEM IAW STC NR SA02203AK.				1	H	7	1 	3R	3	R	 	A806    	5E1
2005022300003	20050223	00003	EA  	2005	2	23	2004FA0000870    	1	20040730	G	5320	601R35031239	ANGLE           			CNDAIR	CL600 	CL6002B19   	1900309	EA  										FUSELAGE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	935SW					7725				FLOOR SUPPORT ANGLE AT FS 621, WL 73 OUTBOARD OF LBL AND RBL 27 CRACKED.  REPAIR IAW BOMBARDIER AEROSPACE EO NR 601R-53-	61-117.					2	L	7	2 	4F			RT	A21EA
2005022300001	20050223	00001	CE  	2005	2	23	2004FA0000871    	1	20040801	G	2730	6565007197CR	BRIDAL CABLE    			CESSNA	500   	560CESSNA   	2076750	CE  										ELEVATOR	FRAYED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05						5600028				ELEVATOR AUTO PILOT BRIDAL CABLE FRAYED TO THE POINT OF LOCKING UP CONTROL.  DURING LOCATING CONTROL BLOCKAGE CABLE BROK	E COMPLETELY INTO AT THE SUPPORT GUIDE PULLEYS.  PRE-SB 560-27-07.					2	L	7	2 	4F			RT	A22CE
2005022300002	20050223	00002	CE  	2005	2	23	2004FA0000872    	1	20040809	G	3240	6242020519	BRAKE           			CESSNA	650   	650         	2076802	CE  										MLG	OUT OF ADJUST   	I				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			GL	13	260VP					6500190				ON DEPARTURE FROM MKE, CREW NOTED A SHIMMY IN THE NOSE WHEEL AND ABORTED TAKEOFF.  INSPECTION FOUND NOSE GEAR FRICTION B	RAKE DRAG LOW.  ADJUSTED FRICTION BRAKE PER CE650 MM.  COMPLETED HIGH SPEED (100 KTS) TAXI CHECK WITH NO SHIMMY EVIDENT.	  RELEASED AIRCRAFT FOR SERVICE.  (M)				2	L	7	2 	4F				A9NM
2005012700065	20050127	00065	GL  	2005	1	27	2004FA0000873    	1	20040922	G	2810		FUEL CELL       			AMTR  	CHALGR	CHALLENGERII	05624JT	GL  											MISMANUFACTURED 	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	13	2079S	13   				CH22017				DURING CRUISE FLIGHT, THE ROTAX ENGINE EXPERIENCED POWER LOSS AND PILOT PERFORMED EMERGENCY LANDING.  AIRCRAFT SUSTAINED	 SUBSTANTIAL DAMAGE AND PILOT WAS SERIOUSLY INJURED.  SUBSEQUENT INVESTIGATION REVEALED THAT WATER WAS IN BOTH CARBURETO	R FUEL BOWLS, THE FUEL FILTER AND THE FUEL TANK.  DISCOVERED THAT THE 10 GALLON PLASTIC FUEL TANK HAD A LOW POINT MOLDED	 INTO IT FOR COLLECTION OF WATER AND DEBRIS, HOWEVER THERE WAS NO FUEL DRAIN VALVE IN ORDER TO SUMP THE TANK.			1	H	7	1 	3I			NT	EXPA1H71
2004121300001	20041213	00001	SO  	2004	12	13	2004FA0000874    	2	20041006	G	7414		IMPULSE COUPLING			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					MAGNETO	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	6935C	1225 	1225 		D02HA094R	347870167	807783R			WHILE PERFORMING AD 96-12-07, THE MECHANIC NOTICED THAT THE STOP PIN FOR THE IMPULSE COUPLING WAS MISSING.  INSPECTED TH	E ACCESSORY SECTION AND FOUND THE PIN WEDGED BETWEEN THE CRANK CASE AND A GEAR.  REMOVED THE PIN, NO FURTHER DAMAGE WAS 	FOUND.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE
2005022300179	20050223	00179	NM  	2005	2	23	2004FA0000876    	1	20040719	G	6220	900R2101006107	ROTOR HEAD      	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	91   	91   		0099990080	9000085				DURING ACCOMPLISHMENT OF AD 2002-10-05, "MAIN ROTOR UPPER HUB INSP", FOUND (2) OUT OF (10) HOLES CRACKED IN UPPER HUB FL	ANGE AS DEPICTED IN MD HELICOPTERS SERVICE BULLETIN 900-072 PART TOTAL TIME: 91.23 HRS.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005022300178	20050223	00178	NM  	2005	2	23	2004FA0000877    	1	20041012	G	6220		ROTOR HEAD      			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			HO	HOVERING       	1			EA	11	3PD	1478 								HAD VIBRATION (.7 IPS) CAUTION ON IDS DURING FLIGHT AND HIGH VIBRATION ON SHUT DOWN BETWEEN 30-40 PERCENT NR.  INSPECTED	 MAIN ROTOR SYSTEM IAW MAINTENANCE MANUAL AND FOUND (3) OUT OF (5) FLEXBEAMS CRACKED.  REPLACING FLEXBEAMS WITH NEW UPDA	TED FLEXBEAMS.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005022300167	20050223	00167	GL  	2005	2	23	2004FA0000878    	1	20041008	G	3213		AXLE            			AMTR  	ZENITH	ZENITHCH701 	05611WI	GL  	ROTAX 	912   	ROTAX912UL  	 	EU  					WHEEL ASSEMBLY	SEPARATED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	701TD	68   	66   			73993	4403395			LEFT MAIN AXLE SEPARATED FROM BACKING PLATE AT LANDING CAUSING MAIN SPRING TO DIG IN, WHICH CAUSED THE PLANE TO NOSE OVE	R.  INSPECTION OF THE AXLE ASSEMBLY REVEALED VERY LITTLE WELD PENETRATION AND THE WHOLE DESIGN WAS VERY INADEQUATE FOR T	HE TYPE OF OPERATIONS THAT THIS GEAR ASSEMBLY MARKETED TO.				1	H	7	1 	3I	3	O	NT	EXPA1H71	EXPE3I
2004120600080	20041206	00080	SO  	2004	12	6	2004FA0000879    	1	20040809	G	8011	MZ6222	STARTER         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540J4A5   	41532	EA  					ENGINE	INTERMITTENT    	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	05	833WC	330  	330  			327640059	L319548			UPON ENGINE START UP, PILOT WENT TO ENGAGE STARTER, STARTER DID NOT ENGAGE.  INVESTIGATED STARTER AND FOUND STARTER BEND	IX WOULD NOT ENGAGE.  SUSPECT FAULTY BENDIX.					1	L	7	1 	3O	3	O	 	A3SO    	1E4
2004120600085	20041206	00085	EA  	2004	12	6	2004FA0000880    	2	20040802	G	8520	LW11033	CRANKCASE       			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					ENGINE	DAMAGED         	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			E	M	R	VIBRATION/BUFFET          	OVER TEMP                 	PARTIAL RPM/PWR LOSS      	CL	CLIMB          	1			NM	04	3542W		77   			32428	L1204540			WHILE CLIMBING OUT FROM RAWLINS, WY ON A FLIGHT TO HOLLISTER, CA., THE ENGINE STARTED TO RUN ROUGH AND THE PILOT NOTICED	 THAT THE OIL TEMPERATURE WAS RED LINED.  THE PILOT RETURNED TO THE AIRPORT FOR EMERGENCY LANDING UNDER PARTIAL ENGINE P	OWER.  THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  THE ENGINE WAS INSPECTED FOR THE ROUGH RUNNING AND IT WAS FOUND TH	AT THE CRANKCASE WAS DAMAGED BY THE CRANKSHAFT AT THE REAR OF THE FRONT THRUST BEARING AREA.			1	L	7	1 	3O	3	O	 	A3SO    	E295
2004120600105	20041206	00105	EA  	2004	12	6	2004FA0000881    	2	20040805	G	8550	29A21372	DRIVE ASSY      			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					SCAV PUMP	LEAKING         	B				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA		325PA	396  				3257237	L1096861A			PILOT REPORTED OIL LEAKING FROM ENGINE.  THE DRIVE ASSEMBLY FOR THE TURBO SCAVENGE PUMP WAS FOUND LEAKING.  THE PUMP WAS	 REMOVED FROM THE ENGINE, REPAIRED AND REINSTALLED.  NO LEAKS FOUND AFTER GROUND RUN.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA
2005020200042	20050202	00042	EA  	2005	2	2	2004FA0000882    	2	20040706	G	7414	BL68256013	MAGNETO         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	06	333TG	108  	108  			32R7680320	L2299648A			PILOT REPORTED OIL UNDER COWLING AFTER A WEEKEND OVERNIGHT.  INVESTIGATED OIL LEAK AND FOUND THE MAGNETO MOUNTING FLANGE	 CRACKED.  MAGNETO WAS PROPERLY TORQUED, SUSPECT MAGNETO HOUSING FATIGUED.					1	L	7	1 	3O	3	O		A3SO    	1E4
2005020200124	20050202	00124	SO  	2005	2	2	2004FA0000883    	1	20040820	G	8011	MZ6222	STARTER         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	INTERMITTENT    	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	06	833WC	6    	6    			327640059	L319548			UPON ENGINE START UP, PILOT WENT TO ENGAGE STARTER, STARTER DID NOT ENGAGE.  INVESTIGATED STARTER AND FOUND STARTER BEND	IX WOULD NOT ENGAGE.  SUSPECT FAULTY BENDIX.					1	L	7	1 	3O	3	O		A3SO    	1E4
2004120300043	20041203	00043	SO  	2004	12	3	2004FA0000884    	1	20041122	G	3230	1159SCL56613	TRUNNION PIN    			GULSTM	GV    	GV          	3980116	SO  										MLG	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23M	2281 				579				AIRCRAFT IN MAINTENANCE FOR THE SCHEDULED 5 YEAR LANDING GEAR CORROSION INSPECTION, FOUND AFT TRUNNION PINS AND THRU BOL	T NAS1962C56 SEVERELY CORRODED.  PARTS REPLACED WITH NEW.					2	L	7	2 	4F			RT	A12EA
2004120300044	20041203	00044	CE  	2004	12	3	2004FA0000885    	1	20041119	G	2722	1900741	SERVO           			BEECH 	200   	200BEECH    	1152920	CE  										RUDDER	BINDING         	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	11	773TP	1594 				BB1722				RIGHT RUDDER BOOST SYSTEM DID NOT TEST PROPERLY WHEN THE RIGHT ENGINE WAS BROUGHT UP TO POWER.  FOUND THE RIGHT RUDDER B	OOST SERVO BELLOWS WAS HANGING UP IN THE SERVO.  WOULD NOT RETRACT ALL THE WAY.  REPLACED THE SERVO AND SYSTEM OPERATED 	NORMALLY.				1	L	7	2 	4T			 	A24CE
2005020100093	20050201	00093	CE  	2005	2	1	2004FA0000887    	1	20040726	G	5730	390331204	SKIN            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RT WINGTIP	CRACKED         	B			CGHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	88ER	342  				RB17				THE RT WINGTIP HAS A CRACK APPROXIMATELY 7 INCHES LONG ON THE FAR OB END, AFT HALF OF THE WINGTIP.  THE CRACK RUNS FORE 	/ AFT ON THE WINGTIP.					1	7		2 	3F	4	F	RT	A00010WI	E3GL
2005020100127	20050201	00127	SO  	2005	2	1	2004FA0000888    	1	20040713	G	7603	A9200410	CABLE           			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360*       	41514	EA  					THROTTLE	WORN            	B			IG8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	929TE	333  				10208				SWEDGED-IN PORTION OF THE CABLE GUIDE DISPLAYED .110 INCH FORE AND AFT PLAY INDICATING IMPENDING FAILURE OF THE SWIVEL J	OINT.  CABLE WAS REMOVED AND GIVEN FOR EVALUATION.  THIS CONDITION WAS APPARENTLY CAUSED BY DIRT CONTAMINATION.  (THE PR	OTECTIVE RUBBER BOOT OVER THE SWIVEL JOINT HAD CRACKED, ALLOWING DIRT CONTAMINATION OF THE JOINT.)  THIS SUBMITTER RECOM	MENDS THAT THE THROTTLE CABLE SWIVEL JOINT AND ITS RUBBER BOOT BE CLOSELY INSPECTED AT EACH 100 HOUR AND/OR ANNUAL INSPE	CTION TO PREVENT EXCESSIVE WARE AND SUBSEQUENT FAILURE OF THE THROTTLE CABLE. (EA07NEL200405197)		1	L	7	1 	3O	3	O	NT	1L71    	E286
2005030800122	20050308	00122	EA  	2005	3	8	2004FA0000889    	2	20040909	G	7250	3053094	TURBINE         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	SHIFTED         	B			CGHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	40PT	258  				BB1291				NEW STYLE, PN SEGMENT INSTALLED AT HSI 258 HRS PRIOR.  THIS NEW STYLE SEGMENT SHIFTS AFT RESULTING IN HOT SECTION FAILUR	E.  VERY COMMON WITH THIS PN SEGMENT 3053094/ MFG NEEDS TO CHANGE DESIGN.					1	L	7	2 	4T	4	T		A24CE   	E4EA
2004122100021	20041221	00021	CE  	2004	12	21	2004FA0000890    	1	20041008	G	5610	10138402521	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	701FC	749  				FC291				THE AIRCRAFT WAS AT 33,000 FT WITH THE WINDSHIELD HEAT OFF, SPEED OF 290 KNOTS AND CABIN PRESSURIZED TO 6.5 PSI WHEN THE	 WINDSHIELD CRACKED.  THEY WERE ALSO IN CLEAR AIR, WITH NO TURBULENCE.  (GL21200500727)					2	L	7	2 	4T	3	T	 	A24CE   	E2NE
2004122100054	20041221	00054	GL  	2004	12	21	2004FA0000891    	1	20040824	G	2720	MS5184422	SLEEVE          			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  	LYC   	O235  	O235*       	41505	EA  					RUDDER CABLE	FAILED          	D			EIPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	49DW	1    				463				NICOPRESS SLEEVE (ZINC PLATED COPPER) WAS INSTALLED ON A .0625 INCH STAINLESS CABLE AND PULLED OUT UNDER FLIGHT LOADS.  	A TEST WAS MADE USING ANOTER SLEEVE AND THE CABLE ALSO PULLED OUT USING A PULL TEST.  A TEST WAS PERFORMED USING THE SAM	E CABLE AND A NICOPRESS (NON PLATED COPPER), THE PULL TEST WAS SATISFACTORY.				1	M	7	1 	3O	3	O	RT	EXPA1M71	E223
2004122100055	20041221	00055	EU  	2004	12	21	2004FA0000892    	1	20040820	G	3220	ES128545	TRUNNION        			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NLG	CRACKED         	B			IOQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	788FS	5649 				319				DURING A 1200 HOUR SCHEDULED INSPECTION, THE OUTER STRUT BODY OF THE NOSE LANDING GEAR UPPER TRUNNION WAS FOUND TO HAVE 	A CRACK IN THE OUTER BARREL STARTING FROM THE UPPER THREAD LOCK BORE EXTENDING DOWN 5.75 INCHES.					2	M	7	2 	4F	4	F	 	A2SW    	E6WE
2004122100083	20041221	00083	EA  	2004	12	21	2004FA0000893    	2	20041117	G	8550	ES48110	OIL FILTER      			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					ENGINE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	265TB	48   				T20608351				REMOVED THIS FILTER AND CUT OPEN TO INSPECT CONTENTS AS PAR OF A ROUTINE OIL CHANGE.   FOUND THE FILTER MEDIA HAD SEPARA	TED WHERE THE ENDS ARE CRIMPED TOGETHER.  FOUND THE GASKET BETWEEN THE INNER FILTER AND THE END PLATE IMPROPERLY INSTALL	ED.  THIS GASKET WAS TORN AND HANGING INTO THE FILTER PIC 2,3, AND 4.  HAVE CUT OPEN 3  OIL FILTERS THIS BRAND, ALL 3 HA	VE SHOWN THE SAME FAILURES.  HAVE SENT COPIES OF PICTURES TO MFG ENGINEERING DEPT.  NO IMMEDIATE DAMAGE TO THE ENGINE NO	TED.  THESE FAILURES ARE CAUSING UNFILTERED OIL TO CIRCULATE THROUGH THE ENGINE.		1	H	7	1 	3O	3	O	RT	A4CE    	E14EA
2004122900152	20041229	00152	SO  	2004	12	29	2004FA0000894    	1	20041125	G	5753	8290503	BELLCRANK       			PIPER 	PA46  	PA46350P    	7104602	SO  										TE FLAPS	CRACKED         	D				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			SW	99	DEZPA	1379 				4622184				BEFORE LANDING, PILOT SELECTED 10 DEGREES FLAPS & ACFT DRIFTED LT.  ABORTED LANDING, RAISED FLAPS & DID A GO AROUND THIN	KING, THAT ONE OF THE MLG HAD NOT COME DOWN.  AT THE 2ND ATTEMPT, HAD SAME PROBLEM & REALIZED THE PROBLEM WAS NOT THE ML	G, BUT THE FLAP SYS.  RT FLAP HAD NOT GONE DOWN, RAISED FLAPS AGAIN & LANDED WITHOUT FLAPS.  AFTER LDG, A FUNCTIONAL CHE	CK OF FLAPS, NO ABNORMALITIES.  AFTER INSP, RT FLAP INBOARD BELLCRANK FOUND CRACKED ABOUT 80% OF CIRCUMFERENCE.  OTHER B	ELLCRANKS OF BOTH FLAPS WERE VISUALLY INSP & NO PROBLEM FOUND. PILOTS STATES, THAT HE & OTHER PILOTS  HAVE NEVER LOWERED	 THE FLAPS AT SPEEDS HIGHER THAN THOSE SPECIFIED IN THE ACFT POH.   	1	L	7	1 	3O			RT	A25SO
2004122900163	20041229	00163	EA  	2004	12	29	2004FA0000895    	1	20041124	G	2710	C6CW10861	CONTROL ROD     			DHAV  	DHC6  	DHC6        	2802606	EA  										AILERON CONTROL	FAULTY          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	70465	173  	173  			554				DURING A VISUAL INSPECTION OF THE CONTROL ROD, IT WAS DISCOVERED THE ROD DID NOT HAVE A CRIMPED SLEEVE WHICH IT SHOULD.						1	H	7	2 	3T			RT	A9EA
2004122900165	20041229	00165	EA  	2004	12	29	2004FA0000896    	1	20041124	G	2710	C6CW10861	CONTROL ROD     			DHAV  	DHC6  	DHC6        	2802606	EA  										AILERON CONTROL	FAULTY          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	70465	173  	173  			554				DURING A VISUAL INSPECTION OF THE CONTROL ROD, IT WAS DISCOVERED THE ROD DID NOT HAVE A CRIMPED SLEEVE WHICH IT SHOULD.						1	H	7	2 	3T			RT	A9EA
2004122900188	20041229	00188	CE  	2004	12	29	2004FA0000897    	1	20041203	G	3222	968200183	RETAINER        			BEECH 	58    	58          	1152740	CE  										NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	440BL	4107 				TH801				DURING ANNUAL INSPECTION, FOUND UPPER NOSE GEAR STRUT HOUSING RETAINER CRACKED APPX 80% ACROSS.						1	L	7	2 	3O			 	3A16
2004123000014	20041230	00014	GL  	2004	12	30	2004FA0000898    	1	20041101	G	3220		FAIRING         			CIRRUS	SR    	SR22        	2130001	GL  										NLG	DEPARTED        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	1457C					0547				NOSE WHEEL FAIRING DEPARTED AIRPLANE ON CROSSWIND LANDING.  HAD SIGNIFICANT SHIMMY IN THE FRONT WHEEL UPON TOUCHDOWN.  D	ISCOVERED UPON REACHING RAMP AREA OF REAR PART OF FRONT WHEEL FAIRING.					1	L	7	1 	3O			NT	A00009CH
2004123000020	20041230	00020	NM  	2004	12	30	2004FA0000902    	1	20041119	G	5320	210056033	CHANNEL         			PIPER 	PA60  	PA60601     	7106010	NM  										ZONE 100	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	7529S	3410 				61016182				ON INSPECTION, FOUND PART CRACKED AT RIVET HOLES WHERE ATTACHED TO P/N 210056-031 CHANNEL.						1	M	7	2 	3O			RT	A17WE
2005012700052	20050127	00052	SO  	2005	1	27	2004FA0000904    	1	20041124	G	3710		SHAFT           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	LTIO540*    	41533	EA  					VACUUM PUMP	SHEARED         	B			FFKR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	06	333TG	202  	202  		C04616	32R7680320	L2299648A			AIRCRAFT WAS ON SHORT FINAL WHEN VACUUM PUMP FAILED.  AFTER INSPECTION AND REMOVAL OF THE VACUUM PUMP, THE SHEAR SHAFT H	AD SHEARED.					1	L	7	1 	3O	3	O		A3SO    	E14EA
2005012700053	20050127	00053	SO  	2005	1	27	2004FA0000905    	1	20041201	G	2910	HYC5005	POWERPACK       			PIPER 	PA32  	PA32R300    	7103213	SO  										HYD SYSTEM	BURNED          	D				O				OTHER                   				S	J		AFFECT SYSTEMS            	WARNING INDICATION        		LD	LANDING        	1			SO	05	898DS					32R7780358				OWNER REPORTED LANDING GEAR WOULD NOT EXTEND.  IMPLEMENTED EMERGENCY EXTENSION SUCCESSFULLY.  TROUBLESHOOTING REVEALED T	HE FOLLOWING: 1) THE HYDRAULIC POWER PACK MOTOR BRUSHES AND COMMUTATOR WERE WORN WELL BEYOND LIMITS. 2) THE VENT HOLE FO	R THE POWER PACK WAS BLOCKED BY A FACTORY INSTALLED WASHER (NOT REMOVED ON INSTALLATION) 3) THERE WERE INTERMITTENT CONT	ACTS BETWEEN SELECTOR HANDLE WIRING CAUSING THE GEAR MOTOR TO CYCLE INTERMITTENTLY AFTER POWER PACK REPLACEMENT.  REPLAC	ED THE POWER PACK ASSEMBLY, REPAIRED THE WIRING, AND REMOVED THE VENT HOLE COVER (ON THE NEW POWER PACK).  SYSTEM OPS CK	S PER MFG SPECS.	1	L	7	1 	3O				A3SO
2005012700054	20050127	00054	SO  	2005	1	27	2004FA0000906    	1	20041201	G	2910	HYC5005	POWERPACK       			PIPER 	PA32  	PA32R300    	7103213	SO  										HYD SYSTEM	BURNED          	D				O				OTHER                   				S	J		AFFECT SYSTEMS            	WARNING INDICATION        		LD	LANDING        	1			SO	05	898DS					32R7780358				OWNER REPORTED LANDING GEAR WOULD NOT EXTEND.  IMPLEMENTED EMERGENCY EXTENSION SUCCESSFULLY.  TROUBLESHOOTING REVEALED T	HE FOLLOWING: 1) THE HYDRAULIC POWER PACK MOTOR BRUSHES AND COMMUTATOR WERE WORN WELL BEYOND LIMITS. 2) THE VENT HOLE FO	R THE POWER PACK WAS BLOCKED BY A FACTORY INSTALLED WASHER (NOT REMOVED ON INSTALLATION) 3) THERE WERE INTERMITTENT CONT	ACTS BETWEEN SELECTOR HANDLE WIRING CAUSING THE GEAR MOTOR TO CYCLE INTERMITTENTLY AFTER POWER PACK REPLACEMENT.  REPLAC	ED THE POWER PACK ASSEMBLY, REPAIRED THE WIRING, AND REMOVED THE VENT HOLE COVER (ON THE NEW POWER PACK).  SYSTEM OPS CK	S PER MFG SPECS.	1	L	7	1 	3O				A3SO
2005020200070	20050202	00070	SO  	2005	2	2	2004FA0000907    	1	20041109	G	5610	1159SCB310012	WINDOW          			GULSTM	G1159 	GIV         	3980115	SO  										COCKPIT	OUT OF LIMITS   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	941AM	630  				1499				PILOT REPORT OF POSSIBLE PROBLEM WITH COPILOT SIDE WINDOW HEAT. TROUBLESHOOTING REVEALED BUSS TO BUSS RESISTANCE TOO HIG	H, CAUSE FOR WINDOW REPLACEMENT.  WINDOW VERY DIFFICULT TO REMOVE, EXTRAORDINARY MEASURES TAKEN, AS INCORRECT SEALANT WA	S APPLIED DURING MANUFACTURE.  SEALANT WAS NOT TYPE 1425 OR EQUIVALENT AS CALLED OUT IN MAINTENANCE MANUAL.				2	L	7	2 	4F			RT	A12EA
2005022400146	20050224	00146	EU  	2005	2	24	2004FA0000908    	1	20041014	G	3010	FAL1005D	HOSE            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					ANTI-ICE SYS	COLLAPSED       	B			PAZR	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			GL	03	87TH	427  				178				DURING ENGINE RUN-UP, PHYSICALLY CHECKED LEADING EDGE FOR HEAT AND FOUND COLD.  RT IB ANTI-ICE FLEXHOSE WAS REMOVED AND 	VISUALLY INSPECTED.  FOUND THE INNER LINING HAD COLLAPSED, BLOCKING AIRFLOW THROUGH HOSE.  HOSE WAS REPLACED WITH NEW.  	FAULTY HOSE WAS MARKED "3Q01".  THIS FLEXHOSE, P/N FAL1005D, IS REFERENCED IN DASSAULT SERVICE BULLETIN F10-A246.  THIS 	HOSE WAS LAST REPLACED ON 4/22/2003 AT 6213.2 HRS TTAF AND 5458 TOTAL LANDINGS BY CRS# BONR551C.			2	L	7	2 	4F	4	F		A33EU   	E6WE
2005020200100	20050202	00100	NE  	2005	2	2	2004FA0000909    	2	20041119	G	7230	9204M87P02	RETAINER        			DOUG  	DC10  	DC1030F     	3023504	WP  	GE    	CF6   	CF650C2     	30018	NE  					NR 3 ENGINE	MISLOCATED      	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99						46917	517228			DURING A ROUTINE "A-CHECK", FINNAIR FAA REPAIR STATION WAS REQUESTED TO PERFORM FAN BLADE LUBRICATION OF POSITION NR 3 E	NGINE ON DA-10,N303WL.  INSPECTION OF THE FAN BLADES REVEALED THAT ALL FAN BLADE SPACERS WERE IMPROPERLY INSTALLED.  THE	 SPACER RETAINER LIPS WERE HANGING LOOSE, TOWARD THE WEB AREA OF THE FAN DISK, INSTEAD OF UNDER THE SPACERS BENEATH EACH	 FAN BLADE.  IT WAS ALSO NOTED THAT THE STARTERS QUAD-RING WAS NOT SECURED BY A BOLT.  ATTACHMENTS TO ORIGINAL REPORT SE	NT TO FRANKFURT IFO WERE FORWARDED TO PMI FOR WORLD CARGO.		2	L	7	3 	4F	4	F	RT	A22WE   	E23EA
2005020200131	20050202	00131	GL  	2005	2	2	2004FA0000910    	1	20041107	G	5720	AA819	SCREW           			TCRAFT	BC    	BC12D       	8850316	GL  										WING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5031M	1550 				10331				WHILE REMOVING THE JURY STRUTS BEFORE REMOVING THE WINGS FOR RECOVER, WHEN THE BOLT HOLDING THE JURY STRUT TO THE ADJUST	ING SCREW AT THE FRONT SPAR WAS REMOVED THE ADJUSTING SCREW WAS IN TWO PIECES.  THE EAR THAT IS WELDED TO THE SCREW BROK	E JUST ABOVE THE WELD.  THE DESIGN OF THE ADJUSTING SCREW IS SUCH THAT THE THREADED PART POINTS STRAIGHT UP AND IS OPEN 	FOR MOISTURE AND/OR DIRT TO ACCUMULATE INSIDE THE SCREW.			1	H	7	1 	3O				A696
2005031000005	20050310	00005	EU  	2005	3	10	2004FA0000911    	1	20041125	G	2910	90G229	PRESSURE SWITCH 			AMD   	FALC50	FALCON50MYST	2730106	EU  										NR 1 HYD SYSTEM	LEAKING         	B				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	99	77NT	8871 	8871 			77				LOSS OF NR 1 HYDRAULICS.  INSPECTORS, FOUND HYDRAULIC NR 1 SYSTEM PRESSURE SWITCH LEAKING.  PRESSURE SWITCH, HYDRAULIC P	UMP NR 1 AND NR 2 REPLACED.					2	L	7	3 	4F				A46EU
2005030800057	20050308	00057	EU  	2005	3	8	2004FA0000912    	1	20041022	G	3244	M08401	TIRE            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					MLG	DEFORMED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	164GB	234  				164				THIS TIRE WAS MOUNTED ON THE RIGHT INBOARD SIDE (NR 3).  CUPPING WAS NOTICED ON THE INSIDE EDGE OF THE TIRE ALL THE WAY 	AROUND WITH CORD SHOWING.  TIRE WAS REPLACED.  CONTACTED FALCON TECH OPS.  THEY HAD NOT HEARD OF THIS ITEM AND ASKED ME 	TO CONTACT THE TIRE MANUFACTURE.  CONTACTED MICHELIN, CONFIRMED THE PROBLEM AND SAID THEY WERE WORKING ON IT.				2	L	7	3 	4F	4	F		A46EU   	E6WE
2005030800058	20050308	00058	EU  	2005	3	8	2004FA0000913    	1	20041022	G	3244	M08401	TIRE            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					MLG	DEFORMED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	164GB	234  				164				THIS TIRE WAS MOUNTED ON THE RIGHT INBOARD SIDE (NR 3).  CUPPING WAS NOTICED ON THE INSIDE EDGE OF THE TIRE ALL THE WAY 	AROUND WITH CORD SHOWING.  TIRE WAS REPLACED, CONTACTED FALCON TECH OPS. THEY HAD NOT HEARD OF THIS ITEM AND ASKED ME TO	 CONTACT THE TIRE MANUFACTURE, CONTACTED MICHELIN.  THEY CONFIRMED THE PROBLEM AND SAID THEY WERE WORKING ON IT.				2	L	7	3 	4F	4	F		A46EU   	E6WE
2005022200280	20050222	00280	SO  	2005	2	22	2004FA0000914    	2	20041022	G	8530	6399576	ROCKER          	CONT        		CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520D   	17032	SO  					NR 3 CYLINDER	BROKEN          	D				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	07	4068L		3    			4210068	1885208D			ANNUAL PRE-INSPECTION RUN-UP RAN GOOD.  POST INSPECTION RUN-UP RAN ROUGH.  SUSPECTED A STICKING VALVE.  FURTHER INVESTIG	ATION REVEALED A BROKEN EXHAUST ROCKER ARM AND STUCK VALVE FOR NR 3 CYLINDER ON THE LEFT ENGINE.  ALSO, NOTED IS AN APPA	RENT INCLUSION IN THE BROKEN ROCKER ARM.				1	L	7	2 	3O	3	O	RT	A7CE    	E7CE
2005030800053	20050308	00053	SO  	2005	3	8	2004FA0000915    	2	20041022	G	8530	6399576	EXHAUST ROCKER  			CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520D   	17032	SO  					NR 3 CYLINDER	BROKEN          	D				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			GL	07	4068L		3    			4210068	1885208D			ANNUAL PRE-INSPECTION RUN-UP RAN GOOD.  POST INSPECTION RUN-UP RAN ROUGH.  SUSPECTED A STICKING VALVE.  FURTHER INVESTIG	ATION REVEALED A BROKEN EXHAUST ROCKER ARM AND STUCK VALVE FOR NR 3 CYLINDER ON THE LEFT ENGINE.  ALSO, NOTED IS AN APPA	RENT INCLUSION IN THE BROKEN ROCKER ARM.				1	L	7	2 	3O	3	O	RT	A7CE    	E7CE
2005030800158	20050308	00158		2005	3	8	2004FA0000916    	2	20041209	G	7414	M3975	COIL            	SLICK       																MAGNETO	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27		600  	600  		96100581					MAGNETO IMPULSE COUPLING WEAR & IGNITION COIL FAILURE, FAILED IGNITION COIL: BROKEN HIGH-TENSION SECONDARY WINDINGS RESU	LTING IN MISFIRING OF THE SPARK PLUGS, INDUCING MX OF MAGNETO.  EXTREME WEAR AROUND MAGNET SHAFT OVER TAPERED PORTION BE	TWEEN IMPULSE CAM AND MAIN SHAFT COMPRISING OF A CONDITION WHERE THE HARDENED CAM ASSY HAS COME INTO ANGULAR INTERFERENC	E WITH THE (SOFTER) MAGNET SHAFT WHICH IT IS DESIGNED TO MOUNT AROUND. THE CONCENTRIC WEAR ON THE SHAFT INCLUDES A SHARP	 RAISED EDGE AT THE LARGEST OUTER DIAMETER OF THE MAGNET SHAFT TAPER. POSSIBLE CATASTROPHIC FAILURE OF THE MAGNETO MAY H	AVE RESULTED FROM THE SHAFT BREAKING AT THE EDGE NEAREST THE BASE OF THE DISPLACED MATERIAL.
2005030800059	20050308	00059	EU  	2005	3	8	2004FA0000917    	1	20041103	G	3244	M15101	TIRE            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					MLG	DEFORMED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	164GB	256  				164				THIS MICHELIN TIRE WAS MOUNTED ON THE LEFT INBOARD SIDE (NR 2).  CUPPING WAS NOTICED ON THE INSIDE EDGE OF THE TIRE ALL 	THE WAY AROUND.  TIRE WAS REPLACED, THEN CONTACTED FALCON TECH OPS.  THIS HAD HAPPENED ON ANOTHER TIRE BUT DIFFERENT PAR	T NUMBER (OMB NR 2120-0003).  THEY HAD NOT HEARD OF THIS ITEM AND ASKED ME TO CONTACT THE TIRE MANUFACTURE.  I THEN CONT	ACTED MICHELIN.  THEY CONFIRMED THE PROBLEM AND SAID THEY WERE WORKING ON IT.			2	L	7	3 	4F	4	F		A46EU   	E6WE
2005022200169	20050222	00169	NM  	2005	2	22	2004FA0000918    	1	20040728	G	5730		SKIN            			UNIVAR	415   	415CD       	0420304	NM  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9474					4851				INSPECTION OF WING CENTER SECTION PER AD 02-26-02 FOUND LIGHT CORROSION ON LOWER SKINS, MODERATE CORROSION ON 3 STIFFENE	RS.  REPLACED STIFFENERS, CLEANED AND TREATED SKIN.  AIRCRAFT WAS OUTSIDE WITHOUT COVER FOR AT LEAST 30 YEARS.					1	L	7	1 	3O				A718
2005022200170	20050222	00170	NM  	2005	2	22	2004FA0000919    	1	20040728	G	5730		SKIN            			UNIVAR	415   	415CD       	0420304	NM  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9474					4851				INSPECTION OF WING CENTER SECTION PER AD 02-26-02 FOUND LIGHT CORROSION ON LOWER SKINS, MODERATE CORROSION ON 3 STIFFENE	RS.  REPLACED STIFFENERS, CLEANED AND TREATED SKIN.  AIRCRAFT WAS OUTSIDE WITHOUT COVER FOR AT LEAST 30 YEARS.					1	L	7	1 	3O				A718
2004122900149	20041229	00149	NM  	2004	12	29	2004FA0000920    	1	20040728	G	5730		SKIN            			UNIVAR	415   	415CD       	0420304	NM  										WING CENTER SECT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9474					4851				INSPECTION OF WING CENTER SECTION PER AD 02-26-02 FOUND LIGHT CORROSION ON LOWER SKINS, MODERATE CORROSION ON 3 STIFFENE	RS.  REPLACED STIFFENERS, CLEANED AND TREATED SKIN.  AIRCRAFT WAS OUTSIDE WITHOUT COVER FOR AT LEAST 30 YEARS.					1	L	7	1 	3O			 	A718
2005030800063	20050308	00063	SO  	2005	3	8	2004FA0000922    	1	20041122	G	3211	1159SCL56613	TRUNNION PIN    			GULSTM	GV    	GV          	3980116	SO  										MLG	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	300K	2722 				587				AIRCRAFT IN MAINTENANCE FOR THE SCHEDULED 5 YEAR LANDING GEAR CORROSION INSPECTION.  FOUND AFT TRUNNION PINS AND THRU BO	LT PN: NAS1962C56 SEVERELY CORRODED.  PART REPLACED WITH NEW.					2	L	7	2 	4F			RT	A12EA
2004122200125	20041222	00125	WP  	2004	12	22	2004FA0000923    	1	20041214	G	6210	C0162	BLADE           			ROBSIN	R44   	R44         	7640120	WP  										MAIN ROTOR	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	667SA	775  				726				PREFLIGHT INSPECTION FOUND ONE OF THE BLADES APPEARED TO HAVE SKIN SEPARATION AT TRAILING EDGE TIP APPROX 1/4" LONG.  SE	NT DIGITAL PHOTO TO ROBINSON AND THEY REQUESTED BOTH BLADES BE SENT TO THEM FOR INSPECTION.  UPON INSPECTION AT FACTORY 	BOTH BLADES WERE SCRAPPED DUE TO CORROSION DELAMINATION.  SHIP HAS RECENTLY CHANGED OWNERS BUT PRIOR OWNER OPERATED SHIP	 IN FLORIDA.  SHIP WAS MANUFACTURED IN EARLY 2000 AND ONLY HAS 775 HOURS SINCE NEW.  ROBINSON DOES NOT CONSIDER THIS A D	EFECT BUT CLAIMS THE PROBLEM WAS THE CORROSIVE ENVIRONMENT IT WAS OPERATED IN.		1	G	7	1 	3O			 	H11NM
2005012400017	20050124	00017	WP  	2005	1	24	2004FA0000924    	1	20041116	G	6720	369H753113	TORQUE TUBE     			HUGHES	369   	369D        	4470706	WP  										T/R PEDAL	OUT OF LIMITS   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	CFMAL					611010D				FOUND AN AREA ON THE T/R PEDAL TORQUE TUBE THAT WAS DRESSED OUT WAY BEYOND LIMITS NEARLY HALF THE WALL THICKNESS AND THE	 AREA NOTED COULD NOT BE SEEN CLEARLY UNTILL IT WAS DISASSEMBLED.  REPLACED TUBE.					1	G	7	1 	3U				H3WE
2004122200054	20041222	00054		2004	12	22	2004FA0000925    	4	20041221	G	3417	962830A1S8	ADC             			DHAV  	DHC2  	DHC2*       	2800108	EA  										COCKPIT	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	47AK					726				DURING GROUND FUNTIONAL TEST OF THE INITIAL INSTALLATION OF AIR DATA COMPUTER (ADC) INSTALLED AS PART OF THE CHELTON FLI	GHT SYSTEMS EFIS-SV SYSTEM UNDER STC SA02203AK, ENCOUNTERED 100FT ALTITUDE DRIFT WITHIN 5 MINUTES AFTER BAROMETRIC PRESS	URE HAD BEEN SET.				1	H	7	1 	3R			 	A806
2005012400046	20050124	00046	WP  	2005	1	24	2004FA0000926    	1	20041116	G	6700	369H7131503	CYCLIC STICK    			HUGHES	369   	369D        	4470706	WP  										FLIGHT CONTROLS	LOOSE           	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	CFMAL					611010D				DURING ANNUAL INSPECTION IT WAS DISCOVERED THAT THE CYCLIC STICK HAD ABOUT HALF FORE AND AFT PLAY CAUSED BY A LOOSE FIT 	AT THE CYCLIC PIVOT POINT AT THE CYCLIC TORQUE TUBE.  WHEN IT WAS DISASSEMBLED IT WAS FOUND TO HAVE BEEN SHIMMED WITH CO	MPRESSOR SHIMS WHICH HAVE AN ID OF .3125 INCH AND THE BOLT IS .250 INCH THE SHIMS BEING TOO BIG, MORE THAN LIKELY, SHIFT	ED TO ONE SIDE OR THE OTHER OFF OF THE EDGE OF THE BEARING BUSHING AND GOT HAMMERED AND LOST TENSION THEN IT WAS A MATTE	R OF THE BEARINGS GOUGING INTO THE CASTING.		1	G	7	1 	3U				H3WE
2005020100005	20050201	00005	CE  	2005	2	1	2004FA0000927    	1	20041221	G	2720	51310103	BRACKET         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					ZONE 300	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	11	678DB	4794 	4794 			421B0876				COMPLIED WITH MFG MEB 00-4 RUDDER BEARING INSPECTION/REPLACEMENT.  FOUND RUDDER LOWER HINGE BEARING BRACKET INSTALLED UP	SIDE DOWN FROM FACTORY.  REPLACEMENT PROCEDURE DESCRIBED IN MEB FOUND ERRONEOUS AND INADEQUATE TO COMPLETE SATISFACTORY 	REPLACEMENT OF BRACKET.  MS 2047AD4-11 AND AD 5-11 RIVETS CALLED OUT IN MEB ARE OF THE INADEQUATE LENGTH.  THIS WILL REQ	UIRE -12 OR -13 LENGTH RIVETS. REPLACEMENT PN 5131010-3 IS NOT SAME SIZE AS ORIGINAL AND DOES NOT APPEAR TO HAVE ADEQUAT	E EDGE DISTANCE FROM RIVET HOLES AS WELL AS CAUSING BULGING OF VERTICAL STABILIZER SKINS BECAUSE IT IS SLIGHTLY TOO WIDE	.  A MAJOR RE-WRITE OF THIS MEB AND ITS COMPLIANCE INSTRUCTIONS IS NEEDED.	1	L	7	2 	3O	3	O		A7CE    	E7CE
2005020100006	20050201	00006	CE  	2005	2	1	2004FA0000928    	1	20041221	G	5313	1014400311	STRINGER        			BEECH 	200   	B200        	1152922	CE  										FUSELAGE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	200EW	5391 				BB1163				STRINGER NR 9 ON THE LT SIDE FOUND CRACKED DURING NON-RELATED MAINTENANCE.						1	L	7	2 	4T				A24CE
2005020100016	20050201	00016	GL  	2005	2	1	2004FA0000931    	1	20041216	G	3213		STRUT           			AMTR  	CH601 	ZODIAC      	       	GL  	ROTAX 	912   	ROTAX912S2  	 	EU  					LT MLG	BROKEN          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	09	601RT	318  	100  			63314				THE LT MAIN GEAR STRUT FAILED AT THE LOWER WELDMENT WHERE THE STRUT ATTACHES TO THE FORK. THIS DAMAGE HAD PROGRESSED ARO	UND THE ATTACHMENT IN THE FORM OF A CRACK UNTIL WEEKEND TO THE POINT OF FAILURE. THIS PART HAD BEEN FABRICATED BY THE KI	T MANUFACTURER.				1	L	7	1 	3O	3	O	NC	EXPA1L71	E00051EN
2005031000023	20050310	00023	CE  	2005	3	10	2004FA0000932    	1	20041213	G	5720	515610211	ANGLE           			CESSNA	421   	421C        	2076016	CE  										LEFT WING	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	717LR	2300 				421C1109				LEFT WING NACELLE, ANGLE JUST AFT OF FIREWALL EXHIBITED SEVERE CORROSION. CORROSION WAS TRANSFERED TO UPPER WING SKIN AN	D FUEL CELL.					1	L	7	2 	3O				A7CE
2005021500142	20050215	00142	SO  	2005	2	15	2004FA0000933    	1	20041127	G	5610	1159SCB31023	WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					COCKPIT	CRACKED         	B			N38R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	970SJ					1146				PILOTS WINDSHIELD CRACKED ENROUTE, CREW DIVERTED DUE TO THE FACT THAT MFG SERVICE CENTER THERE.  CREW FOLLOWED NORMAL LA	NDING PROCEDURES, AND LANDED AIRCRAFT UNEVENTFULLY.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE
2005031000033	20050310	00033	NM  	2005	3	10	2004FA0000934    	1	20041216	G	2810	900P3661120101	FUEL CELL       			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					FUSLEAGE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	11	902PD	1602 				9000084				DURING TROUBLESHOOTING A FUEL LEAK FOUND THAT WHEN THE FUEL CELL WAS FLEXED, FUEL WOULD WEEP FROM EXTERIOR SURFACE. REMO	VED FUEL CELL AND SENT OUT FOR TEST AND REPAIR. EVALUATION RESULTS SHOWED WEEPING/ POROUS CONDITION OVER 80 PERCENT OF T	HE CELL AND CELL TO BE BEYOND REPAIR. REPLACING CELL WITH SERVICEABLE UNIT. CELL DATE OF MANUFACTURE : 07/99, TOTAL TIME	 ON AIRCRAFT 1602.2			1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005020100091	20050201	00091	CE  	2005	2	1	2004FA0000935    	1	20041220	G	5730	10140453S	SKIN            			BEECH 	200   	B200        	1152922	CE  										LT WING	DELAMINATED     	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	200EW	5391 				BB1163				SKIN DELAMINATION ON LT WING CENTER SECTION UPPER SURFACE AFT OF THE SPAR NOTICED BY MAINTENANCE CREW, WHILE MAINTENANCE	 WAS BEING COMPLETED ON A NON-RELATED MATTER.					1	L	7	2 	4T				A24CE
2005031000041	20050310	00041	SO  	2005	3	10	2004FA0000936    	2	20041115	G	8520	649990	CRANKSHAFT      								CONT  	O550  	IO550C      	 	SO  					ENGINE	FRACTURED       	C				B				EMER. DESCENT           				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	23		2316 	469  				684556			CRANKSHAFT FRACTURED IN FLIGHT BETWEEN THE NR 1 AND 2 CONNECTING ROD JOURNALS.  AIRCRAFT MADE A SAFE LANDING.											3	O			E3SO
2005031000042	20050310	00042	SO  	2005	3	10	2004FA0000937    	2	20041115	G	8520	649990	CRANKSHAFT      								CONT  	O550  	IO550C      	 	SO  					ENGINE	FRACTURED       	C				B				EMER. DESCENT           				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	23		2316 	469  				684556			CRANKSHAFT FRACTURED IN FLIGHT BETWEEN THE NR 1 AND 2 CONNECTING ROD JOURNALS.  AIRCRAFT MADE A SAFE LANDING.											3	O			E3SO
2005031000029	20050310	00029	NM  	2005	3	10	2004FA0000938    	1	20041216	G	6220	900R2101006107	HUB             			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11		1852 	77   			9000085				DURING ACCOMPLISHMENT OF AD 2002-10-05 "MAIN ROTOR UPPER HUB INSP" FOUND BOLT HOLES CRACKED AS DEPICTED IN MD HELICOPTER	S SERVICE BULLETIN 900-072. PART TOTAL TIME: 1852 HRS					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005031000032	20050310	00032	NM  	2005	3	10	2004FA0000939    	1	20041216	G	6220	900R1103001113	BEAM            	DOUG        		DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					M/R HUB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	902PD	1602 	100  		0099990078	9000084				DURING 100 HOUR INSPECTION, FOUND FLEX BEAM CRACKED IN AREA OF LEG GOING INTO UPPER HUB. REPLACED PART WITH UPDATED SERV	ICEABLE PART.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005031000031	20050310	00031	NM  	2005	3	10	2004FA0000940    	1	20041216	G	6220	900R2101006107	HUB             			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	902PD	292  	100  			9000084				DURING ACCOMPLISHMENT OF A.D. 2002-10-05 " MAIN ROTOR UPPER HUB INSP." FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPIC	TED IN MD HELICOPTERS SERVICE BULLETIN 900-072. PART TOTAL TIME: 292 HRS					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005031000047	20050310	00047	CE  	2005	3	10	2004FA0000941    	1	20041221	G	5313	1014400339	STRINGER        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FUSELAGE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	200EW	5391 				BB1163				STRINGER NR 9 ON THE RT SIDE WAS FOUND CRACKED DURING NON-RELATED MAINTENANCE.						1	L	7	2 	4T	4	T		A24CE   	E4EA
2005021500088	20050215	00088		2005	2	15	2004FA0000942    	4	20040914	G	3417	962830A1S8	ADC             			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					COCKPIT	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	31589					327840135				UNIT REPORTING ERRONEOUS ALTITUDE READINGS UP TO 1000 FEET OFF.  (AL05200401238)						1	L	7	1 	3O	3	O		A3SO    	1E4
2005012100158	20050121	00158	EA  	2005	1	21	2004FA0000943    	1	20040729	G	2820	660526AS	TRANSDUCER      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL FLOW	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	95DG	100  				572				FUEL FLOW TRANSDUCER INOPERATIVE-NOT PROVIDING SIGNAL TO IDU.						1	H	7	1 	3R	3	R		A806    	5E1
2005031100079	20050311	00079	NE  	2005	3	11	2005FA0000000    	1	20041130	G	6320	643520048101	BEVEL GEAR      	SKRSKY      		SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					M/R GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC		2215 		A6125	64084				DURING NDT INSPECTION, GEAR WAS MPI`D AND REJECTED FOR CRACKS.  LOCATION OF CRACKS WERE IN ATTACHMENT FLANGE BOLT HOLES 	(18 EACH).  EVERY HOLE HAS APPROXIMATELY .1250 INCH LONG CRACK STARTING ON THE GEAR TO SHAFT ATTACHMENT SIDE EXTENDING D	OWN INTO THE HOLE.  UPON DISASSEMBLY, FRETTING WAS FOUND ON ATTACHMENT FLANGE OF GEAR.  FRETTING BETWEEN GEAR AND SHAFT 	TYPICALLY CAUSES THIS DEFECT.  THIS MGB ASSEMBLY WAS O/H SEVERAL YEARS AGO AND DID NOT INCORPORATE THE REVISED TORQUE PR	OCEDURE CURRENTLY USED.  A REVISED TORQUE PROCEDURE WITH ENSURING A DRY FIT AT ASSEMBLY HAS REDUCED FRETTING THUS PREVEN	TS CRACKING. (NM09200504351) (K)	2	G	7	2 	4U	4	U		H6EA    	E15EA
2005031100030	20050311	00030	NE  	2005	3	11	2005FA0000001    	1	20041130	G	7160	575219	DUCT            			SKRSKY	S64   	CH54B       	8142610	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE	WRONG PART      	B			JYDR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	158AC		651  			64081				DURING TEARDOWN OF F/T ASSEMBLY, A BROKEN EPR PROBE WAS FOUND AND THE INLET DUCT WAS SITTING LOW WHICH WOULD ALLOW MORE 	AXIAL TRAVEL OF INLET DUCT DURING OPERATION.  AFTER REMOVING INLET DUCT, FOUND THE OVERALL HEIGHT OF INLET DUCT TO BE SH	ORT.  THIS CAUSED WEAR IN THE AFT FLANGE OF THE INLET DUCT AND PUT EXTRA LOAD ON PROBES.  THIS INLET DUCT WAS PURCHASED 	AS A SERVICEABLE PART.  HEIGHT IS NOT REQUIRED TO TAKE THIS DIMENSION AT OVERHAUL.  IT IS CHECKED WHEN INLET DUCT HAS AN	 AFT FLANGE REPAIR AND FORWARD SNAP REPAIR BY SUPPLIER.  SUPPLIERS REPAIR RESTORES TO BLUE PRINT HEIGHT OF 7.270 INCH -	7.310 INCH.  THE HEIGHT OF THIS INLET DUCT IS 7.250 INCH.  CHECK OVERALL HEIGHT OF INLET DUCT.  (MDR04-068) (K)	2	G	7	2 	4U	4	U		H6EA    	E15EA
2005021500171	20050215	00171	NE  	2005	2	15	2005FA0000002    	1	20041206	G	6210	151520604000	SPAR            			SKRSKY	S64   	S64E        	8142604	NE  										M/R BLADE	CRACKED         	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CGESG	5301 			64M48515147	64065				BLADE WAS RECEIVED WITH AN UNSERVICEABLE BIM INDICATION.  DURING LEAK CHECK, A CHORDWISE CRACK, APPROX .5 INCH LONG WITH	 A CORROSION PIT IN THE CENTER, WAS FOUND.  THE CRACK IS LOCATED APPROX 70.75 INCH FROM TIP END AND 3.25 INCH FROM L/E. 	 CORROSION PIT A CENTER OF CRACK.  PREVENT CORROSION PITTING. (K)				2	G	7	2 	4U				H4EA
2005030800220	20050308	00220	SO  	2005	3	8	2005FA0000003    	1	20041209	G	5200		DOOR FRAME      			GULSTM	G1159 	G1159B      	3953535	SO  										DOOR	CRACKED         	B			N38R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	211SJ					75				DURING AIRCRAFT 4000 LANDING INSPECTION, FOUND APPROX A 1 INCH CRACK AT THE UPPER FORWARD RADIUS OF DOOR FRAME.  STOP DR	ILLED CRACK AND REPAIRED WITH AN OVERLAY DOUBLER IAW THE SRM.  OVERLAY INSTALLED (WET) WITH PRC 1440. (K)					2	L	7	2 	4F			RT	A12EA
2005032800072	20050328	00072	EA  	2005	3	28	2005FA0000004    	2	20041119	G	7200		INVERTER        			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A27      	52043	EA  					RT ENGINE	MALFUNCTIONED   	B			TIMR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			NM	07	326CA					U135				ON CLIMB OUT, RT ENGINE TORQUE DROPPED TO 500.  AC RETURNED, WHERE THE TORQUE SYSTEM WAS JET CAL, GAUGES SWAPPED SIDE TO	 SIDE AND ALL SYSTEMS WORKED AS REQUIRED.  MAINTENANCE SUSPECTS AN ELECTRICAL SPIKE FROM THE NR 1 INVERTER.  THE GAUGES 	STUCK ON 500 BUT DROPPED TO ZERO WHEN INVERTER NR 2 SELECTED.  INVERTER NR 1 AND NR 2 INSPECTED, CONNECTOR PLUG, INSPECT	ED THE WIRES, NOTHING WAS FOUND AND MAINTENANCE CANNOT DUPLICATE THE PROBLEM.  SWITCH OF INVERTERS PRODUCED NO PROBLEMS 	WITH TORQUE SYSTEM.  (K)		1	L	7	2 	3T	4	T		A14CE   	E4EA
2005030800239	20050308	00239	CE  	2005	3	8	2005FA0000005    	1	20041116	G	5210		CABLE           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A27      	52043	EA  					PAX DOOR	BROKEN          	B			TIMR	C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			CL	CLIMB          	1			NM	07	153GA					UB34	PCE41706			ON CLIMBOUT THE AIRSTAIR DOOR OPENED.  AC RETURNED, WHEN  AIRSTAIR DOOR OPENED IN FLIGHT, DOOR DAMPER BROKE AND SUPPORT 	CHAINS BROKE.  CHAIN HIT PROPELLER AND CAUSED NOTICEABLE DAMAGE.  DOOR ANNUNCIATOR LIGHT WAS NOT ILLUMINATED SO NO INDIC	ATION OF ANY PROBLEM WAS EVIDENT.  CAUSE FOR DOOR FAILURE WAS DOOR CABLE WHICH TURNS LOCKING CAMS BROKE WHEN DOOR WAS CL	OSED.  PILOT NEGLECTED TO CHECK CAM MARKS FOR ALIGNMENT WITH GUN SIGHTS LOCATED ON DOOR FRAME.  GROUND PERSONNEL DID NOT	 REALIZE THE DOOR INSIDE CAM CABLE BROKE, AS A RESULT, HANDLE IS STOWED, DOOR PIN POPS OUT INDICATING DOOR IS CLOSED.  B	OTH SWITCHES ON THE DOOR FOR THE ANNUNCIATOR MAKE A CLOSED CIRCUIT CAUSING THE LIGHT TO GO OUT.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2005042100006	20050421	00006	EA  	2005	4	21	2005FA0000006    	2	20041228	G	7200	31019912	BLADE           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT ENGINE	BROKEN          	B			TIMR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	153GA					UB34				AIRCRAFT DEPARTED, AT CRUISE, THE LT ENGINE HAD AN EXPLOSIVE NOISE AND THE LEFT ENGINE SEIZED.  PRE INSPECTION OF ENGINE	 INDICATES LOSS OF CT BLADE. (K)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2005020100100	20050201	00100	EU  	2005	2	1	2005FA0000010    	1	20041207	G	7810	FIOA5SCP2013	CLAMP           			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					TAIL PIPE	CRACKED         	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	224EA	6992 				257088	P77269			THE DEFECT IS A FATIGUE CRACK, CAUSED BY BEING OVERSTRESSED DUE TO LOAD LIMITS, POSSIBLE OVERTORQUED.  MAYBE THIS PART S	HOULD BE MADE STRONGER,  TO HANDLE THE STRESS.  THIS DEFECT WAS FOUND BY A PENETRANT INSPECTION.  THE LOCKING NUT NEEDS 	TO BE REMOVED, IN THIS CASE THE DEFECT WOULD NOT HAVE BEEN NOTICED IF THE LOCKING NUT HAD NOT BEEN REMOVED. (CE092005019	13) (K)			2	L	7	2 	4F	4	F		A3EU    	E6WE
2005021500087	20050215	00087	SO  	2005	2	15	2005FA0000011    	1	20041206	G	7120	8621202	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	VO360*      	41514	EA  					RT ENGINE	CRACKED         	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	2234B	2864 				447995107				ON COMPLETEING MAINTENANCE ON RT ENGINE, IT WAS NOTICED THAT THE ENGINE MOUNT WAS CRACKED AT A WELD JOINT ABOUT 6 INCHES	 BELOW THE RT UPPER ISOLATION MOUNT.  THE CRACK HAS FOLLOWED THE WELD LAP AND OUT INTO THE TUBE FOR ABOUT TWO THIRDS THE	 WAY AROUND THE TUBE.				1	L	7	2 	3O	3	O		A19S0   	1E1
2005033000064	20050330	00064	CE  	2005	3	30	2005FA0000012    	1	20041206	G	6120	1013890293	GOVERNOR        			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	OVERSPEED	MALFUNCTIONED   	B			LX5R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			GL	19	981LL	2435 				FL265	PCEPK0267	FWA2851		DURING NORMAL GROUND RUN-UP.  THE AIRCRAFT PROPELLER AUTO-FEATHER SYSTEM WAS OPERATIONALLY CHECKED.  BOTH LT AND TR PROP	ELLER SWITCHES WERE SELECTED AND BOTH PROPELLERS FEATHERED CORRECTLY.  WHEN THE SWITCHES WERE RELEASED THE LT PROPELLER 	DID NOT COME OUT OF THE FEATHERED POSITION BUT THE RT PROPELLER WORKED CORRECTLY.  A SERVICEABLE OVERSPEED GOVERNOR WAS 	INSTALLED IN THE LT POSITION.  OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.  UNKNOWN WHAT CAUSED	 THE COMPONENT TO FAIL POSSIBLE INTERNAL SWITCH OR SERVO FAILURE, COMPONENT SENT FOR OVERHAUL/ REPAIR.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2005033000065	20050330	00065	CE  	2005	3	30	2005FA0000013    	1	20041209	G	3230	583800901	MOTOR           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	1564A	68   				CE1321	830028R			DURING FLIGHT OF AIRCRAFT, PILOT REPORTED GEAR WOULD NOT RETRACT.  MAINTENANCE TECHNICIAN FOUND LANDING GEAR MOTOR WAS I	NTERMITTENT AND SLOW TO RETRACT.  NO RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O		3A15    	E5CE
2005030100044	20050301	00044	SO  	2005	3	1	2005FA0000015    	1	20041120	G	3233	762365	ROD END         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					LT MLG ACTUATOR	BENT            	C				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	03	62688					277654144				DURING ROLL-OUT AFTER LANDING, THE LT MAIN GEAR COLLAPSED, INVESTIGATION WHILE THE AIRCRAFT WAS ON JACKS.  REVEALED THAT	 THE ACTUATOR ROD END WAS BENT. (NE03200504405) (K)					1	L	7	2 	3O	3	O		1A10    	E14EA
2005033000066	20050330	00066	EU  	2005	3	30	2005FA0000016    	1	20041227	G	5754		FITTING         			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					SLAT	DAMAGED         	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	56LT				133000	21				FOLLOWING DAMAGE WAS FOUND WHILE LT IB SLAT (PN F50B133B8, SN 133000 WAS AT THIS FACILITY FOR REPAIR.  MILLED FITTING, (	PN F50B133014) IS ATTACH POINT FOR NR 4 (OB) RAIL.   SIX FASTENERS WERE IMPROPERLY INSTALLED THROUGH INNER SKIN OF SLAT.	  FOUR BLIND FASTENERS WERE LOCATED THROUGH INNER SKIN INTO EDGE OF  MILLED FITTING.  ONE SOLID FASTENER WAS THROUGH INN	ER SKIN AND FLUSHED ON OUTER SKIN, THIS WAS ALSO DRILLED THROUGH EDGE OF MILLED FITTING. , WHICH CAUSED OUTER SKIN TO BE	 DISTORTED.  ONE SOLID FASTENER WAS COUNTERSUNK ON OUTER SKIN THROUGH THE INNER SKIN.  MISDRILLED FASTENERS WERE FOUND D	URING PRELIMINARY INSPECTION.  DAMAGE TO THE MILLED FITTING WAS FOUND DURING THE TEAR DOWN PHASE OF REPAIR WORK.	2	L	7	3 	4F	4	F		A46EU   	E6WE
2005032800083	20050328	00083	SO  	2005	3	28	2005FA0000017    	1	20041105	G	3230	7642603	DRAG BRACE      			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	BROKEN          	B			TUDR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	13	1128Q	3172 				28R7737027				PILOT REPORTED A LOUD, SHARP (POP) SOUND WHILE IN FLIGHT.  PRIOR TO LANDING HE LOWERED THE LANDING GEAR AND MADE A NORMA	L LANDING.  THE NOSE GEAR UPPER DRAG BRACE WAS BROKEN JUST FORWARD OF THE AREA WHERE THE LANDING GEAR ACTUATOR ATTACHES 	TO THE BRACE.  THERE DID NOT APPEAR TO BE ANY OTHER DAMAGE IN THE AREA.  A POSSIBLE CAUSE OF FAILURE IS FATIGUE DUE TO T	HE NR OF HOURS OR CYCLES ON THE PART.  (SW13200501658)			1	L	7	1 	3O	3	O		2A13    	1E10
2005020100175	20050201	00175	GL  	2005	2	1	2005FA0000018    	1	20041111	G	7921	654585	OIL COOLER      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE OIL	CRACKED         	B			LC1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	1527C	474  				0564				THIS AIRCRAFT HAS HAD AN OIL COOLER REPLACED FOR THE SAME DEFECT AT <300 HOURS.  THE NEW OIL COOLER IS CRACKED AGAIN AT 	THE LOWER LT FLANGE AREA.  NOTE:  MFG HAS A SIX POINT ENGINE MOUNT OPTION AVAILABLE TO REDUCE VIBRATION IN THE AIRCRAFT.	  THIS AIRCRAFT HAD SUBSTANTIAL VIBRATION AND HAS HAD THAT MOUNT INSTALLED AT THE FIRST OIL COOLER REPLACEMENT AND THE O	WNER REPORTS A NOTICEABLE DIFFERENCE IN VIBRATION LEVELS.  THIS MAY HAVE CONTRIBUTED TO THE ORIGINAL CRACKING BUT NOT SO	 MUCH THE 2ND OCCURRENCE.  THIS HAS BEEN AREA FLAGGED BY MFG DURING A RECENT SERVICE CENTER MEETING AND IS POSTED ON THE	 SC WEB SITE.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2005031000064	20050310	00064	SO  	2005	3	10	2005FA0000021    	2	20041224	G	7414	BL68256013	MAGNETO         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  	HARTZL	HCC2Y	CHCC2YK1    	GL  	ENGINE	CRACKED         	B			FFKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	333TG	336  	336  			32R7680320	L2299648A	CH34693B		WHEN PERFORMING A VISUAL INSPECTION OF THE ENGINE COMPARTMENT EXCESSIVE OIL WAS FOUND IN THE ENGINE COMPARTMENT.  FOUND 	THE DUEL MAGNETO MOUNTING FLANGE CRACKED.  REMOVED MAGNETO, CRACKED MOUNTING FLANGE PIECE FELL OFF OF MAGNETO HOUSING.					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
2005031000057	20050310	00057	CE  	2005	3	10	2005FA0000022    	1	20041228	G	7111		COWL FLAP       			CESSNA	337   	T337C       	2075714	CE  											INOPERATIVE     	G				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NE	03	2663S					3370963				THE OWNER INSTALLED STC SA01091AT. THIS STC REMOVES THE ELECTRIC COWL FLAP MOTOR, AND INSTALLED A COMPLETELY MECHANICAL 	SYSTEM.   THE OWNER COMPLAINED THAT HE COULD NOT THE CLOSE REAR COWL FLAP IN FLIGHT. 					1	H	7	2 	3O				A6CE
2005020100008	20050201	00008	CE  	2005	2	1	2005FA0000031    	1	20041012	G	3230		CABLE           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT MLG	BROKEN          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	494CW					RK4				DURING SCHEDULED INSPECTION FOUND LT MAIN GEAR UPLOCK EMERGENCY EXTENSION CABLE BROKEN NEAR OB END.  REPLACED CABLE WITH	 NEW PN128-380021-55 CABLE ASSEMBLY AND RIGGED IAW BE 400/400A, MM 32-30-00.  ORIGINAL PN, PART TT NOT SUPPLIED, POSSIBL	Y ORIGINAL.  ASSEMBLY PN FOR THIS SN RANGE AIRCRAFT HAS BEEN SUPERSEDED TWICE IAW CURRENT BE 400/400A IPC.  APPEARS TO H	AVE FAILED FROM AGE/TIME IN SERVICE.  RECOMMEND ESTABLISHING A LIFE-LIMIT ON THIS CABLE ALSO, OR ISSUE A SB REQUIRING IM	PROVED PN CABLE INSTALLATION.  TTAF: 5397.4 HRS.		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA
2005021500076	20050215	00076		2005	2	15	2005FA0000032    	4	20041201	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360B1E    	41514	EA  	MCAULY	1A170	1A170E      	GL  	SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	35253					172S8831				DURING 100 HRS INSPECTION, FOUND FWD BULKHEAD OF THE SPINNER CRACKED 4 PLACES AROUND PROPELLER BOLT HOLES.  RECOMMENDATI	ON:  BULKHEAD MATERIAL STRONGER OR THICKER.  (WP07200507539)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2005020100002	20050201	00002	CE  	2005	2	1	2005FA0000033    	1	20041105	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BREAKER	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	5530A					CE1342				PILOT SELECTED GEAR DOWN AND NOTHING HAPPENED, SELECTED GEAR DOWN AGAIN AND GEAR CAME DOWN.  ON FURTHER TROUBLESHOOTING 	FOUND RELAY WAS INTERMITTNET, PROBABLE CAUSE AT THIS TIME UNKNOWN, THIS IS SUPPOSE TO BE AN IMPROVED RELAY SO THERE IS N	O RECOMMENDATIONS AT THIS TIME.				1	L	7	1 	3O	3	O		3A15    	E5CE
2005021500093	20050215	00093	CE  	2005	2	15	2005FA0000034    	1	20041019	G	2750	SM50D7	RELAY           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					TE FLAPS	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	19	7232R	69   				BL69				WHILE THE AIRCRAFT WAS IN FLIGHT, THE FLAPS FAILED TO EXTEND TO THE SELELCTED APPROACH POSITION.  THE PILOT CYCLED THE F	LAP SELECT SWITCH TO UP AD BACK TO APPROACH AND THE FLAPS EXTENDED.  MAINTENANCE INVESTIGATED THE REPORTED PROBLEM AND W	AS ABLE TO DUPLICATE THE PROBLEM ON THE GROUND.  WHEN THE FLAPS WERE SELECTED TO APPROACH THE FLAPS MOVED APPROXIMATELY 	5 DEGREES AND QUIT MOVING.  AFTER ACCESS WAS GAINED TO THE FLAP MOTOR/GEARBOX AND RELAY, A TAP ON THE RELAY RETURNED THE	 FLAPS TO NORMAL SELECTOR SWITCH RESPONSE OPERATION.  INSTALLATION OF A REPLACEMENT RELAY SOLVED THE PROBLEM.  THE (FAIL	ED ) RELAY HAD 69.0 HOURS. (WP19200503541)	1	L	7	2 	4T	4	T		A24CE   	E4EA
2005021500100	20050215	00100		2005	2	15	2005FA0000035    	4	20041216	G	2561	GA12P0201	LIFE VEST       																	CABIN	FAILED          	B			KO1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25										INDIVIDUAL FLOAT DEVICE FAILED CELL PRESSURE TEST DUE TO INFLATION VALVE RUPTURE.  DOM: NOV 1981.
2005030200040	20050302	00040	GL  	2005	3	2	2005FA0000036    	3	20041216	G	6111	C3260	PITCH ROD       													MCAULY	2AF34C	D2AF34C305  	GL  	YOKE	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								900205		MULTIPLE CRACKS WERE FOUND DURING MAGNAFLUX INSPECTION.  BOTTOM AND TOP OF PITCH CHANGE YOKE.  EXCESSIVE STRESS MIGHT HA	VE BEEN THE CAUSE OF FAILURE.															5	C	P5EA
2005021500104	20050215	00104	CE  	2005	2	15	2005FA0000038    	1	20041102	G	1430	NAS	BOLT            			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					MLG ATTACH	IMPROPER PART   	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	76ML					44674				DURING ANNUAL INSPECTION, IT WAS FOUND THAT ONE OF THE NAS BOLTS HOLDING THE IB END OF THE LANDING GEAR WAS TOO SHORT AN	D DID NOT GO ALL THE WAY THROUGH THE NAS NUT.  THESE BOLTS WERE INSTALLED AT THE FACTORY, DURING A REPAIR IN 2001.  FAIL	URE WOULD RESULT IN ONE LANDING GEAR LEG COLLAPSING.  (EA17200504802)				1	H	7	1 	3O	3	O		A759    	1E12
2005033000067	20050330	00067	SO  	2005	3	30	2005FA0000039    	1	20041207	G	7120	79584008	MOUNT           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	BROKEN          	B			N9VR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	03	7063C	3552 				287625068				FOLLOW A LANDING, THE FORWARD AND AFT MOUNTING THAT SECURE THE ALTERNATOR TO THE AIR CONDITIONER MOUNT BROKE, ALLOWING T	HE ALTERNATOR TO SLIP, STRIKING AND DAMAGING THE LOWER NOSE BOWL.					1	L	7	1 	3O	3	O		2A13    	E274
2005033000068	20050330	00068	SW  	2005	3	30	2005FA0000040    	1	20041218	G	2612	1734361600F	FIRE DETECTOR   			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					RT ENGINE	FAILED          	B			OZ5R	A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			NM	05	158MC					AC726B				RT ENGINE FIRE WARNING LIGHT FLICKERED ON AND OFF DURING CLIMB.  CREW RETURNED TO STATION.  FAILED FIRE DETECTOR PROBE (	CENTER CERAMIC INSULATOR LOOSE).  REPLACED FIRE DETECTOR LOCATED BELOW THE OIL COOLER MOUNTED ON THE FIREWALL. (NM052004	00110)  (K)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005020100066	20050201	00066	SW  	2005	2	1	2005FA0000041    	1	20041231	G	2150	20475546	ACM             			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					RIGHT	SEIZED          	B			OZ5R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			NM	05	430MA		2959 			AC710B				ON TOUCHDOWN, THE CREW NOTICED AN ACRID SMELL IN THE COCKPIT.  THE CREW LANDED AND TAXIED IN WITH NO FURTHER INCIDENT.  	TROUBLESHOOTING FOUND THE SOURCE TO THE RT ACM.  INITALLY DEFERRED ACM IAW MEL, LATER CHANGED THE ACM,  MEL WAS CLEARED.	  (NM05200403534) (K)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000069	20050330	00069	SW  	2005	3	30	2005FA0000042    	1	20040303	G	3260	MS246614	SQUAT SWITCH    			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					MLG	DAMAGED         	B			OZ5R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	05	159MC					AC726B				LANDING GEAR WOULD NOT RETRACT DURING CLIMBOUT, WHEN CREW WAS RETURNING FOR LANDING, GPWS GAVE (TO LOW GEAR) ALERT.  THE	 CREW THEN INITIATED A GO-AROUND, ASKED TOWER TO CONFIRM, THREE GEAR DOWN, DID CONFIRM.  CREW DECLARED EMERGENCY, MADE N	ORMAL LANDING, DURING TAXI, DISCOVERED NOSE WHEEL STEERING WAS INOPERATIVE.  MAINTENANCE TO VERIFY DISCREPANCY, GEAR RET	RACTED CORRECTLY.  FURTHER TROUBLESHOOTING COULD NOT GET GEAR TO FAIL TO OPERATE WHILE ON JACKS.  REPLACED LT OB MAIN GE	AR SQUAT SWITCH, DUE TO SUSPECTED WATER INGRESSION, CHANGED LANDING GEAR CONTROL HANDLE AND LT LANDING GEAR CONTROL CIRC	UIT BREAKER, PRECAUTIONARY ACTION.  AC WAS RELEASED AND OPS CHECK FLIGHT WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005031100073	20050311	00073	SW  	2005	3	11	2005FA0000043    	1	20040304	G	5270		WARNING SYSTEM  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					CARGO DOOR	MALFUNCTIONED   	B			OZ5R	O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			NM	05	430MA					AC710B				CARGO DOOR WARNING LIGHT CAME ON IN FLIGHT DURING THE START OF THE DESCENT TO THE NEXT STATION.  ATC WAS NOTIFIED.  THE 	LIGHTS STAYED ON FOR APPROXIMATELY 10 MINUTES.  DOOR CLOSING PROCEDURES, DOOR HARD TO CLOSE, DOOR CLICK CLACK RIGGING/LU	BRICATION, OR SWITCH RIGGING.  ALL CLICK CLACKS AND MICRO SWITCHES.  NO DEFECTS NOTED.  AN OPERATIONAL CHECK FLIGHT WAS 	COMPLETED WITH NO DISCREPANCIES.  AIRCRAFT WAS RETURNED TO SERVICE. (K)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005031100074	20050311	00074	SW  	2005	3	11	2005FA0000044    	1	20040307	G	6120	8690671	BLOCK           			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					BETA SYS	LEAKING         	B			OZ5R	A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			NM	05	850LS					DC850B				AFTER TURNING BLEEDS ON DURING CLIMB, CREW IMMEDIATELY NOTICED AN ODOR AND THEN SAW SMOKE.  BLEEDS WERE TURNED OFF, CHEC	KLIST ITEMS COMPLETED.  CHECKED FOR ANNUNCIATOR LIGHTS, PRESSURE INDICATIONS, AND FIRE LIGHT INDICATIONS, ALL WERE NORMA	L.  CREW RETURNED TO STATION AND LANDED WITH NO FURTHER INCIDENT.  INITALLY SUSPECTED ACM FAILURE, BUT FOUND OIL LEAKING	 IN THE LT ENGINE SPINNER/ COWL AREA.  TIGHTEN FITTING, SAFETIED AND PERFORMED GROUND RUN LEAK CHECK, OPS CHECK GOOD.  P	ERFORMED OPERATIONAL CHECK FLIGHT, OPS CHECK GOOD. (K)		2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
2005033000070	20050330	00070	SW  	2005	3	30	2005FA0000045    	1	20040320	G	5230		DOOR            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					CARGO CLICKCLACK	MALFUNCTIONED   	B			OZ5R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	854LS					DC854B				THE CARGO DOOR WARNING LIGHT CAME ON DURING CLIMBOUT, CREW RETURNED TO THE STATION.  ONE OF THE FOLLOWING:  DOOR CLOSING	 PROCEDURES, DOOR HARD TO CLOSE, DOOR CLICK CLACK RIGGING/ LUBRICATION, OR SWITCH RIGGING.  ALL SWITCHES AND CLICK CLACK	S WERE INSPECTED AND LUBRICATED, NO DEFECTS WERE NOTED.  AIRCRAFT GROUND PRESSURIZATION RUN WAS PERFORMED, OPS CHECKED G	OOD.  (NM05200403789) (K)			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
2005033000071	20050330	00071	SW  	2005	3	30	2005FA0000046    	1	20040322	G	5230	27240050027	DOOR            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					CARGO	OUT OF ALIGNMENT	B			OZ5R	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			NM	05	159MC					AC728B				CARGO DOOR WARNING LIGHT CAME ON AS POWER WAS BEING APPLIED FOR TAKEOFF, CREW DISCONTINUED TAKEOFF ROLL AND RETURNED TO 	GATE.  ONE OF THE FOLLOWING: DOOR CLOSING PROCEDURES, DOOR HARD TO CLOSE, DOOR CLICKCLACK RIGGING/ LUBRICATION, OR SWITC	H RIGGING.  CLICK CLACKS, BAYONET PINS, MICROSWITCHES WERE CLEANED AND LUBED.  DOOR OPS CHECK GOOD, FLIGHT CONTINUED WIT	H NO FURTHER DOOR PROBLEMS.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000072	20050330	00072	SW  	2005	3	30	2005FA0000047    	1	20040407	G	2435	23079010	STARTER GEN     			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					RIGHT	FAILED          	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			NM	05	453LA					DC852B				ON DESCENT RT GENERATOR FAILED, CREW TRIED TO RESET GEN, AS CREW WAS FOLLOWING PROCEDURES TO DETERMINE SOURCE OF MALFUNC	TION, LT GEN TRIPPED OFFLINE, POSSIBLY DUE TO LOAD.  LT GEN WAS RESET AND STAYED ON LINE BRIEFLY, THEN TRIPPED OFFLINE A	GAIN.  CREW WAS IN VFR CONDITIONS WITH AIRPORT IN SIGHT, LANDED WITHOUT INCIDENT.  SUSPECTED GEN PARALLELING CIRCUIT PRO	BLEM, GCU OR STARTER GEN PROBLEM.  AFTER EXTENSIVE TROUBLESHOOTING, DETERMINED THAT GENERATOR FUNCTION OF RT STARTER GEN	ERATOR HAD FAILED.  IT IS SUSPECTED THAT THER IS AN INTERNAL PROBLEM WITH STATOR WINDINGS.  BRUSHES AND COMMUTER WERE IN	SPECTED AND FOUND IN GOOD SERVICEABLE CONDITION.  START GEN TEARDOWN EVALUATION HAS BEEN REQUESTED.	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
2005021500136	20050215	00136	SW  	2005	2	15	2005FA0000048    	1	20040503	G	5230		HANDLE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					CARGO DOOR	INCORRECT       	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	05	159MC					AC728B				THE CARGO DOOR WARNING LIGHT CAME ON DURING CLIMBOUT, CREW RETURNED TO STATION.  ONE OF THE FOLLOWING:  DOOR CLOSING PRO	CEDURES, DOOR HARD TO CLOSE, DOOR CLICKCLACK RIGGING/ LUBRICATION, OR SWITCH RIGGING.  MAINTENANCE FOUND HANDLE NOT FULL	Y ROTATED TO CLOSED POSITION, CHECKED DOOR AND CLICKCLACKS, RECLOSED THE DOOR AND STOWED THE HANDLE, NO FURTHER PORBLEMS	 NOTED.  CREW CONTINUED FLIGHT WITH NO FURTHER INCIDENTS. (NM05200404459) (K)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005021500079	20050215	00079		2005	2	15	2005FA0000051    	4	20041226	G	3421	5040030911	INDICATOR       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ATTITUDE	MALFUNCTIONED   	B			OZ5R	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NM	05	60NE					760B				NOTE: WRITTEN UP BY CREW AS DG PRECESSING.  VERIFIED WITH MAINTENANCE THAT THE ATTITUDE INDICATOR WAS PRECESSING.  BAD A	TTITUDE INDICATOR.  REMOVED AND REPLACED FO ATTITUDE INDICATOR.  NO OTHER DEFECTS NOTED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005021500153	20050215	00153	SW  	2005	2	15	2005FA0000052    	1	20040515	G	2100	22008681	VANE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					CABIN AIR	FAILED          	B			OZ5R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			NM	05	60NE					AC760B				MRR-M04-10,  AIRCRAFT FILLED WITH SMOKE DURING LANDING.  CREW TAXIED IN WITH NO FURTHER INCIDENT.  SUSPECT ACM COOLING T	URBINE FAILURE.  INITIALLY DEFERRED THE NR 1 ACM, DURING TROUBLESHOOTING, FOUND THE DESWIRL VANE CENTER SUPPORT STRUTS H	AD ALL FAILED.  REPLACED ACM ASSEMBLY, DUE TO FAILURE OF THE INLET AIR DESWIRL VANE SUPPORT STRUTS.  THE CENTER CONE HAD	 SHIFTED DUE TO THE BROKEN SUPPORT STRUTS.  THIS CAUSED DECREASED AIRFLOW, LEADING TO HIGHER TEMPERATURES, CAUSING SMOKE	 IN THE CABIN.  THIS PART IS A LOW FAILURE ITEM.  THE NEW PART USED TO REPLACE IS A PMA PART THAT IS ALUMINUM, NOT THE C	OMPOSITE COMPOSITION OF THE OLD PART. (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005021500169	20050215	00169	WP  	2005	2	15	2005FA0000053    	2	20040602	G	7310	31024692	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					MANIFOLD	LEAKING         	B			OZ5R	C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			NM	05	159MC					AC728B				MRR-M04-11, ENGINE RPM ONLY WENT TO 97 PERCENT DURING TAKEOFF ROLL AND TORQUE WAS ALSO LOW, ALSO, THERE WAS LITTLE RESPO	NSE TO POWER LEVER MOVEMENT.  CREW ABORTED TAKEOFF AND RETURNED TO THE GATE.  INITIALLY SUSPECTED FCU FAILURE, BUT UPON 	INSPECTION FOUND FCU INPUT ARM ROD END DISCONNECTED.  RECONNECTED ROD END AND SAFETIED.  A FUEL LEAK WAS NOTED WHEN COWL	ING WAS OPENED, AND WAS FOUND TO BE COMING FROM THE SECONDARY FUEL MANIFOLD LOCATED AT THE 8:00 OCLOCK POSITION.  THE F	UEL MANIFOLD LINE WAS REPLACED.  MR`S WERE ISSUED TO INSPECT ALL OTHER AIRCRAFT FUEL MANIFOLD LINES, FUEL NOZZLE TASK CA	RD WAS ISSUED TO INCLUDE INSPECTION OF THE MANIFOLD LINES AT EACH INSPECTION.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000073	20050330	00073	SW  	2005	3	30	2005FA0000054    	1	20040811	G	5230	2724052005	SEAL            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					CARGO DOOR	PINCHED         	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	05	853LS					DC853B				MRR-M04-12, CARGO DOOR WARNING LIGHT ON ANNUNCIATOR AND SECONDARY DOOR UNSAFE WARNING ON SIDE PANEL BOTH CAME ON DURING 	CLIMBOUT.  CREW FOLLOWED PROCEDURES, RETURNED.  CREW CHECKED CARGO DOOR HANDLE, FOUND FULLY STOWED UPON RETURN.  RIGGING	 OR ADJUSTMENT OF DOOR. FOUND DOOR SEAL SHIMMED TO TIGHTLY AT DOOR LWR EDGE OPENING, CAUSING DOOR TO BE HARD TO CLOSE.  	SEAL WAS SHIMMED THIS TIGHTLY IN PART DUE TO SEAL NOT INFLATING TO FULL PRESSURE, DUE TO INFLATION LINE NOT BEING FULLY 	ALIGNED WITH FEED THROUGH FOR IT IN THE DOOR FRAME.  DOOR SEAL WAS REPLACED, MAINTAINING ALIGNMENT OF SEAL.  DOOR SEAL S	WITCHES WERE ADJUSTED.  CARGO DOOR WARNING SYS AND LATCH SYS WAS OPS CHECKED AND OPERATED CORRECTLY.	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
2005033000074	20050330	00074	SW  	2005	3	30	2005FA0000055    	1	20041010	G	3230	246006	SELECTOR VALVE  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					MLG	FAILED          	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			NM	05	27465	613  				AC755B				MRR-M04-14, THE LANDING GEAR FAILED TO EXTEND USING NORMAL OR ALTERNATE BUSS, CREW FOLLOWED EMERGENCY CHECKLIST AND EXTE	NDED GEAR USING MANUAL GEAR EXTENSION SYSTEM.  THE CREW LANDED WITH NO FURTHER INCIDENT.  FAILED HYDRAULIC LANDING GEAR 	SELECTOR VALVE.  INITIALLY REPOSITIONED AIRCRAFT UNDER A SPECIAL FERRY PERMIT TO MAINTENANCE BASE, THEN CHANGED THE GEAR	 SELECTOR VALVE.  GEAR OPS CHECKED GOOD. (NM0520050916) (K)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000075	20050330	00075	SW  	2005	3	30	2005FA0000056    	1	20041014	G	2910		LINE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					HYDRAULIC SYS	FAILED          	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	1119K					DC830B				MRR-M04-15, BOTH HYDRAULIC PRESSURE LOW LIGHTS CAME ON INFLIGHT.  CREW CHECKED GAGE AND FOUND HYDRAULIC PRESSURE AT (0).	  HYDRAULIC FLUID LOSS DO TO SYSTEM LEAK.  REPLACED LINE IN LEFT WHEEL WELL.  LEAK CHECKED ALL SYSTEM LINES AFTER REPAIR	, NO ADDITIONAL LEAKS NOTED. (NM05200502367) (K)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
2005033000076	20050330	00076	SW  	2005	3	30	2005FA0000057    	1	20041114	G	2910	27810321857	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYDRAULIC SYS	PIN HOLE        	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	27465					AC755B				MRR-M04-16, DURING CRUISE, CREW NOTED LOSS OF HYDRAULIC PRESSURE, ENROUTE TO NEXT STATION.  HYDRAULIC LINE LEAK.  REPLAC	ED HYDRAULIC GEAR UP LINE LOCATED UNDER THE FLOORBOARDS IN THE CABIN ON LT SIDE OF THE AIRCRAFT. (NM05200502368) (K)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000077	20050330	00077	SW  	2005	3	30	2005FA0000058    	1	20041123	G	2910		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYDRAULIC SYS	LEAKING         	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	05	27465					AC755B				MRR-M04-17, DURING CLIMBOUT, CREW NOTED LOSS OF HYDRAULIC PRESSURE ENROUTE TO NEXT STATION.  HYDRAULIC LINE LEAK.  REPLA	CED NOSE GEAR UP HYDRAULIC LINE, LEAK CHECK AND OPS CHECK GOOD.  (NM05200502369) (K)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005031100047	20050311	00047	SW  	2005	3	11	2005FA0000059    	1	20041203	G	2621	3030020	FIRE BOTTLE     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  						EMPTY           	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	3114G					AC583				MRR-M04-18, DURING FLIGHT THE LT FIRE EXTINGUISHER (E) LIGHT CAME ON BRIEFLY SEVERAL TIMES.  THE CREW MONITORED THE LIGH	T AND THE FLIGHT WAS CONTINUED TO THE DESTINATION WITH NO INCIDENT.  FIRE EXTINGUISHER (E) LIGHT WAS FOUND ON, AND THE F	IRE EXTINGUISHER BOTTLE WAS FOUND EMPTY DURING TROUBLESHOOTING BY MAINTENANCE.  THE SQUIB HAD BEEN FIRED.  REPLACED FIRE	 EXTINGUISHER BOTTLE AND SQUIB HAD BEEN FIRED.  REPLACED FIRE EXTINGUISHER BOTTLE AND SQUIB.  FIRE BOTTLE PN: 3030020, S	N 05782B1 OH 7-14-04, INSTALLED 7-19-04.  NO DEFECTS WERE NOTED DURING TROUBLESHOOTING OR PARTS CHANGES.  PRESS TO TEST 	FUNCTION AND ALL OTHER FUNCTION CHECKS WERE GOOD.  (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000078	20050330	00078	SW  	2005	3	30	2005FA0000060    	1	20041205	G	2120		SMOKE           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					COCKPIT	DETECTED        	B			OZ5R	B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	05	3114G					AC583				MRR-M04-19, CREW NOTICED SMOKE IN COCKPIT AS THEY WERE CLIMBING THROUGH 12,000 FT, DESCENDED TO 10,000 FT, DEPRESSURIZED	, TURNED OFF BLEEDS, AND CONTINUED TO STATION UNPRESSURIZED.  SUSPECTED ACM FAILURE OR BLEED HEAT CNTRL VALVE FAILURE.  	RAN BOTH ENG FOR 20 MIN, NO SMOKE NOTICABLE IN CABIN.  INSPECTED LT AND TR TEMP CNTRL VALVES, WITH NO DEFECTS NOTED.  IN	SPECTED LT AND RT ACMS, WITH NO DEFECTS NOTED.  SERVICED BOTH ACMS AND REMOVED, CLEANED, REINSTALLED WATER SOCKS.  RAN E	NG SECOND TIME WITH NO DEFECTS NOTED.  COULD NOT DUPL ORIGINAL WRITE-UP.   WATER SEPARATOR ICED UP, AND WHEN IT WARMED U	P, STEAM CAME THROUGH, MIMICING SMOKE.  (NM05200502386) (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000079	20050330	00079	SW  	2005	3	30	2005FA0000061    	1	20041219	G	2910		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYDRAULIC SYS	CRACKED         	B			OZ5R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	27465					AC755B				MRR-M04-20, DURING CRUISE, CREW NOTED LOSS OF HYDRAULIC PRESSURE ENROUTE TO NEXT STATION.  THEY DIVERTED TO AN AIRPORT W	ITH BETTER RUNWAYS FOR LANDING FLAPS UP AND WITH NO NOSE WHEEL STEERING.  CREW MANUALLY EXTENDED THE GEAR, THE LANDED FL	APS UP AND WITHOUT NOSE WHEEL STEERING.  CREW LANDED WITH NO FURTHER INCIDENT.  HYDRAULIC LINE LEAK.  REPLACED HYDRAULIC	 GEAR UP LINE IN THE COCKPIT, LEAK CHECK AND OPS CHECK GOOD.  CRACK OR EROSION IN THE BEND RADIUS SEEMS TO ORIGINATE AT 	TOOLING MARKS IN THE OUTSIDE OF THE CURVE.  THIS IS A MFG (FACTORY) MADE LINE.  LINE WAS REPLACED, BOTH HYD PUMPS AND FI	LTER WERE REPLACED DUE TO BEING RUN MORE THAN 20 MIN W/O HYDRAULIC FLUID.  SYSTEM OPS CHECKED GOOD. (NM05200502387) (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005031100038	20050311	00038	SW  	2005	3	11	2005FA0000062    	1	20041222	G	5230		HANDLE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					CARGO DOOR	OUT OF RIG      	B			OZ5R	B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	60NE					AC760B				CARGO DOOR WARNING LIGHT CAME ON IN FLIGHT, CREW DESCENDED AND DEPRESSURIZED, AND THE LIGHT WENT OUT.  CREW LANDED AT CL	OSEST AIRPORT.  FOUND CARGO DOOR HANDLE NOT COMPLETELY STOWED WHEN CHECK AT ARRIVAL.  INSPECTED CARGO DOOR AND LATCHES, 	CLEANED AND LUBED SWITCHES.  DOOR OPS CHECK GOOD.  NO FURTHER PROBLEMS NOTED WITH THE DOOR. (NM05200502388) (K)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005031100043	20050311	00043	SW  	2005	3	11	2005FA0000063    	1	20041225	G	3233	2752010003	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					NLG	FAILED          	B			OZ5R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	05	27465	57   				755B				RED GEAR NOSE UNSAFE LIGHT CAME ON IN FLIGHT.  LANDED, CHECKED NOSE GEAR WELL NOTICED RT GEAR ACTUATOR BROKE.  FORWARD E	ND OF ACTUATOR BROKE OFF.  AIRCRAFT BROUGHT BACK, BROKEN ACTUATOR REMOVED AND BRACE MFG  AND INSTALLED IAW SFP.  UPON RE	TURN, NLG STRUT AND WHEEL WELL WERE INSPECTED FOR DAMAGE WITH NO DEFECTS NOTED.  AN OVERHAULED ACTUATOR WAS INSTALLED, R	IGGED, AND A LEAK AND OPERATION CHECKS WERE PERFORMED WITH NO OTHER DEFECTS NOTED. (K)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005031100039	20050311	00039	WP  	2005	3	11	2005FA0000064    	2	20041206	G	7261	31080261	SCAVENGE PUMP   			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					NR 2 ENGINE	FAILED          	B			OZ5R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	430MA					AC710B				MRR-M04-23, NR 2 ENGINE OIL PRESSURE LIGHT CAME ON AS FLIGHT LEVELED OUT IN CRUISE, OIL PRESSURE GAUGE WAS CHECKED AND F	OUND PRESSURE DROPPING.  CREW DID A PRECAUTIONARY INFLIGHT SHUTDOWN, AND RETURNED TO STATION.  LOSS OF OIL PRESSURE DUE 	TO LOSS OF OIL FRM REAR SCAVANGE PUMP AREA.  REMOVED ENGINE, REPLACED SCAVANGE PUMP AND REINSTALLED ENGINE.  MFG HAS CHA	NGED PUMP DESIGN TO DECREASE REAR SCAVANGE PUMP FAILURES. (K)			2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
2005032800094	20050328	00094	CE  	2005	3	28	2005FA0000068    	1	20041202	G	5312		BULKHEAD        			CESSNA	206   	P206        	2073304	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2527X					P2060027				WHILE PERFORMING INSPECTION PORTION OF AD PERTAINING TO  THE AFT VERTICAL FIN ATTACHMENT BULKHEAD, ONE CRACK WAS FOUND I	N EACH OF LOWER IB PORTIONS OF THE RUDDER CABLE CUTOUTS AT APPROXIMATELY THE 4 O`CLOCK POSITION ON THE LT CUTOUT AND THE	 8 O`CLOCK POSITION ON THE RT CUTOUT.  CRACKS WERE EACH APPROX .2500 INCH LONG, ORIGINATING AT THE EDGE OF THE CUTOUT AN	D TRAVELING IN A DIRECTION PERPENDICULAR TO GANGENT OF RADIUS OF CUTOUT AT POINT OF ORIGIN.  ALL OTHER AREAS OF INSP PRE	SCRIBED BY AD WERE FOUND TO BE WITHIN LIMITS AND NO OTHER DISCREPANCIES WERE FOUND.  NO OBVIOUS REASON FOR CRACKS IN THI	S LOCATION UNLESS POINTS OF CONCENTRATED STRESS CAUSED BY RUDDER DEFLECTION.  (SO09200502375) (SO09200502381) (K)	1	H	7	1 	3O	3	O		A4CE    	E5CE
2005021500125	20050215	00125	NE  	2005	2	15	2005FA0000069    	2	20040913	G	7320	660526AS	TRANSDUCER      			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL FLOW	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	1018A	551  				178				REMOVED FUEL FLOW TRANSDUCER (PN 660526AS) INSTALLED UNDER STC NR SA809GL.  UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS 	AND CAUSING THE AIR DATA COMPUTER (ADC) ALSO INSTALLED IN THE AIRCRAFT TO FUNCTION IMPROPERLY.  AIR DATA COMPUTER INSTAL	LED UNDER IAW STC NR SA02203AK.				1	H	7	1 	3R	3	R		A806    	5E1
2005021500137	20050215	00137	NE  	2005	2	15	2005FA0000070    	2	20040913	G	7320	660526AS	TRANSDUCER      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL FLOW	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	67673	651  				1284				REMOVED FUEL FLOW TRANSDUCER (PN 660526AS) INSTALLED UNDER STC SA809GL.  UNIT PROVIDING ERRONEOUS FULE FLOW READINGS AND	 CAUSING THE AIR DATA COMPUTER (ADC) ALSO INSTALLED IN THE AC TO FUNCTION IMPROPERLY.  AIR DATA COMPUTER INSTALLED IAW S	TC SA02203AK. (K)				1	H	7	1 	3R	3	R		A806    	5E1
2005021500135	20050215	00135		2005	2	15	2005FA0000072    	4	20040715	G	2320	9903333142	AUDIO CONTROL   			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					COCKPIT	INOPERATIVE     	B			GJQR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			NM	01	39WP					294				FLIGHT CREW REPORTED ACRID SMELL IN THE COCKPIT ON APPROACH TO LANDING.  NR 2 VHF COMM NOT FUNCTION REPORTED BY FLIGHTCR	EW.  INSPECTION DID CONFIRM NR 2 COMM TRANSCEIVER WAS INOPERATIVE.  REMOVED AND REPLACED WITH SERVICEABLE UNIT.  ADDITIO	NAL TROUBLESHOOTING AND INSPECTION TO AIRFRAME AND AVIONICS RELATED COMPONENTS DID REVEAL THE AUDIO CONTROL PANEL (PN990	-3333-142) NR 2 VHF COMM TRANSCEIVER.  AUDIO CONTROL PANEL RETURNED FOR INSPECTION, REPAIR AND RETURNED TO SERVICE.  (NM	01200501124) (K)		2	L	7	3 	4F	4	F		A46EU   	E1NM
2005033000122	20050330	00122	GL  	2005	3	30	2005FA0000081    	3	20040901	G	6111	84334	BLADE           													HARTZL	HCA2V	HCA2VF2     	GL  	PROPELLER	CRACKED         	B			NWOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05								Y2155		PROPELLER BLADE CRACKED .33 OF DIAMETER AT RETENTION GROVE. (K)																5	C	P24EA
2005033000123	20050330	00123		2005	3	30	2005FA0000082    	1	20040722	G	1430	SL12596	BOLT            																	CONNECTING ROD	MISMANUFACTURED 	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03										THE CONNECTING ROD BOLT, PN SL12596, LOT NR 575765, WAS FOUND TOO SHORT FOR PROPER INSTALLATION.  THE FREE LENGTH OF THE	 BOLTS IN QUESTION WERE 2.2485 TO 2.2491.  MFG SL1458B REQUIRES A TWO STEP TORQUE PROCESS.  FIRST, TORQUE BOLTS TO 35 FT	 LBS AND MEASURE, IF THE BOLT IS SHORTER THAN 2.255, THE BOLT IS REJECTED.  SECOND, THE BOLT MUST NOT EXCEED LENGTH OF 2	.256 AT THE FINAL TORQUE OF 55 FT LBS.  THE SUSPECT BOLTS WOULD NOT ATTAIN REQUIRED LENGTH AT 35 FT LBS.  THE DEFECT IS 	CAUSED BY GRINDING THE BOLT TOO SHORT OF A DIMENSION AT MFG.  AN INSPECTION RATE WOULD NEED TO BE INREASED TO A LEVEL TH	AT WOULD ENSURE PROPER QUALITY CONTROL. (K)
2005030100043	20050301	00043	CE  	2005	3	1	2005FA0000085    	1	20041214	G	2820	151613621	FUEL LINE       			CESSNA	337   	P337H       	2075731	CE  	CONT  	O470  	TSIO470*    	17026	SO  					FUEL SYSTEM	SPLIT           	D				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			NE	05	991	1006 				P3370350				AIRCRAFT DEPARTED BGR, TEMPERATURE THE PREVIOUS RIGHT AND DAY WERE CLOSE TO FREEZING.  AIRCRAFT RETURNED WITH FUEL SMELL	 IN COCKPIT.  INVESTIGATION FOUND LT FUEL CROSSFEED LINE HAD SPLIT.  UPON REMOVAL OF LINE, PRESENCE OF WATER WAS FOUND. 	 PROBABLE CAUSE WAS WATER FROZEN IN LINE.  THERE ARE NO PROVISIONS OR PROCEDURES TO DRAIN THIS OR THE RT CROSSFEED LINES	.  (NE05200503189) (K)			1	H	7	2 	3O	3	O		A6CE    	3E3
2005030100023	20050301	00023	CE  	2005	3	1	2005FA0000086    	1	20041217	G	2721		PIN             			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					COCKPIT	OUT OF ADJUST   	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	72KF	32   				18281361				TRANSIT CUSTOMER HAD RUDDER TRIM STICK IN FULL RT TRIM CONDITION AND COULD NOT TRIM LT.  FOUND THAT IF TRIMMED TOO FAR T	O RT.  THE INDICATOR PIN WOULD JUMP OUT OF TRIM WHEEL TRACK AND COULD LOCK TRIM WHEEL.  WE READJUSTED INDICATOR PIN AND 	CENTERED CONTROLS.  THIS IS THE 2ND INCIDENT. (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4
2005030100053	20050301	00053	GL  	2005	3	1	2005FA0000087    	1	20040430	G	2497	VM1000DPU	WIRE            			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360A1D     	41514	EA  					ELECTRICAL SYS	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	36HY	117  				2154				DURING TROUBLESHOOTING OF WIRES IN VM1000 SYSTEM, WIRE J4-13, VOLTAGE SENSE, CAME LOOSE AND SHORTED TO GROUND.  THIS WIR	E IS CONNECTED DIRECTLY TO BUS WITH NO CIRCUIT PROTECTION.  LATER MODEL AIRCRAFT DO INCORPORATE CIRCUIT PROTECTION IAW M	FG.  RECOMMEND EARLIER AIRCRAFT BE RETRO-FITTED WITH NEW DESIGN.  WIRE IS HELD IN WITH SCREW CLAMP TYPE TERMINAL.  IF TH	IS HAD COME LOOSE IN FLIGHT AND IN-FLIGHT FIRE COULD HAVE OCCURRED. (K)			1	H	7	1 	3O	3	O	NC	A22NM   	E286
2005033000126	20050330	00126	EU  	2005	3	30	2005FA0000088    	1	20041209	G	2450		HOLDER          			BRAERO	1000  	BAE1251000A 	1500104	EU  	PWA   	305   	PW305       	 	NE  					ELECTRICAL FUSE	DESTROYED       	B			R14R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	533QS					259033				AIRCRAFT WAS SQUAWKED WITH NR 1 ALTERNATOR DROPPING OFF IN FLIGHT.  DURING TROUBLESHOOTING THE TECHNICIAN FOUND SMOKE TR	AILS ON THE GG PANEL.  LOCATED ON THE AFT SIDE OF THE REAR FACE OF THE PRESSURE BULKHEAD.  A MORE CLOSE INSPECTION REVEA	LED A DESTROYED FUSE HOLDER WITH ACCOMPANING WIRE DAMAGE, GCU AND LINE CONTACTOR DAMAGE, AND A HOLE BURNED THROUGH THE G	G PANEL ITSELF AT THE FUSE HOLDER LOCATION.  THE DAMAGE WAS CENTERED UNDER THE LEFT SIDE OF THE FUSE BLOCK WHICH HAD DES	INTERGRATED.  IT WAS UNDETERMINED AS TO WHICH COMPONENT INITIATED THE DAMAGE.  (EA17200504804)		2	L	7	2 	4F	4	F	RT	A3EU    	E35NE
2005030100046	20050301	00046	CE  	2005	3	1	2005FA0000089    	1	20041202	G	2421		ARMATURE        			BEECH 	95    	95          	1153402	CE  	LYC   	O360  	O360A4A     	41514	EA  					GENERATOR	FAILED          	D				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			NM	01	21JC				10887	TD224	L1071836AC			THE GENERATOR WAS JUST O/H, WITHOUT DISASSEMBLING THE GENERATOR, LOOKING IN TO PULLEY SIDE, YOU COULD SEE THAT THE ARMAT	URE HAD PARTIALLY UNWOUND.  TO THE POINT WHERE ONE ARMATURE WIRE WAS RUBBING LARGE AMOUNTS OF FIELD COVERING OFF.  THIS 	CAUSED THE ARMATURE WIRE TO BREAK.  THIS FIELD COVERING FOD CIRCULATED THROUGH THE COMMUTATOR/BRUSHES TO DISINTEGRATE.  	THINK THEY ARENT WINDING THE ARMATURES TIGHT ENOUGH. (NM01199419959) (K)			1	L	7	2 	3O	3	O		3A16    	E286
2005030100033	20050301	00033	EA  	2005	3	1	2005FA0000090    	2	20041106	G	7322	MA3A105199	CARBURETOR      			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	CONTAMINATED    	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	15	2534N					3879A0903	L1913615	4333		ENGINE QUIT DURING FLIGHT DUE TO CARBURETOR MALFUNCTION 4 MILES SOUTHEAST OF AIRPORT, MAKING AN EMERGENCY LANDING WITHOU	T DAMAGE TO AIRCRAFT, PILOT OR PASSENGER.  CARBURETOR WAS REMOVED FROM AIRCRAFT AND SENT FOR OVERHAUL.  (WO NR 88013).  	AIRCRAFT HAD BEEN SETTING FOR A LONG PERIOD OF TIME, WITH FUEL TANKS HALF FULL, MAKING MOISTURE IN THE FUEL SYSTEM.  REC	OMMENDATION FOR OWNERS, DRAIN FUEL SYSTEM AND RUN THE ENGINE AT LEAST ONCE A WEEK FOR AIRCRAFT TIE DOWN OUTSIDE OF HANGA	R.  (SO15200509104) (K)		1	L	7	1 	3O	3	O		A18SO   	E223	5	N	P9045
2005030100056	20050301	00056		2005	3	1	2005FA0000091    	4	20041114	G	2300		SMOKE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					COCKPIT	DETECTED        	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	05	75776					17267942				PILOT REPORTED SMOKE IN THE COCKPIT.  INVESTIGATION FOUND THE (AUDIO AMP) CIRCUIT BREAKER POPPED.  COULD NOT FIND THE DI	RECT CAUSE.  HOWEVER, THE RADIOS ARE ORIGINAL EQUIPMENT, WHICH MAY HAVE CAUSED THE SMOKE IN THE COCKPIT.  (SO05200504849	)				1	H	7	1 	3O	3	O	NT	3A12    	E274
2005032800095	20050328	00095	SO  	2005	3	28	2005FA0000092    	2	20041117	G	8530	655783	INTAKE VALVE    			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NR 4 CYLINDER	BROKEN          	B			VA1R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	19	111KJ	492  				421C1230				INTAKE VALVE IN NR 4 CYLINDER FAILED IN FLIGHT.  THE VALVE FACE BROKE IN 3 PIECES.  THE QUILL SHAFT BROKE AND SHUTDOWN T	HE ENGINE.  THIS IS 3RD ONE SEEN WITH  400-500 HOURS IN SERVICE. (K)					1	L	7	2 	3O	3	O		A7CE    	E7CE
2005030100050	20050301	00050	SO  	2005	3	1	2005FA0000094    	2	20041127	G	7322	NA53A1	CARBURETOR      			AMTR  	STCROX	PIETENPOLAIR	7040363	GL  	CONT  	A65   	A658        	17003	SO  					ENGINE	OBSTRUCTED      	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			C	R		F.O.D.                    	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SO	05	899JP					0101	3537658			PILOT REPORTED POWER LOSS IN CRUISE FLIGHT AND COULD NOT MAINTAIN ALTITUDE.  PRECAUTIONARY LANDING WAS MADE ON HIGHWAY, 	MINOR DAMAGE TO AIRCRAFT; NO INJURIES TO PILOT.  INVESTIGATION REVEALED A WAS OF STEEL WOOL IN THE VENTURI OF THE CARBUR	ETOR.  STEEL WOOL HAD BEEN PLACED IN THE HEAT MUFFS TO INCREASE HEAT TRANSFER.  THE STEEL WOOL EXITED THE SMALL HOLE IN 	THE MUFF, WENT THROUGH THE SCAT HOSE AND INTO THE  CARBURETOR CAUSING THE POWER LOSS.  (SO05200505084) (K)			1	H	7	1 	3I	3	O	NC	EXPA1H71	E205
2005032800088	20050328	00088	CE  	2005	3	28	2005FA0000095    	1	20041203	G	2435	23046110	BEARING SUPPORT 			MTSBSI	MU2   	MU2B40      	5780440	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					BEARING	LOOSE           	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	361MA				11412	429SA				DURING 400 HOUR SPECIAL ENGINE INSPECTION OF STARTER GENERATOR THE AFT BEARING RETAINER SCREWS WERE FOUND BACKED OUT, WH	ICH CAUSED AFT BEARING TO BE LOOSE.  BEARING FAILURE CAN CAUSE CATASTROPHIC FAILURE OF STARTER GENERATOR.  4 MS3526543 S	CREWS HOLD RETAINER TO FRAME.  THE SCREWS HAVE HOLES IN HEAD FOR SAFTEY WIRE, BUT WERE NOT SAFTIED.  THE AVAILABLE CMM F	OR THE S/G DOES NOT MENTION SAFTEYING THESE SCREWS.  SCREWS TIGHTENED AND SAFTIED AND UNIT PUT BACK IN SERVICE.  SUGGEST	 OPERATORS OF AIRCRAFT PERIODICALLY REMOVE UNIT AND COOLING FAN COVER AND ENSURE BEARING RETAINER IS SECURE. (K)		1	H	7	2 	3T	3	T	RT	A10SW   	E2WE
2005033000128	20050330	00128	CE  	2005	3	30	2005FA0000096    	1	20041206	G	1430	26520023	BOLT            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ENG MOUNT	CORRODED        	B			DELR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	431AS	10723				431				BOLT SHEARED AT THREADS DURING REMOVAL.  SIGNS OF INTERNAL CORROSION ON BOLT.						2	L	7	2 	4F	4	F		A10CE   	E6WE
2005030100055	20050301	00055	CE  	2005	3	1	2005FA0000097    	1	20041115	G	5610	10138402521	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  										COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	20NK	1858 				FA51				LT POSITION, INNER PLY OF WINDSHIELD SHATTERED AT 29 K, -38 DEGREE C, 8-10 SECONDS AFTER THE RT WINDSHIELD.  INNER PLY H	AD SHATTERED.  RECOMMEND SUBSEQUENT SCHEDULED WINDSHIELD RETORQUES BE CAREFULLY PREFORMED TO ENSURE ORIGINAL CONTOUR OF 	WINDSHIELD INSTALLATION  PER KIT 101-5043-3 IS NOT ALTERED RESULTING IN POSSIBLE STRESS LOCATIONS IN WINDSHIELD FRAME.				2	L	7	2 	4T				A24CE
2005021500114	20050215	00114	CE  	2005	2	15	2005FA0000098    	1	20041107	G	3244	5004549E	HEAT SHIELD     	GOODYEAR    		CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					LT MLG TIRE	DAMAGED         	B			J0UR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	09	567EA				NOV77761	5000067				PILOT REPORTED, HE HAD HIT AN OBJECT ON RUNWAY DUE TO IMPACT SOUND HEARD ON LT SIDE OF AC AND BRAKE ANTI-SKID FAIL INDIC	ATION.  INVESTIGATED LT WHEEL AREA AND DISCOVERED THAT TIRE HEAT SHIELD HAD PARTIALLY DISLOGED FROM WHEEL ASSY.  INSPECT	ED AREA AND FOUND PART OF HEAT SHIELD HAD TORN AWAY CUTTING BRAKE ANTI-SKID WIRE HARNESS, BENDING GEAR DOOR ROD, AND DEN	TING IB AREA OF LT LANDING LIGHT HSG.  INSPECTED RT TIRE HEAT SHIELD AND FOUND IT LOOSE ALSO.  INSP FOUND RT SHIELD TO B	E INSTALLED CORRECTLY IAW MFG MM.  DECISION WAS MADE TO REPLACE RT SHIELD.  TIRE HEAT SHIELD HAS NOT HARD MOUNT ATTACHME	NT TO WHEEL ASSY.  UPGRADING AC TO NEW STYLE WHEEL/BRAKE ASSY IS THE ONLY VIABLE FIX TO PREVENT THIS FROM HAPPENING.	1	L	7	2 	4F	4	F		A22CE   	E1NE
2005021500118	20050215	00118		2005	2	15	2005FA0000099    	4	20041215	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5023J	97   				172S8964				DURING A 100 HR INSPECTION THE FORWARD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AROUND 4 OF THE 6 BOLT HOLES. THINK THAT	 THE CAUSE OF THE PROBLEM IS THAT THE TORQUE OF THE PROP WAS RAISED AND THE NEW TORQUE IS NOT ENOUGH TO CAUSE THE BULKHE	AD AROUND THE BOLT HOLES TO BE PULLED INTO THE CHAMFERED AREA OF THE PROPELLER BOLT HOLES.  THIS STRESSES THE BULKHEAD A	ND ALLOWS CRACKS TO START.  TO PREVENT THIS PROBLEM POSSIBLY CONSIDER MAKING THE BULKHEAD OF THICKER MATERIAL OR REDESIG	NING THE PART SO THAT WHEN IT IS TORQUED THERE IS STRESS RELIEF AROUND THE BOLT HOLES SO THAT THE BULKHEAD SITS FLAT. (K	)	1	H	7	1 	3O			NT	3A12
2005021700006	20050217	00006	EA  	2005	2	17	2005FA0000101    	2	20040712	G	8530	LW19001	EXHAUST VALVE   			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					NR 3 CYLINDER	SEIZED          	D				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	01	102LP	1159 				18281121	L2837148A			UPON TAKEOFF, PILOT REPORTED POWER LOSS AND ROUGH RUNNING ENGINE.  INVESTIGATION FOUND NR 3 CYLINDERS EXHAUST VALVE SEIZ	ED.  THIS WAS 4TH OCCURENCE SINCE NEW (1999).  INSTITUTED 300 HOUR VALVE GUIDE REAM AND 25 HOUR OIL CHANGE.  MFG DENIED 	REQUEST TO INCREASE VALVE GUIDE CLEARANCE.				1	H	7	1 	3O	3	O	NT	3A13    	1E4
2005030200028	20050302	00028	SO  	2005	3	2	2005FA0000103    	1	20040902	G	5730	1159W2000510	SKIN            			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					RT WING	CORRODED        	B			GR4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	826GW					210				DURING WING (RIGHT) NOT INSPECTION, EXFOLIATION CORROSION NOTED ON WING UPPER PLANK AND FRONT BEAM BETWEEN RBS 284 THRU 	375.  EXFOLIATION CORROSION REMOVED IAW SRM.  REPAIRS COMPLETED.					2	L	7	2 	4F	4	F	RT	A12EA   	E2EU
2005021700007	20050217	00007	SO  	2005	2	17	2005FA0000104    	1	20040902	G	5414	1159P203263	COWLING         			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					LT NACELLE	CORRODED        	B			GR4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	826GW	7997 				210				DURING LT ENGINE MID-LIFE UPDATES, LT FIXED COWL WAS INSPECTED AND CORROSION WAS NOTED.  FIXED COWL WAS REPAIRED.						2	L	7	2 	4F	4	F	RT	A12EA   	E2EU
2005021700008	20050217	00008		2005	2	17	2005FA0000105    	4	20041212	G	3418	SLZ9692	PROBE           			GULSTM	G1159 	G1159B      	3953535	SO  										NR 2 AOA	BROKEN          	B			N38R	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			EA	05	4NR					255				NR 2 STICK SHAKER AND PUSHER ACTIVATED IN FLIGHT.  ENROUTE, CREW ENCOUNTERED ABOVE MENTIONED ISSUE.  CREW DIVERTED, DECL	ARED AN EMERGENCY.  LANDING WAS UNEVENTFUL.  MAINTENANCE DEPARTMENT WAS NOTIFIED IMMEDIATELY.  REMOVED AND REPLACED NR A	OA PROBE, PN ON SLZ9692, SN ON LH1250B.  OPS CHECKED SATISFACTORY.				2	L	7	2 	4F			RT	A12EA
2005030200031	20050302	00031	CE  	2005	3	2	2005FA0000106    	1	20040924	G	2435	23080023	STARTER GEN     			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE73123B   	 	WP  					RT ENGINE	FAILED          	B			EPDR	E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			NM	13	901P		914  			199	P99524			PILOT REPORTED VIBRATION, FOLLOWED BY RT GENERATOR INOPERATIVE LIGHT.  PRECAUTIONARY ENGINE SHUTDOWN WAS DONE.  REPLACED	 STARTER GEN, OPS NORMAL.  A TEARDOWN REPORT WILL BE REQUESTED FROM VENDOR. (K)					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE
2005030200032	20050302	00032	CE  	2005	3	2	2005FA0000107    	1	20041111	G	7830	2550012513	IDLER LINK      			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					THRUST REVERSER	FAILED          	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	101CC	1783 				RK277				THE UPPER IDLER LINK PN 202-0008-1, FAILED AT THE DOOR END PREVENTING THE THRUST REVERSER TO STOW PROPERLY AND DAMAGED T	HE SUPPORT ASSY.  PILOT`S WERE UNAWARE OF THE PROBLEM UNTIL THE T/R DOORS WERE NOTICED TO NOT BE FULLY STOWED ON WALK AR	OUND. (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA
2005033000143	20050330	00143	EU  	2005	3	30	2005FA0000111    	1	20041117	G	3710	1U128006	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					VACUUM SYS	SHEARED         	B			VJ3R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	862AF	447  				85002				DURING RUN-UP OF AIRCRAFT PILOT REPORTED LOST OF INSTRUMENT VACUUM SUCTION.  MAINTENANCE TECHNICIAN FOUND VACUUM PUMP HA	D A BROKEN SHAFT.  UPON REPLACEMENT OF VACUUM PUMP INSTRUMENT SUCTION WAS FOUND TO BE OK.  RECOMMEND FINDING A REPLACEME	NT THAT IS MORE DURABLE. (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4
2005033000146	20050330	00146	CE  	2005	3	30	2005FA0000113    	1	20041019	G	3213	60411022	PISTON          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					RT MLG STRUT	DAMAGED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	248FX	4051 			035	188				DURING 3000 LANDING INSPECTION OF MLG UPPER BEARINGS AND RETENSION PINS, FOUND RT MLG PISTON TO HAVE A SECTION OF CHROME	 MISSING APPROX .250 INCH X .10 INCH AND AREA WHERE THE CHROME HAS CIRCUMFERENCE CRACKS MEASURING AN AREA OF APPROX 3.0 	INCH X 1.0 INCH.  MANUFACTURE TO EVALUATE. (K)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
2005033000148	20050330	00148	EU  	2005	3	30	2005FA0000114    	1	20041113	G	5610	350A25900400	WINDSHIELD      			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	CRACKED         	B			MHIR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	25	456AE					3492				DURING DESCENT TO LANDING, PILOT NOTED CENTER WINDSHIELD CRACKED FROM JOGGLE POINT ACROSS LOWER WINDSCREEN.  REPAIRED WI	NDSCREEN IAW SRM FOR FLIGHT MAINTENANCE.  REPLACED WINDSCREEN WITH NEW.  CENTER WINDSCREEN HAS PROBLEMS WITH CRACKING DU	RING TEMPERATURE CHANGES (COLD WEATHER). (K) (RECORD NR 98050)				1	G	7	2 	3U	3	U		H9EU    	E00054EN
2005033000149	20050330	00149	EU  	2005	3	30	2005FA0000115    	1	20041119	G	6310	365A32653000	COUPLING        			AEROSP	AS365 	AS365N2     	8680815	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENG TO MR GB	CRACKED         	B			MHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	886TW					6413				DURING INSPECTION FOUND RT FORWARD ENGINE/ MGB DRIVE FLEX COUPLING CRACKED.  REPLACED WITH NEW.  (RECORD NR 98086) (K)						1	G	7	2 	3U	3	U	RT	H10EU   	E19EU
2005030100059	20050301	00059	NE  	2005	3	1	2005FA0000121    	2	20040903	G	8520	LW13683	BEARING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2B   	 	NE  					ENGINE	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7436L	1000 				317400994				RT REAR MAIN BEARING BEGAN TO SHRED METAL INTO OIL FILTER AFTER LANDING.  OIL CHANGE AND FILTER CUT OPEN.  THIS WAS FOUN	D ON A PRE-BUY.  LETTER TO FAA SENT SEPT 03, 2005, BUT NO REPLY. (K)					1	L	7	2 	3O	3	O		A20SO   	E14EA
2005032800097	20050328	00097	EA  	2005	3	28	2005FA0000123    	2	20041116	G	8530		CYLINDER        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR 2	FAILED          	B			AW4R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	11	3925H					240903				PILOT REPORTED THAT ENGINE BEGAN RUNNING ROUGH.  READINGS FORM THE ENGINE MONITOR SHOWED THAT NR 2 CYLINDER FAILED.  PIL	OT ELECTED TO LAND.  INVESTIGATION SHOWED THAT BOTH UPPER THROUGH BOLTS AND BOTH UPPER CYLINDER ATTACH STUDS FOR NR 2 CY	LINDER HAD FAILED AT THE CYLINDER FLANGE.  THE LOWER AT THROUGH BOLT FOR NR 1 CYLINDER WAS ALSO FOUND FAILED AT THE CYLI	NDER FLANGE.  ALL 4 CYLINDERS HAD BEEN REPLACED 205.2.  HOURS PREVIOUSLY AT 4177.7 HOURS.  FAILURE OF THE STUDS AND BOLT	S APPEARS TO BE CONSISTENT WITH EITHER UNDER TORQUE OR OVER-TORQUE OF THE NUTS AT INSTALLATION.  (K)		1	L	7	1 	3O	3	O		2A3     	1E10
2005033000168	20050330	00168	SO  	2005	3	30	2005FA0000125    	2	20041202	G	8520	TCM652832	CRANKSHAFT      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					ENGINE	BROKEN          	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	210FC					421B0908				CRANKSHAFT BROKE AT NR 2 MAIN.  NO SIGNS OF OIL STARVATION.  NO SIGNS OF CASE FRETTING.  CASE WAS DAMAGED BEYOND REPAIR.	  (K)					1	L	7	2 	3O	3	O		A7CE    	E7CE
2005033000169	20050330	00169	SO  	2005	3	30	2005FA0000126    	1	20041129	G	5740	62701153	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	CORRODED        	B			E85R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	8086Z					447995329				AIRCRAFT EXPERIENCED COMPLETE STABILATOR PRIMARY CONTROL FAILURE.  CAUSE OF FAILURE WAS DETERMINED TO BE CORROSION OF LO	WER STABILATOR CONTROL CABLE FORWARD CABLE END JUST T/E OF BARREL.  ESTABLISH A TIME LIFE REPLACEMENT OF CONTROL CABLE. 	 PROBLEM IS NOT DETECTABLE DURING PERIODIC INSP IAW MM. (K)				1	L	7	2 	3O	3	O		A19S0   	E286
2005030100058	20050301	00058	CE  	2005	3	1	2005FA0000127    	1	20041025	G	3020	24648000	HEATER          			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE INLET	CRACKED         	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			NM	07	43CE	552  				P21000703				PILOT REPORTED SMELLING A BURNED ODOR WHILE DESCENDING IN SEVERE ICING CONDITIONS.  ON A POST FLIGHT INSPECTION OF THE A	IRCRAFT A V SHAPED CRACK WITH THE TIP MISSING WAS FOUND IN THE ENGINE INLET HEATER.  IT APPEARS THAT PART OF THE HEATER 	HAS SHORTED OUT CAUSING THIS PART TO CRACK.  THE HEATER WAS TESTED AND WAS STILL OPERATIONAL. (K)				1	H	7	1 	3O	3	O		3A21    	E8CE
2005030100028	20050301	00028	SO  	2005	3	1	2005FA0000128    	2	20041222	G	8520	292266R	CRANKCASE       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	885C					421C0406				ENGINE CASE CRACK BY NR 3 FORWARD CYLINDER UPPER THROUGH BOLT RADIATING DOWNWARD SEVERAL INCHES.  AD ADDRESSES THIS PROB	LEM, BUT THESE MODEL NR ENGINE ARE NOT INCLUDED.  THIS HAS HAPPENED TO THIS ENGINE ONCE BEFORE, 2 YEARS AGO. (K)					1	L	7	2 	3O	3	O		A7CE    	E7CE
2005030100062	20050301	00062	SO  	2005	3	1	2005FA0000129    	1	20041221	G	5751	8656206	SKIN            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O320  	O320*       	41508	EA  					LT AILERON	CRACKED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	3047U	7707 				447995262				DURING AN ANNUAL INSPECTION OF THE AIRCRAFT THE LT AILERON ASSEMBLY WAS FOUND TO HAVE A CRACK IN THE OB SKIN.  PROBABLE 	CAUSE OF CRACKING OF THE LT AILERON ASSEMBLY IS UNKNOWN.  AILERON REMOVED FOR MAINTENANCE AND REPAIRED BY REPLACING DAMA	GED PART. (K)				1	L	7	2 	3O	3	O		A19S0   	E274
2005030100065	20050301	00065	SO  	2005	3	1	2005FA0000130    	1	20041221	G	5751	8656206	SKIN            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					LT AILERON	CRACKED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2202X	8034 				447995278				DURING AN ANNUAL INSPECTION OF THE AIRCRAFT THE LT AILERON ASSEMBLY WAS FOUND TO HAVE A CRACK IN THE OB SKIN.  PROBABLE 	CAUSE OF CRACKING OF THE LT AILERON ASSEMBLY IS UNKNOWN.  AILERON REMOVED FOR MAINTENANCE AND REPAIRED BY REPLACING DAMA	GED PART.  (K)				1	L	7	2 	3O	3	O		A19S0   	E286
2005030100067	20050301	00067	SO  	2005	3	1	2005FA0000131    	1	20041221	G	5751	8656206	SKIN            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					LT AILERON	CRACKED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2247B	8022 				447995108				DURING AN ANNUAL INSPECTION OF THE AIRCRAFT THE LT AILERON ASSEMBLY WAS FOUND TO HAVE A CRACK IN THE OB SKIN.  PROBABLE 	CAUSE OF CRACKING OF THE LT AILERON ASSEMBLY IS UNKNOWN.  AILERON REMOVED FOR MAINTENANCE AND REPAIRED BY REPLACING DAMA	GED PART.  (K)				1	L	7	2 	3O	3	O		A19S0   	E286
2005040100025	20050401	00025		2005	4	1	2005FA0000133    	1	20040919	G	2434	ALK1242AAS2	HOUSING         	ELECTROSYS  																ALTERNATOR	MISREPAIRED     	B			KC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03					E020668					IN PREPARING ALTERNATOR FOR INSTALLATION.  CLOSE INSPECTION REVEALED THAT LIGHT PRESSURE ON NEGATIVE DIODE CAUSED DIODE 	TO BECOME UNSEATED FROM BORE IN HOUSING.  INSPECTION OF BORE SHOWED THAT THE BORE WAS OVERSIZED AND HAD BEEN PAINTED DUR	ING OVERHAUL.  DIODE BORE DIMENSION (.499 INCH +/- .001 INCH) IS CRITICAL TO RELIABLE OPERATION OF THE ALTERNATOR.  (THE	 DIODES RELY ON A PRESS FIT TO MAINTAIN ADEQUATE HEAT DISSIPATION AND CURRENT FLOW AND SHOULD NOT BE INSTALLED IN A BORE	 THAT HAS PAINT OR ANY OTHER ELECTRICALLY RESISTIVE MATERIAL IN IT.) THIS FAILURE IS EXACTLY THE SAME AT THE UNIT THAT W	AS BEING REPLACED, HAVE SEEN NUMEROUS OTHER (LOOSE DIODES), RETURNED TO FACTORY FOR WARRANTY.
2005030100060	20050301	00060	EU  	2005	3	1	2005FA0000135    	1	20041001	G	3411		PITOT TUBE      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					PITOT/STATIC SYS	OUT OF POSITION 	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	527PB	114  				527				PILOT LOST AIRSPEED INDICATION ON A POST 91 FLIGHT.  AIRCRAFT RETURNED, FOUND PITOT TUBE SLIPPED OUT FROM B-NUT AT T-FIT	TING, BEHIND INTERIOR PANEL ON RT SIDE, APPROXIMATELY AT FRAME 23.  SUSPECT TUBING INSERT WAS NOT INSERTED FAR ENOUGH IN	TO TUBING DURING MANUFACTURE. (K)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
2005030100019	20050301	00019	EA  	2005	3	1	2005FA0000144    	2	20040814	G	8540	70384	GEAR SHAFT      								LYC   	O540  	O540E4B5    	41532	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05		765  					L1019440			AT AIRCRAFT 100 HOUR ENGINE WAS FOUND WITH TIGHT SPOT.  REMOVED ENGINE ACCYS AND FOUND GOVERNOR SHAFT NOT TURNING DISASS	EMBLED ENGINE.  FOUND GOVERNOR IDLER GEAR SHAFT (PN 70384) BROKEN IN 3 PARTS; ALL GOV GEARS HAD RG TEETH, 1 OF 2 KNOWN F	AILURES, ON SHAFT  (PN 70384) WITH SAME SERIAL/ BATCH NUMBERS.									3	O			E295
2005030200029	20050302	00029		2005	3	2	2005FA0000145    	4	20041210	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PROP SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	796WW					172S8635				DURING ANNUAL INSPECTION FOUND FWD BULKHEAD OF THE SPINNER CRACKED 5 PLACES AROUND PROPELLER BOLT HOLES.  RECOMMEND: BUL	KHEAD MATERIAL STRONGER OR THICKER. (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10
2005041500182	20050415	00182		2005	4	15	2005FA0000146    	4	20041216	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	154ME					172S8534				DURING 100 HOURS INSPECTION, FOUND PROP SPINNER FWD BULKHEAD CRACKED SEVERAL PLACES.  LOWER PROP BOLTS TORQ SETTING OR M	AKE BULKHEAD STRONGER.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2005040100075	20050401	00075		2005	4	1	2005FA0000147    	4	20041222	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROP SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2134M					172S9552				DURING ANNUAL INSPECTION, FOUND PROP SPINNER FWD BULKHEAD CRACKED AROUND 2 BOLT HOLES.  RECOMMENDATION: MANUFACTURE BULK	HEAD STRONGER OR THICKER.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10
2005030100051	20050301	00051	SO  	2005	3	1	2005FA0000148    	2	20041120	G	8530		CYLINDER        			UNIVAR	415   	415C        	0420302	NM  	CONT  	C85   	C8512       	17008	SO  	MCAULY	1B90	1B90*       	GL  	ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	2919H	24   				3544	29175712	19046		CYLINDER AND ROD FAILURE RESULTED IN CASE FAILURE CAUSING CYLINDER TO COME OF ENGINE.  CAUSE UNKNOWN.  NR 4 PISTON (AE-C	530348) FAILURE.  (WP09200502317).  (K)					1	L	7	1 	3O	3	O		A718    	E233	5	N	P842
2005032800110	20050328	00110	EU  	2005	3	28	2005FA0000150    	1	20041124	G	3220	120A5211	SWIVEL          			GROB  	120   	G120A       	1660208	EU  										NLG	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	1761 				85003				INSPECTION OF NOSE GEAR UPPER TRUNNION BOLTS FOUND CRACKS AROUND WELDS AND ON THE EARS FOR THE SWIVEL TUBE.   PROBABLE C	AUSE EXCESSIVE STRESSES IN THIS AREA.  AT THIS TIME NO RECOMMENDATION UNTIL MFG MAKES DETERMINATION OF CAUSES. (K)					1	L	7	1 	3O			RT	A49CE
2005040400089	20050404	00089	EU  	2005	4	4	2005FA0000151    	1	20041124	G	3220	120A5211	SWIVEL          			GROB  	120   	G120A       	1660208	EU  										NOSE GEAR	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	864AF	1665 				85004				INSPECTION OF NOSE GEAR UPPER TRUNNION BOLTS FOUND CRACKS AROUND WELDS AND ON THE EARS FOR THE SWIVEL TUBE.  PROBABLE CA	USE EXCESSIVE STRESSES IN THIS AREA.  AT THIS TIME NO RECOMMENDATION UNTIL MFG MAKES DETERMINATION OF CAUSES.  (K)					1	L	7	1 	3O			RT	A49CE
2005040400004	20050404	00004	EU  	2005	4	4	2005FA0000152    	1	20041124	G	3210		BOLT            			GROB  	120   	G120A       	1660208	EU  										NLG TRUNNION	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	867AF					85007				INSPECTION OF NOSE GEAR UPPER TRUNNION BOLTS FOUND CRACKS AROUND WELDS AND ON THE EARS FOR THE SWIVEL TUBE.  PROBABLE CA	USE EXCESSIVE STRESSES IN THIS AREA.  AT THIS TIME NO RECOMMENDATION UNTIL MFG MAKES DETERMINATION OF CAUSES. (K)					1	L	7	1 	3O			RT	A49CE
2005040100028	20050401	00028	EU  	2005	4	1	2005FA0000153    	1	20041124	G	3220	120A5211	SWIVEL          			GROB  	120   	G120A       	1660208	EU  										NLG	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	862AF	1755 				85002				INSPECTION OF NOSE GEAR UPPER TRUNNION BOLTS, FOUND CRACKS AROUND WELDS AND ON THE EARS FOR THE SWIVEL TUBE.  PROBABLE C	AUSE EXCESSIVE STRESSES IN THIS AREA.  AT THIS TIME NO RECOMMENDATION UNTIL MFG MAKES DETERMINATION OF CAUSES.  (K)					1	L	7	1 	3O			RT	A49CE
2005030100020	20050301	00020	CE  	2005	3	1	2005FA0000157    	1	20041123	G	3213	0541124	AXLE            			CESSNA	170   	170A        	2072304	CE  	CONT  	C145  	C145*       	17012	SO  					LT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	5430C	2871 				19560				LT MAIN GEAR WHEEL AXLE BROKE BETWEEN GEAR LEG AND WHEEL RACE.  (GL11200505686) (K)						1	H	7	1 	3O	3	O		A799    	E253
2005030100106	20050301	00106	CE  	2005	3	1	2005FA0000158    	1	20041101	G	2434	991059111RX	ALTERNATOR      			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	ENGINE	FAILED          	B			AIHR	O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			GL	11	801AL		417  			18280767	L2749848A	000544		PILOT DECLARED EMERGENCY, TOTAL ELECTRICAL FAILURE.  DIAGNOSTIC INSPECTION REVEALED ALTERNATOR FAILURE.  PILOT FAILED TO	 SEE WARNING LIGHT; DISCHARGE ON AMMETER AND LOW VOLT READING ON VOLT METER.  (GL11200505028) (K)					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C
2005030100018	20050301	00018	SO  	2005	3	1	2005FA0000159    	1	20041026	G	5320	6345100	SUPPORT         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER PEDAL	DAMAGED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	7665F					32R7780075				RUDDER PEDAL FLEXING DURING BRAKING ACTION. (K)						1	L	7	1 	3O	3	O		A3SO    	E14EA
2005031100008	20050311	00008	NE  	2005	3	11	2005FA0000160    	1	20041101	G	6320	51635200582	RING GEAR       	SKRSKY      		SKRSKY	S58T  	S58JT       	8141807	NE  	PWA   	PT6T  	PT6T3       	52045	EA  					GEAR TEETH	DAMAGED         	B			JTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	827MW	1902 			S58H17561084	58827				RING GEAR DAMAGED.						2	G	7	2 	4U	4	U		1H11    	E22EA
2005030200065	20050302	00065	EU  	2005	3	2	2005FA0000162    	1	20041020	G	4920	A4504174	COMPRESSOR WHEEL	HAMSTD      		BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					APU	DAMAGED         	B			OTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	48Y					258009				RECENTLY EXPERIENCED A PROBLEM WITH A RELATIVELY LOW TIME COMPRESSOR WHEEL.  THIS NEW STYLE COMPRESSOR WHEEL IS A REPLAC	EMENT WHEEL TO SUPPORT AD NR20021502.  THE WHEEL IN QUESTION LOST A LARGE INDUCER TIP THAT PENETRATED, AND CAME VERY CLO	SE TO EXITING THE AIR INLET HOUSING.  THIS WHEEL WAS INSTALLED 20 MONTHS AGO.  AT THE TIME OF THIS EVENT IT HAD ACCUMULA	TED 265.1 HOURS AND 660 CYCLES.  BESIDES THE MISSING INDUCER TIP, SEVERAL BLADES EXHIBIT INDUCER BLADE CRACKS CLOSE TO T	HE WHEEL BORE.  THERE WAS NO INDICATION OF BEARING FAILURE, FOD, OR IMPACT WITH THE AIR INLET.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
2005040100077	20050401	00077	EA  	2005	4	1	2005FA0000163    	2	20041020	G	8520	72877	TAPPET          	LYC         		SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	882				L2821948A	2161	L282A48A	DY5166B		ON ANNUAL 100 HR INSP, OIL STRAINER CLEANED, METAL PIECE FOUND IN STRAINER, METAL PIECE SENT TO MFG FOR ANALYSIS, REPORT	 INDICATED.  PIECE FROM TAPPET BODY.  CYCLE REDUCED, INSP OF TAPPPET BODIES, FOUND NIS INLET, BODY WITH PIECE MISSING FR	OM SURFACE, PROBABLE CAUSE MFG DEFECT.  ALSO NOTICED, ON CYLINDER REMOVAL, SEVERE CORRODION OF 4 CYLS, WHICH RESULTED IN	 CYLS, WHICH RESULTED IN CYL BEING SCRAP. (K)			1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P25EA
2005040100078	20050401	00078	SO  	2005	4	1	2005FA0000164    	2	20041105	G	8520	653387788	LIFTER          			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	CORRODED        	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	956C	308  				0387	686694			DURING A RECENT MFG SYMPOSIUM, THE PROBLEM OF UNAIRWORTHY LIFTERS IN MFG ENGINES DISCUSSED.  MFG ENGINE HAVE BEEN NOT HO	LDING UP WELL IN THESE AREAS AND MANY SC`S ARE RECOMMENDING AN INSPECTION OF THE LIFERS DURING SCHEDULED MAINTENANCE.  T	HIS AC WAS UNDERGOING AN ANNUAL INSPECTION AND THE OWNERS AGREED TO HAVE THE LIFTERS CHECKED AS THE WARRANTY PERIOD ENDS	 THIS MONTH.  WITH 308.5 HOURS  TSN, WE FOUND 3 LIFTERS SPALLED AND PITTED.  IT IS MY EXPERIENCE THAT THE CAUSE FOR THIS	 IS THE USE OF A MULTI-VISCOSITY OIL SINCE NEW.  RECOMMEND STRAIGHT WEIGHT OILS ALWAYS ESPECIALLY IN THESE ENGINES.  ALS	O RECOMMEND 25 HOUR OIL CHANGES REGARDLESS OF THE USAGE OF THE AIRCRAFT. (EA07200501466)	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2005030800271	20050308	00271	SO  	2005	3	8	2005FA0000165    	2	20041029	G	7321	6329168	FMU             			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	LT ENGINE	OUT OF ADJUST   	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			WP	19	3278Q	1053 	816  			4020078	502452	941052		LT ENGINE LOST POWER ON FINAL APPROACH DUE TO THE FUEL METERING UNIT BECOMING OUT OF ADJUSTMENT.  UNIT WAS ADJUSTED IAW 	CSM AND ENGINE FUEL PRESSURES AND FLOWS WERE ADJUSTED IAW MFG SB97-3.  GROUND RUN WAS PERFORMED AND FLIGHT TEST CONDUCTE	D.  NO DEFECTS WERE NOTED WITH EITHER ACTION.  NO RECOMMENDATIONS FOR NON-RECURRENCE AS THE FUEL SETTINGS CHANGE WITH TH	E CHANGE IN CONSULTED ON THIS BY THIS COMPANY AND OTHERS WITH THE ONLY RECOMMENDATION THAT PRESSURES AND FLOWS BE ADJUST	ED AT SEASONAL CHANGE. (WP19200504117)		1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
2005030800273	20050308	00273	SO  	2005	3	8	2005FA0000166    	2	20040712	G	8520	649895	CRANKSHAFT      			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	09	36934	768  				414A0486	208086J			CRANKSHAFT CRACKED						1	L	7	2 	3O	3	O		A7CE    	E8CE
2005033000049	20050330	00049	EA  	2005	3	30	2005FA0000167    	2	20041026	G	8530		STUD            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					NR 2 CYLINDER	FAILED          	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	33129		850  			28R7535124	RL870551A			(4) EA DECK STUDS ON NR 2 CYLINDER, FAILED.						1	L	7	1 	3O	3	O		2A13    	1E10
2005030800275	20050308	00275	SO  	2005	3	8	2005FA0000168    	2	20041026	G	8520		STUD            			CESSNA	206   	P206        	2073304	CE  	CONT  	O520  	IO520A      	17032	SO  					ENGINE	FAILED          	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	2625X		433  			P2060125	112599R			(2) EA DECK STUDS ON NR 1 CYLINDER FAILED. (K)						1	H	7	1 	3O	3	O		A4CE    	E5CE
2005040100036	20050401	00036	SO  	2005	4	1	2005FA0000169    	2	20041025	G	8520	653877	LIFTER          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	SPALLED         	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6484A	884  				21063535	295048			DURING SCHEDULED OIL CHANGE, METAL WAS FOUND IN THE FILTER.  FURTHER INVESTIGATION DISCOVERED THE TAPPETS STARTING TO FA	IL.  THIS CONDITION CAN BE A RESULT OF IMPROPER HEAT-TREATING.  WITHOUT BEING FAMILIAR WITH MFG PROCESS, CAN NOT RECOMME	ND A PLAN FOR PREVENTIVE ACTION. (K)				1	H	7	1 	3O	3	O		3A21    	E5CE
2005030800280	20050308	00280	SO  	2005	3	8	2005FA0000170    	2	20041105	G	7314	65335385	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	977DC	43   				C0177				FUEL PUMP FAILS TO HOLD PROPER PRESSURES.  SAME PROBLEM WITH ORIGINAL PUMP.  CHANGED PUMP, SET PRESSURES IAW SI 097-3B. 	 PRESSURES TO BE RE-ADJUSTED APPROXIMATELY ONCE EVERY 2-3 WEEKS.  NOTICED PRESSURES CHANGE WITH SEASON TEMPERATURES. (K)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO
2005030800109	20050308	00109	SO  	2005	3	8	2005FA0000172    	1	20041026	G	3213	2705301	STRUT           			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540*      	41532	EA  					RT MLG	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	9014P					244475				PERFORMING ROUTINE SERVICE, THE RT MLG STRUT WAS FOUND LEAKING 5606 HYDRAULIC FLUID.  DISCOVERED THAT THE STEEL (4130) A	TTACHMENT FOR THE GEAR DOOR HAD CREATED DISSIMILAR METAL CORROSION AND CREATED A PIN HOLE LEAK.  THIS PART NEEDS TO BE R	EMOVED AND CHECKED TO PREVENT THIS FROM RE-OCCURRING.				1	L	7	1 	3O	3	O		1A15    	1E4
2005032800082	20050328	00082	SO  	2005	3	28	2005FA0000173    	1	20041012	G	3220	472681	LINK            			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					TAIL WHEEL	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	1121C					182221				ON LANDING ROLLOUT, AIRCRAFT DRIFTED TO THE LT AND WENT INTO SOFT GROUND, COMING TO REST ON IT`S NOSE.  FOUND LINK (PN 4	72681) PARTIALLY STRAIGHTENED, CAUSING THE RT TAIL WHEEL SPRING ASSY TO FAIL. (K)					1	H	7	1 	3O	3	O		1A2     	E274
2005040400065	20050404	00065	SO  	2005	4	4	2005FA0000185    	1	20040806	G	2140	94E421	PRESSURE SWITCH 			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	CLOSED          	B			IS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										CUSTOMER BOUGHT EXCHANGE HEATER.  CORE RETURNED TO US HAD A DISTORTED COMBUSTION TUBE.  FOUND COMBUSTION AIR PRESSURE SW	ITCH 94E42-1 CLOSED AT ALL TIMES.  THIS PARTICULAR SWITCH IS A NORMALLY OPEN SWITCH.  SWITCH CLOSES WHEN COMBUSTION 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.  THIS SWI	TCH DOES NOT GET TESTED IAW AD 96-20-07.  THIS FR65D79-3EL HEATER WAS BUILT IN OCTOBER 1997.  (K)		1	L	7	2 	3O				A20SO
2005040400072	20050404	00072	SO  	2005	4	4	2005FA0000186    	1	20040813	G	2140	94E423	PRESSURE SWITCH 			PIPER 	PA34  	PA34200T    	7103406	SO  										HEATER	CLOSED          	D			IS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		76   			A02020068					CUSTOMER WAS CHECKING HEATER IAW AD96-20-07 EVEN THOUGH HE WASNT REQUIRED TO DO SO, AND FOUND THE COMBUSTION AIR PRESSU	RE SWITCH CLOSED AT ALL TIMES.  THIS IS A NORMALLY OPEN SWITCH.  CUSTOMER INFORMED US THAT THE HEATER HAS 76 HRS. TT.  T	HIS WAS A WARRANTY CLAIM.  UPON RECEIPT OF THE DEFECTIVE SWITCH, CONCLUDED THAT THE SWITCH WAS CLOSED AT ALL TIMES.  THI	S SWITCH (AND HEATER) IS NOT REQUIRED TO BE TESTED IAW AD 96-20-07.  THE HEATER, THIS SWITCH IS INSTALLED ON IS PN FR90D	38-1EL AND WAS BUILT IN FEBRUARY 2002.  TO PREVENT RECURRENCE, HAVE OPERATORS CHECK HEATERS AND SWITCHES WITH A SB OR AD	.  (K)	1	L	7	2 	3O				A7SO
2005033000027	20050330	00027	NM  	2005	3	30	2005FA0000189    	1	20040613	G	5711	41513027	SPAR CAP        			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	3620H	958  				4245				WHILE PERFORMING A 3 YEAR INSPECTION OF THE WING CENTER SECTION IAW AD, NOTE: 2002-26-02 AND MFG SB NR 31, THE FORWARD U	PPER SPAR CAPSTRIP, PN 415-13027 WAS FOUND TO HAVE AN AREA OF INTERGRANULAR (IG) CORROSION NEAR THE UPPER WING ATTACH FI	TTING.  THE CORROSION WAS BARELY VISIBLE WITH THE WING CENTER SECTION INSTALLED ON THE AIRCRAFT.  THE FULL EXTENT OF THE	 IG CORROSION WAS NOT KNOWN TILL THE WING CENTER SECTION SPAR WAS REMOVED FROM THE AIRCRAFT, STRIPPED OF PAINT AND THORO	UGHLY CLEANED.  INITIALLY THE AREA OF CORROSION APPEARED TO LOOK LIKE PEALING PAINT.  CLOSER INSPECTION REVEALED AN AREA	 .6250 WIDE X 6 INCHES LONG X .1875 INCH DEEP.  RECOMMEND A CLOSE AND THOROUGH INSPECTION OF WING CENTER INSPECTION FOR 	1	L	7	1 	3O	3	O		A718    	E213
2005042500194	20050425	00194	EU  	2005	4	25	2005FA0000206    	1	20041014	G	2910	M20R751802A2	LINE            			AMD   	FALC20	FALCONF     	2720306	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HYD SYSTEM	CHAFED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	132EP	4397 				463				2 HYDRAULIC PIPES WERE CHAFING AGAINST EACH OTHER IN THE RT ENGINE PYLON.  THE 2 PIPES WERE REMOVED AND REPLACED, ENSURI	NG NO CONTACT BETWEEN THEM.  (GL19200501324) (K)  (NR1 OF 2 )					2	L	7	2 	4F	4	F		A7EU    	E6WE
2005040400100	20050404	00100	CE  	2005	4	4	2005FA0000207    	1	20041017	G	5755	24920016KIT	PANEL           			LEAR  	60    	60LEAR      	5170707	CE  										RT WING SPOILER	DAMAGED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	228FX					132				WHILE PERFORMING SCHEDULED INSPECTION THE RT SPOILER PANEL WAS FOUND TO BE DAMAGED AT THE FORWARD IB CORNER.  THIS SPOIL	ER PANEL WAS PREVIOUSLY INSTALLED AT THIS STATION ON 9/29/2002 AT TT:3939.5 & TC:2774.  SB 60-27-2 WAS USED TO INSTALL A	ND TRIM THE PANEL AT INSTALLATION.  THE SB TRIM CLEARANCE FOR THIS PANEL IS .030 INCH TO .060 INCH, MFG MM 27-60-01 TRIM	 CLEARANCE IS .050 INCH TO .080 INCH.  THE PANEL CLEARANCE WAS FOUND TO BE AT .040 INCH WHICH WAS TOO TIGHT WHEN USED AS	 SPOILERONS IN FLIGHT.  INCORRECT TRIM GAP IN SB 27-60-2.  MFG EVALUATE AND MAKE CHANGE. (EA09200500519) (K)		2	L	7	2 	4F			RT	A10CE
2005040400090	20050404	00090	CE  	2005	4	4	2005FA0000208    	1	20041006	G	5755	2422510	PANEL           			LEAR  	60    	60LEAR      	5170707	CE  										LT WING SPOILER	DAMAGED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	240FX					167				AIRCRAFT ARRIVE WITH LT SPOILER PANEL DAMAGE AT THE IB FWD EDGE CORNER.  AN INSPECTION WAS ACCOMPLISHED WITH NEGATIVE RE	SULTS.  THIS SPOILER PANEL WAS PREVIOUSLY INSTALLED AT THIS STATION ON 9/16/2004 FOR A SIMULAR DEFECT AT TT: 4277.5 AND 	TC: 2923. SB 60-27-2 WAS USED TO INSTALL AND TRIM THE PANEL AT INSTALLATION.  THE SB TRIM CLEARANCE FOR THIS PANEL IS .0	30 INCH TO .060 INCH, MFG MM 27-60-01 TRIM CLEARANCE IS .050 INCH TO .080 INCH.  THE PANEL CLEARANCE WAS FOUND TO BE AT 	.040 INCH WHICH WAS TOO TIGHT WHEN USED AS SPOILERONS IN FLIGHT.  INCORRECT TRIM GAP IN SB 27-60-2.  MFG TO EVALUATE AND	 MAKE CHANGE.  (EA09200500525) (K)	2	L	7	2 	4F			RT	A10CE
2005042500195	20050425	00195	WP  	2005	4	25	2005FA0000209    	2	20041026	G	7200		STATOR          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	ERODED          	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	422FX					135	P116281			DURING 600/1200 HOUR INSPECTION, FOUND (9) NINE BY PASS STATOR BLADES WITH EROSION DAMAGE ON THE LEADING EDGE.  BLADES W	ERE REMOVED AND REPALCED IAW MM.  PROBABLE CAUSE: DESIGN ENGINEERING EVALUATE.  (EA09200500613) (K)					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005040400074	20050404	00074	EU  	2005	4	4	2005FA0000210    	1	20041229	G	3000	7847232	ANTI-ICE VALVE  			AMD   	FALC90	FALCON900B  	2730171	EU  	GARRTT	TFE731	TFE731*     	01518	WP  						FAILED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	203CW	1181 				33				DURING TROUBLESHOOTING FOR (HIGHER THAN NORMAL) GASPER AIR TEMPERATURE, FOUND THE TURBOFAN TURBINE ANIT-ICE VALVE DISASS	EMBLED BETWEEN THE VALVE AND THE MOTOR.  NO DAMAGE CAN BE SEEN ON THE VALVE.  THE 2 THREADED PARTS WERE FOUND UNTHREADED	.  THE DYSFUNCTIONAL PART WAS REMOVED AND REPLACED WITH A NEW VALVE PN 784723-3.  REF AMM 21-512. (K)				2	L	7	3 	4F	4	F	RT	        	E6WE
2005040400078	20050404	00078	CE  	2005	4	4	2005FA0000211    	1	20041229	G	7921	10046A	OIL COOLER      			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					RT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	2025P					P476				COOLER SPLIT AT WELD ON END OF COOLER.  SPLIT WAS 2+ INCHES LONG RIGHT DOWN THE CENTER OF THE WELD.  (GL19200501920) (GL	19200502021) (K)					1	L	7	2 	3O	3	O		A12CE   	E10EA
2005040400006	20050404	00006	NE  	2005	4	4	2005FA0000225    	2	20041025	G	8500	50B043	ROD             								PWA   	4060  	PW4060      	52119	NE  					LPC MODULE	NICKED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03							P724153			ENGINE WAS RECEIVED FOR PHASE III MODEL CONVERSION.  DURING TEARDOWN SEVERAL TIE RODS WERE FOUND WITH NICKED DOWN AREA I	N THREADS.  PARTS WERE SENT TO T.C. HOLDER FOR INVESTIGATION.  REF RMR NR 31481.										4	F			E24NE
2005040400069	20050404	00069	EU  	2005	4	4	2005FA0000227    	1	20041014	G	2910	M20R751804A1	PIPE            			AMD   	FALC20	FALCONF     	2720306	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HYD SYSTEM	CHAFED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	132EP	4397 				463				2 HYDRAULIC PIPES WERE CHAFING AGAINST EACH OTHER IN THE RT ENGINE PYLON.  THE 2 PIPES WERE REMOVED AND REPLACED ENSURIN	G NO CONTACT BETWEEN THEM.  (GL19200501324).  (K)  (NR 2 OF 2)					2	L	7	2 	4F	4	F		A7EU    	E6WE
2005042500200	20050425	00200	CE  	2005	4	25	2005FA0000228    	1	20041022	G	2697	P133	WIRE HARNESS    			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RT FIRE DETECT	CHAFED          	B			WVER	O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			EA	09	418FX					120				RT ENGINE FAIL CAS AMBER LIGHT ILLUMINATED AND RT ENGINE FIRE RED WARNING LIGHT ILLUMINATED IN FLIGHT ON FINAL APPROACH 	TO PNE.  PROBLEM: SEVERAL WIRES WERE CHAFED THOUGH ON THE P133 WIRING HARNESS.  FOUND CHAFED ON FRAME NEAR THE TAIL CONE	 RELAY PANEL.  REPAIRED WIRES IAW MM.  OPERATIONAL CHECKED OK.  PROBABLE CAUSE:  IMPROPER WIRE ROUTING/PROTECTION. (EA09	200500610) (K)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005040100109	20050401	00109	EU  	2005	4	1	2005FA0000229    	1	20040624	G	2910	723088325	TUBE            			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NOSE WHEEL WELL	LEAKING         	G			UG1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	437SJ					437				TUBE LEAKING THRU SEVERAL PIN HOLES, SUSPECT INTERNAL CORROSION.  SLOW EVACUATION OF HYDRAULIC FLUID PREVENTED ACTUATION	 OF HYDRAULIC FUSE.  TAKEOFF WITH GEAR (UP) SELECTION REVEALED SLOW ACTUATION AND A RETURN TO BASE.  GEAR (DOWN) SLOW BU	T CAME DOWN AND LOCKED.  LAND WITHOUT INCIDENT. (EA03200405351)				2	M	7	2 	4F	4	F		A2SW    	E6WE
2005040100110	20050401	00110	EU  	2005	4	1	2005FA0000230    	1	20040908	G	3320	F5053136501	SIGN            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					LT CABIN	BURNED          	B			QU2R	D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			EA	17	450K	9437 				186				SMOKE WAS OBSERVED IN THE CABIN AFTER START OF TAXI TO ACTIVE RUNWAY, THE CREW SHUT DOWN ENGINES, SHUT OFF ALL POWER AND	 DISCONNECTED BATTERY.  FOUND SOURCE OF SMOKE TO BE FROM A NO SMOKING/SEATBELT SIGN LOCATED IN THE LT SIDE OF CABIN AT F	RAME 20.  THE AIRCRAFT WAS SECURED AND FERRYED TO A MAINTENANCE BASE.  UPON FURTHRE INVESTIAGTION, FUND NO CONCLUSIVE EV	IDENCE BUT SUSPECT PROBLEM ORIGINATED AT THE INTERFACE OF THE WIRING TO THE NO SMOKING/SEATBELT SIGN.			2	L	7	3 	4F	4	F		A46EU   	E6WE
2005032800091	20050328	00091	SW  	2005	3	28	2005FA0000232    	1	20040808	G	3260	V31	WARNING SWITCH  			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	6344Q					670427				LANDING GEAR WARNING SWITCH FOUND LOOSE ON THE ATTACH AREA OF THROTTLE CABLE CAUSING INTERMITTENT OPERATION OF HORN.  SC	REWS WERE TIGHTENED AND SYSTEM OPERATES NORMALLY.(K)					1	L	7	1 	3O	3	O		2A3     	1E10
2005042500211	20050425	00211	NM  	2005	4	25	2005FA0000233    	1	20041105	G	3246		WHEEL           			BOEING	737   	7373H4      	1384600	NM  	CFMINT	CFM56 	CFM563B1US  	 	GL  					MLG	CRACKED         	B			SWAX	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	29	322SW					23343				WHEEL/ TIRE ASSY WENT FLAT.  SHOP FINDINGS THROWN TREAD AND 4 BROKEN WHEEL TIE BOLTS.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2005042500212	20050425	00212	CE  	2005	4	25	2005FA0000234    	1	20041026	G	8011	642083A12	ADAPTER         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					STARTER	SLIPPED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1556A					CE1318				INSTALLED NEW ENGINE IN AIRCRAFT AND PERFORMING ENGINE SET UP.  MAINTENANCE CREW NOTICED STARTER ADAPTOR SLIPPING.  NEW 	PART SO REMOVED FOR WARRANTY. NO RECOMMENDATION AT THIS TIME. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE
2005040400108	20050404	00108	CE  	2005	4	4	2005FA0000235    	1	20041112	G	7810	LW12126	EXHAUST RISER   			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT ENGINE	CRACKED         	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3731G					310R0906				FOUND LT ENGINE OB EXHAUST RISER CRACKED WHILE PERFORMING A 50 HOUR EXHAUST INSPECTION IAW AD 00-01-16.  (GL21200500869)	 (K)					1	L	7	2 	3O	3	O		3A10    	E8CE
2005031100063	20050311	00063	SW  	2005	3	11	2005FA0000236    	1	20041021	G	5230		DOOR FRAME      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					CARGO DOOR	CRACKED         	B			Q8LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	160WA					TC399				DURING A FLUORESCENT PENETRANT INSPECTION OF (CARGO DOOR FRAME LOWER END FORE AND AFT NEAR BAYONET PIN). (FC STUN-M00-2-	1-1) A CRACK OF APPROXIMATELY 0.250 INCH WAS DETECTED.  THE PROBABLE CAUSE IS SERVICE INDUCED FATIGUE CRACKING.  AREA OF	 CONCERN HAS ALREADY BEEN REINFORCED WITH DOUBLER PLATE AND ADDITIONAL RIVETS.  STOP HOLE WILL BE DRILLED AT CRACK END T	O PREVENT FURTHER LENGTHENING.			2	L	7	2 	4T	3	T	RT	A8SW    	E2WE
2005040400010	20050404	00010		2005	4	4	2005FA0000237    	4	20041026	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	796WW	393  				172S8635				DURING 100 HOUR INSPECTION OF THE PROPELLER, CRACKS NOTED AROUND ALL BOLT HOLES OF THE FWD BULKHEAD. (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2005040100111	20050401	00111	NM  	2005	4	1	2005FA0000238    	1	20041118	G	7500		CLAMP           			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   	      	CFE73811B   	 	NE  					BLEED AIR	LOOSE           	B			BTVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	248JF					11				CLIMBING THROUGH 27,000 FT THE RT GENERATOR WENT OFFLINE, SHORTLY AFTERWARDS, LT GENERATOR WENT OFFLINE, AN EMERGENCY WA	S DECLARED AND THE AC LANDED WITH NO FURTHER INCIDENT, INVESTIGATION FOUND A LOOSE CLAMP CONNECTING A BLEED AIR DUCT TO 	THE CABIN COLD TEMPERATURE CONTROL VALVE.  IT IS SUSPECTED THAT BLEED AIR LEAKING AT THIS AREA CAUSED THE GENERATOR CONT	ROL UNITS TO STOP WORKING DUE TO OVERHEATING.  THE CLAMP WAS TIGHTENED AND A LEAK CHECK PERFORMED.  A FUNCTIONAL CHECK O	F THE GENERATOR SYS PERFORMED.  NO DISCREPANCIES WERE NOTED.  GENERATOR CNTRL UNITS WERE REPLACED AS A PRECAUTIONARY MEA	SURE GCU`S WERE SENT TO THE MFG AND FOUND TO FUNCTION IAW DESIGN SPECIFICATION. (K)	2	K	7	3 	4F	4	F	RT	A50NM   	E44NE
2005030800279	20050308	00279	NM  	2005	3	8	2005FA0000239    	1	20041027	G	7810		EXHAUST PIPE    			AERORS	J2    	J2          	5500604	NM  	LYC   	O360  	O360*       	41514	EA  					ENGINE	BROKEN          	G				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CL	CLIMB          	1			SW	11	62SJ					091				(ACCIDENT NR DFW05CA024)  ON TAKEOFF CLIMB, EXHAUST PIPE BROKE AND WENT THROUGH 4 BLADED PROPELLER, SHEARING OFF ONE PRO	PELLER BLADE.  EXHAUST PIPE STRUCK RT TAILBOOM, DOING STRUCTURAL DAMAGE TO TAILBOOM.  (SW11200502888) (K)					1	G	7	1 	3O	3	O	NC	H6WE    	E286
2005040400020	20050404	00020	CE  	2005	4	4	2005FA0000240    	1	20041109	G	3240		PEDAL           			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					BRAKE	MISALIGNED      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	808DT					T20608278				RT SIDE BRAKE PEDALS:  DURING A FLT CHECK, THE INSTRUCTOR FOUND HE RARELY HAD BRAKES DUE TO TOE PEDALS GOING OVER TOO FA	R, HIS FOOT COULD NOT GO OVER ANYMORE TO STOP THE AIRCRAFT.  DURING OK OUT, SEEMS THE LINKAGE ON PEDALS IS MISALIGNED AL	LOWING THE PDEALS TO GO OVER TOO FAR, JUST ABOUT TO FIREWALL. (K)				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA
2005040100076	20050401	00076	EA  	2005	4	1	2005FA0000241    	2	20040915	G	7414	S4LN20105136029	MAGNETO         			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					RIGHT	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	9198B	351  				283857				OVERHAUL DATE, MFG, 5-2001 - GEAR FAILURE (PN AB-357584) ELECTRODE BRASS FINGRE ON NYLON GEAR WAS LOOSE AND CONTRACTED B	RASS ELECTRODES.  ON PN 10-357424 DISTRIBUTOR BLOCK FILLING BLOCK WITH CONDUCTIVE PARTICLES WHICH ENDED UP SHORTING OUT 	ONE IGNITION LEAD CAUSING ROUGH RUNNING ENGINE. (K)				1	L	7	1 	3O	3	O		2A13    	E286
2005040400052	20050404	00052	CE  	2005	4	4	2005FA0000242    	1	20041115	G	5610	10138402522	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NM	13	20NK					FA51				INNER PLY OF WINDSHIELD SHATTERED AT 29,000, -38 DEGREES C., RT HAND POSITION.  THEN 8-10 SECONDS LATER LT WINDSHIELD SH	ATTERED.  RECOMMEND SUBSEQUENT SCHEDULED WINDSHIELD RETORQUES BEING CAREFULLY PERFORMED TO ENSURE ORIGINAL CONTOUR OF WS	 INSTALLATION IAW KIT 101-50433 IS NOT ALTERED RESULTING IN STRESS LOCATIONS IN WINDSHELL FRAME.  (NM13200500756) (NM132	00501246) (K)			2	L	7	2 	4T	4	T		A24CE   	E4EA
2005031100006	20050311	00006	EU  	2005	3	11	2005FA0000243    	1	20041109	G	2121	900A6047	FAN             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					AIR CONDITIONER	MISMANUFACTURED 	B			D94R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	204TX	322  				3711				LOCKING SET SCREW MISSING FROM FAN, FAN DETATCHED FROM MOTOR.  UPON RECEIPT OF NEW FAN, FOUND SET SCREW ALSO MISSING. (K	)					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005040400060	20050404	00060	CE  	2005	4	4	2005FA0000244    	1	20041103	G	2520	551900921	FRAME           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT	CRACKED         	B			LQUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	219MS					5500180				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  CHAIR WAS REPAIRED IAW STO1042WI STRUCTURAL SEAT REPAIR.	 (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE
2005040400082	20050404	00082	CE  	2005	4	4	2005FA0000245    	1	20041103	G	2520	551900922	FRAME           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT	CRACKED         	B			LQUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	219MS					5500180				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  CHAIR WAS REPAIRED IAW STO1042WI STRUCTURAL SEAT REPAIR.	 (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE
2005040400002	20050404	00002	CE  	2005	4	4	2005FA0000246    	1	20041103	G	2520	551900932	FRAME           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT	CRACKED         	B			LQUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	219MS					5500180				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. ALSO, PREVIOUS INAPPROPRIATE REPAIR.  CHAIR WAS REPAIRED 	IAW STO1042WI STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE
2005042600016	20050426	00016	EA  	2005	4	26	2005FA0000254    	2	20041225	G	7322	6230103	GASCOLATOR      			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					BOWL CONTACT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	75EH	2895 				282121				SURFACE AREA WHERE BOWL ASSEMBLY (63479-00) CONTACTS THE FRAME (COVER 14428-00) OF THE FUEL FILTER BENDS AS WIRE ASSEMBL	Y (BAIL 494-644) IS TIGHTENED.  OVER THE YEAR THE FORCE OF THE BAIL ACTUALLY BENDS THE FRAME TO WHERE THE GASKET WILL NO	 LONGER SEAL AND FUEL WILL SEEP BY THE GASKET WHEN THE BOWL IS CROCKED FORWARD AND AFT.  90 DEGREES TO THE LOCATIO OF TH	E BAIL ASSEMBLY.  THE ONLY OPTION TO REMEDY THE SITUATION IS TO REPLACE WITH FACTORY NEW  OR STC REPLACEMENT.  (SO152005	14114)		1	L	7	1 	3O	3	O		2A13    	E286
2005042600017	20050426	00017	EA  	2005	4	26	2005FA0000256    	2	20041225	G	8550	CH48110	OIL FILTER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2166L					287990259				WHEN OIL FILTER WAS CUT OPEN FOR INSPECTION, A PIECE OF STRING WAS DISCOVERED WRAPPED AROUND THE FILTER MEDIUM.  NO OTHE	R PROBLEM WAS DISCOVERED AT THIS TIME.  BETTER Q.C. IN MFG WILL CORRECT SITUATION.  (SO15200514115)					1	L	7	1 	3O	3	O		2A13    	E286
2005040400094	20050404	00094	EU  	2005	4	4	2005FA0000260    	1	20041209	G	2450		ALTERNATOR      			BRAERO	1000  	BAE1251000A 	1500104	EU  	PWA   	305   	PW305       	 	NE  					NR 1	FAILED          	B			R14R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	533QS					259033				AIRCRAFT WAS SQUAWKED WITH NR 1 ALTERNATOR DROPPING OFF IN FLIGHT.  DURING TROUBLESHOOTING THE TECHNICIAN FOUND SMOKE TR	AILS ON THE (GG PANEL),  LOCATED ON THE AFT SIDE OF THE REAR FACE OF THE PRESSURE BULKHEAD.  A MORE CLOSE INSPECTION REV	EALED A DESTROYED FUSE HOLDER, WITH ACCOMPANYING WIRE DAMAGE, GCU AND LINE CONTACTOR DAMAGE.  THERE WAS A HOLE BURNED TH	ROUGH THE (GG PANEL) ITSELF AT THE FUSE HOLDER LOCATION.  THE DAMAGE WAS CENTERED UNDER THE LT SIDE OF THE FUSE BLOCK, W	HICH HAD DESINTEGRATED.  IT WAS UNDETERMINED AS TO WHICH COMPONENT INITIATED THE DAMAGE.  (EA17200504804)		2	L	7	2 	4F	4	F	RT	A3EU    	E35NE
2005040400092	20050404	00092	CE  	2005	4	4	2005FA0000261    	1	20040805	G	3220		MECHANISM       			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NLG	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	05	1840Q					177RG0240				NOSE LANDING GEAR FAILED TO EXTEND DURING APPROACH 8/5/04.  NOSE GEAR WAS CONFIRMED TO NOT BE EXTENDED BY COCKPIT INDICA	TION AND WING MOUNTED MIRROR.  SEVERAL ATTEMPTS WERE MADE TO EXTEND NOSE GEAR, TO NO AVAIL.  MANUAL NOSE GEAR EXTENSION 	WAS ALSO ATTEMPTED, EMERGENCY CK LIST, TO NO AVAIL.  EMERGENCY DECLARED, AC LANDED NOSE GEAR UP.  WHEN AC WAS LIFTED, NO	SE GEAR DOORS FELL OPEN, NOSE GEAR WAS ABLE TO BE PUMPED DOWN.  INSP, NO OBVIOUS CAUSAL FACTOR OF INCIDENT COULD BE DETE	RMINED.  AC TO BE REPAIRED.  (1ST OCCURRENCE.  JULY, 2000 SAME AS ABOVE, NO SINGLE CAUSE IDENTIFIED. AC REPAIRED, FLOWN 	APPROX 700 HRS TIL THIS INCIDENT.) (NM05200400085) (K)	1	H	7	1 	3O	3	O		A20CE   	1E10
2005032800102	20050328	00102	CE  	2005	3	28	2005FA0000262    	1	20041004	G	5753		RIB             			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540*       	41532	EA  					LT FLAP TRACK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	210BB					R18201430				LT WING IB FLAP TRACK RIB ASSY, PN 1221010-15, HAS 2 BRACKETS RIVETED TO EITHER SIDE OF IT TO ATTACH FLAP TRACK RIB ASSY	 TO WING LOWER IB T/E SKIN, REF TO AS FLAP WELL SKIN) PN 0720601-101.  ONE OF BRACKETS HAD CRACKED ALLOWING BRACKET TO T	WIST SLIGHTLY, DECREASING CLEARANCE BETWEEN BRACKET AND FLAP ROLLER SLOT IN FLAP TRACK RIB ASSY.  ON GROUND, PILOT TRIED	 TO RAISE FLAPS.  FRONT OF LT FLAP IB SUPPORT ARM RIB ASSY CAUGHT ON CRACKED AND TWISTED BRACKET JAMMING IB END OF FLAP.	  NORMALLY THERE IS ABOUT .1250 INCH CLEARANCE BETWEEN THE BRACKET AND FRONT OF FLALP SUPPORT ARM.  FLAP MOTOR CONTINUED	 TO RUN, TRYING TO RETRACT FLAPS, CAUSING SUBSTANTIAL DAMAGE TO JAMMED LT FLAP.  REPLACED CRACKED BRACKET, LT FLAP. (K)	1	H	7	1 	3O	3	O		3A13    	E295
2005042600020	20050426	00020		2005	4	26	2005FA0000265    	1	20040802	G	2910		LINE            																	HYD SYSTEM	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		78   								HAD 3 HYDRAULIC LINE FAILURES CAUSING LOSS OF LANDING GEAR OPERATION WITHIN 70 HOURS.  2 FAILURES WERE DUE TO LOOSE B-NU	TS, 1 WAS FAILURE OF LINE AT FLARE.  LINES ARE SOFT ALUMINUM, THIN WALL TUBING WITH NO SPEC NUMBER APPEARS TO BE 3003-0 	USED FOR AIR AND VACUUM LINES.  SHOULD BE 5052-0 FOR GEAR HYDRAULIC SYSTEM.
2005031100071	20050311	00071	SO  	2005	3	11	2005FA0000267    	1	20040902	G	5312	1159B2156225	BULKHEAD        			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					FUSELAGE	CRACKED         	B			GR4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	826GW	7997 				210				DURING COMPLIANCE OF NDT EDDY CURRENT INSP OF FS-793.75 BULKHEAD, CAP ANGLE WAS FOUND CRACKED.  NEW CAP ANGLE WAS INSTAL	LED IAW DWG NR SE20000210, REV. D.					2	L	7	2 	4F	4	F	RT	A12EA   	E2EU
2005040400091	20050404	00091	SO  	2005	4	4	2005FA0000268    	1	20040902	G	5730	1159W200059	PANEL           			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					LT WING	CORRODED        	B			GR4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	826GW					210				DURING WIG (LT) NDT INSPECTION EXFOLIATION CORROSION NOTED ON WING UPPER PLANK AND FRONT BEAM BETWEEN RBS 284 THRU 375. 	 REMOVED EXFOLIATION CORROSION IAW SRM.  REPAIRS COMPLETED.					2	L	7	2 	4F	4	F	RT	A12EA   	E2EU
2005031100069	20050311	00069	SO  	2005	3	11	2005FA0000269    	1	20040902	G	5414	1159P203264	COWLING         			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					RT NACELLE	CORRODED        	B			GR4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	826GW	7997 				210				DURING RT ENGINE MID-LIFE UPDATES, RT FIXED COWL WAS INSPECTED AND CORROSION WAS NOTED.  FIXED COWL WAS REPAIRED.						2	L	7	2 	4F	4	F	RT	A12EA   	E2EU
2005031400093	20050314	00093	SO  	2005	3	14	2005FA0000270    	2	20040928	G	8530	649358CN	CYLINDER HEAD   			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ENGINE	SEPARATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	28127		817  			8030972	224129R	EC1592A		AIRCRAFT ANNUAL INSP- 2 WEEKS PRIOR- REPLACED EXHAUST AND INTAKE VALVES ON NR 2 CYLINDER DUE TO LOW COMPRESSION.  FLEW 6	 HOURS PRIOR TO INCIDENT.  IN CRUISE FLIGHT, ENGINE SUDDENLY RAN VERY ROUGH WITH VIBRATION.  VFR WITH FLIGHT FOLLOWING. 	 DECLARED EMERGENCY AND LANDED AT NEAREST AIRPORT(3F3), 18 MILES AWAY.  POST FLIGHT INSPECTION:  NR 2 CYLINDER BROKE INT	O 2 PIECES- SEPARATED AT TOP OF BARREL AND JUNCTURE OF HEAD.  HEAD WAS HELD ON BY VALVE COVER AND PUSH RODS.  THIS CYLIN	DER IS REPORTEDLY NOT SUBJECT TO EXISTING ADS OR MANDATORY SB THAT COVER OTHER ECI CYLINDERS WITH SIMILAR PROBLEMS.  (SW	05200502730)	1	L	7	1 	3O	3	O		A18CE   	E5CE	5	C	P25EA
2005032800078	20050328	00078	SO  	2005	3	28	2005FA0000272    	1	20041124	G	3246	40120C	WHEEL           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	898DS					32R7780358				OWNER REPORTED AIRCRAFT HARD TO TOW.  UPON INSPECTION, FOUND LT MLG WHEEL (ASSY 40-120C) BINDING.  REMOVED LT MLG WHEEL 	AND FOUND INNER WHEEL HALF FLANGE WITH APPROXIMATELY 5 INCH CRACK.  FLANGE HAD SEPARATED ENOUGH TO BIND ON BRAKE ASSY BA	CKING PLATE.  REPLACED WHEEL ASSY WITH NEW.  REMOVED AND INSPECTED RT MLG WHEEL ASSY.  NO DEFECTS NOTED.  AC RETURNED TO	 SERVICE.  (SO05200405828)			1	L	7	1 	3O	3	O		A3SO    	E14EA
2005031000090	20050310	00090		2005	3	10	2005FA0000274    	1	20041222	G	2922	RC914UK096	BYPASS SWITCH   	PALL        																FILTER	SHEARED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99		4550 								1 OF THE SREWS (P/N AA-2100-11D99)HAD THE HEAD SHEAR OFF JUST UNDER THE HEAD. THIS SCREW, 1 OF 4 HOLD THE FILTER BYPASS 	DIFFERENTIAL PRESSURE INDICATOR TO THE TOP OF THE FILTER ASSEMBLY. THE AFFECTED SYSTEM WAS THE RUDDER STANDBY. HYDRAULIC	 FLUID WAS LEAKING STATICLY WITH THE SYSTEM DEPRESSURIZED.
2005040400073	20050404	00073	SO  	2005	4	4	2005FA0000279    	2	20041213	G	8520	653877	LIFTER          								CONT  	O550  	IO550C      	 	SO  					ENGINE	SPALLED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		600  								ON 6 DIFFERENT ENGINES DURING OIL CHANGES OR TROUBLESHOOTING FOR LOW OIL PRESSURE, HAVE FOUND A SPALLED LIFTER.  ONLY ON	CE WAS THE PROBLEM WAS THE PROBLEM CAUGHT EARLY ENOUGH THAT THE CAMSHAFT WAS NOT DAMAGED AND NEEDING REPLACEMENT. (K)  (	1 OF 2)									3	O			E3SO
2005033000031	20050330	00031	SO  	2005	3	30	2005FA0000280    	2	20041213	G	8520	653888	LIFTER          								CONT  	O550  	IO550C      	 	SO  					ENGINE	SPALLED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		600  								ON 6 DIFFERENT ENGINES DURING OIL CHANGES OR TROUBLESHOOTING FOR LOW OIL PRESSURE, HAVE FOUND A SPALLED LIFTER.  ONLY ON	CE WAS THE PROBLEM CAUGHT EARLY ENOUGH THAT THE CAMSHAFT WAS NOT DAMAGED AND NEEDING REPLACEMENT.  (K)  (2 OF 2)										3	O			E3SO
2005031100080	20050311	00080	EU  	2005	3	11	2005FA0000281    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		1607 			SC205					THE BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSEMBLY TO THE HONEYCOMB FLAP END-RIB HAVE FA	ILED.  INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COM	PROMISED.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE IN	TEGRITY OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSY AND THE FLAP END-RIB (IB	 AND OB) SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG NOTIFIED. (K)		1	L	7	1 	3T			RT	A60EU
2005031100082	20050311	00082	EU  	2005	3	11	2005FA0000282    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		3090 			SC224					BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSY  TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  	INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISE	D.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY	 OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSEMBLY AND THE FLAP END-RIB (IB AN	D OB) SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED.		1	L	7	1 	3T			RT	A60EU
2005031100084	20050311	00084	EU  	2005	3	11	2005FA0000283    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		3797 			SC149					BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSY  TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  	INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISE	D.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY	 OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSY AND THE FLAP END-RIB (IB AND OB	) SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED.(K)		1	L	7	1 	3T			RT	A60EU
2005031100085	20050311	00085	EU  	2005	3	11	2005FA0000284    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		3797 			SC141					BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSY  TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  	INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISE	D.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY	 OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSEMBLY AND THE FLAP END-RIB (IB AN	D OB) SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED. (K)		1	L	7	1 	3T			RT	A60EU
2005031100081	20050311	00081	EU  	2005	3	11	2005FA0000285    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAPS	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		4562 			SC127					BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSY  TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  	INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISE	D.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY	 OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSEMBLY AND THE FLAP END-RIB (IB AN	D OB) SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED. (K)		1	L	7	1 	3T			RT	A60EU
2005031100083	20050311	00083	EU  	2005	3	11	2005FA0000286    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		2988 			SC193					BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSY  TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  	INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISE	D.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY	 OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSY AND THE FLAP END-RIB (IB AND OB	) SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED. (K)		1	L	7	1 	3T			RT	A60EU
2005040400063	20050404	00063	EU  	2005	4	4	2005FA0000287    	1	20040809	G	5753	T700A5755000000	CARRIAGE        			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		3561 								BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR METAL CARRIAGE ASSY (PN  TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  	INSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISE	D.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY	 OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSY AND THE FLAP EN-RIB (IB AND OB)	 SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED. (K)		1	L	7	1 	3T			RT	A60EU
2005031100086	20050311	00086	EU  	2005	3	11	2005FA0000288    	1	20040809	G	5753		RIB             			SOCATA	TBM   	TBM700      	8682000	EU  										TE FLAP	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		3647 			SC134					BONDED INSERTS WHICH PROVIDE THE ATTACH POINTS FOR THE METAL CARRIAGE ASSY TO THE HONEYCOMB FLAP END-RIB HAVE FAILED.  I	NSPECTION OF THE INSERTS REVEALS THAT THE SEAL BETWEEN THE BONDED INSERT AND THE HONEYCOMB STRUCTURE BECOMES COMPROMISED	.  WATER IS INTRODUCED INTO THE HONEYCOMB END-RIB AND THE HONEYCOMB STRUCTURE FAILS.  IMMEDIATELY INSPECT THE INTEGRITY 	OF THE IB AND OB FLAP ATTACH POINTS.  ANY MOVEMENT NOTED BETWEEN THE FLAP CARRIAGE ASSY AND THE FLAP END-RIB (IB AND OB)	 SHOULD REQUIRE REMOVAL OF THE FLAP FOR FURTHER INSPECTION OF THE BONDED INSERTS.  MFG HAS BEEN CONTACTED. (K)		1	L	7	1 	3T			RT	A60EU
2005040100035	20050401	00035	CE  	2005	4	1	2005FA0000289    	1	20041109	G	2897	EE366L	WIRE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					HEAT FUEL VENT	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	100RU					LJ1433				HEAT ELEMENT INOPERATIVE DUE TO BROKEN WIRE AT TIME VENT TUBE WHERE IS IS GROUNDED.  IT IS CAUSED BY IMPROPER PROTECTIVE	 COATING ON WIRES.  IT WEAR OFF AND OPENS THE WIRE FROM GROUND. (K)					1	L	7	2 	3T	3	T	RT	3A20    	E2NE
2005040100026	20050401	00026	CE  	2005	4	1	2005FA0000290    	1	20041109	G	2897		WIRE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					HEATED FUEL VENT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	100RU					LJ1433				HEAT ELEMENT INOPERATIVE, DUE TO BROKEN WIRE AT TIP OF VENT TUBE WHERE IT IS GROUNDED.  IT IS CAULED BY IMPROPER PROTECT	IVE COATING ON THE WIRE.  THE COATING WEARS OFF AND OPENS THE WIRE FROM GROUND. (K)					1	L	7	2 	3T	3	T	RT	3A20    	E2NE
2005040400025	20050404	00025		2005	4	4	2005FA0000315    	4	20040505	G	2564	S8012	CYLINDER        																	LIFE RAFT	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					F46392					DURING RECEIVING INSPECTION OF LIFE RAFT (PN RA4610220, SN F46392) IT WAS FOUND THAT THE CYLINDER (PN S-801-2, SN 55396P	, DATE OF MFG.  10-1973 WAS CHARGED AND INSTALLED ON THE LIFE RAFT.  THE CYLINDER WHICH IS A DOT 3HT 3000 RATED CYLINDER	 HAD PAST ITS 24 YEAR SERVICE LIFE ON 10-1997 AND WAS HYDROSTATICALLY RETESTED ON 12-98 AND 12-02 BY REG NR PMMC AS SHOW	N (STAMPED) ON THE CROWN OF THE CYLINDER.  ONCE A DOT 3HT3000 RATED CYLINDER REACHES ITS 24 YEAR SERVICE LIFE IT CANNOT 	BE HYDROSTATICALLY RETESTED AND MUST BE REMOVED FROM SERVICE.  THE COMPANY THAT SERVICE THE LIFE RAFT LAST, FAILED TO CO	MPLY THE REGULATIONS FOR SERVICING THE CYLINDER.
2005032800114	20050328	00114	SW  	2005	3	28	2005FA0000316    	1	20040927	G	3220	206020110103	SKID            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					VERTICAL FIN	FRACTURED       	B			KBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	407MH	4517 				53100				DURING PRE-FLIGHT INSPECTION, FOUND TAIL SKID LOOSE IN VERTICAL FIN.  UPON CLOSER EXAMINATION, TAIL SKID PULLED OUT FROM	 FIN ASSEMBLY.  THE TAIL SKID HAD CRACKED COMPLETELY AROUND AND THROUGH AT THE ATTACHMENT BOLT HOLE.  BY APPEARANCE OF T	HE BROKEN ENDS OF THE TUBE, THIS CRACK PROPAGATION WAS SLOW.  NO OTHER DAMAGE, OR DEFORMATION OF TAIL SKID NOTED DURING 	REPLACEMENT OF THE NEW TAIL SKID.  HISTORY, AC WAS INVOLVED IN A HARD LANDING/ TAIL ROTOR SUDDEN STOPPAGE.(K)			1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2005042700015	20050427	00015		2005	4	27	2005FA0000317    	4	20040415	G	2565	C19347101	FRANGIBLE LINK  	AIRCRUISERS 																EVAC SLIDE	INCORRECT       	B			PN8D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					0324RP					RECEIVED EVACUATION SLIDE FOR RECERTIFICATION.  DURING DISASSY EACH FRANGIBLE LINKS (PNC19347-101, 4EA, PN C19347-102,1E	A, PN C19347-105,2EA) WERE FOUND WITH (4) STRANDS OF BLACK NYLON THREAD SECURING EACH HALF OF FRANGIBLE LINK TOGETHER.  	FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, REUSED BY SECURING HALVES TOGETHER WITH BLACK NYLON THREAD.  NORMAL OR UNUSED FR	ANGIBLE LINKS ARE TWO LOOPS SECURED WITH STRANDS OR BREAKING WIRES, HAVING A SPECIFIC BREAKING STRENGTH WHICH ARE COVERE	D WITH HEAT SHRINK TUBING.  IF SLIDE WAS DEPLOYED WITH MODIFIED FRANGIBLE LINKS, SLIDE WOULD POSSIBLY EXTEND RAPIDLY, TO	E END OF SLIDE WOULD EXTEND UNDER THE AC.  ONCE FRANGIBLE LINKS ARE BROKEN, REQUIRED TO BE REPLACED WITH NEW. (1 OF 3)
2005032800040	20050328	00040		2005	3	28	2005FA0000318    	4	20040415	G	2565	C19347102	LINK            	AIRCRUISERS 																SLIDE	BROKEN          	B			PN8D	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19					0324RP					RECEIVED EVACUATION SLIDE FOR RECERTIFICATION.  DURING DISASSY, EACH FRANGIBLE LINK (PN C19347-101, 4EA, PN C19347-102, 	1EA, PN C19347-105, 2EA), WERE FOUND WITH (4) STRANDS OF BLACK NYLON THREAD SECURING EACH HALF OF FRANGIBLE LINK TOGETHE	R.  FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, REUSED BY SECURING HALVES TOGETHER WITH BLACK NYLON THREAD.  NORMAL OR UNUSE	D FRANGIBLE LINKS HAVE TWO LOOPS SECURED WITH STRANDS OF BREAKING WIRES HAVING SPECIFIC BREAKING STRENGTH WHICH ARE COVE	RED WITH HEAT SHRINK TUBING.  IF SLIDE WAS DEPLOYED WITH MODIFIED FRANGIBLE LINKS, SLIDE WOULD POSSIBLE EXTEND RAPIDLY A	ND TOE END OF SLIDE WOULD EXTEND UNDER AC.  ONCE FRANGIBLE LINKS ARE BROKEN, REQUIRED TO BE REPLACED WITH NEW. (2 OF 3)
2005040100068	20050401	00068		2005	4	1	2005FA0000319    	4	20040415	G	2565	C19347105	LINK            	AIRCRUISERS 																ECAPE SLIDE	INCORRECT       	B			PN8D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					0324RP					RECEIVED EVACUATION SLIDE FOR RECERTIFICATION.  DURING DISASSY EACH FRANGIBLE LINKS (PN C19347-101, 4EA, PN C19347-102, 	1EA, PN C19347-105, 2EA) WERE FOUND WITH (4) STRANDS OF BLACK NYLON THREAD SECURING EACH HALF OF FRANGIBLE LINK TOGETHER	.  FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, REUSED BY SECURING HALVES TOGETHER WITH BLACK NYLON THREAD.  NORMAL OR UNUSED	 FRANGIBLE LINKS ARE TWO LOOPS SECURED WITH STRANDS OR BRAKING WIRES, HAVING SPECIFIC BREAKING STRENGTH WHICH ARE COVERE	D WITH HEAT SHRINK TUBING.  IF SLIDE WAS DEPLOYED WITH MODIFIED FRANGIBLE LINKS, SLIDE WOULD POSSIBLY EXTEND RAPIDLY, TO	E END OF SLIDE WOULD EXTEND UNDER THE AC.  ONCE FRANGIBLE LINKS ARE BROKEN, REQUIRED TO BE REPLACED WITH NEW.  (3 OF 3)
2005042700016	20050427	00016		2005	4	27	2005FA0000320    	4	20040415	G	2565	C19347101	FRANGIBLE LINK  																	EVAC SLIDE	INCORRECT       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					0258RP					RECEIVED EVACUATION SLIDE FOR RECERTIFICATION.  DURING DISASSY EACH FRANGIBLE LINKS (PN C19347-101, 4EA, PN C19347-102, 	1EA, PN C19347-105, 2EA) WERE FOUND WITH (4) STRANDS OF BLACK NYLON THREAD SECURING EACH HALF OF FRANGIBLE LINK TOGETHER	.  FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, REUSED BY SECURING HALVES TOGETHER WITH BLACK NYLON THREAD.  NORMAL OR UNUSED	 FRANGIBLE LINKS ARE TWO LOOPS SECURED WITH STRANDS OR BRAKING WIRES, HAVING A SPECIFIC BRAKING STRENGTH WHICH ARE COVER	ED WITH HEAT SHRINK TUBING.  IF SLIDE WAS DEPLOYED WITH MODIFIED FRANGIBLE LINKS, SLIDE WOULD POSSIBLE EXTEND RAPIDLY, T	OE END OF SLIDE WOULD EXTEND UNDER THE AC.  ONCE FRANGIBLE LINKS ARE BROKEN, REQUIRED TO BE REPLACED WITH NEW. (1 OF 3)
2005040100043	20050401	00043		2005	4	1	2005FA0000321    	4	20040415	G	2565	C19347102	LINK            																	ESCAPE SLIDE	INCORRECT       	C			PN8D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										RECEIVED EVACUATION SLIDE FOR RECERTIFICATION.  DURING DISASSY EACH FRANGIBLE LINKS (PN C19347-101, 4EA, PN C19347-102, 	1EA, PN C19347-105, 2EA) WERE FOUND WITH (4) STRANDS OF BLACK NYLON THREAD SECURING EACH HALF OF FRANGIBLE LINK TOGETHER	.  FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, REUSED BY SECURING HALVES TOGETHER WITH BLACK NYLON THREAD.  NORMAL OR UNUSED	 FRANGIBLE LINKS ARE 2 LOOPS SECURED WITH STRANDS OR BRAKING WIRES, HAVING A SPECIFIC BREAKING STRENGTH WHICH ARE COVERE	D WITH HEAT SHRINK TUBING.  IF SLIDE WAS DEPLOYED WITH MODIFIED FRANGIBLE LINKS, SLIDE WOULD POSSIBLY EXTEND RAPIDLY, TO	E END OF SLIDE WOULD EXTEND UNDER THE AC.  ONCE FRANGIBLE LINKS ARE BROKEN, REQUIRED TO BE REPLACED WITH NEW (2 OF 3)
2005042700017	20050427	00017		2005	4	27	2005FA0000322    	4	20040415	G	2565	C19347105	FRANGIBLE LINK  																	EVAC SLIDE	INCORRECT       	B			PN8D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					0324RP					RECEIVED EVACUATION SLIDE FOR RECERTIFICATION.  DURING DISASSY EACH FRANGIBLE LINKS (PN C19347-101, 4EA, PN C19347-102, 	1EA, PN C19347-105, 2EA) WERE FOUND WITH (4) STRANDS OF BLACK NYLON THREAD SECURING EACH HALF OF FRANGIBLE LINK TOGETHER	.  FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, REUSED BY SECURING HALVES TOGETHER.  FRANGIBLE LINKS WERE PREVIOUSLY BROKEN, 	REUSED BY SECURING HALVES TOGETHER WITH BLACK NYLON THREAD.  NORMAL OR UNUSED FRANGIBLE LINKS ARE 2 LOOPS SECURED WITH S	TRANDS OR BREAKING WIRES, HAVING A SPECIFIC BREAKING STRENGTH WHICH ARE COVERED WITH HEAT SHRINK TUBING.  IF SLIDE WAS D	EPLOYED WITH MODIFIED FRANGIBLE LINKS, SLIDE WOULD POSSIBLY EXTEND RAPIDLY, TO END OF SLIDE WOULD EXTEND UNDER THE AC.
2005042700019	20050427	00019	SW  	2005	4	27	2005FA0000323    	1	20040927	G	7500	44C13	CLAMP           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					P3 BLEED AIR	LOOSE           	B			OZ5R	J	A			DUMP FUEL               	UNSCHED LANDING         			E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			NM	05	60NE					AC760B				AFTER TAKEOFF, AT ABOUT 400 FT, NR 2 ENG FIRE WARNING LIGHT CAME ON.  ENG PARAMETERS CHECKED NORMAL.  CREW FOLLOWED EMER	GENCY PROCEDURES, RETURNED TO FIELD.  AFTER LANDING, ENGINE WAS SHUTDOWN BY USING THE STOP AND FEATHER BUTTON.  CREW DIS	CHARGED ENGINE FIRE EXTING BOTTLE.  AFTER DEPLANING PASSENGERS, CREW PERFORMING WALKAROUND, OBSERVED FLAMES COMING OUT O	F ENG INTAKE AND TAILPIPE, DISCHARGED CABIN FIRE EXTING DOWN ENG INLET.  FOUND BROKEN BLEED AIR CLAMP IN COWLING WHEN CO	WLING WAS OPENED.  BROKEN CLAMP ALLOWED BLEED AIR TO TURN ON THE FIRE WARNING LIGHT, INTERNAL ENG FIRE WAS CAUSED BY MAL	FUNCTION IN FUEL SHUTOFF.  (NM05200500912) (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005033000019	20050330	00019	SW  	2005	3	30	2005FA0000324    	1	20040406	G	7921	20163A	OIL COOLER      			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					NR 2 ENGINE	BLOCKED         	B			OZ5R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			NM	05	459AM					AC700	P44628			ON CLIMBOUT, NR 2 ENG OIL TEMP WENT UP TO RED LINE, OIL PRESSURE DROPPED.  LOW OIL PRESSURE LIGHT HAD NOT COME ON.  CREW	 MADE PRECAUTIONARY SHUTDOWN ON NR 2 ENG, LANDED BACK AT BASE WITH NO FURTHER INCIDENT.  OIL WAS FOUND IN TAILPIPE OF NR	 2 ENG, NO OIL FOUND IN ENG INLET.  REAR CARBON SEAL HAD FAILED DUE TO EROSION, VIBRATION, OR COMB.  OIL COOLER WAS REPL	ACED, OIL TEMP RETURNED TO NORMAL RANGES.  INTERNAL PARTIAL BLOCKAGE IS SUSPECTED.  TEARDOWN, EVALUATION OF OIL COOLER R	EQUESTED.  BORESCOPE OF HOT SECTION DISTRESS, CK OF GEARBOX OIL FOR CONTAMINATION, IF ANYTHING FOUND, REAR CARBON SEAL W	ILL BE REPLACED. (NM052004040470) (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005042700020	20050427	00020	EU  	2005	4	27	2005FA0000325    	1	20041105	G	1430	A10212D	BOLT            			AIRBUS	A330  	A330*       	       	EU  										BYPASS VALVE	CRACKED         	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					FRO99BD					DOOR BYPASS VALVE WAS RETURNED FOR INVESTIGATION.  REASON FOR RETURN WAS ON PUSHBACK, FLIGHT CREW REPORTED GREEN RESERVO	IR LOW LEVEL, WHERE THE INVESTIGATION FOUND A LEAK ON DOOR BYPASS VALVE.  IDENTIFIED THAT BOLT HAD SHEARED.  INVESTIGATI	ON AT MFG INDICATED THAT INITIATING FORCE HAD RESULTED IN CRACK THAT PROPAGATED ACROSS BOLT SECTION, RESULTING IN FAILUR	E.  BOLTS COULD BE YIELDED WHEN TIGHTENED.  ALSO AFFECTED IS DOOR BYPASS VALVE. (K)			2	L	7	2 	4F			RT	A46NM
2005032800098	20050328	00098	EU  	2005	3	28	2005FA0000326    	1	20041105	G	5210	FRM530014D	BYPASS VALVE    			AIRBUS	A330  	A330*       	       	EU  										DOOR	LEAKING         	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										A DOOR BYPASS VALVE WAS RETURNED FOR INVESTIGATION.  THE REASON FOR RETURN WAS ON PUSHBACK, FLIGHT CREW REPORTED GREEN R	ESERVOIR LOW LEVEL,  WHERE THE INVESTIGATION FOUND A LEAK ON THE DOOR BYPASS VALVE.  INVESTIGATION IDENTIFIED THAT BOLT 	HAD SHEARED.  FURTHER INVESTIAGATION AT MFG, THAT AN INITIATING FORCE HAD RESULTED IN A CRACK THAT PROPAGATED ACROSS THE	 BOLT SECTION, RESULTING IN FAILURE.  BOLTS COULD BE YIELDED WHEN TIGHTENED.(K)			2	L	7	2 	4F			RT	A46NM
2005032800099	20050328	00099	EU  	2005	3	28	2005FA0000327    	1	20041105	G	5210	HTE960023053	BOLT            			AIRBUS	A330  	A330*       	       	EU  										BYPASS VALVE	CRACKED         	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					FR099BD					A DOOR BYPASS VALVE WAS RETURNED FOR INVESTIAGTION.  THE REASON FOR RETURN WAS ON PUSHBACK, FLIGHT CREW REPORTED GREEN R	ESERVOIR LOW LEVEL, WHERE THE INVESTIGATION FOUND A LEAK ON THE DOOR BYPASS VALVE.  INVESTIGATION IDENTIFIED THAT BOTL H	AD SHEARED.  FURTHER INVESTIAGTION INDICATED THAT INITAIATING FORCE HAD RESULTED IN A CRACK THAT PROPAGATED ACROSS THE B	OLT SECTION, RESULTING IN FAILURE.  THE BOLTS COULD BE YIELDED WHEN TIGHTENED.(K)			2	L	7	2 	4F			RT	A46NM
2005040400077	20050404	00077	EU  	2005	4	4	2005FA0000328    	1	20041105	G	1430		BOLT            			AIRBUS	A330  	A330*       	       	EU  										BYPASS VALVE	CRACKED         	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										A DOOR BYPASS VALVE WAS RETURNED FOR INVESTIAGTION.  THE REASON FOR RETURN WAS ON PUSHBACK, FLIGHT CREW REPORTED GREEN R	ESERVOIR LOW LEVEL, WHERE THE INVESTIGATION FOUND A LEAK ON THE DOOR BYPASS VALVE.  THE INVESTIGATION IDENTIFIED THAT BO	LT HAD SHEARED.  FURTHER INVESTIAGTION AT MFG INDICATED THAT INITIATING FORCE HAD RESULTED IN A CRACK THAT PROPAGATED AC	ROSS THE BOLT SECTION, RESULTING IN FAILURE.  THE BOLTS COULD BE YIELDED WHEN TIGHTENED.  (K)			2	L	7	2 	4F			RT	A46NM
2005040400026	20050404	00026		2005	4	4	2005FA0000329    	2	20041105	G	7314	568128300100	PUMP            			AIRBUS	A330  	A330*       	       	EU  										FUEL SYS	CORRODED        	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										A FUEL PUMP SHOWS EVIDENCE OF CAVITATIONAL EROSION ON A STRUCTURAL PILLAR WITHIN THE PUMP.  THIS PILLAR CONTAINS A PASSA	GEWAY FOR ELECTRICAL WIRES, WHICH FORMS PART OF THE MOTOR EXPLOSION CONTAINMENT ZONE.  THERE IS A CONCERN THAT THE EROSI	ON COULD MIGRATE TO THE PASSAGEWAY AND THEREFORE BREACH THE EXPLOSION CONTAINMENT ZONE.  MFG IS COMMUNITATING WITH AC MF	G. (K)			2	L	7	2 	4F			RT	A46NM
2005040100099	20050401	00099	SO  	2005	4	1	2005FA0000330    	1	20040806	G	3246	551792	WHEEL           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	NLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	8252Z	7639 				288116011	L913639A			NOSE WHEEL FLANGE BROKE OFF DURING TAXI.  CLOSE INSPECTION SHOW CRACK MIGHT HAVE STARTED FROM CORROSION UNDER THE FLANGE	 WHICH IS THE THINNEST PART OF THE WHEEL ASSY.  RECOMMEND INSPECTION ON HIGH TIME WHEELS.  ESPECIALLY ON AIRCRAFT WHICH 	DO NOT FLY FREQUENTLY.  (EA25200408022)				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2005042700021	20050427	00021	CE  	2005	4	27	2005FA0000331    	1	20040928	G	7500	973800011	SLEEVE          			BEECH 	200   	200BEECH    	1152920	CE  	LYC   	O320  	O320*       	41508	EA  					LT BLEED AIR	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05		13061				BP38				BLEED AIR COUPLING FAILED LT ENGINE NACELLE.  THIS PART IS ATHE FIRST COUPLING DOWN STREAM OF THE FLOW PAC.  THE HEAT GO	T TO IT, AGING AC ISSUE, 1983 MFG DATE.					1	L	7	2 	4T	3	O		A24CE   	E274
2005042700022	20050427	00022	GL  	2005	4	27	2005FA0000332    	1	20041221	G	7810		EXHAUST PIPE    			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	990P	254  				0945	917219			AIRCRAFT OWNER SQUAWKED MANIFOLD PRESSURE AT 11 PERCENT.  FOUND EXHAUST CRACKED AT NR 5 CYLINDER EXHAUST PORT.  CRACK EM	INATES FROM REAR OF MOUNTING FLANGE AND SPIRALS DOWN COUNTER CLOCKWISE SEVERAL INCHES FROM THERE.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2005042700025	20050427	00025	EU  	2005	4	27	2005FA0000333    	1	20041209	G	1420	3722514110	CONNECTOR       			AGUSTA	A109  	A109A2      	0260120	EU  										DME  R/T	VIBRATION       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										VIBRATION PROBLEM HAS BEEN IDENTIFIED WITH THE DISTANCE MEASURING EQUIPMENT (DME) RECEIVER-TRANSMITTER (RT) INSTALLED ON	 THE AIRCRAFT.  THIS PROBLEM RESULTS IN INTERMITTENT DME DISPLAY OR LOSS OF POWER TO THE DME INDICATOR.  THIS FAILURE OC	CURS AFTER APPROX EVERY 400 HOURS OF OPERATION AND IS THE RESULT OF VIBRATION BETWEEN THE DME RT UNIT AND THE ROTORCRAFT	 MOUNTING SURFACE.  THE DME RT UNIT IS HARD MOUNTED ON AN AVIONICS SHELF LOCATED IN THE TAILBOOM, AFT OF THE REAR BAGGAG	E COMPARTMENT.  VIBRATION BETWEEN THE AC HARNESS PLUG CONNECTOR AND THE DME RT MATING CONNECTOR RESULTS IN LOSS OF ELECT	RICAL CONTACT BETWEEN SOME OF THE CONNECTOR PINS.  PROBLEM CAN BE CORRECTED BY MOUNTING THE DME RT ON VIBRATION ISOLATOR	1	G	7	2 	3U				H7EU
2005040100060	20050401	00060		2005	4	1	2005FA0000334    	4	20041014	G	2562		BATTERY         			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300*       	17022	SO  					ELT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	6735A					28835				FOUND D (LARGE) SIZE DURACELL BATTERIES USED IN ELT`S EXPELLING AND CORRODED.  EXPIRATION DATE 2008						1	H	7	1 	3O	3	O	NT	3A12    	E253
2005033000033	20050330	00033		2005	3	30	2005FA0000335    	1	20041004	G	2410	ES4307	ROTOR           	ELECTROSYS  																ALTERNATOR	DEFECTIVE       	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					E074260					ALTERNATOR DEFECTIVE AS RECEIVED FROM MFG, ROTOR RUBBING ON STATOR WINDINGS.  THIS CONDITION COULD EASILY BE FLET WHEN T	URNING ALTERNATOR DRIVE SHAFT BY HAND. (K)
2005033000053	20050330	00053	NM  	2005	3	30	2005FA0000336    	1	20040203	G	2913	624022	ADAPTER         	VICKERS     		BOEING	747   	747*        	       	NM  										HYD PUMP	ERODED          	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					MX535816					EROSION AROUND STROKING PISTON PORT.  FLUID FLOW AGAINST SOFT METAL.  STRONGER MATERIAL FOR HOUSING. (MECHANIC - BSI, JO	B 192845) (K)					2	L	7	4 	4F			RT	A20WE
2005040100063	20050401	00063	CE  	2005	4	1	2005FA0000349    	1	20041220	G	7430	103572001	IGNITION SWITCH 			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	CARBONED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	3132W	2377 				CE477				ENGINE STOPPED RUNNING DURING TAXI TO RUNWAY.  INVESTIGATION SHOWED A LOT OF CARBON IN SWITCH CONTACTS.  (SW05200506081)						1	L	7	1 	3O	3	O		3A15    	E5CE
2005042700064	20050427	00064	CE  	2005	4	27	2005FA0000362    	1	20041117	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	07	1570A	245  				CE1333	830089R			PILOT SELECTED GEAR UP AND NOTHING HAPPENED.  LANDING GEAR WOULD NOT RETRACT.  MAINTENANCE TECHNICIAN TROUBLESHOOT GEAR 	SYSTEM AND FOUND THAT THE DYNAMIC RELAY WAS INTERMITTNET.  NO RECOMMENDATION AT THIS TIME. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE
2005040100094	20050401	00094	CE  	2005	4	1	2005FA0000365    	1	20041215	G	5711	052340050	SPAR            			CESSNA	172   	R172E       	2072413	CE  	CONT  	O360  	IO360D      	17025	SO  					LT WING	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7892N	15628				R1720283	01080462			WHILE REPLACING THE FLAP TRACK ASSY, A CRACK APPROXIMATELY 2 INCHES IN LENGTH AND RUNNING THROUGH THE LOWER RIVET HOLES 	WAS FOUND UNDER THE LT IB FLAP TRACK.  PROBABLE CAUSE WAS A FLAP OVERSPEED DURING FLIGHT.  (SO09200502861)					1	H	7	1 	3O	3	O		3A17    	E1CE
2005040100062	20050401	00062	CE  	2005	4	1	2005FA0000367    	1	20041129	G	5753	052323113	FLAP TRACK      			CESSNA	172   	R172E       	2072413	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	1P235	1P235*      	GL  	LT WING	WORN            	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SO	09	7892N					R1720283	553125D	LF001		WHILE FLAPS WERE BEING RETRACTED, THE LT IB FLAP ATTACH BRACKET CAUGHT ON THE WING COVE PANEL SUPPORT.  THIS CAUSED SUBS	TANTIAL DAMAGE TO THE COVE PANEL SUPPORT AS WELL AS THE ATTACH BRACKET.  CAUSE WAS DETERMINED TO BE WORN FLAP TRACKS.  T	HE FLAP TRACKS AND ROLLERS WERE REPLACED WITH NEW PARTS AND THE LT FLAP WAS REPLACED WITH A SERVICEABLE ASSY DUE TO LACK	 OF PART AT THE MFG FOR REPAIR.  SINCE MFG DOES NOT HAVE LIMITATIONS ON THEIR FLAP TRACKS, SUGGEST THAT THEY BE REMOVED 	AND REPLACED AT 5,000 HOUR INTERVALS. (K)		1	H	7	1 	3O	3	O		3A17    	E1CE	5	N	P12EA
2005042700069	20050427	00069	CE  	2005	4	27	2005FA0000368    	1	20040928	G	7110	055036125	SPRING          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALT AIR DOOR	MISSING         	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			SO	15	53570	743  				172S9397				ON RETURN TO BASE, PILOT REPORTED WHEN CLIMING TO 8000 PT ENGINE SURGED/POWER DROP 2 TIMES.  AIRCRAFT WAS DUE A PHASE 1 	INSPECTION.  WHILE INSPECTING THE ALT AIR DOOR, NOTICED THE DOOR STUCK IN THE OPEN POSITION.  FURTHER INSPECTION REVEALE	D THE SPRING THAT CONTROLS THE DOOR WAS MISSING FROM THE HINGE ASSY.  INSPECTED INSIDE OF  SERVO.  NO DAMAGE BUT DID NOT	 LOCATE THE SPRING.  THE DOOR SHOWS SIGNS OF WEAR ON SEALING EDGES.  FEEL THE SYSTEM IS WEAK AND NEEDS TO BE IMPROVED. (	K)		1	H	7	1 	3O	3	O	NT	3A12    	1E10
2005040100095	20050401	00095	    	2005	4	1	2005FA0000370    	1	20041101	G	3246	9543426	WHEEL           			AMD   	STC   	STCFALC50   	       	    	GARRTT	TFE731	TFE7312B    	 	WP  					NLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	38WP					292				MAINTENANCE CREW FIRST NOTICED TIRE SERVICE BECOMING MORE FREQUENT OVER THE PERIOD  OF 2 OR 3 DAYS.  TIRE PRESSURES WERE	 DROPPING APPROX 10 PERCENT TO 15 PERCENT OVERNIGHT.  SUBSEQUENT INSPECTION OF THE TIRE AND WHEEL ASSY REVEALED AIR ESCA	PING THROUGH THE CASTING ADJACENT THE RAISED VALVE CORE BOSS.  LIQUID LEAK DETECTOR ALSO CONFIRMED THE LEAK AND LOCATION	.  NOTE: SECOND WHEEL TO DEVELOP A LEAK IN SAME AREA, WAS RETURNED FOR EVALUATION INSPECTION AND THE DISPOSITION OF THIS	 WHEEL IS NOT KNOWN AT THIS TIME.  (K)		2	L	7	2 	4F	4	F		A46EU   	E6WE
2005040400017	20050404	00017	NM  	2005	4	4	2005FA0000371    	1	20041019	G	2910	4AS7118102503	B-NUT           			GULSTM	200   	200         	4500308	NM  										LT HYD SYS	SPLIT           	B			K5SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	363GA	438  				063				LT HYDRAULIC PRESSURE LINE IN AFT EQUIPMENT BAY SPLIT AT AFT B-NUT FITTING.  INSTALLATION WAS POST SB.  PROBABLE CAUSE W	AS STRESSED INSTALLATION AND VIBRATION.  (K)					2	L	7	2 	4F			RT	A53NM
2005033000036	20050330	00036	EU  	2005	3	30	2005FA0000372    	1	20041121	G	3213	ES12858501	HOUSING         			ISRAEL	1124  	1124        	4500102	EU  										NLG STRUT	CRACKED         	C			GONR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	730CA	8017 				295				AFTER LANDING, TAXIIED TO REPAIR SERVICE, THE NOSE STRUT BOTTOMS OUT, STOPPED AT RAMP.  EXITED AC, NOTED A LARGE PUDDLE 	OF HYDRAULIC FLUID AROUND NLG.  JACKED AC UP, NOTICED THE LARGE CRACK IN THE LOWER STRUT HOUSING, STARTING FROM BACK SID	E OF TORQUE KNEE ATTACH FITTING ON THE LOWER STRUT BODY.  REMOVED NLG ASSY, DISASSEMBLED, INSP PN E51L858501 INNER BODY 	AND PN 52 NBC2064YZP BEARING CRACKED.  THE CRACKS LOOKED LIKE THEY HAD STARTED BEFORE.  PROBABLE CAUSE: NOT DISCONNECTIN	G SICCORS PRIOR TO TOWING AC.  (SW01200502590)		2	M	7	2 	4F				A2SW
2005040400061	20050404	00061	SO  	2005	4	4	2005FA0000373    	1	20041015	G	5541	2072904	RIB             			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CORRODED        	D			HQ8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8544P	7000 				244001				DURING AN ANNUAL INSPECTION, MORE THAN NORMAL SURFACE CORROSION WAS FOUND ON THE RUDDER TAIL POST.  UPON DISASSEMBLY OF 	THE RUDDER,  DISSIMILAR METAL CORROSION WAS PRESENT WHERE THE STEEL STIFFENER ATTACHES TO THE LOWER RIB (PN 2072904).  (	WP07200505592) (K)				1	L	7	1 	3O	3	O		1A15    	E14EA
2005033000011	20050330	00011	SO  	2005	3	30	2005FA0000374    	1	20041015	G	5541	2072910	SPAR            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CRACKED         	D			HQ8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8544P					244001				DURING SERVICE OF AIRCRAFT THE RUDDER WAS REMOVED.  NOTHING WAS FOUND ABNORMAL.  REMOVAL OF THE UPPER RUDDER HINGE (PN 2	018300.  CRACKS WERE FOUND AT THE HINGE ATTACH POINT OF THE RUDDER SPAR (2072910).  (WP07200505589) (K)					1	L	7	1 	3O	3	O		1A15    	E14EA
2005040100096	20050401	00096	SO  	2005	4	1	2005FA0000375    	1	20041015	G	5541	2072910	SPAR            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CRACKED         	D			HQ8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9180P					244670				DURING SERVICE OF THE AIRCRAFT THE RUDDER WAS REMOVED.  NOTHING WAS FOUND ABNORMAL.  REMOVAL OF THE UPPER RUDDER HINGE (	PN 2018300).  CRACKS WERE FOUND AT THE HINGE ATTACH POINT OF THE RUDDER SPAR (2072910). (K)					1	L	7	1 	3O	3	O		1A15    	E14EA
2005040100039	20050401	00039	SO  	2005	4	1	2005FA0000378    	1	20041124	G	2497		WIRE            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	SPEY  	SPEY51114   	54523	EU  					CABIN CB PANEL	PINCHED         	B			ACNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	477JB					1214				UPON REPLACEMENT/ UPGRADE OF A CIRCUIT BREAKER IN THE CABIN SERVICES CIRCUIT BREAKER PANEL, IN THE RT RADIO RACK AT FS 1	10, A 20 GA WIRE WAS FOUND PINCHED AND HAD PREVIOUSLY SHORTED TO THE FACE PLATE LEAVING A SCORCH MARK ABOUT THE SIZE OF 	A DIME.  THE WIRE WAS SUBSEQUENTLY REPAIRED, PROPERLY STOWED AND UNIT APPROVED FOR RETURN TO SERVICE.  REF GAC DWG NR LC	41 390035-01 - L MAIN UNSEITCHED WIRE NR 1XX102D12 FROM TB1.  SUGGEST TECH TAKE EXTRA CARE IN THE RE-MOUNTING OF THIS SE	RVICE PANEL TO AVOID CATCHING WIRES ON THE AFT SUPPORT BRACKETS. (K)		2	L	7	2 	4F	4	F	RT	A12EA   	E2EU
2005040100100	20050401	00100	CE  	2005	4	1	2005FA0000379    	1	20040928	G	5511	08322502	SPAR            			CESSNA	310   	310R        	2074245	CE  										STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	3556G	5067 				310R0869				FOUND THE MAIN (REAR) STABILIZER SPAR WITH SEVERE CORROSION AT THE LOCATIONS WHERE THE BONDING SCREWS WERE ATTACHED. (K)						1	L	7	2 	3O				3A10
2005040400095	20050404	00095	SO  	2005	4	4	2005FA0000380    	1	20041215	G	3220	487484	SPRING          			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	MISSING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	32749					28R7535085				SPRINGS (PN487-484 AND PN 487-483) ON THE NOSE GEAR RETRACTION LINK ASSY FAILED, LETTING THE ARM ASSY SWING AROUND AND J	AM BETWEEN THE DOWNLOCK PIN AND THE MUFFLER.  (NM07200502447)					1	L	7	1 	3O	3	O		2A13    	1E10
2005040400044	20050404	00044	SO  	2005	4	4	2005FA0000381    	1	20041215	G	3220	487483	SPRING          			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	MISSING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	32749					28R7535085				SPRINGS (PN487-484 AND PN487-483) ON THE NOSE GEAR RETRACTION LINK ASSY FAILED, LETTING THE ARM ASSY SWING AROUND AND JA	M BETWEEN THE DOWNLOCK PIN AND THE MUFFLER.  (NM07200502447) (K)					1	L	7	1 	3O	3	O		2A13    	1E10
2005042700089	20050427	00089	SO  	2005	4	27	2005FA0000391    	1	20041221	G	5350	8644606	SKIN            	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NOSE CONE	CRACKED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2202X	8034 			8644638	447995278				DURING AN ANNUAL INSPECTION OF THE AIRCRAFT THE NOSE CONE ASSY WAS FOUND TO HAVE A CRACK IN THE TOP SKIN.  PROBABLE CAUS	E OF CRACKING OF THE NOSE CONE ASSY IS UNKNOWN.  THE NOSE CONE WAS REPAIRED AND AIRCRAFT RETURNED TO SERVICE.  OF 3 AIRC	RAFT INSPECTED, ALL 3 HAD CRACKS IN THE SAME SKIN IN THE SAME LOCATION.  (SO09200503396) (K)				1	L	7	2 	3O	3	O		A19S0   	E286
2005040100069	20050401	00069	SO  	2005	4	1	2005FA0000392    	1	20041221	G	5350	8644606	SKIN            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NOSE CONE	CRACKED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2247B					447995108				DURING AN ANNUAL INSPECTION OF THE AIRCRAFT, THE NOSE CONE ASSY WAS FOUND TO HAVE A CRAK IN THE TOP SKIN.  PROBABLE CAUS	E OF CRACKING OF THE NOSE CONE ASSY IS UNKNOWN.  THE NOSE CONE WAS REPAIRED AND AIRCAFT RETURNED TO SERVICE.  (SO0920050	3394) (K)				1	L	7	2 	3O	3	O		A19S0   	E286
2005042700090	20050427	00090	SO  	2005	4	27	2005FA0000393    	1	20041221	G	5350	8644606	SKIN            	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O320  	O320*       	41508	EA  					NOSE CONE	CRACKED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	3047U	7707 			8644638	447995262				DURING AN ANNUAL INSPECTION OF THE AIRCRAFT THE NOSE CONE ASSY WAS FOUND TO HAVE A CRACK IN THE TOP SKIN.  PROBABLE CAUS	E OF CRACKING OF THE NOSE CONE ASSY IS UNKNOWN.  THE NOSE CONE WAS REPAIRED AND AIRCRAFT RETURNED TO SERVICE.  (SO092005	03395) (K)				1	L	7	2 	3O	3	O		A19S0   	E274
2005032800037	20050328	00037	EA  	2005	3	28	2005FA0000411    	2	20041031	G	8520	SL3601SC	PISTON RING     			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	4238F					287715010				ON NIGHT IFR FLIGHT, DEPARTED WITH 7.5 QTS OF OIL IN THE ENGINE.  WHEN ARRIVED AT DESTINATION 1.4 HOURS LATER AND PERFOR	MED A POST FLIGHT INSPECTION, FOUND THAT THE CRANKCASE WAS DOWN 4 QUARTS OF OIL AND THERE WAS NO SIGN OF AN OIL LEAK.  U	PON INSPECTION, FOUND THE NR 3 CYLINDER TO BE HEAVILY CONTAMINATED WITH OIL.  THE CYLINDER WAS REMOVED AND FOUND THAT TH	E OIL CONTROL RING WAS BROKEN.  THE CYLINDER WAS INSPECTED NEW RINGS WERE INSTALLED AND THE AIRCRAFT WAS RETURNED BACK T	O SERVICE.  NOW THIS SHOULDN`T HAPPEN ON BRAND NEW CYLINDERS WITH 200 HOURS ON THEM.  THE CYLINDERS WERE BY MFG, ALSO RI	GS WERE PN SL-3601-SC, MFG DATE 10/1/2002. (K)	1	L	7	1 	3O	3	O		2A13    	E274
2005040400034	20050404	00034	EA  	2005	4	4	2005FA0000412    	2	20041226	G	8520	SL3601SC	PISTON RING     			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	4238F					287715010				CROSS COUNTRY FLT, HEADED TO 2ND FUEL STOP, HEARD A SLIGHT RPM CHANGE IN ENGINE THAT WAS INTERMITTENT.  UPON LANDING, PE	RFORMED MAG CHECK AND ONE MAG WAS A LITTLE ROUGH, HAD THE PLUGS PULLED AND FOUND THAT THE PLUG ON NR 4 CYLINDER WAS FOUL	ED WITH TRACES OF OIL AND LEAD.  PLUGS WERE CLEANED AND REINSTALLED.  TO BE ON SAFE SIDE, JUST IN CASE HAD A 2ND OIL RIN	G FAILURE, CHANGED FLIGHT TO CHECK OIL CONSUMPTION.  UPON LANDING,  FOUND IT HAD CONSUMED OVER 3 QUARTS OF OIL.  HAD CYL	INDER PULLED AND FOUND THE OIL CONTROL RING BROKEN.  THIS WAS 2ND RING TO FAIL IN LESS THAN 220 HOURS.  RING WAS THE SAM	E MANDATE AS THE PREVIOUS RING THAT FAILED.  BELIEVE BAD BATCH OF RINGS LUCKY IT WAS CAUGHT BEFORE ENG FAILURE. (K)	1	L	7	1 	3O	3	O		2A13    	E274
2005040100105	20050401	00105	NE  	2005	4	1	2005FA0000422    	2	20040819	G	7261	51G186	CARBON SEAL     			BOEING	747   	747*        	       	NM  	PWA   	PW4062	PW4062      	 	NE  					ENGINE	FAILED          	B			P0ER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		26   					729183			FAILED CARBON SEAL, RESULTING IN LOSS OF OIL, IFSD AND ATB.  (NE03200504012)						2	L	7	4 	4F	4	F	RT	A20WE   	E24NE
2005040400093	20050404	00093	CE  	2005	4	4	2005FA0000423    	1	20041217	G	8011	S24432	CONTACTOR       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	TSIO520M    	17040	SO  					STARTER	FAILED          	B			RDDR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			WP	21	PKMPZ	27   			0428008	U20606130				STARTER CONTACTOR DID NOT DISENGAGE AFTER ENGINE START.  THIS RESULTED IN FAILURE OF THE STARTER AS WELL.  SITUATION DID	 NOT BECOME APPARENT UNTIL AFTER TAKEOFF.  PERHAPS BECAUSE AT HIGH POWER SETTINGS THE ALTERNATOR PRODUCED MAXIMUM POWER 	AND AT HIGH SPEED THE STARTER MOTOR WOULD DRAW FEWER AMPS THAN AT LOW SPEED, ALLOWING THE BUS VOLTAGE TO RISE AND ILLUMI	NATE THE LAMP BRIGHTER.  MFG HAS BEGUN SUPPLYING A COMPACT, LIGHTWEIGHT STARTER ON NEW ENGINE.  THIS AC HAD FACTORY NEW 	ENGINE INSTALLED 21.7 HOURS PRIOR TO FAILURE.  INVESTIGATION INDICATES LIGHTWEIGHT STARTERS HAVE HIGHER CURRENT DRAW THA	N LARGER STARTER USED PREVIOUSLY.  MFG CONTACTOR CAN NOT HANDLE LOAD.  REMOVED AND REPLACED STARTER CONTACTORS. (K)	1	H	7	1 	3O	3	O		A4CE    	E8CE
2005042700128	20050427	00128	CE  	2005	4	27	2005FA0000424    	1	20041217	G	8011	S24432	CONTACTOR       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	TSIO520M    	17040	SO  					STARTER	FAILED          	B			RDDR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			WP	23	PKMAU	23   				U20606365				STARTER CONTACTOR DID NOT DISENGAGE AFTER ENGINE START.  RESULTED IN STARTER FAILURE.  SITUATION DID NOT BECOME APPARENT	 UNTIL  AFTER TAKEOFF.  STARTER ENGAGED WARNING LIGHT INSTALLED BUT DID NOT INDICATE CLEARLY UNTIL AFTER TAKEOFF.  BECAU	SE AT HIGH POWER SETTINGS ALTERNATOR PRODUCED MAXIMUM PWR & AT HIGH SPEED STARTER MOTOR WOULD DRAW FEWER AMPS THAN AT LO	W SPEED, ALLOWING BUSS VOLTAGE TO RISE AND ILLUMINATE THE LAMP BRIGHTER.  MFG HAS BEGUN SUPPLYING COMPACT, LIGHTWEIGHT S	TARTER ON NEW ENGINES.  ENGINE INSTALLED 23.7 HOUR PRIOR.  INVESTIGATION INDICATES LIGHTWEIGHT STARTERS HAVE A HIGH CURR	ENT DRAW THAN LARGER STARTER.  SUSPECT MFG CONTACTOR CANNOT HANDLE LOAD.  REMOVED AND REPLACED STARTER CONTACTORS. (K)	1	H	7	1 	3O	3	O		A4CE    	E8CE
2005042700130	20050427	00130		2005	4	27	2005FA0000426    	1	20040511	G	6100	B4460	PIN             													MCAULY	3A32C	3A32C76     	GL  	PROPELLER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99								801412		ON MAY 17, 2004, AUTHORIZED BY NTSB TO DO A TEARDOWN ONLY ON PROPELLER.  UPON WHICH (PN 134460) ACTUATING PIN, WAS FOUND	 BROKEN IN HALF; START OF THREADS.  PARTS INVOLVED WERE TAKEN BY FSDO.  FSDO FORWARDED THEM TO NTSB FOR INVESTIGATION.  	CANNOT COMMENT ON PROBABLE CAUSE.														5	C	P21EA
2005033000041	20050330	00041	GL  	2005	3	30	2005FA0000434    	2	20041031	G	7200		ENGINE          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  						MAKING METAL    	B			EOOR	A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	NR	NOT REPORTED   	1			AL	03	C6PHC					180257D	CAE833793			PILOT HAD ENGINE CHIP LIGHT ILLUMINATION FOLLOWED ALMOST IMMEDIATELY WITH A NOISE/VIBRATION, THEN A POWER LOSS/ DECEL.  	AC LANDED WITHOUT INCIDENT AND PILOT HAD TO SHUT OFF THE ENGINE.  CHIP PLUGS AND OIL FILTERS WERE CONTAMINATED WITH META	L.  DISASSEMBLY OF ENGINE AND ENGINE GEARBOX REVEALED A FAILURE OF THE 2.5 BEARING TO A POINT THAT .33 THE CIRCUMFERENCE	 OF THE SAG SHAFT, INNER RACE, WAS GOUGED TO AN APPROX DEPTH OF .040 INCH TO .045 INCH.  NO OTHER SOURCE OF METAL WAS FO	UND.		1	G	7	1 	3U	3	U		H3WE    	E4CE
2005033000042	20050330	00042		2005	3	30	2005FA0000435    	4	20041021	G	3420	8350006213	AHRS            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	4485X	783  				327640026				THE AHRS INSTALLED AS PART OF THE FLIGHT SYSTEMS, EFIS-SV STC NR SA02203AK FAILED- WAS PROVIDING NO HEADING INFORMATION.	  THE CIRCUIT BREAKER HAD TO BE PULLED TO KEEP THE GPS ON LINE.  (AL05200500173) (K)					1	L	7	1 	3O	3	O		A3SO    	E14EA
2005033000043	20050330	00043		2005	3	30	2005FA0000436    	4	20041028	G	3417	962830A1S8	ADC             			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					COCKPIT	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	4485X	174  				327640026				AIR DATA COMPUTER REPORTING 300 FEET & ERROR.  UNIT INSTALLED AS PART OF FLIGHT SYSTEMS, INC  STC NR SA02203AK.  (AL0520	0500176) (K)					1	L	7	1 	3O	3	O		A3SO    	1E4
2005033000045	20050330	00045		2005	3	30	2005FA0000437    	4	20040816	G	3417	962830A1S8	ADC             			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	1999U	563  				18501768				ADC PROVIDING ERRONEOUS HEADING AND ALTITUDE READINGS.  ADC INSTALLED AS PART OF FLIGHT SYSTEM EFIS-SV SYSTEM.  UNDER ST	C NR SA02203AK.  (K)					1	H	7	1 	3O	3	O		3A24    	E5CE
2005033000035	20050330	00035		2005	3	30	2005FA0000438    	4	20040616	G	3420	8350006214	AHRS            			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					COCKPIT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8200M					328006048				AHRS REPORTING TO IDU WANDERING HEADING AND ERRONEOUS ACCELL/DECELERATION.  UNIT INSTALLED AS PART OF FLIGHT SYSTEMS, IN	C EFIS-SV SYSTEM.  (K)					1	L	7	1 	3O	3	O		A3SO    	1E4
2005040100011	20050401	00011		2005	4	1	2005FA0000439    	4	20041110	G	3417	962830A1S8	ADC             			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					COCKPIT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9417G	1043 				U20601617				ALTITUDE WAS 100 FEET OFF.  UNIT INSTALLED AS PRAT OF THE FLIGHT SYSTEM, INC EFIS-SV IAW STC NR SA02203AK.  (AL052005001	75) (K)					1	H	7	1 	3O	3	O		A4CE    	E5CE
2005040100073	20050401	00073		2005	4	1	2005FA0000440    	4	20041028	G	3417	962830A1S8	ADC             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	331AK	690  				208B0739				NR 2 ADC UNIT REPORTING 350 FEET ERROR.  UNIT INSTALLED AS PART OF THE FLIGHT SYSTEMS, INC EFIS-SV SYSTEM UNDER STC NR S	A02203AK.  (AL05200500174) (K)					1	H	7	1 	3T	3	T		A37CE   	E2NE
2005040400037	20050404	00037	SO  	2005	4	4	2005FA0000441    	1	20040915	G	3110	401405000101	DISPLAY         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					INTRUMENT PANEL	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8127Q	291  				327940269				THE INSTRUMENT DISPLAY UNIT (IDU) PRIMARY FLIGHT DISPLAY INSTALLED AS PART OF FLIGHT SYSTEM, INC EFIS-SV SYSTEM FAILED. 	 DURING BOOT-UP, THE DISPLAY SHOWED VERTICAL LINES ACROSS THE SCREEN.  (K)					1	L	7	1 	3O	3	O		A3SO    	1E4
2005040100103	20050401	00103	CE  	2005	4	1	2005FA0000442    	1	20041108	G	5330		SKIN            			BEECH 	58    	58          	1152740	CE  										FUSLAGE	CORRODED        	B			VIBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	1648W					TH251				PERFORMED INCOMING INSPECTION OF AC FOR REPAIR OF CORROSION AT DOORWAY ENTRY.  UPON INSPECTION, EXTENSIVE CORROSION WAS 	FOUND AT VARIOUS LOCATIONS WHERE INSULATION WAS FACTORY INSTALLED.  THIS INSULATION WAS FOUND TO BE DAMP AND HAD EXPOSED	 EDGES.  THIS RESULTED IN MAY STRINGERS BEING REPLACED ALONG THE SIDES OF THE FUSELAGE AS WELL AS FUSELAGE SKINS FOR AN 	AREA OF ABOUT 3 FT X 3 FT ON EACH SIDE OF THE AIRCRAFT.  EXTENSIVE CORROSION WAS FOUND AT THE AFT WING SPAR CARRY-THROUG	H STRUCTURE AND THE CO-PILOTS ENTRY DOOR FRAME.		1	L	7	2 	3O				3A16
2005040100108	20050401	00108	SO  	2005	4	1	2005FA0000444    	2	20041223	G	8530	637781	EXHAUST VALVE   	CONT        		CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NR 1 CYLINDER	BROKEN          	B			I3PD	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	761QK				4182104	21062432	512584			PILOT REPORTED HEARING A BANG AND NOTICED AN ENGINE VIBRATION AND REDUCTION IN TEMPERATURE ON HIS ENGINE MONITOR.  PILOT	 REPORTED AN EMERGENCY TO ATC AND MADE A SAFE LANDING AT AIRPORT.  MAINTENANCE PERFORMED AN ENGINE COMPRESSION TEST AND 	FOUND CYLINDER NR 1 HAD -0-(ZERO) COMPRESSION.  REMOVED CYLINDER NR1 AND FOUND EXHAUST VALVE HEAD MISSING APPROX 40 PERC	ENT.  THE MISSING PIECE OF THE EXHAUST VALVE WAS FOUND IN THE INTAKE TUBE AND HAD CONTACTED THE TOP OF THE PISTON AND TO	P OF THE CYLINDER HEAD.  PROBABLE CAUSE OF FAILURE IS UNDETERMINED.		1	H	7	1 	3O	3	O		3A21    	E8CE
2005040100038	20050401	00038	EU  	2005	4	1	2005FA0000460    	1	20040517	G	2497		WIRE HARNESS    			ISRAEL	1124  	1124        	4500102	EU  										COCKPIT ENTRY	ARCED           	B			XZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	900VP					289				FOUND WIRE HARNESS CHAFFING AND ARCING IN THE AREA OF THE COCKPIT ENTRANCE OVERHEAD.  THIS PROBLEM HAS BEEN ADDRESSED BY	 SB 1124-24A-154.  CONSIDERATION SHOULD BE GIVEN TO MAKE THIS AD.  DUE TO POTENTIAL OF IN-FLIGHT SMOKE AND FIRE HAZZARD.	 (K)				2	M	7	2 	4F				A2SW
2005050300258	20050503	00258	CE  	2005	5	3	2005FA0000477    	1	20041122	G	3233		ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15*       	52060	NE  					NOSE GEAR	WORN            	B			MDOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	228CC					5500133				RECEIVED SECOND NLG TO REPLACE THE FIRST ONE SENT TO US OUT OF LIMITS AND FOUND THE SAME PROBLEM.  FOUND TO HAVE EXCESSI	VE IN LINE MOVEMENT OF THE LOCKING MECHANISM.  MOVEMENT IN EXCESS OF .1250 INCH, MAX ALLOWED .035. (K)					1	L	7	2 	4F	4	T		A22CE   	E1NE
2005041400105	20050414	00105	SO  	2005	4	14	2005FA0000489    	1	20041215	G	1430		RIVET           			GULSTM	G1159 	G1159B      	3953535	SO  										FUSELAGE	LOOSE           	B			N38R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	211SJ					75				UPON X-RAY INSPECTION OF AIRCRAFT FOR A 4000 LANDING INSPECTION, FOUND SEVERAL WORKING RIVETS AROUND CABIN WINDOWS AS IN	DICATED.  LT NR 3 WINDOW; ONE (1) WORKING RIVET, LT NR 4 WINDOW; FOUR (4) WORKING RIVETS, LT NR 5 WINDOW, ONE (1) WORKIN	G RIVET, RT NR 3 WINDOW, TWO (2) WORKING RIVETS; RT NR 4 WINDOW, ONE (1) WORKING RIVET; RT NR 5 WINDOW, TWO (2) WORKING 	RIVETS.  ALL DISCREPANT RIVETS WERE EITHER REPLACED OR REBUCKED FOR SATISFACTORY SECURITY. (K)			2	L	7	2 	4F			RT	A12EA
2005050500067	20050505	00067	SO  	2005	5	5	2005FA0000522    	1	20041107	G	8011		DRIVE ASSY      			PIPER 	PA28  	PA28161     	7102803	SO  										STARTER	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	151LH	451  	326  		D0701748112	2842194				STARTER FAILED AFTER 326.8 HRS SINCE REPAIR. THIS IS THE THIRD TIME THIS S/N STARTER HAS FAILED, INCLUDING BEING REPAIRE	D.  SAME FAILURE EACH TIME- BENDIX DRIVE JAMS.					1	L	7	1 	3O				2A13
2005050500071	20050505	00071	SO  	2005	5	5	2005FA0000534    	1	20040911	G	8011		DRIVE ASSY      			PIPER 	PA28  	PA28161     	7102803	SO  										STARTER	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	152LH	248  	248  		D081443112	2842195				NEW STARTER FAILED AFTER 248.9 HOURS- BENDIX DRIVE JAMS.						1	L	7	1 	3O				2A13
2005050500061	20050505	00061	SO  	2005	5	5	2005FA0000536    	1	20040212	G	8011	MHB6016	STARTER         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	11	151LH	125  	48   			2842194				STARTER FAILED AFTER 48.1 HOURS SINCE REPAIR FOR  SB A-112.						1	L	7	1 	3O	3	O		2A13    	E274
2005050400085	20050504	00085	SO  	2005	5	4	2005FA0000538    	1	20041118	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	FAILED          	D				K				NONE                    				L	W		NO TEST                   	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			EA	15	146LH	76   	76   			2844102	L3109151A			NEW REPLACEMENT STARTER FAILED 76.4 HOURS AFTER INSTALLATION. BENDIX DRIVE JAMS, STARTER WILL NOT OPERATE. STARTER IS NO	T EFFECTED BY SB A-112. 4TH STARTER CHANGE ON AIRPLANE, 3RD DUE TO MECHANICAL FAILURE ALL WITHIN 205 HOURS (APPROX. 1 YE	AR). REVERTED TO HEAVY STARTER MODEL P/N MZ-4222.				1	L	7	1 	3O	3	O		2A13    	1E10
2005050400077	20050504	00077	SO  	2005	5	4	2005FA0000561    	1	20040224	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	FAILED          	D				K				NONE                    				W	L		INADEQUATE Q C            	NO TEST                   		TX	TAXI/GRND HDL  	1			EA	15	146LH	123  	52   			2844102	L3109151A			STARTER REPAIRED W/O 6883 SB A-112. FAILED IN SERVICE 52.1 HOURS LATER. FAILURE DUE TO PARTS.						1	L	7	1 	3O	3	O		2A13    	1E10
2005052500040	20050525	00040	EU  	2005	5	25	2005FA0000659    	1	20040810	G	6410	355A12003108	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	DELAMINATED     	B			EHAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	353EV	531  				2444				DURING A ROUTINE ALF INSPECTION, THE MECHANIC DISCOVERED DELAMINATION ON THE TAILROTOR BLADE.  THE DELAMINATED TRIM TAB 	WAS APPROX 3 INCHES LONG AND 2 INCHES IB OF THE TRIM TAB RIVET.  THE TAILROTOR ASSY WAS REMOVED AND SENT TO A BLADE REPA	IR FACILITY FOR EVALUATION AND REPAIR.  (K)				1	G	7	1 	3U	3	U		H9EU    	E19EU
2005052500041	20050525	00041	EU  	2005	5	25	2005FA0000660    	1	20040912	G	6410	355A12003108	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	CRACKED         	B			EHAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	350EV	2697 				2961	9034			TAIL ROTOR BLADE, FOUND CRACK APPROX 3.2500 INCH LONG, RUNNING PARALLEL TO TRIM TAB.  (K)						1	G	7	1 	3U	3	U		H9EU    	E19EU
2005052500044	20050525	00044	EU  	2005	5	25	2005FA0000661    	1	20040913	G	6410	355A12003108	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	DELAMINATED     	B			EHAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	350EV	2697 				2961				DURING A ROUTINE ALF INSPECTION, THE MECHANIC DISCOVERED DELAMINATION ON THE TAILROTOR BLADE.  THE TAILROTOR SHOWED NO S	IGNS OF IMPACT.  THE DELAMINATED TRIM TAB WAS APPROXIMATELY 3 INCHES LONG AND 2 INCHES IB OF THE TRIM TAB RIVET.  THE TA	ILROTOR ASSY WAS REMOVED AND SENT TO MFG FOR EVALUATION AND REPAIR.  (K)				1	G	7	1 	3U	3	U		H9EU    	E19EU
2005052500140	20050525	00140	GL  	2005	5	25	2005FA0000676    	3	20041110	G	6114		DOWEL PIN       			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER HUB	SHEARED         	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	620ZE	3670 				421C0301		771538		PROPELLER OVERHAULED AND REINSTALLED.  TEST FLIGHT REVEALED VIBRATION.  DETERMINED TO BE SHEARED DOWEL PINS CAUSING LOOS	E PROPELLER TO CRANK PROP DRIVE SHAFT.  (K)					1	L	7	2 	3O				A7CE    		5	C	P45GL
2005052500170	20050525	00170	SO  	2005	5	25	2005FA0000677    	2	20041110	G	8520	TCM634503	MAIN BEARING    			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NR 2	DELAMINATED     	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	9SD	321  				421B0888	235244L			BEARING CRACKED AND DELAMINATED IN NR2 MAIN BEARING SADDLE.  HEATED CRACKS IN NR2 MAIN JOURNAL.  THIS HAS BEEN NOTED ON 	OTHER ENGINES WE HAVE DISASSEMBLED.  BEARING BORN DATE 10-02.  THIS WAS A NEW CASE AND NO SIGNS OF FRETTING ON THE CASE 	HALF. (K)				1	L	7	2 	3O	3	O		A7CE    	E7CE
2005052500177	20050525	00177	SO  	2005	5	25	2005FA0000678    	2	20041227	G	7414	4720N107891	MAGNETO         			NAMER 	F51   	P51D        	6402304	WP  	PCKARD	V1650 	V1650*      	49001	SO  					LT	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	51JB					4473029A				LT MAGNETO FAILED CAUSING ENGINE DETONATION.  SUGGEST CLOSER INSPECTION, INTERVAL OF MAGNETO`S OPERATION.  (K)						1	L	7	1 	4V	4	V		L113    	EXP4V
2005052500178	20050525	00178		2005	5	25	2005FA0000679    	4	20041220	G	2561	GA12P0201	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED.  MFG RECOMMENDED CELL PRESSURE TEST.  DOM: MAY 1981.  (K)
2005052500180	20050525	00180	NM  	2005	5	25	2005FA0000681    	1	20041229	G	3213		STRUT           			LANCAR	LC42  	LC42550FG   	5150002	NM  	CONT  	O550  	IO550*      	 	SO  					NLG	LOOSE           	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	191DW	127  				42022				DURING INSPECTION OF NOSE GEAR STRUT HARDWARE IT WAS FOUND TO HAVE LOOSE STRUT MOUNTING HARDWARE. (K)						1	L	7	1 	3O	3	O	RT	A00003SE	E3SO
2005052500193	20050525	00193	EU  	2005	5	25	2005FA0000683    	1	20041124	G	7600	DHS77240030	SWITCH          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	BINDING         	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	17	747R					3341				SWITCH DOES NOT FULLY EXTEND, CAUSING ENGINE TO REMAIN AT IDLE AFTER TWIST GRIP IS PLACE BACK INTO THE (VOL) POSITION DU	RING IN-FLIGHT EMERGENCY PROCEDURE TRAINING.  REMOVED FROM SERVICE, REPLACED WITH NEW. (K)					1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005052500194	20050525	00194	CE  	2005	5	25	2005FA0000684    	1	20041111	G	2910	AE1011923H0152	HOSE            			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					HYDRAULIC SYS	RUPTURED        	B			CNQ3	O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			GL	13	521FP	2892 				7500016				HYDRAULIC HOSE RUPTURED IN AREA ADJACENT TO SLEEVE ALLOWING LOSS OF HYDRAULIC FLUID TO (SYSTEM A).  HOSE BEING SENT TO M	FG FOR EVALUATION.  (GL13200505055) (K)					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH
2005052500195	20050525	00195	EA  	2005	5	25	2005FA0000685    	2	20041217	G	8520	LW10346	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	FAILED          	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	525AA		225  			318052111				CRANKSHAFT BROKEN AT NR3 MAIN, THEN AT 2 OTHER PLACES. (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA
2005052500199	20050525	00199	CE  	2005	5	25	2005FA0000688    	1	20041222	G	3233	9581001727	ACTUATOR        			BEECH 	58    	58          	1152740	CE  										MLG	LEAKING         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	23PC	152  				TH2071				DURING FIRST ANNUAL INSPECTION, NOTED OIL PUDDLED UNDER LANDING GEAR ACTUATOR ASSY AND ACTUATOR OIL LEVEL LOW.  REMOVED 	ACTUATOR ASSY FOR LEAK INVESTIGATION AND FOUND SCREWS SECURING UPPER AND LOWER ACTUATOR HOUSINGS TOGETHER LOOSE (WERE AB	LE TO LOOSEN WITH FINGER PRESSURE ONLY).  MINIMAL SEALANT NOTED ON ACTUATOR HOUSING MATING SURFACES, MOSTLY BARE METAL. 	 ALSO FOUND SECTOR GEAR STOP NOT SEALED TO HOUSING, OIL APPEARS TO HAVE GOTTEN BETWEEN STOP AND MINIMAL SEALANT APPLIED.	  REASSEMBLED ACTUATOR ASSY IAW SRM,  ACTUATOR O/H INSTRUCTIONS, NO EXTERNAL LEAKAGE NOTED.  (K)		1	L	7	2 	3O				3A16
2005052500200	20050525	00200	CE  	2005	5	25	2005FA0000689    	1	20041222	G	5343	9511003119	SUPPORT ANGLE   			BEECH 	58    	58          	1152740	CE  										MLG	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	23PC	152  				TH2071				DURING ANNUAL INSPECTION FOUND SUPPORT ANGLE WHERE LT IB MAIN GEAR DOOR AFT HINGE IS ATTACHED, CRACKED.  PROBLEM NOTED O	N OTHER LOW-TIME LATE SERIAL NUMBER BE 58 SERIES AIRCRAFT.  PROBLEM SEEMS TO BE RELATED TO CHANGE TO ONE-PIECE MACHINED 	IB DOORS DUE TO STIFFNESS OF NEWER STYLE DOORS COMPARED TO THE OLDER BUILT-UP RIVETED SHEET METAL CONSTRUCTION DOORS.  S	TRESS FROM DOOR AIR LOADS AND/OR RETRACTED POSITION TENSION SEEMS TO BE BEING TRANSFERRED INTO IB DOOR HINGE SUPPORT STR	UCTURE. (K)		1	L	7	2 	3O				3A16
2005052500201	20050525	00201	CE  	2005	5	25	2005FA0000690    	1	20041222	G	5343	9511003119	SUPPORT ANGLE   			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					MLG	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	158WC	219  				TH2008				DURING ANNUAL INSPECTION FOUND SUPPORT ANGLE WHERE LT IB MAIN GEAR DOOR HINGE IS ATTACHED, CRACKED.  PART WAS REPLACED 2	 YEARS PREVIOUSLY FOR SAME OCCURRENCE.  ALSO FOUND ANGLE ON ADJACENT LT IB DOOR HINGE SUPPORT CRACKED, AS WELL AS SUPPOR	T ANGLES FOR RT MAIN GEAR DOOR HINGE BRACKETS.  PROBLEM SEEMS TO BE RELATED TO CHANGE TO 1-PIECE MACHINED IB DOORS DUE T	O STIFFNESS OF NEWER STYLE DOORS COMPARED TO THE OLDER BUILT-UP RIVETED SHEET METAL CONSTRUCTION DOORS, STRESSES SEEM TO	 BE TRANSFERRED INTO IB DOOR HINGE SUPPORT STRUCTURE.  (K)		1	L	7	2 	3O	3	O		3A16    	E3SO
2005052600071	20050526	00071	SW  	2005	5	26	2005FA0000694    	1	20041105	G	5712		RIB             			BBAVIA	7     	7AC         	2110102	SW  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	83258					1922				THE FIRST WING RIB LOCATED IB OF THE AILERONS WAS FOUND CRACKED ALONG THE RADIUS OF THE ATTACH TAB WHERE THE RIB IS SECU	RED TO THE AFT SPAR.  THIS AIRCRAFT WAS SUBJECTED TO YEARS OF PREVAILING WINDS QUARTERING AGAINST THE T/E OF THE LT AILE	RON.  NO GUST LOCKS WERE UTILIZED.  THE RIBS WERE REPAIRED AND THE WINGS RECOVERED.  THE OWNER HAS ERECTED A MORE SUITAB	LE SHELTER.  (GL11200505059) (K)			1	H	7	1 	3O				A759
2005052600079	20050526	00079	CE  	2005	5	26	2005FA0000695    	1	20040608	G	5711	5147	SPAR            			BBAVIA	11    	11CC        	9140404	CE  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	4159E	835  				11CC64				A CRACK IN THE REAR SPAR OF THE RT WING WAS FOUND.  THIS CRACK IS RUNNING WITH THE WOOD GRAIN,  AND APPROX 13 INCHES LON	G.  THE CRACK IS EMANATING LT AND RT OF CENTER FROM THE UPPER BOLT HOLE OF THE MOST IB COMPRESSION STRUT.  AFTER DISASSE	MBLY IT WAS DETERMINED THAT THE COMPRESSION STRUT MOUNT BOLT WAS PREVIOUSLY OVER TIGHTENED, CAUSING CRUSHING OF THE SPAR	 WOOD, WHICH PRECIPITATED THE CRACK IN THE SPAR.			1	H	7	1 	3O				A796
2005052600083	20050526	00083	CE  	2005	5	26	2005FA0000696    	1	20041215	G	5712	052340050	SPAR            			CESSNA	172   	R172E       	2072413	CE  										LT WING IB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7892N	15628				R1720283				WHILE REPLACING THE FLAP TRACK ASSY, A CRACK APPROX 2 INCHES IN LENGTH AND RUNNING THROUGH THE LOWER RIVET HOLES, WAS FO	UND UNDER THE LT IB FLAP TRACK.  PROBABLE CAUSE WAS A FLAP OVERSPEED DURING FLIGHT.  (K)					1	H	7	1 	3O				3A17
2005052600084	20050526	00084	CE  	2005	5	26	2005FA0000697    	1	20041214	G	2930	98807101	PRESSURE SWITCH 	CESSNA      		CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					HYD PWR PACK	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			WP	25	2164S	195  			219	21061125				LANDING GEAR FAILED TO FULLY RETRACT AFTER TAKEOFF.  FOUND THAT THE WIRE SOLDERED TO THE HYDRAULIC POWER PACK PRESSURE S	WITCH HAD CORRODED BENEATH THE HEAT-SHRINK TUBING, NEAR THE SOLDER JOINT.  SUSPECTED:  THE MFG OF THE PRESSURE SWITCH AS	SY USED ACID CORE SOLDER TO ATTACH THE WIRE LEADS TO THE SWITCH.  (K)				1	H	7	1 	3O	3	O		3A21    	E8CE
2005052600085	20050526	00085	CE  	2005	5	26	2005FA0000698    	1	20041101	G	3340	MS357561	KEY             	GRIMES      		CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LANDING LIGHT	MISSING         	B			R1JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	10RM				5591	4250074				THE RT WING RETRACTABLE LANDING LIGHT WAS FAILED, REMOVED, SENT OUT FOR O/H.  RETURNED FROM O/H, INSTALLED 8/6/04 AND OP	S CHECKED OK.  UNIT FAILED 11/1/04 AND WAS REMOVED.  UNITS MOTOR WORM GEAR WAS ACCESSED, REMOVED AND THE MECHANIC DETECT	ED NO WOODRUFF KEY WAS INSTALLED AND ONLY SET SCREWS WERE DRIVING THE GEAR STRIPPING THE PARTS.  A NEW WORM GEAR AND WOO	DRUFF KEY  FURNISHED BY THE O/H AGENCY WERE DELIVERED, AND INSTALLED IAW STANDARD PRACTICES.  RECOMMEND CLOSER INSPECTIO	N.		1	L	7	2 	3T	4	T	RT	A7CE    	E4EA
2005052600086	20050526	00086	CE  	2005	5	26	2005FA0000699    	1	20041101	G	3340	A6582	WORM GEAR       	GRIMES      		CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LANDING LIGHT	MISSING         	B			R1JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	10RM				5591	4250074				THE RT WING RETRACTABLE LANDING LIGHT WAS FOAIED, REMOVED, SENT OUT FOR O/H.  RETURNE FROM O/H, INSTALLED 8/6/04 AND OPS	 CHECKED OK.  UNIT FAILED 11/1/04 AND WAS REMOVED.  UNITS MOTOR WORM GEAR WAS ACCESSED, REMOVED AND THE MECHANIC DETECTE	D NO WOODRUFF KEY  WAS INSTALLED AND ONLY SET SCREWS WERE DRIVING THE GEAR, STRIPPING THE PARTS.  A NEW WORM GEAR AND WO	ODRUFF KEY FRUNISHED BY THE O/H AGENCY WERE DELIVERED, AND INSTALLED IAW STANDARD PARCTICES.  RECOMMEND CLOSER INSPECTIO	N.  (K)		1	L	7	2 	3T	4	T	RT	A7CE    	E4EA
2005052600097	20050526	00097	CE  	2005	5	26	2005FA0000702    	1	20041217	G	2740		NUT             			BEECH 	MU300 	400A        	1155402	CE  										JACKSCREW	WORN            	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	400HD		756  		921009	RK191				DURING A AND B  INSPECTION NOTICED CLUNK IN PITCH TRIM.  FOUND ACTUATOR IN FULL NOSE DOWN POSITION CONTACTING VERTICAL F	IN CAP SUPPORT.  UPON FURTHER INVESTIGATION FOUND JACKSCREW FREEPLAY MEASURED .075 MAX ALLOWABLE FREEPLAY IS .020.  ACTU	ATOR OVERHAUL INTERVAL IS 1800 HOURS.  THIS ACTUATOR WAS O/H 11/21/2000 WITH 756.2 TSO.  NEXT SCHEDULED O/H DUE IN 1043.	8 HOURS.  FRAME CONTACT MAY HAVE HAD EFFECT ON PREMATURE WEAR.  (K)			2	H	7	2 	4F			RT	A16SW
2005052600098	20050526	00098	CE  	2005	5	26	2005FA0000703    	1	20041217	G	3230	35823071	CONNECTOR       			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					MLG	LOOSE           	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	712TA					RK186				INVESTIGATED LANDING GEAR RETRACT SYSTEM FAULT (LANDING GEAR WOULD NOT RETRACT WHEN GEAR HANDLE SELECTED (UP) AFTER TAKE	OFF) FOUND P162 CONNECTOR LOOSE, NOT FULLY SEATED ON A162 PC BOARD ASSY.  J1 CONNECTOR, RESEATED P162 CONNECTOR TO A162J	1 CONNECTOR, LANDING GEAR RETRACT/EXTENSION SYSTEM OPERATIONS NORMAL DURING 10 RETRACT/EXTENSION CYCLES.  (K)				2	H	7	2 	4F	4	T	RT	A16SW   	E1NE
2005052600099	20050526	00099	SO  	2005	5	26	2005FA0000704    	2	20041112	G	8520	634503	MAIN BEARING    			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	DELAMINATED     	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	10FF					421C0082				NR 3 MAIN BEARING APPEARED TO DELAMINATE.  ALL THE BRASS OR BRONZE SEPARATED FORM THE BEARING SHELL.  THE CRANKSHAFT, NR	 3 JOURNAL DOES NOT SHOW SIGNS OF OIL STARVATION. (K)					1	L	7	2 	3O	3	O		A7CE    	E7CE
2005052600119	20050526	00119	SO  	2005	5	26	2005FA0000708    	1	20041208	G	2140	94E42	PRESSURE SWITCH 	JANITROL    		PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					HEATER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	250CT	276  			A96100018	3177820011				HEATER SHOWED SIGNS OF ABNORMAL COMBUSTION IE. SOOT TRAIL FROM FUEL DRAIN VENT.  UPON INVESTIGATION.  FOUND COMBUSTION A	IR BLOWER FAN WHEEL ASSY HAD COME APART AND FODED HEATER.  FAN MOTOR WOULD STILL RUN.  AIR PRESSURE SWITCH HAD FAILED IN	 CLOSED POSITION IAW AD, SWITCH DOESN`T NEED OPS TESTING.  RECOMMENDED THAT ALL COMBUSTION AIR PRESSURE SWITCHES, BE TES	TED AND THAT THE COMBUSTION AIR FAN WHEEL ASSY BE INSPECTED AT SAME INTERVALS AS IN AD.  (K)			1	L	7	2 	3T	4	T		A8EA    	E4EA
2005052600121	20050526	00121	SO  	2005	5	26	2005FA0000709    	1	20041208	G	2140	B07D67	BLOWER          	JANITROL    		PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					HEATER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	250CT	276  			A96100018	31T7820011				HEATER SHOWED SIGNS OF ABNORMAL COMBUSTION IE. SOOT TRAIL FROM FUEL DRAIN VENT.  UPON INVESTIGATION, FOUND COMBUSTION AI	R BLOWER FAN WHEEL ASSY HAD COME APART AND FOD`D HEATER.  FAN MOTOR WOULD STILL RUN AIR PRESSURE SWITCH HAD FAILED IN CL	OSED POSITION.  IAW AD AIR PRESSURE SWITCH DOESN`T NEED OPS TESTING.  RECOMMEND THAT ALL COMBUSTION AIR PRESSURE SWITCHE	S BE TESTED AND THAT THE COMBUSTION AIR FAN WHEEL ASSY BE INSPECTED AT SAME INTERVALS AS CALLED FOR BY AD.  (K)			1	L	7	2 	3T	4	T		A8EA    	E4EA
2005060100212	20050601	00212	SO  	2005	6	1	2005FA0000755    	2	20041220	G	8530	501868	ROCKER          			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NR 1 CYLINDER	BROKEN          	D				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	CGDMD		10   			421B0917				ENGINE BECAME ROUGH IN FLIGHT ENGINE SHUTDOWN FOUND RT ENGINE NR 1 CYLINDER EXHAUST ROCKER ARM BROKEN.  (K)						1	L	7	2 	3O	3	O		A7CE    	E7CE
2005060200008	20050602	00008	CE  	2005	6	2	2005FA0000759    	1	20041006	G	3232	221302214	ACTUATOR        			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					NLG	OBSTRUCTED      	B			OMKR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	756TK					R18201150				AC NOSE DAMAGE DUE TO FAILURE OF NOSE GEAR TO EXTEND FOR LANDING.  PROP LINKAGE RUNS DOWN OUTSIDE NLG TUNNEL, IS ATTACHE	D TO IT IN 2 PLACES WITH ADEL CLAMPS, STANDOFFS, AND AN3 BOLTS.  AFT ATTACH HOLE IS DIRECTLY IN LINE WITH NOSE DOOR ACT 	ARM, WHICH IS HOLLOW SINCE ITS A WELD ASSY MADE OF STEEL TUBING.  AC HAD AFT AN3 BOLT INSTALLED WITH THREADS AND NUT FAC	ING OR PROTRUDING INTO WHEEL WELL.  BOLT END HAS HIT ACT ARM EACH GEAR RETRACTION UNTIL IT BECAME LOOSE ENOUGH TO POP OV	ER INTO END OF HOLLOW ACT ARM TUBE.  THIS NOW LOCKED ACT ARM INTO POSITION, LOCKED GEAR DOORS CLOSED, PREVENTING GEAR EX	TENSION. LT TUNNEL SIDE WAS REPLACED W/FACTORY PN, BOLT HOLE COMES PREDRILLED. NO REF TO PROP CABLE ROUTING. (K)	1	H	7	1 	3O	3	O	RT	3A13    	E295
2005062800171	20050628	00171	SO  	2005	6	28	2005FA0000809    	1	20041108	G	5711	6707002	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					WING	CORRODED        	B			N2YR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	8740N					2825555				UPPER SPAR CAP WAS FOUND WITH SEVERE EXFOLIATION CORROSION BEHIND THE FUEL TANK.  TANK WAS PULLED TO COMPLY WITH SB.  TH	ERE WAS NO INDICATION OF CORROSION SWELLING ON THE SURFACE OF THE WING.  THE AREA WHERE THE CORROSION OCCURRED IS NOT VI	SIBLE FROM INSPECTION PANEL ACCESS AND REQUIRES THAT THE FUEL TANKS BE PULLED FOR INSPECTION OF THIS AREA.  MFG HAS ADDR	ESSED THIS IN SB.  (K)			1	L	7	1 	3O	3	O		2A13    	E274
2005071900023	20050719	00023	SO  	2005	7	19	2005FA0000946    	2	20040428	G	7314	6559211A2	PUMP            			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE FUEL	FAILED          	P				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			SO	11	10368	156  				290286	684961	002495		ENGINE FAILED ON FINAL APPROACH.  WAS ABLE TO RESTART AFTER LANDING BUT HAD TO PULL THE MIXTURE CONTROL LEAN ABOUT 1INCH	 TO KEEP IT RUNNING.  AFTER COOLDOWN, MIXTURE WAS OK AGAIN.  THIS IS THE FIRST OF 3 FUEL PUMP FAILURES ON THIS AIRCRAFT/	ENGINE IN APPROX 90 HOURS.  THIS FUEL PUMP WAS INSTALLED ON THE ENGINE AT THE FACTORY WHEN THIS NEW ENGINE WAS BUILT.  N	EITHER MFG HAS BEEN ABLE TO DETERMINE THE CAUSE OF ANY OF THE PUMP FAILURES.			1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P3EA
2005080300013	20050803	00013	CE  	2005	8	3	2005FA0001081    	1	20041115	G	3233	78820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					LT MLG	CRACKED         	B			BNZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	9988B	1407 				172RG1108				PILOT REPORTED LT MAIN LANDING GEAR WOULD NOT FULLY RETRACT.  FOUND LT ACTUATOR CRACKED AT FORWARD BOLT HOLE.  (GL192005	04417) (K)					1	H	7	1 	3O	3	O		3A17    	E286
2005081700147	20050817	00147	SO  	2005	8	17	2005FA0001118    	2	20040930	G	8500		ENGINE          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					RT	MAKING METAL    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	76MJ	108  				421C1204	604158			DURING OIL CHANGE (ROUTINE) FOUND BEARING MATERIAL COMING OUT OF SUMP PLUG.  PIECES APPROX. .1250-.2500 INCH WIDE, .5 IN	CH LONG AND VARIOUS SMALLER PIECES.  ENGINE WAS OVERHAULED 12/01/03:  OWNER COMPLAINED OF VIBRATION FROM START.  O/H SAI	D NORMAL.  AFTER ENGINE CHANGE, VIBRATION WENT AWAY.  (NM09200414007) (K)				1	L	7	2 	3O	3	O		A7CE    	E7CE
2005082200078	20050822	00078	CE  	2005	8	22	2005FA0001119    	1	20041101	G	2700	065001790100	ROLL SERVO      			BEECH 	58    	58          	1152740	CE  										FLT CONTROLS	BINDING         	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	658RA	1027 				TH1892				FOUND FLIGHT CONTROLS BINDING WHEN YOKE TURNED.  BINDING WAS CAUSED BY PARTIALLY SEIZED OUTPUT BEARING IN AUTOPILOT ROLL	 SERVO.  FOUND BEARING AND MOTOR DEFECTIVE.  INSTALLED EXCHANGE SERVO.  (K)					1	L	7	2 	3O				3A16
2005082200080	20050822	00080	CE  	2005	8	22	2005FA0001120    	1	20041111	G	2700	065001790100	ROLL SERVO      			BEECH 	58    	58          	1152740	CE  										FLT CONTROLS	DEFECTIVE       	B			FTUR	O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NE	05	658RA	3    				TH1892				AIRCRAFT WENT INTO UNCOMMANDED TURN WITH AUTOPILOT ENGAGED.  REMOVED DEFECTIVE ROLL SERVO KS271C WITH 3.4 HOURS ON IT SI	NCE OVERHAUL BY MFG. (K)					1	L	7	2 	3O				3A16
2005081600222	20050816	00222	NM  	2005	8	16	2005FA0001121    	1	20041112	G	3411		STATIC PORT     			ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE731*     	01518	WP  					LT FWD	CLOGGED         	B			LN7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	50TQ					065				AIRSPEED DISPARITY DURING IFR APPROACH, WATER IN LT STATIC PORT.  FIRST TIME OCCURRENCE W/ THIS AC OUTSIDE DURING RAINST	ORM LASTING 3 HOURS.  STATIC DRAINS DRY, WATER ACCUMULATED JUST INSIDE STATIC PORT.  DID NOT KNOW WHY STATIC PORT HEATER	 DID NOT REMOVE THE MOISTURE.  RESULT OF PROBLEM: AIRSPEED DISPARITY/ EFIS AIR DATA CHECK SOM ERROR/ PILOTS ABORTED APPR	OACH AND PERFORMED MISSED/ RETURNED TO DEPARTURE.  BLEW OUT STATIC PORT, SUBSEQUENT FLIGHTS, OPS CHECKED GOOD.  (K)			2	L	7	2 	4F	4	F	RT	A16NM   	E6WE
2005081600224	20050816	00224	EU  	2005	8	16	2005FA0001122    	1	20041104	G	3210	S20	BEARING         	GROB        		GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					RT MLG TRUNION	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	864AF					85004				DURING INSPECTION OF MAIN LANDING GEAR, DISCOVERED EXCESSIVE FORE AND AFT PLAY IN RT MLG LEG.  RT MAIN LEG COULD MOVE FO	RE AND AFT 4MM OR MORE.  GEAR LEG WAS REMOVED.  INSPECTION OF THE AFT TRUNION ASSY REVEALED THAT THE BEARING HAD FAILED 	AND HAD EXCESSIVE PLAY IN IT.  UPON REMOVING THE BEARING, IT WAS DISCOVERED THAT IT APPEARS TO BE CONSTRUCTED FROM DIFFE	RENT MATERIAL THAN THE OTHER BEARINGS ALTHOUGH ALL BEARINGS HAVE THE SAME PN.  THIS BEARING SEEMS TO HAVE A BRASS OR BRO	NZE INNER RACE WHICH HAS BECOME LOOSE AND IS CAPABLE OF MOVING WITHIN THE STEEL OUTER RACE.  OTHER BEARINGS OF SAME PN I	N AC LANDING GEAR SYS HAVE A STEEL INNER AND OUTER RACE.  THIS BRG HAS BEEN RETURNED TO MFG FOR FURTHER INVESTIGATION.	1	L	7	1 	3O	3	O	RT	A49CE   	1E4
2005081600218	20050816	00218	EA  	2005	8	16	2005FA0001123    	2	20041108	G	7320	RSA5AD1	SERVO           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					FUEL INJECTOR	INOPERATIVE     	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			WP	07	863AF	196  				85003				PILOT REPORTED LOW FUEL FLOW ON TAKEOFF, UPON FURTHER INVESTIGATION THE MECHANIC FOUND THE FUEL FLOW WAS AT 149 PPH UNTI	L THE ENGINE GOT HOT THEN THE FUEL FLOW DROPPED DOWN TO 142-144 PPH.  NO RECOMMENDATION AT THIS TIME. (K)					1	L	7	1 	3O	3	O	RT	A49CE   	1E4
2005082200082	20050822	00082	CE  	2005	8	22	2005FA0001124    	1	20041101	G	8011	642083A10R	ADAPTER         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE STARTER	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5581T	87   				CE1350				DURING ATTEMPTING TO START THE ENGINE.  THE STARTER WOULD NOT TURN ENGINE TO START.  MAINTENANCE TECHNICIAN FOUND THAT T	HE STARTER ADAPTER WOUD NOT ENGAGE TO START THE ENGINE DUE TO STARTER ADAPTER SLIPPING.  REPLACED START ADAPTER AND ENGI	NE STARTED GOOD.  NO RECOMMENDATION AT THIS TIME. (K)				1	L	7	1 	3O	3	O		3A15    	E5CE
2005082200084	20050822	00084	CE  	2005	8	22	2005FA0001125    	1	20040923	G	3234	551417527	HANDLE          			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LANDING GEAR	LACK OF LUBE    	B			XZAR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	17	97SK	4416 				S5500127				LANDING GEAR WOULD NOT EXTEND WITH ACTUATION OF SELECTOR HANDLE DOWN.  EMERGENCY EXTENSION WAS ACTIVATED,  AND AIRCRAFT 	LANDED WITHOUT INCIDENT.  AFTER JACKING AND INSPECTING SYS, IT WAS FOUND THAT THE LANDING GEAR HANDLE WOULD MOVE UP AND 	DOWN, BUT THE SPRING LOADED IN AND OUT MOTION WAS STUCK OUT.  THIS CAUSED THE DOWN SWITCH NOT TO MAKE CONTACT WITH THE H	ANDLE, NOT ALLOWING THE LANDING GEAR TO EXTEND.  LUBRICATION OF THE SPRING AND SLIDER PORTION OF THE SELECTOR HANDLE WIT	H SPRAY LUBRICANT FREED UP THE MECHANISM AND ALLOWED CONTACT BETWEEN SWITCH AND HANDLE.  ONLY REQUIRED LUBRICATION IS DU	RING INSTALLATION.	1	L	7	2 	4F	4	F	RT	A22CE   	E1NE
2005082200085	20050822	00085	SO  	2005	8	22	2005FA0001126    	1	20041015	G	5541	2072907	RIB             			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CRACKED         	D			UVNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9180P	3900 				244670				CRACK WAS FOUND IN THE RIB THAT ATTACHES THE RUDDER COUNTER WEIGHTS.  THIS HAS BEEN NOTICED IN THE PAST, THE FIX IS TO R	EPLACE RIB.  PARTS NO LONGER AVAILABLE.  NOTICED THIS ON AIRFRAMES WITH MORE THAN 4000 HOURS.  (K)					1	L	7	1 	3O	3	O		1A15    	E14EA
2005081700183	20050817	00183	EU  	2005	8	17	2005FA0001127    	1	20041015	G	3350	ELW3039010201	LIGHT           			AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	DAMAGED         	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	900Q	89   				10				THE AIRCRAFT WAS ON MFG SPI RAMP.  THE CABIN LED LIGHT STRIP IN AFT CABIN BECAME WARM CAUSING HEAT DAMAGE TO THE LIGHT S	TRIP.  THE LIGHT BOARD WAS SENT TO EMTEQ LIGHTING FOR EVALUATION.  EMTEQ DETERMINED THE CAUSE OF THE FAILURE TO BE ELECT	RO STATIC DISCHARGE DAMAGE.  MFG REP TRAVELED TO FACILITY TO INSPECT INSTALLED CABIN LED BOARDS.  NO DEFECTS WERE FOUND 	ON ANY OF THE CABIN LED LIGHT BOARDS OR THE INSTALLATION OF THE SYS.  MFG IS WORKING ON PLAN TO PREVENT THIS FROM HAPPEN	ING IN THE FUTURE.  (K)		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE
2005082400096	20050824	00096	SW  	2005	8	24	2005FA0001205    	1	20041229	G	5343	9981002815	ATTACH FITTING  			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	982G					7ECA321				A CRACK WAS FOUND IN THE TORQUE KNEE ATTACH LUG (UPPER RADIUS) ON THE RT MAIN LANDING GEAR BRACE ASSEMBLY.						1	H	7	1 	3O	3	O		A759    	E223
2005092000072	20050920	00072	EU  	2005	9	20	2005FA0001254    	1	20041205	G	3241	95426531	TRANSDUCER      			AMD   	FALCON	FALCON20    	2730103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					ANTI SKID SYS	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	82TN					384				NORMAL APPROACH WITH A GOOD ANTI-SKID CK, AC WENT OFF END OF 6000 FT WET RUNWAY.  INSP OF TIRE MARKS AFTER ACCIDENT, NO 	EVID OF BRAKING ACTION.  NO CAUSE OF FAILURE.  ON TEST FLT AFTER REPAIR, RT ANTI-SKID WOULD NOT TEST IN AIR.  ANTI-SKID 	WAS LEFT ON LANDING, BRAKING OPERATED NORMALLY.  TAXING AFTER LANDING, RT BRAKES QUIT WORKING WHILE ANTI-SKID WAS ON.  L	T AND RT BRAKES WORKED NML WHEN ANTI SKID WAS TURNED OFF.  TESTED ALL OF ANTI-SKID TRANSMITTERS, FOUND NR 3 TRANSMITTER 	TO HAVE AN OPEN CIRCUIT IN 70 PERCENT OF ITS TRAVEL.  MM TEST SPECIFIES TO HOLD BOTH BRAKE PEDALS, SPIN ONE TRANSDUCER W	HICH SHOULD CAUSE ALL BRAKES TO RELEASE.  THIS TEST PERFORMED AFTER ACCIDENT, BEFORE TEST FLT, CHECKED OK BOTH TIMES.	2	L	7	2 	4F	4	F	RT	A7EU    	E6WE
2005090800077	20050908	00077	CE  	2005	9	8	2005FA0001268    	1	20041020	G	2510		STRUCTURE       	CESSNA      		CESSNA	501   	501         	2076603	CE  										SEAT BASE	CRACKED         	C			GVRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	7700T					5010248				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  	CHAIR WAS REPAIRED IAW STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F				A27CE
2005090800076	20050908	00076	GL  	2005	9	8	2005FA0001269    	1	20041118	G	3213	40005401	CYLINDER        			AMTR  	AEROST	AEROSTARBIRD	0560582	GL  	LYC   	O540  	TIO540*     	41532	EA  					MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	7411S	3968 				60001627				COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BRAZED OR SILVER SOLDERED TOGETHER-WOR	KING COLLAR CAUSED PART TO WORK AND CRACK BOSS.  (K)					1	M	7	1 	  	3	O		EXPA1M71	E14EA
2005090800075	20050908	00075	GL  	2005	9	8	2005FA0001270    	1	20041118	G	3213	40005401	CYLINDER        			AMTR  	AEROST	AEROSTARBIRD	0560582	GL  	LYC   	O540  	TIO540*     	41532	EA  					MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	7411S	3968 				60001627				COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BRAZED OR SILBER SOLDERED TOGETHER- WO	RKING COLLAR CAUSED PART TO WORK AND CRACK BOSS.  RECOMMEND INSPECTION OF COLLAR AT BOTTOM OF GEAR STRUT FOR ANY MOVEMEN	T OR WORKING BETWEEN COLLAR AND THE STRUT CYLINDER ASSEMBLY- DYE CHECK COLLAR WHERE PART IS MACHINED FOR CLEARANCE ON TO	RQUE LINKS.  (K)			1	M	7	1 	  	3	O		EXPA1M71	E14EA
2005092000020	20050920	00020	NM  	2005	9	20	2005FA0001271    	1	20041118	G	3213		COLLAR          			PIPER 	PA60  	PA60601P    	7106012	NM  										MLG STRUT	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	91VK	4148 				61P06157963				COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BRAZED OR SILVER SOLDERED TOGETHER, WO	RKING  COLLAR CAUSED PART TO WORK AND CRACKED BOSS.  RECOMMEND INSPECTION OF COLLAR AT BOTTOM OF GEAR STRUT FOR ANY MOVE	MENT OR WORKING BETWEEN COLLAR AND THE STRUT CYLINDER ASSY - DYE CHECK WHERE PART IS MACHINED FOR CLEARANCE ON TORQUE LI	NKS.  (K)			1	M	7	2 	3O			RT	A17WE
2005091500018	20050915	00018	EA  	2005	9	15	2005FA0001273    	1	20041015	G	2797		WIRE            			CNDAIR	CL601 	CL6013A     	8070802	EA  										VERTICAL STAB	SHORTED         	B			RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03						5175				WHILE TROUBLESHOOTING INTERMITTENT UPPER BEACON CIRCUIT BREAKER FAULT, DISCOVERED LT ELEVATOR CONTROL CABLE HAD TORN THR	OUGH WIRING CONDUIT IN VERTICAL STABILIZER.  THE CABLE WORE THROUGH THE CONDUIT AND SHORTED OUT THE WIRING FOR THE UPPER	 BEACON.  REPAIRED WIRING CONDUIT, REPLACED WIRING AND REPLACED CONTROL CABLE IAW MFG INSTRUCTIONS.  REPAIR OF CONDUIT A	LLOWED SUFFICIENT CLEARANCE BETWEEN CABLE AND CONDUIT.  UNCLEAR IF CONDUIT WAS INSTALLED AT FACTORY OR AT TIME OF COMPLE	TION.  SUGGEST INSPECTION OF THIS AREA ON OTHER SIMILAR AIRCRAFT.  DEFECT DIFFICULT TO NOTICE DUE TO ACCESSIBILITY OF AR	EA IN TAIL.  (K)	2	L	7	2 	4F			RT	A21EA
2005091900216	20050919	00216	CE  	2005	9	19	2005FA0001298    	1	20041209	G	2420	DOF10300B	ALTERNATOR      			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	FAILED          	C				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SW	15	732YK		351  			21061879				OVERHAULED ALTERNATOR FAILED IN FLIGHT AFTER 351 HOURS IN SERVICE.						1	H	7	1 	3O	3	O		3A21    	E8CE
2005103100158	20051031	00158	GL  	2005	10	31	2005FA0001397    	1	20041104	G	7603		THROTTLE CABLE  			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					ENGINE	FAILED          	B			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	102U	622  				C0205				THROTTLE CABLE BROKEN INSIDE OF CABLE HOUSING 26 INCHES FROM CABLE END.  NOTED THAT CABLE ASSEMBLY MAKES TIGHT RADIUS BE	ND BEHIND INSTRUMENT PANEL, JUST AFT OF FIREWALL.  (K)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO
2005031000030	20050310	00030	CE  	2005	3	10	2005R0037        	1	20041216	G	3242	1338932	BRAKE DISC      	BFGOODRICH  		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG BRAKE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	2663Y	194  	194  		0110	5500602				BRAKE ASSEMBLY P/N: 2-1528-6, S/N'S: 0110 AND 1390.  BOTH OF THESE BRAKES ARE IN COMPLIANCE WITH MFG SB 2-1528-32-2, REV	 5, DATED 3 APR, 2003.  BOTH BRAKES WERE UNDERGOING VISUAL INSPECTION AT 202 LANDINGS AND 194.7 HRS SINCE OVERHAUL.  BOT	H BRAKES HAD STATORS P/N: 133-893-2 CHG D, WITH CRACKS IN THE STOP HOLE AREA OF THE LONG EXPANSION SLOTS.				1	L	7	2 	4F	4	F		A22CE   	E1NE
2007013000182	20070130	00182	EU  	2007	1	30	2007FA0000089    	1	20040706	G	2711	1075010	O-RING          			FOKKER	F28   	F28MK4000   	4990810	EU  										AILERON TAB	LEAKING         	D				A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	23	159AD					11227				AT 1004Z, AIRCRAFT DEPARTED, APPROX 30 MIN INTO FLIGHT, PILOTS CALL PTK OPS RADIO AND REPORTED TOTAL LOSS OF NR 2 HYD SY	STEM FLUID.  AIRCRAFT RETURNED TO DEPARTURE.  AFTER ARRIVING, THE FLIGHT MECHANIC INSPECTED THE AIRCRAFT AND FOUND THE R	T AILERON TAB LOCK OUT ACTUATOR FILTER O-RING HAD RUPTURED.  (K)				2	L	7	2 	4F			RT	A20EU
2007061300216	20070613	00216	CE  	2007	6	13	2007FA0000421    	1	20040205	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		9318 	3323 							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
	20081028		SO  	2008	10	28	2008F00023       	2	20041007	G	8520		PUSHROD         			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	E				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	05	5421M					402B0021				ENGINE HAD MANIFOLD AND FUEL PRESSURE VARIATION IN FLT, THE ACFT BEGAN TO VIBRATE AND THE PILOT SHUTDOWN ENGINE.  THE NR	 1 AND NR 2 ROD`S FAILED AND SEPARATED FROM THE CRANKSHAFT AND CREATED (2) LARGE HOLES IN THE CASE AND KNOCKING BOTH MAG	NETOS LOOSE. THERE ARE SIGNS OF OIL STARVATION ON THE CRANK AND OVERHEATING ASIGNS ON  THE CRANKSHAFT.  REMOVAL OF OTHER	 CYLINDERS INDICATED OIL STARVATION ON THE NR (6) AND (5) ROD`S ALSO.  OVERHEATING OF THE CRANK AT THOSE LOCATIONS IS EV	IDENT. PILOT VERIFIED LOSING OIL PRESSURE BEFORE SHUTTING THE ENGINE. (K)		1	L	7	2 	3O	3	O		A7CE    	E5CE
	20081028		SW  	2008	10	28	2008FA0000711    	1	20041003	G	5620	33036710	WINDOW          			GULSTM	690TP 	690C        	7630517	SW  										CABIN	CRACKED         	B			TKTR	A				UNSCHED LANDING         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	11	XBDMT	380  				11360				ACFT LOST PRESSURIZATION. AFTER LANDING THE RT CABIN WINDOW WAS FOUND CRACKED. AFTER REMOVAL THE CRACK WAS FOUND TO EXTE	ND FROM THE TOP OF THE WINDOW INTO MOUNTING SCREW HOLE NR 22 AFT OF THE FRONT OF THE WINDOW THEN FWD 14 INCHES THROUGH 1	3 MOUNTING HOLES. THE CRACK THEN TURNED DOWN AND CONTINUED ACROSS THE TOP FWD CORNER OF THE WINDOW FOR 10 MORE INCHES IN	TO MOUNTING HOLE NR 5 FROM THE TOP ON THE FWD EDGE OF THE WINDOW.  (K)			1	H	7	2 	3T				2A4
	20081028		CE  	2008	10	28	2008FA0000713    	1	20041013	G	2510	05140778	SEAT FRAME      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	20454	5822 				17261300				DURING A ROUTINE 100 HOUR INSPECTION IT WAS DISCOVERED THAT THE PILOTS FULLY ADJUSTABLE SEAT FRAME WAS CRACKED IN SEVERA	L PLACES.  SOME AREAS WERE COVERED UP BY THE UPHOLSTERY WHICH IS GLUED TO THE FRAME IN THAT AREA. OTHER AREAS OF CONCERN	 WERE INCOMPLETE WELDS DONE AT THE FACTORY. (3) OUT OF (4) SUPPORT LEGS WERE CRACKED AT THE WELD AND AT THE ATTACHMENT P	OINT TO THE BOTTOM SEAT ASSY. (K)			1	H	7	1 	3O	3	O	NT	3A12    	E274
	20081028		CE  	2008	10	28	2008FA0000714    	1	20041009	G	2420	53954732	V-BELT          			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	O470N       	17026	SO  					ALTERNATOR	DEPARTED        	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SO	19	55FL					CD996				PILOT REPORTED LOSS OF ELECTRICAL POWER IN CRUISE FLIGHT DURING NIGHT VFR. V-BELT OBSERVED MISSING FROM ACCESSORY CASE A	BSENT FROM ALTERNATOR PULLEY. V-BELT APPARENTLY LOST IN FLIGHT THROUGH OPENING IN LOWER COWLING. OWNER REPORTS THAT ONLY	 25-30 HOURS WAS PUT ON THIS COMPONENT. (K)				1	L	7	1 	3O	3	O		3A15    	E273
	20081028		GL  	2008	10	28	2008FA0000716    	1	20040929	G	5100		SPAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O200  	O200*       	17020	SO  						DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	885CT					C0085				DURING THE 6000 HR INSPECTION, DELAMINATION FOUND IN THE TOP AFT CORNERS OF THE SPAR BRIDGE, BOTH SIDES. AFTER FURTHER I	NVESTIGATION BY FACTORY PERSONNEL, CRACKS WERE FOUND DOWN THROUGH THE DIFFERENT LAYERS OF GLASS NOT THROUGH THE CARBON F	IBER. RECOMMEND THAT THE AREA BE THOROUGHLY INSPECTED DURING THE 1000 HR INSPECTIONS. BRIGHT LIGHTS AND A MAGNIFYING GLA	SS MUST BE USED.  THESE CRACKS AND DELAMINATION ARE IN PROHIBITED AREA ACCORDING TO CHAPTER 51-00 STANDARD PRACTICES AND	 STRUCTURES. (K)		1	L	7	1 	3O	3	O	NT	TA4CH   	E252
2004050600028	20040506	00028	CE  	2004	5	6	206040204        	1	20040402	G	7820	12502505	MUFFLER         			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	BULGED          	B			JBZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	5224U					2060224				WHILE PERFORMING A ROUTINE PREFLIGHT INSPECTION, MECHANIC LOOKED UP TAILPIPES OF EXHAUST SYSTEM AND NOTICED SILENCER CON	E HAD EXTENDED TO POSITION THAT WAS JUST SHORT OF CLOSING OFF EXHAUST PATH.  THIS CONDITION OCCURRED OVER A PERIOD OF LE	SS THAN 50 HOURS WHEN SAME MECHANIC HAD PERFORMED SAME VISUAL INSPECTION AND NOTED NO UNUSUAL CONDITIONS.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE
2005022300198	20050223	00198	NE  	2005	2	23	2104             	2	20041015	G	7200		ENGINE          			BOEING	767   	767300      	1385204	NM  	GE    	CF6   	CF680C2B7   	 	NE  					NR 1	VIBRATION       	H				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			EA	15	VPBAZ					30111	704956			NR 1 ENGINE SHUT DOWN DURING FLIGHT DUE TO VIBRATION.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2005052000072	20050520	00072	GL  	2005	5	20	21200003A        	1	20040519	G	2410		ALTERNATOR      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	LOOSE           	B			DEBR	H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	99	449CD					1320	917617			THIS ACFT HAD A ALTERNATOR NR 1 FAIL LIGHT. UPON TROUBLE SHOOTING IT WAS FOUND THAT THE AFT HOUSING OF THE ALTERNATOR WA	S LOOSE. FOUR SCREWS ATTACHING THE HOUSING WERE STILL SAFETY WIRED.  IT DOES NOT  APPEAR THAT SCREWS HAD LOOSENED OR THA	T THE FORWARD HOUSING THREADS WERE DAMAGED. IT IS OUR OPION THAT AT ASSEMBLY THE ALTERNATOR FROM TELEDYNE CONTINENTAL MO	TORS MANFACTUER WAS TORQUED AND SEFETY WIRED AND THAT THE AFT HOUSING WAS NOT FULLY SEATED TO THE FRONT HOUSING DUE TO I	NTERFERENCE FROM THE INTERNAL PARTS OF THE ALTERNATOR. THIS IS THE THIRD ALTERNATOR WITH A LOOSE AFT HOUSING. FAILURE TO	TAL TIMES OF THE THREE ALTERNATORS RANGE FROM 79.6 HOURS TO 232.2 HOURS.  WE ARE AWARE OF AT LEAST 10-12 TOTAL FAILURES	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2004122700001	20041227	00001	SO  	2004	12	27	21200003AA       	1	20041107	G	3210	653193	CYLINDER        	PIPER       		PIPER 	PA28  	PA28180     	7102808	SO  										RT MLG	BROKEN          	C				K				NONE                    				P			NO WARNING INDICATION     			LD	LANDING        	1			GL	03	4830L	4797 				284173				ON FINAL LANDING AFTER SEVERAL TOUCH AND GO`S, STUDENT PILOT AND CFI THOUGHT THAT THEY BLEW THE LT TIRE BECAUSE THE RT W	ING CAME UP.  AFTER FULL STOP, NOTED THAT THE UPPER TORQUE LINK ATTACH LUGS OF THE RT MLG CYLINDER HAD BOTH BROKEN OFF, 	DISCONNECTING THE TORQUE LINK ASSY ALLOWING THE STRUT TO FULLY OPEN AND MISALIGNING THE WHEEL.  OTHER THAN THE CYLINDER 	ASSY, NO OTHER DAMAGE INCURRED.  THE LT MLG CYLINDER WAS DYE PENETRATED AND BOTH ATTACH LUGS HAD CRACKS PRESENT.  VISUAL	LY LOOKING AT WHERE THE BREAK OCCURED, IT WAS APPARENT THAT THE CRACKS HAD BEEN THERE FOR SOMETIME AND THAT CORROSION HA	D OCCURRED.  BOTH CYLINDERS WILL BE REPLACED.  PIPER SERVICE BULLETIN NR 1131 DATED AUGUST 2003 WAS NOT COMPLIED WITH.	1	L	7	1 	3O			 	2A13
2004100400150	20041004	00150	SW  	2004	10	4	21200003EAI      	1	20040923	G	2150	35BD219DUM	BEARING         	AIRCOM      		BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ACM	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03					64	36333				DURING FIRST GROUND RUN AFTER INSTALLATION OF AIRCOM CABIN AIR CONDITIONING SYSTEM (P/N 412AC-106-2 - STC SR00066DE) A M	ECHANIC INSPECTING THE SYSTEM NOTICED THE IDLER PULLY ON P/N 412AC-3036-1 SHAFT ASSEMBLY WAS NO LONGER IN ALIGNMENT WITH	 THE MAIN DRIVE PULLY & COMPRESSOR.  AFTER ENGINE SHUTDOWN AND FURTHER INSPECTION IT WAS DETERMINED THAT THE IDLER PULLE	Y BEARING ASSEMBLY HAD FAILED WITH THE BEARING SEAL AND MOST OF THE BALL BEARINGS MISSING.  AFTER REMOVAL AND INSPECTION	 THERE WAS NO EVIDANCE OF ANY INTERNAL BEARING LUBRICATION.  LESS THAN 5 BALL BEARINGS WERE RECOVERED (ON THE AIRCRAFT R	OOF AND ON THE GROUND AROUND THE AIRCRAFT).  AFTER FURTHER INSPECTION THERE WAS NO EVIDANCE OF FOD DAMAGE TO THE ENGINES	1	G	7	2 	4U	4	U	 	H4SW    	E22EA
2004030300188	20040303	00188		2004	3	3	21200004         	4	20040221	G	2210	55X	AUTOPILOT SYS   			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	DEFECTIVE       	C				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NM	10	2084S		700  			21061050				AIRCRAFT PORPOISES WHILE IN ALTITUDE HOLD MODE.  DISABLE ALTITUDE HOLD MODE.  MAINTENANCE CONFIRMS DEFECTIVE UNIT BY MAN	UFACTURER.  MANUFACTURER UNABLE TO SUPPLY REPLACEMENT PART.					1	H	7	1 	3O	3	O		3A21    	E8CE
2004101800092	20041018	00092	GL  	2004	10	18	22010904         	1	20041004	G	7160	AN334	BOLT            	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ALT AIR DOOR	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	968BG	205  				0968				DURING REMOVAL AND REPLACEMENT OF THE P/N 15708-001 INDUCTION DUCT ASSY.  IT WAS NOTED THAT THE INDUCTION DUCT WAS CRACK	ED IN AREA OF AN3-34 BOLT WHICH SERVES AS HINGE POINT FOR ALTERNATE AIR DOOR. AFTER REMOVING BOLT IT WAS FOUND TO  HAVE 	A GROOVE WORN INTO BOLT SHANK ALL THE WAY AROUND (360 DEGREES). IT APPEARS THAT INDUCTION DUCT SUPPORT BRACKET P/N 15671	-002, MADE OF STAINLESS STEEL, IS WEARING INTO BOLT. IT IS VERY DIFFICULT TO TELL IF THERE IS CRACKING ON DUCT (CRACKING	 LOCATED AT BOTTOM OF DUCT) WITHOUT REMOVING IT. THE CONDITION OF THE BOLT CANNOT BE VERIFIED UNLESS IT IS REMOVED.   TH	IS MODEL AIRCRAFT, WITH THE PLASTIC TYPE INDUCTION DUCTS SHOULD BE INSPECTED FOR THIS CONDITION AS SOON AS POSSIBLE.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2005022300124	20050223	00124	GL  	2005	2	23	2201092004       	1	20041004	G	1430	AN334	BOLT            	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					INDUCTION DUCT	CHAFED          	B			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	968BG	205  				0968				DURING REMOVAL AND REPLACEMENT OF THE P/N 15708-001 INDUCTION DUCT ASSY IT WAS NOTED THAT DUCT WAS CRACKED IN THE AREA O	F THE AN3-34 BOLT THAT SERVES AS THE HINGE POINT FOR THE ALTERNATE AIR DOOR.  AFTER REMOVING THE BOLT IT WAS FOUND TO BE	 CHAFFED ALL THE WAY AROUND THE SHANK (360 DEGREES). IT APPEARS THE INDUCTION DUCT SUPPORT BRACKET P/N 15671-002, MADE O	F STAINLESS STEEL, IS WEARING IT'S WAY INTO THE BOLT SHANK. SEVERAL OTHER AIRCRAFT WERE INSPECTED AND WERE FOUND TO HAVE	 BOLT WEAR AND/OR CRACKING OF THE DUCT IN THE SAME AREA.  THE CRACKING OF THE DUCT IS VERY DIFFICULT TO SEE WITHOUT REMO	VING THE ASSY AND THE CHAFFING OF THE BOLT CANNOT BE SEEN WITHOUT REMOVING IT.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2004102700101	20041027	00101	GL  	2004	10	27	220192004        	1	20041004	G	1430	AN334	BOLT            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ALT AIR DOOR	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	968BG	205  				0968				DURING REMOVAL AND REPLACEMENT OF PN 15708-001 INDUCTION DUCT ASSY IT WAS NOTED THAT INDUCTION DUCT WAS CRACKED IN AREA 	OF AN3-34 BOLT WHICH SERVES AS HINGE POINT FOR ALTERNATE AIR DOOR.  AFTER REMOVING BOLT IT WAS FOUND TO HAVE A GROOVE WO	RN INTO BOLT SHANK ALL THE WAY AROUND (360 DEGREES).  IT APPEARS THAT INDUCTION DUCT SUPPORT BRACKET PN 15671-002, STAIN	LESS STEEL, IS WEARING IT'S WAY INTO BOLT.  OTHER AC WERE INSPECTED IN THIS AREA AND ALL WERE FOUND TO HAVE SOME DEGREE 	OF WEAR ON BOLT AND CRACKING ON THE DUCT ASSY IN SAME AREA. IT IS VERY DIFFICULT TO TELL IF THERE IS CRACKING ON DUCT (C	RACKING LOCATED AT BOTTOM OF DUCT) WITHOUT REMOVING IT. CONDITION OF THE BOLT CANNOT BE VERIFIED UNLESS IT IS REMOVED.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2004122900154	20041229	00154	SO  	2004	12	29	2304             	1	20041105	G	2910		HYDRAULIC SYSTEM			GULSTM	G1159 	GIV         	3980115	SO  											LEAKING         	H				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	99	VPBSH					1466				APPROX 3.5 HR INTO FLIGHT, RETURN TO BLOCK DUE TO HYD FLUID LOSS.						2	L	7	2 	4F			RT	A12EA
2004123000057	20041230	00057	GL  	2004	12	30	24041004         	1	20041028	G	7160	15671002	BRACKET         	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  										INDUCTION DUCT	CHAFED          	B			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	787CD					0918				THE INDUCTION DUCT SUPPORT BRACKET P/N 15671-002 HAS BEEN FOUND TO BE CHAFING INTO THE ALTERNATE AIR DOOR PIVOT BOLT P/N	 AN3-34.  REPORTED THIS CONDITION BEFORE.  A CHECK OF MULTIPLE AIRCRAFT HAVE SHOWED SIGNS OF CHAFFING AT THIS LOCATION. 	 SUGGEST CLOSE LOOK AT THIS AREA WHEN PERFORMING MAINTENANCE.  IT IS NECESSARY TO REMOVE THE DUCT ASSY P/N 15708-001 TO 	PERFORM THIS INSPECTION.			1	L	7	1 	3O			NT	A00009CH
2005020200099	20050202	00099	GL  	2005	2	2	24331            	1	20041102	G	1430	AN334	BOLT            			CIRRUS	SR    	SR22        	2130001	GL  										ALT AIR DOOR	CHAFED          	B			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	361CD	312  				0885				THE BOLT (P/N AN3-34) THAT SERVES AS THE PIVOT FOR THE ALTERNATE AIR DOOR IN THE INDUCTION DUCT ASSEMBLY (P/N 15708-001)	 IS BEING CHAFFED BY THE INDUCTION DUCT SUPPORT BRACKET (P/N 15671-002).  IN ADDITION TO THE CHAFFED BOLT THE INDUCTION 	DUCT ASSY IS SUSCEPTIBLE TO CRACKING.  ALSO INSPECTED 14 OTHER AIRCRAFT WITH COMPARABLE TIME OR LESS AND FOUND SIGNS OF 	CHAFFING AND/OR INDUCTION DUCT CRACKING REQUIRING REPLACEMENT OF THE INDUCTION DUCT ASSY.  THIS CONDITION IS VERY DIFFIC	ULT TO INSPECT WITHOUT REMOVING THE INDUCTION DUCT ASSY.		1	L	7	1 	3O			NT	A00009CH
2004120900119	20041209	00119	GL  	2004	12	9	25921104         	1	20041129	G	1430	AN334	BOLT            			CIRRUS	SR    	SR22        	2130001	GL  										ALR AIR DOOR	CHAFED          	B			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	302CD	158  				1076				THE BOLT (P/N AN3-34) THAT SERVES AS THE PIVOT FOR THE ALTERNATE AIR DOOR IN THE INDUCTION DUCT ASSY (P/N 15708-001) IS 	BEING CHAFED BY THE INDUCTION SUPPORT BRACKET (P/N 15671-002). IN ADDITION TO THE CHAFED BOLT THE PLASTIC DUCT IS SUSCEP	TIBLE TO CRACKING AROUND THE PIVOT BOLT ON THE BOTTOM OF THE DUCT ASSY. THIS AREA IS VERY DIFFICULT TO INSPECT WITHOUT R	EMOVING THE DUCT ASSEMBLY. ALSO, IT IS NECESSARY TO REMOVE THE NUT AND SUPPORT BRACKET TO INSPECT THE BOLT FOR CHAFFING.			1	L	7	1 	3O			NT	A00009CH
2005012600166	20050126	00166	GL  	2005	1	26	26251204         	1	20041203	G	1430	AN334	BOLT            	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  										ALT AIR DOOR	CHAFED          	E			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	822TW	128  				1066				THE BOLT (P/N 3-34) THAT SERVES AS THE PIVOT FOR THE ALTERNATE AIR DOOR IN THE INDUCTION DUCT ASSY (P/N 15708-001) IS BE	ING CHAFED BY THE INDUCTION DUCT SUPPORT BRACKET (P/N 15671-002).  IN ADDITION TO THE CHAFFED BOLT THE PLASTIC DUCT IS S	USCEPTIBLE TO CRACKING AROUND THE PIVOT BOLT ON THE BOTTOM OF THE DUCT ASSY.  THIS AREA IS VERY DIFFICULT TO INSPECT WIT	HOUT REMOVING THE DUCT ASSY.  ALSO, IT IS NECESSARY TO REMOVE THE NUT AND SUPPORT BRACKET TO INSPECT THE BOLT FOR CHAFFI	NG.		1	L	7	1 	3O			NT	A00009CH
2004092000027	20040920	00027	CE  	2004	9	20	2688200400001    	1	20040903	G	7800	2254008	CROSSOVER TUBE  			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					EXHAUST SYS	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	5091T	1400 				R18201814				DURING ANNUAL INSPECTION, DISCOVERED CRACK APPROXIMATELY 1.5 INCHES IN LENGTH AROUND THE LT CROSSOVER ASSEMBLY (PN 22540	08).  UPON REMOVAL, ALSO FOUND DETERIORATION IN THE SLIP JOINT CONNECTING THE RT CROSSOVER ASSEMBLY (PN 2254013).  REPLA	CED BOTH PARTS WITH FACTORY NEW.				1	H	7	1 	3O	3	O	 	3A13    	E295
2004092000028	20040920	00028	CE  	2004	9	20	2688200410001    	1	20040903	G	7800	2254008	CROSSOVER TUBE  			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					EXHAUST SYS	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	5091T	1400 				R18201814				DURING ANNUAL INSPECTION, DISCOVERED CRACK APPROXIMATELY 1.5 INCHES IN LENGTH AROUND THE LT CROSSOVER ASSEMBLY (PN 22540	08).  UPON REMOVAL, ALSO FOUND DETERIORATION IN THE SLIP JOINT CONNECTING THE RT CROSSOVER ASSEMBLY (PN 2254013).  REPLA	CED BOTH PARTS WITH FACTORY NEW.				1	H	7	1 	3O	3	O	 	3A13    	E295
2004091700067	20040917	00067	CE  	2004	9	17	2689200410001    	1	20040902	G	7810	2254008	CROSSOVER TUBE  			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					RT ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	5091T	1400 				R18201814				DURING ANNUAL INSPECTION, DISCOVERED CRACK APPROXIMATELY 1.5 INCHES IN LENGTH AROUND THE LT CROSSOVER ASSEMBLY.  UPON RE	MOVAL, ALSO FOUND DETERIORATION IN THE SLIP JOINT CONNECTING THE RT CROSSOVER ASSEMBLY (PN 2254013).  REPLACED BOTH PART	S WITH FACTORY NEW.				1	H	7	1 	3O	3	O	 	3A13    	E295
2005031000054	20050310	00054	GL  	2005	3	10	270112           	1	20041223	G	1430	AN334	BOLT            	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  										ALR AIR DOOR	CHAFED          	E			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	308CD	147  				1026				THE BOLT (P/N 3-34) THAT SERVES AS THE PIVOT FOR THE ALTERNATE AIR DOOR IN THE INDUCTION DUCT ASSY (P/N 15708-001) IS BE	ING CHAFFED BY THE INDUCTION DUCT SUPPORT BRACKET P/N 15671-002. IN ADDITION TO THE CHAFFED BOLT THE PLASTIC DUCT IS SUS	CEPTABLE TO CRACKING AROUND THE PIVOT BOLT ON THE BOTTOM OF THE DUCT ASSY. THIS AREA IS VERY DIFFICULT TO INSPECT WITHOU	T REMOVING THE DUCT ASSY. ALSO, IT IS NECCESSARY TO REMOVE THE NUT AND SUPPORT BRACKET TO VISUALLY INSPECT THIS AREA.			1	L	7	1 	3O			NT	A00009CH
2005031000052	20050310	00052	GL  	2005	3	10	27011204         	1	20041223	G	1430	AN334	BOLT            	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  										ALR AIR DOOR	CHAFED          	E			YD5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	308CD	147  				1026				THE BOLT (P/N 3-34) THAT SERVES AS THE PIVOT FOR THE ALTERNATE AIR DOOR IN THE INDUCTION DUCT ASSY (P/N 15708-001) IS BE	ING CHAFED BY THE INDUCTION DUCT SUPPORT BRACKET P/N 15671-002. IN ADDITION TO THE CHAFED BOLT THE PLASTIC DUCT IS SUSCE	PTABLE TO CRACKING AROUND THE PIVOT BOLT ON THE BOTTOM OF THE DUCT ASSY. THIS AREA IS VERY DIFFICULT TO INSPECT WITHOUT 	REMOVING THE DUCT ASSY. ALSO, IT IS NECCESSARY TO REMOVE THE NUT AND SUPPORT BRACKET TO VISUALLY INSPECT THIS AREA.			1	L	7	1 	3O			NT	A00009CH
2004092000060	20040920	00060	CE  	2004	9	20	2724             	1	20040816	G	3244	301361311	TIRE            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A6       	52043	EA  					MLG	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	350NY					FL283				PROBLEM FOUND DURING NORMAL WORN TIRE REPLACEMENT.  CORD (WIRE LIKE MATERIAL) WAS NOT DEEP ENOUGH IN THE RUBBER OF THE T	IRE SEAT AREA WHICH LEFT A GROOVE (MIRROR IMAGE OF THE CORD) IN THE NR 3 MAIN WHEEL RIMS (INNER AND OUTER HALVES).  THE 	GROOVES COVERED MORE THAN HALF THE DIAMETER OF THE OF THE WHEEL RIMS TO A MAX DEPTH OF JUST UNDER .020 INCH.  BECAUSE OF	 THE LENGTH OF THE GROOVES, THE WHEEL ASSEMBLY REQUIRED REPLACEMENT. (WHEEL P/N 101-8001-47)			2	L	7	2 	4T	3	T	RT	A24CE   	E4EA
2005031000053	20050310	00053	GL  	2005	3	10	27641204         	1	20041223	G	2425	116118001	BRACKET         	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  										RT INST PANEL	CHAFED          	E			YD5R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	15	581MD	157  				1098				THE PILOT REPORTED A LOSS OF VOLTAGE INDICATION ON THE MFD WITH ALL OTHER SYSTEMS OPERATING NORMALLY. THROUGH TROUBLESHO	OTING IT WAS DISCOVER THAT WIRE #ANEN983-22 WAS CHAFFED THROUGH  THE INSULATION (THE AREA IN QUESTION IS LOCATED ABOVE T	HE CO-PILOTS KICK PANEL AND BEHIND THE RIGHT HAND INSTRUMENT PANEL). THE AIRCRAFT RECENTLY HAD THE X-M WEATHER KIT OPTIO	N INSTALLED. IT APPEARS THAT WHEN THE KIT IS INSTALLED IT IS POSSIBLE FOR THE WIRE HARNESS TO BE MOVED TO THE POINT WHER	E IT CAN CHAFFE ON THE X-M AFT MOUNTING BRACKET. SINCE THIS IS DIFFICULT TO SEE ANTI-CHAFFE MATERIAL SHOULD BE INSTALLED	 ON THE AFT BRACKET TO ELIMINATE THE POSSIBILITY OF THIS CONDITION.	1	L	7	1 	3O			NT	A00009CH
2005030800056	20050308	00056	EU  	2005	3	8	2961             	1	20041022	G	3244	M08401	TIRE            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					MLG	DEFORMED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	164GB	234  				164				THIS TIRE WAS MOUNTED ON THE RIGHT INBOARD SIDE (NR 3).  CUPPING WAS NOTICED ON THE INSIDE EDGE OF THE TIRE ALL THE WAY 	AROUND WITH CORD SHOWING. TIRE WAS REPLACED.  CONTACTED FALCON TECH OPS.  HAD NOT HEARD OF THIS ITEM AND ASKED ME TO CON	TACT THE TIRE MANUFACTURE.  CONTACTED MICHELIN, CONFIRMED THE PROBLEM AND SAID THEY WERE WORKING ON IT.				2	L	7	3 	4F	4	F		A46EU   	E6WE
2004092000089	20040920	00089	EA  	2004	9	20	2AUG04           	1	20040802	G	3244	256K433	TIRE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30015	NE  					MLG	SEPARATED       	C				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			GL	23	710VF	45   				5050				APPROXIMATELY 1 TO 2 SECONDS BEFORE TAKEOFF, PILOT REPORTED A SLIGHT FORWARD LURCH TO AIRCRAFT AS IF IT WAS GOING THROUG	H A PUDDLE. CHECK ALL FLT PARAMETERS NO ABNORMALITIES NOTED.  CALL TOWER TO ASK FOR RUNWAY INSPECTION, GROUND PERSONNEL 	REPORTED FINDING PIECES OF TIRE AND WHAT LOOKED LIKE AN ANTENNA (IT WAS THE IB WOW INPUT PROX SWITCH).  THE ENTIRE TREAD	 SEPARATED FROM THE CASING AND CAUSED CONSIDERABLE DAMAGE TO AIRCRAFT.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004042900032	20040429	00032	EU  	2004	4	29	314431004        	1	20040310	G	6220	350A31191600	STARFLEX        			SNIAS 	350   	AS350B3     	8680954	EU  										MAIN ROTOR	CRACKED         	E			S4WA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5226R	1047 				3144				STARFLEX BUSHING CRACKED AT BONDING JOINT, INDICATING SEPARATION.						1	G	7	1 	3U			 	H9EU
2004072100057	20040721	00057	EA  	2004	7	21	32029A           	1	20040715	G	7910		CABLE           			WACO  	UPF7  	UPF7        	9601302	EA  										OIL TANK	BROKEN          	B			W2OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	32029	5500 				5660				CABLE ASSEMBLY THAT SECURES THE OIL TANK BROKE ON REINSTALLATION OF THE OIL TANK. ON FIRST LOOK, THE CABLE ENDS APPEARED	 TO BE THE OLD STYLE WOVEN CABLE SPLICE. AFTER THE CABLE BROKE WHILE TIGHTENING THE TURNBUCKLE, IT WAS FOUND THE CABLE W	AS WRAPPED AROUND THE THIMBLE, SAFETY WIRE WAS WRAPPED AROUND THE TWO PIECES OF CABLE, AND THE JOINT SOLDERED. THE AIRCR	AFT WAS REBUILT IN 1987. THE LOGBOOK ENTRIES DO NOT INDICATE WHETHER THE CABLE WAS CHANGED. HAD THE CABLE FAILED, THE OI	L TANK WOULD HAVE NOT BEEN RESTRAINED AND FREE TO MOVE ON THE TUBING MOUNT. THIS TYPE OF CABLE SPLICE IS UNAIRWORTHY AND	 PRESENTED A SIGNIFICANT SAFETY HAZARD. NICOPRESS SLEEVES WOULD HAVE BEEN THE APPROPRIATE METHOD TO FABRICATE THE CABLE.	1	Q	7	1 	3R			 	A642
2004072100056	20040721	00056	EA  	2004	7	21	32029B           	1	20040715	G	3242		CABLE           			WACO  	UPF7  	UPF7        	9601302	EA  										BRAKE SYS	DEFECTIVE       	B			W2OR	K				NONE                    				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			GL	09	32029					5660				CABLE ASSY CONNECT BRAKE PEDALS TO MASTER CYLINDERS WERE INSPECTED UNDER MORE SCRUTINY AFTER FINDING DEFECTIVE CABLE SEC	URING OIL TANK. CABLE ENDS APPEARED TO BE OLD STYLE WOVEN CABLE SPLICE. FOUND CABLE WAS WRAPPED AROUND THIMBLE, SAFETY W	IRE WAS WRAPPED AROUND TWO PIECES OF CABLE,  JOINT SOLDERED. CORROSION PRESENT IN SOLDERED SAFETY WIRE EVIDENCED AS A GR	EENISH, WHITE POWDER. CABLES HAVE BURNED LOOKING AREAS AT SOLDERED AREA THAT MAY HAVE BEEN CAUSED BY TORCH USED TO HEAT 	AREA. AC WAS REBUILT IN 1987. LOGBOOK ENTRIES DO NOT INDICATE CABLES WERE CHANGED. HAD CABLE FAILED, BRAKES WOULD BECOME	 INOPERATIVE.  CABLE SPLICE IS UNAIRWORTHY.  AC SHOULD NOT HAVE PASSED ANNUAL INSPECTIONS WITH THESE CABLES INSTALLED.	1	Q	7	1 	3R			 	A642
2004050300184	20040503	00184		2004	5	3	32404            	4	20040308	G	2350	0110040110	AUDIO PANEL     			CIRRUS	SR    	SR22        	2130001	GL  											FAILED          	G				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	01	8160N	57   				0734				DURING CRUISE, PILOT NOTED FAILURE OF AUDIO SYSTEM. ELECTRICAL BURNING ODOR ACCOMPANIED SYSTEM FAILURE. PILOT ELECTED TO	 SHUT DOWN ELECTRICAL POWER AND MAKE A PRECAUTIONARY LANDING.   EVALUATION OF AIRCRAFT FOUND FAILURE OF AUDIO PANEL.					1	L	7	1 	3O			NT	A00009CH
2004050300151	20040503	00151	SO  	2004	5	3	3M57931704       	1	20040317	G	2742	5913114	RESOLVER        			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					STAB ACTUATOR	INACCURATE      	B			LD2R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	15	23M	2780 	400  			579	11261262			FLAP STAB MISCOMPARE CAS MESSAGE. STAB ACTUATOR HAS BAD RESOLVER.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN
2005012600187	20050126	00187	CE  	2005	1	26	4001             	1	20041207	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	53564	916  				172S9442				BENDIX DRIVE HOUSING CRACKED AND BROKE OFF OF STARTER.						1	H	7	1 	3O			NT	3A12
2004092000054	20040920	00054	EU  	2004	9	20	4007053          	1	20040225	G	2720	8011540140140	RUDDER PEDAL    			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	109MS	2672 				1008				THE RUDDER PEDAL FOOT ASSEMBLIES ARE MADE UP OF A FOOT PEDAL WHICH SLIPS INTO A TUBE AND RIVETED TOGETHER WITH 6 BLIND R	IVETS. (FOOT PEDAL IS OFFSET FROM THE TUBE, SO THE PEDAL WANTS TO ROTATE IN THE TUBE WHEN PUSHING FORWARD ON THE PEDAL) 	 THE RIVETS WERE LOOSE IN BOTH PILOT'S RUDDER PEDAL ASSEMBLIES AND THE COPILOT'S RIGHT ASSEMBLY.  OLD RIVETS WERE REMOVE	D, PARTS ASSEMBLED WITH LIGHT COAT OF STRUCTURAL ADHESIVE, AND NEW RIVETS INSTALLED AS RECOMMENDED BY TECHNICAL SUPPORT.			1	H	7	2 	3O	3	T	RT	A59EU   	E2NE
2004030400071	20040304	00071	CE  	2004	3	4	40188138         	1	20040226	G	5520	556555026	BRACKET         			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					BALANCE WEIGHT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	26NS	7280 				5000340				BALANCE WEIGHT ARM FOR ELEVATOR CONTROL SYSTEM IS CRACKED.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004092000055	20040920	00055	EU  	2004	9	20	4046             	1	20040910	G	2720	8011540140102	RUDDER PEDAL    			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	122PA	453  				1038				THE RUDDER PEDAL FOOT ASSEMBLIES ARE MADE UP OF A FOOT PEDAL WHICH SLIPS INTO A TUBE AND RIVETED TOGETHER WITH 6 BLIND R	IVETS. (FOOT PEDAL IS OFFSET FROM THE TUBE, SO THE PEDAL WANTS TO ROTATE IN THE TUBE WHEN PUSHING FORWARD ON THE PEDAL) 	THE RIVETS WERE LOOSE IN BOTH PILOT'S AND BOTH COPILOT'S RUDDER PEDAL ASSEMBLIES. TO REPAIR: OLD RIVETS WERE REMOVED, PA	RTS ASSEMBLED WITH LIGHT COAT OF STRUCTURAL ADHESIVE, AND NEW RIVETS INSTALLED AS RECOMMENDED BY TECHNICAL SUPPORT.			1	H	7	2 	3O	3	T	RT	A59EU   	E2NE
2004050700004	20040507	00004	CE  	2004	5	7	40590            	1	20040420	G	2731		BEARING         			CESSNA	414   	414A        	2075907	CE  										ELE TRIM TAB	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	6815T	3846 				414A0645				DURING ANNUAL INSPECTION FOUND THE ELEVATOR TRIM TAB HORN BEARING FROZEN.  WHEN HORN WAS REMOVED TO REPLACE THE BEARING 	THE 2 ATTACHMENT SCREWS IN THE FORWARD HOLES OF THE BEARING WERE FOUND SEVERELY CORRODED.  MORE THAN 50 PERCENT OF THE O	RRIGINAL DIAMETER WAS ERODED AWAY.				1	L	7	2 	3O			 	A7CE
2004071900029	20040719	00029	CE  	2004	7	19	409798           	1	20040629	G	3246		NUT             			CESSNA	500   	550         	2076604	CE  										WHEEL BEARING	LOOSE           	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	669B	269  				5501060				WHEN REMOVING WHEEL FOR TIRE CHANGE FOUND THE LT MAIN WHEEL NUT HAD NOT BEEN TIGHTENED CAUSING RUINED BEARING SEALS.  TH	IS WAS THE FIRST ACCESS SINCE THE AIRCRAFT WAS DELIVERED NEW FROM THE FACTORY.					1	L	7	2 	4F			 	A22CE
2004092000059	20040920	00059	CE  	2004	9	20	4101             	1	20040816	G	3244	301361311	TIRE            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A6       	52043	EA  					MLG	GROOVED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	350NY					FL283				PROBLEM FOUND DURING NORMAL WORN TIRE REPLACEMENT.  CORD (WIRE LIKE MATERIAL) WAS NOT DEEP ENOUGH IN THE RUBBER OF THE T	IRE SEAT AREA WHICH LEFT A GROOVE (MIRROR IMAGE OF THE CORD) IN THE NR 4 MAIN WHEEL RIMS (INNER AND OUTER HALVES).  THE 	GROOVES COVERED A THIRD OF THE DIAMETER OF THE WHEEL RIMS TO A MAX DEPTH OF JUST UNDER .018 INCH.  BECAUSE OF THE LENGTH	 OF THE GROOVES, THE WHEEL ASSEMBLY REQUIRED REPLACEMENT. (WHEEL P/N 101-8001-47).			2	L	7	2 	4T	3	T	RT	A24CE   	E4EA
2004110300119	20041103	00119	SO  	2004	11	3	417011           	1	20041015	G	5730		ACCESS PANEL    			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					WING	DEBONDED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	767TP	617  				4697036				WING FUEL PANELS HAVE A FOAM FILLER BLOCK AND SEALANT TO PREVENT WATER FROM BEING TRAPPED AT PANELS.  THE SEALANT HAD TO	RN FREE AND THE FOAM BLOCK WAS FLOATING LOOSE IN THE TANK FROM ONE PANEL AND WAS LOOSE FROM A SECOND PANEL BUT WAS NOT F	REE IN THE TANK YET.  THESE PIECES ARE ABOUT 5 INCHES LONG, 3 INCHES WIDE AND .5 INCH THICK.  PANELS WERE REPAIRED AND R	EINSTALLED IAW MM.			1	L	7	1 	3O	3	T	RT	A25SO   	E2NE
2005012700068	20050127	00068	CE  	2005	1	27	418611           	1	20041111	G	2121	EM6039	BLOWER          			BEECH 	90    	E90         	1152914	CE  										COCKPIT	FAILED          	B				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	09	999SE					LW344				SMOKE IN COCKPIT CAUSED BY FAILED ELECTRICAL MOTOR ON VENT BLOWER ASSEMBLY.  LOG BOOK WAS NOT AVAILABLE AT TIME OF INSTA	LLATION, SO TOTAL TIME OF PART IS UNKNOWN.					1	L	7	2 	3T				3A20
2005020100015	20050201	00015	CE  	2005	2	1	4356             	1	20041221	G	8011	EBB131A	STARTER         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	DESTROYED       	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03			195  			17274489	2115			ON ENGINE START, STARTER BENDIX DID NOT DISENGAGE.  ALL BENDIX DRIVE ENGAGEMENT TEETH SHEARED AND DAMAGED ENGINE STARTER	 RING GEAR.  TIME SINCE OVERHAUL BY KELLY AEROSPACE 195.0					1	H	7	1 	3O	3	O	NT	3A12    	E274
2004051200028	20040512	00028	EA  	2004	5	12	5040050504A      	1	20040505	G	3241	6002504	SENSOR          			CNDAIR	CL600 	CL6002B16   	1900305	EA  										WHEEL SPEED	FAILED          	E			S4WA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	07	807Z	5201 				5040				OB FAIL LIGHT STAYED ON DURING ANTI-SKID TEST.  TEST BOX SHOWED OUT LO FAIL.						2	L	7	2 	4F			RT	A21EA
2004051200025	20040512	00025	EA  	2004	5	12	5040050504B      	1	20040505	G	5610	6003303025	WINDSHIELD      			CNDAIR	CL600 	CL6002B16   	1900305	EA  										COCKPIT	DELAMINATED     	E			S4WA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	807Z	1104 				5040				LT FWD WINDSHIELD DELAMINATED.						2	L	7	2 	4F			RT	A21EA
2004050700003	20040507	00003	CE  	2004	5	7	5266S            	1	20040317	G	7830	2660016507	SUPPORT BEAM    			LEAR  	60    	60LEAR      	5170707	CE  										THRUST REVERSER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	601GG					192				LT AND RT THRUST REVERSER, THE SUPPORT BEAMS, ALSO KNOWN AS BIRD CAGES PN 266-0016-507 ARE CRACKING AT THE GUIDE ROD FEE	D THROUGHS.  THIS DISCREPANCY HAS BEEN OBSERVED ON THE FOLLOWING  N620JF, 60-074, N114PJ, 60-114, N600GG 60-115, N91772 	60-053, N60UU 60-007, N603SC 60-096, N415NP 60-024, N43NR 60-043, N601GG 60-192.  AFTER INSTALLING THE NEW REPLACEMENT S	UPPORT BEAM PN 288-0019-1 WE HAVE DISCOVERED NO CRACKS AT THE GUIDE ROD FEED THROUGHS			2	L	7	2 	4F			RT	A10CE
2004091400182	20040914	00182	SW  	2004	9	14	535062004        	1	20040702	G	3510		CONTROL CABLE   			MOONEY	M20   	M20M        	5870222	SW  										OXYGEN SYSTEM	OBSTRUCTED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	12XL					270325				A RIVE NUT ON THE BRACKET HOLDING THE O2 CONTROL CABLE HAS CAUSED THE O2 CONTROL TO FAIL TO REACH ITS (FULL ON) POSITION	.  IF THE O2 CONTROL CABLE IS NOT SET AT (FULL ON) OR (FULL OFF) (IN OTHER WORDS, WHEN THE CONTROL IS IN-BETWEEN EITHER 	SETTING) THERE IS A LIKELIHOOD OF THE O2 BOTTLE EMPTYING ITS CONTENTS INTO THE TAILCONE IN A SHORT PERIOD OF TIME. THE C	RUX OF THIS PROBLEM IS A RIVNUT PREVENTING FULL TRAVEL OF THE O2 CONTROL. THIS DEFECT COULD AFFECT MORE THAN ONE AIRCRAF	T.		1	L	7	1 	3O			RT	2A3
2004022500024	20040225	00024	WP  	2004	2	25	54017            	2	20040112	G	7200	31026131	PLENUM          			DORNER	DO228 	DO228*      	       	EU  	GARRTT	TPE331	TPE3315     	01514	WP  					ENGINE	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25							P39350			FOUND CRACKED AT IGNITER BOSS LOCATION.						1	H	7	2 	4T	4	T	RT	A16EU   	E4WE
2004022500027	20040225	00027	WP  	2004	2	25	54140            	2	20040119	G	7200	310166811	PLENUM          			LEAR  	35    	31          	5170530	CE  	GARRTT	TPE331	TPE33110UG  	01514	WP  					ENGINE	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	CGEMQ						P63118			FOUND CRACKED AT THE PRIMARY FUEL NOZZLE BOSS.						2	L	7	2 	4F	4	T	RT	A10CE   	E4WE
2004022500029	20040225	00029	WP  	2004	2	25	54140A           	2	20040119	G	7200	310166811	PLENUM          			JETAIR	JETSTM	JETSTM4101  	1500501	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  					ENGINE	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25										FOUND CRACKED AT DRAIN.						2	L	7	2 	4T	4	T	RT	A41NM   	E4WE
2004050300162	20040503	00162	WP  	2004	5	3	54148            	2	20040119	G	7230	310166811	PLENUM          								GARRTT	TPE331	TPE33110UG  	01514	WP  					ENGINE	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25										FOUND CRACKED AT DRAIN BOSS.											4	T			E4WE
2004091400147	20040914	00147		2004	9	14	54951            	4	20040720	G	3417	8220842421	ADC             			CNDAIR	CL604 	CL604       	1900301	EA  										NR 2	FAILED          	C				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			GL	17	495BA		13   			5495				NR 2 AIR DATA COMPUTER (ADC) FAILED SHOWING ALTITUDE FLAG AND VERTICAL SPEED FLAG.   MDC CODES 350-000812 AND 351-080112	, 351-0106F2.					2	L	7	2 	4F			RT	A21EA
2005052400252	20050524	00252	EU  	2005	5	24	62GX20281        	1	20041122	G	3411	ST600R	STATIC PORT     			ISRAEL	GALAXY	GALAXY      	4500307	EU  										FUSLEAGE	CORRODED        	D			QRRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	62GX	2028 				031				AIRCRAFT ADC (AIR DATA COMPUTER) - 200 FT SPLIT ON APPROACH TO LAND IN HEAVY RAIN.  FOUND MOISTURE IN STATIC PORTS (4 EA	) DURING POST FLIGHT INSPECTION.  CLOSER INSPECTION REVEALED CORROSION ON THE INTERIOR OF THE STATIC PORTS.  EXISTING ST	ATIC PORTS (ST600R) HAVE LARGER DIAMETER HOLES THAN THE REPLACEMENT STATIC PORTS WHICH MAY ALLOW WATER ENTRY.  REPLACED 	STATIC PORTS WITH NEW ONES.  NO FURTHER DEFECTS. (EA13200504025) (K)			2	L	7	2 	4F			RT	A53NM
2004071900025	20040719	00025	CE  	2004	7	19	6346753          	1	20040707	G	2510	081278216	FRAME           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	29053	NE  	MCAULY	4HFR34	4HFR34C660  	NE  	SEAT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	800AB	7844 				4410162				CO-PILOTS BOTTOM WAS BROKEN IN THE REAR AT BOTH .2500 INCH AND .5000 INCH TUBES ON THE RT AND LT SIDE WHERE THE SIDE TUB	ES ATTACH TO THE REAR CROSS PIECE AT THE GUSSETS. FORWARD CROSS PIECE TUBING WAS BROKEN AT THE LT SEAT ADJUSTMENT BRACKE	TS AND CRACKED HALF WAY THROUGH AT THE RT ADJUSTMENT BRACKETS.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	5	C	3PNE
2004030100160	20040301	00160	CE  	2004	3	1	6521             	1	20040217	G	5420	505403042	BEAM            			CESSNA	421   	421C        	2076016	CE  										NACELLE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	3922C	9480 	93   			421C0419				DURING VISUAL INSPECTION OF BOTH LT AND RT NACELLE STRUCTURES, CRACKS WERE OBSERVED ON BOTH NACELLE, AFT BEAMS ON THE TO	P AND AFT, OB AREAS. FOLLOWING EVALUATION OF THIS STRUCTURE BY THIS INSPECTION CREW AND A LOCAL DER, IT WAS DETERMINED T	HAT REPAIR OF THIS STRUCTURE IS NOT ECONOMICALLY FEASIBLE AND REQUIRES REPLACEMENT OF BOTH LT AND RT BEAM ASSEMBLIES, PR	OVIDED BY MFG. CLOSE ATTENTION TO THIS AREA IS RECOMMENDED DURING AIRCRAFT INSPECTION.			1	L	7	2 	3O			 	A7CE
2004030100114	20040301	00114	CE  	2004	3	1	6604             	1	20040212	G	5343	07436062	FITTING         			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					NLG	BROKEN          	B				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	11	7371Q	2737 				18261011				ABORTED TAKEOFF AFTER LOUD NOISE HEARD ON TAKEOFF AND RUDDER KICKED FULL DEFLECTION.  FOUND NOSE GEAR LOWER FITTING BROK	EN IN TWO,  INSPECT THIS FITTING CLOSELY AT ANNUAL.					1	H	7	1 	3O	3	O	NT	TA13    	E273
2004011200206	20040112	00206	GL  	2004	1	12	7011203          	1	20040106	G	2820	51020001	CONNECTOR       			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUEL HOSE	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	975CW	124  				0424	686724	FP1958B		AIRCRAFT WAS IN FOR AN ANNUAL INSPECTION. A FUEL LEAK WAS NOTED AS A DISCREPANCY. FURTHER INVESTIGATION REVEALED THAT TH	E ORIGIN OF THE LEAK WAS COMING FROM A HOSE/BULKHEAD FITTING CONNECTION ON THE FIREWALL. THE HOSE B-NUT WAS FOUND TO BE 	FINGER TIGHT. THE FITTING HAD BEEN TORQUE STRIPED BUT THE STRIPE WAS BROKEN. MAINTENANCE LOGS WERE REVIEWED BUT SHOWED N	O WORK PERFORMED ON THE FUEL SYSTEM, HOWEVER A STARTER ADAPTOR HAD BEEN RECENTLY REPLACED. IMMEDIATE INVESTIGATION OF AN	Y FUEL LEAK CANNOT BE OVERSTATED. THIS AIRCRAFT ALSO HAD A LOOSE FUEL PUMP ADJUSTMENT SCREW JAMB NUT.		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2004051400112	20040514	00112		2004	5	14	705050704        	4	20040504	G	3414	26465933	INDICATOR       			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					AIRSPEED	ERRATIC         	E				C				ABORTED TAKEOFF         				M			OVER TEMP                 			TO	TAKEOFF        	1			SO	35	705AC	870  	870  			209				AIRCRAFT ABORTED TAKEOFF DUE TO A AIRSPEED INDICATION ANOMALY.  BRAKES EXPERIENCED AN OVERHEAT.						2	M	7	2 	4F	4	F	 	A2SW    	E6WE
2004122900153	20041229	00153	NM  	2004	12	29	7529S            	1	20041119	G	5320	210056033	CHANNEL         			PIPER 	PA60  	PA60601     	7106010	NM  										FUSLEAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	7529S	3410 				61016182				ON INSPECTION, FOUND PART CRACKED AT RIVET HOLES WHERE ATTACHED TO P/N 210056-031 CHANNEL.						1	M	7	2 	3O			RT	A17WE
2004030400098	20040304	00098	CE  	2004	3	4	8570000          	1	20040227	G	2731	S3280	GEAR            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELEVATOR TRIM	SLIPPED         	A			JJBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	857CA	5662 				UE403				WHILE CHECKING ELEVATOR TRIM FOR FCD BE2703 DISCOVERED ELEVATOR TAB DIAL MECHANISM MOUNT ASSY HAD SLIPPED CAUSING THE TR	IM INDEX MARK CALIBRATION TO CHANGE. UPON FURTHER INSPECTION IT WAS DISCOVERED THAT THE SLIPPAGE WAS CAUSED BY A PRESSED	 ON GEAR IN THE ELEVATOR TAB DIAL MECHANISM MOUNT ASSY THAT HAD SLIPPED ON ITS SHAFT.				2	L	7	2 	4T	3	T	RT	A24CE   	E2NE
2005011300062	20050113	00062	WP  	2005	1	13	872SJ001         	1	20041021	G	5330		SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  										ZONE 100	CORRODED        	B			GKZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	872SJ					46040				LAV ACCESS SERVICE PANEL HAS CORROSION UNDER PAINT GBAMC NR 04161 AND NR 04185 UPON INVESTIGSTION FOUND SKIN TO BE OUT O	F LIMITS BELOW LIP ON ACCESS DOOR, REMOVED DAMAGED SKIN AREA OF 1.75X9.00 FABED FILLER,FABED FINGER DOUBLER FOR BACK, FA	B DOUBLER FOR EXTERNAL, INSTALLED SPLICE, INSIDE DOUBLER& OUTSIDE DOUBLER IAW COTNEY AEROSPACE DWG W93-RO3 REV.IR-CLOSED	-			2	L	7	4 	4F			RT	4A25
2005011300041	20050113	00041	WP  	2005	1	13	872SJ002         	1	20041021	G	5330		SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  										FUSELAGE	CORRODED        	B			GKZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	872SJ					46040				A/C COMP AREA INTERIOR A/C OUTFLOW DUCT HAS CORROSION GBAMC NR 04160 CLEANED CORRISON ON INTERIOR A/C OUTFLOW DUCT PANEL	 IAW DC-8 SRM 51-1-8,CORRISON FOUND TO BE OUT OF LIMITS IAW DC-8 SRM 53-2-0. MATERIAL THICKNESS.130,MATERIAL LOSS .104 F	ABED DOUBLER IAW COTNEY AEROSPACE INC. DWG W93-R02 REV IR AND INSTALLED DOUBLER AT STA 35 TO 55 AND L28R TO TO L30R IAW 	DC-8 SRM 51-1-21 SUPPORTED BY 8110-3. -CLOSED-			2	L	7	4 	4F			RT	4A25
2005022200226	20050222	00226	WP  	2005	2	22	872SJ003         	1	20041022	G	5248		DOOR            			DOUG  	DC8   	DC871F      	302199D	WP  										CARGO BAY	CORRODED        	B			GKZR	K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SW	11	872SJ					46040				D-PIT, AFT BULKHEAD DOOR 645 CORRODED GBAMC NR#04172 CUT OUT DAMAGED MATERIAL ON D PIT DOOR AFT BULKHEAD DOOR 645 IAW DC	-8 SRM 52-2-0 FIG 4 SHEET 2.  FABRICATED DOUBLER PATCH OUT OF 7075T6 .032 AND INSTALLED DOUBLER PATCH ON D-PIT BULKHEAD 	DOOR IAW DC-8 SRM 52-2-0 FIG 4 SHEET 2.				2	L	7	4 	4F			RT	4A25
2004111000014	20041110	00014	WP  	2004	11	10	872SJ004         	1	20041022	G	5320		FLOOR SUPPORT   			DOUG  	DC8   	DC871F      	302199D	WP  										FUSELAGE	CORRODED        	B			GKZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	872SJ					46040				LT W/W LT SIDE UPPER, SECOND FLOOR SUPPORT HAS CORROSION ON LOWER SIDE. GBAMC NR04176 -OPEN-						2	L	7	4 	4F			RT	4A25
2004111000050	20041110	00050	WP  	2004	11	10	872SJ005         	1	20041022	G	5330		FINGER DOUBLER  			DOUG  	DC8   	DC871F      	302199D	WP  										FUSELAGE	CORRODED        	B			GKZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	872SJ					46040				CARGO AREA RT SIDE STA 960 HAS CORROSION UNDER FINGER DOUBLER UNDER FLOORBOARD.  GBAMC NR04182 -OPEN-						2	L	7	4 	4F			RT	4A25
2004111000049	20041110	00049	WP  	2004	11	10	872SJ006         	1	20041027	G	5330		FINGER DOUBLER  			DOUG  	DC8   	DC871F      	302199D	WP  										FUSELAGE	CORRODED        	B			GKZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	872SJ					46040				LT OB TOP SIDE OF WHEEL WELL PRESSURE DOGHOUSE BETWEEN STA 960 AND 980, FINGER DOUBLER HAS CORROSION ON FWD UNDERSIDE. G	BAMC NR304186 -OPEN-					2	L	7	4 	4F			RT	4A25
2004111000048	20041110	00048	WP  	2004	11	10	872SJ007         	1	20041022	G	5310		STRUCTURE       			DOUG  	DC8   	DC871F      	302199D	WP  										LT MLG WW	CORRODED        	B			GKZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	872SJ					46040				LT WW UPPER LT SIDE FWD AND AFT OF NR 6 FLOOR SUPPORT HAS CORROSION. GBAMC NR04178 -OPEN-						2	L	7	4 	4F			RT	4A25
2005022200267	20050222	00267	WP  	2005	2	22	872SJ008         	1	20041102	G	5320		GUSSET          			DOUG  	DC8   	DC871F      	302199D	WP  										FUSELAGE	CRACKED         	B			GKZR	K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SW	11	872SJ					46040				RT UPPER GUSSET CRACKED AT STA XW5.000 GBAMC NR#04187.  STOP DRILLED, FAB`D  DOUBLER IAW DC-8 SRM.  INSTALLED TOP AND BO	TTOM DOUBLER IAW DC-8 SRM 51-1-21 AT STA XW5.000					2	L	7	4 	4F			RT	4A25
2004070600129	20040706	00129	CE  	2004	7	6	A001ABB          	1	20040618	G	2730	55653421	PUSHROD         			CESSNA	500   	550         	2076604	CE  										RT ELEVATOR	BENT            	B			DYCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	840MQ					427				RIGHT ELEVATOR PUSH ROD WAS INITIALLY REMOVED FROM THE AIRCRAFT WHEN IT WAS DISCOVERED DURING AN INSPECTION TASK THAT TH	IS ROD WAS ASSEMBLED USING ALUMINUM RIVETS, SHOULD BE MONEL RIVETS PER THE TASK.  UPON REMOVAL, INSPECTION PERSONNEL DIS	COVERED THAT THIS ROD WAS BENT.  REMOVAL OF LEFT ELEVATOR PUSHROD REVEALED THAT IT TOO WAS BENT - CORRECT RIVETS WERE IN	STALLED.  BENDS IN THESE RODS WERE NOT READILY APPARENT UNTIL REMOVAL FROM AIRCRAFT.  TWO NEW RODS WERE ORDERED FROM CES	SNA.  ONE ROD ROLLED PERFECTLY STRAIGHT ON A SURFACE PLATE, THE OTHER APPEARED TO BE MIS-MANUFACTURED.  THIS ROD WHILE N	OT OBVIOUSLY BENT, OSCILLATED WHEN ROLLED ON THE SURFACE PLATE. THE FORMED END WITH A CLEVIS FORK INSTALLED WAS NOT FORM	1	L	7	2 	4F			 	A22CE
2005020800092	20050208	00092	GL  	2005	2	8	AE0R200400002    	2	20041221	G	7250	23076976	TURBINE BLADES  			EMB   	145   	EMB145LR    	3260212	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	FRACTURED       	B			CHQA	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SO	03	279SK	591  				145379	CAE311220			ENGINE S/N CAE311220 WAS DELIVERED TO SHOP FOR REPAIR 11/03/04 DUE TO IN-FLIGHT SHUTDOWN.  DURING DISASSEMBLY, DAMAGE WA	S NOTED TO THE TURBINE.  ONE 1ST STAGE TURBINE BLADE WAS FRACTURED BELOW THE PLATFORM.					2	L	7	2 	4T	4	F	RT	T00011AT	TE6CH
2004122200169	20041222	00169	EU  	2004	12	22	AE1              	1	20041210	G	5520		STRUCTURE       			PILATS	PC6T  	PC6B2H2     	7090213	EU  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	FAILED          	P				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			EA	25	7391U	15954				2028	PCE40186	BOA19977		FAILURE OF ELEVATOR ATTACH POINT AND OR HARDWARE.  ACTUAL CAUSE IS UNKNOWN BECAUSE THE ELEVATOR HAS NOT BEEN LOCATED FOR	 RECOVERY.					1	H	7	1 	3T	4	T	 	7A15    	E4EA	6	C	P15EA
2005081700058	20050817	00058	EU  	2005	8	17	AE110304         	1	20041103	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  										FUEL PUMP	CRACKED         	B			E80R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07										THE PUMP WAS RECEIVED FROM THE OVERHAUL FACILITY TO THIS REPAIR STATION WITH THE IMPELLER CRACKED AND CRUSHED TO WHERE T	HE PRESSURE AND FLOW OF THE FUEL WOULD BE DEGRADED.  OTHER PUMPS RECEIVED HAD FOREIGN MATERIAL IN THE IMPELLER (DEBRIS A	ND INSECT PARTS).  QUALITY DEPARTMENT HAS BEEN NOTIFIED. (K)				1	G	7	2 	3U			O	H88EU
2005022200016	20050222	00016	SW  	2005	2	22	ALGA095160       	1	20040607	G	6210	206015001119	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	B			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	40LP	1162 				45233				DURING ROUTINE A/F INSPECTION, CORROSION AND SEPARATION WAS NOTED ON LOWER SURFACE SKIN/SPAR INTERFACE IMMEDIATELY O/B O	F GRIPFINGER.  REPLACED W/SERVICABLE PART.					1	G	7	1 	3U				H2SW
2005021700127	20050217	00127	SW  	2005	2	17	ALGA098260       	1	20041206	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	B			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457AL	666  				53151				UNIVERSAL BEARING HAS AXIAL PLAY BEYOND LIMITS.  REPLACED WITH NEW BY FIELD MAINTENANCE.						1	G	7	1 	3U			O	H2SW
2005021700128	20050217	00128	SW  	2005	2	17	ALGA098261       	1	20041206	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	B			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457AL	666  				53151				UNIVERSAL HAS AXIAL PLAY BEYOND LIMITS.  REPLACED WITH NEW BY FIELD MAINTENANCE.						1	G	7	1 	3U			O	H2SW
2004051300025	20040513	00025	CE  	2004	5	13	AMCR200400001    	1	20040407	G	1420	MS3106E10SL3S	CONNECTOR       			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ44        	66000	GL  					STROBE	BURNED          	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	179DV	13   			20122	525A0172				LT WINGTIP STROBE ASSEMBLY WAS INSTALLED 13 HOURS PRIOR IAW SB525A-33-02. WHEN STROBE FAILURE WAS NOTED, FOUND CONNECTOR	 SEVERELY BURNED, WITH ONE PIN COMPLETELY BURNED AWAY (ON POWER SUPPLY SIDE). POWER SUPPLY FAILED ALSO (MFG:FLIGHT COMPO	NENTS AG).  CHANGED POWER SUPPLY AND STROBE UNIT.				1	L	7	1 	4F	4	F	RT	A1WI    	E3GL
2004083000046	20040830	00046	SO  	2004	8	30	AMCR200400003    	1	20040820	G	3250	41001	SOLENOID        	GULSTM      		GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					MLG	SHORTED         	B			AMCR	O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			GL	09	251DV	19   			505B	1522				UPON LOWERING THE LANDING GEAR, TWO CIRCUIT BREAKERS POPPED FOR THE NOSE STEERING.  INVESTIGATION FOUND A SHORTED SOLENO	ID VALVE IN THE STEERING SYSTEM. THE SOLENOID WAS SHORTED TO GROUND INTERNALLY.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE
2004092000056	20040920	00056	EU  	2004	9	20	AMCR200400004    	1	20040909	G	3246		FUSIBLE PLUG    			AMD   	FALC90	FALCON900B  	2730171	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					WHEEL	LEAKING         	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	523AC	3158 				139				DURING A PREFLIGHT, FOUND TIRE PRESSURE TO BE DOWN SIGNIFICANTLY. INVESTIGATION FOUND ONE WHEEL FUSE PLUG TO BE LEAKING.	 WHEN FUSE WAS REMOVED, THERE APPEARED TO BE A SLIGHT DENT ON THE FACE OF THE FUSE, SIMILAR TO HANDLING DAMAGE. HISTORY 	SHOWS THIS TO BE AN ORIGINAL FUSE SINCE THE WHEEL WAS NEW.				2	L	7	3 	4F	4	F	RT	        	E6WE
2004122900151	20041229	00151	SO  	2004	12	29	AMCR200400005    	1	20041103	G	2750		ROLLER          			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					TE FLAPS	OUT OF POSITION 	B			AMCR	K				NONE                    				S			AFFECT SYSTEMS            			LD	LANDING        	1			GL	09	524AC					686				AFTER LANDING, THE PILOT WAS NOT ABLE TO RAISE THE FLAPS FROM THE 39 DEGREE POSITION AND HAD ASSOCIATED CAS MESSAGES CON	CERNING THE FLAP SYSTEM.  VISUAL INSPECTION REVEALED THE FLAPS TO BE OVER-EXTENDED WHICH CAUSED EACH OB ROLLER TO BE OUT	 BEYOND THE FLAP TRACK. THE FLAP SHIFTED SLIGHTLY AND THE ROLLERS JAMMED BEHIND THE TRACK.  BESIDES SOME ROLLERS EXHIBIT	ING SOME WEAR, NO DAMAGE WAS FOUND.  THE FLAPS WERE FULLY RIGGED IAW THE MM AND RETURNED TO SERVICE.  NOTE: THE FLAP SYS	TEM WAS PREVIOUSLY RIGGED A FEW WEEKS PRIOR FOR A CONDITION IN WHICH THE FLAPS APPEARED NOT TO FULLY STOW.		2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN
2005020100007	20050201	00007	SO  	2005	2	1	AMCR200400006    	1	20041213	G	2730	1159H4002811	ACTUATOR        			GULSTM	G1159 	GIV         	3980115	SO  										HYD SYSTEM	BYPASSING       	B			AMCR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	09	528GA	44   				1528				JUST BEFORE DESCENT, CREW GOT A 3 BONG ANNUNCIATION "LOW COMBINED FLUID". ON HYDRAULICS SYNOPTIC PAGE, CREW NOTICED FLUI	D MIGRATION FROM COMBINED SIDE TO FLIGHT SIDE, WITH "COMBINED" SYSTEM LOW AND "FLIGHT" SYSTEM HIGH.  AN UNEVENTFUL LANDI	NG TOOK PLACE, UPON SHUTDOWN,  "FLIGHT" SYSTEM DUMPED FLUID OVERBOARD.  INVESTIGATION TURNED UP NOTHING AND NUMEROUS CHE	CKS WERE ACCOMPLISHED WITH NO MIGRATION NOTED.  AIRCRAFT THEN FLEW BACK TO MANUFACTURER AND FLUID MIGRATION WAS NOTED AG	AIN.  MANUFACTURER FOUND THE 'ELEVATOR SERVO' ACTUATOR WAS BYPASSING INTERNALLY, AS WAS THE RT 'GROUND SPOILER' ACTUATOR	 AND 'FLIGHT POWER SHUTOFF VALVE' ALSO. AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER HYDRAULIC SYSTEM ANOMALIES.	2	L	7	2 	4F			RT	A12EA
2004050300121	20040503	00121		2004	5	3	ANCF200400008    	4	20040414	G	3436	4059845911	COMPUTER        			DOUG  	MD80  	MD83        	3023681	NM  										WINDSHEAR/GUIDAN	INOPERATIVE     	W			ANCF	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SO	23	583AN		1635 			53183				WINDSHEAR ALERT WAS PRESENTED TWO TIMES DURING TAKE OFF BEFORE REACHING 60 KTS.   WINDSHEAR COMPUTER WAS REPLACED IAW AM	M 34-47-00 PAG 201. TEST WINDSHEAR AND GUIDANCE SYSTEM WAS PERFORMED IAW AMM 34-47-00 PAG 201.					2	L	7	2 	4F			RT
2004081800171	20040818	00171		2004	8	18	ANCF200400027    	4	20040812	G	3413	4067241863	INDICATOR       			DOUG  	MD80  	MD83        	3023681	NM  	PWA   	JT8   	JT8D219     	52053	NE  					RATE OF CLIMB	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	23	632CT					49632				AFTER T/O THE LT RATE OF CLIMB IND FAIL.  IAW AMM 34-14-01/201 THE VERTICAL SPEED INDICATOR LT POS. WAS REMOVED AND REPL	ACED. OPS CHECKED ON GROUND, SATISFACTORY.					2	L	7	2 	4F	4	F	RT	        	E9NE
2004102900005	20041029	00005	SO  	2004	10	29	AOC04001         	2	20040712	G	8530	AEC631397SN2A	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	DAMAGED         	B			R29R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	19	9802Z	23   				U20606667	291297R			FOLLOWING SEVERAL WRITE UPS CONCERNING HIGH CYLINDER TEMP, THE CYLINDERS WERE REMOVED AFTER EXTENSIVE TROUBLESHOOTING RE	VEALED NO DEFECT. UPON INSPECTION OF THE CYLINDERS, IT WAS NOTED THAT THREE CYLINDERS HAD UNUSUAL CIRCULAR MARKS ON THE 	CYLINDER WALLS. ONE CYLINDER HAD CRACKING IN THE NICKEL PLATING AROUND ONE OF THE MARKS. NEW CONTINENTAL STEEL CYLINDERS	 WERE INSTALLED AND CYLINDER TEMP RETURNED TO NORMAL. REMOVED CYLINDERS SENT BACK TO MANUFACTURER.			1	H	7	1 	3O	3	O	 	A4CE    	E5CE
2004092000086	20040920	00086	SO  	2004	9	20	AOC04002         	2	20040721	G	8530	AEC631397SN2A	CYLINDER        			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520C    	17040	SO  					ENGINE	DAMAGED         	B			R29R	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	19	3160L	223  				U20602815	217211R			FOLLOWING SEVERAL WRITE UPS CONCERNING HIGH CYLINDER TEMP, THE CYLINDERS WERE REMOVED AFTER PREVIOUS LIKE PROBLEMS WITH 	ANOTHER AIRCRAFT. UPON INSPECTION OF THE CYLINDERS, IT WAS NOTED THAT THREE CYLINDERS HAD UNUSUAL CIRCULAR MARKS ON THE 	CYLINDER WALLS. NEW ECI CYLINDERS WERE INSTALLED AND CYLINDER TEMP RETURNED TO NORMAL. REMOVED CYLINDERS SENT BACK TO MA	NUFACTURER.			1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004090800161	20040908	00161	CE  	2004	9	8	AOC04003         	1	20040722	G	2421	F424R	ALTERNATOR      			CESSNA	206   	U206G       	2073356	CE  										ENGINE	WORN            	B			R29R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	9938Z	170  				U20606757				PILOT REPORTED ALTERNATOR SYSTEM FAILURE. FOUND ALTERNATOR FAN AND PULLEY TO HAVE EXCESSIVE SIDE PLAY AS WELL AS FORE AN	D AFT PLAY ON THE ALTERNATOR SHAFT. SUSPECT FRONT BEARING FAILURE.					1	H	7	1 	3O			 	A4CE
2004083000202	20040830	00202	SO  	2004	8	30	AOC04004         	2	20040720	G	8530	AEC631397SN2A	CYLINDER        			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	DAMAGED         	B			R29R	O				OTHER                   				M			OVER TEMP                 			CR	CRUISE         	1			SW	19	9811Z	34   				U20606674	245523			AFTER REPORTS OF HIGH CYLINDER TEMP, CYLINDERS WERE REMOVED FOR INSPECTION. THREE CYLINDERS FOUND TO HAVE UNUSUAL MARKS 	ON THE ECI CYLINDER WALLS, SIMILAR TO TWO OTHER ENGINES WITH THE SAME PROBLEMS. CYLINDERS REPLACED WITH NEW ECI CYLINDER	S AND CYLINDER TEMP RETURNED TO NORMAL.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE
2004082300095	20040823	00095	SO  	2004	8	23	AOC04005         	2	20040728	G	8530	AEC631397SN71	CYLINDER        			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520A      	17032	SO  					ENGINE	CHIPPED         	B			R29R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										UPON RECEIVING INSPECTION OF NEW ECI CYLINDERS, ONE CYLINDER WAS FOUND TO HAVE THE NICKEL PLATING CHIPPED (.7500 INCH LO	NG X .0312 INCH WIDE) AT THE BASE OF THE CYLINDER SKIRT. PACKAGING APPEARED TO BE ADEQUATE AND THE CYLINDER WAS NOT DROP	PED. SUSPECT PROBLEM WITH NICKEL PLATING PROCESS.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE
2005022200205	20050222	00205	CE  	2005	2	22	AOC04006         	1	20040818	G	2110	1015552119	COMPRESSOR      			BEECH 	300   	B300C       	1152933	CE  										AIR CONDITIONER	DAMAGED         	B			R29R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	8230Q	81   				FM3				PILOT REPORTED FREON AIR CONDITIONING SYSTEM INOPERATIVE FOLLOWING A FLIGHT.  FOUND COMPRESSOR CLUTCH PLATE HAS SEPARATE	D FROM THE COMPRESSOR AND WAS FOUND IN THE LOWER ENGINE COWL.  FIRE SLEEVE ON OIL LINE FROM THE OIL COOLER HAD IMPACT DA	MAGE (SLEEVE CUT) BUT NO DAMAGE TO THE OIL LINE.  NO OTHER DAMAGE NOTED.				2	L	7	2 	4T			RT	A24CE
2004033000163	20040330	00163	EU  	2004	3	30	AUS20040001      	1	20040103	G	3231	5322112082	ROD             			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG DOOR	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) LT NOSE LANDING GEAR DOOR OPERATING ROD BROKEN IN AREA LOCATEDADJACENT TO LOWER WITNESS HOLES.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004033000164	20040330	00164	GL  	2004	3	30	AUS20040002      	3	20040104	G	6111		CLIP            	MCAULY      		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	PROPELLER BLADE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1280 							(AUS) PROPELLER BLADE ROOT CIRCLIP AND ASSOCIATED SHIMS SEPARATED.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL
2004033000165	20040330	00165	NE  	2004	3	30	AUS20040003      	3	20040106	G	6110	4HFR34C652	PROPELLER       	SWRNGN      		SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE3312U    	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	LIGHTNING STRIKE	W				O				OTHER                   				C			F.O.D.                    			CR	CRUISE         	1			AU	S 			944  		DC873B					(AUS) LIGHTNING STRIKE ON RT PROPELLER AND RT FUSELAGE ADJACENT TO SAS VANE. SAS CIRCUIT BREAKER POPPED.  DAMAGE TO RT P	ROPELLER AND RT FUSELAGE CONSISTENT WITH LIGHTNING STRIKE.					2	L	7	2 	4T	3	T	RT	A5SW    	E3WE	6	C	3PNE
2004033000166	20040330	00166		2004	3	30	AUS20040004      	4	20040104	G	2210	4051601937	CONTROL PANEL   			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AUTOPILOT SYSTEM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					90101410					(AUS) AUTOPILOT MODE CONTROL PANEL FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004033000167	20040330	00167	EA  	2004	3	30	AUS20040005      	2	20040104	G	7322		NEEDLE          			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	CARBURETOR	STICKING        	W				O				OTHER                   				E	Y	B	VIBRATION/BUFFET          	ENGINE STOPPAGE           	SMOKE/FUMES/ODORS/SPARKS  	LD	LANDING        	1			AU	S 										(AUS) FIRE IN ENGINE COWLS.   SUSPECT CAUSED BY STICKING CARBURETOR NEEDLE AND SEAT CAUSING FLOODING OF ENGINE.  EXCESS 	FUEL LEAKED INTO COWLS AND IGNITED.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004033000169	20040330	00169	CE  	2004	3	30	AUS20040006      	1	20040107	G	5341	BB148	WASHER          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT & RT WING	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING LOWER ATTACHMENT BOLT WASHERS INCORRECTLY FITTED.  DAMAGE TO BATHTUB FITTING.  PERSONNEL/MAINTENANC	E ERROR.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004033000170	20040330	00170	EA  	2004	3	30	AUS20040007      	2	20040108	G	7414	103827991	ROTOR           	BENDIX      		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	MAGNETO	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			274  		9032476					(AUS) RT ENGINE MAGNETO ROTATING MAGNETIC SLIPPED ON SHAFT BY APPROXIMATELY 25 DEGREES.						1	L	7	2 	3O	3	O	 	A29CE   	1E10	5	C	P43GL
2004033000171	20040330	00171	NE  	2004	3	30	AUS20040008      	1	20040108	G	3230	2071235	BEARING RACE    			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR INTERCONNECT ROD SPHERICAL BEARING INNER RACE CRACKED. FOUND DURING INSPECTION IAW AD/S-76/66 PT4.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
2004033000172	20040330	00172	CE  	2004	3	30	AUS20040009      	1	20040105	G	7120	26011895	SUPPORT         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	H3B3M	HCB3M       	GL  	ENGINE MOUNT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE SUPPORT HOUSING FOR AIR CONDITIONER DRIVE LEAKING OIL. INVESTIGATION FOUND THE SUPPORT HOUSING ALIGNMENT SP	IGOT TO BE TOO LONG TO FIT INTO THE RECESS IN THE ENGINE MOUNT PAD. THESPIGOT BOTTOMS OUT ON THE SEAL CARRIER CAUSING A 	0.33MM (0.013IN) GAP ON THE GASKET FLANGE. THE SPIGOT BOTTOMING ON THE PAD CAUSES EXCESSIVE WEAR ON THE DRIVE SHAFT SPLI	NES PN 2601267-2 AND THE INTERNAL SPLINES ON THE DRIVE GEAR PNO 3100450-01.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P9NE
2004033000173	20040330	00173	NE  	2004	3	30	AUS20040010      	1	20040108	G	6210	7615009043050	CAP             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					MAIN ROTOR BLADE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN ROTOR BLADE TIP CAP TOP SKIN CRACKED IN AREA ADJACENT TO THE ATTACHMENT DOUBLER. CRACK LENGTH 270MM (10.62IN)	. TIP CAP HAD DISBONDED INTERNALLY FROM THE METAL DOUBLER ASSEMBLY AND THE KEVLAR SKIN HAD CRACKED AND DELAMINATED.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
2004033000174	20040330	00174	EU  	2004	3	30	AUS20040011      	1	20040110	G	5740	SD3230488XA	ATTACH FITTING  			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING STRUT FORWARD LOWER STRUT TO STUB WING ATTACHMENT LUG CORRODED ON AFT FACE. DEPTH OF CORROSION 3.327MM (0.	131IN) WHICH IS APPROXIMATELY 13 PERCENT OF THE FITTING THICKNESS.  FOUND DURING INSPECTION IAW AD/SD3-60/48 AMDT2.					2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE
2004033000175	20040330	00175	NM  	2004	3	30	AUS20040012      	1	20040101	G	2742	4012373817	ACTUATOR        			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	STABILIZER	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) YAW DAMPER LINEAR ACTUATOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004033000176	20040330	00176	EU  	2004	3	30	AUS20040013      	2	20040105	G	7200	CFM563C1	ENGINE          			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  						OVERHEATED      	W				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			AU	S 							724786			(AUS) ENGINE EXCEEDED EGT LIMITS. EGT REACHED 938 DEGREES C.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004033000177	20040330	00177	NM  	2004	3	30	AUS20040014      	1	20040105	G	2781	189929	PROXIMITY SWITCH			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					SLATS	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 					196670					(AUS) NR 3 LEADING EDGE SLAT PROXIMITY SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004033000178	20040330	00178		2004	3	30	AUS20040015      	4	20040114	G	6113	05502636	SUPPORT         	MCAULY      		CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			30   							(AUS) PROPELLER SPINNER FORWARD SUPPORT CRACKED AROUND PROPELLER BOLT ATTACHMENT HOLES.   SUPPORT HAD BEEN FITTED 30 HOU	RS AGO DUE TO THE SAME PROBLEM WITH THE PREVIOUS SUPPORT.					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
2004033000186	20040330	00186	NM  	2004	3	30	AUS20040016      	1	20040113	G	3230	161A661143	SPRING          			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					MLG UPLOCK	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR AFT UPLOCK SPRING MISSING.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004042900003	20040429	00003	NE  	2004	4	29	AUS20040018      	2	20040112	G	7210	5074T51G10	GEARBOX         			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER GEARBOX BYPASS PIN ACTIVATED.  FOUND DURING INSPECTION IAW AD/CT7/10 (SB CT7-72-0453).  METAL CONTAMINAT	ION OF CHIP DETECTOR ALSO PRESENT.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE
2004042900004	20040429	00004	NM  	2004	4	29	AUS20040019      	1	20040114	G	2910	AN81510D	COUPLING        			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD MANIFOLD	FRACTURED       	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) NR 2 HYDRAULIC SYSTEM PRESSURE MANIFOLD INLET UNION FRACTURED.  LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004042900005	20040429	00005	SO  	2004	4	29	AUS20040020      	1	20040115	G	5540	63502000	HINGE           			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	MCAULY	1C160	1C160EGM    	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER RUDDER HINGE BRACKET CONTAINED SEVERE CORROSION EXTENDING TO APPROXIMATELY 50 PERCENT OF THE DEPTH OF THE BR	ACKET.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P910
2004042900006	20040429	00006	SO  	2004	4	29	AUS20040021      	1	20040115	G	7120	J961340	MOUNT           			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	MCAULY	1C160	1C160EGM    	GL  	ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LOWER ENGINE MOUNT LOOSE.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P910
2004042900007	20040429	00007	NM  	2004	4	29	AUS20040022      	1	20040106	G	2621		EXTINGUISHER    			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					LAVATORY	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CS41B TOILET WASTE DISPOSAL SYSTEM BUILT IN FIRE EXTINGUISHER MISSING.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004042900008	20040429	00008	NM  	2004	4	29	AUS20040023      	1	20040108	G	3397	J1	CONNECTOR       			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					OEU	ARCED           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) OVERHEAD ELECTRONICS UNIT (OEU) 1-2-1 D7466 LOCATED AT DL2 HAD A DAMAGED J1 CONNECTOR. OVERHEATING OF UNIT CAUSED 	PLASTIC CONNECTOR TO MELT CAUSING SHORT CIRCUIT WITH ARCING AND SPARKING.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004042900009	20040429	00009	NM  	2004	4	29	AUS20040024      	1	20040118	G	3244	275Q221	TIRE            			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					MLG	SEPARATED       	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LT NOSE WHEEL TIRE TREAD SEPARATED.  TCAS ANTENNA COVER RIPPED OFF AND FOUND ON RUNWAY.  DAMAGE CAUSED TO NLG AIR/	GROUND SENSOR, BRACKETRY AND WIRING CONDUIT.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004042900010	20040429	00010		2004	4	29	AUS20040025      	4	20040116	G	2210		AUTOPILOT SYS   			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NEITHER AUTOPILOT WOULD TRIM THE AIRCRAFT.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004042900011	20040429	00011	EU  	2004	4	29	AUS20040026      	1	20040116	G	5270		WARNING LIGHT   			AIRBUS	330   	A300*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					CARGO DOOR	ILLUMINATED     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) FORWARD CARGO DOOR MESSAGE.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A26NM   	E13NE
2004042900012	20040429	00012	EU  	2004	4	29	AUS20040027      	1	20040118	G	2120		UNKNOWN         			AIRBUS	330   	A330300     	       	EU  	GE    	CF6   	CF680       	30025	NE  					GALLEY	FUMES           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) PLASTIC SMELLING FUMES IN REAR GALLEY. INVESTIGATION COULD FIND NO CAUSE FOR THE FUMES.						2	L	7	2 	4F	4	F	RT	        	E13NE
2004042900013	20040429	00013	NM  	2004	4	29	AUS20040028      	1	20040118	G	5523	65C2638415A	TRIM TAB        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TAB FREE PLAY EXCEEDED MAXIMUM LIMIT OF 0.9144MM (0.036IN).  FREE PLAY MEASURED 1.143MM (0.045IN).  FOUND	 DURING INSPECTION IAW AD/B737/175 AND EI 737-55-12R5.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004042900014	20040429	00014	WP  	2004	4	29	AUS20040029      	2	20040119	G	7210		PLANETARY GEAR  			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE7314R    	01518	WP  					ENGINE	VIBRATES        	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			AU	S 										(AUS) RT ENGINE VIBRATION.  INVESTIGATION FOUND THE VIBRATION CAME FROM THE PLANETARY GEARSET.						2	L	7	2 	4F	4	F	RT	A16NM   	E6WE
2004042900015	20040429	00015		2004	4	29	AUS20040030      	4	20040103	G	3418	C809072	TRANSDUCER      			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) STALL WARNING VANE FAILED DUE TO FAULTY TRANSDUCER.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004042900016	20040429	00016	NM  	2004	4	29	AUS20040031      	1	20040120	G	2910		HOSE            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					HYD SYSTEM	BURST           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK ACTUATOR HYDRAULIC HOSE BURST.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004042900017	20040429	00017	WP  	2004	4	29	AUS20040032      	1	20040120	G	3260		SWITCH          			GOVT  	N22   	N24A        	3880104	WP  										MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LT MAIN LANDING GEAR SWITCH FAILED AND WIRES BROKEN.  LANDING GEAR OVERRAN EXTENSION AND JAMMED PREVENTING LANDING	 GEAR FROM BEING RETRACTED.					1	H	7	2 	3T			 	A7PC
2004042900018	20040429	00018	CE  	2004	4	29	AUS20040033      	1	20040120	G	3230	EVE4001	MOTOR           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	HYD PUMP	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			108  							(AUS) LANDING GEAR HYDRAULIC PUMP ELECTRIC MOTOR FAULTY. INVESTIGATIONFOUND BROKEN WIRE IN THE MOTOR WINDINGS.						1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL
2004042900019	20040429	00019	NE  	2004	4	29	AUS20040034      	3	20040118	G	6114	8173891	SEAL            	HAMSTD      		DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	PROP HUB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					MFG950719					(AUS) PROPELLER HUB NR 3 BLADE SEAL LEAKING DUE TO FRACTURE OF SEALSPRING IN THE AREA ADJACENT TO THE WELDMENT.  NR 2 BL	ADE SEAL WAS ALSO REPLACED AS A PRECAUTION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004042900020	20040429	00020	NM  	2004	4	29	AUS20040035      	1	20040121	G	2824	MA20A10011	ACTUATOR        			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					FUEL TRANSFER	STICKING        	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) FUEL CROSSFEED VALVE ACTUATOR FAILED.  CROSSFEED VALVE STUCK IN THE OPEN POSITION.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004042900021	20040429	00021	SO  	2004	4	29	AUS20040036      	1	20040120	G	3241	396512	VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	ANTISKID SYS	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT IB BRAKE ANTISKID VALVE SUSPECT FAULTY.  BRAKE LOCKED ON LANDING CAUSING FAILURE OF BRAKE UNIT AND DEFLATION OF	 MAIN WHEEL TIRE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE
2004042900022	20040429	00022	CE  	2004	4	29	AUS20040037      	1	20040121	G	5744	58244659	BRACKET         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING OB AILERON ATTACHMENT BRACKET CRACKED.  INVESTIGATION FOUND INDICATIONS OF SURFACE INTERGRANNULAR CORROSIO	N AND CONFIRMATION OF A CRACK LOCATED APPROXIMATELY 3.175MM (0.125IN) BEHIND THE BEARING HOUSING. CRACK LENGTH APPROXIMA	TELY 12.7MM (0.5IN).				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004042900023	20040429	00023	NM  	2004	4	29	AUS20040038      	1	20040122	G	2752	7341529001	ACTUATOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP POWER DRIVE UNIT BYPASS VALVE ROTARY ACTUATOR FAULTY.  INVESTIGATION FOUND THE ROTARY ACTUATOR 	PURPLE INDICATION ARM PIVOT RETAINING PIN ADRIFT AND CAUSING INTERFERENCE BETWEEN THE ACTUATOR DRIVE AND ACTUATOR HOUSIN	G.				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004042900024	20040429	00024	NM  	2004	4	29	AUS20040039      	1	20040123	G	7830	CF680C2	THRUST REVERSER 			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) NR 3 AND NR 4 ENGINE THRUST REVERSERS FAILED TO OPERATE. SUSPECT CAUSED BY FROZEN LINE TO PILOT VALVE.  LOCAL TEMP	ERATURE WAS 15 DEGREES F (-9.5 DEGREES C).  BOTH THRUST REVERSERS OPERATED SATISFACTORY FOLLOWING HEATING AND RECYCLING 	OF CIRCUIT BREAKER.  NR 1 ENGINE THRUST REVERSER WAS ALREADY LOCKED OUT.				2	L	7	4 	4F	4	F	RT	A20WE   	E23EA
2004042900025	20040429	00025		2004	4	29	AUS20040040      	4	20040123	G	2215	6225734002	SERVO           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	AUTOPILOT	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			3902 							(AUS) AUTOPILOT CAUSED AIRCRAFT TO PITCH UP ON APPROACH.  INVESTIGATION FOUND ELEVATOR AUTOPILOT SERVO FAULTY.  RT ENGIN	E OVERTORQUED TO 134 PERCENT AND LT ENGINE OVERTORQUED TO 125 PERCENT DURING RECOVERY FROM AUTOPILOT MALFUNCTION.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
2004042900026	20040429	00026	NM  	2004	4	29	AUS20040041      	1	20040124	G	2710	256T34304	GEARBOX         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AILERON CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7860 							(AUS) RT INBOARD AILERON ANGLE GEARBOX FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004042900027	20040429	00027	NM  	2004	4	29	AUS20040042      	1	20040122	G	2781		SENSOR          			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					LE SLATS	OUT OF ADJUST   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 										(AUS) LEADING EDGE FLAP NR 2 EXTEND SENSOR OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004031500001	20040315	00001	NM  	2004	3	15	AUS20040043      	1	20040117	G	5210	723D1009	ACTUATOR        			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					PAX DOOR	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			34991							(AUS) RT UPPER DECK DOOR FLIGHT LOCK ACTUATOR INTERMITTENT IN OPERATION. ACTUATOR INTERMITTENTLY UNLOCKS DOOR HANDLE.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU
2004031500006	20040315	00006	CE  	2004	3	15	AUS20040044      	1	20040127	G	5740	35115050602	ATTACH FITTING  			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING UPPER AFT ATTACHMENT FITTING CORRODED.  MAXIMUM DEPTH OF CORROSION 1.27MM (0.050IN).  FOUND DURING INSPECT	ION IAW AD.					1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880
2004031500007	20040315	00007	NM  	2004	3	15	AUS20040045      	1	20040123	G	5210		PIN             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PAX DOOR	OUT OF ADJUST   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) L1 FORWARD ENTRY DOOR CRACKED OPEN IN FLIGHT WITH HANDLE MOVING APPROXIMATELY HALF WAY UP.   INVESTIGATION FOUND T	HE DOOR LOCK SENSOR LATCH PIN TO BE 0.762MM (0.030IN) OUT OF LIMITS.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004031500008	20040315	00008		2004	3	15	AUS20040046      	4	20040122	G	3418	C809072	TRANSDUCER      			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	STALL WARNING	STICKING        	W				O				OTHER                   				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT STALL WARNING SYSTEM TRANSDUCER STICKING IN FORWARD POSITION.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500009	20040315	00009	SW  	2004	3	15	AUS20040047      	1	20040130	G	5330	2722197002	DOUBLER         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE DOUBLER LOCATED AT RT EMERGENCY EXITS, BADLY CORRODED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004031500010	20040315	00010	NM  	2004	3	15	AUS20040048      	1	20040129	G	5310	65056131	DOOR FRAME      			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT CARGO DOOR CUTOUT FRAME LOCATED AT BS 1090 RIB BL28 CRACKED.  CRACK LENGTH 8.255MM (0.325IN).						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004061000075	20040610	00075	GL  	2004	6	10	AUS20040050      	2	20040129	G	7250	6890040	SHIELD          	ALLSN       	250C20R     	HUGHES	369   	369E        	4470707	WP  	ALLSN 	25OC  	250C20R     	 	GL  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1231 		CAT36291					(AUS) FIRST STAGE TURBINE NOZZLE SHIELD CRACKED AROUND 90 PERCENT OF RADIUS. ONE PIECE OF SHIELD ABOUT THE SIZE OF A 50 	CENT PIECE DISLODGED AND WAS FOUND SITTING IN THE BOTTOM OF THE COMBUSTION LINER.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004061000076	20040610	00076	SW  	2004	6	10	AUS20040052      	1	20040125	G	6320	70061L275W210A	HOSE            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR GB	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) MAIN TRANSMISSION OIL HOSE LEAKING. FURTHER INVESTIGATION FOUND THE HOSE WAS CHAFING IN THE AREA UNDER THE IDENTIF	ICATION TAG.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA
2004061000081	20040610	00081	NE  	2004	6	10	AUS20040053      	2	20040128	G	7261	4074T58P09	O-RING          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R375	R3754123F21 	NE  	ENGINE OIL	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			853  							(AUS) LT ENGINE POWER TURBINE (C) SUMP COVER O-RING SEAL LEAKING.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P17NE
2004061000093	20040610	00093	CE  	2004	6	10	AUS20040054      	1	20040114	G	2910	P40791	VALVE           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					HYD SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HYDRAULIC SHUTOFF VALVE FAULTY.  INVESTIGATION FOUND DIODE SPLICE D5100 OPEN CIRCUITED.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004061000108	20040610	00108	GL  	2004	6	10	AUS20040055      	2	20040128	G	7200	695686	ENGINE          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RIGHT	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			6242 							(AUS) RT ENGINE FAILED TO START. FURTHER INVESTIGATION FOUND N2 SHAFT NOT BEING DRIVEN BY N2 GEARBOX.  INVESTIGATION IS 	CONTINUING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061000109	20040610	00109	CE  	2004	6	10	AUS20040056      	1	20040123	G	3252	35825145	DAMPER          			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	NLG	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 			478  							(AUS) NOSE WHEEL SHIMMY DAMPER END CAP RETAINING CIRCLIP MISSING.						1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL
2004061000110	20040610	00110	CE  	2004	6	10	AUS20040058      	1	20040202	G	5554	10164001417	HINGE           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	RUDDER TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CENTER HINGE CONTAINED EXFOLIATION CORROSION IN THE HINGE BRACKET WEB.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004061000111	20040610	00111		2004	6	10	AUS20040059      	4	20040203	G	3416	5934PAM1	ALTIMETER       			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTIMETER FITTED TO AIRCRAFT WITH INCORRECT ALTITUDE RANGE. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004061000112	20040610	00112		2004	6	10	AUS20040060      	4	20040203	G	3416	5035P	ALTIMETER       			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTIMETER FITTED TO AIRCRAFT WITH INCORRECT ALTITUDE RANGE. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004061000113	20040610	00113	EU  	2004	6	10	AUS20040061      	1	20040203	G	3610	3925308	VALVE           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PNEUMATIC SYS	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 			1884 							(AUS) PNEUMATIC SYSTEM SHUTOFF VALVE FAULTY. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004061000114	20040610	00114	CE  	2004	6	10	AUS20040062      	1	20040116	G	2910	S217840095A	HOSE            			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MLG DOOR ACT	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOOR ACTUATOR HOSE FAILED. LOSS OF HYDRAULIC FLUID.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL
2004061000115	20040610	00115	EA  	2004	6	10	AUS20040063      	2	20040128	G	8530		EXHAUST VALVE   			NEWZE 	FU24  	FU24954     	6280102	WP  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	STICKING        	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 			1367 							(AUS) NR 2 CYLINDER REAR PUSHROD COVER BENT AND LEAKING OIL. SUSPECT CAUSED BY STICKING EXHAUST VALVE.						1	L	7	1 	3O	3	O	 	A9PC    	1E15	5	C	P25EA
2004061000116	20040610	00116	CE  	2004	6	10	AUS20040064      	1	20040203	G	1420	606171	CONNECTOR       			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	ENGINE	CONTAMINATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE INSTRUMENT CLUSTER CONNECTOR CONTAMINATED.						1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL
2004061000117	20040610	00117	EU  	2004	6	10	AUS20040065      	1	20040205	G	2612		HARNESS         			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502*     	41580	EA  					FIRE DETECTION	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NR 4 ENGINE FIRE WARNING SYSTEM WIRING HARNESS FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061000118	20040610	00118	EU  	2004	6	10	AUS20040066      	1	20040203	G	7931	IPTE1191000200D1	SENSOR          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	ENGINE OIL PRESS	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE PROPELLER GEARBOX OIL PRESSURE SENSOR FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE
2004061000119	20040610	00119	EU  	2004	6	10	AUS20040067      	1	20040202	G	3710	687751710	HOSE            			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1G6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	VACUUM DIST	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VACUUM HOSE KINKED. DISTORTION WAS LOCATED ON FRAME F AT THE TOP FRONT LT DOOR FRAME AND WAS CAUSED BY THE BEND RA	DIUS BEING TOO SMALL AFTER PASSING OVER THE FRAME. PERSONNEL/MAINTENANCE ERROR.					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920
2004061000120	20040610	00120	NE  	2004	6	10	AUS20040068      	2	20040205	G	7261	311136401	PLUG            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE OIL	MISSING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE BREATHER IMPELLER SHAFT COUPLING STOP/PLUG ASSEMBLYAND RETAINING RING MISSING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061000121	20040610	00121	CE  	2004	6	10	AUS20040069      	1	20040113	G	3411		FITTING         			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	PITOT/STATIC SYS	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STATIC SYSTEM T FITTING UNAPPROVED PART. FITTING WAS A COMMERCIAL PRODUCT.  PERSONNEL/MAINTENANCE ERROR.  UNAPPROV	ED PART.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA
2004061000122	20040610	00122		2004	6	10	AUS20040070      	4	20040204	G	3452	8221338002	TRANSPONDER     			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ATC	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ATC TRANSPONDER FAILED SELF TEST.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061000123	20040610	00123		2004	6	10	AUS20040071      	4	20040125	G	2300	TH2507JJ1	CONTROLLER      			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COMMUNICATIONS	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) COMMUNICATION SYSTEM CONTROL BOX FAILED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004061000124	20040610	00124		2004	6	10	AUS20040072      	4	20040104	G	2565		BATTERY         			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ESCAPE SLIDE	DISCHARGED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3R DOOR ESCAPE SLIDE EMERGENCY LIGHTING FAILED TO ILLUMINATE. INVESTIGATION FOUND THE BATTERY FLAT.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU
2004061000125	20040610	00125	CE  	2004	6	10	AUS20040073      	1	20040210	G	5753	052390114	ARM             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SUPPORT ARM TO FLAP SUPPORT ARM RIB RIVETS MISSING DUE TO CORROSION.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004061000126	20040610	00126	CE  	2004	6	10	AUS20040074      	1	20040105	G	8011		DRIVE GEAR      			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE STARTER	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			154  							(AUS) ENGINE STARTER MOTOR DRIVE GEAR TEETH STRIPPED.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL
2004061000127	20040610	00127	EA  	2004	6	10	AUS20040075      	2	20040205	G	7322	105267	CARBURETOR      			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	FUEL CONTROL	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			62   							(AUS) CARBURETOR FAULTY.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL
2004061000128	20040610	00128	CE  	2004	6	10	AUS20040076      	1	20040211	G	5711		SPAR            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING SPAR WEB DISBONDED IN AREA LOCATED AT CWS 57.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004061000129	20040610	00129	CE  	2004	6	10	AUS20040077      	1	20040205	G	2497		WIRE HARNESS    			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	DC POWER DISTRIB	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING LOOM CHAFED AND BURNED BY ELEVATOR COUNTERWEIGHT.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL
2004061000130	20040610	00130	CE  	2004	6	10	AUS20040078      	1	20040211	G	3210	12411171	LANDING GEAR    			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MAINS	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LT MAIN LANDING GEAR LEG COLLAPSED.  THE LEG WAS A NEWLY FITTED ITEM AND FAILED 530MM (20.8IN) FROM THE IB TIP OF 	THE LEG.  AIRCRAFT TAILPLANE, ELEVATOR, WINGTIP AND POD DAMAGED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA
2004061000131	20040610	00131	NM  	2004	6	10	AUS20040080      	1	20040206	G	2910		HYDRAULIC SYSTEM			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					HYDRAULIC SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061000132	20040610	00132	EA  	2004	6	10	AUS20040081      	2	20040210	G	7322	MA4SPA	CARBURETOR      	LYC         		PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	FUEL CONTROL	ICED            	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 					DC2950					(AUS) ENGINE FAILED DURING LANDING. SUSPECT CAUSED BY CARBURETOR ICING.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004061000133	20040610	00133	CE  	2004	6	10	AUS20040082      	1	20040203	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   			CL	CLIMB          	1			AU	S 			207  							(AUS) ALTERNAOR FAILED.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL
2004061000134	20040610	00134	SO  	2004	6	10	AUS20040083      	1	20040204	G	2710	3866003	FITTING         	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	AILERON CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NA					(AUS) LT AND RT AILERON CONTROL ROD ATTACHMENT FITTINGS, LOOSE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004061000136	20040610	00136	EA  	2004	6	10	AUS20040084      	2	20040207	G	8520	LW11997	SEAL            			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360C1A   	41514	EA  					CRANKSHAFT	WORN            	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE CRANKSHAFT SEAL LEAKING. INVESTIGATION FOUND SEAL HAD DISINTEGRATED AROUND THE SEALING LIP.						1	G	7	1 	3O	3	O	 	4H12    	1E10
2004061000137	20040610	00137	EA  	2004	6	10	AUS20040085      	2	20040208	G	8520	LW11997	SEAL            			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					CRANKSHAFT	WORN            	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE CRANKSHAFT SEAL LEAKING. INVESTIGATION FOUND SEAL HAD DISINTEGRATED AROUND THE SEALING LIP. THIS IS A REPLA	CEMENT SEAL AFTER THE SEAL FAILURE IN MDR 04/0084.					1	G	7	1 	3O	3	O	 	4H12    	1E10
2004061000146	20040610	00146	NM  	2004	6	10	AUS20040086      	1	20040206	G	2740	AR6460M2	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					STAB CONTROL	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) STABILIZER TRIM ACTUATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061000148	20040610	00148	EU  	2004	6	10	AUS20040087      	1	20040205	G	6123	1310176	VALVE           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	PROP FEATHERING	FAULTY          	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE PROPELLER FEATHER SOLENOID VALVE FAULTY.   VALVE WAS SLOWLY BLEEDING PCU PRESSURE.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL
2004061000149	20040610	00149	EU  	2004	6	10	AUS20040088      	1	20040211	G	3242	1597400	ROTOR           	CLEVELAND   		PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					1229					(AUS) RT BRAKE ROTOR BROKEN INTO TWO PIECES WITH ONE PIECE LODGING BETWEEN THE BRAKE ASSEMBLY AND WHEEL. ON DISASSEMBLY 	IT WAS NOTED THAT THE ROTOR HAD BEEN BROKEN FOR SOME TIME.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004061000150	20040610	00150	NE  	2004	6	10	AUS20040089      	3	20040206	G	6110	4HFR34C652	PROPELLER       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT &  RT	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT AND RT PROPELLERS FAULTY.   BOTH ENGINES OVERTEMPED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061000152	20040610	00152	CE  	2004	6	10	AUS20040090      	1	20040102	G	8011	643109	SPRING          	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE STARTER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE STARTER ADAPTER CLUTCH SPRING TANG BROKEN OFF CAUSING SPRING TO SLIP ON GEAR.   BROKEN PIECE OF SPRING FOUN	D IN BASE OF STARTER ADAPTER.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA
2004061000153	20040610	00153	EU  	2004	6	10	AUS20040091      	1	20040209	G	3246	5006227	WHEEL           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	NLG	VIBRATES        	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR WHEELS VIBRATING.  INVESTIGATION COULD FIND NO OBVIOUS DEFECTS BUT REPLACED THE NOSE WHEELS AND 	SERVICED THE SHIMMY DAMPER.  THE AIRCRAFT WAS THEN RETURNED TO SERVICE WITH NO FURTHER DEFECTS REPORTED.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE
2004061000154	20040610	00154	CE  	2004	6	10	AUS20040092      	1	20040203	G	5730	8135105	SKIN            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	LT WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING INNER LEADING EDGE SKIN DELAMINATING IN AREA LOCATED ABOVE THE BYPASS DUCT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004061000155	20040610	00155	CE  	2004	6	10	AUS20040093      	1	20040205	G	3230		CIRCUIT BREAKER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	TRIPPED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR WOULD NOT EXTEND.  CIRCUIT BREAKER (60AMP)FOUND TRIPPED.  CB RESET AND RETRACTION TESTS CARRI	ED OUT WITH NO REOCCURANCE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004061000156	20040610	00156		2004	6	10	AUS20040094      	4	20040210	G	6122	661001002	GOVERNOR        			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	PROPELLER	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) RT PROPELLER OVERSPEED GOVERNOR HAD AN INTERMITTENT FAULT.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL
2004061000157	20040610	00157	EU  	2004	6	10	AUS20040095      	1	20040212	G	2450	6TC210	CIRCUIT BREAKER 			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC POWER	FAILED          	W				O				OTHER                   				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 										(AUS) RT WINDSCREEN HEAT CIRCUIT BREAKER OVERHEATED CAUSING LOSS OF AC POWER AND SMOKE IN THE COCKPIT.   WIRING, BUSBAR 	AND CB LA5 LOCATED ADJACENT TO CB ALSO REPLACED DUE TO DAMAGE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061000158	20040610	00158	CE  	2004	6	10	AUS20040096      	1	20040206	G	5311		FRAME           			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) FUSELAGE FRAME LOCATED AT RF 265-760 CRACKED IN AREA ADJACENT TO FLOORBEAM.   FOUND DURING INSPECTION IAW AD/BEECH	200/65.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061000159	20040610	00159	NM  	2004	6	10	AUS20040097      	1	20040209	G	2761	65448517	ACTUATOR        			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					DRAG CONTROL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 GROUND SPOILER OB ACTUATOR BODY CRACKED AND LEAKING IN AREA NEXT TO RETRACT FITTING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061000160	20040610	00160	NM  	2004	6	10	AUS20040098      	1	20040210	G	2730		BEARING         			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					ELEVATOR CONTROL	SEIZED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL CENTERING UNIT MOUNT BEARING SEIZED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061000161	20040610	00161	EU  	2004	6	10	AUS20040099      	1	20040212	G	7712	02597	SWITCH          			FOKKER	F27   	F27MK500    	4990629	EU  	RROYCE	DART  	DART531     	 	EU  	ROTOL	R4304	R1934304    	EU  	ENGINE	FAULTY          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			736  							(AUS) RT ENGINE LOW TORQUE SWITCH FAULTY.   WORKSHOP INVESTIGATION FOUND THE FOLLOWING DEFECTS WITH THE SWITCH:  SLIGHT 	DISTORTION ON SWITCH BASE  SWITCH CAP O'RING GROOVES SCORED.   PIN TERMINAL ASSEMBLY HAD CORROSION ON PINS.					2	H	7	2 	4T	4	T	 	A817    	E297	6	C	P899
2004061500019	20040615	00019	NE  	2004	6	15	AUS20040100      	2	20040214	G	7200	3038400	ENGINE          			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	LEFT	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			AU	S 							PCE123314			(AUS) LT ENGINE OIL LEAK EVIDENT IN P2.5 CAVITY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061000178	20040610	00178	NE  	2004	6	10	AUS20040101      	2	20040216	G	7230	3035569	IMPELLER        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ENG COMPRESSOR	DAMAGED         	W				O				OTHER                   				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 										(AUS) LT ENGINE LP IMPELLER BADLY DAMAGED.  FURTHER INSPECTION ALSO FOUND SEVERE DAMAGE TO THE HP IMPELLER AS WELL AS TH	E GAS GENERATOR CASE AND THE LP DIFFUSER CASE.  A DENT WAS ALSO FOUND IN THE COMBUSTION CHAMBER OUTER LINER.  SUSPECT CA	USED BY FOD.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
2004061000179	20040610	00179	NE  	2004	6	10	AUS20040102      	2	20040211	G	7250	3053094CL	SHROUD          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	TURBINE SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE TURBINE SHROUD AND BLADES DAMAGED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004061000180	20040610	00180	SO  	2004	6	10	AUS20040103      	1	20040205	G	5312	62444005	BULKHEAD        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD CORRODED IN AREA BENEATH VERTICAL FIN FRONT ATTACHMENT PLATE AND STRINGER HAT ASSEMBLY ATTACHMEN	T AREA.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004061000181	20040610	00181	SO  	2004	6	10	AUS20040104      	1	20040205	G	3222	35123002	FORK            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	NLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK CONTAINED INTERGRANNULAR CORROSION IN ATTACHMENT AREA.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004061000184	20040610	00184	SW  	2004	6	10	AUS20040105      	1	20040122	G	5711	129579	SPAR            			BBAVIA	7     	7EC         	2110120	SW  	LYC   	O235  	O235C1      	41505	EA  	AMTR	C8289	C8289       	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING FRONT AND REAR SPARS CRACKED. CRACKS APPEAR TO ALIGN WITH THE ATTACHMENT FITTING BOLT HOLES.  SPARS ARE CO	NSTRUCTED FROM TIMBER.  FOUND DURING INSPECTION IAW AD/CHA/23 AMDT4.					1	H	7	1 	3O	3	O	 	A759    	E223	5	N	EXPP5N
2004061000185	20040610	00185	EU  	2004	6	10	AUS20040106      	1	20040217	G	2434	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DC GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 GENERATOR DRIVESHAFT WORN AT INNER (FORWARD) BEARING AREA.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004061000186	20040610	00186	SW  	2004	6	10	AUS20040107      	1	20040102	G	5302		SKIN            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAILBOOM CRACKED IN LOWER SKIN TO UPPER SKIN ATTACHMENT RIVET LINE LOCATED ON AFT RT SIDE.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004061500020	20040615	00020	NM  	2004	6	15	AUS20040108      	1	20040211	G	4930	82830105139	PIPE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	APU FUEL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU GRAVITY FUEL FEED LINE CHAFED.  DEPTH OF DAMAGE 0.0508MM (0.002IN). FOUND DURING INSPECTION IAW AD/DHC-8/093 (	SB8-49-019).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061000187	20040610	00187	EU  	2004	6	10	AUS20040109      	1	20040213	G	2910	1379305A155	HOSE            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K	F		FLUID LOSS                	FLT CONT AFFECTED         		DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK FLEXIBLE HOSE FAILED.   LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
2004061000189	20040610	00189	NM  	2004	6	10	AUS20040111      	1	20040213	G	5270		SWITCH          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					DOOR WARNING SYS	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN CARGO DOOR NR 1 AND NR 7 LATCH INDICATOR MICROSWITCHES OUT OF ADJUSTMENT.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004061000191	20040610	00191	EU  	2004	6	10	AUS20040112      	1	20040215	G	2120		ODOR            			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) ELECTRICAL ODOR IN CABIN IN AREA OF SEAT 48JK.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE
2004061000192	20040610	00192	EU  	2004	6	10	AUS20040113      	1	20040219	G	6730	SC5072	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					TAIL ROTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			200  							(AUS) TAIL ROTOR SERVO FAULTY.  INVESTIGATION FOUND ALTHOUGH FULL TAIL ROTOR PEDAL CONTROL WAS AVAILABLE, THE ACTUATOR G	AVE LIMITED OUTPUT.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004061000193	20040610	00193	CE  	2004	6	10	AUS20040114      	1	20040213	G	8011	D083645	GEAR            	LYC         		CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE STARTER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					D083645					(AUS) STARTER MOTOR BENDIX DRIVE GEAR DISINTEGRATED.  ENGINE RING GEAR TEETH DAMAGED.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL
2004061000205	20040610	00205	CE  	2004	6	10	AUS20040115      	1	20040218	G	5311	10144009133	FRAME           			BEECH 	200   	B200C       	1152924	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 (3OFF) LOCATED AT STN 285.188, STN 278.5 AND STN291.875 CRACKED. FRAME PART NUMBERS PN 101-440091-	33, PN 101-440090-27 AND PN 101-440092-31. FOUND DURING INSPECTION IAW AD.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061000206	20040610	00206	CE  	2004	6	10	AUS20040116      	1	20040216	G	8011	PM2401H	MOTOR           	LYC         		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	ENGINE STARTER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					85035913					(AUS) ENGINE STARTER MOTOR BENDIX DRIVE WOULD NOT ENGAGE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004061000208	20040610	00208	EA  	2004	6	10	AUS20040118      	2	20040220	G	7313	73772	NOZZLE          	LYC         		PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	FUEL INJECTOR	BLOCKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) NR 4 CYLINDER FUEL INJECTOR NOZZLE BLOCKED.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920
2004061000209	20040610	00209	NM  	2004	6	10	AUS20040119      	1	20040224	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/XMSN	DISTORTED       	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   	E274
2004061000210	20040610	00210	CE  	2004	6	10	AUS20040120      	1	20040202	G	5312	8050	STRUCTURE       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD CLEAT LOCATED AT STRINGER 7L AND BULKHEAD BEAM AT STRINGER 6L CRACKED. FOUND DURING INSPECT	ION IAW AD.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004061000212	20040610	00212	SW  	2004	6	10	AUS20040121      	1	20040220	G	2731	2742004003	ACTUATOR        			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ELEVATOR TAB	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) PITCH TRIM ACTUATOR SLIPPING.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004061000213	20040610	00213	SW  	2004	6	10	AUS20040122      	1	20040224	G	2740	27043062009	BRACKET         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER PITCH TRIM ACTUATOR UPPER ATTACHMENT BRACKET CRACKED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004061000214	20040610	00214	NM  	2004	6	10	AUS20040123      	1	20040224	G	3230	BACH8A06EE0260T	HOSE            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					MLG	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR ACTUATOR UP LINE LEAKING DUE TO CHAFING ON B SYSTEM LOW PRESSURE RETURN LINE.  ENGINE DRIVEN 	PUMP FAILED AND RETURN FILTERS CONTAMINATED.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061000216	20040610	00216	SW  	2004	6	10	AUS20040124      	1	20040224	G	2752	2736053001	ACTUATOR        			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING TRAILING EDGE FLAP ACTUATOR HOUSING CRACKED AND LEAKING FROM A HAIRLINE FRACTURE AT THE END OF THE HOUSING	.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061000217	20040610	00217	CE  	2004	6	10	AUS20040125      	1	20040219	G	2497		WIRE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT WING	MISROUTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING IN BOTH LT AND RT WINGS CONTACTING FUEL VENT LINES LOCATED AT WS 145.   PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA
2004061000218	20040610	00218	EA  	2004	6	10	AUS20040126      	2	20040224	G	7322	105235	VALVE           	LYC         	O540J3C5    	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	FUEL CONTROL	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					75113808					(AUS) CARBURETOR ACCELERATOR PUMP DISCHARGE CHECK VALVE LOOSE AND SEPARATED.						1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA
2004061000220	20040610	00220	NM  	2004	6	10	AUS20040127      	1	20040224	G	2120	61B600051155	BLANKET         			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					AIR DISTRIBUTION	DETERIORATED    	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) APU DUCT INSULATION BLANKET BURNED AND IN POOR CONDITION.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU
2004061000225	20040610	00225	CE  	2004	6	10	AUS20040128      	1	20040224	G	3260		SWITCH          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR UPLOCK SWITCH OUT OF ADJUSTMENT.  MICROSWITCH WAS SWITCHING OFF LOADING VALVE BUT NOT THE IN 	TRANSIT LIGHT. INVESTIGATION FOUND SOME WEAR IN THE SWITCH WHICH AFFECTED ADJUSTMENT.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004061000226	20040610	00226	EU  	2004	6	10	AUS20040129      	1	20040226	G	1430	HC554H0074000	BOLT            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RUDDER STRUCTURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER FIXED HINGE BOLT CRACKED UNDER BOLT HEAD.   BOLT IS LOCATED AT VERTICAL STABILISER RIB 5.  CRACK LENGTH 2.2	86MM (0.090IN).  FOUND DURING NDT INSPECTION.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061000227	20040610	00227	NE  	2004	6	10	AUS20040130      	1	20040225	G	7170	0174078010	DRAIN VALVE     			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) ENGINE START DRAIN VALVE LEAKING DUE TO ORING SEAL FAILURE.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
2004061000229	20040610	00229	CE  	2004	6	10	AUS20040131      	1	20040225	G	2910	4529101060001	PIPE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HYDRAULIC SYSTEM	FRACTURED       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PRESSURE LINE LOCATED IN RT ENGINE PYLON AREA FRACTURED AND LEAKING IN AREA OF RINGLOK SWAGE ON UPPER EN	D OF THE LINE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004061000238	20040610	00238	NM  	2004	6	10	AUS20040132      	1	20040226	G	7120	UL22991	LINK            	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					ENGINE MOUNT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT ENGINE FAIL SAFE LINK ASSEMBLY DAMAGED. RT AFT ATTACHMENT HARDWARE VERY LOOSE AND NUT WAS NOT SECURED BY SPLIT	 PIN. FOLLOWING DISASSEMBLY OF THE FAIL SAFE LINK IT WAS FOUND THAT THE LP TURBINE SUPPORT TO WHICH THE LINK WAS ATTACHE	D WAS ALSO DAMAGED WITH THE ATTACHMENT HOLE BEING ELONGATED AND FRETTING DAMAGE CAUSED BY THE LINK. ATTACHMENT BUSHING A	ND BOLT BOTH BADLY WORN.			2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004061000239	20040610	00239	EU  	2004	6	10	AUS20040133      	1	20040206	G	5711		SPAR CAP        			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1G6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR WING SPAR BOTTOM SPAR CAP CRACKED IN AREA OF LT SIDE WING ATTACHMENT. CRACK LENGTH 6MM (0.236IN). FOUND DURIN	G EDDY CURRENT INSPECTION.					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920
2004061000240	20040610	00240	CE  	2004	6	10	AUS20040134      	1	20040114	G	3230	50450107	TORQUE TUBE     			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR TORQUE TUBE BROKEN.						1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P22EA
2004061000241	20040610	00241	SO  	2004	6	10	AUS20040135      	1	20040228	G	2721	6345703	ARM             			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	RUDDER TAB	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) RUDDER TRIM ARM ASSEMBLY SEPARATED FROM RUDDER PEDAL BAR.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P25EA
2004061000243	20040610	00243	EA  	2004	6	10	AUS20040136      	2	20040227	G	7322	252434710	FUEL CONTROL    			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE	FAULTY          	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		DE	DESCENT        	1			AU	S 			272  							(AUS) ENGINE FUEL CONTROL UNIT FAULTY.  INVESTIGATION FOUND PRESSURE ON THE MIXTURE ARM CHANGED THE FUEL FLOW RATE CAUSI	NG THE ENGINE TO STOP.					1	G	7	1 	3O	3	O	 	4H12    	1E10
2004061400001	20040614	00001		2004	6	14	AUS20040137      	4	20040229	G	2215	065001501	SERVO           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AUTOPILOT SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AUTOPILOT ROLL SERVO CAPSTAN FOUND IN PIECES ON AIRCRAFT FLOOR. SIX FASTENEING SCREWS FOUND IN CLOSE PROXIMITY TO 	THE SERVO MOUNT.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004061400002	20040614	00002	SO  	2004	6	14	AUS20040138      	1	20040222	G	5313		LONGERON        			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER LT LONGERON TUBE CRACKED IN AREA BETWEEN FORWARD WELD OF LT REAR STABILIZER SUPPORT AND FORWARD WELD OF CROS	S BRACE TUBE.					1	H	7	1 	3O	3	O	 	1A2     	E274	5	N	P88614
2004061400003	20040614	00003	NE  	2004	6	14	AUS20040139      	3	20040223	G	6111	8173881	SEAL            	HAMSTD      		DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER BLADE	UNSERVICEABLE   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					20030212					(AUS) RT PROPELLER NR 3 BLADE SEAL BADLY SPLIT AND SPRING DISTORTED.  NR 1 AND NR 4 BLADE SEALS BROKEN WITH SIGNS OF DIS	TORTION. SEALS WERE FOUND TO HAVE INCORRECT SPRINGS FITTED. LT PROPELLER NR 2 AND NR 3 BLADE SEALS ALSO DAMAGED DUE TO F	IT OF INCORRECT SPRINGS. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061400004	20040614	00004	NM  	2004	6	14	AUS20040140      	1	20040228	G	3244	277A6000454	TIRE            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT NOSE WHEEL TIRE TREAD SEPARATING.   APPROXIMATELY 100MM (4IN) OF TREAD SEPARATED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061400005	20040614	00005	NM  	2004	6	14	AUS20040141      	1	20040229	G	2824	405744	ACTUATOR        			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TRANSFER VALVE	FAILED          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 					3842					(AUS) FUEL CROSSFEED VALVE ACTUATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061400006	20040614	00006	EA  	2004	6	14	AUS20040142      	2	20040302	G	7414	10400553	BEARING         	CONT        		SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAGNETO	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 					B259305G					(AUS) MAGNETO DRIVE SHAFT OUTER BEARING COMPLETELY DESTROYED.  BEARING HAD BEEN RUNNING DRY FOR SOME TIME.  SUSPECT MAGN	ETO ASSEMBLED WITHOUT GREASE IN THE BEARING.   PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920
2004061400007	20040614	00007	NE  	2004	6	14	AUS20040143      	2	20040301	G	7210	CPGB1384	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 			2983 				CPGB1384			(AUS) COMBINING GEARBOX CHIP DETECTOR METAL CONTAMINATION.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA
2004061400008	20040614	00008		2004	6	14	AUS20040144      	4	20040219	G	6122	8210263	GOVERNOR        	MCAULY      		SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			813  							(AUS) LT ENGINE PROPELLER GOVERNOR FAILED.  WORKSHOP INVESTIGATION AND DISASSEMBLY OF THE GOVERNOR FOUND A NUMBER OF FAU	LTS WITH THE UNIT, HOWEVER THE MAIN FAILURE MODE WAS DUE TO THE FLYWEIGHT HEAD ASSEMBLY MISSING ALL TRIGGER TEETH, CAUSE	D BY CONTACT WITH THE MONOPOLE DURING ROTATION OF THE FLYWEIGHT HEAD.  THE MONOPOLE HAD RECENTLY BEEN ADJUSTED AS A FAUL	T FINDING ACTION FOR THE EGT FLUCTUATIONS.  IT IS BELIEVED THAT THIS ADJUSTMENT CAUSED THE REDUCTION IN SETUP GAP BETWEE	N THE MONOPOLE AND THE FLYWEIGHT TEETH.  ALL OTHER DAMAGE TO THE GOVERNOR FOUND DURING DISSASSEMBLY WAS SUBSEQUENT AND D	UE TO THE INITIAL DAMAGE. PERSONNEL/MAINTENANCE ERROR.	2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061400009	20040614	00009	CE  	2004	6	14	AUS20040145      	1	20040223	G	3230	131378252CL	LINK            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL RETRACTION CHAIN CONNECTING LINK INCORRECTLY FITTED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061400010	20040614	00010	WP  	2004	6	14	AUS20040146      	1	20040301	G	1430	AN626	BOLT            		245109      	FLTCHR	24    	FU24AAIRPTS 	3530204	WP  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR TOP TORQUE LINK BOLT FAILED.						1	L	7	1 	3O	3	O	 	4A12    	1E15	5	C	P25EA
2004061400011	20040614	00011	EU  	2004	6	14	AUS20040148      	1	20040303	G	5523	HC552H0321001	PLATE           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ELEVATOR TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ELEVATOR TAB NR 1 HINGE UPPER REINFORCEMENT PLATE CONTAINED LEVEL 2 CORROSION.  CORROSION DIMENSIONS WERE 25.4M	M (1IN) BY50.8MM (2IN) AND PENETRATING TO FULL DEPTH.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061400012	20040614	00012	SW  	2004	6	14	AUS20040149      	1	20040302	G	2913	99101371	PUMP            			GULSTM	G73   	G73         	3951802	SW  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			291  							(AUS) RT HYDRAULIC PUMP FAILED. INVESTIGATION FOUND A FINE BROWN COATING OVER THE SURFACE OF THE PUMP.  SUSPECT PUMP OVE	RHEATED.					1	H	7	2 	3R	4	T	 	A783    	E4EA	6	C	P15EA
2004061400013	20040614	00013	CE  	2004	6	14	AUS20040150      	1	20040218	G	2612	473275	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT ENGINE	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 					1527					(AUS) LT ENGINE FORWARD UPPER FIRE DETECTOR SUSPECT FAULTY.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061500022	20040615	00022	NE  	2004	6	15	AUS20040151      	2	20040301	G	7200	PT6A42	ENGINE          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	LEFT	FLUCTUATES      	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) LT ENGINE FUEL FLOW AND ENGINE TORQUE FLUCTUATING BEFORE ENGINE STARTED TO ROLLBACK.  INVESTIGATION COULD FIND NO 	CAUSE FOR THE DEFECT.  THE ENGINE WAS GROUND RUN AND THEN TEST FLOWN WITH NO FURTHER REOCCURRENCE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004061400014	20040614	00014	EU  	2004	6	14	AUS20040152      	1	20040302	G	3610	JR28930A	DUCT            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PNEUMATIC SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 BLEED AIR SYSTEM BIFURCATED DUCT CRACKED IN AREA OF SUPPORT ATTACHING BRACKET ADJACENT TO THE PRSOV. CRACK LE	NGTH APPROXIMATELY 25MM (0.984IN).					2	L	7	2 	4F	4	F	RT	        	E25NE
2004061400015	20040614	00015	NM  	2004	6	14	AUS20040153      	1	20040302	G	1430	26084383	RIVET           	HONEYWELL   		BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					BRAKE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 					B0367					(AUS) RT MAIN LANDING GEAR NR 3 BRAKE ASSEMBLY BRAKE PADS LOCATED BETWEEN NR 2 AND NR 3 ROTORS HAD SEPARATED AND JAMMED 	THE BRAKE UNIT.  INVESTIGATION FOUND PAD SEPARATION WAS DUE TO RIVET FAILURE.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN
2004061400016	20040614	00016	CE  	2004	6	14	AUS20040154      	1	20040303	G	3221	5842000213	TRUNNION        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PN5842000216					(AUS) NOSE LANDING GEAR TRUNNION CRACKED IN RADIUS LOCATED ON LOWER SIDE OF THE LT ATTACHMENT LUG. CRACK LENGTH APPROXIM	ATELY 12MM(0.472IN). THE TRUNNION WAS THE EARLIER PN 5842000-213 WITH SMALLER DIAMETER ATTACHMENT LUGS. FOUND DURING INS	PECTION IAW MFG SB MEB 88-5 REV2.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA
2004061400017	20040614	00017	SW  	2004	6	14	AUS20040155      	1	20040303	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			AU	S 										(AUS) ENGINE/TRANSMISSION OIL COOLER INTERNAL LEAK. THE LEAK ALLOWED TRANSMISSION OIL TO ENTER THE COMBINING GEARBOX OIL	 SYSTEM UNDERPRESSURE AND OVERFILL THE COMBINING GEARBOX WHICH THEN VENTED THROUGH THE BREATHER.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA
2004061400018	20040614	00018	SO  	2004	6	14	AUS20040156      	1	20040220	G	2810		FUEL TANK       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	CONTAMINATED    	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE MISFIRING IN FLIGHT. INVESTIGATION FOUND CONTAMINATION IN THE LT FUEL TANK.   A HAIR LIKE FIBER WAS FOUN	D IN THE FUEL FILTERS AND INJECTOR NOZZLES.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004061400019	20040614	00019	NM  	2004	6	14	AUS20040157      	1	20040305	G	2910		O-RING          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYDRAULIC SYS	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC SYSTEM A PRESSURE MODULE SUPPLY LINE O-RING SEAL FAILED.   LOSS OF HYDRAULIC FLUID.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004061400020	20040614	00020	CE  	2004	6	14	AUS20040159      	1	20040302	G	8011	D104103	GEAR            	LYC         		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE STARTER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					D104103					(AUS) STARTER BENDIX DRIVE GEAR DISINTEGRATED DURING ENGINE START.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004061400021	20040614	00021	NM  	2004	6	14	AUS20040160      	1	20040228	G	3412	102LA2AG	PROBE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					OUTSIDE AIR TEMP	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			3458 							(AUS) TAT PROBE FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061400022	20040614	00022	EA  	2004	6	14	AUS20040161      	2	20040228	G	8530	LW12416	CYLINDER        			GULSTM	STC   	STCAA5      	       	    	LYC   	O320  	O320E2G     	41508	EA  	MCAULY	1C172	1C172*      	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1001 				L4190629A			(AUS) NR 1 CYCLINDER WORN. PISTON, RING, & BARREL CLEARANCES EXCESSIVE.						1	L	7	1 	3O	3	O	 	A16EA   	E274	5	N	P910
2004061400023	20040614	00023		2004	6	14	AUS20040162      	4	20040209	G	3416	AW2835AB06	ALTIMETER       			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN ALTIMETER OUT OF CALIBRATION.  FOUND DURING INSPECTION IAW AD/INST/9.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061400024	20040614	00024		2004	6	14	AUS20040163      	4	20040209	G	3416	WL102AM53	ALTIMETER       			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STANDBY ALTIMETER/AIRSPEED INDICATOR FAULTY. BENCH TESTING FOUNDTHE LIGHTING UNSERVICEABLE, EXCESSIVE FRICTION AND	 THE STOP AND JUMP TEST OUTSIDE LIMITS. FOUND DURING INSPECTION IAW AD/INST/9 AND BENCH TEST IAW CMM 34-10-61 REV9.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061400025	20040614	00025	EA  	2004	6	14	AUS20040164      	2	20040224	G	8520	LW13908	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L640561A			(AUS) LT ENGINE CAMSHAFT LOBE NR 2 BADLY SPALLED.   METAL CONTAMINATION OF OIL SYSTEM.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004061400026	20040614	00026	CE  	2004	6	14	AUS20040165      	1	20040306	G	7931	1013890235	TRANSDUCER      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENG OIL PRESS	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE OIL PRESSURE TRANSDUCER FAULTY.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004061400027	20040614	00027	GL  	2004	6	14	AUS20040166      	2	20040308	G	7261	AN8334J	FITTING         			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENG OIL PRESS	SEPARATED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							CAG30074BA			(AUS) ENGINE TURBINE OIL PRESSURE FITTING PN AN833-4J SEPARATED FROM GEARBOX COVER PN 6898569 ALLOWING ENGINE OIL TO BE 	PUMPED OVERBOARD.  SUSPECT CAUSED BY B NUT VIBRATING LOOSE ALLOWING THE FITTING TO FRET IN THE COVER. REDUCED OIL FLOW (	AND COOLING) TO THE TURBINE DAMAGED THE TURBINE BEARINGS. BEARING DEBRIS COLLECTED ON THE FORWARD CHIP PLUG.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004061400028	20040614	00028	EU  	2004	6	14	AUS20040167      	1	20040225	G	6123	30048000011	AUTOFEATHER SYS 			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	PROPELLER	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) AUTOFEATHER UNIT SUSPECT FAULTY.  INVESTIGATION COULD FIND NO FAULTS BUT THE LT AND RT AUTOFEATHER UNIT PLUGS WERE	 CLEANED AND FUNCTIONAL TESTS CARRIED OUT.					2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG
2004061400029	20040614	00029	CE  	2004	6	14	AUS20040168      	1	20040309	G	5320	12131842	TUNNEL WALL     			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT SIDE NOSE LANDING GEAR TUNNEL WALL CRACKED IN AREA NEAR RT NOSE LANDING GEAR TORQUE TUBE STIFFENER PN 1213801-2	.  FURTHER INVESTIGATION OF THE STRUCTURE FOUND CRACKS IN THE LT AND RT NOSE GEAR TUNNEL WALLS LOCATED AT THE LOWER END 	OF THE FORWARD ENGINE SHOCK MOUNT ASSEMBLY CHANNEL. CRACKS WERE ALSO FOUND IN THE STIFFENERS PN 1213195-1 AND PN 1213195	-2). AREA HAD BEEN MODIFIED IAW STC NO SA00796AT.			1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL
2004061400030	20040614	00030	CE  	2004	6	14	AUS20040169      	1	20040309	G	5320	12131842	TUNNEL WALL     			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT SIDE NOSE LANDING GEAR TUNNEL WALL CRACKED IN AREA NEAR RT NOSE LANDING GEAR TORQUE TUBE STIFFENER PN 1213801-2	.   AREA HAD BEEN MODIFIED IAW STC NO SA00796AT.  CRACKING WAS FOUND DURING INSPECTION FOLLOWING DISCOVERY OF SIMILAR CR	ACKING AS REPORTED IN MDR 04/0168.				1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL
2004061400031	20040614	00031	NM  	2004	6	14	AUS20040170      	1	20040307	G	2761	252T13013	ACTUATOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					DRAG CONTROL	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			47713							(AUS) NR 6 SPOILER POWER CONTROL ACTUATOR FILTER HOUSING SPLIT. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061400032	20040614	00032	NM  	2004	6	14	AUS20040171      	1	20040216	G	2170	M01AB010102E	HUMIDIFIER      			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					COCKPIT	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 					463					(AUS) HUMIDIFIER FAILED.  BURNING ODOR ON FLIGHTDECK.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061400033	20040614	00033	NM  	2004	6	14	AUS20040172      	1	20040307	G	2823	737M28500011	VALVE           			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NR 2 ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE FUEL SYSTEM SPAR VALVE FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004080600018	20040806	00018	CE  	2004	8	6	AUS20040173      	1	20040223	G	5597		WIRE            			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	ELEVATOR TAB ST	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ELEVATOR TRIM TAB HINGE WIRE MANUFACTURED FROM MILD STEEL. RT TRIM TAB FREEPLAY 7.366MM (0.290IN) AND LT TRIM T	AB FREEPLAY 9.829MM (0.387IN).  MAXIMUM FREEPLAY 2.133MM (0.084IN).  PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA
2004061400034	20040614	00034	NM  	2004	6	14	AUS20040174      	1	20040309	G	3231	4000894E	BELLCRANK       			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	RT MLG DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					R133819					(AUS) RT MAIN LANDING GEAR DOOR BELLCRANK LUG BROKEN.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA
2004061400035	20040614	00035	EU  	2004	6	14	AUS20040175      	1	20040311	G	3260	5EN16	SWITCH          			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR SQUAT SWITCH FAULTY.  INVESTIGATION FOUND THE CONTACTS HAD HIGH RESISTANCE.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
2004061400036	20040614	00036	CE  	2004	6	14	AUS20040176      	1	20040307	G	2820	10138901157	CHECK VALVE     			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUEL DIST	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			6425 							(AUS) FUEL SYSTEM CHECK VALVE SUSPECT FAULTY.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004061400037	20040614	00037		2004	6	14	AUS20040177      	4	20040308	G	3461	1714970501	FMC             			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					FLT MANAGEMENT	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) DUEL FLIGHT MANAGEMENT COMPUTER (FMC) FAILURE. INVESTIGATION FOUND THAT BOTH FMCS EXPERIENCED A RESTART DUE TO AN 	UNHANDLED SOFTWARE EXCEPTION (SOFTWARE PROGRAM ERROR).					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061400038	20040614	00038	SO  	2004	6	14	AUS20040178      	1	20040304	G	1420		CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	RT ENGINE EEC	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE ELECTRONIC ENGINE CONTROL (EEC) AND TORQUE SIGNAL CONDITIONER CONNECTOR PLUGS SUSPECT FAULTY/CONTAMINATE	D.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
2004061400039	20040614	00039	NM  	2004	6	14	AUS20040179      	1	20040312	G	2450	P18	PANEL           			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					AC POWER	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) SMOKE AND BURNING ODOR COMING FROM TOP SECTION OF P18 CIRCUIT BREAKER PANEL.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004061400040	20040614	00040	EA  	2004	6	14	AUS20040180      	2	20040315	G	7414	6089188	IMPULSE COUPLING	SLICK       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	AMTR	C8289	C8289       	GL  	MAGNETO	LOOSE           	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AU	S 					6089188					(AUS) LT MAGNETO IMPULSE COUPLING LOOSE ON SHAFT.  FURTHER INVESTIGATION FOUND THE IMPULSE COUPLING LOCATION KEY SHEARED	.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	EXPP5N
2004080600020	20040806	00020	CE  	2004	8	6	AUS20040181      	1	20040310	G	1430		SCREW           			BEECH 	35    	S35         	1151532	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	FUSELAGE FLOOR	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL CABLE RUBBING ON SCREW.  INVESTIGATION FOUND (A LONGER THAN NORMAL) SCREW HOLDING THE FORWARD CAB	IN FLOOR IN POSITION. INCORRECT SCREW HAD BEEN FITTED DURING REUPHOLSTERING CARRIED OUT APPROXIMATELY TWO WEEKS PREVIOUS	LY.  UNAPPROVED PART.  PERSONNEL/MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880
2004061400041	20040614	00041	NM  	2004	6	14	AUS20040182      	1	20040309	G	5210		PIN             			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					PAX DOOR	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) L2 OUTER DOOR HANDLE MOVED TO VERTICAL POSITION AFTER DEPARTURE.  DURING INVESTIGATION, THE WHOLE HANDLE AND SHAFT	 ASSEMBLY CAME AWAY FROM THE DOOR.   A LOOSE CASTELLATED NUT AND SHIMS WERE FOUND IN THE HOUSING ASSEMBLY. FURTHER INVES	TIGATION FOUND A DEFORMED SPLIT PIN IN THE BOTTOM OF THE DOOR STRUCTURE.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061400042	20040614	00042	CE  	2004	6	14	AUS20040183      	1	20040308	G	2910	572700223	PIPE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	HYDRAULIC SYS	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) HYDRAULIC PIPE CRACKED AND LEAKING.  LOSS OF HYDRAULIC FLUID. PIPE IS LOCATED IN RT WING LEADING EDGE.  INVESTIGAT	ION FOUND TOOLING MARKS ON THE PIPE IN THE AREA OF THE PIPE BEND.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004061400043	20040614	00043	NM  	2004	6	14	AUS20040184      	1	20040309	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 LOCATED AT BS 663.75 STRINGER 3R-3L CRACKED AT S1AND S2R FASTENER HOLES. FOUND DURING EDDY CURRENT 	INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061400044	20040614	00044	SW  	2004	6	14	AUS20040185      	1	20040314	G	6220	471401341	CLAMP           			BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR STABILIZER BAR CLAMP CRACKED.						1	G	7	1 	3O	3	O	 	2H3     	E279
2004061400045	20040614	00045	EU  	2004	6	14	AUS20040186      	1	20040311	G	3260	213NW447AB	SWITCH          			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK SWITCH FAULTY.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE
2004061400046	20040614	00046	NE  	2004	6	14	AUS20040187      	2	20040315	G	7200	CFM567B26	ENGINE          			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					NR 1	CONTAMINATED    	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE GEARBOX CHIP DETECTOR CONTAMINATED.  INVESTIGATION SUSPECTS THAT DEBRIS IS M50 BEARING MATERIAL.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061400047	20040614	00047	EA  	2004	6	14	AUS20040188      	2	20040316	G	7322	252429111	FCU             			MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	ENGINE	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) FUEL CONTROL UNIT FINGER FILTER CONTAMINATED.  WORKSHOP INSPECTION FOUND A FINE HAIR LIKE SUBSTANCE.						1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU
2004061400048	20040614	00048	EA  	2004	6	14	AUS20040189      	3	20040312	G	6111	72CK056	BLADE           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			788  							(AUS) PROPELLER BLADES CONTAINED SEVERE INTERGRANNULAR CORROSION.						1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045
2004061400049	20040614	00049	EA  	2004	6	14	AUS20040190      	3	20040315	G	6111	72CK056	BLADE           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1079 							(AUS) PROPELLER BLADES CONTAINED SEVERE INTERGRANNULAR CORROSION.						1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045
2004061400050	20040614	00050		2004	6	14	AUS20040191      	4	20040225	G	3497		WIRE            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ATC TRANSPONDER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRANSPONDER WIRING SUSPECT FAULTY. TRANSPONDER AND GPS WIRING PARALLEL WHICH CAN CAUSE INACCURATE ALTITUDE READING	S.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA
2004061400058	20040614	00058		2004	6	14	AUS20040192      	4	20040311	G	3414	2083111	INDICATOR       			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AIRSPEED	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					2027					(AUS) FIRST OFFICER'S AIRSPEED INDICATOR/MACHMETER FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061400060	20040614	00060	NM  	2004	6	14	AUS20040193      	1	20040123	G	2121	6066223	FAN             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AIR DISTRIBUTION	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			24556		1072073					(AUS) CABIN RECIRCULATING FAN FAULTY.  SMOKE AND FUMES IN COCKPIT ANDCABIN.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061400062	20040614	00062	NM  	2004	6	14	AUS20040194      	1	20040303	G	2121	7322591E	FAN             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AIR DISTRIBUTION	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			9138 							(AUS) FORWARD EQUIPMENT COOLING FAN SEIZED.   FUMES IN COCKPIT.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061400065	20040614	00065	SO  	2004	6	14	AUS20040195      	1	20040316	G	3213	20029	PIN             	MESSIER     		EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	MLG STRUT	STICKING        	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 					244					(AUS) RT MAIN LANDING GEAR DRAG BRACE STRUT PIVOT PIN BINDING.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
2004061400066	20040614	00066	NE  	2004	6	14	AUS20040196      	2	20040211	G	7297	6068T54P01	WIRE HARNESS    			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	RT ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE W4 (YELLOW) WIRING HARNESS FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL
2004061400068	20040614	00068	GL  	2004	6	14	AUS20040197      	3	20040313	G	6110		BLADE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	LIGHTNING STRIKE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT PROPELLER BLADE EXHIBITED LIGHTNING EXIT MARKS. FURTHER INVESTIGATION FOUND BOTH LT AND RT PROPELLERS MAGNETISE	D BEYOND LIMITS.  LT ENGINE POWER SECTION MAGNETISM BEYOND LIMITS.  LIGHTNING EXIT MARKS FOUND ON LT ELEVATOR OB TRAILIN	G EDGE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061400069	20040614	00069	NM  	2004	6	14	AUS20040198      	1	20040121	G	2910		HYDRAULIC SYSTEM			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					A-SYSTEM	CONTAMINATED    	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC SYSTEM A FAULTY.  ENGINEERING INVESTIGATION SUSPECTS AIR IN HYDRAULIC SYSTEM. LT MAIN LANDING GEAR HYDRA	ULIC HOSE HAD BEEN REPLACED ON THE PREVIOUS DAY.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061400071	20040614	00071		2004	6	14	AUS20040199      	4	20040319	G	2213	4051601935	PANEL           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FLT CONTROLLER	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) AUTOPILOT MODE CONTROL PANEL FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061400072	20040614	00072		2004	6	14	AUS20040200      	4	20040123	G	2215	6225734002	SERVO           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	AUTOPILOT MAIN	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			3902 							(AUS) ELEVATOR AUTOPILOT SERVO FAILED. LOSS OF AUTOPILOT CAUSED AIRCRAFT TO PITCH UP. RT ENGINE OVERTORQUED TO 134 PERCE	NT AND LT ENGINE OVERTORQUED TO 125 PERCENT.  OVERTORQUE INSPECTION ON ENGINES AND PROPELLERS FOUND NO DAMAGE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
2004061400074	20040614	00074	NM  	2004	6	14	AUS20040201      	1	20040309	G	2750		CONTROL SYSTEM  			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) FLAPS FAILED TO MOVE FROM 20 TO 30.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061400076	20040614	00076	SO  	2004	6	14	AUS20040202      	1	20040316	G	5711	67069003	SPAR            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR CORRODED. FOUND FOLLOWING REMOVAL OF FUEL TANK FOR STRUCTURAL DEFECT REPAIR. CORROSION WAS SEVERE ENOUGH	 TO HAVE COMPROMISED STRUCTURAL INTEGRITY.					1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920
2004061400078	20040614	00078	EU  	2004	6	14	AUS20040203      	1	20040305	G	3222		RING            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1542 							(AUS) NOSE LANDING GEAR OVEREXTENDED.  INVESTIGATION FOUND THE OLEO GUIDE RING WORN AND DAMAGED ALLOWING THE RETAINING P	INS TO MIGRATE OUT DISCONNECTING THE GUIDE TUBE FROM THE NOSE FORK.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004061400079	20040614	00079	SO  	2004	6	14	AUS20040204      	1	20040225	G	3230	8623853	TUBE            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	MLG	WORN            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR EXTENSION HYDRAULIC PIPE WORN THROUGH BY CONTACT WITH THE NLG BRAKE FLUID COVER ASSEMBLY.   LOSS	 OF HYDRAULIC FLUID.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920
2004061400080	20040614	00080	NM  	2004	6	14	AUS20040205      	1	20040311	G	5311	65B0175424	FRAME           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME PN 65B01754-24 AND FRAME DOUBLER PN 65B26275-34 CRACKED. INVESTIGATION FOUND CRACKING WAS DUE TO TH	E USE OF A SPLICE PLATE OF THE INCORRECT MATERIAL AS STATED IN BSB 747-53-2483.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004061400081	20040614	00081	GL  	2004	6	14	AUS20040206      	1	20040318	G	3220	AN442	BOLT            			AMTR  	JABIRU	JABIRUSK    	05602CU	GL  	AMTR  	CHEVY8	CHEVYV8     	 	GL  	AMTR	C8289	C8289       	GL  	NLG	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR TRAILING LINK PIVOT BOLT FAILED AT LT PIVOT POINT.						1	H	7	1 	3I	3	V	NC	EXPA1H71	EXPE3V	5	N	EXPP5N
2004061400082	20040614	00082	CE  	2004	6	14	AUS20040207      	1	20040317	G	5514	04320049	BRACKET         			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER STEEL BRACKET CRACKED. CRACK LENGTH 10MM(0.393IN).						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL
2004061400083	20040614	00083	SW  	2004	6	14	AUS20040208      	1	20040318	G	3260		SWITCH          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	STICKING        	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR MICROSWITCH STICKING.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061400084	20040614	00084	NE  	2004	6	14	AUS20040209      	3	20040309	G	6114	660714259	HUB             			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7004 							(AUS) LT PROPELLER HUB CRACKED IN ATTACHMENT BOLT HOLE. FOUND DURING NDT INSPECTION IAW AD/PR/33.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE
2004061400086	20040614	00086	NM  	2004	6	14	AUS20040210      	1	20040318	G	2912	271T00424	FILTER          			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYS	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 HYDRAULIC SYSTEM FILTER MODULE PRESSURE FILTER BOWL SHEARED OFF. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU
2004061400087	20040614	00087	NM  	2004	6	14	AUS20040211      	1	20040319	G	1430	AN3167R	NUT             			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TE FLAPS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT IB FLAP CARRIAGE DEAD WEIGHT ROLLER NUT AND LOCK WASHER MISSING. BOLT WAS STARTING TO MIGRATE FROM POSITION. SU	SPECT CAUSED BY FAILURE OF LOCK WASHER TAB.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004061400088	20040614	00088		2004	6	14	AUS20040212      	4	20040214	G	6122	661001002	GOVERNOR        			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	PROPELLER	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			26765							(AUS) RT PROPELLER OVERSPEED GOVERNOR FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL
2004061400089	20040614	00089	CE  	2004	6	14	AUS20040213      	1	20040312	G	2824	10138901157	VALVE           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUEL TRANSFER	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) DEFECT REPORT NR WAS CREATED IN LIEU OF DATA BEING ATTACHED TO MDR 04/0176.  CANCELLED, DATED 25TH MARCH 2004.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004061400090	20040614	00090	EU  	2004	6	14	AUS20040214      	1	20040320	G	6123	3012534	CLAMP           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT ENGINE PROPELLER REVERSING LEVER CABLE CLAMP BOLT FAILED ALLOWING PROPELLER REVERSING PY LEVER TO DISCONNECT FR	OM PUSH/PULL CABLE.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004061400092	20040614	00092	CE  	2004	6	14	AUS20040215      	1	20040322	G	5740	50110242	FITTING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING AFT LOWER ATTACHMENT FITTING PN 5011024-2, LT WING AFT UPPER ATTACHMENT FITTING PN 5011023-1, RT WING AFT 	LOWER FITTING PN 5011024-2 AND RT WING AFT UPPER FITTING PN 5011023-1 ALL CONTAINED INTERGRANNULAR CORROSION.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA
2004061400093	20040614	00093	EA  	2004	6	14	AUS20040216      	2	20040323	G	7421	URHB32E	SPARK PLUG      			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) SPARK PLUG CRACKED IN AREA BETWEEN HEXAGONAL BODY AND FLANGE AT UPPER THREADED AREA.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004061400094	20040614	00094	EA  	2004	6	14	AUS20040217      	2	20040319	G	8520	LW10292	GEAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			492  							(AUS) CRANKSHAFT IDLER GEAR FRACTURED.  DAMAGE CAUSED TO SHAFT SUPPORT HOLE IN CRANKCASE.  METAL CONTAMINATION OF OIL SY	STEM.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004061400095	20040614	00095	CE  	2004	6	14	AUS20040218      	1	20040322	G	8011	85073009	GEAR            	LAMAR       		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	ENGINE STARTER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					85073009					(AUS) STARTER MOTOR BENDIX DRIVE GEAR DISINTEGRATED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004061400096	20040614	00096	NM  	2004	6	14	AUS20040219      	1	20040229	G	4920	P6452	APU             			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					APU BAY	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FILTER INDICATOR ACTIVATED. INSPECTION FOUND METAL CONTAMINATION OF MAGNETIC PLUG.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061400097	20040614	00097	WP  	2004	6	14	AUS20040220      	2	20040324	G	7261	31035781	PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE OIL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE REAR BEARING OIL SUPPLY PIPE CHAFING ON NTS OIL PIPE.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
2004061400098	20040614	00098	GL  	2004	6	14	AUS20040221      	3	20040324	G	6111	891286	LATCH           	MCAULY      		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	PROPELLER BLADE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					891286					(AUS) PROPELLER EXPERIENCED UNCOMMANDED FEATHER FOLLOWING GROUND RUN. SUSPECT CAUSED BY FAILURE OF THE LOW PITCH STOP LA	TCH PINS.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL
2004061400099	20040614	00099	CE  	2004	6	14	AUS20040222      	1	20040323	G	3230	1018100211	SHAFT           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR RETRACTION DRIVE TUBE FAILED DUE TO INTERFERENCE WITH PNEUMATIC DUCTING CLAMP.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061400100	20040614	00100	EA  	2004	6	14	AUS20040223      	3	20040319	G	6111	72CK056	BLADE           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			732  							(AUS) PROPELLER BLADES CONTAINED SEVERE INTERGRANNULAR CORROSION.						1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045
2004061400102	20040614	00102	SW  	2004	6	14	AUS20040224      	1	20040322	G	2740	3064307	SWITCH          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	STAB CONTROL	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) PITCH TRIM SWITCH INSTALLED INCORRECTLY.  SWITCH HAD BEEN REFITTED FOLLOWING REPAIRS TO THE PILOTS CONTROL YOKE.  	PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061400103	20040614	00103	SW  	2004	6	14	AUS20040225      	1	20040326	G	2897		WIRE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FUEL BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN FUEL BOOST PUMP WIRING CHAFED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061400105	20040614	00105	CE  	2004	6	14	AUS20040227      	2	20040322	G	7314		BEARING         	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	ENGINE FUEL PUMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1446 		B01AA428					(AUS) ENGINE DRIVEN FUEL PUMP FAULTY. PUMP CONTAMINATED WITH A BLACK CARBON POWDER TYPE SUBSTANCE. POOR PUMP LUBRICATION	 CAUSED EXCESSIVE BEARING WEAR.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA
2004061400106	20040614	00106	CE  	2004	6	14	AUS20040228      	1	20040321	G	3297		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK SWITCH WIRE BROKEN.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004061400107	20040614	00107	NE  	2004	6	14	AUS20040229      	2	20040318	G	7220	311467901	CASE            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT ENGINE AIR INLET CASES CORRODED IN AREA WHERE THE INLET CASE MATES WITH THE COMPRESSOR SHROUD.  AIR INLE	T CASE IS MANUFACTURED FROM MAGNESIUM ALLOY.					2	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P56GL
2004061400108	20040614	00108	NM  	2004	6	14	AUS20040230      	1	20040324	G	2823	737M28500011	VALVE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL SELECTOR	STICKING        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			20216		3377					(AUS) NR 1 ENGINE FUEL SHUTOFF VALVE STICKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061400111	20040614	00111	NE  	2004	6	14	AUS20040231      	2	20040327	G	7200		ENGINE          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 4	FIRE            	W				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 4 ENGINE FAILED TO START.  TAILPIPE FIRE OCCURRED DUE TO A LARGE AMOUNT OF RESIDUAL FUEL IN THE ENGINE.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004061400112	20040614	00112	NM  	2004	6	14	AUS20040232      	1	20040318	G	2810	2670137101	CHECK VALVE     			BOEING	737   	737800*     	       	NM  										FUEL STORAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING REFUELING MANIFOLD CHECK VALVE DAMAGED. CHECK VALVE HAD DAMAGE ON THE VALVE BODY, SPRING AND FLAPPERS.  WEAR 	ALSO FOUND ON THE FLAPPER ATTACHMENT LUGS AND THE LUGS ON THE VALVE BODY WHICH HOLDS THE FLAPPER PIN. THE FLAPPER SEPARA	TED FROM THE VALVE AND WAS FOUND IN THE CENTER FUEL TANK.  FOD.				2	L	7	2 	4F			RT	A16WE
2004061400113	20040614	00113	GL  	2004	6	14	AUS20040233      	2	20040321	G	7250		TURBINE         			BOEING	747   	747         	UTILSYS	NM  	AMTR  	CHEVY8	CHEVYV8     	 	GL  					NR 2 ENGINE	FAILED          	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE VIBRATION LEVELS HIGH.  VISUAL INSPECTION OF THE TAIL PIPE FOUND CATASTROPHIC TURBINE FAILURE.  RT COR	E COWL HOLED.  LPT CASE CONTAINED HOLES AND CRACKING.  AIRCRAFT IS FOREIGN REGISTERED.					2	L	7	4 	4F	3	V	RT	A20WE   	EXPE3V
2004061400114	20040614	00114	SW  	2004	6	14	AUS20040234      	1	20040328	G	2720	2770066001	GUST LOCK       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER GUSTLOCK CRACKED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004061400115	20040614	00115	EU  	2004	6	14	AUS20040235      	1	20040324	G	2820		SEAL            			CASA  	C212  	C212        	2410200	EU  	GARRTT	TPE331	TPE3311     	01514	WP  	ROTOL	R334	R334482F13  	GL  	FUEL DIST	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) REFUEL/DEFUEL VALVES NOT CLOSING CORRECTLY ALLOWING AIR TO BE DRAWN INTO ENGINE FUEL SYSTEM. INVESTIGATION FOUND T	HE SEALINGWASHERS INSIDE THE VALVE ASSEMBLIES TO BE DEFECTIVE.					2	H	7	2 	4T	3	T	 	A43EU   	E3WE	6	C	P61GL
2004061400121	20040614	00121	GL  	2004	6	14	AUS20040236      	2	20040317	G	7323	22397	SHAFT           	BENDIX      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE GOVERNOR	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			493  		22397					(AUS) POWER TURBINE GOVERNOR DRIVESHAFT FAILED.   INVESTIGATION FOUND THE DRIVESHAFT COUPLING SPINNING FREELY ON THE DRI	VESHAFT.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004061400126	20040614	00126	EU  	2004	6	14	AUS20040237      	1	20040331	G	2750	HC579L1309000	PIN             			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FAIL SAFE PIN ASSEMBLY OF THE RT FLAP TAB NR 2 HINGE BOLT CRACKED.  FOUND DURING NDT INSPECTION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061400129	20040614	00129	CE  	2004	6	14	AUS20040238      	2	20040322	G	7314	6543511	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	ENGINE FUEL	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1780 							(AUS) INSPECTION OF ENGINE DRIVEN FUEL PUMP FOLLOWING STRIP FOR OVERHAUL.  THE PUMP WAS FOUND TO CONTAMINATED WITH WHAT 	APPEARS TO BE CARBON POWDER.  PUMP SHAFT BUSHING CONTAMINATED, CAUSING PUMP ROTATION TO BE RESTRICTED.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA
2004061500024	20040615	00024	CE  	2004	6	15	AUS20040239      	1	20040302	G	5311		FRAME           			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) FUSELAGE FRAMES CRACKED. CRACKS FOUND IN THE FOLLOWING AREAS:-1. INTERCOSTAL CRACKED AT STRINGER NR 72. FUSELAGE F	RAME CRACKED AT STATION 326.75, STRINGER NO8 AND NO9 3. FUSELAGE FRAME CRACKED AT STATION 337.75, AT STRINGER NR 9,  NR 	10 AND NR 114. LT STRINGER NR 9 CRACKED AT REAR PRESSURE BULKHEAD 5. ATIGUE CRACKS TO SKIN AND STRINGERS AT FUSELAGE STA	TION 326.75  TO 337.75 AND STRINGER NR 9, REAR PRESSURE BULKHEAD 6. MULTIPLE CRACKS IN FUSELAGE SKIN LT SIDE LOWER FRAME	 STATION  337.5.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004061500025	20040615	00025	NM  	2004	6	15	AUS20040240      	1	20040107	G	2497		WIRE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AC GENERATOR	CHAFED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			2145 							(AUS) RT INTEGRATED DRIVE GENERATOR (IDG) FAILED DUE TO A WIRE CHAFING ON THE STATOR HOUSING. SUSPECT INSUFFICIENT INSUL	ATION SLEEVING ON THE WIRE. DURING RECTIFICATION OF THE PROBLEM THE FIREWALL FEED THROUGH CONNECTOR BACKSHELL WAS FOUND 	TO BE LOOSE.				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061500026	20040615	00026	EU  	2004	6	15	AUS20040241      	1	20040331	G	5730	HC571H0236	SKIN            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TOP SKIN SUSPECT CORRODED. REMOVAL OF PAINT FINISH AND FURTHER INSPECTION FOUND THE SKIN TO BE SERVICEABLE WI	TH NO CORROSION OR CRACKING EVIDENT. INSPECTION CARRIED OUT IAW AD/BAE146/61 AMDT2.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004061500027	20040615	00027	EU  	2004	6	15	AUS20040242      	1	20040330	G	2910	1379305A155	HOSE            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR RADIUS ROD UP HYDRAULIC HOSE FAILED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
2004061500028	20040615	00028	CE  	2004	6	15	AUS20040243      	1	20040327	G	3297		WIRE            			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DOWNLOCK SWITCH	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK SWITCH WIRE BROKEN IN AREA APPROXIMATELY 763MM (3IN) FROM SWITCH.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA
2004061500029	20040615	00029	WP  	2004	6	15	AUS20040244      	2	20040319	G	7210	310703411	TORQUE RING     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	RT ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE TORQUE RING BRIDGES FAILED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
2004061500030	20040615	00030	CE  	2004	6	15	AUS20040246      	1	20040329	G	3213	358152607	STRUT           			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			12   							(AUS) MAIN LANDING GEAR STRUT SLIDING MEMBER CRACKED CIRCUMFERENTIALLYAROUND THE LOWER SECTION.						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P22EA
2004061500031	20040615	00031	SW  	2004	6	15	AUS20040247      	1	20040331	G	1430	NAS130427D	BOLT            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	MLG	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK ROLLER BOLT BROKEN.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
2004080600109	20040806	00109	NM  	2004	8	6	AUS20040248      	1	20040331	G	2530	8202017	INSERT          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					GALLEY	WRONG PART      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) INCORRECT OVEN INSERT (TRAYS) USED IN NO4 OVEN. INSERT DID NOTHAVE A HEAT/PROTECTIVE SHIELD FITTED AT THE REAR ALL	OWING THE MEAL PACKAGING TO CONTACT HEATING ELEMENTS. UNAPPROVED PART.PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004062100174	20040621	00174	NM  	2004	6	21	AUS20040249      	1	20040401	G	3150		WARNING SYSTEM  			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) CENTRAL WARNING SYSTEM SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004060900135	20040609	00135	EU  	2004	6	9	AUS20040251      	1	20040329	G	3244	12480131	BALANCE WEIGHT  	GOODYEAR    		PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TIRE	SEPARATED       	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 					12480131					(AUS) RT MAIN LANDING GEAR TIRE BALANCE WEIGHT SEPARATED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004060900136	20040609	00136	CE  	2004	6	9	AUS20040252      	1	20040331	G	2720	1015242653	PUSHROD         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	RUDDER CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER PUSHROD CONTAMINATED WITH WATER CAUSING CORROSION OF THE INTERNAL BORE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004060900137	20040609	00137	EU  	2004	6	9	AUS20040253      	1	20040316	G	5311		FRAME           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 29 RHS CRACKED FROM RIVET IN AREA LOCATED ABOVE STRINGER NR 13.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004060900138	20040609	00138	SO  	2004	6	9	AUS20040254      	2	20040401	G	7322	25765407	SERVO           	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL CONTROL	CONTAMINATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					70470306					(AUS) RT ENGINE FCU REGULATOR AIR SECTION CONTAMINATED WITH OIL.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA
2004060900139	20040609	00139	CE  	2004	6	9	AUS20040255      	2	20040322	G	7322	25765407	SERVO           	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL CONTROL	LEAKING         	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 					70470304					(AUS) ENGINE FCU SERVO STEM SEAL LEAKING FUEL. FURTHER INVESTIGATION FOUND THAT THERE WERE MANY SMALL PARTS OF BLUE RUBB	ER THROUGH OUT THE UNIT. THESE RUBBER PARTS HAD COME FROM A POSSIBLE DAMAGED O RING SEAL DURING ASSEMBLY. ON TOTAL STRIP	 OF THE UNIT NONE OF THE O RINGS SHOWED SIGNS OF DAMAGE INDICATING THAT THE DAMAGED ORING MAY HAVE BEEN CHANGED BUT THE 	RUBBER NOT REMOVED.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA
2004060900140	20040609	00140	EU  	2004	6	9	AUS20040256      	1	20040325	G	2510	959300111	SEAT            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS SEAT BACKREST ASSEMBLY CRACKED IN TWO PLACES.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004060900141	20040609	00141	CE  	2004	6	9	AUS20040257      	1	20040407	G	1420	MS20470AD3	RIVET           			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN RIVET HEADS CORRODED AND MISSING.  RIVETS ARE LOCATED IN THE AREA UNDER THE BELLY OF THE AIRCRAFT AN	D ATTACH THE MAIN LANDING GEAR CASTINGS PNO 0741627-1 AND PNO 0741627-2 TO THE FUSELAGE BELLY SKIN.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA
2004060900142	20040609	00142	NM  	2004	6	9	AUS20040258      	1	20040407	G	3610	8021709	VALVE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PNEUMATIC SYS	FAULTY          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 			5669 		940627					(AUS) LT ENGINE PRESSURE REGULATING VALVE (PRV) FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004060900143	20040609	00143	EU  	2004	6	9	AUS20040259      	1	20040404	G	4920	38004545	APU             			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					APU BAY	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 			3723 							(AUS) APU FAILED TO START DURING TAXI.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE
2004060900144	20040609	00144	NM  	2004	6	9	AUS20040260      	1	20040405	G	5210		STOP            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					PAX DOOR	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) FOLLOWING LOUD CRACKING NOISES IN FLIGHT AN INSPECTION OF THE DOOR AND DOOR CUTOUT AREA WAS CARRIED OUT. I NVESTIG	ATION FOUND THE DOOR STOPS HEAVILY WORN AND DRY.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004060900145	20040609	00145	CE  	2004	6	9	AUS20040261      	1	20040408	G	3230	AS119E10C000	HOSE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION SYSTEM HYDRAULIC HOSE RUPTURED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004061000001	20040610	00001	CE  	2004	6	10	AUS20040262      	1	20040408	G	8011	D112530	GEAR            	LYC         		CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ENGINE STARTER	DISINTEGRATED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					D112530					(AUS) STARTER BENDIX DRIVE GEAR DISINTEGRATED ON START.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA
2004061000002	20040610	00002	NE  	2004	6	10	AUS20040263      	1	20040414	G	2612	7630607902103	FIRE DETECTOR   			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 2 ENGINE	FAULTY          	W				O				OTHER                   				E	B	N	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE FLAME DETECTOR FAULTY.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
2004061000003	20040610	00003	EA  	2004	6	10	AUS20040264      	2	20040406	G	7322	70274603	SERVO           	LYC         		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	FUEL CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					70274603					(AUS) FUEL CONTROL UNIT AIR CHAMBER CONTAMINATED WITH FUEL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004061000004	20040610	00004	CE  	2004	6	10	AUS20040265      	1	20040411	G	2434	10300B	ALTERNATOR      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	DC SYSTEM	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			260  							(AUS) ALTERNATOR FAILED IN FLIGHT.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004061000005	20040610	00005	SW  	2004	6	10	AUS20040266      	1	20040410	G	2150	434422123	SWITCH          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C663  	NE  	CABIN COOLING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEADING EDGE DUCT THERMAL SWITCH FAULTY.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061000006	20040610	00006	EA  	2004	6	10	AUS20040267      	2	20040326	G	7313	252405411	INJECTOR        			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	FUEL SYSTEM	CONTAMINATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1184 							(AUS) RT ENGINE FUEL INJECTORS CONTAMINATED BY SMALL FERROUS (RUST) PARTICLES.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920
2004061000007	20040610	00007	NE  	2004	6	10	AUS20040268      	2	20040411	G	7200		ENGINE          			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	RIGHT	OVERTORQUED     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE OVERTORQUED TO 155 PERCENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061000008	20040610	00008	NM  	2004	6	10	AUS20040269      	1	20040407	G	2421	761574B	IDG             			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					AC GENERATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE INTEGRATED DRIVE GENERATOR (IDG) PRESSURE RELIEF REGULATING VALVE RETAINING COVER SCREW SHEARED.  COVE	R, POPPET VALVE AND SPRING SEPARATED FROM IDG RESULTING IN LOSS OF OIL INTO FAN COWL.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061000009	20040610	00009	EU  	2004	6	10	AUS20040270      	1	20040408	G	2434	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DC GENERATOR	SHEARED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 GENERATOR DRIVESHAFT SHEARED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004061000010	20040610	00010		2004	6	10	AUS20040271      	4	20040414	G	2215	065005656	SERVO           			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AUTOPILOT SYS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT ROLL SERVO FAULTY.  INVESTIGATION FOUND THAT THE SCREWS HOLDING THE CLUTCH HAD LOOSENED ALLOWING THE CLU	TCH TO REMAIN ENGAGED WHEN THE AUTOPILOT WAS DISENGAGED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004061000011	20040610	00011	WP  	2004	6	10	AUS20040272      	2	20040416	G	7210		GEAR            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RT ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 										(AUS) RT ENGINE SUFFERED AN UNCONTAINED GEARBOX FAILURE. DEBRIS FROM THE FAILED GEAR IMPACTED ON THE RT SIDE OF THE AIRC	RAFT CABIN.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
2004061000012	20040610	00012		2004	6	10	AUS20040273      	4	20040416	G	2310	14809	ANTENNA         			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	HF COMMUNICATION	FAILED          	W				O				OTHER                   				D	C		INFLIGHT SEPARATION       	F.O.D.                    		NR	NOT REPORTED   	1			AU	S 										(AUS) HF ANTENNA BROKEN AT VERTICAL STABILIZER. SAFETY RESTRAINING DEVICE FAILED TO RETAIN THE BROKEN CABLE AS THE CABLE	 HAD FAILED ON BOTH SIDES OF THE RESTRAINT CLAMP. THE BROKEN ANTENNA CAUSED NO DAMAGE TO THE AIRFRAME HOWEVER THE SAFETY	 RESTRAINT, COMPRISING A BOLTED TEFLON FITTING SECURED BY NYLON TAPE, HAD REPEATEDLY IMPACTED THE VERTICAL STABILIZER SI	DE PANEL RESULTING IN DELAMINATION, ABRASION AND CRACKING OF THE OUTER SKIN AND DAMAGE TO THE ALUMINUM HONEYCOMB CORE.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE
2004061000013	20040610	00013	EU  	2004	6	10	AUS20040274      	1	20040408	G	2823	7913003K	SHUTOFF VALVE   			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL SELECTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE FUEL SHUTOFF VALVE FAILED TO OPERATE WHEN THE FIRE HANDLE WAS PULLED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004061000014	20040610	00014	NM  	2004	6	10	AUS20040275      	1	20040415	G	2810		FUEL TANK       			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING FUEL TANK LEAKING INTO DRY BAY AT WBL 616.75 LOWER AFT CORNER.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061000015	20040610	00015	EA  	2004	6	10	AUS20040276      	2	20040416	G	7313	252405411	INJECTOR        			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	RT ENGINE	FAULTY          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			37   							(AUS) RT ENGINE FUEL INJECTOR FLOW ERRATIC.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920
2004061000016	20040610	00016	WP  	2004	6	10	AUS20040277      	1	20040420	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/XMSN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS STRETCHED AND WORN.						1	G	7	1 	3O	3	O	 	H10WE   	E274
2004061000017	20040610	00017	EA  	2004	6	10	AUS20040278      	2	20040420	G	7414	E02HA23B	DISTRIBUTOR BLK 	CONT        		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	HO360*      	41514	EA  					MAGNETO	LOOSE           	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					E02HA23B					(AUS) LT MAGNETO DISTRIBUTOR BLOCK LOOSE IN HOUSING.						1	G	7	1 	3O	3	O	 	H10WE   	E286
2004061000018	20040610	00018	EU  	2004	6	10	AUS20040279      	1	20040405	G	7110		SKIN            			BAC   	146   	AVRO146RJ70A	1500095	EU  	LYC   	LF507 	LF5071F     	 	NE  					ENGINE COWLING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE REAR COWLING SKIN CHAFING IN AREA LOCATED JUST BENEATH THE REAR ATTACHMENT/HINGE POINT. CHAFING EVIDENT ON 	ALL EIGHT REAR COWLING DOORS.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061000020	20040610	00020		2004	6	10	AUS20040280      	4	20040419	G	2350	M1035AAABJLB2	PANEL           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	AUDIO	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			41   							(AUS) COPILOTS AUDIO PANEL FAULTY.  SMOKE AND ODOR IN COCKPIT. SMOKE AND ODOR DISSIPATED WHEN CIRCUIT BREAKER POPPED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004061000021	20040610	00021	EU  	2004	6	10	AUS20040281      	1	20040317	G	5343	HC537L0002006	DIAPHRAGM       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG ACT MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR MOUNTING BOSS DIAPHRAGM CRACKED. FOUND DURING INSPECTION IAW AD/BAE146/71.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004061000025	20040610	00025	NM  	2004	6	10	AUS20040282      	1	20040416	G	3242	26123121	BRAKE           			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					RT MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT OB BRAKE WORN BEYOND LIMITS.  BRAKE SEIZED ON WHEEL.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061000026	20040610	00026	NM  	2004	6	10	AUS20040283      	1	20040402	G	2750		FLAP            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TRAILING EDGE	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 										(AUS) AIRCRAFT HAD AN ASSYMETRIC FLAP INDICATION DURING SELECTION.  THE AIRCRAFT HAS HAD A TOTAL OF FOUR SIMILAR OCCURRE	NCES DURING A TWO WEEK PERIOD.   INVESTIGATION IS CONTINUING.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061000027	20040610	00027	NE  	2004	6	10	AUS20040284      	2	20040319	G	7220	311467901	CASE            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60      	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RT ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE AIR INLET CASE CORRODED.						2	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P56GL
2004061000031	20040610	00031	NM  	2004	6	10	AUS20040285      	1	20040417	G	2611	473054	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CARGO BAY	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) BAGGAGE COMPARTMENT SMOKE DETECTOR UNIT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061000032	20040610	00032	NM  	2004	6	10	AUS20040286      	1	20040408	G	2820		GASCOLATOR      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					FUEL SYS	CONTAMINATED    	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 										(AUS) ENGINE FAILED.  INVESTIGATION FOUND WATER AND RUST IN THE AIRCRAFT FUEL FILTER GASCOLATOR AND CARBURETOR.						1	G	7	1 	3O	3	O	 	H10WE   	E274
2004061000034	20040610	00034	EU  	2004	6	10	AUS20040287      	1	20040420	G	7120	001322603	MOUNT           			SAAB  	SF340 	SF340A      	7850100	EU  										ENGINE	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD LOWER ENGINE MOUNT CANISTER ASSEMBLIES (7OFF) RECEIVED AS REPLACEMENT PARTS WERE PRE MODIFICATION ITEMS.  	CANISTERS DID NOT COMPLY WITH AD/SF340/68.					2	L	7	2 	4T			RT	A52EU
2004061000035	20040610	00035	SW  	2004	6	10	AUS20040289      	1	20040416	G	6710	B542DD	BEARING         			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	LACK OF LUBE    	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) COLLECTIVE JACKSHAFT SUPPORT BEARING FAULTY. INVESTIGATION FOUND THAT THE BEARING LUBRICANT HAD DRIED OUT.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004061000036	20040610	00036	NM  	2004	6	10	AUS20040290      	1	20040416	G	5753	65C344836	SPINDLE         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT OB MID FLAP CARRIAGE SPINDLE SUSPECT CRACKED. FOUND DURING ULTRASONIC INSPECTION IAW EI 737-57-72R2.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004061000037	20040610	00037	EU  	2004	6	10	AUS20040291      	1	20040422	G	5730		SKIN            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING STRUCTURE CONTAINED LEVEL 3 CORROSION IN THE FOLLOWING AREAS: CORROSION FOUND ON FORWARD FACE OF FORWARD MAIN	 SPAR AT RIB STATION 129752. ACCESS PANEL Z536FB MOUNTING FLANGE HAD EVIDENCE  OF SURFACE AND DEEPER CORROSION AT RIB 11	974-12795. FORWARD FACE OF LT SPAR HAS CORROSION AT STATION 11460. CORROSION FOUND ON FORWARD FACE OF MAIN SPAR AT WING 	STATION  106505 LT OB AILERON TAB HINGE ARM EXFOLIATION CONTAINED.			2	L	7	2 	4F	4	F	RT	        	E25NE
2004061000038	20040610	00038		2004	6	10	AUS20040292      	4	20040217	G	2213	0119244TF	CONTROLLER      			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AUTOPILOT	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) AUTOPILOT BURNED OUT.  ROLL SERVO ALSO BURNED OUT.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920
2004061000039	20040610	00039	NM  	2004	6	10	AUS20040293      	1	20040416	G	2731	6355B000103	MOTOR           			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ELEVATOR TAB	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) STABILIZER ELECTRIC TRIM MOTOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004061000040	20040610	00040	SW  	2004	6	10	AUS20040294      	1	20040415	G	2435	95066	BEARING         	LUCAS       		SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	STARTER GEN	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 			586  		95066					(AUS) RT ENGINE STARTER-GENERATOR BEARING FAILED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061000041	20040610	00041	EU  	2004	6	10	AUS20040295      	1	20040423	G	2701	GA827302343	BUSHING         			GIPPLD	GA8   	GA8         	3900102	EU  										CONTROL COLUMN	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL WHEEL SHAFT BUSHING GALLED AGAINST WELD PENETRATION ON INNER FACE OF CONTROL COLUMN SLEEVE.						1	H	7	1 	3O			NT
2004061000042	20040610	00042	NM  	2004	6	10	AUS20040296      	1	20040418	G	1430	BACB30US16K47	BOLT            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT VERTICAL FIN FORWARD ATTACHMENT BOLTS FAILED TORQUE TEST.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061000043	20040610	00043	NM  	2004	6	10	AUS20040297      	1	20040420	G	5220	H2052K3833	LATCH           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					EMERGENCY EXITS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PH0225					(AUS) LT OFFWING SLIDE DOOR NR 3 LATCH GUIDE PIN, BUSH AND SPRING MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061000044	20040610	00044	NE  	2004	6	10	AUS20040298      	1	20040318	G	2720		ROD END         			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RUDDER CONTROL	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 			40   							(AUS) RUDDER CONTROL ROD BALL JOINT SEIZED AND ROD END FAILED. THE SEIZED BALL JOINT ALLOWED THE CONTROL ROD END TO BEND	 UP AND DOWN DURING RUDDER APPLICATIONS UNTIL FINAL FAILURE.					1	H	7	1 	3O	3	O	 	1A13    	1E10	5	C	P920
2004061000045	20040610	00045	EU  	2004	6	10	AUS20040300      	1	20040428	G	2730	D19202001	BRACKET         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ELEVATOR CONTROL	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR CONTROL ROD LOCK BRACKET INCORRECTLY INSTALLED AND FOULING ON LT ELEVATOR ROD CAUSING RESTRICTION IN E	LEVATOR MOVEMENT. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	        	E25NE
2004061000046	20040610	00046	EU  	2004	6	10	AUS20040301      	1	20040428	G	5310		DOOR FRAME      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SERVICE DOOR FRAME CONTAINED LEVEL 3 CORROSION LOCATED AT THE BOTTOM FORWARD CORNER.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004061000047	20040610	00047	EU  	2004	6	10	AUS20040302      	1	20040424	G	3242	1090300	PAD             	CLEVELAND   		PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE	SEPARATED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			2050 		1200					(AUS) BRAKE ASSEMBLY WEAR PAD SEPARATED FROM BRAKE DISC ROTOR AND DAMAGED FOUR MORE PADS CAUSING THE BRAKE UNIT TO LOCK 	UP.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004061000048	20040610	00048	SO  	2004	6	10	AUS20040303      	1	20040415	G	3520	11900301	PBE             			EMB   	120   	EMB120      	3260201	SO  										PAX OXYGEN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER BREATHING EQUIPMENT (PBE) UNITS FAULTY.  PBE STORAGE BAGS HAD LOST VACUUM AND ITEMS WERE CHAFED IN CONTA	INMENT BOX.					2	L	7	2 	4T			RT	A31SO
2004061000049	20040610	00049	SW  	2004	6	10	AUS20040304      	1	20040310	G	3411		STATIC PORT     			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PITOT/STATIC SYS	BLOCKED         	W				O				OTHER                   				W			INADEQUATE Q C            			CL	CLIMB          	1			AU	S 										(AUS) PITOT/STATIC INSTRUMENTS FAILED TO OPERATE FOLLOWING TAKEOFF. INVESTIGATION FOUND CLEAR PLASTIC TAPE OVER AFT STAT	IC VENT PORTS. TAPE HAD BEEN LEFT ON FOLLOWING PITOT/STATIC CHECK.  PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004061000050	20040610	00050	NE  	2004	6	10	AUS20040305      	2	20040429	G	7261		OIL SYSTEM      			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE	FAILED          	W				O				OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) ENGINE SHUTDOWN DUE TO LOW OIL PRESSURE WARNING AND ZERO OIL QUANTITY. INVESTIGATION CONFIRMED ENGINE OIL TANK CON	TENTS EMPTY BUT COULD NOT FIND ANY SOURCE OF LEAKAGE. ENGINE WAS REMOVED DUE TO FAILING WINDMILL CRITERIA.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061000051	20040610	00051	CE  	2004	6	10	AUS20040306      	1	20040428	G	5511	053200199	RIB             			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER RIB CRACKED AROUND CIRCUMFERENCE OF AFT ATTACHMENT HOLES.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004061000052	20040610	00052	WP  	2004	6	10	AUS20040307      	1	20040422	G	1430	STD1419	BOLT            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	MISSING         	W				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) CRANKCASE BOLT MISSING. OIL LEAKING FROM CRANKCASE. ENGINE HAD JUST BEEN FITTED AND AIRCRAFT WAS ON TEST FLIGHT.  	PERSONNEL/MAINTENANCE ERROR.					1	G	7	1 	3O	3	O	 	H11NM   	E295
2004061000053	20040610	00053	NE  	2004	6	10	AUS20040308      	2	20040414	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	NR 2	SURGES          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE POWER SURGE. DURING GROUND RUN TORQUE BLED OFF.  INVESTIGATION FAILED TO FIND ANY CAUSE AND THE ENGINE	 WAS REMOVED.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004061000055	20040610	00055	EU  	2004	6	10	AUS20040309      	1	20040420	G	2910	SA7670006131	HOSE            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					DRAG CONTROL ACT	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) ROLL SPOILER ACTUATOR PRESSURE HOSE RUPTURED. LOSS OF YELLOW HYDRAULIC SYSTEM FLUID.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004061000056	20040610	00056	CE  	2004	6	10	AUS20040310      	1	20040414	G	3610	12945085021	MANIFOLD        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PNEUMATIC DIST	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE HP SERVO PRESSURE SUPPLY TUBE TO MANIFOLD WELDED JOINT CRACKED.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004061000057	20040610	00057		2004	6	10	AUS20040311      	4	20040429	G	2210	FCS80	AUTOPILOT SYS   			SWRNGN	SA227 	SA227AT     	8780610	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	COCKPIT	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) AUTOPILOT FAULTY.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P61GL
2004061000058	20040610	00058	NM  	2004	6	10	AUS20040312      	1	20040427	G	1430		BOLT            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					PAX SEAT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SEAT SUPPORT BEAM TO AISLE SIDE LEG STRUCTURE BOLTS SEPARATED AND FOUND UNDER SEAT 12 DEF.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004061000059	20040610	00059	NM  	2004	6	10	AUS20040313      	1	20040426	G	7830		BRAKE ASSY      	GE          		BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					THRUST REVERSER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE THRUST REVERSER LT AND RT ELECTROMECHANICAL BRAKES FAILED SYSTEM TORQUE CHECK.  FOUND DURING INSPECTION 	IAW AD/B767/182 AND AD/B767/83.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004061000060	20040610	00060	NM  	2004	6	10	AUS20040314      	1	20040415	G	1420	MS3470L1412P	CONNECTOR       	LUCAS       		DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	AC GENERATOR	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			5966 		Y10007					(AUS) NR 2 AC GENERATOR FAILED.  REPLACED IAW MANUFACTURERS MM. INVESTIGATION FOUND PHASE IMBALANCE PROTECTION CIRCUITRY	 WIRE CHAFED INSIDE GENERATOR UNIT. CONNECTOR CONTAMINATED WITH OIL.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004061000073	20040610	00073	EU  	2004	6	10	AUS20040315      	2	20040429	G	7210	332BF6	NUT             			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					NR 1 ENG FLANGE	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE OUTPUT DRIVESHAFT TO OUTPUT FLANGE ATTACHMENT NUTS FAULTY.  MATING SURFACE OF NUTS MISALIGNED. NUTS AR	E PART OF BOLT SET PN 332BF6.  SUSPECT MANUFACTURING ERROR.					2	G	7	2 	4U	4	U	 	H4EU    	E12NE
2004061000074	20040610	00074	EU  	2004	6	10	AUS20040316      	1	20040430	G	2822	229945	PUMP            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL BOOST	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT AFT BOOST PUMP INLET CHECK VALVE FLAP SEPARATED AT PIVOT POINT.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600010	20040806	00010	EU  	2004	8	6	AUS20040317      	1	20040427	G	3241		SHAFT           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ANTISKID SYS	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 										(AUS) NR 1 MAIN WHEEL TIRE DAMAGED AND DEFLATED. INVESTIGATION FOUND THAT THE TIRE DEFLATED DUE TO WHEEL LOCKUP ON LANDI	NG ROLL. THE WHEEL LOCKUP WAS CAUSED BY A BENT ANTI-SKID TRANSDUCER DRIVESHAFT WHICH CAUSED THE ANTI-SKID SYSTEM ON THIS	 WHEEL POSITION TO BE NON-OPERATIVE. THE BENT TRANSDUCER SHAFT ALSO CAUSED DAMAGE TO SEVERAL OTHER COMPONENTS NAMELY THE	 BRAKE COOLING FAN MOTOR, FAN DUCT, AND DEBRIS SCREEN COVER. THE BENT ANTI-SKID DRIVE SHAFT APPEARS TO BE CAUSED BY INCO	RRECT FIT OF SHAFT INTO DEBRIS SCREEN SPLINED DRIVE BEARING AT LAST WHEEL INSTALLATION. PERSONNEL/MAINTENANCE ERROR.		2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004080600011	20040806	00011	EU  	2004	8	6	AUS20040318      	1	20040429	G	1430	A203612	BOLT            	HARTZL      		WSK   	M18   	M18DROMADER 	9810102	EU  	GARRTT	TPE331	TPE33111U   	01514	WP  	HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					EVA2790					(AUS) PROPELLER COUNTERWEIGHT TO BLADE CLAMP ATTACHMENT BOLTS (2OFF10) CRACKED.						1	L	7	1 	3O	4	T	 	A47EU   	E4WE	6	C	P44GL
2004080600012	20040806	00012	EA  	2004	8	6	AUS20040319      	2	20040430	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	IO540*      	41532	EA  					ENGINE FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT MOUNTED ENGINE FUEL PUMP LEAKING.						1	G	7	1 	3O	3	O	 	H11NM   	1E4
2004080600013	20040806	00013		2004	8	6	AUS20040320      	4	20040427	G	6122	923309D	SHAFT           	WOODWARD    		BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROP GOVERNOR	SHEARED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					923309D					(AUS) RT ENGINE PROPELLER GOVERNOR DRIVESHAFT SHEARED IN AREA LEVEL WITH THE MOUNTING FACE.						1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920
2004080600014	20040806	00014	EU  	2004	8	6	AUS20040321      	1	20040501	G	5711	AV50903	SUPPORT ANGLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR STRAP SUPPORT FORWARD AND AFT ANGLES CRACKED ALONG RIVET LINE.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920
2004080600015	20040806	00015	EU  	2004	8	6	AUS20040322      	1	20040319	G	2910	4204001	PTU             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYDRAULIC SYSTEM	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 			7184 							(AUS) HYDRAULIC POWER TRANSFER UNIT (PTU) SEIZED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004080600016	20040806	00016	NM  	2004	8	6	AUS20040323      	1	20040409	G	4950		DUCT            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					APU BLEED AIR	LEAKING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) BURNING ODOR IN CABIN.  SUSPECT CAUSED BY APU BLEED AIR DUCT LEAK.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004080600017	20040806	00017	CE  	2004	8	6	AUS20040324      	1	20040427	G	2897	99104207	WIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL INDICATING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			21310							(AUS) RT FUEL TANK QUANTITY WIRE CHAFED ON STRINGERS LOCATED AT STATION PWS 61.80.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004080600044	20040806	00044	CE  	2004	8	6	AUS20040325      	1	20040421	G	3230	57411541	SPACER          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	MLG	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) MAIN LANDING GEAR UPLOCK HOOK ROLLER SPACER WORN.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
2004080600045	20040806	00045	CE  	2004	8	6	AUS20040326      	1	20040405	G	5551	21320082	WEB             			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7977 							(AUS) TAILPLANE ATTACHMENT WEB CRACKED.						1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL
2004080600046	20040806	00046	WP  	2004	8	6	AUS20040327      	2	20040424	G	7261	31032174	PUMP            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE OIL	CRACKED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE OIL PUMP HOUSING CRACKED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004080600047	20040806	00047	NM  	2004	8	6	AUS20040328      	1	20040501	G	2120		ODOR            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 										(AUS) STRONG BURNING ODOR ON FLIGHT DECK AND IN CABIN.  EXTENSIVE INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM OR A	NY EVIDENCE OF BURNING.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080600048	20040806	00048	NM  	2004	8	6	AUS20040329      	1	20040408	G	3244	161U000115	TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					MLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) TIRE DEFLATED DURING FLIGHT.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004080600059	20040806	00059		2004	8	6	AUS20040330      	4	20040502	G	2210	R1053M182	FORCE LIMITER   			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					AUTOPILOT SYSTEM	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT WOULD NOT ENGAGE.  SUSPECT FAULTY FORCE LIMITER.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004080600060	20040806	00060	NM  	2004	8	6	AUS20040331      	1	20040426	G	2761		LINE            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					SPOILER ACTUATOR	LOOSE           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) OB SLAT ACTUATOR HYDRAULIC LINE LOOSE AND LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080600061	20040806	00061	NM  	2004	8	6	AUS20040332      	1	20040420	G	2752	413T1001	MOTOR           			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3843 							(AUS) OB TRAILING EDGE FLAP ELECTRIC MOTOR SEIZED.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA
2004080600062	20040806	00062	WP  	2004	8	6	AUS20040333      	2	20040421	G	7320	69254313	VALVE           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL CONTROL	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) START FUEL VALVE LEAKING BETWEEN VALVE BODY AND SOLENOID.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004080600063	20040806	00063	NE  	2004	8	6	AUS20040334      	1	20040504	G	5280	7620902019043	FITTING         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					MLG DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			7087 							(AUS) LT MAIN LANDING GEAR DOOR HINGE FITTING FAILED.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
2004080600064	20040806	00064	NM  	2004	8	6	AUS20040335      	1	20040501	G	2421		IDG             			BOEING	737   	73776N      	13844CH	NM  	GE    	CFM56 	CFM567B24   	 	NE  					AC GENERATOR	FAULTY          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 INTEGRATED DRIVE GENERATOR (IDG) SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080600065	20040806	00065	NM  	2004	8	6	AUS20040336      	1	20040425	G	2910	BACC27AC10061006	FITTING         			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					HYDRAULIC SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FOUR WAY HYDRAULIC FITTING CRACKED AND LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080600066	20040806	00066	NM  	2004	8	6	AUS20040337      	1	20040403	G	2751	900040813	TRANSDUCER      			BOEING	747   	74748E      	2FOR   	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT IB TRAILING EDGE FLAP ROTARY VOLTAGE DIFFERENTIAL TRANSDUCER (RVDT) FAULTY.						2	L	7	2 	4F	4	F	RT	A20WE   	E23EA
2004080600074	20040806	00074	EU  	2004	8	6	AUS20040339      	1	20040505	G	5310		PLATE           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INSP OF REAR CABIN WET AREA AT FLOOR LEVEL FOUND CORROSION IN FOLLOWING PLATES:  SHEAR PLATE PN HC538H1183-000 LOC	ATED ON TOP OF LONGITUDINAL BEAM FRAME 43 RBL 34.  CORROSION WAS LOCATED ON UPPER SURFACE MEASURING 17.018MM (0.67IN) LE	NGTH, 16.002MM (0.63IN) WIDTH AND 0.508MM (0.020IN) DEPTH.   TOP PLATE PN HC 538J0584-203 LOCATED ON TOP OF LONGITUDINAL	 RAIL FROM FRAME 41 TO 43 RBL 21.  CORROSION LOCATED ON LOWER SURFACE MEASURING 24MM (0.944IN) LENGTH, 18MM (0.708IN) WI	DTH AND 0.838MM (0.033IN) DEPTH.   TOP PLATE PN HC538J1361-000 OF LATERAL FLOOR SUPPORT BEAM AT FRAME 40 BETWEEN LBL 20 	+ RBL 20.   CORROSION LOCATED ON  THE UPPER SURFACE MEASURING 250MM (9.8IN) LENGTH, 45MM 040339 5.	2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004080600075	20040806	00075	NM  	2004	8	6	AUS20040340      	1	20040426	G	2410	B1773	SEAL            			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CSD	LEAKING         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			14217							(AUS) NR 2 CONSTANT SPEED DRIVE (CSD) GENERATOR DRIVE SEAL WORN AND LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004080600076	20040806	00076	NM  	2004	8	6	AUS20040341      	1	20040407	G	2751		INDICATOR       			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAP	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 										(AUS) TRAILING EDGE FLAP DISAGREE INDICATION.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004080600077	20040806	00077	NM  	2004	8	6	AUS20040342      	1	20040418	G	2131	1305026	SELECTOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					CABIN PRESSURE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 			18643							(AUS) CABIN PRESSURE SELECTOR FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004080600078	20040806	00078	EU  	2004	8	6	AUS20040343      	1	20040429	G	6420	1053040212	FITTING         			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR GEARBOX MOUNT CRACKED FROM BOLT HOLE.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10
2004080600079	20040806	00079	EA  	2004	8	6	AUS20040344      	2	20040501	G	7414		BEARING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAGNETO	SEIZED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 			919  							(AUS) MAGNETO REAR BEARING SEIZED. CONTACT BREAKERS MELTED.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920
2004080600080	20040806	00080	EU  	2004	8	6	AUS20040345      	1	20040506	G	1430	HC536B0475000	BOLT            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD OUTER ATTACHMENT SPECIAL BOLT SHAFT CORRODED AND PLATING MISSING. CORROSION WAS LOCATED APPROXIMATELY 12.7	MM (0.5IN) DOWN FROM THE BOLT HEAD.  AREA OF CORROSION 25.4MM (1IN) IN LENGTH BY 9.39MM (0.370IN) IN WIDTH BY0.127MM (0.	005IN) DEPTH.BOLTS ARE  LOCATED IN ZONE 161, FRAME 29 STN 539-4.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004080600081	20040806	00081	EU  	2004	8	6	AUS20040346      	1	20040506	G	5710		SKIN            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TRAILING EDGE CONTAINED CORROSION ON BOTH SIDES.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600082	20040806	00082	EU  	2004	8	6	AUS20040347      	1	20040506	G	5315		FLOORBEAM       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN FLOOR PANEL SUPPORT BEAMS (2OFF) CORRODED. SUSPECT CAUSED BY INCORRECT REMOVAL OF FLOOR PANEL AND GAP SEALAN	T USING A SHARP EDGED TOOL WHICH SCORED THE BEAMS.  CORROSION INITIATED AT THE SCORE MARKS. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600083	20040806	00083	EU  	2004	8	6	AUS20040348      	1	20040506	G	5313		STRINGER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTER CARGO COMPARTMENT CORRODED ON FORWARD FACE OF DOOR SILL BEAM AND LOWER SHELL STRINGERS.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600084	20040806	00084	NM  	2004	8	6	AUS20040349      	1	20040421	G	2130		CABIN PRESSURE  			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  						MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) CABIN DIFFERENTIAL PRESSURE STUCK AT 8.6 PSI.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004080600085	20040806	00085		2004	8	6	AUS20040350      	4	20040423	G	3418	60150301	STRIP           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	STALL WARNING SY	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STALL STRIP MISSING.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004080600086	20040806	00086	EU  	2004	8	6	AUS20040351      	1	20040506	G	5347		SEAT TRACK      			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT TRACKS CORRODED.  PN HC538J0343-001 RT IB SEAT TRACK FOUND CORRODED ON  UPPER SURFACE. CORROSION MEASURES 106	.68MM (4.2IN) LENGTH,  24.13MM (0.95IN) WIDTH WITH DEPTH OUT OF LIMITS.  LOCATION, ZONE 251, FRAME 40, RBL 21 RT.  REPOR	TED CAUSE OF DEFECT, LAVATORY/GALLEY SPILL.  PN HC539J0395 LT OB SEAT TRACK FOUND CORRODED ON THE UPPER SURFACE. CORROSI	ON MEASURES 38.1MM (1.5IN) LENGTH,  21.7MM (0.856IN) WIDTH AND 1.803MM (0.071) DEPTH. LOCATION -  ZONE 251 STA 867 AND 8	54 LBL 43. REPORTED CAUSE OF DEFECT - DISSIMILAR METALS OF THE SEAT TRACK AND THE STEEL FEET OF THE MEAL TROLLEY REAR ST	OWAGE UNIT IN A DAMP ENVIRONMENT.  PN HC538J0343-000 LT IB SEAT TRACK FOUND CORRODED ON.	2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004080600087	20040806	00087	NM  	2004	8	6	AUS20040352      	1	20040427	G	3350	BPS73	BATTERY         			BOEING	767   	767338      	1385151	NM  	RROYCE	RB211 	RB211524*   	 	NE  					EMERGENCY LIGHT	FAULTY          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY LIGHTING SYSTEM POWER SUPPLY AND BATTERY M1395 FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU
2004080600088	20040806	00088	NM  	2004	8	6	AUS20040353      	1	20040416	G	7797		WIRE            			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) ENGINE AIRBORNE VIBRATION MONITOR INDICATION MODULE SELECTOR SWITCH WIRE FROM PIN 19 OF CONNECTOR DM162 BROKEN.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU
2004080600089	20040806	00089	EU  	2004	8	6	AUS20040354      	1	20040506	G	5730		SKIN            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING TIP TRAILING EDGE CORRODED. CORROSION ALSO FOUND UNDERSTATIC DISCHARGER BASE.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600090	20040806	00090	EU  	2004	8	6	AUS20040355      	1	20040506	G	5714		STRINGER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					CENTER WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTER SECTION EXTERNAL LOWER SURFACE Z SECTION STRINGERS CONTAINED LEVEL 3 CORROSION.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600091	20040806	00091	EU  	2004	8	6	AUS20040356      	1	20040506	G	5752	D18016	BRACKET         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AILERON TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON TAB BEARING BRACKET CONTAINED LEVEL 3 CORROSION.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600092	20040806	00092	EU  	2004	8	6	AUS20040357      	1	20040505	G	5311	HC536H1050200	FRAME           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN CROWN FRAME TO SKIN STRUCTURE ANGLE CLEATS (8OFF) CRACKED FROM BEND RADIUS EDGE. THE ANGLE CLEATS ARE LOCATE	D IN FOLLOWING AREAS: FRAME 19A BETWEEN STRINGERS 1 AND 2 LT.   FRAME 19A BETWEEN STRINGERS 2 AND 3 LT 3. FRAME 19B BETW	EEN STRINGERS 1 AND 2 LT.   FRAME 19B BETWEEN STRINGERS 2 AND 3 LT.   FRAME 19C BETWEEN STRINGERS 1 AND 2 LT.   FRAME 19	C BETWEEN STRINGERS 2 AND 3 LT.   FRAME 19D BETWEEN STRINGERS 1 AND 2 LT.   FRAME 19D BETWEEN STRINGERS 2 AND 3 LT THE C	RACKS RANGED IN LENGTH BETWEEN 2.5MM (0.1IN) AND 22.8MM(0.9IN).		2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004080600093	20040806	00093	CE  	2004	8	6	AUS20040358      	1	20040505	G	5511	053200199	ANGLE           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HORIZONTAL STABILIZER AFT RIB ATTACHMENT ANGLE CRACKED. A GAP BETWEEN THE AFT RIB ATTACHMENT ANGLE AND SPAR CAU	SES CRACKING OF THE ANGLE WHEN THE ATTACHMENT BOLTS ARE TENSIONED. ON REMOVAL OF THE FORWARD STABILIZER ATTACHMENT BOLTS	 FRETTING WAS EVIDENT AND  THE BOLTS WERE SHANK BOUND.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004080600094	20040806	00094	NM  	2004	8	6	AUS20040359      	1	20040427	G	5754		SKIN            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT SLAT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LE SLAT T/E WEDGE DELAMINATED ON IB END UPPER FACE.  AREA OF DELAMINATION APPROXIMATELY 70 SQ IN.  FOUND DURING	 INSPECTION IAW AD/767/73.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004080600095	20040806	00095	SO  	2004	8	6	AUS20040360      	2	20040505	G	8550	IO520MB	OIL SYSTEM      			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	CONTAMINATED    	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 			6    				565592			(AUS) METAL CONTAMINATION OF RT ENGINE OIL SYSTEM.  THREE PIECES OF 0.812 MM (0.032IN) LOCKWIRE FOUND IN OIL FILTER.  TW	O MORE PIECES OF LOCKWIRE FOUND IN OIL PRESSURE RELIEF VALVE.  ENGINE HAD 6 HOURS OPERATION SINCE OVERHAUL. PERSONNEL/MA	INTENANCE ERROR.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA
2004080600096	20040806	00096	SO  	2004	8	6	AUS20040361      	2	20040501	G	7310	S112940150	HOSE            			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUEL DISTRIBUTIO	LOOSE           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			60   							(AUS) ENGINE FUEL HOSE LEAKING AT CONNECTION TO CHECK VALVE.  FUEL LEAKING INTO ENGINE BAY.  HOSE HAD NOT BEEN TIGHTENED	 DURING MAINTENANCE. PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL
2004080600097	20040806	00097	SW  	2004	8	6	AUS20040362      	1	20040406	G	6320	206040662101	GEAR            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					BKW11161					(AUS) MAIN TRANSMISSION SUN GEAR PN 206-040-662-101 AND SUN GEAR SHAFT PN 206-040-040-005 WORN BEYOND LIMITS IN SPLINED 	AREAS.  INVESTIGATION FOUND THE SUN GEAR UPPER O RING PN M83248/1-228 WAS TORN AND SLICED IN SEVERAL AREAS AND THE SUN G	EAR LOWER O-RING PN M83248/1-232 WAS ILL FITTING AND COULD BE REMOVED WITH LITTLE EFFORT.  SUSPECT WEAR WAS CAUSED BY CO	NTAMINATION OF THE SUN GEAR SPLINE LUBRICATION GREASE BEING CONTAMINATED WITH TRANSMISSION LUBRICATING OIL DUE TO DAMAGE	D AND ILL FITTING O-RINGS.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004080600098	20040806	00098	EA  	2004	8	6	AUS20040363      	2	20040424	G	7414	2202	BEARING         	BENDIX      	BL6006163   	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	FAILED          	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			AU	S 			420  		E03DA06012					(AUS) LT MAGNETO BEARING FAILED.						1	G	7	1 	3O	3	O	 	H11NM   	E295
2004080600099	20040806	00099	NM  	2004	8	6	AUS20040364      	1	20040429	G	7921		BOLT            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL/OIL COOLER	LOOSE           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) LT TANK FUEL QUANTITY APPROXIMATELY 800 KILOGRAMS LOWER THAN RT TANK. INVESTIGATION FOUND THE FUEL/OIL COOLER FORW	ARD BASKET BOLTS LOOSE BUT ASCERTAINED THIS WAS NOT THE CAUSE OF THE APPARENT FUEL LOSS.  INVESTIGATION CONTINUING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004080600100	20040806	00100	NM  	2004	8	6	AUS20040365      	1	20040506	G	2530	GENM2585015	OVEN            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					GALLEY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 					90022634					(AUS) AFT GALLEY OVEN ELECTRICAL FAULT.  INVESTIGATION FOUND FILTERBOARD CAUGHT FIRE DUE TO THE FORMATION OF DRY SOLDER 	JOINTS ON INDUCTOR CONTACTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004080600101	20040806	00101	NM  	2004	8	6	AUS20040366      	1	20040505	G	2510		PANEL           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					COCKPIT	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT IB DECORATIVE PANEL FORWARD EDGE OVERLAPPING CAUSING CAPTAINS RUDDER PEDALS TO BIND DURING FULL TRAVEL CON	TROL CHECK.  REPOSITIONING PANEL PREVENTED FURTHER BINDING PROBLEMS.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004080600102	20040806	00102		2004	8	6	AUS20040367      	4	20040503	G	2565	737M25651017	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					L2 DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR 2L ESCAPE SLIDE LIGHTS FAILED TO ILLUMINATE FOLLOWING SLIDED EMPLOYMENT.   SUSPECT FLAT BATTERY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004080600103	20040806	00103	CE  	2004	8	6	AUS20040368      	1	20040429	G	3010	27S70510904	BOOT            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	DEICE SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RT WING OUTER DE-ICE BOOT BURST AT THE UPPER SEAM AND SPLIT FOR THE ENTIRE LENGTH FROM THE OB RT NACELLE TO THE WI	NGTIP.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004080600104	20040806	00104	EA  	2004	8	6	AUS20040369      	2	20040503	G	8520	L421861A	ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LEFT	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L421861A			(AUS) LT ENGINE METAL CONTAMINATION.  METAL PARTICLES IN FILTER WERE NON-FERROUS FLAKES WITH THE LARGEST FLAKES APPROXIM	ATELY 6MM BY 4MM (0.236IN BY 0.157IN). SUSPECT BEARING MATERIAL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004080600105	20040806	00105	EU  	2004	8	6	AUS20040370      	1	20040510	G	2810		TANK            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL STORAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING FUEL SYSTEM COLLECTOR TANK CONTAINED LEVEL 3 CORROSION ON LOWER INTERNAL SURFACE.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600106	20040806	00106	EU  	2004	8	6	AUS20040371      	1	20040510	G	2810		TANK            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL STORAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING FUEL SYSTEM COLLECTOR TANK CONTAINED LEVEL 3 CORROSION ON LOWER INTERNAL SURFACE.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004080600107	20040806	00107	EU  	2004	8	6	AUS20040372      	1	20040507	G	5320	HC538H0125007	ANGLE           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT REAR ENTRY SILL PLATE ATTACHMENT ANGLE CONTAINED LEVEL 2 CORROSION ON THE UPPER SURFACE.   AREA OF CORROSION 48	.26MM (1.9IN) LONG BY 20.8MM (0.82IN) WIDE AND 0.584MM (0.023IN) DEEP.  LOCATION OF CORROSION, ZONE 252 STRINGER 19, BET	WEEN FRAMES 41AND 43, BL44 RT.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004080600108	20040806	00108	CE  	2004	8	6	AUS20040373      	1	20040507	G	5511	1016200143	SPAR CAP        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HORIZONTAL STABILISER UPPER REAR SPAR CAP CONTAINED SEVERE INTERGRANNULAR CORROSION.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004080600110	20040806	00110	EU  	2004	8	6	AUS20040374      	1	20040507	G	2797	A157BA2579920	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         			TO	TAKEOFF        	1			AU	S 										(AUS) FLAP CONTROL SYSTEM WIRE BROKEN. FAULT TRACE TO BROKEN WIRE A157B-A25799200 TO FLAP UP CONTROL SWITCH.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004080600111	20040806	00111	CE  	2004	8	6	AUS20040375      	1	20040505	G	3232	6632303003001	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG DOOR	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR IB DOOR ACTUATOR DAMAGED.  ACTUATOR HOUSING END CAP SEPARATED FROM HOUSING DUE TO SHEARING OF	 THE FOUR END CAP BOLT HEADS. LOSS OF HYDRAULIC FLUID.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004080600112	20040806	00112	NM  	2004	8	6	AUS20040376      	1	20040428	G	2750		BEARING         			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TE FLAPS	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) IB FLAP SELECTOR VALVE INPUT ROD SELF ALIGNING BEARING BINDING DUE TO LACK OF LUBRICATION.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004080600113	20040806	00113	CE  	2004	8	6	AUS20040377      	1	20040424	G	5340	26111441	SUPPORT         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP ACTUATOR SUPPORT ASSEMBLY CRACKED.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004092300111	20040923	00111	EU  	2004	9	23	AUS20040378      	1	20040503	G	1420	51224133	CONNECTOR       			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	FIRE DETECTOR	CORRODED        	W				O				OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE FIRE WIRE CONNECTOR CORRODED.  CONNECTOR IS LOCATED AT THE REAR FIREWALL POSITION.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE
2004092300112	20040923	00112	EU  	2004	9	23	AUS20040379      	1	20040505	G	5347		SEAT TRACK      			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN FLOOR STRUCTURE CONTAINED LEVEL 2 CORROSION IN THE FOLLOWING AREAS:  PN HC536H1063-001 RT OB SEAT TRACK END 	ON UPPER  SURFACE. AREA OF CORROSION MEASURED 38.1MM (1.5IN) IN LENGTH  BY 12.7MM (0.5IN) IN WIDTH WITH A DEPTH OF 2.54M	M (0.10IN).  CORROSION LOCATED IN ZONE 222 AT FRAME 18 BETWEEN STATIONS  216.6 AND 240 RT BL43 RT. REPORTED CAUSE OF DAM	AGE  LAVATORY/GALLEY SPILL.   PN HC536H1063-002 LT OB SEAT TRACK ON UPPER SURFACE  AT FORWARD END. AREA OF CORROSION MEA	SURED 25.4MM (1IN) IN  LENGTH BY 6.35MM (0.250IN) IN WIDTH WITH A DEPTH OF 1.066MM (0.042IN).  CORROSION LOCATED IN ZONE	 221 ON FRAME 18 AT BL 42 LT.  REPORTED CAUSE OF DAMAGE LAVATORY/GALLEY SPILL.	2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004092300113	20040923	00113	EU  	2004	9	23	AUS20040380      	1	20040510	G	5280	D26323007	ROLLER          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG DOOR	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN DOOR LOCKING ROLLER INTERNAL DIAMETER WAS TOO SMALL TO FIT OVER THE STEEL STUD IN THE DOOR FRAME.  ROLLER WAS	 A NEW ITEM AND WAS BEING FITTED TO THE DOOR.  SUSPECT FAULTY MANUFACTURE.					2	L	7	2 	4F	4	F	RT	        	E25NE
2004080500080	20040805	00080	EU  	2004	8	5	AUS20040381      	1	20040507	G	5313	STRINGER68	STRINGER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRINGER 68 CRACKED.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004072800201	20040728	00201	NM  	2004	7	28	AUS20040382      	1	20040503	G	3244	165T0100530	TIRE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT MLG	DEFLATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1581 		QF15102					(AUS) LT MAIN LANDING GEAR NR 5 TIRE DEFLATED.  NO DAMAGE TO TIRE EVIDENT.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004072800202	20040728	00202	EA  	2004	7	28	AUS20040383      	2	20040503	G	8530	LW19339	SCREW           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			591  							(AUS) EXHAUST VALVE ROCKER ADJUSTMENT SCREW CRACKED ALLOWING LOCKNUT TO LOOSEN AND ADJUST VALVE CLEARANCE.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2004072800203	20040728	00203	NM  	2004	7	28	AUS20040384      	1	20040426	G	2751	2061141	INDICATOR       			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					TE FLAPS	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 			25055							(AUS) FLAP POSITION INDICATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004072800204	20040728	00204		2004	7	28	AUS20040385      	4	20040414	G	2211	065006401	COMPUTER        			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AUTOPILOT	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) AUTOPILOT COMPUTER FAULTY.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004072800205	20040728	00205	SW  	2004	7	28	AUS20040386      	1	20040504	G	6320	2060400209	GEAR            	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					M/R GEARBOX	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 			554  		BMB45250					(AUS) MAIN ROTOR TRANSMISSION INPUT PINION GEAR FAILED.  GEAR TEETH STARTING TO BREAK DOWN WITH DISTINCT WEAR PATTERN AN	D PITTING ON THE FLANK OF ALL GEAR TEETH AND ADVANCED BREAKING DOWN OF SOME OF THE TEETH.  METAL CONTAMINATION OF TRANSM	ISSION.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004072800206	20040728	00206	NM  	2004	7	28	AUS20040387      	1	20040429	G	2701		CONTROL COLUMN  			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRST OFFICER'S CONTROL COLUMN ELL FITTING CHAFING ON TRANSFER MECHANISM FORK. TRANSFER MECHANISM WAS FOUND TO HAV	E A PRESERVICE BULLETIN FORK FITTED INSTEAD OF A POST SERVICE BULLETIN FORK.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004072900001	20040729	00001	NM  	2004	7	29	AUS20040388      	1	20040509	G	2420		GENERATOR       			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					APU	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			AU	S 										(AUS) APU GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004072900020	20040729	00020	NM  	2004	7	29	AUS20040389      	1	20040511	G	2797	TB262XA3	TERMINAL        			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					RUDDER CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STANDBY RUDDER SHUTOFF VALVE WILL NOT CLOSE ON SELECTION. INVESTIGATION FOUND WIRES W2212-0521-20 AND W5170-0505-2	0 TOTB262-XA3 NOT LOCKED INTO POSITION CAUSING OPEN CIRCUIT.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004072900021	20040729	00021	NM  	2004	7	29	AUS20040390      	1	20040506	G	1430		BOLT            			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					MLG	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LANDING GEAR TO LANDING GEAR DOOR TIE ROD BOLTS INCORRECTLY FITTED.  BOLTS WERE FITTED UPSIDE DOWN.  PERSO	NNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU
2004072900022	20040729	00022	NM  	2004	7	29	AUS20040391      	1	20040510	G	5410	311T106535	DOOR            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE NACELLE/STRUT OB ACCESS DOOR MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004072900023	20040729	00023	CE  	2004	7	29	AUS20040392      	1	20040113	G	5312	0513006103	BULKHEAD        			CESSNA	182   	182B        	2072706	CE  	CONT  	O470  	O470*       	17026	SO  	HARTZL	HC82X	HC82XF1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD CRACKED IN AREA DESCRIBED IN AD/CESSNA180/75AMDT2. CRACK LENGTH APPROXIMATELY 38.1MM (1.5IN). AD	 IS NOT APPLICABLE TO THIS MODEL AIRCRAFT.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P878
2004072900024	20040729	00024	EA  	2004	7	29	AUS20040393      	2	20040511	G	7414	10682014	GEAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MAGNETO	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					GOIJA088R					(AUS) MAGNETO DISTRIBUTOR GEAR FINGER INCORRECTLY FITTED.  FINGER WAS LOCATED APPROXIMATELY 180 DEGREES FROM LOCATING LU	GS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004072900025	20040729	00025	NM  	2004	7	29	AUS20040394      	1	20040506	G	5511		SPAR            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER REAR SPAR SUSPECT CRACKED.  EDDY CURRENT INSPECTION CONFIRMED THE FOLLOWING CRACKS.  STABILI	ZER REAR SPAR RT FORWARD FACE OF TOP WEB ASSEMBLY. CRACK INDICATION CONFIRMED.  CRACK LENGTH 10.16MM (0.400IN)OUT OF FAS	TENER HOLE.   HORIZONTAL STABILIZER CENTER SECTION REAR SPAR RT HOLE.  EDDY CURRENT INSPECTION CARRIED OUT.   WEB CRACKE	D 6 OCLOCK POSITION.			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004072900026	20040729	00026		2004	7	29	AUS20040395      	4	20040511	G	2564	710FAUL2901104	LIFE RAFT       																	CABIN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIFERAFT HOLED IN TOP, ROOF AND FLOOR CHAMBERS. INVESTIGATION FOUND THE HOLES HAD OCCURRED DURING INITIAL PACKING 	ATMANUFACTURE.
2004072900027	20040729	00027	WP  	2004	7	29	AUS20040396      	1	20040511	G	7810	D3171	SHIELD          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	IO540*      	41532	EA  					EXHAUST	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EXHAUST SHIELD MISSING.  ATTACHMENT TABS REMAINED ON EXHAUST ASSEMBLY.						1	G	7	1 	3O	3	O		H11NM   	1E4
2004072900028	20040729	00028	NM  	2004	7	29	AUS20040397      	1	20040510	G	2150	213A10031	SEPARATOR       			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					CABIN COOLING SY	CONTAMINATED    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) AIR CONDITIONING SYSTEM DUCTING, WATER SEPARATORS AND COALESCER BAGS CONTAMINATED WITH OIL. SUSPECT CAUSED BY OVER	FILLING OF APU OIL SYSTEM.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004072900029	20040729	00029	WP  	2004	7	29	AUS20040398      	2	20040506	G	8550	H40671B2	SCAVENGE PUMP   			DHAV  	DHC1  	DCH1CHIPMUNK	2801704	GL  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			48   							(AUS) ENGINE OIL SCAVENGE PUMP CRACKED.						1	L	7	1 	3O	3	I	 	EXPA1L71	A8EU	5	N	EXPP5N
2004072900030	20040729	00030	SW  	2004	7	29	AUS20040399      	1	20040503	G	7712	31080811	PIPE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C663  	NE  	TORQUE SENSOR	CRACKED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE NEGATIVE TORQUE SENSOR (NTS) OIL PIPE CRACKED IN FLARE.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004072900031	20040729	00031	NE  	2004	7	29	AUS20040400      	2	20040512	G	7250	312313102	TURBINE BLADES  			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							PCE94722			(AUS) COMPRESSOR TURBINE BLADES (3 OFF) CRACKED.  CRACKS EMANATE FROM BLADE TIP RADIALLY TOWARDS BLADE ROOT. CRACK LENGT	HS UP TO APPROXIMATELY 7MM (0.27IN). FOUND DURING BOROSCOPE INSPECTION.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P60GL
2004072900032	20040729	00032	EU  	2004	7	29	AUS20040401      	1	20040517	G	2761	P308450102ISS2	ACTUATOR        			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					DRAG CONTROL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT NR 2 LIFT SPOILER ACTUATOR SPINDLE SEIZED IN LOCKED POSITION WITH THE ACTUATOR EXTENDED.  FOUND DURING INSPECTI	ON IAW AD/BA6-27-60-16D BAE MANDATORY ISB 27-137.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004072900033	20040729	00033	CE  	2004	7	29	AUS20040402      	1	20040514	G	5511	053200199	RIB             			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH HORIZONTAL STABILIZER RIB AFT ATTACHMENT ANGLE CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004072900034	20040729	00034	SW  	2004	7	29	AUS20040403      	1	20040516	G	3230	OAS55015	DRAG BRACE      			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPPER DRAG BRACE UPLOCK LUGS FRACTURED.  CAUSED BY DRAG BRACE OUT OF ADJUSTMENT.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004072900035	20040729	00035	SW  	2004	7	29	AUS20040404      	1	20040516	G	2752	2736053003	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	ROTOL	R321	R321482F8   	GL  	TE FLAPS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			1433 							(AUS) RT TRAILING EDGE FLAP ACTUATOR LEAKING FLUID FROM AROUND THE ACTUATOR RAM. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
2004072900036	20040729	00036	EU  	2004	7	29	AUS20040405      	1	20040517	G	5311	HC538H0136002	FRAME           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUSELAGE FRAME 43 CONTAINED LEVEL 2 CORROSION ON THE FORWARD FACE AT FLOOR LEVEL. DAMAGE WAS LOCATED AT ZONE 20	 FRAME 43 STA 726.9 AND WAS 38.1MM (1.5IN) LONG BY 38.1MM (1.5IN) WIDE AND 4.546MM (0.179IN) DEEP. CAUSE OF DAMAGE WAS A	SSESSED AS ENVIRONMENTAL.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004072900037	20040729	00037	NM  	2004	7	29	AUS20040406      	1	20040423	G	2910	DSC1896	VALVE           			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 			99999							(AUS) NR 2 HYDRAULIC SYSTEM CHECK VALVE FAILED. LOSS OF HYDRAULIC FLUID. INVESTIGATION FOUND THE CHECK VALVE HAD SUFFERE	D METAL FATIGUE FAILURE OF THE VALVE BODY WITH THE BODY CRACKING FULLY AROUND THE CIRCUMFERENCE OF THE VALVE BODY.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900057	20040729	00057	NE  	2004	7	29	AUS20040407      	3	20040512	G	6111	8173881	SEAL            	HAMSTD      		DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER BLADE	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			99999							(AUS) LT PROPELLER NR 4 BLADE SEAL FAILED.  INSPECTION OF THE REMOVED SEAL REVEALED THE SEAL TO BE A SEAL FOR A 14SF TYP	E PROPELLER WITH A 14RF TYPE PROPELLER GLAND SPRING SUPPLIED.  THE 14RF GLAND SPRING IS OF A SMALLER DIAMETER WHEN COMPA	RED TO THE 14SF GLAND SPRING.  UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900058	20040729	00058	NE  	2004	7	29	AUS20040408      	3	20040516	G	6111	8173881	SEAL            	HAMSTD      		DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER BLADE	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			99999							(AUS) LT PROPELLER NR 4 BLADE SEAL FAILED.  INSPECTION OF THE REMOVED SEAL REVEALED THE SEAL TO BE A SEAL FOR A 14SF TYP	E PROPELLER WITH A 14RF TYPE PROPELLER GLAND SPRING SUPPLIED. THE 14RF GLANDSPRING IS OF A SMALLER DIAMETER WHEN COMPARE	D TO THE 14SF GLAND SPRING. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900059	20040729	00059	NM  	2004	7	29	AUS20040409      	1	20040427	G	7997		WIRE            			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	OIL PRESS IND	WORN            	W				D				RETURN TO BLOCK         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 ENGINE LOW OIL PRESSURE WARNING LIGHT SWITCH WIRE CHAFED AND SHORT CIRCUITING TO GROUND.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900060	20040729	00060	EU  	2004	7	29	AUS20040410      	1	20040517	G	5320	HC538J1324000	INTERCOSTAL     			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT CABIN FLOOR INTERCOSTAL CONTAINED LEVEL 2 CORROSION ON THESIDE AND UPPER SURFACES. THE INTERCOSTAL DAMAGE WAS 	LOCATED INZONE 251 BETWEEN FRAMES 41 AND 53 AT BL9 LH. AREA OF CORROSION MEASURED 38.1MM (1.5 IN) IN LENGTH BY 3.175MM (	0.125 IN) IN WIDTH AND 0.558MM (0.022 IN) DEPTH.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004072900061	20040729	00061	SW  	2004	7	29	AUS20040411      	1	20040405	G	6720	476221651	BRACKET         			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					TAIL ROTOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DUAL TAIL ROTOR CONTROL PEDAL SYSTEM INTERFERENCE BRACKET NOT FITTED. AD/BELL47/69 REQUIRES THE BRACKET TO BE FITT	ED TO DUALCONTROL BELL/AGUSTA 47 SERIES AIRCRAFT. THE BRACKET PREVENTS INCORRECT FITMENT OF THE DUAL PEDAL CONTROLS. PER	SONNEL/MAINTENANCE ERROR.				1	G	7	1 	3O	3	O	 	2H3     	1E13
2004072900062	20040729	00062	CE  	2004	7	29	AUS20040412      	1	20040427	G	2910	248000131	PIPE            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	HYD POWER PACK	CORRODED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR UP PIPE FROM GEAR SELECTOR HANDLE VALVE TO HYDRAULIC POWER PACK CORRODED WITH A SMALL PINHOLE LEAK.  	A FINE SPRAY OF HYDRAULIC FLUID CONTAMINATED THE REAR OF THE ADF RACK.					1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA
2004072900063	20040729	00063	WP  	2004	7	29	AUS20040413      	1	20040514	G	1430	NAS130310D	BOLT            			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FUEL CONTROL	SEPARATED       	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) GOVERNOR LINKAGE BOLT SEPARATED.  LOSS OF ENGINE CONTROL RESULTED IN AUTO ROTATION AND HEAVY LANDING WITH SOME MIN	OR DAMAGE TO THE AIRCRAFT.					1	G	7	1 	3O	3	O	 	4H12    	1E10
2004072900064	20040729	00064	EU  	2004	7	29	AUS20040414      	1	20040515	G	3233	750470706	SEAL            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG ACTUATOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR ACTUATOR RESTRICTOR SEAL LEAKING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004072900065	20040729	00065	NM  	2004	7	29	AUS20040415      	1	20040513	G	2752	65503245	DRIVE SHAFT     			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					TE FLAP DRIVE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			45797		40216A					(AUS) NR 4 TRAILING EDGE FLAP TRANSMISSION UNIVERSAL DRIVESHAFT WORN AXIALLY BEYOND LIMITS.  END FLOAT WAS APPROXIMATELY	 0.406MM(0.016IN) AT OUTPUT END.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004072900066	20040729	00066	CE  	2004	7	29	AUS20040416      	1	20040519	G	2761	6627602001005	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					DRAG CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING SPOILER ACTUATOR PRESSURE SWIVEL FAILED.   LOSS OFHYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004072900067	20040729	00067	NM  	2004	7	29	AUS20040417      	1	20040516	G	3242	26123121	BRAKE           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					RT MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			553  							(AUS) RT MAIN LANDING GEAR IB BRAKE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004072900068	20040729	00068	NM  	2004	7	29	AUS20040418      	1	20040515	G	7830		BLOCKER DOOR    	RROYCE      		BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					THRUST REVERSER	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE THRUST REVERSER NR 9 BLOCKER DOOR DAMAGED.  CONTROL LINKAGE, FITTING AND APPROXIMATELY 40 PERCENT OF T	HE BLOCKER DOOR MISSING.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU
2004072900069	20040729	00069	NM  	2004	7	29	AUS20040419      	1	20040404	G	2920	571488	SEAL            			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        		CR	CRUISE         	1			AU	S 										(AUS) NR 2 HYDRAULIC STANDBY POWER UNIT DRIVESHAFT SEAL FAILED.  LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900070	20040729	00070	NM  	2004	7	29	AUS20040420      	1	20040421	G	3397	2067051	CONNECTOR       			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LIGHTS	BURNED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 										(AUS) RH OVERHEAD LIGHTING TERMINAL 7 CONNECTOR BURNED AND DAMAGED.ADJACENT TERMINAL 6 ALSO HEAT DAMAGED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900071	20040729	00071	NM  	2004	7	29	AUS20040422      	1	20040514	G	3244		TIRE            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NLG	DAMAGED         	W				C				ABORTED TAKEOFF         				C			F.O.D.                    			TO	TAKEOFF        	1			AU	S 										(AUS) RT NOSE LANDING GEAR TIRE DAMAGED BY DEBRIS ON RUNWAY.  TIRE SHREDDED AND CAUSED DAMAGE TO FORWARD LOWER FUSELAGE 	SKIN.   FOD WAS IDENTIFIED AS THRUST REVERSER BLOCKER DOOR PARTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004072900072	20040729	00072		2004	7	29	AUS20040423      	4	20040517	G	2210		AUTOPILOT SYS   			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					COCKPIT	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) DUAL AUTOPILOT MALFUNCTION.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004072900073	20040729	00073		2004	7	29	AUS20040424      	4	20040525	G	3418	0861F1	SENSOR          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					STALL WARNING SY	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT ANGLE OF ATTACK (AOA) SENSOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004072900074	20040729	00074	SO  	2004	7	29	AUS20040425      	1	20040523	G	3233	762554	ROD END         			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG ACTUATOR	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR ACTUATOR ROD END FAILED.   AIRCRAFT LANDED WITH LT MAIN LANDING GEAR FULLY RETRACTED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004072900093	20040729	00093	NM  	2004	7	29	AUS20040426      	1	20040518	G	5610		WINDSHIELD      			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) FIRST OFFICER'S NR 1 WINDOW OUTER PANE SHATTERED ALONG WITH ARCING FROM THE WINDSCREEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004072900094	20040729	00094	NM  	2004	7	29	AUS20040427      	1	20040520	G	3260		PANEL           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MLG INDICATOR	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR POSITION PANEL FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004072900095	20040729	00095	NM  	2004	7	29	AUS20040428      	1	20040512	G	2121		FAN             			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					AIR DISTRIBUTION	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) SMOKE AND FUMES IN COCKPIT.  SMOKE AND FUMES STOPPED WHEN UPPER FANS SWITCH OFF.  CIRCUIT BREAKER TRIPPED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004072900096	20040729	00096	EU  	2004	7	29	AUS20040429      	1	20040517	G	3230	HC321B0018000	LINK            			BAG   	BAE146	BAE146300A  	1500267	EU  										MLG	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR ASSISTOR JACK TRIANGULAR LINK FAILED AT JACK ATTACHMENT POINT.						2	H	7	4 	4F			RT	A49EU
2004072900097	20040729	00097	NM  	2004	7	29	AUS20040430      	1	20040521	G	2421	AS323710	BOLT            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					AC GENERATOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AAAH003210					(AUS) INTEGRATED DRIVE GENERATOR (IDG) OIL/AIR COOLER BOLTS (5 OFF) MISSING AND REMAINING BOLTS (3 OFF) LOOSE. TWO BOLTS	 AND WASHERS WERE FOUND IN THE COWL.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004072900098	20040729	00098	NE  	2004	7	29	AUS20040431      	2	20040520	G	7261	3400140070	PIPE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					TURBINE ENGINE	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE NR 4 AND NR 5 BEARING OIL SUPPLY LINE B NUT LOOSE (FINGERTIGHT). LOSS OF ENGINE OIL. PERSONNEL/MAINTENANCE 	ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004072900099	20040729	00099	NM  	2004	7	29	AUS20040432      	1	20040430	G	7830	3401659010	NIPPLE          			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					THRUST REVERSER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT THRUST REVERSER OIL SCAVENGE LINE NIPPLE CRACKED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080400214	20040804	00214	NE  	2004	8	4	AUS20040433      	2	20040520	G	7261	3022376	SEAL            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	ENGINE	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE ACCESSORY GEARBOX STARTER-GENERATOR DRIVE SHAFT SEAL WORN. LOSS OF ENGINE OIL.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P60GL
2004080400215	20040804	00215	CE  	2004	8	4	AUS20040434      	1	20040518	G	5320	07120591	SUPPORT BRACKET 			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BATTERY SUPPORT BRACKETS CRACKED.						1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C
2004080500013	20040805	00013	CE  	2004	8	5	AUS20040435      	1	20040330	G	5753	35115396	CLIP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT OB FLAP IB TRACK RIVETS LOOSE IN AREA ADJACENT TO LOWER SKIN ATTACHMENT. FURTHER INSPECTION FOUND BUCKLING AND 	CRACKING OF THE OUTBOARD SHEAR CLIP.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004080500014	20040805	00014	EU  	2004	8	5	AUS20040436      	1	20040401	G	3242	AHA1899	TORQUE TUBE     			BAG   	JETSTM	JETSTM4112  	       	EU  										BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BRAKE ASSEMBLY TORQUE TUBE CONTAINED NUMEROUS CRACKS IN TENON SLOTS. FOUND USING FLUORESCENT MAGNETIC PARTICLE INS	PECTION.  CRACKS WERE FOUND UP TO APPROXIMATELY 6.35MM (0.25IN) IN LENGTH.  BRAKE IS FROM A  REGISTERED AIRCRAFT. BRAKE 	HAD BEEN REMOVED DUE TO RUBBING ON AXLE AND CONTACT WITH WHEEL HUB CAUSING DAMAGE.				1	L	7	2 	4T			RT	A196
2004080500015	20040805	00015	NM  	2004	8	5	AUS20040438      	1	20040513	G	5310	65561001	DOOR FRAME      			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			63697							(AUS) NR 1 CARGO DOOR FRAME CRACKED IN AREAS ADJACENT TO DOOR STOP NR 5 AND NR 6.  FOUND DURING INSPECTION IAW AD/B727/1	65 AND MFG SB727-53A0219.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004080500016	20040805	00016	NM  	2004	8	5	AUS20040439      	1	20040526	G	3244	277A6000204	TIRE            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					MLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 MAIN WHEEL TIRE TREAD SEPARATED AND TIRE DEFLATED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080500017	20040805	00017	SW  	2004	8	5	AUS20040440      	1	20040526	G	7120	206033201167	STIFFENER       			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6394 							(AUS) RT FORWARD ENGINE MOUNT STIFFENER CRACKED THROUGH.   CRACK MIGRATED INTO LATERAL FRAME AT STN 155.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004080500018	20040805	00018	SO  	2004	8	5	AUS20040441      	1	20040521	G	3211	6792631	TRUNNION        			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC3Y	HCC3Y*      	GL  	RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR TRUNNION CRACKED.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P25EA
2004080500019	20040805	00019	NM  	2004	8	5	AUS20040442      	1	20040315	G	2913	6506806	PUMP            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HYDRAULIC SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) LT ENGINE DRIVEN HYDRAULIC PUMP FAILED DUE TO LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004080500020	20040805	00020	NM  	2004	8	5	AUS20040443      	1	20040519	G	2751	98010903	INDICATOR       			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					TE FLAPS	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT OB TRAILING EDGE FLAP INDICATOR FAILED.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU
2004080500021	20040805	00021	EU  	2004	8	5	AUS20040444      	1	20040520	G	2750	676801007	COMPUTER        			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	LF507 	LF5071H     	41580	NE  					TE FLAPS	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) FLAP COMPUTER FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004080500047	20040805	00047	GL  	2004	8	5	AUS20040445      	1	20040130	G	2510		SEAT BELT       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS SEAT BELT SHOULDER HARNESS DOES NOT FULLY RETRACT INTO INERTIA REEL.  INVESTIGATION FOUND A STOP INSTALLED 	IN THE WEBBING IN AN AREA JUST BELOW JUNCTION.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA
2004080500048	20040805	00048	CE  	2004	8	5	AUS20040446      	1	20040526	G	5711	122210523	SPAR            			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C*      	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING MAIN SPAR ANGLE CONTAINED EXFOLIATION CORROSION IN AREA OF WING ATTACHMENT ANGLE.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
2004080500049	20040805	00049	CE  	2004	8	5	AUS20040447      	1	20040517	G	3233	MS2877510	O-RING          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					NLG ACTUATOR	DAMAGED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR UPLOCK ACTUATOR O-RING DAMAGED.  HYDRAULIC FLUID LEAKING FROM ACTUATOR BODY.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
2004080500050	20040805	00050	CE  	2004	8	5	AUS20040448      	1	20040521	G	3234	99102791	SELECTOR VALVE  			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE SOLENOID FAILED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
2004080500051	20040805	00051	CE  	2004	8	5	AUS20040449      	1	20040524	G	8011	85104666	DRIVE ASSY      	LAMAR       		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	STARTER	SEIZED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					85104666					(AUS) STARTER MOTOR BENDIX DRIVE SEIZED INTERNALLY.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004080500052	20040805	00052	EU  	2004	8	5	AUS20040450      	1	20040527	G	3241	F7941116401	WIRE HARNESS    			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	ANTISKID SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			32288							(AUS) LT IB WHEEL SPEED SENSOR WIRE BROKEN.  RB IB TYRE BLOWNOUT.						2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG
2004080500053	20040805	00053	CE  	2004	8	5	AUS20040452      	1	20040519	G	2140	27D39	MOTOR           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	BLOWER	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) CABIN HEATER BLOWER MOTOR FAULTY.  MOTOR WAS VIBRATING AND PRODUCING SMOKE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA
2004080500054	20040805	00054	NM  	2004	8	5	AUS20040453      	1	20040528	G	2710	BACC2C4C05138EG	CONTROL CABLE   			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CABLE OUTER STRANDS BROKEN IN AREA LOCATED AT RT WING SPAR TRAILING EDGE AT WS 1110.  SOME OUTER STRANDS W	ERE ALSO BROKEN IN AN AREA LOCATED FURTHER OB AT APPROXIMATELY WS 1195.  SUSPECT CAUSED BY CABLE WEARING ON FAIRLEADS AL	ONG THE WING TRAILING EDGE.				2	L	7	4 	4F	4	F	RT	A20WE   	E30NE
2004080500055	20040805	00055	NE  	2004	8	5	AUS20040454      	2	20040411	G	7200	3030700	ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	RIGHT	OVERHEATED      	W				O				OTHER                   				M	E	J	OVER TEMP                 	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE OVERTEMPED ON START.  ENGINE REMOVED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004080500079	20040805	00079	CE  	2004	8	5	AUS20040455      	1	20040524	G	1430	NAS14740	BOLT            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UNDERCARRIAGE SADDLE BOLT CRACKED.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA
2004101800186	20041018	00186	NM  	2004	10	18	AUS20040456      	1	20040412	G	2751	2061141	INDICATOR       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 										(AUS) FLAP POSITION INDICATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004101800187	20041018	00187		2004	10	18	AUS20040457      	4	20040330	G	2210		LIMITER         			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					AUTOPILOT SYSTEM	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT TORQUE LIMITER FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004101800188	20041018	00188	NM  	2004	10	18	AUS20040458      	1	20040525	G	2910	272T3100321	PIPE            			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYSTEM	WORN            	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT HYDRAULIC SYSTEM PIPE WORN THROUGH BY BROKEN CLAMP LOCATED IN LT PYLON. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU
2004101800189	20041018	00189	NM  	2004	10	18	AUS20040459      	1	20040527	G	5210	60020019	BOTTLE          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					PAX DOOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7425 		3742					(AUS) DOOR 4L EMERGENCY POWER SUPPLY (EPS) BOTTLE TRIGGER LOCKED BY FITMENT OF A TEMPORARY SAFETY BOLT IN THE TRIGGER ME	CHANISM. THIS SAFETY BOLT WOULD HAVE PREVENTED FIRING OF THE BOTTLE TO OPEN THE DOOR IN AN EMERGENCY SITUATION.  PERSONN	EL/MAINTENANCE ERROR.				2	L	7	4 	4F	4	F	RT	A20WE   	E12EU
2004101800190	20041018	00190	SO  	2004	10	18	AUS20040460      	1	20040601	G	5711	16010	SPAR            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT FORWARD AUXILIARY SPARS CRACKED AT IB LOWER RAD II LOCATED AT STN 27. CRACKS EXTEND FOR APPROXIMATELY 12	.7MM(0.5IN) OB OF THE END OF THE SPAR IN A HORIZONTAL PLANE.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA
2004101800070	20041018	00070	NM  	2004	10	18	AUS20040461      	1	20040530	G	5220		DOOR            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					EMERGENCY EXITS	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT OVERWING EMERGENCY DOOR PREVENTED FROM COMPLETELY OPENING BY THE TARGET FOR THE LT SLIDE COMPARTMENT DOOR CLOSE	D SENSOR (S218) CATCHING ON THE TAIL OF A SCREW NUT INSTALLED ON THE PACKBOARD.  FURTHER INSPECTION REVEALED THAT THE LA	TCH CONTROL ROD THE TARGET IS MOUNTED TO HAD BEEN TWISTED AT THE FIXED CLEVIS END ALLOWING THE TARGET TO DROP INTO THE P	ATH OF THE SCREW INSTALLED ON THE PACKBOARD.			2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004101800071	20041018	00071	EA  	2004	10	18	AUS20040462      	2	20040530	G	7314	62E23186	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL	LEAKING         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE DRIVEN FUEL PUMP LEAKING EXCESSIVELY FROM PUMP BODY. A LARGE AMOUNT OF FUEL WAS SPRAYING ONTO THE TURBOC	HARGER WITH A HIGH RISK OF ENGINE FIRE. THE PUMP WAS A NEW ITEM WITH NO SIGN OF DAMAGE TO THE PUMP AND ALL THE MFGS TAMP	ER WIRES ARE IN PLACE. THERE IS NO SIGN OF LOOSENESS TO THE FOUR ALLEN KEY BOLTS AND THEY APPEAR TIGHT.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004101800072	20041018	00072	EU  	2004	10	18	AUS20040463      	1	20040531	G	3097		WIRE            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WINDSHIELD HEAT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) RT WINDSHIELD HEATING SYSTEM WIRING CABLE DAMAGED AND SHORTING TO EARTH IN AREA NEAR TERMINAL BLOCK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004101800073	20041018	00073	NM  	2004	10	18	AUS20040464      	1	20040528	G	1420	DP1011	CONNECTOR       			BOEING	737   	7378Q8      	13844BX	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ENGINE EGT/TIT	LOOSE           	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE EGT BOTTOM RT PROBE NOT CONNECTED. NO EVIDENCE OF LOCKWIRE. TOP RT PROBE LOOSE AND NOT LOCKWIRED. ELEC	TRICAL CONNECTOR DP0911 LOOSE. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800074	20041018	00074	NM  	2004	10	18	AUS20040465      	1	20040530	G	3242	26123121	BRAKE           			BOEING	737   	737832      	13844CF	NM  	GE    	CFM56 	CFM567B24   	 	NE  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1679 							(AUS) NR 3 BRAKE ASSEMBLY,  BRAKE PADS SEPARATED AND JAMMED THE BRAKE ONTO THE WHEEL.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800075	20041018	00075	NM  	2004	10	18	AUS20040466      	1	20040531	G	2910	82920010363	LINE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HYDRAULIC SYS	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 2 HYDRAULIC SYSTEM, HYDRAULIC PIPE CRACKED INTERNALLY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101800102	20041018	00102	NM  	2004	10	18	AUS20040467      	1	20040529	G	2823	125334D1	VALVE           			BOEING	737   	737724      	13844BY	NM  	GE    	CFM56 	CFM567B24   	 	NE  					FUEL SELECTOR	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 1 ENGINE SPAR VALVE FAILED TO OPEN.  INVESTIGATION COULD FIND NO FAULT WITH THE VALVE.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800114	20041018	00114	NM  	2004	10	18	AUS20040468      	1	20040601	G	2910	EM56203	VALVE           			BOEING	737   	737724      	13844BY	NM  	GE    	CFM56 	CFM567B24   	 	NE  					HYDRAULIC SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE HYDRAULIC SHUTOFF VALVE ELECTRICAL CONNECTOR D764 CROSS THREADED CAUSING DAMAGE TO CONNECTOR AND VALVE	. FOUND DURING INSPECTION IAW SB 737-24A1148.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800115	20041018	00115	NM  	2004	10	18	AUS20040469      	1	20040601	G	7997		WIRE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	OIL PRESS TRANS	WORN            	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE OIL PRESSURE TRANSMITTER CONNECTOR WIRING HAD WORN INSULATION.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101800116	20041018	00116	CE  	2004	10	18	AUS20040470      	1	20040531	G	3220		LANDING GEAR    			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	IO360A1G6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	NOSE	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION OF NOSE LANDING GEAR FOR A NOSE LANDING GEAR FAULT, THE NLG COLLAPSED, TRAPPING THE AME BETWEEN 	THE NOSE CONE AND THE GROUND. DUE TO THE QUICK REACTION OF WORKMATES, THE AME WAS RELEASED FROM BENEATH THE AIRCRAFT AND	 ADMITTED TO HOSPITAL WITH MINOR INJURIES. THE REASON FOR THE NLG COLLAPSE IS STILL BEING INVESTIGATED.				1	L	7	2 	3O	3	O	 	A29CE   	1E10	5	C	P43GL
2004101800117	20041018	00117	WP  	2004	10	18	AUS20040471      	2	20040602	G	7230	31032523	BLADE           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COMPRESSOR	BIRD STRIKE     	W				C				ABORTED TAKEOFF         				C	E	B	F.O.D.                    	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE FIRST STAGE COMPRESSOR BLADE BENT DUE TO BIRDSTRIKE.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2004101800118	20041018	00118	NM  	2004	10	18	AUS20040472      	1	20040530	G	3242	QF45085	SEAL            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					BRAKE	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 					QF45085					(AUS) LT MAIN LANDING GEAR NR 1 BRAKE PISTON SEAL PARTIALLY FAILED ALLOWING BRAKE FLUID TO LEAK ONTO BRAKE ROTORS.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800119	20041018	00119	EU  	2004	10	18	AUS20040473      	1	20040528	G	3320	BV033020205	SOCKET          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	CABIN	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) WINDOW LIGHT LOCATED AT ROW 10 GAVE A BURNING SMELL. INVESTIGATION FOUND THE A BURNT FLUORESCENT LAMP HOLDER AND L	AMP. CAUSE OF THE BURNING WAS AN INCORRECTLY INSTALLED LAMP WHICHCAUSED ARCING AT THE LAMP HOLDER. PERSONNEL/MAINTENANCE	 ERROR.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE
2004101800130	20041018	00130	CE  	2004	10	18	AUS20040474      	1	20040525	G	3010	10136458211	CIRCUIT BOARD   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	AIRFOIL ANTI-ICE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRFRAME DE-ICE SYSTEM PRINTED CIRCUIT BOARD (PCB) TIMER INOPERATIVE.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004101800138	20041018	00138	SW  	2004	10	18	AUS20040476      	1	20040603	G	3230	55010021	DRAG BRACE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT IB LOWER MAIN LANDING GEAR DRAG BRACE CRACKED IN AREA ADJACENT TO GREASE FITTING. FOUND DURING INSPECTION IAW A	D/SWSA226/89 AND SB226-32-068.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004101800139	20041018	00139	NM  	2004	10	18	AUS20040477      	1	20040525	G	7830	CF680C2	THRUST REVERSER 			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT ENGINE THRUST REVERSER FAILED TO OPERATE ON SELECTION DURING LANDING. INVESTIGATION AND ENGINE GROUND RUN COULD	 NOT FAULT SYSTEM. SUSPECT CAUSED BY ICING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004101800140	20041018	00140	NM  	2004	10	18	AUS20040478      	1	20040228	G	3840	45618380	THERMOSTAT      			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AIR SUPPLY	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) POTABLE WATER COMPRESSOR OVERHEATING. INVESTIGATION FOUND THAT THE COMPRESSOR MOTOR HAD SEIZED DUE TO THE OVERHEAT	 THERMOSTAT (THERMAL PROTECTOR) PN 45618-380 FAILING IN A CLOSED POSITION CAUSING THE MOTOR TO CONTINUALLY OPERATE AND F	INALLY SEIZE.				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004101800141	20041018	00141	NM  	2004	10	18	AUS20040479      	1	20040523	G	3260		LIGHT           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MLG	FAULTY          	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWN LIGHT FAILED TO ILLUMINATE ON GEAR SELECTION. INVESTIGATION FOUND A FAULTY LOCK MECHANIS	M IN THE LAMP LENS CAP.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004101800143	20041018	00143	EU  	2004	10	18	AUS20040480      	1	20040602	G	2730	NB451803	CONTROL ROD     			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL ROD CORRODED ON INTERNAL THREADS. FOUND DURING INSPECTION IAW SB 303 AND AD/BN2/082.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920
2004101800144	20041018	00144	CE  	2004	10	18	AUS20040481      	1	20040520	G	3610	12945054V6001	MANIFOLD        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					PNEUMATIC	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) LT BLEED AIR SPLITTER DUCT CRACKED AND LEAKING FROM THE MATING FLANGE RADIUS.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004101800145	20041018	00145	WP  	2004	10	18	AUS20040482      	2	20040518	G	7200	310338025	ENGINE          			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	LEFT	OVERTEMP        	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			3285 							(AUS) LT ENGINE EGT ROSE TO APPROXIMATELY 720 DEGREES WITH A REDUCTION IN TORQUE AND FUEL FLOW.  DUE TO THE EXCESSIVE EG	T THE ENGINE WAS REMOVED FOR AN OVERTEMP INSPECTION. NO RESULTS TO DATE.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
2004101800146	20041018	00146	NE  	2004	10	18	AUS20040483      	2	20040514	G	7200	CFM567B	ENGINE          			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					NR 2	BIRD STRIKE     	W				O				OTHER                   				E	C		VIBRATION/BUFFET          	F.O.D.                    		CL	CLIMB          	1			AU	S 					890451					(AUS) NR 2 ENGINE BIRDSTRIKE.  INSPECTION FOUND EVIDENCE OF BIRD REMAINS IN BOOSTER.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800147	20041018	00147	NM  	2004	10	18	AUS20040484      	1	20040513	G	5753		FLAP TRACK      			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					LT WING	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER REPORTED RAG SEEN IN WING TRAILING EDGE.  INVESTIGATION FOUND RAG LOCATED ON AREA OF LT WING REAR SPAR A	BOVE NR 3 FLAP TRACK.  THE RAG WAS NOT INTERFERING WITH ANY AIRCRAFT SYSTEM.  FOD PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800148	20041018	00148	EU  	2004	10	18	AUS20040485      	1	20040510	G	2730	8500341403	REGULATOR       			FOKKER	F27   	F27MK500    	4990629	EU  	RROYCE	DART  	DART*       	 	NE  	ROTOL	R4304	R1934304    	EU  	ELEVATOR CONTROL	STICKING        	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			6132 							(AUS) ELEVATOR CABLE TENSION REGULATOR STICKY IN OPERATION.						2	H	7	2 	4T	4	T	 	A817    	 	6	C	P899
2004101800149	20041018	00149		2004	10	18	AUS20040486      	4	20040608	G	3416	40598501	LIGHT           	HONEYWELL   		DHAV  	DHC8  	DHC8*       	       	NM  										ALTIMETER, BAROM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					94057779					(AUS) ALTIMETER LAMP FAILED. FOUND DURING INSPECTION IAW AD/RAD/43.						2	H	7	2 	4T			RT	A13NM
2004101800150	20041018	00150	NM  	2004	10	18	AUS20040487      	1	20040603	G	2701	BACB10BW21	BEARING         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CONTROL COLUMN	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) FIRST OFFICER'S CONTROL WHEEL BEARING NOTCHY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004101800151	20041018	00151	NM  	2004	10	18	AUS20040488      	1	20040525	G	3610	8021704	VALVE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PNEUMATIC DIST	FAULTY          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 					9612153					(AUS) RT ENGINE BLEED SYSTEM PRESSURE REDUCING VALVE (PRV) SUSPECT FAULTY. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004101800152	20041018	00152	NM  	2004	10	18	AUS20040489      	1	20040607	G	2430	285A18408	MODULE          			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					DC GENERATING	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRICAL METERS BATTERY AND GALLEY POWER MODULE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800153	20041018	00153	CE  	2004	10	18	AUS20040490      	1	20040529	G	5610		WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS)  PILOTS WINDSHIELD CRACKED ON INSIDE LAMINATE.  OUTER LAMINATE WAS INTACT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004101800154	20041018	00154	SO  	2004	10	18	AUS20040491      	1	20040531	G	7922	53E22144A	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE OIL TEMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			824  							(AUS) ENGINE OIL TEMPERATURE REGULATING VALVE (VERNATHERM) BREAKING UP. METAL CONTAMINATION OF ENGINE OIL SYSTEM.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004101800155	20041018	00155	CE  	2004	10	18	AUS20040492      	1	20040607	G	3231	4532103054003	SHAFT           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR IB DOOR GIMBAL ASSEMBLY SHAFT CRACKED FOR APPROXIMATELY 75 PERCENT OF CIRCUMFERENCE.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004101800156	20041018	00156	NM  	2004	10	18	AUS20040493      	1	20040606	G	5610	5717623097	WINDOW          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) CAPTAIN'S NR 2 SLIDING WINDOW OUTER PANE CRACKED IN UPPER FORWARD CORNER.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004101800157	20041018	00157	NM  	2004	10	18	AUS20040494      	1	20040526	G	1430		BOLT            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B1US  	 	GL  					MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR OB STABILIZING FITTING OB LOWER ATTACHMENT BOLT SHEARED ALONG THE SHANK IN AN AREA COINCIDING	 WITH THE WING REAR SPAR.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
2004101800158	20041018	00158	NM  	2004	10	18	AUS20040495      	1	20040604	G	3520	174080142	OXYGEN MASK     			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PASSENGER OXYGEN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER OXYGEN MASKS INCORRECTLY PACKED INTO PASSENGER SERVICE UNITS (PSU).  OXYGEN MASK HOSES CAUGHT BETWEEN DO	OR AND MASK HOUSING CAUSING HOSES TO BECOME KINKED AND THE DOORS TO BULGE WHEN CLOSED. UNITS AFFECTED WERE LOCATED AT 39	DEF , 37DEF,5JK, 1EF, 48DEF, 45DEF AND 40DEF. TOTAL NUMBER OF MASKS 14.  PERSONNEL/MAINTENANCE ERROR.				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004101800159	20041018	00159	EU  	2004	10	18	AUS20040496      	1	20040607	G	7120	60510021	TRUSS           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	ENGINE MOUNT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE LOWER LT ATTACHMENT TRUSS CORRODED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
2004101800160	20041018	00160	SW  	2004	10	18	AUS20040497      	1	20040610	G	2720	2672003	PEDAL           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	RUDDER CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS RT RUDDER PEDAL CRACKED. CRACK LENGTH 4MM (0.147IN). FOUND DURING INSPECTION IAW SB 227-27-049.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
2004101800161	20041018	00161	NM  	2004	10	18	AUS20040498      	1	20040606	G	2742	6355B000103	ACTUATOR        			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					STAB TRIM	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 					1666					(AUS) HORIZONTAL STABILIZER TRIM ACTUATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800162	20041018	00162	SO  	2004	10	18	AUS20040499      	2	20040418	G	8520	630687P015	PISTON          			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) PISTON FAILED. SUSPECT FAULTY INJECTOR. LIMITED INFORMATION PROVIDED.						1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA
2004101800163	20041018	00163	NM  	2004	10	18	AUS20040500      	1	20040606	G	2530	GENM2585015	OVEN            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					BUFFET/GALLEYS	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 			3609 		90012615					(AUS) FORWARD GALLEY OVEN FAILED.  FIRE EXTINGUISHED DISCHARGED INTO OVEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
2004101800164	20041018	00164	EU  	2004	10	18	AUS20040501      	1	20040610	G	5312		FIREWALL        			BAG   	BAE146	BAE146300A  	1500267	EU  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FIREWALL CRACKED AT 7 O'CLOCK POSITION. FOUND DURING INSPECTION IAW AD/BAE146/053.						2	H	7	4 	4F			RT	A49EU
2004101800165	20041018	00165	EU  	2004	10	18	AUS20040502      	1	20040601	G	7603	SP126E	WASHER          	LYC         		BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	POWER LEVER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THROTTLE QUADRANT FRICTION ADJUSTER WASHER MISSING.  FOUND DURING INSPECTION IAW AD/BN2/69 AND SB 272.						1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920
2004101800166	20041018	00166	NM  	2004	10	18	AUS20040503      	1	20040611	G	2913	66087	PUMP            			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					HYDRAULIC SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE DRIVEN HYDRAULIC PUMP LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004101800167	20041018	00167	NE  	2004	10	18	AUS20040504      	2	20040610	G	7260	3022376	SEAL            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE STARTER-GENERATOR OIL SEAL LEAKING.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004101800168	20041018	00168	CE  	2004	10	18	AUS20040505      	1	20040614	G	2710	05232182	CONTROL ROD     			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	AILERON CONTROL	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT AILERON PUSH-PULL ROD BENT.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004101800169	20041018	00169	NM  	2004	10	18	AUS20040506      	1	20040612	G	6210	A0162	BLADE           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE CORRODED ON BLADE TIP.						1	G	7	1 	3O	3	O	 	H10WE   	E274
2004101800170	20041018	00170		2004	10	18	AUS20040507      	4	20040602	G	6122	A20028	BEARING         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	PROP GOVERNOR	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 			1727 							(AUS) LT ENGINE PROPELLER GOVERNOR FAULTY.  INVESTIGATION FOUND OIL PUMP GEAR PN A20107 WORN, PIVOT PIN PN  A20026 EXTRE	MELY WORN AND BEARING PN  A20028 DESTROYED.  THE HOUSING WAS GOUGED TO A DEPTH OF APPROXIMATELY 3.175MM (0.125IN) IN THE	 BEARING AREA AND THE PUMP WALL WERE BADLY SCORED. METAL CONTAMINATION OF ENGINE OIL  SYSTEM.				1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL
2004101800172	20041018	00172	SO  	2004	10	18	AUS20040508      	1	20040608	G	3232	OAS29243	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG DOOR	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					2626					(AUS) LT MAIN LANDING GEAR DOOR HYDRAULIC RAM FAULTY.  INVESTIGATION FOUND BRINNELLED LOCKING BALLS AND LOW SPRING PRESS	URE ON LOCKPUCK.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004101800173	20041018	00173	EU  	2004	10	18	AUS20040509      	1	20040611	G	3610	3925308	VALVE           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PNEUMATIC DISTRI	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			352  							(AUS) LT BLEED AIR VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE
2004101800174	20041018	00174	NM  	2004	10	18	AUS20040510      	1	20040611	G	2597		WIRE HARNESS    			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PSU	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SERVICE UNIT (PSU) LOOM WORN AND SPARKING. PSU LOCATED AT SEAT 44JK.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004101800175	20041018	00175	NE  	2004	10	18	AUS20040511      	2	20040607	G	7200	ARRIEL1S1	ENGINE          			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  						MAKING METAL    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			654  							(AUS) ENGINE CHIP DETECTORS AND OIL FILTER CONTAMINATED WITH METAL. ENGINE WAS REPLACED.						1	G	7	2 	3U	3	U	 	H1NE    	E19EU
2004101800176	20041018	00176	EU  	2004	10	18	AUS20040512      	1	20040615	G	5411	HC546J0032	RIB             			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NACELLE/PYLON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1, NR 3 AND NR 4 PYLONS HAD NR 4 RIB CRACKED IN THE LOWER FLANGE RADIUS.  PYLON NR 1, CRACK LENGTH 22.86MM (0.9	IN) PYLON NR 3, CRACK LENGTH 12.7MM (0.5IN) PYLON NR 4, CRACK LENGTH 20.32 (0.8IN).					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
2004101800177	20041018	00177	NM  	2004	10	18	AUS20040513      	1	20040611	G	3320		SOCKET          			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	CABIN	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) FRONT RT CABIN FLOUROSCENT LAMP HOLDER ARCING AND SMOKING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101800179	20041018	00179	NM  	2004	10	18	AUS20040514      	1	20040614	G	3233	273A210102	ACTUATOR        			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR ACTUATOR LOCKNUT LOOSE AND LOCKWIRE BROKEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004030400072	20040304	00072	EU  	2004	3	4	B30R20040226     	1	20040219	G	5310		DOOR FRAME      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUSELAGE	CRACKED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204Y	1359 	100  			3101	9571			DURING 100 HOUR INSPECTION DISCOVERED CO-PILOT DOOR POST CRACKED 14 INCHES LONG STARTING 8 INCHES ABOVE CABIN FLOOR, EXC	EEDING THE LIMITS IN REPAIR MANUAL.  REPAIRED CRACK IAW MM.   REQUESTED FROM MFG.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004091400202	20040914	00202	CE  	2004	9	14	B3OR20040709     	1	20040709	G	3240	1280509101	LINE            			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550*      	 	SO  					MLG BRAKE	CUT             	B			B3OR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SW	03	5515Y					21064233	289125R			PILOTS ENTERED THE AC AND TAXIED DOWN THE TAXIWAY. AS BRAKES WERE BEING APPLIED, IT WAS NOTICED THAT RT BRAKE WAS NOT OP	ERATING. AC EXITED TAXI WAY AT A LOW SPEED CAME TO A STOP IN ABOUT FOUR INCHES OF MUD ALONGSIDE OF TAXIWAY. THERE WAS NO	 DAMAGE TO AC OR PROP.  PIC HAD SHUTDOWN ENG WHEN IT WAS REALIZED BRAKES WERE NOT WORKING.  MECH FOUND BRAKE LINE COMING	 FROM AIRFRAME THAT PASSES THROUGH LANDING GEAR STRUT, HAD CONTACTED RT BRAKE DISC.  BRAKE LINE TUBE BEING SOFTER METAL 	THAN BRAKE DISC WAS CUT AND CAUSED BRAKE FLUID TO LEAK OUT CAUSING NO BRAKE SITUATION ON RT SIDE.  FUTHER INVESTIGATION 	SHOWED THAT LINE WAS POSSIBLY STEPPED ON PRIOR TO THE TAXI OPERATION, CAUSING IT TO COME IN CONTACT WITH BRAKE DISC.	1	H	7	1 	3O	3	O	 	3A21    	E3SO
2004091400201	20040914	00201	EU  	2004	9	14	B3OR20040712     	1	20040707	G	2150	900A4031	EVAPORATOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					AIR CONDITIONER	CRACKED         	B			B3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5204X					3099	9570			PILOT WAS OPERATING AC AIR CONDTIONING SYSTEM AND HEARD A NOISE COMMING FROM THE FWD EVAPORATOR UNDER INSTRUMENT PANEL. 	UPON RETURN TO BASE, MECHANIC VERIFIED THAT THE NOISE WAS COMMING FROM THE FWD EVAPORATOR. THE EVAPORATOR WAS REMOVED AN	D IT WAS FOUND TO HAVE CRACKS IN THE HOUSING NEAR THE BLOWER ASSEMBLIES. THE CRACKS CAUSED THE BLOWERS TO BE MISALIGNED 	AND THAT WAS THE SOURCE OF THE NOISE. THE UNIT WAS REPLACED AND THE SYSTEM SERVICED AND OPERATES NORMALLY. THIS OPERATOR	 HAS REPLACED FOUR (4) SUCH EVAPORATOR ASSEMBLIES IN THE PAST TWO (2) YEARS DUE TO CRACKS OF THIS TYPE. MAYBE THE MANUFA	CTURER NEEDS TO LOOK INTO A BETTER HOUSING MATERIAL, THE HARD PLASTIC MATERIAL CURRENTLY USED IS NOT TOUGH ENOUGH.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004092000114	20040920	00114	CE  	2004	9	20	B3OR20040719     	1	20040719	G	7160	21500351	HINGE           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550N      	17042	SO  					ALTERNATE AIR	LOOSE           	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5515Y					21064233	289125R			ANNUAL INSP,  ALTERNATE AIR SOURCE DOOR WAS LOOSE. MECHANIC FOUND DOOR SPRING P/N 1250728-1, HINGE PIN P/N MS20253P2-364	 IN INDUCTION AIR BOX DUCTING.  PIN AND SPRING WERE RE-ASSEMBLED WITH DOOR. WHEN PARTS WERE RE-ASSEMBLED, BOTH UPPER AND	 LOWER ENDS OF HINGE WERE CRIMPED. CRIMPING BOTH ENDS OF  HINGE DOES NOT ALLOW PIN TO FALL OUT, OVER TIME, ALLOW SPRING 	TO COME LOOSE. ABOUT A YEAR AGO, ENGINE INGESTED SPRING AND CAUSED ENOUGH DAMAGE TO NR 5 CYLINDER AND NR 5 PISTON TO HAV	E THEM BOTH REPLACED. MFG MM IS VAUGE ON HOW TO ASSEMBLE THESE PARTS. CRIMPING BOTH ENDS OF THE HINGE WOULD ENSURE THAT 	THESE PARTS WILL NOT COME LOOSE AND NOT GET INGESTED INTO THE ENGINE.	1	H	7	1 	3O	3	O	 	3A21    	E3SO
2004120600034	20041206	00034	CE  	2004	12	6	B3OR20041029     	1	20040922	G	5740	1011200131	ATTACH FITTING  			BEECH 	200   	A200        	1152921	CE  										WING	DAMAGED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y	13789				BC03				ON 22 SEPTEMBER 2004 A 5 YEAR WING BOLT INSPECTION WAS COMPLIED WITH ON A BEECHCRAFT A200 AIRCRAFT. THREE OF THE WING AT	TACH FITTINGS WERE FOUND TO HAVE DAMAGE TO THE FLAT FACE PORTION OF THE FITTINGS, THE AREA WHERE THE WASHER RESTS ON THE	 FITTING. THE DAMAGE WAS SEVERE ENOUGH FOR THE AIRCRAFT MANF, RAYTHEON AIRCRAFT TO BE CONTACTED AND A REPAIR SCHEME TO R	EPAIR THE DAMAGE WAS REQUESTED. THE AFFECTED FITTINGS WERE THE LT LOWER OUTBOARD AFT P/N: 35-115058-2, RT LOWER OUTBOARD	 AFT, P/N: 35-115058-3, AND THE RT LOWER INBOARD FWD FITTING WHICH INCORPORATES THE FWD CARRY THROUGH SPAR, P/N: 101-120	013-1. THE DAMAGE SEEMED TO BE CAUSED BY THE WASHER BEING INSTALLED BACKWARDS AT ONE POINT.	1	L	7	2 	4T			 	A24CE
2004030300202	20040303	00202	SO  	2004	3	3	BHA03RS          	2	20040223	G	8500		ENGINE          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RIGHT	DAMAGED         	E				A				UNSCHED LANDING         				F	K		FLT CONT AFFECTED         	FLUID LOSS                		CL	CLIMB          	1			NM	04	114BH	3094 	1494 			340A1230	503082	020379		DURING FLIGHT, RT ENGINE OIL PRESSURE GAGE INDICATED A SIGNIFICANT INCREASE IN PRESSURE. RT ENGINE DAMAGE OCCURRED.  AIR	CRAFT LANDED WITHOUT FURTHER INCIDENT.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA
2004050300153	20040503	00153	CE  	2004	5	3	BHA04RS          	1	20040408	G	5341	50110241	ATTACH FITTING  			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	414PG	3914 				414A0811				IN COMPLYING WITH SUPPLEMENTAL INSPECTION 57-10-20, FOUND THE RT WING LOWER SPAR ATTACH FITTING HAD SIGNIFICANT CORROSIO	N IN SOME OF THE FITTING MOUNTING HOLES.  THE FITTING WAS REPLACED. NO FURTHERDEFECTS WERE NOTED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE
2004050700001	20040507	00001	SO  	2004	5	7	BHA05RS          	2	20040423	G	8530	TISN712BCA221	CYLINDER HEAD   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	SEPARATED       	B				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NM	04	414PG	204  				414A0811	514461			DURING POWER REDUCTION FROM TAKE-OFF POWER TO CLIMB POWER, A (POP) WAS HEARD AND ONE OF THE ENGINES BEGAN RUNNING ROUGH.	 THERE WAS NO INSTRUMENT/GAGE INDICATION AS TO WHICH ENGINE. AIRCRAFT LANDED WITH OUT INCIDENT. POST FLIGHT EXAMINATION 	FOUND NR 1 ENGINE, NR 6 CYLINDER HEAD HAD SEPARATED.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE
2004123000055	20041230	00055	SO  	2004	12	30	BJ3R200400002    	1	20040927	G	2410	3656624R	ALTERNATOR      			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	DEFECTIVE       	B				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			WP	03	75143		27   			32R7680263	L1444048A			PREVIOUSLY INSTALLED OVERHAULED ALTERNATOR FAILED AFTER APPROXIMATELY 27 HOURS OF OPERATION.  THE ALTERNATOR WAS MANUFAC	TURED BY KELLY AEROSPACE/ELECTROSYSTEMS.  THERE WAS EXCESSIVE BINDING OF THE ALTERNATOR SHAFT AND PULLEY.  IN ADDITION, 	TWO EACH OF THE COOLING FINS BROKE OFF THE ALTERNATOR.				1	L	7	1 	3O	3	O	 	A3SO    	1E4
2005030800055	20050308	00055	EA  	2005	3	8	BJ3R200400003    	2	20041011	G	7314	62E22581	PUMP            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE FUEL	DEFECTIVE       	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			WP	03	242RR	200  				4636348	L1149261A			PILOT REPORTED, WHEN TURNING ON ELECT FUEL BOOST PUMP TO PREPARE FOR DESCENT, ENG RAN VERY ROUGH AND WAS SIGNIFICANT POW	ER LOSS.  ENG WOULD NOT REMAIN RUNNING WITH FUEL BOOST PUMP ON. WHEN THE BOOST PUMP WAS TURNED OFF THE ENG OP WAS SATISF	ACTORY.  DURING SUBSEQUENT TAXI OPERATION, THE ENG WOULD DROP OVER 200 RPM WITH THE BOOST PUMP TURNED ON AND AT LOW RPM 	THE ENG WOULD SHUT DOWN.  AFTER TALKING WITH LYCOMING TECH REPRESENTATIVES, IT WAS DETERMINED THAT THE ENG DRIVEN FUEL P	UMP WAS PRESS SENSITIVE AND COULD NOT OPERATE WITH THE INCREASED FUEL PRESSURE THE ELECTRIC PUMP DELIVERED TO IT. AFTER 	REPLACING THE ENG DRIVEN FUEL PUMP, ENG OPERATION WAS SATISFACTORY WITH AND W/O THE ELECTRIC BOOST PUMP TURNED ON.	1	L	7	1 	3O	3	O	RT	A25SO   	1E4
2004030300200	20040303	00200	CE  	2004	3	3	BROWN2004001     	1	20040223	G	5410		PYLON           			LEAR  	45    	45LEAR      	5170805	CE  										ENG PYLON	VIBRATION       	C				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CE	03						042				AIRCRAFT CONTINUES TO EXPERIENCE A RUMBLE IN FLIGHT AT SPEEDS BETWEEN 430 AND 460 KTAS (NORMAL CRUISE SPEEDS).  MFG HAS 	MADE NUMEROUS ATTEMPS TO CORRECT THE PROBLEM BUT THEY HAVE NOT BEEN SUCCESSFUL.  THE RUMBLE CAN BE HEARD AND FELT IN THE	 COCKPIT AND CABIN.  THE RUMBLE APPEARED TO HAVE COME FROM THE ENGINE PYLON AREAS.  THE ENGINE PYLON AND RT GEAR DOOR LE	ADING EDGE AREAS HAVE BEEN REWORKED IAW MFG ENGINEERING DISPOSITION.  THE PROBLEM HAS NOT BEEN RECTIFIED AS TO DATE.			2	L	7	2 	4F			RT	T00008WI
2005022200207	20050222	00207	NE  	2005	2	22	C7GR861J         	2	20040820	G	7310	419110003	MANIFOLD        	HONEYWELL   							LYC   	LTS101	LTS101750B1 	41560	NE  					PT MODULE	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		900  	900  		G94G001		LE48166BEF			LTS101-750B-1 ENGINE, SN: LE-48166BEF WAS RECEIVED BY THIS REPAIR STATION (CRS NR C7GR861J) FOR ROUTINE MAINTENANCE.  SI	NCE WE HAD RECEIVED SOME NEW MANIFOLD ASSEMBLIES WITH IMPROPERLY TORQUED BOLTS (16 EA) THAT SECURE EIGHT COVERS ON THE I	NJECTOR BLOCKS, DECIDED TO PERFORM A TORQUE CHECK ON THIS FUEL MANIFOLD (TSN = 900 HRS).  BREAKAWAY TORQUES AS LOW AS 18	 IN/LB WAS OBSERVED.  THE PROPER TORQUE IS 40-45 IN/LB.  THIS CONDITION HAS BEEN REPORTED TO HONEYWELL, PHOENIX FOR PROP	ER INVESTIGATION AND RESOLUTION.							3	U			E5NE10
2004031500113	20040315	00113		2004	3	15	CA040102002      	4	20040102	G	3417	9B810202	ADC             			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	INTERMITTENT    	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) PRIOR TO DEPARTURE THE FLIGHT CREW A MACH AIRSPEED WARNING CLACKER INOPERATIVE ASSOCIATED WITH A FLAG ON THE MACH 	AIRSPEED INDICATOR. RECTIFICATION THE MACH AIRSPEED INDICATOR WAS REPLACED. HOWEVER THE SNAG RETURNED ON DECEMBER 29.  T	HE SYSTEM WAS PLACED ON MEL. THE MACH AIRSPEED INDICATOR WAS REPLACED AGAIN ON DECEMBER 31. HOWEVER THE FAULT RETURNED F	OR A THIRD TIME ON JANUARY 2, 2004.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004031500122	20040315	00122	SO  	2004	3	15	CA040103001      	1	20040102	G	5540	4004009	TORQUE TUBE     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RUDDER	CORRODED        	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLYING WITH AD 2003-24-07, FOUND SURFACE CORROSION OF RUDDER TORQUE TUBE (VISUAL INSPECTION OF RUDDER INT	ERNAL STRUCTURE MFG SB NR 1105A. REMOVED TORQUE TUBE AND FOUND AREA TO BE INSPECTED IAW AD REPAIRABLE BUT FOUND THAT THE	 INTERNAL TORQUE TUBE CORROSION SEVERE AND METAL/OXIDE FALLING OFF TORQUE TUBE INTERNAL WALLS. (NOT MENTIONED BY AD). RU	DDER ALUMINUM RIBS TO STEEL TORQUE TUBE CORROSION ALSO NOTED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500132	20040315	00132	EA  	2004	3	15	CA040104001      	2	20040102	G	7320	252444076	FUEL CONTROL    			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	LT ENGINE	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA								PCE52113			(CAN) LT ENGINE HAD TO BE SHUT DOWN IN FLIGHT AS FCU THROTTLE ARM WOULD NOT RETURN TO IDLE. DUE TO WEEKEND AND PARTS ON 	ORDER WE WILL BE REMOVING FCU NEXT WEEK.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC
2004031500140	20040315	00140		2004	3	15	CA040104002      	4	20040101	G	8300		FLANGE          			BOEING	727   	727231      	1384079	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					ACCESSORY GEARBO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						6674486K					(CAN) SCHEDULED MAINTENANCE WAS CARRIED OUT TO REPLACE THE FCU/FUEL PUMP QUAD RING. THE RUN OUT TORQUE INSPECTION WAS CA	RRIED OUT AND THE CLEARANCE FAILED. DISASSEMBLY OF THE AREA DETERMINED THAT THE QUAD RING NUT ATTACHMENT FLANGE WAS CRAC	KED.  THE UNSERVICEABLE GEARBOX WAS REMOVED AND A SERVICEABLE UNIT WAS INSTALLED. NO FURTHER PROBLEM WAS FOUND.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004031500141	20040315	00141	NM  	2004	3	15	CA040105001      	1	20040101	G	2435	51539008D	GCU             	LUCAS       		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	STARTER GEN	FAILED          	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			31251	31251		1163					(CAN) DURING NR 1 ENGINE START AFTER PUSHBACK SMOKE WAS NOTED COMING OUT OF THE GEN EXHAUST DUCT ON THE NR 1 NACELLE.  T	HE PILOT IMMEDIATELY SHUT ENGINE DOWN AND DECLARED AN EMERGENCY, REQUESTED ERS RESPONCE. PASSENGERS WERE DEPLANED AND PI	LOT NOTED THAT GENERATOR WAS STILL SPOOLING AFTER EVERYTHING WAS SHUT DOWN, MAINTENANCE WAS SUMMONED TO AC AND MAIN BATT	ERY WAS DISCONNECTED AND GENERATOR STOPPED.  AC WAS BROUGHT BACK TO HANGAR AND STARTER GEN, GCU AND MAIN BATTERY WERE RE	PLACED AND AIRCRAFT RETURNED TO SERVICE AFTER ALL FUNCTION CHECKS WERE CARRIED OUT. COMPONENTS WILL BE SENT OUT FOR REPA	IR AND INVESTIGATION AS TO WHY THE GEN DIDN'T DISENGAGE AFTER START UP WHICH CAUSED THE INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500156	20040315	00156	EU  	2004	3	15	CA040105008      	1	20040103	G	3260	A23802105	SQUAT SWITCH    			AMD   	FALC20	FALCON20F5  	2730105	EU  	GE    	CF700 	CF7002D2    	30010	NE  					NLG	FROZEN          	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) ON LANDING THE PIC COULD NOT ACTIVATE THE NORMAL BRAKES AND THE NOSE WHEEL STEERING. PIC USED NR 2 BRAKE SYSTEM AN	D DIFFERENTIAL POWER TO CONTROL THE AC. SQUAT SWITCH WAS REMOVED, CLEANED AND RE-INSTALLED.  NORMAL BRAKES AND NOSE WHEE	L STEERING FUNCTION  TESTED SERVICEABLE. AC RETURNED TO SERVICE.  OPERATOR PLANS TO IMPLEMENT MONTHLY INSPECTION AND CLE	ANING OF ALL LANDING GEAR SWITCHES OF MOISTURE.			2	L	7	2 	4F	4	F	RT	A7EU    	E7EA
2004031500165	20040315	00165	NE  	2004	3	15	CA040106002      	2	20040102	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2	MAKING METAL    	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								872684			(CAN) CREW REPORTED APPROXIMATELY 30 MINUTES FROM DESTINATION, THAT NR 2 ENGINE OIL PRESSURE HAD DROPPED BELOW MINIMUM. 	 CREW ELECTED TO PERFORM IN FLIGHT SHUT DOWN. CREW REQUESTED CFR AND LANDED WITHOUT INCIDENT. INSPECTION REVEALED NR 2 E	NGINE 2 QTS LOW WITH NO SOURCE OF OIL LEAKS. AGB CHIP DETECTOR REVEALED SOME METAL DEBRIS. CHIP DETECTOR TROUBLESHOOTING	 KIT WAS INSTALLED AND SECOND INSPECTION OF THE CHIP DETECTOR REVEALED A SIGNIFICANT AMOUNT OF METAL. A BOROSCOPE INSPEC	TION REVEALED THAT THE AXIS P GEAR WAS MISSING TEETH AND THAT THE AXIS B-B GEAR WAS HEAVILY WORN. LAB ANALYSIS OF THE RE	MOVED DEBRIS CONFIRMED TO BE M50 MATERIAL. ENGINE WAS REPLACED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500183	20040315	00183	EA  	2004	3	15	CA040106008      	1	20040106	G	2497		WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					E/E COMP.	FAILED          	W				K				NONE                    				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING, CAUTION MSG ESS TRU 1 ON EICAS A PUFF OF ELECTRICAL ODOR WAS DETECTED AT GATE FOUND A1 CB POPPED WO	ULD NOT RESET. DUE TO THIS SITUATION THREE WIRES WERE CHANGED ALSO TR1 REPLACED AND J12 CONNECTOR REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500186	20040315	00186	EA  	2004	3	15	CA040106011      	1	20040104	G	2710		CONTROL CABLE   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					AILERON	CONTAMINATED    	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXING DURING FLT CONTROL CHECK FOUND AILERONS NOT RETURNING TO NEUTRAL. AFTER INVESTIGATION FOUND WHEEL WEL	L CONTAMINATED WITH DIRT AND MOISTURE. AREA CLEANED AND LUBRICATED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004032500035	20040325	00035	GL  	2004	3	25	CA040107008      	1	20040107	G	7921	654585	OIL COOLER      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL COOLER FOUND CRACKED ON OB FORWARD LOWER CORNER FLANGE WHERE THE BAFFLE IS ATTACHED. CRACK IS ABOUT 1 INCH LON	G.  THIS IS THE THIRD COOLER FOUND CRACKED ON THE TYPE OF INSTALLATION.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2004032500043	20040325	00043	EA  	2004	3	25	CA040108003      	1	20040107	G	2497	BMS1360T01C03G0	WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ELECTRICAL	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE RE-INSTALLING CIRCUIT BREAKER PANEL THAT WAS ROBBED TO SERVICE AN OTHER AIRCRAFT THE MECHANIC NOTICE THREE P	OWER CABLES WERE SHAVING ALONG THE STRUCTURE OF THE PANEL.  (STRAINS WERE SHOWING)  THOSE THREE WIRES WERE REPLACED, FOL	LOWING THIS FINDING, A CAMPAIN WILL BE LAUNCHED DUE TO FIRE POTENTIAL.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004032500046	20040325	00046	CE  	2004	3	25	CA040108007      	1	20040107	G	2820		VALVE           			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					FUEL CROSSFEED	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REFUELING, FBO LINE CREW FAILED TO CARRY OUT SINGLE POINT REFUELING PRE-CHECK. DURING FUELLING, ONLY LT TAN	K WAS FILLED (RT REFUELING VALVE APPARENTLY FAILED IN THE CLOSED POSITION). BY THE TIME THE FLIGHT CREW NOTICED THE DIFF	ICULTY A SIGNIFICANT FUEL IMBALANCE HAD BEEN CREATED, REQUIRING CROSSFEED FROM LT TO RT TANK.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004032500049	20040325	00049	EA  	2004	3	25	CA040109003      	1	20040108	G	5270	600314703	ROLLER          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					STRIKER GUIDE	MISALIGNED      	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) AFTER TAKE OFF, DOOR LATCH CAUTION. 30 SEC LATER, PASSENGER DOOR. PRESSURE OK AND DOOR INDICATION PIN INSIDE WERE 	IN THE GREEN. REPLACED FORWARD STRIKER GUIDE ROLLER IAW FMR. SEAL LUB AND VENT HOLE ALIGN. ALL LATCH PINS & HANDLE LUB.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004032500050	20040325	00050	NM  	2004	3	25	CA040109004      	1	20040109	G	2612		FIRE DETECTOR   			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					ENGINE BAY	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE ENGINE FIRE WARNING BELL SOUNDED CONTINUOUSLY, THERE WERE NO ENGINE WARNING LIGHTS ON.  ON THE GR	OUND MAINTENANCE INSPECTED ALL ENGINES NO FAULTS WERE FOUND. MAINTENANCE WAS UNABLE TO DUPLICATE PROBLEM AGAIN ON THE GR	OUND. THE FIRE DETECTION DETECTOR UNIT P/N 65-24920-3 WAS REPLACED . REMOVED AND INSPECTED AND CLEANED PIN/SOCKETS AN AL	L THREE ENGINE FIRE DETECTION POWER OPERATING UNITS P/N 1011B-1. THE SYSTEM WAS TESTED WITH NO FAULTS. THE AIRCRAFT WAS 	RETURNED TO SERVICE AND OPERATED WITHOUT ANY FURTHER PROBLEMS.		2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004032500062	20040325	00062	EU  	2004	3	25	CA040109006      	1	20040107	G	2913	716988	PUMP            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYDRAULIC SYS	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			23682	23682				LF05559AC			(CAN) IN FLIGHT SHUT DOWN OF NR 2 ENGINE DUE TO LOSS OF OIL PRESSURE AND QUANTITY. MAINTENANCE FOUND EVIDENCE OF HYD FLU	ID MIGRATION INTERNALLY FROM HYDRAULIC PUMP TO THE PUMP SHAFT. SUSPECT THAT HYD FLUID CAUSED DETERIORATION OF THE PUMP S	HAFT SEAL (O-RING) TO THE POINT THAT IT CAUSED THE ENGINE OIL TO BE LOST. PUMP REPLACED.  NR 2 ENGINE ALSO BEING REPLACE	D.			2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004032500063	20040325	00063	NM  	2004	3	25	CA040109007      	1	20040109	G	5610	NP1579029	WINDOW          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PREFLIGHT INSPECTION , FLT ENGINEER DISCOVERED OUTER PLY OF PILOT SIDE WINDOW WITH MULTIPLE CRACKS EXTENDING AR	OUND THE CIRCUMFERENCE OF WINDOW ORIGINATING FROM LOWER FWD CORNER.  NO OBVIOUS IMPACT DAMAGE FOUND ON INSPECTION. NO M.	E.L. RELIEF. MANUFACTURER ADVISED TO CHANGE WINDOW BEFORE FURTHER FLIGHT. OVERNIGHT TEMP: -13C				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004032500068	20040325	00068	EU  	2004	3	25	CA040110001      	1	20040109	G	2997	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF THE CREW SELECTED GEAR UP. THE HYDRAULIC CAWS LIGHT CAME ON AND THE GEAR WOULD NOT FULLY RETRACT. T	HE GEAR WAS EXTENDED FULLY WITH THE HAND PUMP AND AN UNEVENTFUL LANDING CARRIED OUT. UPON INSPECTION BY MAINTENANCE, THE	 HYDRAULIC RELAY K601 WAS FOUND TO BE AT FAULT. THE RELAY WAS REPLACED, GEAR SWINGS CARRIED OUT AND THE AIRCRAFT RETURNE	D TO SERVICE.  THERE ARE SEVERAL OTHER INSTANCES INVOLVING FAILURE OF THESE RELAYS, WITH SIMILAR SNAG CIRCUMSTANCES.  A 	SUGGESTION TO PLACE THESE COMPONENTS ON A HARD TIME INTERVAL IN LIEU OF, ON-CONDITION FOR OTHER OPERATORS WOULD BE BENEF	ICIAL.  WE ARE CURRENTLY RESEARCHING THE TIME BETWEEN FAILURE, AS THESE ARE NOT NORMALLY TIME TRACKED.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004032500069	20040325	00069	NM  	2004	3	25	CA040112001      	1	20040109	G	5610	80260008	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING A FLIGHT THE RT COCKPIT WINDSHIELD CRACKED, ZERO VISIBILITY AND AN EMERGENCY LANDING WAS CARRIED OUT. MAINT	ENANCE TECH'S CHANGED WINDOW AND A/C RETURNED TO SERVICE. A/C JUST CAME OUT OF 'C' CHECK, IS MODSUM 4Q5300002 COMPLETED,	 WHICH REMOVES BOTH WINDSHIELDS FOR RE-SEALING. BELIEVE THAT THE WINDOW WAS DAMAGED DURING THE REMOVAL PROCESS.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004032500071	20040325	00071	NM  	2004	3	25	CA040112003      	1	20040109	G	3242		BRAKE PADS      			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	DAMAGED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, CREW REPORTED THAT THERE WAS SOME DRAGGING FELT WHEN THE BRAKES WERE APPLIED. THE AIRCRAFT RETURNED T	O THE BLOCKS. A DETAILED INSPECTION WAS CARRIED OUT AND NR 4 BRAKE WAS FOUND UNSERVICEABLE. THE BRAKE PADS WERE DAMAGED 	AND BROKEN.  A SERVICEABLE BRAKE WAS INSTALLED IAW MM 32-41-31 AND CHECKED SERVICEABLE.  THERE WAS NO PROBLEM DURING SUB	SEQUENT FLIGHT.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004032500090	20040325	00090	NE  	2004	3	25	CA040112004      	2	20040112	G	8500		ENGINE          			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	RIGHT	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE PILOT NOTICED THE RT ENGINE OIL TEMPERATURE WAS INCREASING SIGNIFICANTLY. THE ENGINE WAS SHUT DOW	N AND FLIGHT CARRIED OUT WITHOUT INCIDENT.					2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603
2004032500091	20040325	00091	SO  	2004	3	25	CA040112005      	1	20040111	G	3230	4204200	ARM             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER TAKE-OFF, CREW SELECTED LANDING GEAR UP. RT MAIN LANDING GEAR STILL INDICATED DOWN AND LOCKED AFTER RETRACTI	ON. CREWS SELECTED GEAR DOWN AND ALL GEAR INDICATED DOWN AND LOCKED. AIRCRAFT RETURNED TO BASE WITH NO FURTHER FAULTS NO	TED BY CREW. VISUAL INSPECTION OF LANDING GEAR SYSTEM CARRIED OUT. FOUND RT MAIN LANDING GEAR RETRACTION ARM P/N 42042-0	0 BROKEN. THIS PART ORIGINAL CRACK LOCATION NOT POSSIBLE TO BE INSPECTED OR FOUND WITH OUT COMPLETE DISMANTLE OF RETRACT	ION SYSTEM. RETRACTION ACTUATOR ROD END P/N 762-554 ALSO DAMAGED.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004032500092	20040325	00092	GL  	2004	3	25	CA040112006      	1	20040107	G	2752		SEAL            	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED FLAP STUCK IN LANDING POSITION, OVERSPED FLAPS 100 KTS FOR 5 MIN,FLAP INDICATOR U/S.  UPON INSPECTI	ON IT WAS FOUND THAT SPLINED RUBBER SEAL PUSHED OUT OF POSITION ON FLAP ACTUATOR ROD ASSY. SPLINED RUBBER SEAL INTERFERE	D WITH FLAP POSITION SWITCHES. RE-INSTALLED SPLINED RUBBER SEAL WITH EPOXY AND ALLOWED TO CURE. FLAP SYSTEM FUNCTION TES	TED, FLAP POSITION LIGHTS AND FLAPS SERVICEABLE. FLAPS INSPECTED FOR OVER SPEED DAMAGE NONE FOUND. AC RELEASED.  IT APPE	ARED THAT THE SPLINES WERE USED TO KEEP THE SEAL IN PLACED BUT AS THERE IS LITTLE LUBRICATION REQUIRED ON THE FLAP ACTUA	TOR SHAFT, FRICTION OF THE SHAFT ON THE SEAL, PULLS THE SEAL OUT OF POSITION AND DRAGS IT ALONG INTO THE SWITCHES.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004032500093	20040325	00093	EU  	2004	3	25	CA040113001      	1	20040113	G	3234	210TS07Y01	SELECTOR        			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					MLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SELECTED GEAR DOWN AND NOTHING HAPPENED FOR AT LEAST A MINUTE, THEN WIGGLED HANDLE THEN THE GEAR CAME DOWN.  NOTE:	  AC SENT TO HANGAR FOR TROUBLE/SHOOTING.					2	L	7	4 	4F	4	F	RT	A197    	E37NE
2004032500094	20040325	00094	NM  	2004	3	25	CA040113002      	1	20040113	G	2824	MA20A10011	ACTUATOR        			BOEING	767   	767209      	1385127	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					CROSSFEED VALVE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ON PRE-DESCENT CHECK WHEN FUEL CROSSFEED WAS CHECKED ON AND OFF, EICAS MESSAGE FUEL CROSSFEED AND VALVE LIGHT ON C	ROSSFEED SWITCH REMAINED ILLUMINATED.  ON GROUND RECYCLED CIRCUIT BREAKER NIL FIX. TAKEN OFF LINE FOR INVESTIGATION FLT 	CANCLED PART: ELECTRIC ACTUATOR REPLACED IAW AMM 28-22-12.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004032500096	20040325	00096	NM  	2004	3	25	CA040113004      	1	20040113	G	5610	141T480150	WINDSHIELD      			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			36170								(CAN) WHILE IN FLT ENROUTE FROM YYZ TO TLV, R1 WINDSHIELD OUTER PANE SHATTERED.  FLT CONTINUED WITHOUT FURTHER INCIDENT.	 MTCE POOLED A WINDOW AND CHANGED.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE
2004032500097	20040325	00097	EU  	2004	3	25	CA040113005      	1	20040113	G	3230	D31AAB4431	SAFETY VALVE    			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, GEAR DID NOT EXTEND NORMALLY ON FIRST ATTEMPT, SECOND ATTEMPT HAD SAME RESULT. CREW ELECTED TO CARRY 	OUT GO AROUND. LANDING GEAR CONTROL LEVER REPLACED AND TESTED IAW MM 32-31-11-400, MLG ISOLATION SAFETY VALVE (85GA) REP	LACED IAW MM 32-31-17. MLG. EXTENDED AND RETRACTED SEVERAL TIMES IAW MM 32-31-00-710-801, CHKD. SERV. REMOVE UNI 32-30-0	482C1024AC 001 FISOS: NINSTALLUNI 32-30-0482 FTN 1341Q9 AC 001REMOVE UNI 32-30-0513 FTN 5Y25Z5 AC FI  SOS: N INSTALL UNI	 32-30-0513FTN 55656R AC.		2	L	7	4 	4F	4	F	RT	A197    	E37NE
2004032500098	20040325	00098	SW  	2004	3	25	CA040113006      	1	20040107	G	6710	AN17415	BOLT            	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					DAMPER ARM	SHEARED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) HELISKI OPERATION. PILOT REPORTED BAD VIBRATION IN TURNS AND CONTROLLABILITY CONCERNS, ALSO IN TURNS. RETURNED TO 	BASE IMMEDIATELY. SHEARED BOLT FOUND WHERE MAIN ROTOR HYDRAULIC DAMPER CONTROL ARM ATTACHES TO STABILIZER BAR CONTROL TU	BE ROD END. BOLT WAS CORRODED WITH EVIDENCE OF BEING LOOSE. ALSO BLACK ON NUT AND WASHER. NO OTHER DAMAGE FOUND. ATTACHM	ENT HARDWARE REPLACED WITH NEW AND AIRCRAFT RETURNED TO SERVICE.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004032500120	20040325	00120	NM  	2004	3	25	CA040113007      	1	20040111	G	5755	65982962	HINGE           			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					SPOILER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			61773								(CAN) DURING SERVICE CHECK, FOUR CRACKS WERE FOUND ON THE NR 7 GROUND SPOILER SUPPORT HINGE.  HINGE REPLACED WITH NEW PA	RT.  ALL HINGES INSPECTED FOR CRACKS, NO FAULTS FOUND.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004032500126	20040325	00126	EU  	2004	3	25	CA040113008      	1	20040108	G	3310	2527	LAMP            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	MAP LIGHT	INOPERATIVE     	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, COCKPIT ROOF MOUNTED MAP LIGHT FAILED, C/B ACTIVATED, CREW NOTICED A SLIGHT ODOR. DURING TROUBLESHO	OTING THE ROOF PANEL WAS REMOVED AND IT WAS DISCOVERED THAT THE LAMP TERMINAL HAD BEEN IN CONTACT WITH AIRFRAME STRUCTUR	E CAUSING THE RUBBER PROTECTIVE BOOT ON THE TERMINALS TO WEAR THROUGH AND GROUND ELECTRICAL SUPPLY.  IT WAS ESTABLISHED 	THAT DURING COMPLETION AT A THIRD PARTY COMPLETION CENTER SPACER RINGS UNDER THE LAMP COLLAR HAD BEEN OMITTED.  FLEET RE	VIEW FOUND THAT SISTER AIRCRAFT WAS IN SAME CONDITION, BUT AN OTHER HAD SPACERS INSTALLED. SPACERS OBTAINED AND INSTALLE	D ON AFFECTED AIRCRAFT.	1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE
2004032500127	20040325	00127	NM  	2004	3	25	CA040113009      	1	20040107	G	2910	82970009121	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, CREW REPORTED NR 2 HYDRAULIC SYSTEM WENT LOW.   NR 2 ISO VALVE LIGHT AND OB ROLL SPOILER CAUTION LIGH	TS CAME ON, WHEN MAIN LANDING GEAR SELECTED DOWN.  AFTER LANDING DOWN DOORS STAYED OPEN AND FLUID LEAKING FROM LT WHEEL 	WELL.  MAINTENANCE FOUND HYDRAULIC LINE FOR NR 2 SYSTEM MLG UP PRESSURE TO BE LEAKING FROM PIN HOLES.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004042900096	20040429	00096	EA  	2004	4	29	CA040113010      	2	20040108	G	7414	10400554	SEAL            			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O320  	O320C1A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	MAGNETO	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						BL6006441					(CAN) ENGINE OIL IN RT MAGNETO SEAL P/N 10-400554 LIP WORN FLAT.  SLEEVE P/N 10-357078 APPEARS TO BE OF SINTERED IRON NO	T STEEL AS SINTERED IRON AND SINTERED BRASS SLEEVES WERE OBSOLETED MANY YEARS AGO. FIVE NEW SLEEVES IN STOCK ALSO APPEAR	 TO BE SINTERED IRON.  NOTE: SEAL IN LT HAND MAGNETO WAS NOT LEAKING BUT WAS WORN FLAT:  DOES THE ENGINE OIL WEEP THRU T	HE NEW SINTERED BUSHING SLEEVES?   IS THERE TOO MUCH TENSION ON THE OIL SEAL GARTER SPRING CAUSING PREMATURE WEAR.  OR I	S THE SINTERED IRON THE CULPRIT CAUSING EARLY SEAL WEAR?		1	H	7	1 	3O	3	O	 	A780    	E274	5	N	P88614
2004032500137	20040325	00137	GL  	2004	3	25	CA040114002      	1	20040111	G	2752		SEAL            	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED FLAP STUCK IN LANDING POSITION, UPON INSPECTION IT WAS FOUND THAT THE SPLINED RUBBER SEAL PUSHED OU	T OF POSITION ON FLAP ACTUATOR ROD ASSY.  SPLINED RUBBER SEAL INTERFERED WITH FLAP POSITION MICRO SWITCHES. RE-INSTALLED	 SPLINED RUBBER SEAL WITH EPOXY AND ALLOWED TO CURE.  FLAP SYSTEM FUNCTION TESTED, FLAP POSITION LIGHTS AND FLAPS SERVIC	EABLE.  IT APPEARED THAT THE SPLINES WERE USED TO KEEP THE SEAL IN PLACED BUT AS THERE IS LITTLE LUBRICATION REQUIRED ON	 THE FLAP ACTUATOR SHAFT,  FRICTION OF THE SHAFT ON THE SEAL,  PULLS THE SEAL OUT OF POSITION AND DRAGS IT ALONG WITH IT	 INTO THE SWITCHES.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004050300245	20040503	00245	GL  	2004	5	3	CA040114003      	2	20040105	G	7323	8575472	LOCK GEAR       								ALLSN 	501D  	501D13      	03004	GL  					SSC	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SPEED SENSITIVE CONTROL (SSC) RECEIVED FROM CHANNEL EXPRESS AS A TYPE-CERTIFICATED COMPONENT.  STANDARD AERO LIMIT	ED (SAL) ASSUMED OWNERSHIP OF SSC, AND PLACED UNIT INTO SAL REPAIRABLE STOCK.  SSC RECENTLY REMOVED FROM SAL STOCK TO BE	 OVERHAULED AND INSTALLED ON A 501-D13 ENGINE.  TECHNICIAN NOTED P/N 8575472, A NON TYPE-CERTIFICATED MILITARY COMPONENT	, WAS EMBODIED IN THE SSC.								4	T			E282
2004032500138	20040325	00138	CE  	2004	3	25	CA040114004      	1	20040107	G	7722	3031566	BUSS BAR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	UNSERVICEABLE   	W				O				OTHER                   				P			NO WARNING INDICATION     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOTS WERE CARRYING OUT AN ENGINE START ON THE RT ENGINE AND NOTICED THAT THERE WAS NO ITT INDICATION SO THE ENGI	NE WAS SHUT DOWN.  MAINTENANCE TROUBLESHOOTING DETERMINED THE ITT HARNESS WAS SERVICEABLE BUT THAT THE ENGINE INTERNAL B	USSBAR HAD FAILED. THE ENGINE WAS SPLIT AT THE C FLANGE AND THE BUSS BAR WAS FOUND SEPARATED FROM THE TOP OF THE JUNCTIO	N BLOCK. THE BUSS BAR P/N 3031566 WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004032500139	20040325	00139		2004	3	25	CA040114005      	4	20040112	G	2297	BACC47DJ1DJ2	PIN             	ROSEMOUNT   		BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					RELAY	MISMANUFACTURED 	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA						A44369					(CAN) UPON ROTATION, TAT PROBE EICAS MESSAGE FOLLOWED BY AUTO THROTTLE DISCONNECT, AND ASSOCIATED WARNINGS.  AIR TURN BA	CK. TAT PROBE REPLACED. GROUND TEST GOOD.  DEFECT RECURRED ON NEXT TAKEOFF.K143 AND K203 AIR/GND RELAYS REPLACED. TESTED	 GOOD IAW MM 30-33-00-501.  NO FAULTS ON RETURN FLIGHT TO YVR.  REVIEW OF THE RECORDS SHOWED 4 REPORTS SINCE 4TH DECEMBE	R 2003.  DUE TO THE INTERMITTENT NATURE OF THIS DEFECT, AS A PRECAUTIONARY MEASURE WIRING CHECKS WERE PERFORMED ON RETUR	N TO YVR. A POOR CRIMP AT THE BASE OF RELAY K203 PIN B2 WAS FOUND. PIN REPLACED.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2004032900059	20040329	00059	NM  	2004	3	29	CA040115001      	1	20040110	G	3230	54C546349	SOLENOID VALVE  			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF AND THE GEAR UP SELECTION THE AIRCRAFT EXPERIENCED A COMPLETE LOSS OF ALL FLUID FROM THE NR2 HYDRAU	LIC SYSTEM.  ALTERNATE LANDING GEAR EXTENSION PREFORMED AND AIRCRAFT RETURNED SAFELY TO BASE.  FINDINGS, LT MLG SOLENOID	 SEQUENCE VALVE FAILED.  SOLENOID SEPARATED FROM VALVE. TWO BOLTS OF FOUR, WHICH CONNECT SOLENOID HOUSING, HAD BROKEN.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080400211	20040804	00211	WP  	2004	8	4	CA040115002      	2	20040113	G	7230	310166812	PLENUM          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54276			(CAN) FLIGHT CREW RECEIVED SPLIT SECOND FIRE WARNING INDICATION ON LT ENG. DUE TO BRIEF NATURE OF IND FLIGHT CREW MONITO	RED GAUGES, DETERMINED FALSE INDICATION. SHORTLY AFTER ENG STARTED LOSING PWR UNTIL IT REACHED ABOUT 55 PERCENT TORQUE. 	 UPON INSP, LT ENG PLENUM DRAIN FIT WAS FOUND CRACKED, PARTIALLY SEPARATED FROM ENG PLENUM IN REARWARD DIRECTION. ALLOWE	D HOT COMBUST GASES INTO ENG COMPART.  PLENUM DRAIN FITTING IS WELDED TO ENG PLENUM.  INSP REVEALED MINOR FIRE DAMAGE TO	 ENG WIRING HARNESS, SURROUNDING AREA. REASON FOR CRACKED FITTING WAS DETERMINED TO BE DRAIN TUBE ATTACHED TO FITTING WA	S INSTALLED IN SUCH WAY IT WAS PUTTING A REARWARD LOAD ON DRAIN FITTING, CAUSING IT TO CRACK AND BREAK AWAY FROM PLENUM.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2004032900060	20040329	00060	NM  	2004	3	29	CA040115003      	1	20040112	G	4920	38007021	APU             			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					APU BAY	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) ON ARRIVAL TO THE GATE, GROUND POWER WAS PLUGGED IN, SMOKE IN THE FLIGHT DECK AND CABIN WHEN APU BLEED AIR AND PNE	UMATICS SELECTED 'ON'. CAPTAIN THEN SELECTED APU ELECTRICAL 'ON' AND F/O CONTACTED GROUND CONTROL TO REQUEST CFR.  SMOKE	 CLEARED AND MAINTENANCE WAS CALLED TO AIRCRAFT. SUSPECT DE-ICE FLUID IN THE APU INLET AS A RESULT OF DE-ICING OUT OF YO	W. APU MEL'D AND GROUND CHECKED SERVICEABLE.  ON NEXT RUN, APU MEL CLEARED FOLLOWING FLIGHT MONITORING AND MAINTENANCE P	ERFORMANCE RUNS.   AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004032900072	20040329	00072		2004	3	29	CA040115005      	4	20040101	G	2562		G SWITCH        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						55130					(CAN) ELT HAS HAD A PREVIOUS HISTORY OF SELF ACTIVATIONS (1 PREVIOUS, ELT ACTIVATED WHILE THE AIRCRAFT WAS INACTIVE).  E	LT WAS RECERTIFIED AND ON INSTALLATION THE UNIT SELF ACTIVATED.  REPAIR SHOP NOTED THAT THE G SWITCH ON THIS MODEL WAS V	ERY SUSCEPTIBLE TO MOISTURE RELATED FAILURES.  DUE TO AGE THERE ARE NO PARTS AVAILABLE FOR REPAIR, THE UNIT WILL BE SCRA	PPED.			1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004032900102	20040329	00102	EU  	2004	3	29	CA040116001      	1	20040116	G	5270		WARNING SYSTEM  			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					CARGO DOOR	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) IN CLIMB OUT OF 17T ECAM MSG DOOR AFT CARGO. PRESSURISATION NORMAL. MSG DISAPPEARED IN CRUISE 10 MIN. LATER. (SEE 	COMMENTS FOR TROUBLESHOOTING. FOR TROUBLESHOOTING, CARRY OUT TSM FAULT ISOLATION TASK NR 32-31-00-810-831 AND 32-31-00-8	10-833.  SENSOR 34WV GAP WITHIN TOLERANCE.  SENSOR 32WV RESISTANCE ONLY 11 OHMS BETWEEN PINS A AND B. (SHOULD BE 13) SEN	SOR 32WV REPLACED IAW AMM 52-71-12. CHECKED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004032900103	20040329	00103	EA  	2004	3	29	CA040116003      	1	20040116	G	2760	270007	PCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					SPOILERS	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REPEAT OF L1411710 UPON RT ENG START WITH HYD PUMPS IN AUTO RT FLT SPOILER HAS UNCOMMANDED DEPLOYMENT TO 50 DEG SL	OWLY AND THEN RETRACTS TO ZERO . SPOILERS DO NOT OPERATE DURING THIS OCCURANCE REGARDLESS OF FLT SPOILER LEVER POSN. UNT	IL RT SPOILER REACHES 0 DEG SECU'S INTERROGATED AND BOTH, NR 1 AND NR 2 FAULT LOG SHOWS CODE 82 (THROTTLE SWITCH). THROT	TLE QUADRANT REPLACED IAW MM., TASK 76-10-00-720-801, CUTOUT, NO FAULTS.  ACFT. SERVICEABLE. TH. QUADRANT REMOVED: FTN N	R  X21X8B INSTALLED: FTN NR JW4J0A.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004033000119	20040330	00119	NE  	2004	3	30	CA040116004      	2	20040113	G	7230		COMPRESSOR WHEEL			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) FOLLOWING UNEVENTFUL LANDING AND ROLL-OUT, CREW NOTED VIBRATION AND RISING ITT. ENGINE WAS SECURED. POST FLIGHT EX	AMINATION SHOWED THAT ROTOR 1 OF THE HPC HAD .3333 OF ONE AIRFOIL MISSING.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
2004033000125	20040330	00125	NM  	2004	3	30	CA040116005      	1	20040104	G	2910	DSC3461	LINE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYDRAULIC SYS	RUPTURED        	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ENGINE START NR 2 HYD CAUTION LIGHT ILLUMINATED, NR 2 QUANTITY NOTED TO BE DECREASING. A/C SHUT DOWN.  LARGE	 HYDRAULIC LEAK FROM NR 2 ENGINE NOTED.  FOUND PRESSURE LINE P/N DSC346-1 RUPTURED IN THE FLEXIBLE SECTION.  LINE REPLAC	ED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004033000126	20040330	00126	CE  	2004	3	30	CA040116006      	1	20040116	G	3242		PIN             			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	BRAKE LINKAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13232								(CAN) DURING GROUND HANDLING THE RT RUDDER PEDAL BRAKE ASSY SEEMED SLOPPY COMPARED TO THE LT UNIT.  INVESTIGATION REVEAL	ED THAT THE PIN THAT CONNECTS THE BRAKE PEDAL TO THE MASTER CYLINDER WAS ALMOST COMPLETELY WORN THROUGH, THIS IS A HOLLO	W SHAFT PIN ASSY.  WORN PARTS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
2004033000127	20040330	00127	NE  	2004	3	30	CA040117001      	1	20040115	G	6320		WARNING LIGHT   			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					GEARBOX OIL	ILLUMINATED     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			24309								(CAN) AT 5500 FT VFR ENROUTE TO THE PLATFORM, JUST NEARING THE COASTLINE, THE MASTER CAUTION AND INTERMEDIATE GEARBOX CH	IP LIGHT ILLUMINATED.					2	G	7	2 	4U	4	U	 	1H15    	1E3
2004033000128	20040330	00128	EA  	2004	3	30	CA040118001      	1	20040107	G	3397	2LA006913	WIRE            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					FLOOD LIGHT	BURNED          	W				O				OTHER                   				A			FLAME/FIRE                			AP	APPROACH       	1			CA											(CAN) THE COPILOT REPORTED FWD FLOOD LIGHT WIRES CAUGHT FIRE. CAPTAIN REPORTED THAT FO PINCHED WIRE WITH FINGERS TO EXTI	NGUISH FLAMES. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE FI FWD FLOOD LIGHT ASSEMBLY WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004033000129	20040330	00129	EA  	2004	3	30	CA040118002      	1	20040113	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) RT WINDSHIELD CRACKED OUTER PLY ON CLIMBOUT.  REPLACED RIGHT WINDSHIELD IAW MM 56-00-00.  THE WINDSHIELD IS POST S	B.					2	L	7	2 	4F			RT	A21EA
2004033000130	20040330	00130	CE  	2004	3	30	CA040119001      	1	20040115	G	3260	404EN16	SWITCH          			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	FAULTY          	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF PILOT SELECTED THE GEAR HANDLE TO THE UP POSITION.  THE GEAR WOULD NOT RETRACT.  AIRCRAFT RETURN TO	 MAINTENANCE BASE.  MAINTENANCE TECH  FOUND RT TRUNNION SWITCH AT FAULT.  SWITCH REPLACED AND LANDING GEAR SYSTEM SWUNG.	 AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4F	4	F	 	A10CE   	E6WE
2004033000131	20040330	00131	CE  	2004	3	30	CA040119002      	1	20040116	G	2121	11438002811	BLOWER          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	AFT VENT	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, CREW NOTED AN ELECTRICAL ODOR AND TRACE OF SMOKE IN CABIN.  AIRCRAFT RETURNED TO AIRPORT WITHOUT FUR	THER INCIDENT.  MAINT FOUND THE AFT VENT BLOWER HAD OVERHEATED DUE TO ONE OF THE BEARING RESISTING ROTATION. THE NORMAL 	TEMPERATURE FUSE THAT IS SUPPOSED TO BLOW, DISCONTINUING POWER TO THE UNIT DID NOT APPEAR TO OPEN PRIOR TO BOTH SPEED RE	SISTORS BECOMING BADLY HEATED AND DISTORTED. THE RESISTORS AND TEMP FUSE ARE CONTAINED INSIDE A METAL CONTAINER MOUNTED 	ON THE SIDE OF THE BLOWER.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004033000145	20040330	00145	NM  	2004	3	30	CA040119003      	1	20040117	G	3810	24E507009G03	WATER HEATER    			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					LAVATORY	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) BURNING ELECTRICAL ODOR NOTICED IN LAVATORY D.   WHEN ODOR BECAME STRONGER, FLIGHT DIVERTED, DECLARING AN EMERGENC	Y, FOUND TO BE THE WATER HEATER AT FAULT HEATER DE-ACTIVATED, UNDER MEL.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004033000151	20040330	00151	NE  	2004	3	30	CA040119004      	2	20040112	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								807608			(CAN) AIRCRAFT HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT.  WHILE IN CRUISE, THE FLIGHT CREW FELT VIBRATI	ON AND NR 2 ENGINE VIBRATION WAS FLUCTUATING BUT WAS WITHIN LIMITS. AFTER A FEW SECONDS, OIL PRESSURE DROPED TO ZERO. TH	E CREW FOLLOWED THE QRH, AN EMERGENCY WAS DECLARED, NR 2 ENGINE WAS SHUT DOWN, AIRCRAFT DIVERTED AND LANDED WITHOUT FURT	HER INCIDENT. ENGINE REMOVED AND REPLACED. AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004033000152	20040330	00152	NM  	2004	3	30	CA040120001      	1	20040120	G	5610	141T480150	WINDSHIELD      			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					COCKPIT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE IN FLIGHT, R1 WINDSHIELD OUTER PANE SHATTERED. (FL370)  R1 WINDOW REPLACED IAW AMM 56-11-01 REMOVED: UNI 56-	10-0174 MPN: 141T4801-50 INSTALLED: UNI 56-10-0174 MPN: 141T4801-50					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE
2004033000153	20040330	00153	WP  	2004	3	30	CA040120002      	1	20040119	G	6322	C1861	HUB             	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CONING FLANGE	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						LOT102A					(CAN) OTHER PART AFFECTED LOWER BEARING C181-3 S/N 1328 UPON REMOVING FAN ASSY FOR ACCESS TO A DEFECTIVE ACTUATOR C051-1	, DAMAGE (FRETTING AND GALLING) WAS DISCOVERED ON BOTH MATING FLANGE OF FAN HUB C186-1 (PART OF D174-2 ASSY) AND LOWER B	EARING C181-3. NO PREVIOUS SIGN OF MOVEMENT WERE NOTED PRIOR TO DISMANTLING FAN ASSY. FAN WAS NEVER REMOVED AFTER IT LEF	T FACTORY. FAN HAD BEEN BALANCED ONCE SINCE NEW. FAN HAS BEEN SPLIT APART FOR INVESTIGATION AND A LARGE AMOUNT OF METAL 	PARTICLES WERE DISCOVERED BETWEEN BACK PLATE AND FAN AND ALSO SOME EXTENSIVE CORROSION BETWEEN SHIM C178-2 FLANGES, HUB 	MATING SURFACE AND FAN ITSELF. PART REMOVED AND RETURNED FOR REPAIR AND FURTHER INVESTIGATION.	1	G	7	1 	3O	3	O	 	H11NM   	E295
2004071200199	20040712	00199	EU  	2004	7	12	CA040120003      	1	20040118	G	3246	300677	WHEEL           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	NLG	DAMAGED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) THE AIRCRAFT ABORTED THE TAKE OFF DUE TO A FLAT NOSE TIRE.  THE WHEEL ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETUR	NED TO SERVICE.  THE WHEEL REMOVED WAS FOUND TO HAVE BEEN PUNCTURED BY THE TOW BAR.					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE
2004033000154	20040330	00154	NE  	2004	3	30	CA040120004      	3	20040120	G	6114	52590	THRUST WASHER   			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	AWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	PROPELLER	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER REMOVED FOR AD 81-13-06R2, CF 83-16 CORROSION INSPECTION. EVIDENCE OF CORROSION WAS NOT FOUND BUT EXTENS	IVE PITTING / GALLING WAS DISCOVERED ON A BEVELED THRUST WASHER P/N 52590 AND FLAT WASHER P/N 57525 AS IDENTIFIED IN HAM	ILTON STANDARD BLADE OVERHAUL MANUAL NO. 130B, PAGE 424. PROPELLER TO BE SENT FOR REPAIR AND OVERHAUL ASSESSMENT.				2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871
2004033000155	20040330	00155	NE  	2004	3	30	CA040120005      	2	20040120	G	7200		ENGINE          			BOEING	767   	76735H      	1385208	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					LEFT	FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI OUT LT ENGINE FLAMED OUT, WITH OIL ODOR IN THE CABIN. RETURNED TO GATE, AIRCRAFT CHANGED, ENGINE REPLACED 	IAW 71-00-02 CONF.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2004033000156	20040330	00156	EU  	2004	3	30	CA040120006      	1	20040120	G	5610	NP1752321	WINDSHIELD      			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			14463								(CAN) AFTER TAKE OFF, CLIMBING THROUGH 10000 FT, THE CAPTS SLIDING WINDOW SHATERED.  CREW ELECTED TO RETURN TO CDG AND L	ANDED APPROX 35000 KG OVER MLW. CAPTS SIDE WINDOW CHANGED IAW 56-12-11. PARTS: SLIDE WINDOW MPN NR NP175232-1 INSTALLED.	  OUTER STRUCTURAL PANE WAS SHATERED ON CAPTS SLIDING WINDOW  (NO) DAMAGED REPORTED ON STRUCTURE.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2004033000157	20040330	00157	CE  	2004	3	30	CA040120007      	1	20040118	G	2435	M230881320	BRUSHES         	LUCAS       		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						98048					(CAN) DURING FLEET WIDE INSPECTION OF PREMATURE BRUSH WEAR. THIS UNIT FOUND TO HAVE EXCESSIVE WEAR. 149.4 SINCE  TBO.618	 HRS OF BRUSH WEAR REMAINING.  TBO 1500 HRS. VENDOR IN CONTACT WITH BRUSH MANUFACTURER.  OTHER OPERATORS FINDING SIMILAR	 SDR ALERT WOULD SPEED RECTIFICATION PROCESS.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004033000158	20040330	00158	NM  	2004	3	30	CA040120008      	1	20040120	G	5511	65174392	RIB             			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			46421								(CAN) DURING C CHECK,THE INSPECTION OF THE HORIZONTAL STABILIZER, REVEALED A CRACK ON THE ELEVATOR HINGE SUPPORT RIB ON 	THE RT SIDE AT STATION 136.5.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004033000168	20040330	00168	NM  	2004	3	30	CA040120009      	1	20040120	G	5510	6524189	BLOCK           			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					HORIZONTAL STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			46421								(CAN) DURING C CHECK, ONE RUB BLOCK (P/N 69-31604-4) WAS FOUND LOOSE ON THE LOWER BEAM. AFTER REMOVAL OF THE BLOCK, IT W	AS FOUND THAT THE LOWER BEAM WAS WORN OUT OF LIMIT AT THE PLACE WHERE THE RUB BLOCK WAS INSTALLED. THE LOWER BEAM HAS TO	 BE REPLACED.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004033000179	20040330	00179	NM  	2004	3	30	CA040121001      	1	20040119	G	7711	10607371	TRANSMITTER     			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					ENGINE EPR	FAILED          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, IT WAS OBSERVED THAT THE NR 1 ENGINE EPR HAD NO INDICATION.  THE AIRCRAFT WAS RETURNED TO THE RAMP.  	AFTER SOME TROUBLESHOOTING, MEL 77-01-01 WAS RAISED.  THIS IS A 3 FLIGHT DAY, A CAT, MEL.  THE  AIRCRAFT WAS DISPATCHED.	ON RETURN TO HOME BASE, THE EPR TRANSMITTER WAS REPLACED AND CHECKED SERVICEABLE AND NO FURTHER PROBLEM DURING SUBSEQUEN	T FLIGHT.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004092000061	20040920	00061	EU  	2004	9	20	CA040121002      	1	20040119	G	5620		WINDOW          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	CABIN	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) AC WAS IN LEVEL FLIGHT AT FL190.  CABIN ALTITUDE WAS 5500 FT, NEAR MAX DIFFERENTIAL OF ABOUT 5.5 PSID.  SLIGHT THU	D WAS HEARD FROM PASSENGER COMPARTMENT.  NO DECREASE IN PRESSURIZATION OR ANY OTHER WARNINGS. FLIGHT CONTINUED WITH NO P	ROBLEMS.  PASSENGER SEATED IN EMERGENCY EXIT SEAT REPORTED THAT HIS WINDOW HAD CRACKED IN MID FLIGHT. ON EXAMINATION BY 	MAINT, OUTER PANE OF TWO PANE CABIN WINDOW HAD CRACKED FROM TOP TO BOTTOM ON A DIAGONAL.  CRACK APPEARS TO HAVE STARTED 	AT A CRAZE( 1.7 IN) IN CENTER OF OUTER PANE.  PORTION OF WINDOW WITH CRAZE WAS  THINNER THAN THE REST.  TWO PANE CONCEPT	 WORKED PERFECTLY, WITH INNER PANE TAKING  PRESSURIZATION LOAD W/O SIGNIFICANT PRESSURE LOSS.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL
2004033000180	20040330	00180	CE  	2004	3	30	CA040121003      	1	20040119	G	2752	66000863	ACTUATOR        			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					TE FLAP	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING PRE-FLIGHT INSPECTION FLUID LOSS WAS NOTED. FLAP ACTUATOR WAS FOUND TO HAVE A CRACKED BODY.						2	L	7	2 	4F	4	F	 	A10CE   	E6WE
2004033000181	20040330	00181	CE  	2004	3	30	CA040121004      	1	20040104	G	5610	1013840252	WINDSHIELD      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WINDOW SHATTERED IN CRUISE, INSIDE AND OUT SIDE PANE.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004033000182	20040330	00182	EU  	2004	3	30	CA040121005      	1	20040121	G	3246	32200022	BEARING         			AIRBUS	A321  	A321211     	3930370	EU  	IAE   	V2530 	V2530A5     	 	NE  					NLG WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT NOSE WHEEL SEPARATED FROM THE NLG SHOCK ABSORBER DURING TAXING IN, IT IS BELIEVED THAT THIS HAPPENED ON THE LAS	T TURN TO THE GATE.  THE AC HAS ACCUMULATED 4,747FH AND 1,813CY.   A FAILURE OF THE NOSE LANDING GEAR WHEEL BEARING (TFU	 32.41.12.006) IS SUSPECTED.				2	L	7	2 	4F	4	F	RT	A28NM   	E40NE
2004033000183	20040330	00183	GL  	2004	3	30	CA040122001      	3	20040121	G	6114	D1657	CYLINDER        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER HUB	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  PROPELLER CYLINDER FOUND DEFECTIVE.  MANUFACTURE DEFECT IN THE C AREA MISSING MATERIAL. THIS HAS BEEN SEEN IN SEV	ERAL OTHER CYLINDERS, MFG WAS CONTACTED ON ALL OF THE DEFECTIVE ASSEMBLIES. MFG INSPECTED AND ANALYZED THEM ALL AND HAS 	NOT PROVIDED ANY LIMITS FOR DAMAGES IN THE C AREA. ALL CYLINDERS HAVE BEEN WARRANTEED FOR REPLACEMENT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004033000184	20040330	00184	CE  	2004	3	30	CA040122002      	1	20040121	G	2750	14601008	CONTROL CABLE   			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION IT WAS DICOVERED THAT THESE CABLES (2EA. 1 LT AND 1 RT) WERE FRAYED WHERE THE CABLE BENDS AROUND	 THE FLAP CABLE QUADRANT LOCATED IN THE WING TRAILING EDGE.					1	H	7	2 	3O	3	O	 	A6CE    	E9CE	5	C	P5EA
2004033000185	20040330	00185	CE  	2004	3	30	CA040122003      	1	20040121	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION IT WAS DISCOVERED THAT THESE CABLES (2EA. 1 LEFT AND 1 RIGHT) WERE FRAYED WHERE THE CABLE BENDS 	AROUND THE FLAP CABLE QUADRANT LOCATED IN THE WING TRAILING EDGE.					1	H	7	2 	3O	3	O	 	A6CE    	E9CE	5	C	P5EA
2004040200003	20040402	00003	CE  	2004	4	2	CA040122004      	1	20040108	G	5210	1295140791	BRACKET         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12505								(CAN) DURING GROUND HANDLING, CREW ATTEMPTED TO OPEN DOOR FROM INSIDE AND THE MAIN HANDLE UPON APPLYING PRESSURE, RELEAS	ED WITHOUT ACTUATING DOOR CAMS. MAINTENANCE FOUND THAT THE MAIN DOOR ACTUATION BRACKETHAD BROKEN INTO TWO PIECES. THE BR	ACKET WAS REPLACED AND THE AIRCRAFT CONTINUED OPERATIONS.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004042900097	20040429	00097	NM  	2004	4	29	CA040122005      	1	20040122	G	2997	W2900086	WIRE            			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					LT PYLON	CHAFED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) FAULT: LT ENGINE HYD. ALT. CURRENT MOTOR DRIVEN PUMP (ACMP)POWER FEEDER WIRES FOUND CHAFFING AND ARCHING ON STRUT 	STRUCTURE. STRUC.  DAMAGE WAS ALSO NOTED DUE TO ARCHING.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2004042900098	20040429	00098	NM  	2004	4	29	CA040122006      	1	20040116	G	5630		WINDOW          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AIRSTAIR DOOR	CHAFED          	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, A PASSENGER NOTICED A SMALL AMOUNT OF SMOKE / FIRE COMING UP FROM THE FLOOR NEXT TO THE MAIN CABIN DO	OR AND POINTED IT OUT TO THE FLIGHT ATTENDANT WHO IMMEDIATELY NOTIFIED THE PILOTS. THE FIRE WAS APPROXIMATELY 1 INCH HIG	H AND WAS LOCATED AT THE MAIN CABIN DOOR HINGE ARM WHERE THE MAIN CABIN DOOR LIGHT WIRES COME OUT OF A CONDUIT. THE PILO	T GOT THE FIRE EXTINGUISHER FROM THE COCKPIT AND PUT OUT THE FIRE. THE PILOT THEN ORDER TO THE PASSENGERS TO EXIT OUT TH	E REAR AIRSTAIR DOOR. THE CIRCUIT BREAKER FOR THE AIRSTAIR DOOR LIGHTS DID NOT TRIP.  MFG IS INVESTIGATING THE EVENT.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004042900100	20040429	00100	SW  	2004	4	29	CA040123001      	1	20040123	G	5744	250000281	WEB             			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	LT IB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON AILERON INSPECTION, CRACK WAS FOUND UNDER LT IB HINGE.  CRACK IS AROUND LOWER OB HINGE MOUNTING HOLE.  ONE CRAC	K OUT OF FIVE AC CHECKED.					1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA
2004042900102	20040429	00102		2004	4	29	CA040123003      	4	20040114	G	3197		WIRE HARNESS    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CHAFED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH FLIGHT ON MULTIPLE OCCASIONS THE PILOTS EHSI SCREEN WOULD POWER DOWN AND RESTART UNCOMMANDED.  IN 	THE TROUBLESHOOTING PROCESS ALL REMOVABLE COMPONENTS WERE REPLACE WITH SERVICEABLE UNITS.  A VISUAL INSPECTION OF THE A/	C WIRING BY THE AVIONICS SHOP REVEALED CHAFED WIRING UNDER THE PILOTS SEAT IN THE OUTFLOW VALVE COMPARTMENT.  WIRING P/N	  REPAIRED 9C95A22, 9C94 A22, 9C3G20, 9C32A22, 3F14A22N,ITN5A24.  CHAFE PROTECTION INSTALLED ON THIS BUNDLE TO PREVENT F	UTURE SIMILAR HAPPENINGS.  SYSTEM TESTED SERVICEABLE AND LOG ENTRIES MADE.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004031500028	20040315	00028		2004	3	15	CA040123004      	4	20040114	G	3197		INSULATION      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ELECTRICAL WIRE	CHAFED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) DURING APPROACH FLIGHT ON MULTIPLE OCCASIONS THE PILOTS EHSI FAILED ON APPROACH , POWERED DOWN AND RE POWERED UNCO	MMANDED.  ON EACH OCCASION THE SYSTEM TESTED NORMAL AFTER LANDING AND DID NOT REOCCUR FOR DAYS. EACH COMPONENT IN THIS S	YSTEM WAS REPLACED WITH A SERVICEABLE UNIT WITH NO CHANGE. DURING INSP OF THE A/C WIRING CHAFED WIRING WAS DISCOVERED UN	DER THE COPILOTS SEAT IN THE OUTFLOW VALVE COMPARTMENT.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004042900103	20040429	00103		2004	4	29	CA040123005      	4	20040123	G	6122	4B2P8	GOVERNOR        																	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION OF THE GOVERNOR, THE FOLLOWING WERE NOTED,1) 52142, DRIVE GEAR, CORROSION ON TEETH PN 50659, IDLER	 GEAR, CORRODED TEETH  50794, BEVEL GEAR, WORN  51866, PILOT VALVE, CORRODED  59818, R.V.PISTON, CORRODED 51742, BASE, C	RACKED.THE ABOVE UNIT WAS ESTIMATED,FOR OVERHAUL, AND THE CUSTOMER ASKED US NOT TO PROCEED UNTIL ADVISED.
2004031500003	20040315	00003	EU  	2004	3	15	CA040123006      	1	20040105	G	2497	WIRE161	WIRE HARNESS    			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 GENERATOR	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			37287	37287							(CAN) DURING APPROACH WHEN ATTEMPTING TO START APU , LOST AC BUSS 1 AND ESSAC , NR 1 GENERATOR WOULD NOT RE-SET, AIRCRAF	T LANDED NORMALLY. MAINTENANCE INSPECTION FOUND CHAFING OF THE 'B' PHASE (YELLOW STRIPE) NR 1 ENGINE GENERATOR WIRING CH	AFED TO GROUND  AT THE LT TOP FWD COWL (WIRING BUNDLE CONTAINING FEEDER CABLE AND GEN CONTROL WIRING), ALSO FOUND CHAFIN	G OF THE NR 1 GENERATOR 'RED STRIPE' WIRING AT PYLON COVER.  NOTE: PREVIOUS SIMILAR EVENT ON THIS AIRCRAFT HAD BEEN BLAM	ED ON CONTAMINATION OF THE CONNECTOR (1XB-7R), PROBLEMS WERE SEVERAL DAYS APART.		2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004071900054	20040719	00054		2004	7	19	CA040123007      	4	20040123	G	6122	4030035	HOUSING         	WOODWARD    																GOVERNOR	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1046046U					(CAN) OIL LEAK AT THE LOWER ECCENTRIC PLATE RETENTION SCREW WAS CAUSED BY IMPROPER HELI COIL INSTALLATIION.  WHEN THE HE	LI COIL WAS INSTALLED, THE HOLE WAS DRILLED TO DEEP, AND BROKE THROUGH INTO THE RESET AND AIR BLEED ROD BORE CAUSING A L	EAK. THE ESTIMATE TO REPAIR THIS UNIT WAS GIVEN TO THE OWNER, AND WE WERE ADVISED NOT TO PROCEED WITH THE LEAK REPAIR ON	 THIS UNIT.
2004031500004	20040315	00004	SO  	2004	3	15	CA040123008      	1	20040120	G	1430	AN546	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	CORRODED        	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) THE AIRCRAFT WAS ON APPROACH WHEN THE CREW COULD NOT GET A DOWN AND LOCKED (GREEN) INDICATION ON THE RT MAIN GEAR.	 THE AIRCRAFT FLEW LOCALLY AND AFTER SEVERAL ATTEMPTS FLEW TO ANOTHER AIRPORT FOR A TOWER FLYBY AND LANDING.  UPON TOUCH	DOWN, THE RT MAIN GEAR LIGHT ILLUMINATED.  MAINTENANCE FOUND THE RT MAIN DOWN LOCK TO BE SLIGHTLY STIFF.  SOME MOISTURE 	AND SLIGHT CORROSION WAS NOTED ON THE PIVOT BOLT FOR THE RT DOWNLOCK AND THE BOLT WAS REPLACED.  BOTH MAIN DOWN LOCKS WE	RE REMOVED, CLEANED, INSPECTED, AND RE-LUBRICATED.  SUBSEQUENT GEAR SWINGS WERE NORMAL AND THE AIRCRAFT WAS RETURNED TO 	SERVICE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500005	20040315	00005	NE  	2004	3	15	CA040123009      	2	20040119	G	7412	103815504C	IGNITER BOX     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE IGNITION	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) THE PILOT MADE TWO ATTEMPTS TO START THE AIRCRAFT.  THE ENGINE FAILED TO START AND THE PILOT NOTED THAT THE IGNITI	ON LIGHT ON THE CAWS PANEL HAD NOT ILLUMINATED DURING EITHER ATTEMPT.  THE CAWS PANEL LIGHTS WERE TESTED AND FOUND SERVI	CEABLE.  AFTER APPROX. 5 MINUTES A THIRD STARTING SEQUENCE WAS INITIATED AND SUCCESSFUL. THE AIRCRAFT RETURNED TO BASE W	ITHOUT FURTHER INCIDENT.  MAINTENANCE CARRIED STARTED THE AIRCRAFT WITH NO INDICATION OF ANY DEFECT.  THE AIRCRAFT WAS S	HUT DOWN, AND FURTHER INVESTIGATION REVEALED THAT THE IGNITION EXCITER BOX WAS NOT FIRING IAW THE ENGINE MFG REQUIREMENT	S.  A REPLACEMENT UNIT WAS INSTALLED, AND TESTED SERVICEABLE.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004031500020	20040315	00020	SO  	2004	3	15	CA040125001      	1	20040122	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) THE FAILURE OF PUMP WAS FOUND BY PILOT AFTER FLIGHT HYDRAULIC PUMP CHECK- PUMP FAILED THE TEST. TIME EXCEEDED 11 S	ECONDS. PUMP REMOVED, INSPECTED - NO DAMAGE FOUND FAILED INTERNALLY.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500021	20040315	00021	EA  	2004	3	15	CA040126001      	1	20040126	G	3234	750006000	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG DOOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  GEAR DISAGREE ON UP SELECTION AFTER T/O.  NOISE IN FLT DECK CONFORMING NOSE GEAR NOT RETRACTED (INDICATED RED HAT	CHING ON EICAS CHECK- LIST CARRIED OUT GEAR INDICATED 3 GREEN AIRCRAFT RETURNED TO AIRPORT. DOOR SELECTOR VALVE REPLACED	 IAW AMM 32-22-15-400-801.  A/C SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500022	20040315	00022	CE  	2004	3	15	CA040126002      	1	20040122	G	7160	1019100209	HINGE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	INLET VANE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAINTENANCE INSPECTION DISCOVERED LT ENGINE INLET VANE HINGE PIN WAS WORKING OUT OF THE HINGE AND CONTACTING THE I	NNER COWL STRUCTURE.   MFG ADVISES THE HINGE ENDS ARE CRIMPED TO PREVENT PIN MOVEMENT, HOWEVER ON THIS ASSY THE PIN APPE	ARS TO HAVE WORN THROUGH THE CRIMP.   HINGE ASSEMBLY REPLACED NEW.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2004031500023	20040315	00023	NM  	2004	3	15	CA040126003      	1	20040114	G	2910	AN81510D	COUPLING        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PRESS MANIFOLD	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) APPROXIMATELY 90 DME FROM LANDING AT THE TOP OF DESCENT THE CREW NOTICED THE NR 2 HYD CONTENTS DROPPING.  AT APPRO	X 12 DME THE NR 2 HYD CAUTION LIGHT ILLUMINATED.  A PAN WAS CALLED AND QRH ACTIONS WERE CARRIED OUT.  ENGINEERING INVEST	IGATION REVEALED THAT THE NR 2 PRESSURE MANIFOLD INLET UNION HAD FRACTURED.  THE UNION WAS REPLACED ALONG WITH THE HYD P	UMP AND THE AIRCRAFT WAS RETURNED TO SERVICE.  OPERATOR HAS BEEN INFORMED OF SYD 8-29-002, WHICH REPLACES THE ALUMINUM F	ITTINGS WITH STAINLESS STEEL FITTINGS FOR THIS AREA.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500024	20040315	00024	EU  	2004	3	15	CA040126004      	1	20040126	G	3232	D3221401700062	UPLOCK          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NLG DOOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOSE LDG DOOR WOULD NOT CLOSE AFTER T/O.  RECYCLED 3 TIMES (NO SUCCESS)  DOOR CLOSED NORMALLY WITH GEAR DOWN.  NLG	 DOOR UPLOCK REPLACED IAW AMM32-31-21-400-001, CONSIDERED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004031500029	20040315	00029	CE  	2004	3	15	CA040126005      	1	20040126	G	2571	10112011613	FLANGE          			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	BATTERY COVER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION REVEALED THE BATTERY COVER SUPPORT FLANGE (FWD) CRACKED WHERE IT ATTACHES TO THE VERTICAL SUPPORT ANGLE	S.   PART TO BE REPLACED NEW.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004031500031	20040315	00031	EA  	2004	3	15	CA040126006      	1	20040126	G	2740	9960023	SWITCH          			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF343A1     	30015	NE  					STAB TRIM	DIRTY           	W				A				UNSCHED LANDING         				F	H		FLT CONT AFFECTED         	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			CA											(CAN) WENT TO DISCONNECT STAB CHANNEL 1, LOST BOTH STAB TRIM CHANNELS AND MACH TRIM.  TRIED TO ENGAGE EITHER STAB CHANNE	L WITHOUT SUCCESS.  ACTIONED QUICK RESPONSE PROCEDURE AND RETURNED TO AIRPORT USING FLAPS 20 IAW QRH.  GREATER THAN NORM	AL FORCE ELEVATOR FORCE WAS REQUIRED DURING APPROACH.  LANDED WITHOUT FURTHER INCIDENT. THE STAB TRIM DISCONNECT SWITCH 	WAS CLEANED AND SYSTEM RETESTED SERVICEABLE IAW FUNCTIONAL TEST PROCEDURE P601R4500 PARA 5.6.20, THEN A/C WAS RETURNED T	O FLIGHT WITHOUT ANY FURTHER OCCURENCES.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500032	20040315	00032	EU  	2004	3	15	CA040126007      	1	20040126	G	3251	Z4242170001	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV3BC      	EU  	NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI A STUDENT PILOT NOTICED THAT THE AIRCRAFT WOULD NOT STEER PROPERLY. MAINTENANCE NOTICED THAT THE RT ST	EERING SPRING WAS BROKEN. THIS HAS BEEN AN ON GOING PROBLEM WITH STUDENTS WHEN THEY TRY TO STEER THE AIRCRAFT WITHOUT GE	TTING THE AIRCRAFT ROLLING FIRST ADDING STRESS TO THE SPRINGS.				1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	USSR
2004031500033	20040315	00033	EA  	2004	3	15	CA040126008      	1	20040106	G	2720	272613	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RUDDER TRIM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) 30 MINS OUT, FL260 RUDDER TRIM FAILED, INADVERTENT AND SUDDEN DISPLACEMENT TO HALFWAY TO FULL NOSE LT. DECLARED EM	ERGENCY, UNEVENTFUL LANDING. RUDDER TRIM FAILED. REMOVED AND REPLACED RUDDER TRIM SWITCH.  OPS CHECKS REQUIRED WHEN PANE	L REINSTALLED IAW27-12-10, REMOVED AILERON/RUDDER TRIM CONTROL PANEL, REINSTALLED TRIM CONTROL PANEL AND TESTED IAW AMM 	27-12-00, CHECKS OK.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500034	20040315	00034	NM  	2004	3	15	CA040127001      	1	20040121	G	2720	682015	SWITCH          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RUDDER TRIM	INOPERATIVE     	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, THE FLIGHT CREW REPORTED RUDDER TRIM INOPERATIVE.  QRH PERFORMED. RETURNED TO DEPARTURE AIRPORT FO	R LANDING WITHOUT FURTHER INCIDENT. MECHANIC RESET THE RUDDER TRIM CB THEN TESTED TRIM, NO MOVEMENT. RUDDER TRIM PANEL R	EMOVED AND PANEL WAS (TAPPED) THEN RE-INSTALLED, THEN TRIM OPERATION WAS NORMAL. RUDDER TRIM SWITCH REPLACED AS PRECAUTI	ON.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004031500035	20040315	00035	EU  	2004	3	15	CA040127002      	1	20040126	G	3000	23053191	LEVER           			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ANTI ICE ACT	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED THAT THE INLET ANTI-ICE SYSTEM WAS UNSERVICEABLE. THE ANTI-ICE VALVE WOULD NOT TO CLOSE. THE CIRCUI	T BREAKER FOR THE SYSTEM ALSO TRIPPED. UPON INSPECTION MAINTENANCE FOUND THAT THE ANTI-ICE LEVER WAS CRACKED AND ELONGAT	ED WHERE IT ATTACHES TO THE ACTUATOR ALLOWING THE ANTI-ICE LEVER TO DISCONNECT FROM THE ACTUATOR. THE ACTUATOR WOULD RUN	 BUT NOT EXTEND OR RETRACT THE INLET ANTI-ICE VALVE.			1	G	7	2 	3U	3	U	 	H3EU    	E4CE
2004031500049	20040315	00049	EA  	2004	3	15	CA040127006      	1	20040127	G	2150	32156221	REGULATOR VALVE 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT & RT PACK	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT PACK HI PRESS. MESSAGE ON T/O, CHECKLIST COMPLETED. LT PACK CAME BACK MOMENTARILY. BOTH PACKS U/S WITH H	IGH PRESS. MSG. LT AND RT PRESSURE REGULATOR VALVES REPLACED, BOTH PACKS OPERATED AT T/O POWER, NO FAULT FOUND. CONS.SER	V.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500050	20040315	00050	EA  	2004	3	15	CA040127007      	1	20040127	G	3250		STEERING SYS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOST NOSEWHEEL STEERING ON LANDING CLT. TRIED NUMEROUS RESETS WITH NO SUCCESS. TUG ARRIVED AND TOWED TO GATE. OUT 	OF SERVICE FOR INVESTGATION.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500051	20040315	00051	EA  	2004	3	15	CA040127008      	1	20040127	G	2120		ODOR            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CABIN	DETECTED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  FLIGHT CREW NOTICED AN ACRID ODOR IN THE COCKPIT.  AFTER NOTING THE ACRID ODOR THE FLIGHT CREW OBSERVED A CIRCUIT	 BREAKER THAT HAD POPPED. THE ODOR SEEMED TO CLEAR AND THEN REOCURRED ASSOCIATED WITH A SOUND.  THE FLT CREW ELECTED TO 	DEC. MAINTENANCE INVESTIGATION UNDER WAY.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500053	20040315	00053	CE  	2004	3	15	CA040127010      	1	20040121	G	5610	10138402521	WINDSHIELD      			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) IN CRUISE 28,000 FT, OAT-32, WINDSHIELD HEAT ON. HEARD A BANG - PILOT'S WINDSHIELD CRACKED. DESCENDED TO 12,500 FT	, REDUCED AIRSPEED AND CABIN PRESSURE DIFFERENTIAL TO 4.0, RETURNED TO BASE. LANDED AIRCRAFT FROM RT SEAT.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004031500054	20040315	00054	NM  	2004	3	15	CA040127011      	1	20040127	G	3230	273T41202	GEAR            			BOEING	767   	7673Y0      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					NLG LOCK	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN GEAR WAS LOWERED, NOSE DID NOT LOCK. CREW WAS ABLE TO EXTEND AND LOCK USING THE ALTERNATE METHOD, CONTINUING 	THE LANDING WITHOUT FURTHER INCIDENT. ACFT REMOVED FROM SERVICE FOR INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE
2004031500058	20040315	00058	EA  	2004	3	15	CA040127015      	1	20040127	G	5270		WARNING LIGHT   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	FALSE ACTIVATION	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, CREW HAD DOOR WARNING INDICATION. CREW ELECTED TO RETURN, LANDED WITHOUT INCIDENT. OFF LINE FOR I	NVESTIGATION.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500059	20040315	00059	EA  	2004	3	15	CA040127016      	1	20040127	G	2613		OVERHEAT SENSOR 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT 14TH DUCT MESSAGE ON EICAS AT 500 AGL (84 PERCENT N1) SHORTLY AFTER T/O, DUCT SHOWED RED BETWEEN COWL A/I AND W	ING A/I VALVES ON ANTI-ICE STATUS PAGE. CREW RETURNED, LANDED 700 KGS OVERWEIGHT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500066	20040315	00066	SW  	2004	3	15	CA040127017      	1	20040105	G	6310	269A54021	NUT             			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					FREEWHEEL UNIT	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL LEAKING FROM FREEWHEEL WAS NOTED AT REFUELING STOP.  NUT (WHICH IS ALSO SEAL RUNNER) WAS FOUND LOOSE.  NUT WAS	 RETORQUED AND FLUSH OF FREEWHEEL PRODUCED NO DISCOLORATION OR PARTICLES.  LEAK CHECK CARRIED OUT AND RETURNED TO SERVIC	E. NOTE: THAT OIL ONLY LEAKED OUT AFTER SHUTDOWN (NO OIL SPRAY). THEREFORE, IN THIS INSTANCE, THE OIL WAS DYNAMICALLY HE	LD IN, EVEN WITH THE LACK OF SEALING AT FRONT.			1	G	7	1 	3O	3	O	O	4H12    	E286
2004031500067	20040315	00067	SO  	2004	3	15	CA040127018      	1	20040124	G	2820	465299	LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START UP, PILOT NOTICED FUEL ODOR IN CABIN SHORTLY AFTER ENGINE START UP. MAINTENANCE WAS NOTIFIED AND AFTE	R INSPECTION IT WAS NOTED A FINE MIST FROM RT FLEXIBLE FUEL PRESSURE LINE. HOSE WAS REPLACED WITH NO FURTHER PROBLEMS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500068	20040315	00068	CE  	2004	3	15	CA040127020      	1	20040112	G	3340	055201913	RING            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LANDING LIGHT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LANDING LIGHT ASSEMBLY MOUNTING RING (MADE OF ALUMINUM, RIVETED INTO COWLING NOSE BOWL) CRACKED THROUGH SEVERAL RI	VET HOLES AND ANCHOR NUT HOLES. THESE RINGS ARE PRONE TO CRACKING, BUT THIS ONE HAS LASTED ONLY 20 MONTHS/1100 HOURS. MA	TERIAL MAY BE TOO BRITTLE. OTHER FACTORS: FREQUENT LANDING LIGHT CHANGES, VIBRATION, POSSIBLE HEAT FROM LIGHTS, POSSIBLE	 OVER TIGHTENING OF SCREWS.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004060900001	20040609	00001	NM  	2004	6	9	CA040127021A     	1	20040127	G	3320		LIGHT           			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					CABIN	ODOR            	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) READING LIGHTS 20DEF & 25DEF SPARKLING WITH ELECTRICAL ODR. POWER REMOVED ODOR DISAPATED. A/C REMOVED FROM SERVICE	 FOR INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004031500089	20040315	00089	SW  	2004	3	15	CA040128001      	1	20040128	G	6510	407340339107	BEARING RACE    			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					T/R DRIVE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) IT WAS BROUGHT TO OUR ATTENTION THAT A BEARING WAS DELIVERED TO A CUSTOMER AND FOUND WITHOUT THE REQUIRED 4 (.062 	DIA.) LUBE HOLES. THE 4 LUBE HOLES TO BE LOCATED IN THE LUBRICATION GROOVES.					1	G	7	1 	3U	3	U	 	R00001RC	E42NE
2004031500090	20040315	00090	EU  	2004	3	15	CA040128002      	1	20040128	G	3510	89151114	OXYGEN BOTTLE   			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					COCKPIT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) RAMP CHECK CREW O2 WAS 1200 PSIG AFTER 3.5 HOURS WE HEARD A RUSHING AIR NOISE WAS F/O O2 MASK THIS NOISE WAS STOP 	BY PUSHING TEST BUTTON O2 WAS DOWN TO 72 PSIG (MUST HAVE BEEN SLOWLY LEAKING ALONG THEN FAILED. CREW O2 BOTTLE AND REG. 	REPLACED. F/O MASK TESTED AND RESET OK.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2004031500091	20040315	00091	NM  	2004	3	15	CA040128003      	1	20040123	G	3020	4100S02801	HEATER          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AIR INTAKE	BURNED          	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER OUR AIRCRAFT ARRIVED ON THE PARKING POSITION OUR TECHNICIAN REPORTED SMOKE AND FLAMES COMING OUT OF THE LT E	NGINE COWLINGS AND AIR INTAKE SECTION. THE FIRE WAS EXTINGUISHED AND THE CAUSE WAS FOUND TO BE THAT THE AIR INTAKE HEATE	R CAUGHT FIRE. THE AIR INTAKE WHICH WAS THE CAUSE,  WAS A PRE MOD UNIT PN 4100S028-01. RELATED REFERENCE, SYD 84-30-02, 	APPLIES ADDITIONAL SEALANT TO PREVENT FLUID INGRESS TO HEATER CORE.  PN 4100S028-03, POST MODSUM 4-113435			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004031500092	20040315	00092	NM  	2004	3	15	CA040128004      	1	20040127	G	7711		LINE            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					PT7 NR 1 ENGINE	CHAFED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) NR 1 ENGINE EPR INDICATION ERRATIC. FOUND PT7 LINE CHAFED ON LT WING LEADING EDGE AT WBL 114.0.  ELBOW AT END OF L	INE CONNECTION FOUND CRACKED.  BOTH CHAFED LINE AND ELBOW REPLACED.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004031500093	20040315	00093	EA  	2004	3	15	CA040128005      	2	20040109	G	7414		BEARING         	CONT        	3200        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MAGNETO	CONTAMINATED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						A0491056R					(CAN) ON RETURN FLIGHT THE LT ENGINE STARTED TO RUN ROUGH. UPON LANDING THE PILOT DID A MAGNETO CHECK AND FOUND THAT THE	 MAGNETO DROP WAS EXCESSIVE. REMOVED MAGNETO WITH COVER OFF FOUND METAL IN BACK OF MAGNETO. INSTALLED OVERHAULED MAGNETO	, GROUND RUN AIRCRAFT NO FAULTS FOUND.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500095	20040315	00095	NM  	2004	3	15	CA040128007      	1	20040126	G	3242	214664	BRAKE DISC      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG BRAKE UNIT	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0092					(CAN) DURING REMOVAL OF THE BRAKE UNIT FROM THE AIRCRAFT, HALF OF THE BRAKE DISC DROPPED ONTO THE FLOOR. ONCE THE BRAKE 	UNIT WAS REMOVED FROM THE AIRCRAFT, THE REMAINING HALF OF THE DISC WAS RECOVERED FROM THE BRAKE UNIT. IT APPEARS TO BE S	OME DEFORMITY OF THE DISC.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500098	20040315	00098	EU  	2004	3	15	CA040129001      	1	20040129	G	2120		ODOR            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					COCKPIT	DETECTED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STRONG ELECTRICAL ODOR FOR 2 MIN DURING DESCENT. WENT AWAY AFTER SHUTTING THE VTRS OFF. CIRCUIT BREAKER WAS PULLED	 FOR THE REMAINING OF THE FLIGHT, DUE UNABLE TO REACH ANYBODY TO INVESTIGATE IN FLIGHT.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004031500106	20040315	00106	EA  	2004	3	15	CA040129002      	1	20040129	G	7110		ACCOUSTIC LINER 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT & RT ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF, THRU 100KIAS N1 VIB. BOTH ENGINES 4.0 (RED),VIB. REDUCED AFTER APROX 5 MIN. FOUND ACCOUSTIC LINER DAMA	GED. A/C REMOVED FROM SERVICE AND SENT TO HGR FOR REPAIR. (MORE INFO WILL FOLLOW).					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004051000033	20040510	00033	EU  	2004	5	10	CA040129004      	1	20040127	G	2600	3473641	HEAD            	KIDDE       		BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FIRE EXTINGUISH	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						10152EL					(CAN) THIS DUAL OUTLET CARGO BAY EXTINGUISHER WAS RECEIVED FOR OVERHAUL AFTER HAVING BEEN DISCHARGED THROUGH ONE OUTLET.	 UPON REMOVAL OF THE DISCHARGE HEAD FROM THE FIRED OUTLET, A SIGNIFICANT AMOUNT OF AN UNIDENTIFIED COARSLY CRYSTALLINE C	ONTAMINANT WAS FOUND INSIDE THE DISCHARGE HEAD. THE MAJORITY OF THE CONTAMINANT WAS PACKED INTO THE UPPER PART OF THE DI	SCHARGE HEAD, BETWEEN THE INSIDE SURFACES OF THE HEAD AND THE DEBRIS SCREEN. SOME OF THE CONTAMINANT HAD ALSO FALLEN INT	O THE INTERIOR OF THE EXTINGUISHER THROUGH THE FIRED OUTLET.THE CONTAMINANT APPEARS TO BE CORROSIVE, BECAUSE SIGNIFICANT	 CORROSION WAS FOUND ON THE DISCHARGE HEAD RETAINING NUT, AND TO A LESSER DEGREE ON THE INSIDE SURFACES OF THE DISCHARGE	2	H	7	4 	4F	4	F		A49EU   	E6NE
2004031500108	20040315	00108	EU  	2004	3	15	CA040129006      	1	20040119	G	6320	350A38101891	BEAM            			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT ON HELISKIING WHEN THIS OCCURRED. INSPECTED IAW AD96-156-071(B) R1 PART 1.1, EVERY 30 HOURS OR 150 CYCLES	. THIS WAS BEING INSPECTED DUE TO THE CYCLES EVERY 2 OR 3 DAYS.  THE CROSSBEAM WAS FOUND SMOKING IN THE REGION OF SUSPEC	TED CRACK.  THE AREA WAS CLEANED, INSPECTED AND FOUND TO BE SERVICEABLE.  AFTER A NEXT DAY FLYING IT WAS INSPECTED AGAIN	 AND FOUND TO BE SMOKING AGAIN REMOVED FROM SERVICE TO BE NDT.  SENT TO A NDT AMO AND CRACK WAS CONFIRMED. THE AD IS WOR	KING.		1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004031500110	20040315	00110	SO  	2004	3	15	CA040129008      	1	20040122	G	3230		BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	BENT            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			14630								(CAN) ON TAKE OFF WHEN GEARS SELECTED UP PILOT FOUND GEARS INTERMITTED INDICATION. NOSE GEAR WON'T STAY UP LOCKED. TROUB	LESHOT SNAG FOUND TUBE ASSEMBLY, NOSE LANDING GEAR IDLER LINK PN: 41770-00, UNSERVICEABLE. UPLOCK HOOK HOLDING BRACKET I	S BENT AND WORN, AS RESULT UPLOCK HOOK MISALIGNED WITH UPLOCK ROLLER, PREVENTING NOSE GEAR FROM LOCKING UP.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500114	20040315	00114		2004	3	15	CA040130001      	4	20040125	G	3417	C17053AC03	ADC             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) DURING LANDING ROLL OUT IAS MISMATCH MESSAGE APPEARED, NR 1 IAS WAS 30 KTS HIGHER THAN NR 2 IAS.  AFTER PARKING AT	 THE ARRIVAL GATE,  NR 1 IAS INDICTED 38 KTS AND TAS WAS SCROLLING.  NR 2 IAS STEADY AT 30 KTS (NORMAL).  MAINTENANCE PU	RGED NR 1 PITOT/STATIC LINES THEN RECONNECTED.  NR 1 IAS CONTINUED TO FLUCTUATE AT 38 KTS FOR SEVERAL MINUTES THEN DROPP	ED TO 30 KTS AND BECAME STEADY. NR 1 ADU REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004031500117	20040315	00117	NM  	2004	3	15	CA040130002      	1	20040106	G	2422	054021	RESISTOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	INVERTER	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA						1882S8					(CAN) COMPONENT RESPONSIBLE FOR INVERTER FAILURE WAS THE RESISTOR (R324) P/N 054021 DESCRIPTION: ON APPROACH, PRIMARY IN	VERTER, SECONDARY INVERTER, AND AUX INVERTER, L26AC BUS, AND R26AC BUS CAUTION LIGHTS ILLUMINATED.  AFTER AUX INVERTER S	WITCHED OFF, PRIMARY, SECONDARY AND BOTH 26AC BUS LIGHTS WENT OUT. CREW BROKE OFF APPROACH AND AC RETURNED.  COULD NOT F	AULT ON GROUND.  PRIMARY INVERTER VOLTAGE INDICATING 107V AND REPLACED.  AUX INVERTER REPLACED FOR T/S.  ALL RELATED CON	NECTOR PLUGS AND CIRCUIT BREAKERS INSPECTED SVC. INVERTERS SENT OUT TO VENDOR AND RETURNED WITH S/N 1882-S8 S WO CONFIRM	ING FAULT, AND NAMING THE RESISTOR AS THE CULPRIT COMPONENT P/N 054021.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500118	20040315	00118	NE  	2004	3	15	CA040130003      	2	20040126	G	7200	3020159	RETAINER        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HOT SECTION WAS GIVEN A SCHEDULED HOT SECTION INSPECTION. FOUR CT SHROUD SEGMENTS HAD SHIFTED SLIGHTLY. THE RE	TAINING RING HAD COME OUT OF THE GROOVE. THIS PROBLEM HAS BEEN DOCUMENTED ON OTHER ENGINES. PWA 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 THE 114A 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
2004042800030	20040428	00030	NM  	2004	4	28	CA040130004      	1	20040107	G	2422	048503	TRANSISTOR      	PHOENIX     	DH103024600C	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	INVERTER	SHORTED         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA						2218S8					(CAN) COMPONENT RESPONSIBLE FOR  INVERTER FAILURE WAS DRIVER TRANSISTOR WHICH SHORTED.  ON APPROACH MSTR CAUTION LIGHT I	LLUMINATED GPWS, PRIM INV, SEC INV, AUX INV, L626AC AND/OR R26AC BUSES,  BOTH TCAS S AND IVSI S FLAGGED, LASTED 1-2 MIN.	 AND THEN RETURNED TO NORMAL. MSTR CAUTION COULD NOT BE RESET, CONTINUOUSLY FLASHING.  INITIATED MISSED APPROACH AND DIV	ERTED. FOUND SECONDARY INV. OUTPUT VOLTAGE LOW.  REPLACED SEC. INV. REPLACED 400 HZ 115V/26V TRANSFMR T1.  REPLACED 400H	Z CNTRL BOX. REPLACED PRIMARY INV.  OPERATION TEST OF AC400 HZ SYSTEM SERVICEABLE IAW MM.  INVERTERS SENT OUT TO VENDOR 	AND RETURNED TO JAZZ WITH WO CONFIRMING FAULT, AND NAMING THE DIVER TRANSISTOR AS THE CULPRIT COMPONENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500119	20040315	00119	NM  	2004	3	15	CA040130005      	1	20040116	G	5610	17180003	WINDOW          			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			14921								(CAN) SHORT WHILE AFTER TAKEOFF AT 13:54 AT 23000 FEET PILOT NOTICED COCKPIT PORT SIDE WINDOW SHOWING SIGNS OF DISCOLORA	TION.  WHEN PILOT NOTICED DISCOLORATION SIDE WINDOW HEAT WAS SELECTED ON.  SHORTLY AFTER HEAT WAS SELECTED ON, OUTER PAN	E CRACKED FOLLOWED NOT LONG AFTER BY A PARTIAL SEPARATION OF OUTER PANE.  SEPARATION PORTION OF WINDOW PANE STRUCK THE L	T IB WING LEADING EDGE AND LT HORIZONTAL STABILIZER CAUSING SOME MINOR DAMAGE TO DEICER BOOTS.  FOLLOWING THIS, AC RETUR	NED TO DORVAL. MAINTENANCE REPLACED THE PORT COCKPIT SIDE WINDOW AND AC WAS RETURNED BACK TO SERVICE. RECORDS INDICATE T	HIS TO BE THE ORIGINAL WINDOW.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500120	20040315	00120	EU  	2004	3	15	CA040130006      	1	20040125	G	6230	11741904	SWASHPLATE      			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					MAIN ROTOR	WORN            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) UPON RETURNING AFTER A TRIP THE PILOTS REPORTED A (HUMP) (VERTICAL VIBRATION) ON THE AIRCRAFT. A VISUAL INSPECTION	 WAS CARRIED OUT ON THE MAIN ROTOR HEAD, BLADES, PITCH LINKS, AND THE SWASHPLATE.  CHECKING THE SWASHPLATE FOUND IT TO H	AVE AN EXCESSIVE AMOUNT OF PLAY.				1	G	7	2 	3U	3	U	 	H13EU   	E5NE10
2004031500133	20040315	00133	CE  	2004	3	15	CA040130007      	1	20040106	G	2434	C6FF10555A	HOUSING         			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	ALTERNATOR	CRACKED         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA						9041135					(CAN) ON INSPECTION OF ALTERNATOR HOUSING 2 RIBS WERE FOUND CRACKED COMPLETELY THROUGH. THERE HAVE BEEN TWO OTHER SIMILA	R ALTERNATORS FOUND WITH CRACKED RIBS.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA
2004031500135	20040315	00135	SO  	2004	3	15	CA040130008      	1	20040127	G	3220	67054003	TRUNNION        			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK EMANATING FROM TOP OF WEB JUST RT OF CENTER STRUT HOUSING.  NO REPORT OF HARD LANDING OR ABUSE.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920
2004031500136	20040315	00136	SW  	2004	3	15	CA040130009      	1	20040130	G	5412		CAP             	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN BEAM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOT UNUSUAL FOR THE OLDER STYLE BEAM CAP TO CRACK.  THIS IS A REGION THAT IS PART OF OUR INSPECTION PROGRAM.  THER	E IS A MORE EXTENSIVE INSPECTION AFTER 10,000 HOURS.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004031500137	20040315	00137	EU  	2004	3	15	CA040131001      	1	20040130	G	2913	704A33690004	DRIVE BELT      			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					HYDRAULIC PUMP	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE BELT BROKE 2 MINUTES AFTER TAKE-OFF.  OAT WAS -15C.  THE AIRCRAFT MADE A NORMAL HYDRAULIC-OFF LANDING.  NO UNC	OMMANDED CONTROL MOVEMENT OCCURRED AT THE TIME OF THE INCIDENT.					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE
2004031500138	20040315	00138	GL  	2004	3	15	CA040202001      	3	20040211	G	6110	LW13792	SEAL            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	BLOWN           	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								L175755A			(CAN) PILOT NOTICED ENGINE SEEPING FROM LT ENGINE COWL, THEY WERE NEAR THE AIRPORT AND DECIDED TO SHUTDOWN LT ENGINE TO 	PREVENT ENGINE DAMAGE. IT WAS DETERMINED ON THE GROUND BY MAINTENANCE THAT THE LT PROP SEAL HAD BLOWN DUE TO A FROZEN BR	EATHER. IT WAS DETERMINED THAT PROBLEM RESULTED FROM AN EXTREME DROP IN TEMPERATURE CAUSING ANY MOISTURE IN THE BREATHER	 FROM PREHEAT TO FREEZE. PROP SEAL WAS REPLACED AND TEST FLIGHT SUCCESSFUL.			1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA
2004031500157	20040315	00157	NE  	2004	3	15	CA040202003      	2	20040102	G	7320		BELLCRANK       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					FUEL LEVER	LACK OF LUBE    	W				K				NONE                    				W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		IN	INSP/MAINT     	1			CA											(CAN) COULD NOT SHUT DOWN LT ENGINE WITH FUEL LEVER. HAD TO PULL FIRE HANDLE. ALSO RT ENGINE VERY DIFFICULT TO SHUT OFF.	 CABLE MECHANISM FOUND STIFF DUE TO VERY COLD WEATHER. FUSELAGE TO PYLON BELLCRANK LUBRICATED AND BOTH SYSTEMS SERVICEAB	LE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004031500158	20040315	00158	WP  	2004	3	15	CA040202004      	1	20040105	G	2133	39271411	OUTFLOW VALVE   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CABIN PRESSURE	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UNABLE TO PRESSURIZE THE AIRCRAFT. AIRCRAFT LANDED. MAINTENANCE FOUND RT PRSO VALVE P/N 392714-1-1 S/N 2653 IN FAU	LT.  VALVE REPLACED.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004031500159	20040315	00159	WP  	2004	3	15	CA040202005      	1	20040109	G	2133	39245431	REGULATOR VALVE 			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CABIN PRESSURE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) COULD NOT PRESSURIZE THE AIRCRAFT. AIRCRAFT LANDED BACK, FOLLOWING INVESTIGATION, MAINTENANCE FOUND IN FAULT THE L	T PILOT PRESSURE REGULATING VALVE P/N 392454-3-1 S/N 6549 AND LT PRESSURE REGULATOR VALVE P/N 392714-1-1 S/N 4522.  BOTH	 VALVES REPLACED AND AIRCRAFT DISPATCHED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004031500160	20040315	00160	WP  	2004	3	15	CA040202006      	1	20040115	G	2910		B-NUT           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					HYD LINE	LOOSE           	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) UPON ARRIVAL AT GATE WHEN APU AIR SELECTED 'ON', CABIN AND COCKPIT FILLED WITH BLUE SMOKE. CAUSED BY THE INGESTION	 OF HYDRAULIC OIL IN THE APU AIR INTAKE. SOURCE OF FLUID CAME FROM RT WHEEL WELL. MAINTENANCE FOUND 2 (B) NUTS LOOSE ON 	ONE HYDRAULIC LINE NEAR RT HYDRAULIC RESERVOIR. NUTS TIGHTENED AND SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004050700016	20040507	00016	WP  	2004	5	7	CA040202007      	1	20040116	G	2752	59370525001	ACTUATOR        			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RT FLAP	LEAKING         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, CABIN AND COCKPIT FILLED WITH BLUE SMOKE SMELLED LIKE SKYDROL. APU HAS INGESTED SKYDROL FROM LEAK R	T WHEEL WELL. AIRCRAFT LANDED BACK. THE USE OF APU HAS BEEN CANCELLED IAW MEL. WATER SEPARATORS AND COALESER BAGS CLEANE	D AND AIRCRAFT DISPATCHED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004031500161	20040315	00161	NM  	2004	3	15	CA040202010      	1	20040202	G	7830		THRUST REVERSER 			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER T/O CREW RECEIVED A FLAP WARNING AND T/O WARNING HORN. SIMILAR  INCIDENT. THE FLIGHT RETURNED AND UPON LANDI	NG, THE RT ENGINE QUIT. A/C REMOVED FROM SERVICE FOR INVESTIGATION. FLIGHT DATA RECORDER REMOVED FOR READOUT. CAPT CONTA	CTED REGARDING ENGINE QUIT STATEMENT, THE ENGINE DID NOT QUIT, IT ROLLED BACK BELOW 60 KTS AFTER THRUST REVERSER STOWED 	NIL EGT, INCREASE NOTICED BY CREW. INCIDENT UNDER INVESTIGATION.			2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004031500162	20040315	00162	CE  	2004	3	15	CA040202011      	1	20040109	G	5260	10151417617	HANDLE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	AIRSTAIR DOOR	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			17475								(CAN) DURING TAKEOFF ROLL THE AIRSTAIR DOOR EXTERIOR HANDLE SEPARATED FROM THE DOOR. FURTHER INSPECTION FOUND IMPACT DAM	AGE TO LT PROPELLER AND LT IB FLAP. APPROXIMATELY ONE INCH MISSING FROM TIP OF ONE PROPELLER BLADE AND DENT IN LOWER SKI	N OF IB FLAP. HANDLE RECOVERED AND INSPECTED FOR CONDITION. RETAINER RING P/N MS16624-1075 MISSING ALLOWING HANDLE TO SE	PARATE FROM DOOR. LSO FOUND PIN P/N MS9048-072 SHEARED. THIS PIN HOLDS SHAFT IN HANDLE. HANDLE ASSEMBLY REPLACED WITH NE	W. PROPELLER ASSEMBLY REPLACED. SKIN REPAIR CARRIED OUT TO IB FLAP.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004031500169	20040315	00169	CE  	2004	3	15	CA040202012      	1	20040113	G	5410	5012000886	SPAR            	RAYTHN      		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						LJ1305					(CAN) NACELLE OB WEB TO SPAR ATTACHMENT CHANNEL CRACKED IN BEND RADIUS ON LOWER END OF CHANNEL. THIS CONDITION EXISTED I	N THE SAME AREA ON BOTH NACELLES. CRACKS ARE COMMON IN THESE AREAS ON HIGH CYCLE AIRPLANES.  LATER SN AIRCRAFT COME FROM	 THE FACTORY WITH DOUBLERS ALREADY INSTALLED IN THESE AREAS.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	STC
2004050700025	20040507	00025	NE  	2004	5	7	CA040202013      	2	20040106	G	7200		ENGINE          								PWA   	PT6   	PT6A112     	52043	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								12566			(CAN) ENGINE WAS INVOLVED IN A PROP STRIKE INCIDENT WHEN AIRPLANE PULLED OFF RUNWAY AND NLG STRUCK A STUMP, FORCE OF THI	S IMPACT COLLAPSED THE LANDING GEAR AND BOTH PROPELLERS STRUCK THE GROUND.  IT WAS CLEAR TO IDENTIFY THAT ENGINE HAD SUF	FERED FROM A PROPELLER STRIKE. EXHAUST DUCT TWISTED CONDITION ALSO CAUSED POWER TURBINE DISK ASSEMBLY AND SEALS TO SEVER	ELY RUB AGAINST THE PT SHROUD RING KNIFE-EDGES AND PTV RING INTERSTAGE BAFFEL, THIS IS ALSO REASON WHY PROPELLER SHAFT W	AS NOT TURNING PRIOR TO DISASSEMBLY. DUCT OUTER SKIN SECTION MOVED OFF CENTER DURING IMPACT, WHICH CAUSED THESE COMPONEN	TS TO RUB AND SEIZE. ENGINE WILL BE RESTORED TO A SERVICEABLE CONDITION THROUGH A COMPLETE OVERHAUL.						3	T			E4EA
2004050700032	20040507	00032	NE  	2004	5	7	CA040202014      	2	20040106	G	7250	PT6A112	ENGINE          								PWA   	PT6   	PT6A112     	52043	NE  						FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								12519			(CAN) ENG  WAS INVOLVED IN A PROP STRIKE INCIDENT, AC PULLED OFF THE RUNWAY AND NLG STRUCK A STUMP, FORCE OF THIS IMPACT	 COLLAPSED LANDING GEAR, BOTH PROPS STRUCK THE GROUND.  IT WAS CLEAR TO IDENTIFY THAT ENG SUFFERED FROM  PROP STRIKE.  E	XHAUST DUCT WAS SEVERELY TWISTED, DISTORTED AND ASSOCIATED IT WERE 2 BENT OIL TRANSFER TUBES. THIS TWISTED CONDITION OF 	EXHAUST DUCT ALSO CAUSED PT DISK ASSEMBLY, SEALS TO SEVERELY RUB AGAINST THE PT SHROUD RING KNIFE-EDGES AND THE PTV RING	 INTERSTAGE BAFFLE, PROP SHAFT WAS NOT TURNING PRIOR TO DISASSEMBLY.  EXHAUST DUCT OUTER SKIN SEC MOVED OFF CENTER DURIN	G IMPACT, WHICH CAUSED THESE COMPONENTS TO DISPLACE, RUB AND SEIZE. ENGINE WILL BE RESTORED TO A SERVICEABLE CONDITION.						3	T			E4EA
2004031500171	20040315	00171	EU  	2004	3	15	CA040202015      	1	20040130	G	6320	332A32323300	TIE ROD         	UROCOP      		SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					M/R GEARBOX	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M279					(CAN) ONE OF THE THREE BOLTS ATTACHING THE ENGINE TO THE MAIN GEARBOX WAS DISCOVERED SHEARED DURING A TURN AROUND CHECK.	 THE BOLT WAS SHEARED ABOUT MIDWAY IN THE THREADED PORTION OF THE BOLT. THE ENGINE WAS REMOVED AND AREA INSPECTED IAW WR	ITTEN PROCEDURES. NO REASON FOR BOLT DAMAGE WAS DETERMINED.				2	G	7	2 	4U	4	U	 	H4EU    	E12NE
2004031500172	20040315	00172	EU  	2004	3	15	CA040202016      	1	20040202	G	3230	D172890	CONTROL CABLE   			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					MLG	BINDING         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) UPON FUNCTIONAL TEST OF LANDING GEAR RETRACTION, THE SECONDARY MECHANICAL NOSE GEAR INDICATOR WAS NOT INDICATING P	ROPER EXTENSION (PROTRUSION OF CABLE END).  PROBLEM TRACED TO BINDING CABLE.  EXAMINATION OF DEFECTIVE PART (REMOVAL OF 	CABLE FROM METAL JACKET BY CUTTING) REVEALED BULGE AT SWAGED END CAUSING CABLE TO BIND WITHIN ITS JACKET. THIS ASSY IS T	O BE LUBRICATED (HAND PACKED) EVERY 48 MONTHS IAW MFG RECOMMENDATIONS. HOWEVER THE LIMITED TRAVEL OF THE CABLE WOULD PRE	-EMPT ANY LUBRICANT FROM REACHING THE SWAGED WIRE PORTION ON THE E-CABLE. ONLY THE METAL ROD END WOULD RECEIVE THE LUBRI	CANT.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
2004031500173	20040315	00173	NM  	2004	3	15	CA040202017      	1	20040106	G	2422	116250	CONNECTOR       		DH103024600C	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LOAD EQUALIZER	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA						1814S8					(CAN) COMPONENT RESPONSIBLE FOR INVERTER FAILURE IS SOLDER CONNECTION ON LOAD EQUALIZER SUBASSEMBLY P/N 116250. ON APPRO	ACH, PRIMARY INVERTER, SECONDARY INVERTER, AND AUX INVERTER, L26AC BUS, AND R26AC BUS CAUTION LIGHTS ILLUMINATED. AFTER 	AUX INVERTER SWITCHED OFF, PRIMARY, SECONDARY AND BOTH 26AC BUS LIGHTS WENT OUT. CREW BROKE OFF APPROACH AND AC RETURNED	. COULD NOT FAULT ON GROUND. PRIMARY INVERTER VOLTAGE INDICATING 107V AND REPLACED. AUX INVERTER REPLACED FOR T/S. ALL R	ELATED CONNECTOR PLUGS AND CIRCUIT BREAKERS INSPECTED SVC.  INVERTERS SENT TO VENDOR AND RETURNED WITH S/N 1814-S8 CONFI	RMING FAULT, AND NAMING SOLDER CONNECTION ON LOAD EQUALIZER SUBASSEMBLY AS CULPRIT COMPONENT P/N 116250.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500174	20040315	00174	CE  	2004	3	15	CA040203001      	1	20040130	G	3260	1EN18	DOWNLOCK SWITCH 			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT MLG	FALSE INDICATION	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON GEAR SELECT DOWN, INDICATED RT MAIN GEAR NOT DOWN AND LOCKED WITH 2 MAIN GEAR DOOR UNSAFE RED. LIGHT BULB TEST 	INDICATED THAT BULBS WERE OK. RECYCLED GEARS SELECTOR 3 TIMES WITH NO SUCCESS.  HYDRAULIC PRESSURE WAS NORMAL. CONDUCTED	 EMERGENCY GEAR EXTENSION PROCEDURE BUT DID NOT OBTAIN NORMAL (DOWN AND LOCK) GREEN LIGHTS. TOWER CONFIRMED THAT THERE W	AS NO LANDING LIGHT ON RT SIDE.  EMERGENCY WAS DECLARED, LANDING WAS PERFORMED WITH NO FURTHER PROBLEMS, BESIDE (DOWN AN	D LOCK) LIGHTS. RT DOWN AND LOCK SWITCH WAS REPLACED, GEAR SWINGS WERE C/O, AND THE SYSTEM WAS FOUND SERVICEABLE AND AIR	CRAFT RELEASED TO SERVICE.	2	L	7	2 	4F	4	F	 	A10CE   	E6WE
2005011200002	20050112	00002	SW  	2005	1	12	CA040203002      	1	20040128	G	3233		ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	BYPASSING       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			20294								(CAN) ACFT RETURNED TO BASE. NLG NOT LOCKING UP, SWINGS CARRIED OUT, NO FAULTS FOUND. CARRIED OUT LOW PSI SWING TESTS, N	O FAULTS FOUND. FOUND RT NLG TIRE FLAT. BOTH NLG TIRES REPLACED. INSP FOR DAMAGE, NO FAULTS FOUND, SWINGS CARRIED OUT, S	YS PREFORMED PER MM.   O/B STRIKERS ON LT & RT MLG AT WEAR LIMITS. RT MLG UPLOCK SWITCHES ADJUSTED. ALL 3 MLGS GREASED. 	SWINGS CARRIED OUT, SYS PREFORMED PER MM.  NLG STILL NOT LOCKING UP. SWINGS CARRIED OUT AGAIN & LOW PSI TEST CARRIED OUT	, APPLIED SIMULATED AIRFLOW ON NLG. MX ACHIEVED SNAG. MLG ACT LEAK CHK CARRIED OUT & RT NLG ACT FOUND BYPASSING HYD FLUI	D. O/H'ED ACT INSTALLED. SWINGS CARRIED OUT WITH SIMULATED AIRFLOW LOAD, SYS FUNCTIONED AS PER MM.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2004032500027	20040325	00027	SW  	2004	3	25	CA040203003      	1	20040202	G	2710	2771026001	CONTROL CHAIN   			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	AILERON	WORN            	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING DECENT THE FLIGHT CREW NOTICED THE AILERONS BINDING AND VERY DIFFICULT TO MOVE.  UPON SLOWING DOWN THE AIRC	RAFT THE AILERON CONTROL RETURNED TO NORMAL.  INVESTIGATION BY MAINTENANCE REVEALED THAT THE 27-71026-001 CONTROL CHAIN 	WAS SEIZED AND ALMOST WORN THROUGH ON A COUPLE OF CHAIN LINK SEGMENTS.  IT APPEARS AS THOUGH DURING HIGH SPEED FLIGHT TH	E AIR LOAD ON THE AILERONS CAUSED HIGHER TENSION LOADS ON THE CONTROL CABLES PUTTING MORE FORCE ON THE CHAIN WHICH THEN 	BECAME VERY DIFFICULT TO MOVE. THE CHAINS (27-71026-001) AND SPROCKETS (26-71010-3) ON BOTH CONTROL COLUMN WHEELS WERE R	EPLACED AND THE AIRCRAFT RELEASED FOR FLIGHT.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2004032500028	20040325	00028	CE  	2004	3	25	CA040203004      	1	20040130	G	3230	MS24171D1	RELAY           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG MOTOR	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) LANDING GEAR FAILED TO EXTEND ON APPROACH. EMERGENCY EXTENSION WAS CARRIED OUT AND AIRCRAFT LANDED SAFELY. MAINTEN	ANCE FOUND THAT THE LANDING GEAR MOTOR WAS NO LONGER RUNNING. THE LANDING GEAR RELAY WAS FOUND INTERNALLY DAMAGED WITH T	HE CONTACTS STUCK IN THE CLOSED POSITION THUS PROVIDING CONTINUOUS POWER TO THE LANDING GEAR MOTOR.  THIS CAUSED THE MOT	OR TO FAIL. P/N OF RELAY MS24171D1			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004050700044	20040507	00044	SW  	2004	5	7	CA040203005      	1	20040122	G	6320	3023724	TUBE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10894								(CAN) DURING THE SCHEDULED INSPECTION CARRIED OUT THE BASE, THE AME NOTICED THAT THE TUBE P/N 3023724 WAS CRACKED BEHIND	 THE B-NUT AREA. THE CRACKED TUBE WAS REMOVED AND REPLACED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004032500029	20040325	00029	CE  	2004	3	25	CA040203006      	1	20040108	G	5610	10138402518	WINDSHIELD      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	BROKEN          	W				B				EMER. DESCENT           				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) IN CRUISE RT WINDSHIELD HEAT ON, WINDOW SHATTERED, DESCENDED TO 12,000 FT, REDUCED AIR SPEED AND CABIN PRESSURE AN	D RETURNED TO BASE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004032500042	20040325	00042	EA  	2004	3	25	CA040203007      	1	20040122	G	2435	2007583	GROUND WIRE     			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STARTER GEN	FAILED          	W				F				ACTIVATE FIRE EXT.      				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			CA											(CAN) ON STARTING THE ENGINE THERE WAS ARCING AND SPARKS COMING FROM THE STARTER GROUND ATTACHMENT LOCATED UNDERNEATH TH	E COCKPIT.  THE SPARKS CAME FROM THE GROUNDING ATTACHMENT BOLT ANCHOR NUT RIVET.  RECOMMEND A BETTER GROUNDING LOCATION 	AND ATTACHMENT.				1	H	7	1 	3R	4	T	 	A815    	E4EA	6	C	P15EA
2005011200003	20050112	00003	CE  	2005	1	12	CA040203008      	1	20040122	G	5210		BOLT            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	PAX DOOR	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) BOLTS, BUSHINGS SEIZED ON MAIN DOOR TOP HALF.  INCORRECT HARDWARE STACK-UP, IE INTERNAL WRENCHING BOLT HAD PLAIN W	ASHER UNDER RADIUS OF HEAD. SEVERAL AIRCRAFT HAVE HAD THESE SAME PROBLEM OF SEIZED/CORRODED PARTS. CAUSED BY LACK OF LUB	RICATION.  MAIN DOOR BOLTS/BUSHING P/N MS20004-505111515-10				1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA
2004032500054	20040325	00054	CE  	2004	3	25	CA040203009      	1	20040116	G	3220	5042013497A	FORK            	CESSNA      		CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN FORK CASTING ON LT SIDE OF TUBE BORE. DISASSEMBLY REVEALED FORK CRACKED COMPLETELY THROUGH LT SIDE 	OF BORE.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA
2004032500055	20040325	00055	CE  	2004	3	25	CA040203010      	1	20040126	G	5610	9031002P	WINDSHIELD      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, PILOT HEARD SMALL CRACK SOUND THOUGHT HE DROPPED SOMETHING, WHILE LOOKING AROUND, NOTICED RT WINDSH	IELD CRACK DESCENDED AND CARRIED ON. LANDED WITHOUT INCIDENT.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P40EA
2004032500056	20040325	00056	NE  	2004	3	25	CA040203011      	2	20040127	G	7322	91620	SHAFT           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					FUEL CONTROL	WORN            	W				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			CA						2ADS1203					(CAN) UPON SUSPECTING A PROBLEM WITH FUEL CONTROL UNIT. REMOVED FCU FROM THE ENGINE TO INSPECT THE SPLINES IAW MFG SBT53	13-107. FOUND THE INTERNAL SPLINES KNIFE EDGED AND VERY CLOSE TO TOTAL FAILURE OF THE FCU. THIS WOULD HAVE LEAD TO THE F	AILURE AND SHUTDOWN OF THE ENGINE. THESE PARTS HAD 434 HOURS SINCE THEY WERE REPLACED WITH SERVICEABLE UNITS. SHAFTS P/N	 9162076081.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA
2004041300024	20040413	00024	NM  	2004	4	13	CA040203012      	1	20040203	G	2910	272T3100351	LINE            			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					HYDRAULIC SYS	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT HYDRAULIC QTY LOST ON T/O ROLL NO HYD FLUID REMAINING ASSOCIATED SYSTEM AFFECTED. FOUND LT HYDRAULIC RETURN LIN	E RUPTURED.  LINE REPLACED, PRESS/CASE FILTERS REPLACED. LEAK AND FUNCTION CHECK SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004032500057	20040325	00057	GL  	2004	3	25	CA040203013      	1	20040123	G	7820	973670	MUFFLER         			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912S3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	ENGINE EXHAUST	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) TAILPIPE NEARLY SNAPPED OFF FROM MUFFLER, INTERNAL BAFFLES LOOSE AND OBSTRUCTING EXHAUST OUTLET PART, CAUSING THE 	BACK PRESSURE TO RISE AND FAILURE OF TAILPIPE HAS OCCURRED. ENGINE POWER WAS ROBBED AND FORCED THE BUILD-UP OF BACK PRES	SURE TO EXIT THE HOLE IT HAS CREATED.  CORRECTION ACTION IS TO SEND MUFFLER TO AN AMO WHOM MAY REPAIR MUFFLER AND COMPLE	TE TAP TESTS TO MUFFLER TO VERIFY THE STATUS OF INTERNAL BAFFLES, AT EVERY INSPECTION.			1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO
2004032500058	20040325	00058	SW  	2004	3	25	CA040203014      	1	20040128	G	6320	206040030101	BEARING RACE    	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	SPALLED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						BKW1417					(CAN) BEARING SPALLED AND CAUSED A CAUTION LIGHT TO COME ON.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004032500059	20040325	00059	EU  	2004	3	25	CA040203015      	1	20040129	G	5347	STCSA9750	ADAPTER         			AIRBUS	310   	A310304     	3930339	EU  										SEAT TRACK	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) THIS PROBLEM AFFECTS AIRCRAFT MODIFIED BY INSTALLATION OF AN EMS MODIFICATION IAW STC SA97-50 ONLY. SEAT TRACK ADA	PTERS, PN 6372 HAVE BEEN DETERMINED TO BE UNDER STRENGTH BY DESIGN. DESIGN DOES NOT MEET THE CERTIFICATION BASIS OF THE 	AIRCRAFT.				2	L	7	2 	4F			RT	A35EU
2004032500086	20040325	00086	CE  	2004	3	25	CA040204005      	1	20040121	G	2710	051010516	CONTROL CABLE   			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON DIRECT CABLE LT AND RT FRAYED EACH IN 3 DIFFERENT PLACES AT PULLEYS, PULLEYS WERE NOT SEIZED, ROTATES FREE	LY, ALSO FRAYED AILERON CARRY THROUGH CABLE P/N 0510105-113 AT PULLEY AREA.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
2004032500088	20040325	00088	EU  	2004	3	25	CA040204009      	1	20040128	G	5210	5521012219	PIN             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX DOOR HANDLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PAX/CREW DOOR HANDLE LOCKING MECHANISM HARD TO OPERATE EXCEPT UPON ARRIVAL AT MAIN BASE. INSPECTING  DOOR, FOUND P	IN LOCK AND ITS SPRING FROM SAFETY LOCKING MECH TO BE MISSING. LOCKING MECH STOPS ACCIDENTAL OPERATION OF DOOR HANDLE IN	SIDE AC.  RELEASE LEVER IS INSTALLED ON INSIDE OF DOOR BELOW INNER HANDLE.  CABLE CONNECTS IT TO A LOCKING PIN WHICH ENG	AGES IN OUTER HANDLE IF PIN LOCK BREAKS OR IS FORCED OUT OF CRANK, COMPRESSION SPRING EJECTS ITSELF AND PIN LOCK AWAY FR	OM AC AND THE DOOR CAN BE OPENED JUST BY ACTIVATING HANDLE.  SUSPECT FORMATION OF ICE BETWEEN THE LOCKING PIN AND THE DO	OR STRUCTURE TO RESTRAIN MOVEMENT OF PIN AND CAUSE A FAILURE OF LOCKING MECHANISM.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004032500089	20040325	00089	EU  	2004	3	25	CA040204010      	1	20040130	G	2435	23085024	BEARING         	LUCAS       		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						Y0253					(CAN) GEN NR 1 FAILED IN FLIGHT. UPON ARRIVAL, MAINTENANCE FOUND THE REAR BEARING OF THE STATER GENERATOR FAILED CAUSING	 THE COOLING FAN TO RUB ON THE CASE.CREATING VIBRATION. STARTER GENERATOR REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004032500101	20040325	00101	NE  	2004	3	25	CA040204011      	2	20040111	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LEFT	FAILED          	W				A				UNSCHED LANDING         				C			F.O.D.                    			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT 31,000 FT, ENGINE SURGE FELT ON LT ENGINE (EPR REDUCED TO 1.67) WITH AN IMMEDIATE ODOR. SAME SURG	E/ODOR WAS FELT A SECOND TIME APPROXIMATELY 45 MINUTES LATER. AIRCRAFT DIVERTED TO POP. MAINTENANCE FOUND FORWARD LAVATO	RY LEAKING. LT ENGINE INSPECTED IAW MM 72-0-04 P.115 AND ENGINE RUN C/OUT TO 2-0 EPR AND NO FAULT FOUND. AIRCRAFT DISPAT	CHED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004032500102	20040325	00102	CE  	2004	3	25	CA040204012      	1	20040114	G	3260	1CH25	DOWNLOCK SWITCH 			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	NLG	FROZEN          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE PILOT SELECTED GEAR DOWN. THERE WAS NO NOSE GEAR INDICATION. AFTER CONFIRMING WITH THE TOWER THAT 	THE GEAR WAS DOWN, THE AIRCRAFT LANDED WITHOUT INCIDENT. THE DOWNLOCK SWITCH WAS FOUND DEFECTIVE AND SUBSEQUENTLY REPLAC	ED.  OAT WAS -25 TO -30 DEGREES CELSIUS.				1	L	7	2 	4T	4	T	 	A14CE   	E2WE	6	C	P40EA
2004032500104	20040325	00104	EA  	2004	3	25	CA040205001      	1	20040129	G	3310		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) SMOKE AND SPARKS WERE COMING FROM THE FIRST OFFICER FLOOD LIGHT. MAINTENANCE ACTION WAS TO REPLACED THE FLOOD LIGH	T ASSEMBLY AND TO RETORQUE THE SIDE WINDOW.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004032500105	20040325	00105	EA  	2004	3	25	CA040205002      	1	20040131	G	3310	2LA00691307	LIGHT           			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FOS FLOOD LIGHT OVER LIGHTING CONTROL PANEL (UNDER RT WINDSHIELD/SIDE WINDOW POST) EMITTS A STRONG ELECTRICAL SMEL	L AND THEN SHORTED OUT WITH ARCHING.  AIRCRAFT CONTINUED ON AND LANDED WITHOUT FURTHER INCIDENT. MTCE FOUND THAT WATER W	AS LEAKING INTO THE CABIN WHEN WATER SPRAY WAS CONCENTRATED ON THE UPPER AREA OF THE RT WINDSHIELD/SIDE WINDOW STRAP. TH	E LIGHT ASSEMBLY WAS REPLACED.			2	L	7	2 	4F			RT	A21EA
2004032500106	20040325	00106	EA  	2004	3	25	CA040205003      	1	20040126	G	5610	601R330333	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			14843								(CAN) DURING CRUISE, FLIGHTDECK LT SIDE WINDOW CRACKED. FLIGHT WAS DIVERTED WHERE THE WINDOW WAS REPLACED. THE CRACKED W	INDOW HAD BEEN FITTED SINCE THE A/C WAS NEW. THERE IS NO PRE OR POST SB FOR SIDE WINDOWS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004032500154	20040325	00154	NE  	2004	3	25	CA040205004      	2	20040131	G	7200		ENGINE          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					NR 2	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, 2000 ASL, NR 2 LOUD BANG FOLLOWED BY ENGINE STOPPAGE, MAYDAY DECLARED, ENGINE SECURED AND QRH DRIL	LS ACTIONED. RADAR VECTORED SINGLE ENGINE APPROACH AND LANDING. FIRE SERVICE ESCORTED ON LANDING, PAX OFFLOADED ON STAND	. THE ENGINE WAS REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004032500121	20040325	00121	CE  	2004	3	25	CA040205005      	1	20040202	G	8011	PM2401H	DRIVE ASSY      	LAMAR       		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	STARTER	JAMMED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						85017317					(CAN) STARTER DRIVE ONCE ENGAGED DID NOT RETRACT JAMMED OUTWARD.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2004032500122	20040325	00122	EU  	2004	3	25	CA040205006      	1	20040203	G	7714		DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EIS	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, THE UPPER PORTION OF THE ENGINE INDICATION SCREEN FAILED TQ, NG, & ITT. THE ALTERNATE SCREEN	 WAS SELECTED AND PERFORMED PROPERLY. THE EIS COMPUTER WAS REPLACED WITH A SERVICEABLE UNIT AND FUNCTION TREATED SERVICE	ABLE.  IT WAS NOTED A NORMAL ENGINE START COULD NOT BE ACCOMPLISHED AS THERE WAS NO ENGINE NG INFORMATION AVAILABLE TO T	HE START COMPUTER TO SIGNAL IGNITION AND BOOST PUMPS.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004032500123	20040325	00123	NE  	2004	3	25	CA040205007      	2	20040122	G	7321		FUEL CONTROL    			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					LT ENGINE	INOPERATIVE     	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING, LT ENG POWER LEVER WAS ADVANCED TO FACILITATE TURN.  THRUST LEVER WAS ADVANCED, LT ENG SUFFERED A R	OLL BACK AND FLAME-OUT. AC WAS TAXIED CLEAR OF RUNWAY, FAULT ANALYSIS RELIGHT ATTEMPTED WITH NO SUCCESS.  RELIGHT WAS SU	CCESSFUL. AC WAS THEN SHUT DOWN AND SURRENDERED TO MAINT FOR ACTION. EVENT FOLLOWED ACTION AND INSTALLATION OF SB 30253.	 FUEL LINE, ATTENUATOR ASSY AND FCU WERE REMOVED AND SENT TO MFG FOR ANALYSIS.  DURING REMOVAL, A BLACK SUBSTANCE WAS DE	TECTED.  SUBSTANCE WAS SENT OFF FOR CHEMICAL ANALYSIS BY MFG. NR C 10420020 REGARDING SUBSTANCE. FUEL LINE, ATTENUATOR A	SSY AND FCU WERE REPLACED, IAW SB 30253.  AC WAS GROUND RUN AND TEST FLOWN SATISFACTORILY, RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004032500124	20040325	00124	NE  	2004	3	25	CA040205008      	2	20040122	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					LEFT	FLAMED OUT      	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING AND TURNING ONTO THE RUNWAY, THE LT ENGINE POWER LEVER WAS ADVANCED TO FACILITATE THE TURN. AS THE T	HRUST LEVER WAS ADVANCED, THE LT ENGINE SUFFERED A ROLL BACK AND FLAME-OUT. THE AIRCRAFT WAS TAXIED CLEAR OF THE RUNWAY 	AND A FAULT ANALYSIS RELIGHT ATTEMPTED WITH NO SUCCESS. THE AIRCRAFT WAS THEN TAXIED TO THE RAMP WHERE A FURTHER RELIGHT	 WAS ATTEMPTED.  THE RELIGHT WAS SUCCESSFUL. THE AIRCRAFT WAS THEN SHUT DOWN AND SURRENDERED TO MAINTENANCE FOR ACTION. 	THE EVENT FOLLOWED ACTION AND INSTALLATION OF SERVICE BULLETIN 30253.		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004032500125	20040325	00125	SW  	2004	3	25	CA040206002      	1	20040128	G	2810	206288017	SIGHT GLASS     			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					RANGE EXTENDER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) SIGHT GLASS ON FORWARD SIDE OF RANGE EXTENDER WAS FOUND TO BE THE CAUSE OF A SLOW FUEL LEAK. WHEN THE AIRCRAFT WAS	 FULL OF FUEL AND KEPT IN THE HANGAR OVER NIGHT A SMALL POOL OF FUEL WAS NOTICED ON THE FLOOR.   A CRACK RUNNING ACROSS 	FROM TWO SCREWS WAS FOUND.  A NEW SIGHT GLASS HAS BEEN ORDERED AND WILL BE INSTALLED WHEN RECEIVED. UPON FURTHER INSPECT	ION OF AIRCRAFT,  ANOTHER WITH THE SAME RANGE EXTENDER WAS FOUND TO HAVE THE SAME CRACK IN THE SAME LOCATION.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004032500140	20040325	00140	SO  	2004	3	25	CA040206003      	1	20040204	G	2140		BLADE           	JANITROL    	B4050       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FAN	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ONE OF FOUR BLADES SEPARATED FROM FAN AND MADE A SIGNIFICANT AMOUNT OF NOISE AND VIBRATION IN THE HEATER SUCH THAT	 THE PILOT SHUT THE HEATER DOWN IN FLT.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004032500141	20040325	00141	EU  	2004	3	25	CA040206004      	1	20040205	G	3110	9728132012	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CAWS	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE CREW NOTICED SOME OF THE CAWS LIGHTS OUT.  THE TEST BUTTON WAS USED TO DETERMINE IF THE BULBS WE	RE AT FAULT. ONCE PRESSED THE CAWS PANEL AND MASTER CAUTION/WARNING ILLUMINATED FOLLOWED A SERIES OF FLICKERING LIGHTS A	ND A ODOR OF BURNED WIRES, THE PANEL THEN GOING BLACK. THE BREAKERS WERE PULLED, THE ODOR DISAPPEARED AND AIRCRAFT CONTI	NUED FLIGHT TO ITS MAIN MAINTENANCE BASE. NO PASSENGERS WERE ON BOARD THE AIRCRAFT. THE CAWS DISPLAY AND CAWS COMPUTER W	ERE BOTH REPLACED AND THE AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER FAULTS.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004032500142	20040325	00142	EU  	2004	3	25	CA040206005      	1	20040202	G	2197		WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HEATING SYSTEM	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ONE POWER WIRE FOR THE FOOT HEATER HEAT CONTROL HAD FALLEN ON TO THE BRAKE LINE THAT RUNS ALONG THE FIREWALL JUST 	AHEAD OF THE RUDDER PEDALS.  AS A RESULT ARCING OCCURED AND BURNED A HOLE IN THE LINE. THE .2500 INCH ALUMINUM BRAKE LIN	E WAS REPLACED, SYSTEM BLED AND THE WIRE WAS REPLACED AND SECURED BETTER TO THE BUNDLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004032900051	20040329	00051	NE  	2004	3	29	CA040208002      	2	20040126	G	7320		FUEL CONTROL    			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RT ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) JUST AFTER TOUCHDOWN THE RT FADEC CAUTION MESSAGE CAME ON FOLLOWED BY THE RT ENG FLAMEOUT CAUTION MESSAGE. MAINTEN	ANCE STARTED AND OPERATED THE ENGINE THROUGH SEVERAL CYCLES WITHOUT DUPLICATION OF THE FLAMEOUT CONDITION. MAINTENANCE R	EPLACED THE RT FADEC AND FUEL MANAGEMENT UNIT, THEN OPERATED THE ENGINE THROUGH SEVERAL MORE CYCLES INCLUDING HIGH POWER	 AND REVERSE WITH NO FLAMEOUT OCCURANCE.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004032900052	20040329	00052	EA  	2004	3	29	CA040208003      	1	20040125	G	4930	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU BAY	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) FOR THE OVERNIGHT, THE FLIGHT CREW WERE ASKED TO LEAVE THE APU RUNNING TO PERMIT AIRCRAFT GROOMING.  APPROXIMATELY	 ONE HOUR AFTER ARRIVAL, THE APU FIRE DETECTION SYSTEM PERFORMED AN AUTO SHUTDOWN AND APU FIRE BOTTLE WAS DEPLETED.  GRO	UND/AIRCRAFT PERSONNEL CONTACTED THE FIRE DEPARTMENT.  THE APU WAS INSPECTED, AND EVIDENCE OF FUEL WAS OBSERVED, HOWEVER	 THE SOURCE OF THE APU FUEL LEAK COULD NOT BE ABSOLUTELY PIN-POINTED AND RESULTED IN THE APU'S REPLACEMENT.  THE AIRCRAF	T RETURNED TO SERVICE FOLLOWING THE APU REPLACEMENT.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004032900073	20040329	00073	CE  	2004	3	29	CA040209001      	1	20040205	G	2121	903840311	BLOWER          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	AIR CONDITIONING	SEIZED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) JUST AFTER LEVELING OUT PILOT NOTICED SMOKE IN THE COCKPIT/CABIN AREA. AIRCRAFT WENT TO 10000 FT, DEPRESSURIZED AN	D ELECTRICAL POWER WAS REMOVED. POWER WAS RESTORED AND AIRCRAFT RETURNED TO BASE WITHOUT FURTHER INCIDENT.  UPON INVESTI	GATION IT WAS DETERMINED THAT THE VENTILATION BLOWER BEARING SEIZED AND CAUSED THE SMOKE. VENT BLOWER WAS REPLACED AND S	YSTEM TESTED SERVICEABLE.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC
2004032900095	20040329	00095	NM  	2004	3	29	CA040209002      	1	20040205	G	5610	57176249	WINDOW          			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE F/O OBSERVED THE R2 SLIDING WINDOW WAS CRACKED.  THE DECISION WAS MADE TO RETURN TO BASE. THE AI	RCRAFT LANDED WITHOUT INCIDENT. THE R2 WINDOW ASSY WAS REPLACED IAW MM 56-12-11 AND CHECKED SERVICEABLE. THE R2 WINDOW H	EAT CONTROLLER AND TEMP SWITCH WERE CHANGED AS A PRECAUTION.  FUNCTIONAL CHECK WAS CARRIED OUT SERVICEABLE IAW MM 30-41-	02. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004032900096	20040329	00096	NM  	2004	3	29	CA040209003      	1	20040205	G	3260	189915	TARGET          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					MLG	MISINSTALLED    	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, THE RT MLG UNSAFE LIGHT ILLUMINATED AND GREEN SAFETY LIGHT WAS OUT. MAINTENANCE INSTALLED LANDING GEA	R PINS AND THE AIRCRAFT TAXIED BACK TO THE RAMP.  DURING INSPECTION OF THE PROXIMITY LANDING GEAR SWITCHES, IT WAS OBSER	VED THE TARGETS WERE INSTALLED IMPROPERLY.  THE TARGETS WERE RE-INSTALLED CORRECTLY IAW MM 32-41-91 AND 32-04-121. FUNCT	ION CHECKED SERVICEABLE IAW MM 32-61-91. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004032900097	20040329	00097	SO  	2004	3	29	CA040209004      	1	20040205	G	6120	2489410	CONTROL CABLE   	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP GOVERNOR	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) AT ENGINE WARMING UP PILOT FOUND ( WHEN TRYING CHECK OF PROP GOVERNOR WORK) LT PROP CONTROL LEVER WENT LOOSE, PROP	 DID NOT FOLLOW SETTING ANY MORE. INSPECTION REVEALED LT PROP GOVERNOR CABLE PN:24894-10 BROKEN AND SEPARATED CABLE END 	FITTING AT GOVERNOR SIDE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004032900098	20040329	00098	WP  	2004	3	29	CA040209005      	1	20040208	G	6320	369D25100505	NOZZLE          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UNIT INSTALLED IN A/C AFTER REPLACEMENT OF CRACKED CASE BY CUSTOMER US REPAIR FACILITY. AFTER INITIAL TEST RUNS IT	 WAS REPORTED TO HAVE VERY LOW OIL PRESSURE, AFTER NUMEROUS HOURS OF TROUBLESHOOTING (PRESSURE PUMP, SWITCH, GAUGE REPLA	CEMENT AND WIRING CHECKS), THE UNIT WAS REMOVED FROM A/C FOR FURTHER INSPECTION. THE T/R O/P PINION WAS REMOVED TO EXPOS	E A LARGE PART OF THE PRESSURE PROBLEM AS THE I/P OIL NOZZLES WERE MISSING. WE HAVE DOCUMENTED THIS ON DIGITALLY WITH PI	CTURES.WE AWAIT FURTHER INSTRUCTION.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2005011200004	20050112	00004	CE  	2005	1	12	CA040209006      	1	20040205	G	2497	P109A20	CONNECTOR       			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ELECTRICAL	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING FOR GROUND POWER SNAG, NOTICED THAT 5A CURRRENT LIMITER FOR HE GROUND POWER ENERGIZATION CI	RCUIT WAS BLOWN. IT SHOULD BE NOTED THAT P109A20 WAS NOT PINNED TO X AT P309, AS WAS INDICATED BY THE WIRE DIAGRAMS FOR 	S/N 31-102. ACFT WIRED AS PER EFFECTIVITY 31-147 AND SUBSEQUENT, WITH P109A20 AT PIN J.				2	L	7	2 	4F	4	F	RT	A10CE   	E6WE
2004032900099	20040329	00099	NM  	2004	3	29	CA040209007      	1	20040206	G	4900	23088002B	STARTER GEN     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	APU	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) APU FAILED TO START, TECHNICIANS FOUND STARTER / GENERATOR BURNED, THE ATTACHED WIRES AND CONNECTORS WERE ALSO FOU	ND DAMAGED.  OPERATOR ADVISED BY THEIR SPARES THAT THE STARTER GENERATOR, P/N 23088-002B SN Y0084 WAS REPAIRED BY THE VE	NDOR ONCE ALREADY. THE GENERATOR WAS REPLACED YESTERDAY AND FAILED AFTER 2 FLIGHTS. THE APU WAS STARTED WITH BATTERY POW	ER.  DUTY CYCLE WAS OBSERVED. TIME SINCE REPAIR: 1.37 CYCLE SINCE REPAIR: 2.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004032900100	20040329	00100	EA  	2004	3	29	CA040209008      	1	20040202	G	2910	6607P953	PRESSURE SWITCH 			DHAV  	DHC6  	DHC6        	2802606	EA  										HYD SYSTEM	OUT OF TOLERANCE	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)  PRESSURE SWITCH HAS A CALIBRATION VARIANCE THAT FALLS OUTSIDE OF THE DRAWING SPECIFICATION. THE ACTUATION OF THE 	UNIT HAS A TIGHTER TOLERANCE FROM ACTUATION, THAN SPECIFIED. THE SWITCH IS DESIGNED TO DEACTUATE, ON DECREASING PRESSURE	, AT A VALUE 150 TO 300 PSI BELOW THE ACTUATION POINT. (DEACTUATION IS LOWER THAN THE 150 PSI BENCH MARK. THIS, IN NO WA	Y, HAS AFFECTED THE RELIABILITY OF THE UNIT.) THERE IS NO CONCERN OF UNITS FUNCTIONALITY OR QUALITY CHARACTERISTICS. IF 	THE TIGHTER TOLERANCE IS ACCEPTABLE/PREFERRED, CUSTOMERS MAY CONTINUE TO USE THEM.		1	H	7	2 	3T			RT	A9EA
2004033000143	20040330	00143	GL  	2004	3	30	CA040209009      	2	20040209	G	7397	JG7039C2C33	WIRE HARNESS    			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13H     	03004	GL  					FUEL QTY	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WINTER MAINTENANCE INSPECTION, WIRES WERE FOUND RUBBING AGAINST EACH OTHER AT A FUEL QUANTITY TRANSMITTER P	ROBE IN THE LT WING AT APPRX WS 253.0.   ONE WIRE HAD CHAFED ENOUGH TO EXPOSED THE BARE WIRE.  ALL OTHER AREAS IN BOTH W	INGS WERE INSPECTED AT THE FUEL QUANTITY PROBES WITH NO OTHER DAMAGE NOTED.				2	L	7	2 	4R	4	T	 	6A6     	E282
2004033000146	20040330	00146	WP  	2004	3	30	CA040209010      	1	20040203	G	2540		WASTE TANK      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LAVATORY	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA											(CAN) ON DESCENT, RT THROTTLE STUCK AT APPROXIMATELY 2 CM ABOVE IDLE POSITION. (UNABLE TO CONTROL POWER ON ENGINE) REGAI	NED CONTROL OF THROTTLE AT 1000 FEET ABOVE GROUND.  FUNCTIONED NORMAL FOR LANDING AND TAXI. MAINTENANCE FOUND ICE BUILD 	UPON RT ENGINE THROTTLE CABLE SYSTEM QUADRANT TO CROSS SHAFT. SYSTEM CLEANED AND CHECKED FREE FOR MOVEMENT. THE ICE BUIL	D UP CAME FROM WATER LEAK FROM RT REAR LAVATORY.  THE LAVATORY FAUCET WAS STUCK OPEN DURING FLIGHT AND OVERFILLED THE WA	STE TANK.  WATER OVERBOARD THE TANK ON THE TOILET FLOOR AND DRIPPED OVER THE ENGINE CONTROL.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004033000147	20040330	00147	EU  	2004	3	30	CA040209011      	1	20040209	G	3297	G21A24	WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG INDICATOR	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) LT MLG GREEN INDICATION WAS INTERMITENTLY LOST.  FAULT COULD BE DUPLICATED BY WIGGLING THE WIRES AT THE ACTUATOR P	LUG.  WIRE G21A24 FOUND BROKEN AT P055 CONNECTOR, REPAIRED, GROUND TESTS SATISFACTORY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004033000148	20040330	00148	NE  	2004	3	30	CA040209012      	2	20040127	G	7321	85634	SHAFT           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					FUEL CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2ADS1203					(CAN) FUEL CONTROL RECEIVED FROM CUSTOMER FOR INSPECTION FOLLOWING PREVIOUS RECORDS ABOUT PUMP FAILURE (WSDR 20040128006	). FUEL CONTROL HAS TSO- 3195.3 AND WAS OPERATING ON EXTENSION TIME DUE TO A GOOD PERFORMANCES.  IT WAS REMOVED FROM A/C	 FOR INSPECTION IAW SB. T5317A-1-107 (CECO SB.73-39).  INSPECTION FOUND WORN EXCESSIVELY, WORN MAIN DRIVE INTERNAL SPLIN	ES, SECONDARY LARGE SPLINE AND PRIMARY PUMP GEAR EXTERNAL SPLINE. THIS IS THIRD CASE OF PUMP-MAIN DRIVE SHAFT FAILURE IN	VESTIGATED.  WE HAVE REPORTED THIS CASE TO MANUFACTURER AND WE ARE WAITING FOR FUTHER GUIDANCE.		1	G	7	1 	4U	4	U	 	H1SW    	E17EA
2004033000149	20040330	00149	EA  	2004	3	30	CA040210001      	1	20040209	G	3310	2LA00691307	LIGHT           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	INOPERATIVE     	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) THE FLIGHT CREW REPORTED, ON POWER UP, SMOKE COMING FROM THE RT SIDE OF COCKPIT.  ADDITIONAL INFORMATION IS THAT T	HE SMOKE WAS COMING FROM AROUND THE FO WINDSHIELD/WINDOW POST.  MAINTENANCE DEFERED THE FLIGHT DECK FLOOD LIGHTS IAW MEL	 33-11-01, AND RETURNED THE AIRCRAFT TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004070900005	20040709	00005	EA  	2004	7	9	CA040210002      	1	20040205	G	2613	601R3103914	CONTROL BOX     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT MLG WW	MISSING         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) PRIOR FIRST FLIGHT OF DAY, PILOT NOTICED THAT GEAR BAY OVERHEAT TEST WAS INOPERATIVE. MECHANIC WENT TO INSPECT LOO	PS IN WHEEL WELL AND DISCOVERED THAT RT WHEEL BIN WAS MISSING.  AFTER INSP, NO DAMAGE WAS FOUND ON FASTENERS HOLES, HOWE	VER SENSING LOOP AC CONNECTOR WAS TORN APART.  CONNECTOR WAS REPAIRED, A NEW WHEEL BIN WAS INSTALLED AND AC RETURNED TO 	SERVICE. OPERATOR LAUNCHED A FLEET INSPECTION ON ALL THEIR AIRCRAFT TO INSPECT WHEEL BIN INSTALLATION, NOTHING ABNORMAL 	WAS FOUND EXCEPT SOME AC HAD A FEW FASTENERS MISSING. AN INTERNAL INVESTIGATION IS CURRENTLY ON GOING AT THIS OPERATOR T	O TRY TO UNDERSTAND THIS OCCURRENCE. NOTE: THE P/N IN QUESTION 601R31039-146.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004033000150	20040330	00150	CE  	2004	3	30	CA040210003      	1	20040208	G	7120	265102215	RING            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE THE ENGINE MOUNT RING (HORSE COLLAR) WAS FOUND CRACKED AT TWO OF THE FOUR CORNERS, INSI	DE JOINT. DUE TO THIS BEING A KNOWN PROBLEM, AN ADDITIONAL TASK CARD TO CHECK FOR THIS CONDITION, INITIATED IN 1999, WAS	 ADDED TO OUR MAINTENANCE SCHEDULE EVERY 100 HOURS. AS A RESULT, WE HAVE DISCOVERED THE CONDITION ON 8 SEPARATE COLLARS.	  THE COLLAR WAS REPLACED AND THE AIRCRAFT RELEASED.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004050700027	20040507	00027	EA  	2004	5	7	CA040210004      	1	20040210	G	3220		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NOSE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UNABLE TO RETRACT NLG ON GEAR UP SELECTION.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004062100145	20040621	00145	CE  	2004	6	21	CA040210005      	1	20040210	G	5230	26012053	HINGE           	CESSNA      		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	CARGO POD DOOR	TORN            	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) ON SHORT FINAL THE PILOT HEARD A LOUD BANG AT THE BEGINNING OF THE FLARE. THE PILOT TAXIED THE AIRCRAFT TO THE CAR	GO RAMP. AFTER THE PILOT GOT OUT OF THE COCKPIT HE NOTICED THAT THE FWD LOWER POD CARGO DOOR WAS MISSING. THE CARGO DOOR	 WAS FOUND ON TOP OF THE SNOW 50 FEET FORM THE THRESHOLD OF THE RUNWAY. THERE WAS NO DAMAGE TO THE AIRCRAFT OR THE DOOR.	 THE ONLY DAMAGE WAS THE TORN HINGE WHERE IT HAD SEPARATED FROM THE DOOR. THE DOOR LATCHING SYSTEM WAS FOUND TO BE OPERA	TING NORMALLY WITH NO DAMAGE OR WEAR TO THE DOOR OR POD ASSY. SUSPECT THAT THE DOOR WAS NOT LATCHED CORRECTLY BEFORE DEP	ARTURE.	1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004040200001	20040402	00001	EU  	2004	4	2	CA040210006      	1	20040206	G	7334	8346	PRESSURE SWITCH 			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	FUEL SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								367302			(CAN) DUE TO INTERNAL LEAKAGE OF DIFFERENTIAL PRESSURE SWITCH, A LOST OF FUEL WAS HAPPENING THRU THE OVERBOARD DRAIN WHI	CH WAS CREATING A PRESSURE DROP IN FUEL PUMP SYSTEM, THE AUX PUMP WOULD THEN COME ON AND OFF THUS CREATING A SMALL FLUCT	UATIONIN THE ENGINE PARAMETERS. AFTER INVESTIGATION AN IMPROVE SWITCH WAS MADE AVAILABLE THRU SB73-011 DUE TO IMPROVED R	ELIABILITY. THE OLD PN 8346 CAN BE NOW IMPROVE BY USING PN 8346-001.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE
2004050700053	20040507	00053	CE  	2004	5	7	CA040210008      	1	20040206	G	3260	1003810061	DOWNLOCK SWITCH 			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	DEFECTIVE       	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			12293								(CAN) ON APPROACH TO HIGH LEVEL WHEN GEAR WAS EXTENDED THE GREEN NOSE GEAR DOWN LIGHT DID NOT ILLUMINATE.  THE RED IN TR	ANSIT LIGHT HAD EXTINGUISHED.  AIRCRAFT LANDED UNEVENTFULLY AND WAS INSPECTED AND DEEMED SAFE FOR SPECIAL FLIGHT PERMIT 	WITH NO PAX.  MAINTENACE FOUND THE NOSE GEAR DOWNLOCK SWITCH TO BE DEFECTIVE.  IT WAS REPLACED AND GEAR SWINGS SHOWED NO	 FURTHER PROBLEMS.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004050700054	20040507	00054	NE  	2004	5	7	CA040211001      	2	20040131	G	7322	2100140007	GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT THROTTLE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT ENGINE WOULD NOT SHUTDOWN AT GATE WITH THRUST LEVER AT SHUT OFF POSITION.  MAINTENANCE REPLACED THE RT THROTTLE	 CONTROL GEARBOX ASSY AND RT MAIN FUEL CONTROL UNIT.  AIRCRAFT RETURNED TO SERVICE.  PARTS REPLACED:  THROTTLE CONT GEAR	 BOX ASSY, P/N: 2100140-007, S/N: 601, MAIN FUEL CONT, P/N: 6078T55P09, S/N: WYG85422,				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004050700055	20040507	00055	EA  	2004	5	7	CA040211002      	1	20040203	G	5610	NP1393219	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT SIDE	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAIN SIDE WINDOW SHATTERED IN CRUISE AT FL370.  AN UNEVENTFUL LANDING FOLLOWED.  THE SIDE WINDOW WAS REPLACED A	ND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004050700056	20040507	00056	SO  	2004	5	7	CA040211003      	1	20040210	G	3245	0923440	TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING , THE PILOT NOTICED A SLIGHT PULL TO THE RT.  WHEN THE PILOT SLOWED THE AIRCRAFT, THE PULL GOT STRONGER	 FOLLOWED BY FLOPPING SOUND.  THE PILOT STOPPED AND SHUT DOWN ON THE RUNWAY.  ON INVESTIGATION OF THE TIRE AND TUBE, A S	MALL .1250  INCH SLIT WAS FOUND IN THE TUBE.  NOTHING SHARP WAS FOUND IN THE TIRE.  SUSPECT THAT THE TUBE HAD A SLIGHT F	OLD ON INSTALLATION AND COLD WEATHER OR RUBBING CREATED A HOLE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004050700057	20040507	00057	WP  	2004	5	7	CA040211004      	1	20040210	G	6310	369F55101	DRIVE SHAFT     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED INSPECTION THE MAIN ROTOR DRIVESHAFT WAS REMOVED AND INSPECTED.  THE DRIVE SPLINES SHOWED EVIDE	NCE OF CORROSION UNDER THE COATING ON THE SPLINES.  ALL SPLINES SHOWED BLACK FLAKES OF THE COATING COMING OFF AND YOU CO	ULD SEE CORROSION UNDER THE COATING.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004050700058	20040507	00058	CE  	2004	5	7	CA040211005      	1	20040123	G	5610	101384025	WINDSHIELD      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DEFECT REPORTED AS,  RT OUTER WINDSHIELD SHATTERED IN FLIGHT.  AIRCRAFT WAS ENROUTE AT FL250 WHEN THE WINDSHIELD S	HATTERED WITH NO PRIOR INDICATIONS AND NO WINDSHIELD HEAT SELECTED, OAT WAS  41C.  THE AIRCRAFT DIVERTED TO HOME BASE.  	UPON INSPECTION IT WAS DISCOVERED THAT THE INNER PANE HAD SHATTERED AND WINDSHIELD REPLACED WITH SUPERCEDED P/N 101-3840	25-24 IAW THE STRESS FREE INSTALLATION KIT INSTRUCTIONS. SCREWS TORQUED FOLLOWING SEALANT CURE TIME.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004040200002	20040402	00002	EA  	2004	4	2	CA040211006      	1	20040205	G	7921	853877	OIL COOLER      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT RETURNED FROM FLIGHT WITH AN EXCESSIVE OIL LEAK ON THE LT ENGINE COWLS. INVESTIGATION DISCOVERED A CRACK 	IN THE OIL COOLER VERNATHERM INLET/OUTLET HOUSING. THE OIL COOLER WAS REPLACED WITH AZERO TIME UNIT AND CHECKED SERVICEA	BLE.THE OIL COOLER HAD BEEN INSTALLED 77.2 HOURS EARLIER AS PART OF A 3000 HOUR BENCH TEST REQUIREMENT.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
2004031500002	20040315	00002	CE  	2004	3	15	CA040211007      	1	20040122	G	5610	10138402524	WINDSHIELD      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDSHIELD INNER LAYER CRACKED IN FLIGHT AT FLIGHT LEVEL 240.  REPORTED OAT -45C.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004031500011	20040315	00011	CE  	2004	3	15	CA040211008      	1	20040122	G	5610	10138402523	WINDSHIELD      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SERVICING THE LT WINDSHIELD WAS FOUND CRACKED IN THE OUTER PLY. REPORTED OAT FOR THE PREVIOUS FLIGHT WAS -4	5C.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004071200163	20040712	00163	SW  	2004	7	12	CA040211009      	1	20040209	G	1430		SCREW           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GOVERNOR	OUT OF ADJUST   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) RT ENGINE WOULD NOT MAKE TARGET TORQUE ON TAKE OFF AFTER 'MAX TORQUE' ADJUSTMENT.  AIRCRAFT ABORTED TAKE OFF AND R	ETURNED TO BLOCKS.  MAINTENENACE FOUND GOVERNOR INTERFERENCE DUE TO INPROPER SCREW 'X' ADJUSTMENT.  SCREW 'X' WAS ADJUST	ED TO MANUFACTURERS SPECIFICATIONS AND AIRCRAFT RELEASED FOR TEST FLIGHT.  AIRCRAFT WAS FOUND SEVICIBLE ON TEST FLIGHT A	ND RELEASED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2004031500012	20040315	00012	SW  	2004	3	15	CA040211010      	1	20040209	G	8012		REGULATOR       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			27214								(CAN) CREW WERE ON A TRAINING FLIGHT AND WENT THROUGH A SIMULATED ENGINE FAILURE. ENGINE WOULD NOT RESTART AFTER 3 ATTEM	PTS. AIRCRAFT RETURNED TO BASE. MAINTENANCE FOUND THE START PRESSURE REGULATOR TO BE AT FAULT.  PART WAS REPLACED AND AI	RCRAFT RETURNED TO SERVICE AFTER SUCCESSFUL ENGINE STARTS IAW MM.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2004031500013	20040315	00013	EU  	2004	3	15	CA040211011      	1	20040114	G	6220	350A31190703	STARFLEX        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M4517					(CAN) ON A ROUTINE AIRFRAME INSPECTION,  A CRACK WAS NOTED ON THE TRAILING EDGE OF THE STAR ARM.  AFTER COMPLETING THE R	EPAIR TO THE AREA IAW THE SRM, IT WAS FOUND TO STILL BE A MUCH DEEPER FLAW.  THE STAR WAS SENT TO MFG FOR FURTHER INVEST	IGATION.  A NEW STARFLEX WAS INSTALLED.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004031500014	20040315	00014	CE  	2004	3	15	CA040212001      	1	20040204	G	5210	051300735	POST            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CREW DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10532								(CAN) DURING 200 HR INSPECTION, CRACK NOTED AT LOWER DOOR HINGE IN LT FRONT DOORPOST.  VISIBLE THROUGH ACCESS HOLE ON IN	SIDE OF POST.  CRACK APPEARS TO HAVE INITIATED DUE TO FLEXING CAUSED BY HINGE PULLING ON POST WHEN DOOR CLOSES.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004031500015	20040315	00015	CE  	2004	3	15	CA040212002      	1	20040130	G	2435	23078330	ARMATURE        	LUCAS       		BEECH 	1900  	1900D       	1154162	CE  										COMMUTATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						97114					(CAN) ONE HALF OF ONE COMMUTATOR BAR MISSING (BROKEN OFF), TIPS OF FAN BLADES BROKEN OFF AND DAMAGED. THE EXACT SEQUENCE	 OF EVENTS CANNOT BE ACCURATELY DETERMINED, BUT IT APPEARS THAT THE PORTION OF THE COMMUTATOR BAR (NOT FOUND) BROKE OFF,	 DAMAGED THE NEAREST BRUSH AND WAS KICKED OUT INTO THE FAN, DAMAGING THE BLADES. BEARINGS SMOOTH, STATOR PASSED ALL CHEC	KS.  PREVIOUS SERVICE WAS A ROUTINE OVERHAUL AND CERTIFICATION OF ALL PARTS INSTALLED IS ON FILE. FAILURE IS UNRELATED T	O WORKMANSHIP. DUE TO THE NATURE OF THIS FAILURE, A COMPLETE OVERHAUL IS NECESSARY.		2	L	7	2 	4T			RT	A24CE
2004031500016	20040315	00016	EU  	2004	3	15	CA040212004      	1	20040203	G	6520	350A020005	GEARBOX         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	MAKING METAL    	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) T/R GEARBOX MAKING METAL. CHIPS DETECTED ON DETECTORS.  REPLACED T/R GEARBOX.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004031500017	20040315	00017	CE  	2004	3	15	CA040212005      	1	20040206	G	5210	50430043619	CHANNEL         	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CABIN DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE DOOR HINGE FOR LOOSE RIVETS, A CRACK WAS DISCOVERED THAT PROPAGATED APPROXIMATELY .7500 T	HE LENGTH OF THE DOOR CHANNEL. THE DOOR WAS REMOVED AND SENT TO AN APPROVED REPAIR STATION.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004031500018	20040315	00018	GL  	2004	3	15	CA040213001      	1	20040209	G	7810	2078000103	EXHAUST STACK   	BOMBDR      		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	CYLINDER HEAD	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LT REAR EXHAUST STACK WAS FOUND COMPLETELY BROKEN AND SEPARATED AT THE BEND NEAR THE CYLINDER.						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO
2004071200171	20040712	00171	CE  	2004	7	12	CA040213002      	1	20040212	G	2720	6233174200	TORQUE TUBE     	CESSNA      		CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					RUDDER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) RECEIVED A RUDDER TORQUE TUBE NOT PROPERLY ASSEMBLED,  FROM A MANUFACTURER.  A RIB WAS NOT INSTALLED CORRECTLY DUR	ING A MANUFACTURING PROCESS.					2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004031500030	20040315	00030	GL  	2004	3	15	CA040213003      	1	20040209	G	7810	2078000107	EXHAUST STACK   	BOMBDR      		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	CYLINDER HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT REAR EXHAUST STACK WAS FOUND CRACKED APPROX .5000  WAY AROUND THE CIRCUMFERENCE AT THE BEND NEAR THE CYLIND	ER.  THIS CRACK WAS IN A SIMILAR LOCATION AS THE ONE THAT LEAD TO THE COMPLETE FAILURE OF THE LT REAR EXHAUST STACK.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO
2004031500038	20040315	00038	EA  	2004	3	15	CA040213004      	1	20040213	G	7830	MPN1267587	POWER UNIT      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					THRUST REVERSER	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LT THRUST UNLOCKED IN CLIMB.  QHR PARTIALLY CARRIED OUT LANDED (WOULD NOT STOW) FELT LIKE IT WAS NEVER DEPLOYED.  	AIRCRAFT CAME BACK FOR TROUBLESHOOTING AND REPAIR.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500039	20040315	00039	EU  	2004	3	15	CA040213005      	1	20040213	G	7830		THRUST REVERSER 			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					ENGINE	SMOKE           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING AND EXITING THE RUNWAY, THE FLIGHT CREW WERE ADVISED BY THE FLIGHT ATTENDANT THAT THE CABIN HAD FILL	ED WITH SMOKE.   ATC CONTACTED AND EMERGENCY VEHICLE RESPONDED.  THE SMOKE IN THE CABIN QUICKLY DISSIPATED AND ATC ADVIS	ED. AFTER DISCUSSION WITH FLIGHT CREW SMOKE WAS INFACT INGESTED SMOKE FROM REVERSERS.  THE CREW LEFT THE REVERSER WELL B	ELOW 60KTS LIMIT. (NO FURTHER ACTION REQUIRED).			2	L	7	2 	4F	4	F	RT	A28NM   	E37NE
2004031500040	20040315	00040	NE  	2004	3	15	CA040213006      	1	20040202	G	6210	6117020201067	SPAR            	SKRSKY      		SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					M/R BLADE	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						61M3314311					(CAN) MAIN ROTOR BLADE LEAK CHECKED AT BASE AND SPAR FOUND TO BE CRACKED.						2	G	7	2 	4U	4	U	 	1H15    	1E3
2004031500041	20040315	00041	EA  	2004	3	15	CA040213007      	1	20040210	G	2720	C2CF209	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RUDDER PEDAL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12498								(CAN) RT RUDDER PEDAL TORQUE TUBE HAD AGGRESSIVE CORROSION BUILD UP ON THE EXTERIOR OF THE TORQUE TUBE IN THE VICINITY O	F THE OIL COOLER. THIS IS A COMMON PROBLEM WITH FLOAT EQUIPPED AIRCRAFT OPERATING IN A SALT WATER ENVIRONMENT.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004031500042	20040315	00042	EA  	2004	3	15	CA040213008      	1	20040210	G	5552	C2T7A	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12498								(CAN) LOSS OF ELEVATOR CABLE TENSION REVEALED WORN ATTACH POINTS ON THE ELEVATOR TORQUE TUBE ASSEMBLY.						1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004031500043	20040315	00043	EA  	2004	3	15	CA040213009      	1	20040210	G	5552	C2TP11	HOUSING         			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			12498								(CAN) LOSS OF ELEVATOR CABLE TENSION REVEALED WORN BEARINGS IN THE C2TP15A HOUSINGS (2), ON REMOVAL OF THE LT HOUSING FO	R BEARING REPLACEMENT A CORROSION ASSISTED CRACK WAS NOTED. FAILURE OF THE BEARING HOUSING WAS NOT EASILY DETECTABLE UNT	IL THE HOUSING ASSEMBLY WAS REMOVED FOR BEARING REPLACEMENT.				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004031500044	20040315	00044	EA  	2004	3	15	CA040213010      	1	20040210	G	2731	C2T41	JACKSCREW       			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ELEVATOR TRIM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12498								(CAN) MINOR CORROSION NOTED ON THE EXTERNAL SURFACE OF THE TRIM DRUM (CABLE GROOVES EXFOLIATING NEAR THE CABLE INDEX PIN	) ON REMOVAL OF THE TRIM DRUM SCREW ASSEMBLY THE MIDDLE PORTION OF THE JACK SCREW PN NR C2T41 WAS FOUND TO BE SEVERELY C	ORRODED IN THE MID PORTION OF THE ACME THREAD.  THIS PART OF THE JACKSCREW IS NOT VISIBLE DURING ROUTINE MAINTENANCE, AN	D REQUIRES THE JACK TO BE DISASSEMBLED TO VERIFY ITS CONDITION.			1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004031500045	20040315	00045		2004	3	15	CA040213011      	4	20040210	G	2562	110324	ANTENNA         	ARTEX       		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ELT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELT ANTENNA FOUND BROKEN AT THE BASE OF THE ANTENNA MOUNTING FLANGE (EXTERNAL).						1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004031500046	20040315	00046	EA  	2004	3	15	CA040215001      	1	20040208	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) TAKE OFF ABORTED AT APPROXIMATIVELY 80 KNOTS BECAUSE RT WINDSHIELD CRACKED. RT WINDSHIELD REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004031500047	20040315	00047	NM  	2004	3	15	CA040216001      	1	20040216	G	2120		ODOR            			BOEING	767   	76735H      	1385208	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					COCKPIT	DETECTED        	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) THE FLIGHT EXPERIENCED AN ACRID ODOR IN THE COCKPIT.  AC DECLARED AN EMERGENCY LANDING AND CARRIED OUT THE QRH. AC	 SENT TO HANGAR FOR INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2004031500048	20040315	00048	WP  	2004	3	15	CA040216002      	1	20040207	G	7933	56B17C	SENSOR          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					OIL TEMP	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) RT ENGINE OIL TEMP EXCEEDED 160 DEGREES DURING CRUISE.  AIRCRAFT DIVERTED.  OIL TEMP SENSOR REPLACED AND AIRCRAFT 	DISPATCHED SERVICEABLE.  ON THE NEXT DAY FEB. 8, 2004, AIRCRAFT DEPARTED  AND SAME PROBLEM CAME BACK DURING CLIMB.   AIR	CRAFT LANDED.  THE OIL TEMP SENSOR WAS REPLACED WITH THE SYSTEM DISPLAY PANEL P/N 201EDP1-1 S/N AD660/072. AIRCRAFT DISP	ATCHED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004031500060	20040315	00060	CE  	2004	3	15	CA040216003      	1	20040114	G	2731	26616151	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELEVATOR TRIM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT WITH AUTOPILOT ENGAGED, PILOT NOTED THAT AIRCRAFT WAS NOT HOLDING ALTITUDE. PILOT DISENGAGED 	AUTOPILOT AND AIRCRAFT PITCHED NOSE UP.  ELECTRIC ELEVATOR TRIM SELECTED BUT NO TRIM MOVEMENT.  ATTEMPTED MANUAL TRIM BU	T TRIM WHEEL WOULD NOT MOVE, SPRING BACK.  PILOT MAINTAINED CONTROL OF AIRCRAFT WITH ELEVATOR AND LANDED WITHOUT INCIDEN	T.  INITIAL INSPECTION UNABLE TO MOVE ELEVATOR TRIM.  AIRCRAFT HANGARED FOR SHORT PERIOD AND TRIM OPERATION OKAY.  ELEVA	TOR TRIM CABLE/CHAIN CIRCUIT INSPECTED, NO DEFECTS. LT AND RT TRIM ACTUATOR DISASSEMBLED AND FOUND MOISTURE. ACTUATORS I	NSPECTED AND LUBRICATED IAW MFG INSTRUCTIONS.	1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004031500061	20040315	00061	NM  	2004	3	15	CA040216004      	1	20040121	G	2910	APT7510004000SG	TRANSDUCER      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING APPROACH TO AIRPORT THE HYDRAULIC ISOLATION VALVE LIGHT ILLUMINATED. THE CREW BROKE OFF THE APPROACH TO CHE	CK LIGHT AND NOTED THE NR 1 HYDRAULIC CONTENTS LOW. AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE PERSONNEL DISCOVERED 	A LEAK FROM THE NR 1 HYDRAULIC STANDBY PUMP PRESSURE TRANSDUCER. NEW TRANSDUCER INSTALLED, HYDRAULIC FLUID REPLENISHED A	ND LEAK CHECKED OKAY. CLOSE INSPECTION OF THE TRANSDUCER FOUND A CRACK IN THE BODY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004031500062	20040315	00062	EA  	2004	3	15	CA040216005      	2	20040110	G	8520	78030	CONNECTING ROD  			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L4427827A			(CAN) ENGINE WAS CONTAMINATED.  ABNORMAL WEAR WAS DETECTED ON FOUR CONNECTING RODS CAUSING METAL CONTAMINATION.  DEMARCA	TION WAS ALSO NOTED ON CRANKSHAFT. AFTER COMPLETING A THOROUGH INSP (MEASUREMENT OF INTERNAL BUSHINGS, A TORSION, PARALL	ELISM, INSPECTION OF CONNECTING RODS, SIDE PLAY INSP OF CONNECTING RODS AND CRANKSHAFT), CONCLUDED THAT ALL MFG INSP REQ	UIREMENTS WERE CARRIED OUT IN CONFORMITY WHEN IT WAS OVERHAULED.  AC WAS IN OPERATION WITH 100 MINERAL OIL (SUMMER OIL) 	BECAUSE 80 MINERAL OIL (WINTER OIL) WAS NOT AVAILABLE.  WE CONCLUDED THAT USE OF 100 MINERAL OIL IN VERY COLD STARTING C	ONDITION CAUSED A LACK OF LUBRICATION IN THIS SPECIFIC AREA.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857
2004031500063	20040315	00063	CE  	2004	3	15	CA040216006      	1	20040213	G	2510	05142132	LOCK            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	COCKPIT SEAT	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING THE PRE-FLT PHASE, THE PILOT ATTEMPTED TO ADJUST THE LT SEAT WHEN THE SEAT BACK DROPPED BACK BEYOND ITS NOR	MAL RANGE OF ADJUSTMENT.  IT WAS DETERMINED THEN THAT THE SEAT WAS NOT IN A SAFE CONDITION TO USE AND THE CREW MADE AN E	NTRY IN THE LOGBOOK THUS GROUNDING THE AIRCRAFT.  CLOSER EXAMINATION OF THE SEAT ADJUSTING MECHANISM BY THE MAINTENANCE 	PERSONNEL REVEALED THAT THE AFT ROD ATTACHMENT FOR THE LOCK CYLINDER HAD SHEARED WHERE THE ROD IS SECURED INTO THE END C	AP. THE CRIMP REMAINED INTACT WHERE AS THE SHEAR OCCURRED JUST FORWARD OF THE CRIMP.  DIRECTLY CAUSING THE SEAT ADJUSTME	NT MECHANISM TO FAIL. A NEW REPLACEMENT PART ORDERED FROM THE MFG.	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004031500064	20040315	00064	NE  	2004	3	15	CA040216007      	2	20040205	G	7220	3036723	RETAINER        								PWA   	120   	PW123D      	52152	NE  					ENG BREATHER	MISSING         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN) ENGINE TSN 13318, TSO291, CSN 13305,AFTER TAKEOFF CONTROL TOWER NOTED FLUID LOSS/SMOKE FROM ENGINE AND INFORMED PI	LOT. PILOT REDUCED POWER AND RETURNED TO DEPARTURE AIRPORT WHERE UNEVENTFUL LANDING WAS MADE. EXAMINATION OF THE ENGINE 	SHOWED BREATHER SHAFT PLUG AND RETAINING CIRCLIP TO BE MISSING. ENGINE REMOVED FOR TEARDOWN TO DETERMINE WHETHER CLIP FR	ACTURED AND ENTERED AGB. OPERATOR IS CHECKING FLEET TO CONFIRM PRESENCE OF CIRCLIP AND PLUG IS PRESENT ON ALL ENGINES. S	HOP HAS IMPLEMENTED DOUBLE WITNESS CHECK OF PLUG & CIRCLIP INSTALLATION.							4	T			E20NE
2004041300029	20040413	00029	GL  	2004	4	13	CA040216008      	1	20040213	G	2510		VISOR           			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					COCKPIT	SEPARATED       	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT WAS MOVING HIS VISOR BACK FROM EXTREME RT SIDE OF VISOR RAIL TO LT, WHEN VISOR FELL OFF RAIL ONTO THROTTLE Q	UADRANT.  LT ENGINE RUN SWITCH ON QUADRANT WAS INADVERTENTLY MOVED TO OFF POSITION BY VISOR IMPACT AND  ENGINE STARTED T	O SHUT DOWN.  PILOT DESCENDED TO FL410 TO KEEP SPEED UP, SELECTED ENGINE RUN SWITCH BACK TO RUN POSITION.  SUCCESSFUL RE	LIGHT OF  ENGINE OCCURRED AND A/C WAS BROUGHT BACK TO FL450 AND TRIP CONTINUED WITHOUT FURTHER INCIDENT.  MAINT CREW RAN	 ENGINES ON GROUND TO VERIFY THROTTLE QUADRANT AND ENGINE RUN SWITCHES FUNCTIONALITY OF ENGINE RUN SWITCH CONFIRMED.  EN	GINE GROUND RUNS PERFORMED BEFORE AIRCRAFT RETURNED TO SERVICE.  NO FURTHER CONCERNS WERE IDENTIFIED.	2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN
2004031500065	20040315	00065	CE  	2004	3	15	CA040217001      	1	20040217	G	7120	265102215	MOUNT           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE THE ENGINE MOUNT RING (HORSE COLLAR) WAS FOUND CRACKED AT TWO OF THE FOUR CORNERS, INSI	DE JOINT.  DUE TO THIS BEING A KNOWN PROBLEM, AN ADDITIONAL TASK CARD TO CHECK FOR THIS CONDITION, INITIATED IN 1999, WA	S ADDED TO OUR MAINTENANCE SCHEDULE EVERY 100 HOURS.  AS A RESULT, WE HAVE DISCOVERED THE CONDITION ON 9 SEPARATE COLLAR	S.  THE COLLAR WAS REPLACED AND THE AIRCRAFT RELEASED.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004031500069	20040315	00069	SW  	2004	3	15	CA040217002      	1	20040211	G	5210	44P14	HOSE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	DOOR SEAL	CRACKED         	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) THE HOSE THAT SUPPLIES THE CABIN DOOR SEAL CRACKED,  ALLOWING THE SEAL TO DEFLATE WHICH IN TURN ALLOWED THE CABIN 	OF THIS FREIGHTER TO DEPRESSURIZE AT 17000 FT.  THE CREW DESCENDED TO A SAFE ALTITUDE AND COMPLETED THE FLIGHT.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2004031500070	20040315	00070	CE  	2004	3	15	CA040217003      	1	20040217	G	3040	KRP3DH24	RELAY           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	WINDSHIELD	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING OF THE WINDSHIELD HEAT AUTO FUNCTION, THE AUTO RELAY WAS FOUND TO BE INTERNALLY SHORTED AND	 HAD MELTED THE CLEAR CASE. THE RELAY WAS REPLACED AND THE AIRCRAFT RELEASED.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004031500071	20040315	00071	EA  	2004	3	15	CA040217005      	2	20040210	G	8520	LW13521	BEARING         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CONNECT ROD	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								L2549440A			(CAN) NR 5 CONNECTING ROD BEARING FAILED.  BEARING FACE MATERIAL WAS BREAKING AWAY FROM BEARING.  METAL CONTAMINATION WA	S NOTED DURING PREFLIGHT CHECK. CONNECTING ROD BEARING HAD LOST APPROXIMATELY 15 PERCENT OF TOTAL SURFACE AREA.  BOTH TH	E CRANKSHAFT AND IDLER GEAR HAD RECEIVED SIGNIFICANT DAMAGE TO THEIR TEETH.  BOTH GEARS HAD TO BE REMOVED FROM SERVICE.				1	G	7	1 	3O	3	O	 	H11NM   	E295
2004031500074	20040315	00074	NM  	2004	3	15	CA040217008      	1	20040213	G	2750	696670833	CONTROL CABLE   			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					LT IB FLAP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, IT WAS OBSERVED THAT THE LT IB FLAP ASSY WAS DROOPING. UPON FURTHER INVESTIGATION, T	HE CABLE ASSY WAS FOUND FRAYED AND BROKEN. A NEW CABLE ASSY WAS INSTALLED IAW MM 27-51-5 AND FUNCTIONED SERVICEABLE IAW 	MM 27-51-0.  NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004031500078	20040315	00078	SW  	2004	3	15	CA040217009      	1	20040210	G	2497	206075559005	CONNECTOR       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					LEAD GRD CONNECT	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BURNED CABLE CONNECTORS AT FUSELAGE GROUND CONNECTION. LOOSE/CORRODED CONNECTION. CABLE ASSEMBLY REPLACED. THIS MA	Y HAVE CONTRIBUTED TO EARLIER PROBLEMS WITH RCR /VOLT.REG. (CABLE K5B8N AND K5D8N)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004031500084	20040315	00084	EU  	2004	3	15	CA040217012      	1	20040216	G	2435	23085024	STARTER GEN     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	INOPERATIVE     	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING AN ENGINE START THE PILOT NOTED THERE WAS AN ABNORMAL NOISE GENERATING FROM THE ENGINE. THE NOISE WAS NOTIC	EABLE AROUND 10 PERCENT GG SPEED AND DISAPPEARED AFTER STABLE RPM WAS REACHED AT 17 PERCENT GG SPEED. THE STARTER GENERA	TOR WAS REPLACED AND THE NOISE HAS NOT REOCCURRED. NO FURTHER ACTION REQUIRED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004031500085	20040315	00085	WP  	2004	3	15	CA040217013      	2	20040211	G	7240	31016687	COMBUSTION LINER			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	CRACKED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) THE LT ENGINE WOULD NOT PRODUCE RATED POWER, IN FACT IT ONLY WENT TO 80 PERCENT. THE CREW ABORTED THE TAKEOFF ROLL	 AND RETURNED TO THE HANGAR.  ON INVESTIGATION, A CRACK WAS FOUND ON THE LOWER CENTER OF THE COMBUSTION CASE. THE CRACK 	GOES AROUND AN UNUSED PORT ON THE CASE.  THIS APPEARS AT FIRST GLANCE TO BE VERY SIMILAR TO A PREVIOUS PROBLEM HAD WITH 	ANOTHER ENGINE OF THE SAME TYPE. ON THAT ONE IT TURNED OUT TO BE A FAILED SECOND STAGE COMPRESSOR IMPELLER THAT WAS CAUS	ING DAMAGING VIBRATIONS.		2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE
2004031500086	20040315	00086		2004	3	15	CA040218001      	4	20040212	G	2216	40002928511	SERVO           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR TRIM	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ELEVATOR TRIM SERVO WAS VERY NOISY REMOVED FOR REPAIR. LOANER INSTALLED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500087	20040315	00087		2004	3	15	CA040218002      	4	20040212	G	2216	40002928511	SERVO           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR TRIM	JAMMED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN TRIM WAS TESTED BY THE PILOT, THE TRIM SERVO JAMMED AND COULD NOT BE RELEASED. THE FLIGHT WAS CANCELLED. INST	ALLED LOANER NEXT DAY AIRCRAFT SERVICEABLE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500088	20040315	00088	EA  	2004	3	15	CA040218003      	2	20040212	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) OVERHAUL ENGINE WAS INSTALLED AT 7117.6. IN THE PROCESS OF DOING A 100 HOUR, FOUND NR 1 CYLINDER VERY LOW ON COMPR	ESSION. REPLACED CYLINDER WITH OVERHAULED CYLINDER. CHECKED COMPRESSION AFTER INSTALLATION AND COMPRESSION WAS WHERE IT 	WAS SUPPOSED TO BE. GROUND RUN NO FAULTS FOUND.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500099	20040315	00099	EA  	2004	3	15	CA040218004      	2	20040212	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) OVERHAUL ENGINE WAS INSTALLED AT 7117.6. IN THE PROCESS OF DOING A 100 HOUR FOUND NR 6 CYLINDER VERY LOW ON COMPRE	SSION. REPLACED CYLINDER WITH OVERHAUL CYLINDER CHECKED COMPRESSION AFTER INSTALL, COMPRESSION WAS WHERE IT WAS SUPPOSED	 TO BE. GROUND RUN NO FAULTS FOUND.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500100	20040315	00100	EU  	2004	3	15	CA040218005      	1	20040218	G	7830		THRUST REVERSER 			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					NR 1 ENGINE	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER T/O ROTATION ECAM ENG. NR 1 REV. UNLOCKED. NO BUFFET EXPERIENCED. JETTISONED FUEL AFTER ECAM AND RET	URNED TO LAND, OVERWEIGHT 229,000, VERTICAL SPEED AT TOUCHDOWN ESTIMATED APPROX 300/FTM.  THRUST REVERSER PLACED UNDER M	EL 78-30-01.  IAW REQUEST FROM MOC DFDR REMOVED FOR POSSIBLE INVESTIGATION.				2	L	7	4 	4F	4	F	RT	A197    	E37NE
2004031500101	20040315	00101	CE  	2004	3	15	CA040218007      	1	20040128	G	5610	5042006937	WINDSHIELD      			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOTS FRONT WINDOW CRACKED ACROSS WINDOW ON OUTER PANE.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC
2004031500102	20040315	00102	GL  	2004	3	15	CA040219001      	1	20040216	G	7810	2078000107	EXHAUST STACK   			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	CYLINDER HEAD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT REAR EXHAUST STACK WAS FOUND TO BE COMPLETELY FRACTURED IN TWO AT THE BEND NEAR THE CYLINDER HEAD. THIS FAI	LURE IS THE SECOND COMPLETE FRACTURE NOTED IN THE PAST WEEK. A THIRD EXHAUST STACK WAS FOUND CRACKED IN THE SAME LOCATIO	N DURING THE PREVIOUS WEEK.				1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO
2004031500103	20040315	00103	NE  	2004	3	15	CA040219002      	2	20040219	G	7200		ENGINE          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NR 1	STALLED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR 1 ENGINE STALL IN CRUISE.  DUE TO HISTORY MTC ADVISED RETURN FOR INVESTIGATION AND FURTHER T/S.  DFDR PULLED.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004031500104	20040315	00104	NE  	2004	3	15	CA040219003      	2	20040218	G	7200	JT8D15A	ENGINE          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					NR 1	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								685598			(CAN) UPON THE TRANSITIONING FROM CLIMB TO CRUISE, A LOUD BANG WAS HEARD AND SUBSEQUENT VIBRATION FELT THROUGHOUT THE AI	RFRAME.  ALL NR 1 ENGINE PARAMETERS IMMEDIATELY BEGAN TO DETERIORATE RAPIDLY. AT FL280, ENGINE FAILURE DRILL INITIATED A	ND COMPLETED.  ATC ADVISED OF ENGINE FAILURE.  EMERGENCY DECLARED AND AIRCRAFT RETURNED.  EMERGENCY CREW MET AIRCRAFT AN	D AFTER INSPECTION OF ENGINE, AIRCRAFT WAS THEN TAXIED BACK TO RAMP AND SHUT DOWN.  MORE TO FOLLOW AFTER INVESTIGATION.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004031500116	20040315	00116	EA  	2004	3	15	CA040219005      	1	20040129	G	2701	C3CF3915	CONTROL COLUMN  			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14020								(CAN) CONTROL COLUMN FOUND CRACKED IN THREE LOCATIONS WHEN SB 3/39 CW.						1	H	7	1 	3R	4	T	 	A815    	E4EA	6	C	P15EA
2004031500126	20040315	00126	SO  	2004	3	15	CA040219006      	1	20040218	G	3213	4041304	AXLE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	BROKEN          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			16094								(CAN) PILOT WAS TAXIING OUT FOR TAKEOFF WHEN THE AXLE BROKE. VIBRATION AND NOISE WAS HEARD. TAXIED BACK AND DISCOVERED T	HE MAIN WHEEL HAD TILTED OVER AND WAS RUBBING ON THE FORK ASSEMBLY.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004031500127	20040315	00127	EA  	2004	3	15	CA040220001      	2	20040219	G	8520		PISTON RING     			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER NR 4 REMOVED DURING 100 HR INSPECTION DUE TO OIL CONTAMINATED SPARK PLUG. TOP COMPRESSION RING FOUND IN S	EVERAL PIECES EMBEDDED INTO PISTON. ALL CYLINDERS REMOVED FROM BOTH ENGINES, 8 TOTAL AND 3 OTHER PISTONS FOUND WITH CRAC	KED TOP COMPRESSION RINGS. NOTE THAT ALL OTHER CHECKS WHERE NORMAL, COMPRESSION TEST RESULTS ABOVE 70PSI.  AFFECTED CYLI	NDERS SENT TO OVERHAUL FACILITY FOR REPAIR/REPLACEMENT.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004031500128	20040315	00128		2004	3	15	CA040220002      	4	20040211	G	3416	24929412	ALTIMETER       			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A36      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA						1535					(CAN) CAPTAIN'S ALTIMETER ERROR OF APPROXIMATELY 1,000 FEET CHECKED OK PRIOR TO DEPARTURE. NOT SURE WHEN FAILURE OCCURRE	D, BUT NOTICED ERROR AT LEVEL CRUISE.  MAINTENANCE CONFIRMED NO STATIC SYSTEM LEAKS.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA
2004031500129	20040315	00129	CE  	2004	3	15	CA040220003      	1	20040211	G	3234	404EN16	SWITCH          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A36      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG SELECTOR	CONTAMINATED    	W				A				UNSCHED LANDING         				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) LANDING GEAR FAILED TO EXTEND WHEN SELECTED. APPROXIMATELY 1-5 MINUTES GEAR EXTENDING WITH NO ADDITIONAL CREW ACTI	ONS. AIRCRAFT RETURNED TO MAINTENANCE BASE. AIRCRAFT EXPOSED TO -30 DEGREES COLD SOAK FOR APPROXIMATELY 3 HOURS. AIRCRAF	T PREVIOUS OPERATED IN WARM CLIMATES FOR 20 YEARS. MAINTENANCE FOUND VERY DIRTY AND (GUMMED) SWITCHES IN LANDING GEAR CO	NTROL HANDLE. FIRST EXPOSURE TO COLD CONDITIONS SINCE IMPORT.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA
2004031500130	20040315	00130	WP  	2004	3	15	CA040220004      	1	20040216	G	2410	902241	WHEEL           	PRESTOLITE  		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ALTERNATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						F219612E					(CAN) BROKEN ALTERNATOR FAN WHEEL.  REPLACED WHEEL.						1	G	7	1 	3O	3	O	 	H11NM   	E295
2004031500131	20040315	00131	WP  	2004	3	15	CA040220005      	1	20040211	G	7711	LC80E1	TRANSMITTER     			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					EPR	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) TAKEOFF REJECTED DUE TO RT ENGINE EPR INDICATION INOPERATIVE.  AIRCRAFT WAS DISPATCHED IAW MEL 77-1 FOR THE DAY. E	PR TRANSMITTER REPLACED ON THE FOLLOWING DAY AND AIRCRAFT DISPATCHED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004031500134	20040315	00134	CE  	2004	3	15	CA040220006      	1	20040213	G	2820	05001183	LINE            			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C172	1C172MTM    	GL  	FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL LINE WAS FOUND CHAFED DURING 200 HR INSPECTION.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004031500148	20040315	00148	CE  	2004	3	15	CA040220007      	1	20040218	G	2133	47061	VALVE           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENERGENCY PRESS	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING THE CLIMB THE AIRCRAFT EMERGENCY PRESSURIZATION VALVE OPENED WITH OUT BEING SELECTED. THE CREW DEPRESSURIZE	D THE AIRCRAFT AND RETURNED TO BASE. THE EMERGENCY PRESSURIZATION VALVE WAS REPLACED AND THE AIRCRAFT SYSTEMS FUNCTION C	HECKED SERVICABLE				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
2004031500149	20040315	00149	EA  	2004	3	15	CA040220008      	2	20040218	G	7510	909100999	HOSE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ANTI ICE SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT COWL ANTI ICE FLEX HOSE FOUND CRACKED DURING OPS 1 INSPECTION.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004031500150	20040315	00150	EA  	2004	3	15	CA040220009      	2	20040202	G	7220	109910029121	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) LOWER FORWARD COWL AIR INLET DUCT CRACKED. REPAIR TO BE ACCOMPLISHED IAW MFG FIELD REPAIR PROCEDURE.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004031500151	20040315	00151	CE  	2004	3	15	CA040220010      	1	20040202	G	5610	10138402523	WINDSCREEN      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIR CREW REPORTED THAT THE PILOTS WINDSCREEN WAS DISCOLOURED AT THE OB EDGES AND HAD A MILKY APPEARANCE. THE WINDS	CREEN HAD PREVIOUSLY BEEN REPAIRED BY THE MFG. THE WINDSCREEN WAS REPLACED WITH A NEW UNIT AND THE DAMAGED UNIT WAS RETU	RNED TO THE MFG FOR EVALUATION.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004050300220	20040503	00220	GL  	2004	5	3	CA040222001      	1	20040220	G	2752		SEAL            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IT WAS FOUND THAT THE SPLINED RUBBER SEAL PUSHED OUT OF POSITION ON FLAP ACTUATOR ROD ASSY.  ON THIS AIRCRAFT IT D	ID NOT MAKE CONTACT WITH THE FLAP POSITION SWITCHES. THE COMPLETE ASSY WAS REMOVED AND SENT  FOR INSPECTION. NEW ASSY IN	STALLED.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004031500152	20040315	00152	EU  	2004	3	15	CA040223001      	1	20040221	G	2597	RDAV400111	WIRE            			AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					VIDEO SYSTEM	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLE SHOOTING THE NON-DEPLOYMENT OF A VIDEO MONITOR IT WAS FOUND THAT THE JUNCTION BOX FOR THIS MONITOR H	AD FAILED. THE UNIT SMELLED OF BURNED ELECTRICAL MATTER. THERE WHERE SIGNS OF ARCING SHOWING ON THE OUTSIDE CASE. THE AS	SOCIATED MONITOR DID NOT WORK AND DID NOT WORK WITH ANOTHER JUNCTION BOX. BOTH THE MONITOR AND JUNCTION BOX WERE REPLACE	D AND FUNCTIONED SERVICEABLE. THE JUNCTION BOX WILL BE INVESTIGATED.			2	L	7	2 	4F	4	F	RT	A28NM   	E40NE
2004031500153	20040315	00153	NM  	2004	3	15	CA040223002      	1	20040217	G	5610	56100165	WINDOW          			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON ARRIVAL AT GATE THE CREW NOTICED F/O NR 4 EYEBROW WINDOW CRACKED. SUSPECT INTERNAL O/HEAT WINDSHIELD SYSTEM C	HECKED SERVICEABLE NR 4 EYEBROW WINDOW REPLACED AIRCRAFT RETURNED TO SERVICE					2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004031500154	20040315	00154	EU  	2004	3	15	CA040223003      	1	20040216	G	2910	10546641	MANIFOLD        			BOLKMS	117   	BK117A1     	5626010	EU  										HYD SYSTEM	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UNIT SENT FROM THE USA FOR RECTIFICATION OF SEAL LEAKS. DURING DISSASEMBLY EXCESSIVE CORROSION WAS FOUND IN ONE OF	 THE VALVE MANIFOLD ATTACHMENT BOLT HOLES. BORE NOMINAL DIMENSION IS 6.4MM, BORE OVERSIZED TO 7.4MM AND CORROSION DAMAGE	 REMAINED. PART SCRAPED. BORE POSSIBLY DAMAGED DURING A PREVIOUS INSTALLATION OF THE BOLT.				1	G	7	2 	3U			 	H13EU
2004031500163	20040315	00163	CE  	2004	3	15	CA040224001      	1	20040218	G	7830	282D0007505	PRESSURE SWITCH 	EATON       		LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					HCU	FALSE INDICATION	W				O				OTHER                   				L	J		NO TEST                   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING AIRCRAFT, FLIGHT CREW INCREASE ENGINE POWER.  ONE THRUST REVERSER LIGHT STAYS ON. AFTER TROUBLESHOOT	ING, MAINTENANCE REPLACED HYDRAULIC CONTROL UNIT. THE PRESSURE SWITCH INSIDE THE HCU GIVES A FALSE INDICATION. AIRCRAFT 	RETURN TO SERVICE.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
2004032500026	20040325	00026	EA  	2004	3	25	CA040224002      	2	20040216	G	7261		OIL SYSTEM      			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA								PCE51909			(CAN) PILOT REDUCED ENG POWER FOR LANDING AFTER FIRST FLIGHT OF DAY,  RT ENGINE PRESSURE DECREASE WAS OBSERVED. TECH DIS	COVERED  LARGE QUANTITY OF CARBON IN ENGINE OIL FILTER. ENGINE WAS REMOVED AND SENT TO MFG FOR INVESTIGATION.  ENGINE WA	S DISSEMBLED AT THE (C FLANGE) FOR AN ITT PROBLEM. AFTER REASSEMBLY, ALL GROUND TESTS WERE PERFORMED AND AC WAS RETURNED	 TO SERVICE AND ENGINE OIL WAS ADDED. AN INTERNAL INVESTIGATION DETERMINED THAT CARBON DISCOVERED IN FILTER WAS MADE OF 	LITTLE BLACK STONES. FUNNEL THAT WAS USED TO ADD ENGINE OIL WAS LOCATED, INSPECTED AND CLEANED AND SAME LITTLE BLACK STO	NES WERE DISCOVERED IN THE FUNNEL. WE WERE NOT ABLE TO DETERMINE THE ORIGIN OF THE LITTLE BLACK STONES.	1	L	7	2 	3T	4	T	 	A8EA    	E4EA	6	C	P15EA
2004031500164	20040315	00164	CE  	2004	3	15	CA040224003      	1	20040216	G	3240		RIVET           	CLEVELAND   		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	BRAKE PAD RIVETS	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1544					(CAN) BRAKE ASSEMBLY S/N 1544 WAS FOUND WITH THE BRAKE PAD RIVETS SHEARED ALLOWING THE PADS TO BECOME DISLODGED, THIS IS	 THE SECOND TIME WE HAVE HAD WEAR PADS BEING DISLODGED FROM THE PRESSURE PLATE ASSEMBLY.  THIS BRAKE ASSEMBLY WAS IN SER	VICE FOR ONE YEAR SINCE NEW.  NO TIMES AVAILABLE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004050300221	20040503	00221	EA  	2004	5	3	CA040224004      	2	20040217	G	7310	3011587	BEARING         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FCU ROD END	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION, THE ROD ENDS WERE FOUND TO BE BADLY WORN ON THE ROD FROM THE START CONTROL TO FUEL CONTROL UNIT.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC
2004050300222	20040503	00222	NM  	2004	5	3	CA040224005      	1	20040224	G	3220	65462154	TORQUE LINK     			BOEING	737   	7372T2      	1384491	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33572								(CAN) DURING THE SCHEDULED NOSE LANDING GEAR SEAL CHANGE AT THE C CHECK, A CRACK WAS DISCOVERED AT THE LOWER TORQUE LINK	 ATTACHMENT LUG.  THE FINDING RESULTED IN THE TORQUE LINK BEING REPLACED.  NOTE A FLEET CAMPAIGN HAS BEEN ISSUED TO VISU	ALLY INSPECT ALL TORQUE LINKS ON FLEET.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004042700073	20040427	00073	EU  	2004	4	27	CA040224006      	1	20040220	G	3260		WARNING LIGHT   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT MLG	ILLUMINATED     	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) 3 GREEN ANNUNICATOR LIGHTS CAME AS WELL AS RED WARNING LIGHT ON LT MLG.  AC DID FLY OVER TO CONFIRM LT MLG WAS DOW	N.  PILOT SELECTED 30 DEGREES OF FLAP TO SLOW AC DOWN. WHEN 30 DEGREES OF FLAP WAS REACHED, 3 RED WARNING LIGHTS FOR LT 	MLG CAME ON.  AC LANDED WITHOUT INCIDENT. WHEN TAXING TO HANGAR, FLAPS WERE RETRACTED TO 15 DEGREES, 3 RED WARNING LIGHT	S WENT OUT INDICATING LT MLG SYS WAS NORMAL. AC JACKED AND MLG CYCLED TO DUPLICATE PROBLEM. SYS OPERATED NORMAL. PINS OF	 CONNECTOR WERE SPRAYED WITH ELECTRICAL CONTACT CLEANER AND REINSTALLED ON TO ACTUATOR. OTHER WIRES IN SYS WERE INSPECTE	D, LT MLG CYCLED SEVERAL TIMES AND NO DEFECTS FOUND. AC WAS RELEASED BACK TO SERVICE.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004031500170	20040315	00170		2004	3	15	CA040225001      	4	20040213	G	3497	MS2536175	CIRCUIT BREAKER 			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					EDU	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE OFF ROLL (LESS THAN 20 KTS), THE CAPT'S PFD, MFD,  NR 2 EDU AND NR 1 RTU WENT BLANK THAN CAME BACK ON.	  REPLACED 75 AMP. DC ESS FEED, CIRCUIT BREAKER IN LT DCPC.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004031500175	20040315	00175	EA  	2004	3	15	CA040225002      	1	20040218	G	3340	2LA00691307	LIGHT           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	INOPERATIVE     	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) FLOODLIGHT CAUSED SMOKE IN THE FLT DECK.  CB POPPED AND WHEN FLOOD LIGHT WAS TURNED OFF IT QUIT SMOKING.  FLOOD LI	GHT ASSEMBLY WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004031500176	20040315	00176	EA  	2004	3	15	CA040225003      	1	20040220	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE FIRST OFFICER'S SIDE WINDOW HAD A PLY CRACK. THE SIDE WINDOW WAS THE OLDER CONFIGURATION. THE WI	NDOW WAS REPLACED IAW AMM.					2	L	7	2 	4F			RT	A21EA
2004050300224	20040503	00224	NE  	2004	5	3	CA040225004      	2	20040225	G	7200		ENGINE          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NR 1	STALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REPEAT NR 1 ENG STALL. (MORE INFO WILL FOLLOW)						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004031500177	20040315	00177	CE  	2004	3	15	CA040225005      	1	20040121	G	2710	051010513	CONTROL CABLE   			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FRAYED AT PULLEY AREA. WING ROOT PULLEY WAS NOT SEIZED.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
2004031500180	20040315	00180	EA  	2004	3	15	CA040225008      	1	20040223	G	5247	70821271	BRACKET         			CNDAIR	CL600 	CL6002C10   	1390015	EA  										APU DOOR	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) APU SHUT DOWN BY ITSELF UPON LANDING AT APROX. 100 KTS. INVESTIGATION REVEALED THAT 2 BOLTS MS9556-45 SECURING APU	 INLET DOOR ARM TO CLAMP WERE NOT TORQUED PROPERLY AND INLET DOOR SHAFT SLIPPED AND CLOSED DOOR UPON FINAL LANDING DUE T	O VIBRATION. APU SHUT DOWN WAS IMMINENT. ATTEMPT TO RESTART DURING TAXI WAS UNSUCCESSFUL. IN 2 PREVIOUS FLIGHT, APU SHUT	 DOWN OCCURRED AT 41000 FT AT 4.5 HRS.  DOOR RIGGING WAS ADJUSTED BUT REAL CAUSE NOT YET DISCOVERED AT THAT POINT. 2 BOL	TS WERE RETORQUED AND FUNCTIONAL CHECK CARRIED OUT AND FOUND SERVICEABLE.		2	L	7	2 	4F			RT	A21EA
2005011200005	20050112	00005	EA  	2005	1	12	CA040225010      	1	20040224	G	5220	CC670380011	ESCAPE HATCH    			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	UNLOCKED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) IMMEDIATELY FOLLOWING FINAL LANDING WHILE DECELERATING THROUGH 70 KTS & DEPRESSURIZING AIRCRAFT, COCKPIT ESCAPE HA	TCH FELL OPEN INSIDE THE COCKPIT. INVESTIGATION REVEALED THAT NEITHER THE PILOT OR THE ACA HAD CONFIRM ALIGNMENT OF LOCK	 PINS WITH GREEN BANDS BEFORE INTENDED FLIGHT BUT THE HANDLE WAS STOWED. COMPLETE MANUFACTURING FUNCTIONAL CHECK WERE CA	RRIED OUT ON THEESCAPE HATCH AND WAS FOUND SERVICEABLE. SUSPECT DOOR NOT PROPERLY LOCKED (POSIT IVELY) AND VIBRATIONS AN	D MULTIPLE LANDINGS WAS SUFFICIENT TO COMPLETELY UNLOCK THE PINS AND OPEN THE DOOR. THE HATCH COULDN'T BE OPEN WHILE PRE	SSURIZED. ISOLATED CASE. PILOT CHECK LIST WILL BE REVISED TO SHOW DOOR CLOSED AND LOCKED IN LIEUOF CLOSED AND LATCHED.	2	L	7	2 	4F			RT	A21EA
2004032500036	20040325	00036	CE  	2004	3	25	CA040225011      	1	20040224	G	2750	14601008	CONTROL CABLE   			CESSNA	337   	337A        	2075704	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP CABLES REMOVED FOR INSPECTION DUE TO SERVICE DIFFICULTY ALERT AL-2003-05. LT AND RT OUTBOARD FLAP CABLES FOUN	D TO BE FREYED AT THE INBOARD BELLCRANK, APPROXIMATELY 1 INCH FROM THE SWAGGED TERMINAL. BOTH CABLES ARE ORIGINAL CESSNA	 FLAP CABLES AND WERE REPLACED WITH NEW CESSNA FLAP CABLES. ALSO, THE RT, INBOARD FLAP CABLE WAS FREYED AT THE INBOARD B	ELLCRANK, APPROXIMATELY 1 INCH FROM THE SWAGGED TERMINAL.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA
2004050300230	20040503	00230	NM  	2004	5	3	CA040225012      	1	20040225	G	2710	550030017	ACTUATOR        			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					RT AILERON	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			66125								(CAN) EICAS MESAGE AILERON LOCKOUT, FOUND RT AILERON LOCK OUT ACTUATOR STUCK IN THE EXTEND POSITION, ACTUATOR REPLACED.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2004050300232	20040503	00232	SW  	2004	5	3	CA040225013      	1	20040218	G	2140		BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HEATER	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT PILOT COULD SMELL SOMETHING ABNORMAL, HE LOOKED AT CB PANEL AND NOTICED HELICRAFT HEATER CB SWITCH H	AD TRIPPED. HE THEN TURNED OFF BLEED AIR TO PREVENT HEAT DAMAGE, ONCE BLOWER WAS REMOVED IT WAS DETERMINED THAT THE BEAR	INGS HAD FAILED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004032500037	20040325	00037	CE  	2004	3	25	CA040225014      	1	20040224	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	337A        	2075704	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP CABLES REMOVED FOR INSPECTION, REFERENCE SD ALERT AL-2003-05 IB FLAP CABLE, RT SIDE, PART NR 1460100-7 FRAYED	 APPROX 50 PERCENT AT IB BELLCRANK. 1 INCH FROM SWAGGED TERMINAL. ALSO BOTH OB CABLES PN 1460100-8 FRAYED AT IB BELLCRAN	K, APPROX. 1 INCH FROM SWAGGED TERMINAL. ALL CABLES ARE ORIGINAL FLAP CABLES AND HAVE BEEN REPLACED WITH NEW FLAP CABLES	 SUPPLIED BY MFG.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA
2005011200006	20050112	00006	GL  	2005	1	12	CA040225015      	3	20040218	G	6114	A251352	BOLT            			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER BOLTS WERE BEING INSTALLED AND TORQUED TO THE SPECIFIED VALUE OF 25 - 30 POUNDS FOOT. AS THE TORQUE WAS 	REACHING APPROXIMATELY 27 FOOT POUNDS, THE BOLT BROKE. THE BREAK WAS WHERE THE THREADS MEET THE GRIP. A SECOND BOLT WAS 	TORQUED AND IT BROKE AT APPROXIMATELY THE SAME TORQUE VALUE AND AT THE SAME LOCATION.				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2005011200007	20050112	00007	CE  	2005	1	12	CA040225016      	1	20040219	G	3397		LIGHT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PAX CABIN	MISWIRED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A 1900 D LANDED AT A MX BASE WITH 3 ELECTRICAL SNAGS. CABIN LIGHTS WOULD INTERMITTENTLY CHANGE FROM PARTIAL TO FUL	L. ON LANDING, GROUND FINE SELENOIDS WERE CHANGING FROM FLT MODE TO GROUND MODE AND STEERING DISCONNECT ACTUATOR CYCLED 	FROM GROUND TO FLT MODES NUMEROUS TIMES. IN DEPTH INVEST REVEALED THAT WIRING OF CABIN & READING LIGHTS WAS NOT IN ACCOR	DANCE WITH WIRING MANUAL. IT APPEARS FROM MANUFACTURE, THE POSITIVE LEAD WAS NOT ALWAYS INSTALLED ON HOT SIDE OF BULBS. 	GENERAL FEELING IS THAT THE ELECTRICAL BUSS WAS BEING BACKFED 28VDC. THE LIGHTING SYSTEM WAS REWIRED IAW THE WIRING MANU	AL AND ALL THREE SYSTEMS FUNCTIONED NORMALLY. A FLEET WIDE INSPECTION AND RECTIFICATION OF THE WIRING IS IN PROGRESS.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005011200008	20050112	00008	EU  	2005	1	12	CA040225017      	1	20040224	G	2750	5757117701600	SENSOR          			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF ABOUT 100 FOOT ABOVE GROUND LEVEL FLAPS LOCK ECAM MESSAGES, TRIED RESET , NIL FIX, RETURN TO GATE. 	RESET OF THE COMPUTER SLAT FLAP COMPUTERS ON GROUND FIXED THE PROBLEM BUT SAME THING HAPPENNED ON THE SECOND ATTEMPT. AI	RCRAFT UNDER INVESTIGATION				2	L	7	4 	4F	4	F	RT	A197    	E37NE
2004050300240	20040503	00240	EA  	2004	5	3	CA040226001      	1	20040221	G	2497		VOLT REGULATOR  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELECTRICAL	FAILED          	W				A				UNSCHED LANDING         				B	G	H	SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   	CR	CRUISE         	1			CA											(CAN) AFTER DEPARTURE, THE AIRCRAFT SUFFERED A COMPLETE ELECTRICAL FAILURE. THE CREW NOTICED A BURNING ODOR. THE AIRCRAF	T RETURNED WITHOUT FURTHER INCIDENT. UPON INVESTIGATION IT SEEMS LIKE A VOLTAGE SURGE OCCURRED, BOTH GPS ACU'S, BOTH COM	M'S, RCR, DME, NR 1 NAV, NR 1 VOLTAGE REGULATOR ARE ALL UNSERVICEABLE AFTER THE EVENT.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2004032500038	20040325	00038	EU  	2004	3	25	CA040226002      	1	20040217	G	6410	10531980	BLADE           	UROCOP      		BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR	PEELING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR BLADES RECEIVED FROM MFG WITH THE PAINT REFINISHED AFTER REPAIR OR INSPECTION ARE PEELING OR SHREDDING 	TO THE BLADE BODY SURFACE BELOW.  THIS IS OCCURRING USUALLY WITHIN THE FIRST 100 HOURS OF OPERATION.  THE NEW REFINISHED	 PAINT SURFACE IS THICK ENOUGH TO PROTRUDE CONSIDERABLY ABOVE THE LEADING EDGE ABRASION STRIP CAUSING THE PAINT TO PEEL 	BACK ON THE SURFACE OF THE BLADE, CAUSING IMBALANCE, AND BLADE SURFACE TO BE SUSCEPTIBLE TO MOISTURE. THE PAINT REFINISH	ING PROCESS APPEARS TO BE TOO THICK WITH NO TRANSITION POINT TO THE LEADING EDGE ABRASION STRIP. THIS IS AN ON GOING PRO	BLEM INVOLVING NUMEROUS TAIL ROTOR BLADE SETS FOR THE PAST 18 MONTHS.	1	G	7	2 	3U	3	U	 	H3EU    	E4CE
2004032500039	20040325	00039	EA  	2004	3	25	CA040226003      	1	20040224	G	2421	721428	IDG             			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502*     	41580	EA  					LT ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL NOTED LEAKING FROM LT ENGINE DRAIN MAST.  INTEGRATED DRIVE GENERATOR REMOVED AND ACCESSORY DRIVE GARLOCK SEAL 	AND IDG SHAFT O-RING REPLACED.  LEAK RETURNED AT DRAIN MAST TWO DAYS LATER.  IDG WAS REMOVED AND INSPECTED.  THE LEAK WA	S DETERMINED TO ORIGINATE FROM THE INTEGRATED DRIVE GENERATOR CARBON SEAL. THIS IS AN ABNORMAL OCCURRENCE.  IDG REPLACED	 WITH SERVICEABLE UNIT.			2	L	7	2 	4F	4	F	RT	A21EA   	E6NE
2004032500040	20040325	00040	EA  	2004	3	25	CA040226004      	2	20040224	G	7322	G20102	FLOAT VALVE     			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502*     	41580	EA  					CARBURETOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND RUN MAINTENANCE NOTED A RUMBLE FROM THE RT ENGINE AT HI IDLE AND BELOW.  THE ECOLOGY TANK FLOAT VALV	E WAS REMOVED AND THE FLOAT WAS FOUND TO BE CORRODED AND DETERIORATED PREVENTING PROPER VALVE OPERATION. THE VALVE WAS H	ELD OPEN ALLOWING AIR TO BE DRAWN INTO THE INLET SIDE OF THE ENGINE DRIVEN FUEL PUMP CAUSING THE PUMP TO CAVITATE. ABOVE	 HIGH IDLE THE EJECTOR VALVE CLOSES THE SUCTION LINE PREVENTING FURTHER CAVITATION AND STOPPING THE RUMBLE. A NEW FLOAT 	VALVE WAS INSTALLED AND A SUBSEQUENT GROUND RUN CONFIRMED THE REPAIR.		2	L	7	2 	4F	4	F	RT	A21EA   	E6NE
2004050300242	20040503	00242	WP  	2004	5	3	CA040226006      	2	20040224	G	7200	TPE33110UA	ENGINE          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	RIGHT	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			22198					P54043			(CAN) ONCE AT LEVEL FLIGHT THE RT ENGINE OIL PRESSURE WAS NOTICE TO BE AT THE LOWER END OF THE GREEN ARC 70 PSI, THE OIL	 PRESSURE WAS MONITORED UNTIL IT DROPPED TO 65 PSI AND THE CREW ELECTED TO RETURN. THE PRESSURE REMAINED STABLE AT 65 PS	I, UNTIL TOUCHDOWN WHERE THE OIL PRESSURE DROPPED TO ZERO. THE ENGINE WAS SECURED AND THE LANDING COMPLETED WITHOUT FURT	HER INCIDENT. A SUBSEQUENT INSPECTION REVEALED EXCESSIVE METAL IN THE OIL FILTER, THE LT ENGINE WAS REMOVED FOR REPAIR. 	 FOLLOWUP INFORMATION WILL BE ADDED ONCE TEAR DOWN AND ANALYSIS IS COMPLETE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2004050300243	20040503	00243	WP  	2004	5	3	CA040227001      	2	20040224	G	7200	TPE33110UA	ENGINE          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	RIGHT	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			22198					P54043			(CAN) ONCE AT LEVEL FLIGHT THE RT ENGINE OIL PRESSURE WAS NOTICE TO BE AT THE LOWER END OF THE GREEN ARC 70 PSI, THE OIL	 PRESSURE WAS MONITORED UNTIL IT DROPPED TO 65 PSI AND THE CREW ELECTED TO RETURN. THE PRESSURE REMAINED STABLE AT 65 PS	I, UNTIL TOUCHDOWN WHERE THE OIL PRESSURE DROPPED TO ZERO. THE ENGINE WAS SECURED AND THE LANDING COMPLETED WITHOUT FURT	HER INCIDENT. A SUBSEQUENT INSPECTION REVEALED EXCESSIVE METAL IN THE OIL FILTER, THE LT ENGINE WAS REMOVED FOR REPAIR. 	 FOLLOWUP INFORMATION WILL BE ADDED ONCE TEAR DOWN AND ANALYSIS IS COMPLETE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2005011200009	20050112	00009	SW  	2005	1	12	CA040227002      	1	20040226	G	2140	1898221	HEAT EXCHANGER  			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					AIR CON SYS	CONTAMINATED    	W				A				UNSCHED LANDING         				W	B		INADEQUATE Q C            	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) ACFT LEVELED OFF IN CRUISE, FLT CREW NOTICED A FOUL ODOUR. FUMES BECAME QUITE STRONG & FLT CREW CALLED MX & RETURN	ED TO BASE. ENROUTE, SEVERAL PAX WERE SUPPLIED O2 DUE TO ODOUR. UPON INSP OF ACFT & MX RECORDS FROM PREVIOUS NIGHT, AIR 	TO AIR HEAT EXCHANGER ASSY FOR RT WING AIR CON SYS FOUND REPLACED. UPON REMOVAL OF EXCHANGER, ODOUR FOUND TO BE COMING F	ROM HEAT EXCHANGER ITSELF. ODOUR ASSOCIATED WITH CHEMICALS USED IN REPAIR PROCESS OF EXCHANGER. REPAIR FACILITY CONTACTE	D ABOUT CHEMICALS & PROCEDURES USED FOR REPAIR OF HEAT EXCHANGERS & NORMAL PROCESS TO FLUSH EXCHANGER. IT APPEARS AS THO	UGH ISOPROPYL FLUSH & OVEN DRYING PROCESS WERE MISSED ON ALL 4 HEAT EXCHANGERS.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2004050300248	20040503	00248	NE  	2004	5	3	CA040227003      	2	20040206	G	7322	PD12H4	CARBURETOR      			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CP356035			(CAN) AIRCRAFT LANDED AND THROTTLES RETURNED TO IDLE, THE NR 2 ENGINE LOADED UP AS IF IT WAS EXCESSIVELY RICH AND THE EN	GINE STOPPED. IT WAS IN TAXI PHASE SO THE AIRCRAFT ROLLED TO PARKING POSITION. MAINTENANCE FOUND THAT THE IDLE MIXTURE W	AS EXCESSIVELY RICH AND WOULD NOT RESPOND TO ADJUSTMENT CARBURETOR WAS REPLACED AND THE AIRCRAFT RELEASE FOR RETURN TO S	ERVICE. CARBURETOR WITH ONLY 3.8 HOURS TSO, WAS SENT FOR WARRANTY AND REPORT OF DEFECT.			2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603
2004050300251	20040503	00251	CE  	2004	5	3	CA040228001      	1	20040227	G	2720	AN2311	CLEVIS BOLT     			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	RUDDER BELCRANK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RUDDER CABLE CLEVIS BOLTS INSPECTED DURING ROUTINE INSPECTION FOUND TO BE WORN APPROX. 30 PERCENT THROUGH THE BOLT	. NEW CLEVIS BOLTS PART NUMBER AN23-11 INSTALLED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA
2004050300252	20040503	00252	SO  	2004	5	3	CA040301001      	1	20040219	G	2497	W23X1A1G20	CIRCUIT BREAKER 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  		BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) CIRCUIT BREAKER SENT FOR EVALUATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004050300264	20040503	00264	EU  	2004	5	3	CA040301003      	1	20040224	G	2420	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	SHEARED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) ON RETURN FLIGHT, THE FLIGHT CREW HAD A GEN 2 FAILURE SO DECREASED ELECTRICAL LOAD AND CONTINUED TO MAINTENANCE BA	SE.  MAINTENANCE REMOVED THE GEN 2 AND INSPECTED IT FOR ANY FAULTS.  A REPLACEMENT GENERATOR WAS BEING INSTALLED WHEN IT	 WAS NOTICED THAT THE DRIVE PULLEY WAS LOOSE AND DID NOT SEEM TO BE CONNECTED TO THE ENGINE. THE HOUSING WAS REMOVED AND	 THE DRIVE SHAFT WAS FOUND TO BE SHEARED, NO OTHER DAMAGE WAS NOTICED. A NEW SHAFT, BEARINGS AND GASKET WERE INSTALLED. 	 SYSTEM WAS GROUND TESTED SERVICEABLE.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004050300270	20040503	00270	NM  	2004	5	3	CA040301004      	1	20040215	G	2150	7786832	HEAT EXCHANGER  			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CABIN AIR	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			15073								(CAN) PILOT REPORTED UNABLE TO CONTROL CABIN ALTITUDE AT LOWER POWER SETTINGS.  AFTER ARRIVAL MAINTENANCE FOUND FORWARD 	HEAT EXCHANGE CRACKED/SPLIT OPEN.  UNIT REPLACED AND AIRCRAFT RETURNED TO SERVICE. NOTE: THIS HEAT EXCHANGER HAD BEEN RE	PAIRED FOR (CRACK ALONG INSIDE WELD OF PRIMARY INLET HEADER) IN  MAY OF 2002.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004050300275	20040503	00275	EU  	2004	5	3	CA040301005      	1	20040216	G	5302	350A2310534451	SUPPORT         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK WAS DISCOVERED IN MAY ON THE NR 5 HANGER BEARING SUPPORT. THIS PART WAS REPLACED IN THE FIELD USING ALL TH	E APPROPIATE TOOLING. SOMETIME LATER THE PILOT COMPLAINED OF A HIGH FREQ VIBRATION. THE SHAFT WAS REBALANCED TO .2 IPS. 	AGAIN ABOUT 20 HOURS LATER THE PILOT COMPLAINED OF A HIGH FREQ, AGAIN IT WAS DETERMINED THE SHAFT WAS OUT OF BALANACE.  	FURTHER INVESTIGATION DETERMINED THE HANGER SUPPORT WAS AGAIN CRACKED.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004050300276	20040503	00276	CE  	2004	5	3	CA040301006      	1	20040225	G	7810	17540071	TUBE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HAIRLINE CRACK IN TUBING, AROUND APPROXIMATELY .25 OF THE CIRCUMFERENCE, IMMEDIATELY BELOW WELDED FLANGE. CRACK WA	S ON IB SIDE OF FLANGE AND NOT READILY VISIBLE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004050300277	20040503	00277	EA  	2004	5	3	CA040301007      	2	20040229	G	7210	3021467	BEARING         	PWA         		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					REUX GEARBOX	DISINTEGRATED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) VISUAL INSPECTION REVEALED BEARING RETAINING FAILURE. APRROXIMATELY ONE QUARTER OF RETAINER MISSING. WILL SEND TO 	PWC FOR EXAMINATION.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004050300278	20040503	00278	NE  	2004	5	3	CA040302001      	3	20040223	G	6114	73030SOCN817388	SEAL            	HAMSTD      		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	BLADE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						20030512					(CAN) EXCESSIVE OIL LEAK FROM RT PROP, NR 3 BLADE.  BLADES NR 1, 3, 4 REMOVED, BLADE SEALS AND SPRING ASSEMBLIES INSPECT	ED. ON INSP ONE SEAL WAS FOUND TO BE BADLY SPLIT WITH A DISTORTED SPRING. OTHER 2 BLADE SEALS SPRING ASSEMBLIES WERE BRO	KEN AND SHOWING SIGNS OF DISTORTION.  ALL 3 BLADE SEAL AND SPRING ASSEMBLIES WERE REPLACED WITH NEW.  LEAK CHECK CARRIED	 OUT, NIL LEAKS. NR 2 BLADE SEAL AND SPRING ASSEMBLY PREVIOUSLY REPLACED DUE TO OIL LEAK, SPRING WAS FOUND TO BE BROKEN 	DURING REPLACEMENT.  LT PROP INSPECTED AS PRECAUTIONARY MEASURE, NR 1, 4 BLADES CHECKED SERVICEABLE, NR 2, 3 BLADE SEALS	 FOUND TO BE DAMAGED DUE TO INCORRECT SPRINGS FITTED. NEW SEALS AND SPRING ASSEMBLIES FITTED, NO DEFECTS.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004050400002	20040504	00002	EA  	2004	5	4	CA040302002      	2	20040221	G	7230		BLADE           			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	COMPRESSOR	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON 2ND FLIGHT OF THE DAY, A SUDDEN PARTIAL POWER LOSS OCCURRED ON NR 1 ENGINE, A STRONG SMELL ACCOMPANIED THE POWE	R LOSS.  ENGINE NR 1 WAS SUBSEQUENTLY SHUT DOWN. THE AIRCRAFT COMPLETED AN UNEVENTFUL UNSCHEDULED LANDING.  UPON SUBSEQU	ENT INSPECTION IT WAS FOUND THAT ENGINE SUFFERED SEVERE DAMAGE TO THE COMPRESSOR SECTION RESULTING FROM THE LOSS OF A BL	ADE FORM THE FIRST STAGE COMPRESSOR.  THE BLADE WAS FOUND STUCK IN THE INLET SCREEN AND ALL THE FIRST STAGE BLADES SUFFE	RED SEVERE DAMAGE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE
2004050400003	20040504	00003	WP  	2004	5	4	CA040302003      	1	20040131	G	2435	150SG117Q	STARTER GEN     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	BURNED          	W				B				EMER. DESCENT           				H	A	D	ELECT. POWER LOSS-50 PC   	FLAME/FIRE                	INFLIGHT SEPARATION       	CR	CRUISE         	1			CA											(CAN) WHILE IN FLIGHT PILOT NOTICED NR BEGIN TO DROP. HE INITIATED AN AUTOROTATION, HEARD A LOUD BANG, AND THE RPM CAME 	BACK UP. UPON LANDING FLAMES AND SMOKE WERE NOTICED IN THE ENGINE BAY. PILOT EXTINGUISHED FIRE AND DETERMINED IT WAS THE	 STARTER GENERATOR. IT APPPEARS THE BEARINGS SEIZED WHICH WAS BRINGING DOWN THE ENGINE RPM UNTIL THE SG SHAFT SHEARED.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004050400006	20040504	00006		2004	5	4	CA040302004      	4	20040214	G	5301	143232	CABLE           		143232      	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					HOOK END	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT HAD UNCOMMANDED LOAD RELEASE. INVESTIGATION DETERMINED THAT A FRAYED MANUAL RELEASE CABLE HAD CAUSED THIS PR	OBLEM. IT WAS BADLY FRAYED WHERE THE CABLE WENT INTO THE CARGO HOOK.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004050400007	20040504	00007		2004	5	4	CA040302005      	4	20040225	G	5301	143232	CABLE           		143232      	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					HOOK END	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT HAD UNCOMMANDED LOAD RELEASE. INVESTIGATION REVEALED THAT THE MANUAL RELEASE CABLE HAD FRAYED WHERE THE CABL	E GOES INTO THE CARGO HOOK. THIS CAUSED THE HOOK TO RELEASE. THIS IS A ONBOARD SYSTEMS KEEPERLESS HOOK.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004050400008	20040504	00008	SW  	2004	5	4	CA040302006      	1	20040224	G	2822	2C271	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL BOOST	DESTROYED       	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA											(CAN) DURING GROUND RUN FOR MAINTENANCE ACTIVITY STROBING OF TAIL ROTOR ASSEMBLY AN EXPLOSING AND SUBSEQUENT FIRE OCCURR	ED IN THE FUEL CELL ASSEMBLY AND AFT PASSENGER COMPARTMEN.  AIRCRAFT WAS ON ITS FOURTH START OF THE DAY FOR TAIL ROTOR B	ALANCING CHECK, FIRE EXTINGUISHED.  AIRCRAFT SUFFERED SERIOUS STRUCTUREAL DAMAGE. MINOR GROUND MAINTENANCE PERSONNEL INJ	URY.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004050400009	20040504	00009	EA  	2004	5	4	CA040302007      	1	20040221	G	3897	4E32644	DRAIN MAST      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					WATER SYS	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FWD GALLEY WATER SYSTEM PUMP WAS NOT OPERATING. TROUBLESHOOTING REVEALED THAT A WIRE BEHIND THE GALLEY WAS AT FAUL	T, NO COMMAND WAS BEING SENT TO THE PUMP.  MAINT REMOVED THE GALLEY AND FOUNDTHE WIRING FROM THE PORTABLE WATER SYSTEM C	ONTROLLER TO BE DAMAGED FROM OVERHEATING, SPECIFICALLY WIRES GBG7044W-22 & GBG7044B-22 TO THE DRAIN HEATERS FROM A177P3 	PINS 20 AND 21. THIS OVERHEATING HAD ALSO AFFECTED ADJACENT WIRES OVER A CONSIDERABLE LENGTH, REQUIRING REPLACEMENT OF E	NTIRE WIRING BUNDLE FROM THE PWS CONTROLLER, HARNESS PN SH670-59071-001. THIS HARNESS INCLUDES THE WIRING FROM PLUGS A17	7P1, A177P2, A177P3 AND A177P4.  A SHORT WAS FOUND IN THE HEATING CIRCUIT OF DRAIN MAST ASSY HR02 (P/N 4E3264-4 )	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004050400011	20040504	00011	WP  	2004	5	4	CA040303001      	2	20040302	G	7230	3072163	BLADE           	GARRTT      		LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					FAN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						970322900732					(CAN) A MECHANIC WAS CARRYING OUT A SERVICE CHECK AND HE NOTICED FOD IN THE RT ENGINE INTAKE.  UPON INSPECTION OF THE IN	TAKE, FOUND A PIECE OF BLADE RUB STRIP MISSING, REAR ACOUSTIC LINER DAMAGE AND TWO DAMAGED FAN BY PASS STATOR BLADES. ON	E FAN BLADE DAMPENER WAS ALSO MISSING.  ENGINE REPLACED.				2	L	7	2 	4F	4	F	 	A10CE   	E6WE
2004050400012	20040504	00012	CE  	2004	5	4	CA040303002      	1	20040226	G	2435		PLUG            	PWA         		LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					GEAR SHAFT	DISLODGED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) EN-ROUTE, THE CREW OBSERVED A LOSS OF OIL PRESSURE. THE ENGINE WAS SECURED AND AN UNEVENTFUL LANDING WAS MADE. EXA	MINATION OF THE ENGINE REVEALED THAT A PLUG IN THE STARTER GEAR SHAFT ASSEMBLY WAS DISLODGED, SUCH THAT PRESSURE OIL COU	LD ESCAPE THE ENGINE. FURTHER EXAMINATION SHOWED THAT THE PLUG HAD NOT BEEN ADEQUATELY SWAGED INTO THE BORE OF THE GEAR 	SHAFT. OTHER OPERATORS WHO HAVE GEAR SHAFTS FROM THE SAME PROCESS BATCH OF GEAR SHAFTS HAVE BEEN ADVISED AND THEIR GEAR 	SHAFTS ARE BEING RE-INSPECTED TO CONFIRM ADEQUATE SWAGING OF THE PLUG.		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
2004050400013	20040504	00013	CE  	2004	5	4	CA040303003      	1	20040221	G	3010	571531025	TUBE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					BLEED AIR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			10921	10921							(CAN) DURING FLIGHT THE CREW NOTICE AN INTERMITENT WING O/H WARNING. MAINTENANCE WAS CONTACTED AND THE AIRCRAFT INSPECTE	D. INSPECTION REVEALED A CRACK IN BLEED AIR TUBE PN 5715310-25. THE TUBE WAS REPLACE. THERE WAS NO RESULTING DAMAGE FROM	 THE BLEED AIR LEAK.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
2004050400014	20040504	00014	CE  	2004	5	4	CA040303004      	1	20040302	G	5310		GUSSET          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	WINDOW POST	UNBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE REMOVING A BROKEN CO-PILOT WINDSHIELD IT WAS NOTED CHAFFING ON THE WINDSHEILD FRAME.  INTERIOR TRIM THAT IS 	ATTACHED TO THE CENTER PILLAR HAD BECOME UNATTACHED AND FALLEN DOWN INTO CONTACT WITH THE WINDSHEILD PILLAR GUSSET.   MF	G WAS IMMEDIATELY CONTACTED AND A REPAIR SCHEME FORWARDED TO ALLOW THE AIRCRAFT TO RETURN TO SERVICE.				1	L	7	2 	4T	4	T	 	A14CE   	E2WE	6	C	P40EA
2004050400015	20040504	00015	NM  	2004	5	4	CA040303005      	1	20040302	G	3242		BRAKE           			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					MLG	CONTAMINATED    	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) NR 5 BRAKE SMOKING ON ARRIVAL. A/C HAS JUST RETURNED FROM PAINT, IT IS SUSPECTED THAT EXCESS FLUID HAD COLLECTED O	N THE SURROUNDING AREA OF NR 5 BRAKE. BRAKE AND WHEEL AREA THOROUGHLY CLEANED.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2004050400016	20040504	00016	EU  	2004	5	4	CA040304001      	1	20040227	G	2910		PILOT VALVE     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FORE, AFT SERVO	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA						DE013					(CAN) IN ORDER TO COMPLY WITH AIRWORHTINESS DIRECTIVE CF-2003-002R1, THE FLIGHT CONTROL RODS WERE DISCONNECTED AND THE P	ILOT VALVE WAS FOUND TO BE SEIZED ON THE FORE AND AFT SERVO.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005011200010	20050112	00010	NM  	2005	1	12	CA040304002      	1	20040301	G	3244	DSC475	TIRE            			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ACFT DECLARED EMERGENCY DURING DECENT INTO BASE & LANDED WITHOUT INCIDENT. IT APPEARS RT O/B TIRE BLEW WHILE IN WH	EEL WELL & CAUSED EXTENSIVE DAMAGE TO AFT NACELLE & WHEEL WELL AREA, & CAUSED FINGERNAIL TO DEPART A/C IN FLT.  DAMAGE C	AUSED LOSS OF NR 2 HYD SYS DUE TO DAMAGED LINES IN THE AFT NACELLE AREA. WHILE IN CRUISE FLT APPROX 35 MILES SOUTH OF IT	'S NEXT BASE WHEN INCIDENT OCCURRED.  ACFT LANDED SAFELY HOWEVER DUE TO NR 2 HYD SYS FAILURE CREW ELECTED TO STOP A/C ON	 RUNWAY & DEPLANED PAX. TIRE WAS  RE-CAPPED. THIS WAS TIRE'S FIRST RE-CAP & HAD 603 CYCLES ON IT WHEN IT BLEW. TIRE HAD 	APPROX 1200-1300 TOTAL CYCLES ON IT SINCE NEW. THE ISSUE IS UNDER INVESTIGATION BY THE NTSB.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004050400017	20040504	00017	EU  	2004	5	4	CA040304003      	1	20040225	G	6730	704A34635019	O-RING          	DUNLOP      		SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					CHECK VALVE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HAD A HARD OVER CYCLIC PROBLEM WITH AN ENGINE, THE AIRCRAFT WAS EQUIPPED WITH MFG SERVOS. HAD THIS PROBLEM AT 30 D	EGREES C TO -15 DEGREES C (OUTSIDE TEMPERATURE), NO DIFFERENCE. BOLT LATERAL SERVOS WAS DUE FOR OVERHAUL, SEND SERVOS FO	R OVERHAUL AND REINSTALLED THESE SERVOS AFTER OVERHAUL, NOTHING CHANGED. REPLACED THE VALVE FILTER BLOCK AND NOTHING CHA	NGE. REPLACED THE LT INPUT CHECK VALVE AT THE SERVO AND HAD A GAIN OF 60 PERCENT. REPLACED THE RT INPUT CHECK VALVE AT T	HE SERVO AND HAD A GAIN OF 100 PERCENT, NO MORE FEED BACK. FOUND THE O-RING INSIDE OF THE CHECK VALVE (FLAT).		1	G	7	1 	3U	3	U	NC	H9EU    	E5NE
2004050400018	20040504	00018	EU  	2004	5	4	CA040304004      	1	20040225	G	2913	704A33690004	BELT            	AEROSP      		SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					HYD PUMP	UNBONDED        	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			F	Z		FLT CONT AFFECTED         	SIGNIFICANT FAILURE REPORT		CR	CRUISE         	1			CA											(CAN) WHILE IN FLIGHT THE PILOT EXPERIENCE A LOST OF HYDRAULIC POWER AND EMERGENCY LANDED ON A NEAR BY LEAKE WITH NO DAM	AGE TO AIRCRAFT. AFTER INSPECTION THE HYDRAULIC BELT HAS BEEN FOUND SECTIONED AT THE GLUED JOINT.					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE
2004050700021	20040507	00021	NE  	2004	5	7	CA040304005      	2	20040303	G	7321	4147T70P02	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								GEE950069			(CAN) DURING TEST FLIGHT PROCEDURES, AFTER DOING RELIGHT OF LT ENGINE, THERE WAS NO THROTTLE REPONSE ON THE LT ENGINE.  	THE CREW DECLARED AN EMERGENCY AND CARRIED OUT A SINGLE ENGINE LANDING WITHOUT FURTHER INCIDENT.  UPON RETURN, ALL ENGIN	E RIGGING WAS VERIFIED ( STATIC AND DYNAMIC ) WITHOUT ANY FINDINGS.  EVERYTHING WAS NORMAL.  THEN, A/C WAS TAKEN OUT TO 	RUN ENGINE AND PROBLEM WAS CONFIRMED, THEN FAULT ISOLATION LED TO THE FUEL CONTROL UNIT SINCE MOTIVE FLOW WAS PRESENT.  	THE FUEL CONTROL UNIT WAS REPLACED AND A/C RAN SERVICEABLE.  IT HAS SINCE RETURNED TO FLIGHT WITHOUT FURTHER OCCURENCES.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004050700022	20040507	00022	CE  	2004	5	7	CA040304007      	1	20040303	G	7602	5038901027	CONTROL CABLE   			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	MIXTURE CONTROL	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE PILOT NOTICED THAT THE RT MIXTURE WAS NOT RESPONDING TO CONTROL MOVEMENT. THE AIRCRAFT RE	TURNED TO BASE UNEVENTFULLY AND UPON MAINTENANCE INSPECTION FOUND THE ENGINE SIDE OF THE CABLE HAD BROKEN AT THE ROD END	 WHERE THE CABLE SHEATH WAS SWAGED ONTO THE CABLE. THE CABLE IS BEING REPLACED. THE TOTAL TIME ON THIS CABLE ASSY WAS 4.	6 TSN.			1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920
2004050700023	20040507	00023	NM  	2004	5	7	CA040304008      	1	20040227	G	6120	3034384	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	P3 SENSE	OUT OF POSITION 	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) THE SHOP ENGINEER WAS TAKING STOCK OF ENGINE WHEN HE NOTICED THAT THE PCU CONTROL ROD (CONDITION) P/N 87620097-023	,POWER PLANT BUILD IPC REF 71-00-02 FIG 10ITEM 2 WAS CONTACTING THE P3 AIR PRESSURE SENSING LINE P/N 3034384 (PW) IPC 72	-01-30 FIG 1 ITEM 10 BEFORE CONTACTING THE HMU STOP AT MAX SETTING.THIS OCCURS WHEN THE HMU IS REPLACED AND THE T FITTIN	G P/N MS9196-04 IS NOT POSITIONED PROPERLY AND OVERLOOKED WHEN RIGGING IS DONE.THE OFFENDING PART IPC REF 72-01-40 FIG 1	 ITEM 120 WAS REPOSITIONED SO A GAP BETWEEN THE SENSE LINE AND THE CONTROL ROD WAS SUFFICIENT FOR FULL AND NORMAL MOVEME	NT OF THE HMU CONTROL ROD. THE MECHANISM WAS FUNCTIONED WITH NO REOCCURRENCE OF THE PROBLEM ON THE ENGINE IN QUESTION.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004050700024	20040507	00024	NE  	2004	5	7	CA040304009      	3	20040304	G	6114	69494R124	SEAL            	HAMSTD      		LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	PUMP HOUSING	DISLODGED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA						233452					(CAN) DEPARTING ,THE CREW OBSERVED A LOW PROPELLER FLUID INDICATION ON NR 2. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RE	TURNED TO POINT OF DEPARTURE. MAINTENANCE FOUND THE PACKING FOR THE PRESSURE SUMP FILLER PORT DISLODGED. PACKING REPOSIT	IONED, FLUID LEVEL SERVICED,  AIRCRAFT GROUND CHECKED SERVICEABLE.				2	H	7	4 	4T	4	T	 	A1SO    	E282	6	C	P906
2004050700026	20040507	00026	EU  	2004	5	7	CA040304011      	1	20040303	G	2910	69596	MAXARET         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	HYD SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A FLIGHT THE AIRCRAFT WAS BEING PULLED INTO THE HANGAR.  AN AME WAS WALKING PAST THE AIRCRAFT AND NOTICED TH	E LT ANTI-SKID COVER WAS MISSING THE THREE RIVETS ON THE CASE.  ON REMOVAL OF THE COVER THE COMPOSITE BLOCKS DESIGNED TO	 HOLD THE DRIVE PORTION OF THE MAXARET AND THE DRIVING HEAD WERE FOUND BROKEN.  THE MAXARET APPEARS TO HAVE SEIZED CAUSI	NG THE DAMAGE.  THIS UNIT HAS NO LIFE OR OVERHAUL LIMITS.  THE ONLY SCHEDULED INSPECTION OF THE UNIT IS WHEN IT IS INSTA	LLED.		2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL
2004050700034	20040507	00034	WP  	2004	5	7	CA040305001      	1	20040304	G	5240		HOOK            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					SERVICE DOOR	DISENGAGED      	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, CREW EXPERIENCED CABIN DEPRESSURIZATION AND ILLUMINATION OF (REAR SERVICE DOOR UNLOCKED) LIGHT. UPON	 RETURN TO THE RAMP, MAINTENANCE PERSONEL DISCOVERED ONE OF THE FOUR HOOKS THAT HOLD THE DOOR CLOSED WAS NOT PROPERLY EN	GAGED IN IT'S YOKE. AFTER INSPECTING THE DOOR AND CYCLING SEVERAL TIMES, THE DOOR WAS CLOSED AND THE A/C WAS PRESSURIZED	 ON THE GROUND. THE AIRCRAFT WAS THEN RETURNED TO SERVICE.			2	L	7	2 	4R	4	T	 	6A6     	E282
2004050700035	20040507	00035	NM  	2004	5	7	CA040305002      	1	20040304	G	3260		PROXIMITY SENSOR			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	DISCONNECTED    	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, CREW SELECTED LANDING GEAR UP, AFTER SELECTION OF LANDING GEAR UP THE CREW HAD AN UNSAFE NOSE GEAR 	INDICATION, AND PROCEEDED TO SELECT LANDING GEAR DOWN WHEN SELECTION DOWN WAS COMPLETED THE NOSE GEAR INDICATION REMAINE	D NOSE UNSAFE, BUT ALTERNATE NOSE DOWN AND SAFE WAS GREEN (POSITIVE DOWN) CREW DECLARED EMERGENCY LANDING, LANDED SAFELY	.  MAINTENANCE FOUND BROKEN WIRE AT NOSE LANDING GEAR DRAG STRUT PROXIMITY SENSOR, WIRES WERE REPAIRED, GEAR SWING CARRI	ED OUT AND AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004050700037	20040507	00037	EA  	2004	5	7	CA040305004      	1	20040304	G	3310	RV4NBYSD502A	RHEOSTAT        	BOMBDR      		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CAPT DIMMER	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			28503								(CAN) DURING PRE-FLIGHT CHECKS ON THE RAMP, THERE WAS A BURNING ODOR IN THE COCKPIT AND SMOKE WAS OBSERVED COMING OFF TH	E CAPTAIN'S SIDE OVERHEAD CEILING PANEL IN THE COCKPIT. AIRCRAFT POWER WAS SHUT DOWN.  MAINTENANCE INVESTIGATION REVEALE	D A BURNED RHEOSTAT ON THE DIMMER CONTROL FOR THE CAPTAIN'S OVERHEAD LIGHT. THE PANEL ASSY WAS REPLACED WITH NO FURTHER 	FAULTS.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004050700038	20040507	00038	NM  	2004	5	7	CA040305005      	1	20040303	G	5755	85711503001	BRACKET         	AEROSP      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ROLL SPOILER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36304			095					(CAN) ROLL SPOILER MOUNTING BRACKET P/N 85710559-001. THE AIRCRAFT WAS IN THE PAINT SHOP BEING PREPPED FOR PAINT AND THE	 CLEANERS THAT WERE CLEANING THE AREA IN AND AROUND THE RT OB ROLL SPOILER ACTUATOR ON THE REAR SPAR NOTICED A LARGE CRA	CK IN THE MOUNTING BRACKET.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004062100120	20040621	00120	EA  	2004	6	21	CA040306002      	1	20040304	G	2170		COALESCER BAG   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CABIN AIR	CONTAMINATED    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, ELECTRICAL TYPE ODOR, WITH CLEAR/GREY SMOKE COMING FROM F/O SIDE PANEL AREA.  SMOKE CONTINUED ACROSS 	TOWARDS CAPTAIN'S SIDE. CREW WAITED 10-15 SECONDS, SMOKE DID NOT CLEAR.  AIRCRAFT DID A EMERGENCY EVACUATION ABOUT 200 Y	ARDS FROM INTENDED GATE POSITION DUE TO SMOKE IN THE COCKPIT.  AIRCRAFT WAS POWERED DOWN AND DEPLANED.  SMOKE AND ODOR T	HEN DISSIPATED.  MAINTENANCE RAN APU, UPON BLEED SELECTION, OIL BURNING ODOR NOTED.  APU OIL LEVEL WAS FOUND .5000 QUART	 OVERSERVICED.   REMOVED AND REPLACED BOTH COALESCER BAGS.  RAN BOTH PACKS FOR LONG TIME.  NO FURTHER DEFECTS NOTED.  AI	RCRAFT RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004050700045	20040507	00045	NE  	2004	5	7	CA040306003      	2	20040227	G	7320		FADEC           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	LIGHTNING STRIKE	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING APPROACH, WITH FLAPS 20, GEAR UP, WING AND COWL ANTI-ICE ON, CONTINUOUS IGNITION ON AC HIT BY A SEVERE LIGH	TNING STRIKE.  WITHIN 10 SECONDS, ENGINE 2 FLAMED OUT WITH N1 AROUND 20 PERCENT.  AROUND 10 SECONDS AFTER, FADEC AUTO RE	LIGHT SUCCESSFULLY CARRIED OUT.  WITHIN THAT TIME FRAME MESSAGES RT ENG DEGRADED, RT ENG BLEED AND STALL FAIL APPEARED. 	 QRH APPLIED, ALL ENGINES PARAMETERS NORMAL.  AC LANDED WITHOUT FURTHER INCIDENT.  ON GROUND, LIGHTNING STRIKE CONFIRMED	 WITH SEVERAL IMPACT ON  FUSELAGE.  ENGINE RUNS SUCCESSFULLY CARRIED OUT TO CONFIRM GOOD OPERATION OF ENGINE AND FADEC.R	 FADEC AND DFDR.  REMOVED FROM AC FOR ANALYSIS.  STRUCTURAL DAMAGES REPAIRED AND AC RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004050700047	20040507	00047	CE  	2004	5	7	CA040308001      	1	20040218	G	1430	A251352	BOLT            			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSTALLATION OF THE PROPELLER, WHEN TIGHTENING THE BOLTS TO THE SPECIFIC TORQUE OF 25-30 POUNDS FOOT.  ONE 	OF THE BOLTS BROKE AT APPROXIMATELY 27 POUNDS FOOT.  THE BOLT BROKE AT THE BASE OF THE THREADS NEAR THE START OF THE GRI	P. A SECOND BOLT WAS TIGHTENED USING A DIFFERENT TORQUE WRENCH AND IT ALSO BROKE AT THE BASE OF THE THREADS AND AT APPRO	XIMATELY THE SAME TORQUE VALUE.  THE TORQUE WRENCHES HAD BEEN CERTIFIED APPROXIMATELY ONE WEEK PRIOR.  THE PROPELLER AND	 BOLTS HAD BEEN OVERHAULED AT A PROPELLER OVERHAUL SHOP AND WERE BEING REINSTALLED ON THE AIRCRAFT.		1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918
2004050700048	20040507	00048	EU  	2004	5	7	CA040308002      	1	20040224	G	2913	704A33690008	BELT            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYDRAULIC PUMP	STRETCHED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSPECTING THE HYDRAULIC DRIVE BELT IAW 63.00.00.601 PARA 4 FOR PROPER TENSION IT WAS FOUND TO BE LOOSE.  AT	TEMPTS WERE MADE TO TENSION THE BELT IAW 63.00.00.401 PARA 4.2.3.   WE WERE UNABLE TO GET THE REQUIRED TENSION DUE TO NO	 MORE MOTION OF THE TENSIONING BRACKET.  MET 63.00.00.601 PARA 4.1 STATES THAT IF YOU CANT ACHIEVE REQUIRED TENSION REPL	ACE THE BELT WHICH OCCURRED.  THIS IS THE LATEST BELT PT NR 704A33690008  POLY V 597K4  WHICH HAS A PUBLISHED LIFE IAW M	SR OF 1500 HOURS. THIS BELT FAILED INSPECTION AT 371. HOURS.  DISCUSSIONS WITH MFG INDICATED THAT A LOWER TIGHTENING TEN	SION IS IN THE WORKS SO THE BELT WOULD NOT BE RUNNING AS TIGHT.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004050700049	20040507	00049	GL  	2004	5	7	CA040308003      	1	20040301	G	2752		SEAL            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A 50 HR INSPECTION, IT WAS FOUND THAT THE SPLINED SEAL PUSHED OUT OF POSITION ON FLAP ACTUATOR ROD ASSY.  O	N THIS AIRCRAFT IT DID NOT MAKE CONTACT WITH THE FLAP POSITION SWITCHES.  THE COMPLETE ASSY HAD BEEN REPLACED ONLY 26.3 	HRS PREVIOUSLY DUE TO AN UNRELATED PROBLEM.  MFG SUGGESTED WE CLEAN THE AREA WITH ALCOHOL AND RE-GLUE THE SEAL USING LOC	TITE 409 ADHESIVE.  THIS HAS BEEN CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE.			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004050700050	20040507	00050	EA  	2004	5	7	CA040308005      	1	20040308	G	5297	840534	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					SERVICE DOOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SERVICE DOOR EXTERIOR HANDLE WAS OUT AFTER LANDING WITH NO CAUTION OR INDICATIONS. SWITCH REPLACED. DOOR RIGGED IA	W AMM.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004070900007	20040709	00007		2004	7	9	CA040308006      	4	20040308	G	3425		COMPUTER        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FLT DIR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FAULT:FD AND ALL RAW DATA FAILURE X3 DURING FINAL APPROACH. FOUND EVIDENCE OF DIRT INSIDE IAPS CARD CAGE, CLEANED,	'SERV.'					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004050700051	20040507	00051	CE  	2004	5	7	CA040308007      	1	20040302	G	3230		GEARBOX         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA						405880					(CAN) DURING FLIGHT THE LANDING GEAR TOOK LONGER THAN NORMAL TO RETRACT. COULD NOT DUPLICATE THE PROBLEM IN THE HANGAR E	VEN WHEN SWINGING THE GEAR WITH EXTRA LOADS.  SUSPECTED THAT THE CLUTCH WAS SLIPPING DURING RETRACTION WITH THE INCREASE	D LOADS DURING FLIGHT. THE LANDING GEAR GEARBOX WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE WITH OUT FURTHER I	NCIDENT.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2004050700040	20040507	00040	SO  	2004	5	7	CA040308008      	1	20040303	G	5540	4004009	TORQUE TUBE     	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RUDDER ASSY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20210			315435					(CAN) DURING INSPECTION IAW AD 2003-24-07 RUDDER FOUND TORQUE TUBE CORRODED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004040500001	20040405	00001	EA  	2004	4	5	CA040308009      	1	20040304	G	3310	82510189S103	RHEOSTAT        			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	COCKPIT LIGHT	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			28497	28497							(CAN) DURING MAINT WHEEL REPLACEMENT ON RAMP , FLIGHT CREW (ONLY PERSONNEL ONBOARD) NOTICED SMOKE IN THE COCKPIT (NO FIR	E) . MAINTENANCE INSPECTION FOUND OVERHEAD READING LIGHT RHEOSTAT WAS SOURCE OF SMOKE.  COCKPIT OVERHEAD PANEL ASSEMBLY 	WITH RHEOSTAT REPLACED.  AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004040500002	20040405	00002	SO  	2004	4	5	CA040308010      	1	20040221	G	2731	4420000	TRIM SYSTEM     			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR TRIM	LACK OF LUBE    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) PILOT REPORTED ELEVATOR TRIM JAMMED FULL FORWARD AND COULD NOT TRIM NOSE UP.  ELEVATOR TRIM JACK FOUND NOT LUBRICA	TED.  SHAFT LUBRICATED, SYSTEM FUNCTIONS NORMAL. FORWARD TRIM JACK SPOOL CHECKED OK.  SPOOLING AROUND ELECTRIC ACTUATOR 	CKECKED OK. CABLE TENSION CHECKED OK.  AFT TRIM TAB ACTUATOR FREE PLAY CHECKED WITHIN LIMITS IN MM.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004040500003	20040405	00003	CE  	2004	4	5	CA040309001      	1	20040303	G	7603	1143890503	CONTROL CABLE   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	POWER LEVER	SEVERED         	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING AND SUBSEQUENT TAXI THE RT ENGINE SPOOLED UP AND DID NOT RESPOND TO POWER LEVER MOVEMENT. THE ENGINE	 WAS SHUT DOWN AND THE AIRCRAFT COMPLETED TAXI TO THE TERMINAL ON THE LT ENGINE. MAINTENANCE INVESTIGATED AND DISCOVERED	 THAT THE POWER LEVER CABLE HAD BEEN SEVERED BY THE PULLEY OF THE VAPOR CYCLE AIR CONDITIONING SYSTEM. THE CABLE HAD BEE	N ROUTED TOO CLOSE TO THE PULLEY DURING AN ENGINE REMOVAL AND REINSTALLATION 64 HOURS PRIOR TO THE INCIDENT.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004040500004	20040405	00004	EA  	2004	4	5	CA040309002      	1	20040304	G	6320	61352095012	COVER           	SKRSKY      		CARSON	S61   	S61LSKRSKY  	       	EA  	GE    	CT58  	CT581401    	30011	NE  					M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26356			A14994					(CAN) CRACK ON LOWER LT LEG OF MAIN GEARBOX REAR COVER DISCOVERED ON DAILY INSPECTION.						2	G	7	2 	4U	4	U	 	H8EA    	1E3
2004040500005	20040405	00005	NE  	2004	4	5	CA040309003      	1	20040307	G	6320		FILTER          	SKRSKY      	613520600046	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					M/R GEARBOX	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			18054			A141027					(CAN) MAIN GEAR BOX OIL PRESSURE DROPPED IN FLIGHT. AIRCRAFT RETURNED TO LANDING AREA AND SHUT DOWN.  EXAMINATION OF MGB	 COARSE SCREEN FILTER REVEALED RESIN COATING FROM INSIDE OF MGB HAD FLAKED OFF.  MGB REPLACED.					2	G	7	2 	4U	4	U	 	1H15    	1E3
2004040500006	20040405	00006	NM  	2004	4	5	CA040309004      	1	20040225	G	2742	6355B000103	MOTOR           			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					STAB TRIM	JAMMED          	W				H				DEACTIVATE SYST/CIRCUITS				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  2 HRS INTO FLT (STAB OUT OF TRIM) LIGHT ILLUMIN. NON-NORMAL CKLIST WAS COMPLETED,  ELEC TRIM REMAINED INOP,TRIM C	HANGES ACCOMPLISHED MANUALLY. MAINT CTRL WAS CONSULTED AND CB 6B AND 610 WERE PULLED AND RESET. (STAB OUT OF TRIM) LIGHT	 CONTINUED INTERMITTENT, PILOTS CONTINUED MANUALLY INPUT REQUIRED TRIM CHANGES. STAB BECAME COMPLETELY JAMMED NON-NORMAL	 CKLIST WAS COMPLETED. STAB REMAINED JAMMED FOLLOWING COMPLETION OF CKLIST,  MAINT CTRL REQUESTED THAT CB 6B AND 610 BE 	PULLED AND LT OUT. MAN CTRL OF STAB WAS RESTORED AND A NON-NORMAL LANDING WAS COMPLETED, WITHOUT FURTHER INCIDENT. UPDAT	E: MAR.09/04 - MFG HAS REQUESTED FLIGHT DATA RECORDED READOUT FROM SUBJECT FLIGHT AND RELATED TROUBLESHOOTING RESULTS.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2005011200011	20050112	00011	EA  	2005	1	12	CA040309005      	1	20040309	G	2520	C3FF183	LOCK PIN        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					SEAT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) INCORRECT PART DISCOVERED DURING SEAT INSPECTION THE PROPER SEAT LOCK PIN HAD BEEN REPLACED BY A GROUND DOWN A/N B	OLT					1	H	7	1 	3R	4	T		A815    	E4EA
2004040500007	20040405	00007	NM  	2004	4	5	CA040310001      	1	20040306	G	4997		CONNECTOR       	GARRTT      	GTCP8511    	BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU	BURNED          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			CR	CRUISE         	1			CA						P34583					(CAN) INDICATION OF APU FIRE AT 35,000 FT. AFTER DISCHARGING BOTTLE AND SHUTTING DOWN APU, RED WARNING LIGHT EXTINGUISHE	D. CREW DIVERTED AND AC LANDED W/O INCIDENT.  MAINT INSP FOR FIRE DAMAGE IAW SRM 51-4-10. FIRE CONTAINED BETWEEN BLKHD S	TA.1156 AND APU EXHAUST BAFFLE. NO EVIDENCE OF BURNED PRIMER OR DISCOLORED METAL.  APU EGT AND TAIL PIPE FIRE DETECTION 	WIRING HARNESS FOUND BURNED, TAIL PIPE FIRE. APU TUB REMOVED AND INSP,  NO LEAKS AND NO INDICATION OF FIRE DAMAGE. MAINT	 SUSPECT CAUSED OFFIRE AT EGT CONNECTORS TO WIRE HARNESS, FOUND BURNED.  POSSIBLE SHORT OCCURRED, DAMAGED WIRING HARNESS	ES REPLACED AND APU FIRE DETECTION SYSTEM TESTED SERVICEABLE. APU FIRE BOTTLE REPLACED. AC RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004040500008	20040405	00008	EU  	2004	4	5	CA040310002      	1	20040308	G	2510	EQMFG200002901	SEAT BELT       			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SHOULDER HARNESS INERTIA REEL ON COPILOT'S SEAT WOULD NOT RETRACT AFTER FULL EXTENSION.  THE PN SPECIFIED IN 9B AP	PLIES TO THE 4 POINT HARNESS ON ENERGY ABSORBING STYLE OF SEAT.					1	G	7	1 	3U	3	U	 	H9EU    	E00054EN
2004040500009	20040405	00009	SO  	2004	4	5	CA040310003      	1	20040226	G	2435	MHB4016B	STARTER GEN     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT WAS AT AIRPORT.  AFTER STARTING THE RT ENGINE, THE PILOT WENT TO START THE LT ENGINE, THE ENGINE WOULD NO	T TURN OVER, FOUND THAT THE STARTER WAS TURNING OVER BUT THE BENDIX WOULD NOT TURN. CHANGED LT STARTER ENGINE STARTED.  	NO FAULTS FOUND.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004040500010	20040405	00010	SW  	2004	4	5	CA040310004      	1	20040225	G	5313	206031314123	LONGERON        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE THE ENGINEER DETECTED THE ENGINE MOUNT TO BE LOOSE.  FURTHER INVESTIGATION INDICATED 	A CRACKED LONGERON WITH THE ENGINE MOUNT IS ATTACHED.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004040500011	20040405	00011	EA  	2004	4	5	CA040310005      	2	20040108	G	8520		CAMSHAFT        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								L52772T			(CAN) CAMSHAFT LOBES AND LIFTERS WEARING PREMATURALLY.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004072900075	20040729	00075		2004	7	29	CA040310007      	4	20040308	G	2561		BATTERY         																	LIFEJACKET LIGHT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) SEALED BATTERIES ARE INTEGRAL PART OF SURVIVOR LIGHT IN AVIATION LIFEJACKET.  LIFEJACKET AND LIGHT IS USED AS PART	 OF HELICOPTER PASSENGER TRANSPORTATION SUIT SYSTEM APPROVED TO CAN/CGSBS-65.17-99.  SEVERAL BATTERIES IN THIS LOT NUMBE	R HAVE BEEN LEAKING AND SOME HAVE BEEN DIM OR FAILED TO FUNCTION WHEN TESTED. STORAGE LIFE IS STATED AS 60 MONTHS.  HAVE	 NOT YET CONFIRMED THE NATURE OF THE LEAKING SUBSTANCE.  WE ARE REMOVING ALL OF THE LIGHTS OF THIS BATCH DESIGNATION FRO	M SERVICE. APPROXIMATELY 100 LIGHTS IN TOTAL.  BATTERY ONLY 16 MONTH.
2004040500013	20040405	00013	CE  	2004	4	5	CA040310008      	1	20040218	G	1430	A251352	BOLT            	MCAULY      		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						K19086					(CAN) UPON APPLICATION OF 27 FT/LBS TO 2 OF THE MOUNTING BOLTS AT THE THREADS FAILED.   BOLTS FORWARDED TO COMPANY FOR E	VALUATION.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918
2004040500014	20040405	00014	SO  	2004	4	5	CA040310009      	1	20040310	G	3230	WTC345	POWERPACK       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHEN THE PILOT SELECTED GEAR UP, ONE OF THE GEARS WAS NOT RETRACTING AND THE TRANSITION LIGHT REMAINED ILLUMINATED	.  AFTER SEVERAL ATTEMPTS THE GEAR RETRACTED AND EVERYTHING WAS NORMAL. THE POWER PACK WAS REPLACED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004040500015	20040405	00015	NM  	2004	4	5	CA040310010      	1	20040309	G	5610	NP15790213	WINDOW          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THROUGH 6000 FT. THE OUTER PANE OF THE CAPTAIN'S SIDE WINDOW SHATTERED. THERE WAS NO NOTICEABLE CHAN	GE IN PRESSURIZATION. THE CAPTAIN DEPRESSURIZED THE AIRCRAFT AND THE FLIGHT RETURNED WITHOUT FURTHER INCIDENT. DETERMINE	D TO BE OUTER PLY (NON-STRUCTURAL).WINDOW SPEED TAPED AND DETERMINED TO BE SAFE FOR FERRY.  A/C FERRIED FOR REPAIRS. LOG	 PAGE 343040 AND 343041 EXPLAIN THE DEFECT AS DESCRIBED ABOVE, AND DESCRIBE THE RECTIFICATION DETAILS TO BE AS FOLLOWS: 	 LT SIDE WINDOW REPLACED, AND TEMP CONTROLLER REPLACED.  LT SIDE WINDOW P/N NP157902-13, S/N 00213H4459 TEMP CONTROLLER 	P/N SYLZ50970, S/N 724C REASON FOR FAILURE NOT YET DETERMINED.  TEAR DOWN REPORTS TO FOLLOW.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004040500016	20040405	00016	CE  	2004	4	5	CA040311001      	1	20040310	G	3260	JE6	SWITCH          			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) UPON APPROACH THE LANDING GEAR WAS SELECTED DOWN WITH NO GREEN LIGHT DOWN AND LOCKED INDICATION ON THE RT GEAR.  T	HE GEAR WAS CYCLED, THE MANUAL EXTENSION WAS PERFORMED ALL WITH THE SAME RESULT.  THE AIRCRAFT LANDED UNEVENTFULLY AND U	PON INVESTIGATION THE MICRO SWITCH ACTUATOR TAB WAS FOUND BROKEN AT THE ATTACHING BRACKET.  THE ACUATOR WAS REPLACED AND	 THE GEAR WAS SWUNG NUMEROUS TIMES SERVICEABLE.			1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P36EA
2004040500017	20040405	00017	NM  	2004	4	5	CA040311002      	1	20040208	G	6120	697073002	PITCH CONTROL   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1 PROP	INOPERATIVE     	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT EXPERIENCED NR 1 PROPELLER TO FEATHER PITCH JUST AFTER TAKEOFF POWER WAS SET ON.  PIREP RATING POWER SET,	 NR 1 ENG TORQUE INDICATION IN TURNED RED AND PROPELLER RPM DECREASED TO 200RPM. CONDITION LEVER MOVED TO START/FEATHER 	THEN BACK TO MAX BUT NO HELP.  TAKE OFF REJECTED.  NR 1 PROP REMAINED FEATHERED DURING TAXI TO GATE. PP FAULTS CHECKED, 	NO FAULTS.  EMU DOWNLOAD, NO PP EXCEEDENCE RECORDED. ENGINE RUN-UP  CHECKS, COULD NOT DUPLICATE. CLEANED FADEC, PEC AND 	PCU CONNECTORS. REPLACED NR 1 PCU FOR TROUBLESHOOTING.  AIRCRAFT RTS.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004041300008	20040413	00008	GL  	2004	4	13	CA040311003      	2	20040210	G	7261	6896451	TRANSFER TUBE   								ALLSN 	250C  	250C30P     	03013	GL  					OIL SYSTEM	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FERRULE UNDER B NUT OF SCAVENGE OIL LINE FROM NR 8 BEARING WAS WRONGLY MANUFACTURED, CAUSING PENDING FRACTURE OF F	LANGE.  HAS CAUSED 360 DEGREE LINE AROUND THE BASE OF THE FLANGE. TUBE REPLACED, A/C RETURNED TO SERVICE.  OIL LOSS AT T	HIS LOCATION WOULD HAVE CAUSED OIL STARVATION TO NR 8 BEARING RESULTING IN ENGINE FAILURE.									3	U			E1GL
2004040500018	20040405	00018	WP  	2004	4	5	CA040311004      	1	20040307	G	2910	7936907615	LINE            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ON DEPARTURE LT HYD PRESSURE LIGHT ILLUMINATED IN FLIGHT WITH HYD PRESS. READING ZERO. AIRCRAFT LANDED.  MAINTENAN	CE FOUND LT EDP INOPERATIVE.  LT EDP SWAPPED WITH RT EDP AND AIRCRAFT DISPATCHED IAW MEL 29-5.EDP P/N AS666411-L-5666  S	/N MX134145-4M. THE LT HYDRAULIC QTY LOW LIGHT ILLUMINATED IN FLIGHT WITH QTY INDICATION OF 3 QTS WITH SYSTEM PRESSURIZE	D.  FOLLOWING INVESTIGATION BY MAINTENANCE, FOUND LT PIPE ASSY-FUSELAGE SECTION HYD SYSTEM PRESSURE P/N 7936907-615 CRAC	KED AT FLARE.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004040500019	20040405	00019	EU  	2004	4	5	CA040311005      	1	20040310	G	2822	9868411404	PUMP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST	INOPERATIVE     	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT THE PILOT NOTED A 2 LED DIFFERENCE BETWEEN LT AND RT FUEL INDICATORS. A FEW MINUTES LATER T	HE RT BOOST PUMP LT INDICATOR CAME ON. THE LT REMAIN ON FOR THE DURATION OF THE FLIGHT AND THE FUEL IMBALANCE REMAINED. 	 ON THE GROUND THE FUEL BOOST PUMPS WERE TESTED MANUALLY. THE RT BOOST PUMP INDICATED NORMALLY BUT NO SOUND OF THE PUMP 	RUNNING WAS NOTED. THE FUEL PUMP WAS REPLACED AND THE SYSTEM TESTED SERVICEABLE. NO FURTHER ACTION WAS REQUIRED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004040500020	20040405	00020	GL  	2004	4	5	CA040311006      	2	20040302	G	8550	23038229	SEPARATOR       			AROFAL	OH58  	OH58C       	1181580	SW  	ALLSN 	250C  	T63A720     	03002	GL  					OIL/AIR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								AE405314			(CAN) ON DISASSEMBLY OF THE GEARBOX ASSEMBLY, THE AIR OIL SEPARATOR GEAR SHAFT WAS FOUND SHEARED AT THE JUNCTION OF GEAR	 AND SHAFT. THE ENGINE WAS SENT TO THE SHOP FOR METAL CONTAMINATION.  THE AIRCRAFT HAD PREVIOUSLY BEEN INVOLVED IN A WIR	E STRIKE.  THE ENGINE RAN FOR 5 MINUTES AFTER THE STRIKE BUT BOTH CHIP DETECTORS HAD A LOT OF METAL.				1	G	7	1 	3U	3	U	NC	H22NM   	E4CE
2004040500021	20040405	00021	EU  	2004	4	5	CA040311007      	1	20040311	G	3340	0320713406	LIGHT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EXTERIOR	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) NAVIGATION LIGHT ASSEMBLY (TAIL) APPEARS TO HAVE PROBLEMS WITH THE TOP BULB BURNING OUT. THERE HAS BEEN 8 BULBS P/	N 972.87.87.184 REPLACED WITHIN 7 DAYS. THE COMPLETE ASSEMBLY HAS BEEN REPLACED ALONG WITH A ELECTRONIC SWITCH UNIT. THE	 SAME RESULTS. THE BULBS THEMSELVES ARE EXTREMELY HOT WITHIN A SORT TIME OF OPERATION.(SECONDS) THIS NAV LIGHT ASSEMBLY 	IS PART OF A KIT P/N 500.50.12.276 DUAL NAV LIGHT SYSTEM.  MFG S/B 33-009 WAS USED FOR THE INSTALLATION OF THIS PRODUCT.	  IN SHORT, THE LIGHT IS UNRELIABLE.  ON GOING TRIALS ARE CONTINUING TO FIND A SOLUTION.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004040500022	20040405	00022	NE  	2004	4	5	CA040311008      	2	20040308	G	7230	3040933	DISK            								PWA   	PT6   	PT6A67B     	52043	NE  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE WAS STRIPPED AS PART OF ROUTINE SCHEDULED OVERHAUL. VISUAL EXAMINATION OF HPC DISK 3 SHOWS CRACK IN RIM OF 	DISK. FURTHER INVESTIGATION IS UNDERWAY.										4	T			E26NE
2004040500023	20040405	00023	WP  	2004	4	5	CA040311009      	1	20040310	G	3220		STRUT           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	DEFLATED        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, L/G SELECTED UP, NOSE GEAR UNSAFE LIGHT ON WITH ASSOCIATED BUFFERING & NOISE. AIRCRAFT LANDED. M	AINTENANCE FOUND NOSE OLEO DEFLATED. NOSE STRUT SERVICED, GEAR RETRACTION CARRIED OUT AND AIRCRAFT DISPATCHED SERVICEABL	E.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004040500024	20040405	00024	EA  	2004	4	5	CA040311010      	2	20040309	G	8520	LW16812	LIFTER          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LT ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L44377T			(CAN) DURING A ROUTINE INSPECTION, METAL CONTAMINATION WAS DETECTED IN THE FULL FLOW OIL FILTER CARTRIDGE ELEMENT. THE L	IFTER ASSEMBLIES WERE REMOVED NEXT TO DETERMINE THEIR CONDITION. THIS HAS BEEN A RECURRING PROBLEM ON THIS MODEL ENGINE.	 THE SURFACE OF THE LIFTERS HAD EVIDENCE OF SPALLING AND SURFACE CHIPS. THE ENGINE WAS SUBSEQUENTLY REMOVED FROM THE AIR	CRAFT FOR INSPECTION BY THE OVERHAUL SHOP. A S IMILAR INSPECTION WAS CARRIED OUT ON THE RIGHT ENGINE, HOWEVER THERE WAS 	NO EVIDENCE OF DAMAGE DUE TO THE CONDITION DESCRIBED ABOVE.		1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA
2004040500025	20040405	00025	CE  	2004	4	5	CA040311011      	1	20040227	G	5210	50430043619	CHANNEL         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION A CRACK WAS DISCOVERED ALONG THE TRAILING EDGE OF THE CABIN DOOR CHANNEL P/N 50430043619. THE CR	ACK PROPAGATED APPROXIMATELY 6 IN, JUST ABOVE THE DOOR HINGE. THE DOOR WAS REMOVED AND SENT TO AN APPROVED OVERHAUL SHOP	, REPAIRED AND REINSTALLED.  AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004040500026	20040405	00026	EA  	2004	4	5	CA040312002      	2	20040309	G	8530		CONNECTING ROD  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA								L230368A			(CAN) DURING CRUSE, THE CREW HEARD NOISES COMING FROM THE NR 2 ENGINE, SHORTLY AFTER THERE WAS A LOUD BANG AND VIBRATION	. THE CREW NOTICED OIL AND SMOKE COMING FROM THE ENGINE COWL, THE PROP WAS FEATHERED AND ENGINE STOWED. THE OIL HIT THE 	TURBOCHARGER AND IGNITED CAUSING FIRE TO FLOW ALONG THE LOWER WING AND CAUSED DAMAGE TO THE LOWER SKIN AND GEAR DOOR. TH	E LOWER FLAP SKIN ALSO SHOWED SIGNS OF HEAT DAMAGE. THE A/C LANDED WITH NO FURTHER PROBLEMS.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004040500027	20040405	00027	SO  	2004	4	5	CA040312003      	2	20040312	G	8530	C8512F	CYLINDER HEAD   			CESSNA	120   	120         	2071402	CE  	CONT  	C85   	C8512F      	17008	SO  	MCAULY	1B90	1B90CM      	GL  	ENGINE	MISALIGNED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ENGINE WAS SENT TO ENGINE SHOP FOR PROP STRIKE INSPECTION.  UPON REINSTALLATION OF NR 1 CYLINDER, IT WAS DISCOVERE	D THAT THE BARREL AND HEAD WERE MISALIGNED BY APPROX. 5 DEGREES (UNIT WAS REPLACED).  ENGINE SHOP ADVISES THIS IS A DEFE	CT OCCURING DURING ORIGINAL ASSEMBLY AT THE FACTORY AND FURTHER ADVISE THAT THIS IS THE SECOND ONE THEY HAVE FOUND.				1	H	7	1 	3O	3	O	 	A768    	E233	5	N	P842
2004040500028	20040405	00028	NM  	2004	4	5	CA040312004      	1	20040311	G	3230		ACCESSORY UNIT  			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					MLG	FAULTY          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) DURING APPROACH AND LANDING GEAR HANDLE EXTENDED, IT WAS OBSERVED THAT THERE WAS AN UNSAFE LT LANDING GEAR LIGHT. 	 IT WAS DECIDED THAT A MISSED APPROACH WOULD BE CARRIED OUT AND GO AROUND.  EMERGENCY PROCEDURES WERE CARRIED OUT.  TOWE	R WAS NOTIFIED OF THE PROBLEM AND EMERGENCY EQUIPMENT WAS MADE READY. IT WAS CONFIRMED THE GEAR WAS DOWN AND LOCKED AND 	THE LANDING WAS PERFORMED WITHOUT INCIDENT. MTCE INSPECTED THE AIRCRAFT AND THE LANDING GEAR ACCESSORY UNIT WAS SWAPPED 	WITH ANOTHER AIRCRAFT FOR TROUBLESHOOTING.  IT WAS CONFIRMED THAT THE L/G ACCESSORY UNIT WAS AT FAULT AND A SERVICEABLE 	UNIT WAS INSTALLED, ADJUSTED AND FUNCTIONED SERVICEABLE IAW MM 32-09-121. NO FAULT DURING SUBSEQUENT FLIGHT.	2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004040500029	20040405	00029	GL  	2004	4	5	CA040315001      	2	20040309	G	7210	6850209	GEARBOX         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2 REDUCTION	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AT TOP OF CLIMB ENROUTE, NR 2 RGB CHIP LIGHT OBSERVED. THE INDICATION WOULD NOT CLEAR, NR 2 ENGINE WAS SHUT DOWN. 	 MAINTENANCE FOUND BOTH RGB CHIP PLUGS BRIDGED.  NR 2 ENGINE WAS REPLACED FOR CONVENIENCE AND THE AIRCRAFT RETURNED TO S	ERVICE.				2	H	7	4 	4T	4	T	 	A1SO    	E282	6	C	P906
2004040600001	20040406	00001	NM  	2004	4	6	CA040315002      	1	20040313	G	8011	97907021	START VALVE     			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING DEPARTURE CREW WAS UNABLE TO START NR 1 ENGINE. MAINTENANCE CALLED TO PERFORM A MANUAL START.   FOUND THE B	OTTOM OF THE START VALVE CRACKED AT THE ADJUSTMENT SCREW.  VALVE REPLACED AND A/C DEPARTED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004040600002	20040406	00002	SO  	2004	4	6	CA040315003      	1	20040310	G	3245	650X10600X6	TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	FLAT            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) A/C DEPARTED WITH 10KT WINDS AND BLOWING SNOW. A/C MADE ROUTINE TAKE OFF AND FLIGHT. AFTER LANDING, DURING TAXI ON	 RUNWAY, PILOT NOTICED A/C WAS PULLING TO ONE SIDE. PILOT TAXIED OFF RUNWAY AND PARKED. HE THEN VISUALLY INSPECTED LT MA	IN TIRE AND SAW IT WAS FLAT. MAINT WAS DISPATCHED.  MAINT REPLACED MAIN WHEEL AND INSTALLED NEW TUBE IN NOSE WHEEL. UPON	 INSP MAIN ASSY HAD A SHEARED VALVE STEM AND NOSE TUBE HAD A PIN HOLE IN IT.  CAUSE OF  SHEARED VALVE STEM IS BELIEVED T	O HAVE BEEN FROZEN BRAKES.  CAUSE OF PIN HOLE IN THE NOSE TUBE IS BELIEVED TO HAVE BEEN THE CHANGE IN TEMPERATURE BETWEE	N  AREA OF DEPARTURE AND AREA OF ARRIVAL CAUSING WHEEL PRESSURE TO HAVE GONE DOWN AND TUBE GETTING PINCHED.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004040600003	20040406	00003	CE  	2004	4	6	CA040315004      	1	20040311	G	2510	05130391	LIGHTER         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	COCKPIT	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SMOKE/ FUMES DETECTED IN COCKPIT DURING CRUISE FLT.  CREW SURVEYED ELECTRICAL SYSTEM CONTROLS AND FOUND CIGAR LIGH	TER TO BE HOT. REMOVED LIGHTER FROM DASH AND RETURNED TO BASE WITH NO FURTHER COMPLICATIONS. INSPECTION REVEALED COILS O	F LIGHTER SHORTED CAUSING FUMES.  MAINTENANCE DISCONNECTED POWER WIRE TO LIGHTER ASSEMBLY IAW AD 78-08-03. NOTE: THIS AD	 DOES NOT APPLY TO THIS A/C SN BUT CERTAINLY WAS AFFECTED IN THIS INSTANCE, SHIPS AFFECTED BY THIS SN SHOULD BE REVISITE	D BY THE AD ISSUER.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004041300011	20040413	00011	CE  	2004	4	13	CA040315008      	1	20040302	G	2823	1013890253	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYSTEM	FAILED          	W				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PRESTART CHECKS FLIGHT CREW COULD NOT EXTINGUISH (LOW FUEL PRESSURE) WARNING LIGHT. FLIGHT CANCELLED. INSPE	CTION FOUND RT FUEL SHUT OFF VALVE HAD FAILED IN THE CLOSED POSITION. VALVE  HAD BEEN RECENTLY OVERHAULED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004041300012	20040413	00012	EU  	2004	4	13	CA040315009      	1	20040306	G	5330		SKIN            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36314								(CAN) A PILOT IN THE PROCESS OF DOING HIS DAILY INSPECTION OF THE AIRCRAFT NOTICED A CRACK (2.5 INCHES) IN THE LT FORWAR	D FUSELAGE SKIN JUST BELOW A LAP JOINT BETWEEN FRAMES 10 AND 11 NEAR THE WATER LINE. THE AIRCRAFT WAS REMOVED FOR SERVIC	E, A SECTION OF SKIN IN THE AFFECTED AREA WAS REMOVED AND SENT FOR ANALYSIS, THE BREAK OCCURRED ON AN INSIDE RADIUS OF T	HE SKIN THAT WAS CHEMICALLY MILLED.  OUR SHEET METAL PEOPLE EXAMINED THE SPECIMEN THAT WAS REMOVED AND THEY FELT THAT TH	E RADIUS OF THE CONTOUR WAS A BIT SHARP WHERE THE CRACK OCCURRED.  THE AIRCRAFT WAS TEMPORARILY REPAIRED IAW BARA/AVR/66	81/04-DC INSTRUCTIONS FROM THE MANUFACTURER WITH A PERMANENT REPAIR DUE AT THE NEXT C-CHECK.	2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004041300013	20040413	00013	NM  	2004	4	13	CA040315010      	1	20040308	G	3250	65727628	COLLAR          			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG STEERING	WORN            	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA				12000							(CAN) THE TAKE-OFF WAS REJECTED AT 70KTS DUE TO NLG SHIMMEY. BOTH NLG WHEELS REPLACED AND STEERING COLLAR ADJUSTMENT CHE	CKED. AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004041300014	20040413	00014	CE  	2004	4	13	CA040315011      	1	20040308	G	7712	3012347	VALVE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	TORQUEMETER	ERODED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA								PS0164			(CAN) FLIGHT CREW REPORTED OCCASIONAL PROBLEMS WITH TORQUE INDICATION DURING POWER REDUCTIONS. TORQUE INDICATION WOULD H	ANG UP AT VARIOUS HIGH SETTINGS DESPITE POWER REDUCTIONS TO IDLE. FROM A PREVIOUS CASE OF THIS ON ANOTHER AIRCRAFT, THE 	POWER REDUCTION CASE WAS SPLIT WITH AN EXPECTATION THAT THE TORQUEMETER VALVE WAS PREMATURELY WORN, AND IT WAS.   A PREV	IOUS SUBMISSION UNDER AGL-0120 REFLECTS EXACTLY THE SAME PROBLEM, PRESENTATION AND FIX.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004041300015	20040413	00015	EU  	2004	4	13	CA040315012      	1	20040314	G	6730	AC67246	SERVO VALVE     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COLLECTIVE	UNSERVICEABLE   	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) PILOT REPORTED THAT WHEN HE TRIED TO PULL THE COLLECTIVE UP,  IT FELT VERY HEAVY.   IT WAS NOTED DURING TROUBLESHO	OTING THAT THE SPOOL VALVE WAS VERY DIFFICULT TO MOVE AND THEN IT WOULD ONLY MOVE A SMALL AMOUNT.  A SERVICEABLE SERVO W	AS INSTALLED AND CONTROLS CHECKED OUT NORMAL.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2005042700315	20050427	00315		2005	4	27	CA040315013      	1	20040316	G	2435	03601018	BEARING         																	ARMATURE	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						15154					(CAN) LUCAS USES BARDEN BEARINGS WITH THE LUCAS LOGO AND PART NUMBER STAMPED ON. BEARINGS REMOVED MADE BY SKF. LUCAS NEV	ER USED SKF BEARINGS.
2004041300016	20040413	00016	SO  	2004	4	13	CA040315014      	2	20040312	G	8530	538684	BUSHING         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								357431			(CAN) DURING OIL CHANGE, NOTED A .5000 LONG X .1250 INCH WIDE ROUND PIECE OF WHAT APPEARS TO BE BUSHING MATERIAL STUCK O	N THE OIL DRAIN PLUG S MAGNET.  FOUND THE NR 5 CYLINDER CONNECTING ROD S PISTON PIN BUSHING HAD A MISSING PIECE WHICH MA	TCHES THE PIECE FOUND ON THE OIL SUMP DRAIN PLUG.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA
2004071900053	20040719	00053	CE  	2004	7	19	CA040316001      	1	20040301	G	2621		WIRE            			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	SQUIB	MISWIRED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN THE ENGINEER WAS TASKED TO PERFORM A SCHEDULED SQUIB REPLACEMENT IAW THE MAINTENANCE SCHEDULE, HE FOUND THAT 	THE SQUIB WIRING WAS INCORRECTLY WIRED.  SOLUTION: THE ENGINEER RE-WIRED THE SQUIB CORRECTLY.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004072100064	20040721	00064	EA  	2004	7	21	CA040316002      	1	20040223	G	3150	8220179013	CONTROL UNIT    			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					DISPLAY	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) BLEED AIR OVERHEAT CONDITION (LT HAND) DOWNSTREAM OF ENG BLEED AIR SHUT OFF VALVE.  WARNING WAS INTERMITTENT, BUT 	REMAINED ON.  FOLLOWING AFM PROCEDURES, LT ENG WAS SHUT DOWN IN FLIGHT WHEN WARNING PERSISTED AFTER AFFECTED BLEED VALVE	 WAS CLOSED. AC WAS DIVERTED DEFECT WAS TROUBLESHOT.  AFTER SWAPPING BLEED LEAK CONTROL UNITS, DEFECT APPEARED TO BE REC	TIFIED.  DEFECT REOCCURRED WHILE AC POWER RED UP IN HANGAR.  REVEALED THAT SOURCE OF FALSE INDICATION ORIGINATED IN NR 1	 DISPLAY CONTROL UNIT (DCU).  INVESTIGATION DID NOT REVEAL PREVIOUS EXAMPLES OF THIS TYPE OF FAILURE.  DCU IS DESCRIBED 	AS A COMPLEX COMPUTER THAT MONITORS VARIOUS SYS AND DISPLAYS FAILURES, FAULTS TO FLIGHT CREW. DCU WAS REPLACE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004072100065	20040721	00065	CE  	2004	7	21	CA040316003      	1	20040311	G	3260	MS243313	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	OVERHEATED      	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) AC WAS SITTING ON RAMP WITH GROUND POWER ATTACHED TO AC, AC MASTER SWITCH ON.  SMOKE ORIGINATING FROM LOWER SIDE O	F IB SECTION OF RT WING. CREW WAS NOTIFIED, AC WAS POWERED DOWN ELECTRICALLY, GPU REMOVED. SMOKE STOPPED WITH POWER OFF,	  VERIFIED TO BE COMING FROM RT WHEEL WELL.  CAUSE OF  SMOKE WAS QUICKLY ISOLATED TO LANDING LIGHT SAFETY SWITCH IN RT M	AIN GEAR WELL. THIS PLUNGER TYPE SWITCH IS ACTIVATED BY GEAR DOOR, UPON RETRACTION, REMOVES POWER SOURCE TO LANDING LIGH	T AS BACK UP TO COCKPIT SWITCH. NORMALLY POWER IS ALWAYS APPLIED THROUGH THIS SWITCH.  FAULT WAS ISOLATED TO SWITCH ONLY	, WITH NO ASSOCIATED HEAT DISTRESS TO AC OR TO WIRING. AC ELECTRICAL SYS WAS VERIFIED SERVICEABLE, SWITCH REPLACED.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004041300017	20040413	00017	EU  	2004	4	13	CA040316004      	1	20040218	G	2435	03600923	BEARING         	LUCAS       		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						98103					(CAN) OPERATOR HEARD GRINDING NOISE DURING ENGINE START.  NOISE WAS LOUDEST AT 10 PERCENT NG.  ABORTED START AND INVESTI	GATED.  FOUND RADIAL PLAY AT FAN END OF ARMATURE.  REPLACED STARTER GEN.  SENT FAILED UNIT FOR REPAIRS.  FOUND THE ADE B	EARING HAD RADIAL PLAY, MEASURED .0045 INCH.  INSPECTED FOR CORRECT ASSY AT PREV OVERHAUL, FOUND OK(BRG PART NR TOWARD A	RMATURE).  REMOVED BEARING.  IT RATTLES, IS LOOSE, HAS CONSIDERABLE PLAY BOTH RADIALLY AND AXIALLY.  IF LEFT IN SERVICE,	 THIS WOULD HAVE FAILED AND DESTROYED THE STARTER-GEN WITHIN AFEW HOURS.  BEARINGS WERE REPLACED AND UNIT OVERHAULED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004041300018	20040413	00018	NM  	2004	4	13	CA040316006      	1	20040305	G	2897	W5200100718	WIRE            			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					PYLON	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) RT SPAR FUEL SHUTOFF VALVE CB C1062 ACTIVATED DURING SHUTDOWN AFTER FLIGHT. CB WOULD NOT RESET, AND SPAR VALVE DIS	AGREEMENT LIGHT ALSO ILLUMINATED.  TROUBLESHOOTING REVEALED WIRE HAD CHAFING DAMAGE AT BULKHEAD LOCATED AT STATION PP ST	N 208.40 VISIBLE BEHIND PANEL 313N5018.  WIRE WAS  REPAIRED IAW SWPM20-30-12.  GIVEN THE PROBLEM IS IN THE FLAMMABLE ARE	A OF THE NACELLES, IT IS SUGGESTED THAT THE COMPLETE WIRE BUNDLE CONTAINING WIRE W5200-1007-18 BE INSPECTED REPAIRED AN 	D PROTECTED AS REQUIRED BETWEEN CONNECTION POINTS AT D92292J AT BRACKET AN2285 TO THE VALVE CONNECTOR D2022 AT STN PP ST	N 265.60AFTSN 7524:36 AFCSN 2509	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2004050600009	20040506	00009		2004	5	6	CA040316007      	4	20040304	G	2310	064101700	COUPLER         			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	HF  AMPLIFIER	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA						P2193					(CAN) HF SYS FAILED, SMOKE AND BURN SMELL CAME FROM HF PWR AMP/COUPLER.  UNIT WAS REMOVED AND SENT FOR INSP.  FOUND THAT	 HARDWARE ATTACHING COVER ON CONNECTOR J9524 TO FACEPLATE OF UNIT HAD CONTACTED PRINTED CIRCUIT BD AND SHORTED +28 VDC S	UPPLY TO GROUND. ELEC TRACE MELTED AND OPENED CIRCUIT TO UNIT.   PC BOARD WAS REPAIRED, TRACE REPLACED. UPON TESTING IT 	WAS FOUND THAT COUPLER WOULD NOT TUNE AT ALL. TROUBLESHOOTING DISCLOSED, VSWR SENSOR WAS NOT OPERATING PROPERLY. IT WAS 	DISCOVERED CNTRL BOARD HAD AN OBSOLETE MICROPROCESSOR. MOST OF BOARDS ARE OBSLETE. WIRING ON AC FOR HF SYS WAS TESTED IA	W  WIRING MANUAL AND NO FAULT WAS FOUND. REPLACEMENT HF PWR AMP/COUPLER WAS INSTALLED, SYSTEM TESTED, OK.	2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE
2004041300019	20040413	00019	NM  	2004	4	13	CA040316008      	1	20040305	G	3010	85720014005	BOOT            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT LE DEICE	DELAMINATED     	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA			36874	36874							(CAN) CREW REJECTED TAKE-OFF AT ROTATION DUE TO STICK PUSHER SHAKE.  AIRCRAFT WAS AT MORE THAN 80 KNOTS AT TIME OF REJEC	TION.  FLIGHT RETURNED TO GATE. BOTH STALL SYSTEMS CHECKED SERVICEABLE ON THE GROUND. FOUND THAT THE LT LE DEICE BOOT DE	LAMINATING CAUSING THE STALL/STICK SHAKER TO ACTIVATE. THE LEADING EDGE WAS REPLACED AND THE AIRCRAFT BROUGHT BACK TO SE	RVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004041300020	20040413	00020	NM  	2004	4	13	CA040316009      	1	20040229	G	2750	M390166105L	RELAY           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAP CONTROL	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH FLAPS FAILED TO LOWER WHEN SELECTED. AIRCRAFT DID A GO AROUND AND THE PERFORMED AN UNEVENTFUL FLAPLESS	 LANDING. MAINTENANCE NOTED THAT FLAP POWER CAUTION LIGHT NOT OPERATING WHEN FLAP LEVER SELECTED. TROUBLESHOOTING DISCOV	ERED RELAYS AT 2752-K2 AND 2752-K3 HAD FAILED. RELAYS REPLACED AND FLAPS FUNCTION CHECKED SERVICEABLE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004041600030	20040416	00030		2004	4	16	CA040316010      	4	20040316	G	6122	13101053612033	SOLENOID        	WOODWARD    																GOVERNOR	UNSECURE        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1826703					(CAN) UPON RECEIVING INSPECTION OF EXCHANGE GOVERNOR FROM HONEYWELL IT WAS NOTED THAT THE RESET SOLENOID P/N 1310-105 WA	S LOOSE AND IMPROPERLY LOCKED. ALSO THE 3612-033 PICK UP PLUG WAS FOUND TO BE MISSING LOCKWIRE. THE RESET SOLENOID WAS T	HEN TIGHTENED UP AND PROPERLY LOCKED AND THE PICK UP PLUG WAS LOCKED.
2004041600031	20040416	00031		2004	4	16	CA040316011      	4	20040316	G	6122	46200161310105	ADAPTER         	WOODWARD    																UNFEATHERING	UNSECURE        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						920265					(CAN) UPON RECEIVING AN EXCHANGE GOVERNOR FROM MFG. IT WAS NOTED THAT THE 4620-016 UNFEATHERING ADAPTER PLATE WAS MISSIN	G LOCKWIRE AND THE RESET SOLENOID 1310-105 WAS FOUND TO BE LOOSE AND POORLY LOCKED. THE UNFEATHERING PLATE WAS THEN LOCK	ED AND THE SOLENOID WAS TIGHTENED AND LOCKED PROPERLY.
2004071900079	20040719	00079	EA  	2004	7	19	CA040317001      	1	20040222	G	5270	840534	PROXIMITY SWITCH			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT AT APPROX FL290, (PAX DR OUT HNDL) CAUTION MESSAGE ILLUMINATED.  CREW COMPLIED WITH QRH, INCLUDING VI	SUALLY VERIFYING ALL 8 ALIGNMENT INDICATORS CONFIRMED DOOR LOCKED AND OUTER HANDLE STOWED.  CAS MESSAGE PERSISTED.  LAND	ING WAS UNEVENTFUL AND NO EMERGENCY WAS DECLARED.  REPLACED PROXIMITY SWITCH PS2MB.  PASSED OPS TEST, AIRCRAFT RETURNED 	TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080400216	20040804	00216	EU  	2004	8	4	CA040317002      	1	20040310	G	3242	16402201	BRAKE DISC      			BNORM 	BN2   	BN2B27      	7080227	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISC FAILED AROUND FLANGE.  PART 6 OF SB 7071 ASK PILOTS TO LOOK AT WHEELS DISC ON PRE-FLIGHT INSPECTION, AT THE S	TAGE OF THE CRACK NOW IT WOULD HAVE BEEN NEXT TO IMPOSSIBLE TO SEE THE CRACK WITHOUT CLEANING THE DISC.					1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920
2004042800029	20040428	00029	EA  	2004	4	28	CA040317003      	2	20040309	G	7200		ENGINE          								PWA   	PT6   	PT6A27      	52043	EA  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11359								(CAN) ENG WAS REMOVED FROM WING, NOTED HIGHER THAN NORMAL OIL TEMP, OIL DISCOLORATION. UPON REMOVAL, EXH  DUCT WAS MISSI	NG SECT OF INNER DUCT EXPOSING PT SHAFT HSG TO EXH  GASES.  IT WAS FOUND THAT REAR SECTION OF EXH  DUCT INNER SKI JUMP S	ECTION, EXTENDING FWD FROM NR 3 BRG END ABOUT 5 INCHES HAD DISAPPEARED.  SAME SECTION OF INSULATION BLANKET HAD ALSO DIS	APPEARED.  IMPACT MARKS IN ONE EXH PORT AREA, NO SIGNIFICANT DAMAGE TO PT DISK, BLADES INDICATING THAT EXH  DUCT SKIN HA	D FRACTURED INTO A LARGE NR OF SMALL PIECES.  THERE WERE A NR OF CRACKS EMANATING FROM SURFACE CORROSION PITS IN AREAS A	WAY FROM FRACTURE EDGES THAT EXTENDED ACROSS DUCT WALL.  MATERIAL DEGRADATION WAS PRIMARY CAUSE, FAILURE OF THIS DUCT.						4	T			E4EA
2004041300021	20040413	00021	CE  	2004	4	13	CA040317004      	1	20040311	G	5520	115610010125	SPLINE          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION FOUND THREE VISUAL CRACKS IN OB SECTION OF THE ELEVATOR TRAILING EDGE SPLINE, AS DESCRIBED IN OTHER 	SDR'S /SERVICE DIFFICULTY ADVISORY.					1	L	7	2 	4T	4	T	 	A14CE   	E2WE	6	C	P40EA
2004041300022	20040413	00022	EA  	2004	4	13	CA040318001      	2	20040309	G	7250	3032151	RING            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE VANE	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE HOT END BORESCOPE INSPECTION, HOT END DISTRESS WAS NOTED.  POWER SECTION REMOVED FROM AIRCRAFT, HOT	 END REMOVED. COMBUSTION CHAMBER CRACKED (MANY) ON NR 2 LOUVERED COOLING RING.  SMALL DUCT BURNED/WARPED IN TWO AREAS (V	ANES).  VANE RING ASSEMBLY, SEVERE BURNING ON 1 VANE AT TRAILING EDGE APPROXIMATELY .5 SQUARE INCH MISSING.  ADJACENT VA	NE TRAILING EDGE CRACKED. VANE RIM BURNED AND CRACKED (3032151).  HOUSING ASSEMBLY, CT SHROUD, ONE SEGMENT 3018503 WARPE	D INWARD CAUSING CT BLADE CONTACT.   BLADE LEADING EDGE AT TIP ROUNDED. DISK/BLADE ASSEMBLY, CONTACT WITH WARPED BLADE S	HROUD SEGMENT.	1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004041300023	20040413	00023	SW  	2004	4	13	CA040318003      	1	20040309	G	6510	2120406883	COUPLING        	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					DRIVESHAFT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A20218					(CAN) DRIVESHAFT UNDERGOING SCHEDULED 600 HR/12 MONTH INSPECTION/LUBRICATION.  COUPLING HAS EXCESSIVE CORROSION.  PART R	EPLACED. COUPLING P/N 212-040-688-3.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004041300025	20040413	00025	SW  	2004	4	13	CA040318004      	1	20040311	G	6420	AN5161A	GREASE FITTING  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR	CLOGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 50 HOUR LUBRICATION INTERVAL. FITTINGS WOULD NOT PASS GREASE. FITTING REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2004041300026	20040413	00026	WP  	2004	4	13	CA040318005      	1	20040315	G	5610	5887275505	WINDSHIELD      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CENTER WINDSHIELD CRACKED IN FLIGHT AND SPARK, CREW DECIDED TO TURNBACK. THE CENTER WINDSHIELD WAS REPLACED IAW TH	E MM 56-10-01. THE WINDSHIELD ANTI-ICE AND ANTI-FOG SYSTEM WAS CHECKED SERVICEABLE IAW THE AMM.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004050300163	20040503	00163	CE  	2004	5	3	CA040318006      	1	20040304	G	5330	1304300515	SKIN            			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSP, SEVERAL LOOSE RIVETS IN FWD AREA OF PRESSURE VESSEL, 2 RIVET HEADS SHEARED OFF AT FS 201.775.  AFTER 	REMOVING ELEC PANEL AND DUCTS UNDER CABIN FLOOR, CRACKS WERE DETECTED IN RADIUS OF RIB WHERE IT ATTACHES TO STINGER 16, 	15L. STRIPPED PAINT OFF BELLY FROM FS 158 TO 201 TO FACILITATE CLOSER INSP 2 CRACKS WERE VISUALLY DETECTED IN SKIN AROUN	D RIVET HOLES FOR STRINGERS 16.  HAD EDDY CURRENT TESTING ON ENTIRE AREA WITH CRACKS FOUND AND NOTED IN BELLY SKIN AT FS	179.525 AT 1ST RIVET LT OF C/L , 1ST RIVET RT OF CENTER LINE AND 8TH RIVET RT OF CENTER LINE. EDDY CURRENT TESTING WAS  	CARRIED OUT ON RIB WITH CRACKS NOTED IN RADIUS ON OB SIDE OF STRINGER 15 LT AND BOTH SIDES OF STRINGER 16 (C/L).	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004080500022	20040805	00022	EA  	2004	8	5	CA040318007      	1	20040318	G	7830		THRUST REVERSER 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) EICAS MSG R REV. UNLOCKED DISPLAYED DURING FINAL APPROACH. ENG POWER WAS AT IDLE. NOTICED AC ROLL AND YAW.   EMERG	ENCY STOW SELECTED AND A/P DISCONNECTED.  RT REVERSER NOT SELECTED ON LANDING ROLL.  REVERSER DEACTIVATED AND AC DXD UND	ER MEL. VERBAL COMMENT FROM THE CREW WAS THAT THEY FELT THE REVERSER HAD UNLOCKED/PARTIALLY DEPLOYED FLT RECORDER PULLED	 FOR FURTHER EVALUATION.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080500023	20040805	00023	NE  	2004	8	5	CA040318009      	2	20040317	G	7200		ENGINE          			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA								GEE950064			(CAN) WHILE CARRYING OUT RELIGHT TESTS, RT ENGINE DID NOT RELIGHT VIA WINDMILL OR ATS.EMERGENCY WAS DECLARED AND SUCCESS	FULL SINGLE ENGINE APPROACH WAS COMPLETED WITHOUT FURTHER INCIDENT.  RT ENGINE WAS REPLACED AND AC FLOWN SINCE WITHOUT F	URTHER INCIDENTS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004041300027	20040413	00027	EU  	2004	4	13	CA040319001      	1	20040312	G	2731	Z4244120000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	ELEVATOR TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION, IT WAS NOTICED THAT THE AFT TRIM CABLE HAD A BROKEN STRAND FORWARD OF THE RT PULLEY 	NEAR THE TRIM DRUM.  THROUGH EXPERIENCE IT WAS FOUND THAT CONDITION WOULD LEAD TO A TOTAL FAILURE OF THE CABLE IN THE NE	AR FUTURE.  THE CABLE WOULD FRAY SO MUCH THAT IT WOULD BIND UP IN THE DRUM ASSEMBLY RENDERING THE ELEVATOR TRIM SYSTEM I	NOPERABLE. THIS SYSTEM IS CLOSELY INSPECTED EVERY 100 HOUR INSPECTION DUE TO SIMILAR FAILURES OF THIS CABLE.			1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE
2004041300028	20040413	00028	CE  	2004	4	13	CA040319002      	1	20040309	G	3020	1099100491	ANTI-ICE SYSTEM 			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIR INTAKE ANTI-ICE LIP WAS FOUND CRACKED AT THE WELDED ATTACH JOINTS AT BASE OF EXHAUST INLET/OUTLET TUBES.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2005042700316	20050427	00316	EU  	2005	4	27	CA040319003      	1	20040304	G	2820		VALVE           			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					FUEL SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) CREW REPORTED SEVERAL INCIDENTS OF UNEXPLAINED FUEL LOSS FROM RT FUEL SYS RESULTING IN INCONSISTENT FUEL IMBALANCE	S ON VARIOUS OCCASIONS. NO VISIBLE SIGNS OF FUEL SYS LEAKAGES WITHIN ACRFT NOR ON GROUND.  FUEL QTYS CLOSELY MONITORED B	Y CREW WHILE TROUBLE SHOOTING PERFORMED.  AIR RELEASE VALVE, & SUCTION VALVE BOTH REPLACED DURING TROUBLESHOOTING THIS C	ORRECTED DISCREPANCY.  BOTH VALVES HAVE BEEN SENT OUT FOR BENCH CHK, & RESULTS WILL BE SUBMITTED WHEN THE SHOP REPORTS A	RE RETURNED TO IDENTIFY THE CULPRIT(S).		2	L	7	2 	4F	4	F	RT	A28NM   	E311NE
2004080500024	20040805	00024	CE  	2004	8	5	CA040319005      	1	20040312	G	2820	652635537	LINE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL TANK	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE INSP PROCESS OF SB550-28-14, WING FUEL BOOST PUMP WIRING INSPECTION, IT WAS NOTED THAT BOOST PUMP WIRIN	G WAS RUBBING ON MAIN EJECTOR TO CHECK VALVE ALUMINUM FUEL LINE P/N 6526355-37, CAUSING CHAFFING WEAR THROUGH FUEL LINE.	 THE WEAR WAS APPROX 75 PERCENT OF WALL THICKNESS ON LT FUEL TANK LINE AND 45 PERCENT ON RT FUEL TANK LINE. THERE WAS NO	 NOTICABLE WEAR THROUGH WIRING OUTTER INSULATION AROUND AREA IN CONTACT WITH LINE. BOTH LT AND RT FUEL LINES WERE REPLAC	ED WITH NEW.   SB KIT INCLUDES INSTALLATION OF NEW CLAMPS AND STAND OFFS TO HOLD THE BOOST PUMP WIRING AWAY FROM ALL STR	UCTURE AND FUEL LINES AS WELL AS RE-ROUTE WIRE UNDER RATHER THAN OVER THE FUEL LINE NOTED.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004041300030	20040413	00030	NM  	2004	4	13	CA040319006      	1	20040317	G	2421	700842A	CSD             			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					AC GENERATOR	FAILED          	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, IT WAS OBSERVED THAT ELECTRICAL POWER WAS LOST WITH NR 3 GENERATOR. A REJECTED TAKE-OFF WAS CARRIE	D OUT AND AIRCRAFT RETURNED TO THE GATE WITHOUT INCIDENT. NR 3 ENGINE CONSTANT SPEED DRIVE WAS DISCONNECTED AND SYSTEM W	AS DEFERRED IAW MEL 24-01. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2005011200012	20050112	00012	EA  	2005	1	12	CA040321001      	1	20040317	G	5610		STRAP           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					WINDSHIELD	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DE-ICE FLUID AND WATER APPEARS TO BE LEAKING AROUND THE FOS MAP LIGHT. FOUND FLUID LEAKING FROM THE RT I STRAP FAS	TENERS BETWEEN THE FOS WINDOW AND WINDSHIELD. I STRAP WAS RE-SEALED AND RE-TORQUE.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005011200013	20050112	00013	EA  	2005	1	12	CA040321002      	1	20040118	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE CAPTAIN WINDSHIELD HAD SHATTERED IN CRUISE. THE WINDSHSIEL IS THE NEW CONFIGURATION. THE WINDSHIELD WAS REMOVE	D AND REPLACED.					2	L	7	2 	4F			RT	A21EA
2005011200014	20050112	00014	EA  	2005	1	12	CA040321003      	1	20040113	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF341A      	 	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE LEFT SIDE WINDOW HAD SHATTERED.  AN EMERGENCY DESCENT WAS TAKEN.THE REMAINDER OF THE FLIGHT, APPROACH AND LAND	ING WERE UNEVENTFUL. THE WINDOW WAS REPLACED. THE WINDOW IS OLDER VERSION.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005011200015	20050112	00015	CE  	2005	1	12	CA040322001      	1	20040224	G	2912	99122813	FILTER HOUSING  			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ANTI SKID PUMP	BROKEN          	W				D				RETURN TO BLOCK         				K	W		FLUID LOSS                	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI PRIOR TO TAKE-OFF EXPERIENCED A BRAKE ANTI-SKID PUMP FILTER BOWL FAILURE WITH A HYDRAULIC FLUID LOSS. 	THIS EVENT OCCURRED BEFORE ON NOV. 19, 2002 (1725.6 HRS TTSN AND 1534 TCSN), ON BOTH TIMES A CRACK WAS FOUND ON FILTER B	OWL THREADS.THE FIRST FAILURE WAS REPORTED TO CESSNA AND THE DEFECTIVE PART WAS SENT FOR INVESTIGATION AND THE FILTER BO	WL CRACKED WAS DUE TO A MACHINING DEFECT DURING MANUFACTURE. SEVERAL FILTER BOWLS WERE OFFSET DURING MACHINING, WHICH CA	USED A THIN WALL AT THE THREADS AND COULD CRACK.A SECOND SCR REPORT WILL BE SENT TO CESSNA. WE ARE EVALUATING THE NEED T	O REPLACE THE HOUSING ON A REGULAR BASIS TO PREVENT RE-OCCURRENCE, UNTIL CESSNA PROVIDE A FIX.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004041600032	20040416	00032	NM  	2004	4	16	CA040322002      	1	20040319	G	5210	693741810	ROLLER CAM      			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					PAX DOOR	SHEARED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, CREW HEARD A LOUD BANG AND FELT A CORRESPONDING PRESSURE BUMP. UPON RETURNING TO THE APRON, IT WAS D	ISCOVERED THAT THE AFT UPPER GUIDE ROLLER ON THE MAIN ENTRANCE DOOR HAD SHEARED OFF. AFTER INSPECTING THE DOOR, THE CREW	 ELECTED TO CONTINUE THE FLIGHT UNPRESSURIZED. THE A/C RETURNED TO A MAINTENANCE FACILITY WHERE THE DOOR WAS REPLACED.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004080500056	20040805	00056	WP  	2004	8	5	CA040322003      	2	20040312	G	7200		ENGINE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LEFT	FLUCTUATES      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			15839					P44720C			(CAN) AIRCRAFT TOOK OFF AND THEN PILOT RETURNED WHEN HE NOTICED THAT THE LT ENGINE EGT WAS FLUCTUATING.  RUNUPS WERE CAR	RIED OUT BY MAINTENANCE AND CONFIRMED THAT WHEN THE SHORT HARNESS WIRING WAS WIGGLED THE INDICATION WOULD FLUCTUATE.  CO	NTACTS WERE CLEANED AND WIRING SECURED.  NO OTHER FLUCTUATIONS HAVE BEEN NOTICED SINCE .				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2004080500057	20040805	00057	EA  	2004	8	5	CA040322004      	1	20040322	G	2913	848847	PUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FAULT:AFTER TAKE-OFF MASTER WARNING AND GEAR DISAGREE MSG ON EICAS. ACTION:  FOUND METAL CONTAMINATION IN HYD. SYS	T. NR 3, IN RETURN PRESS, CASE DRAIN FILTERS.  ALL FILTERS REPLACED AND SYSTEMS FLUSHED IAW AMM 29-10-00-617-803.   HYD 	PUMPS 3A, B REPL'D.  NOSE GEAR STRUT SERVICED AND G/SWING C/OUT IAW AMM 32-20-00.  ACFTSERV.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080500058	20040805	00058	SO  	2004	8	5	CA040322005      	2	20040310	G	7414	103493504	MAGNETO         			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	ENGINE	FAILED          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) THE LT MAGNETO FAILED OPERATIONAL MAGNETO CHECK DURING PRE FLIGHT RUN-UP. AT TIMES THE RPM WAS NOTED TO HAVE DROPP	ED BY 200. DURING SUBSEQUENT TROUBLESHOOTING IT WAS NOTED THAT THE MAGNETO DROP WAS WELL WITHIN LIMITS AT 50 RPM BUT WOU	LD LATER DROP TO A TOTAL OF 200 RPM. EVERY 3 SECONDS THE RPM DROP WOULD CHANGE FROM 50/ 200 RPM. THE SAME CONDITION EXIS	TED AT HIGH POWER SETTINGS AS WELL. WITH BOTH MAGNETOS OPERATING AT HIGH POWER A SLIGHT RPM CYCLING COULD BE DETECTED. T	WO LOWER SPARK PLUGS WERE REPLACED DUE TO CARBON FOULING. THE MAGNETO WAS REMOVED AND INSPECTED AND FOUND CONTAMINATED W	ITH ENGINE OIL DUE TO A FAILED SHAFT SEAL. UNIT WAS REPLACED AND THE AIRCRAFT GROUND CHECKED SERVICEABLE.	1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
2005011200016	20050112	00016	EA  	2005	1	12	CA040322006      	1	20040311	G	4920	3846068	PLENUM          			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502*     	41580	EA  					APU	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						P110					(CAN) WHEN APU STARTED IT WOULD NOT ACCELERATE PAST 40 PERCENT. INVESTIGATION FOUND A LARGE BREACH OF PLENUM ASSY. NATUR	E OF FRACTURES APPEARS TO BE FATIGUE RELATED DUE TO VIBRATION. APU REMOVED AND FURTHER INVESTIGATION REVEALED A COMPLETE	LY DETACHED PIECE BROKEN BRACKET RESTING IN THE COMPRESSOR INLET DUCT. PIECE WAS IDENTIFIED AS A BROKEN FLANGE FROM THE 	INSIDE OF THE INLET DUCT. INSPECTION OF THE COMPRESSOR ROTOR SHOWED SIGNIFICANT DAMAGE FROM CONTACT WITH THE BRACKET. EL	BOW TUBE ASSEMBLY P/N 3846007-1 ATTACHED TOTHE INLET PLENUM WAS ALSO FOUND TO BE LOOSE AND WORN FROM VIBRATION. WHEN THI	SAPU WAS INSTALLED IT WAS REPORTED TO HAVE A HIGH PITCH WHINE. THE CAUSE WAS NOT DETECTIBLE. IT OPERATED NORMALLY UNTIL	2	L	7	2 	4F	4	F	RT	A21EA   	E6NE
2004041600033	20040416	00033	SO  	2004	4	16	CA040322007      	2	20040311	G	8530	631397	CYLINDER HEAD   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	SEPARATED       	W				O				OTHER                   				E	D	B	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	SMOKE/FUMES/ODORS/SPARKS  	CR	CRUISE         	1			CA								195786R			(CAN) IN FLIGHT SEPARATION OF CYL NR 3 HEAD.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P36EA
2004041600034	20040416	00034	NM  	2004	4	16	CA040322008      	1	20040322	G	2520	25606801	SEAT BACK       			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					CABIN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE IN THE AIR, SEATBACK 17K BROKE AT HINGE CAUSING PAX WHO WAS SITTING IN SEAT TO HURT THEIR BACK. YYZ MTCE TO 	REPAIR DURING O/NIGHT.STUD PIVOT PIN REPLACED.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004041600035	20040416	00035	WP  	2004	4	16	CA040323001      	1	20040318	G	4900		CSD             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					APU	OVERSERVICED    	W				A				UNSCHED LANDING         				W	M	J	INADEQUATE Q C            	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING CRUISE FROM FLL, LT CSD OIL TEMP WENT HIGH. GENERATOR SWITCHED OFF. AIRCRAFT LANDED BACK TO FLL DUE TO APU 	NOT START. MAINTENANCE FOUND LT CSD OIL OVERFILLED. CSD RESERVICED IAW MM AND AIRCRAFT DISPATCHED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004080500059	20040805	00059	EU  	2004	8	5	CA040323002      	1	20040318	G	2923	9603001153	PUMP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		LD	LANDING        	1			CA											(CAN) AIRCRAFT WAS ON DECENT. WHEN GEAR DOWN WAS SELECTED DOWN GRINDING NOISES WERE HEARD IN THE CABIN AND THE NOSE DOWN	 AND LOCKED LIGHT WAS NOT ILLUMINATED. EMERGENCY PROCEDURES WERE USED TO GET THE NOSE DOWN LOCKED LIGHT AND THE A/C WAS 	LANDED WITHOUT FURTHER INCIDENT. HYDRAULIC FLUID WSA NOTICED LEAKING IN THE POWER PACK AREA. THE A/C WAS FERRIED. ON CHA	NGING THE POWER PACK A CRACK WAS DISCOVERED ON THE PUMP BODY ON THE OPPOSITE END FROM THE MOTOR.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005011200017	20050112	00017	SW  	2005	1	12	CA040323003      	1	20040323	G	3211	71470209L	TUBE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FUSELAGE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS INSTRUCTED BY THE NATIONAL DEFENSE SPECIAL INSPECTION, THE VERTICAL TUBE, ON THE LT SIDE OF THE A/C JUST ABOVE 	THE LANDING GEAR TUBE STRUCTURE, WAS FOUND BROKEN JUST ABOVE THE WELD.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874
2005011200018	20050112	00018	WP  	2005	1	12	CA040323005      	2	20040313	G	7200		ENGINE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RIGHT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			15475								(CAN) RT ENGINE EXPERIENCED RPM FLUCTUATIONS AND SRL LIGHT ANNUCIATOR LIGHT FLICKERING.  AIRCRAFT RETURNED TO BASE.  PIN	 B ON INLET TEMP WIRING REPAIRED.  AIRCRAFT RETURNED TO SERVICE					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2005011200019	20050112	00019	CE  	2005	1	12	CA040323006      	1	20040318	G	2760		ROLL PIN        			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					SPOILER MIXER	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) DURING MX, FOUND 1 ROLL PIN LOOSE AND ONE ROLL PIN MISSING ON THE LT OUTPUT SECTOR OF THE ROLL SPOILER MIXER UNIT.	 - STILL HAD ISSUES WITH RIGGING AND REMOVED AND OPENED UP THE SPOILER MIXER UNIT. FOUND ANOTHER ROLL PIN MISSING AND ON	E LOOSE ON THE L/H OUTPUT SECTOR (INSIDE THE UNIT) - CLOSER INSPECTION OF THE ROLL PINS SHOWED THEY HAD BEEN TAPERED DUR	ING INSTALLATION - WE HAD PREVIOUSLY COMPLIED WITH SB750-27-38 WHICH CALLS OUT FOR A ONE TIME INSPECTION OF SPOILER MIXE	R UNIT FOR LOOSE OR MISSING ROLL PINS (DOES NOT REQR AN INSPECTION OF PINS INSTALLED WITHIN THE UNIT)- REV 1 OF THEBULLE	TIN STATES NO REWORK REQR ON AIRCRAFT THAT HAVE PREVIOUSLY COMPLIED WITH THE ORIGIANL ISSUE.- THE ROLL SPOILER MIXER UNI	2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH
2005011200020	20050112	00020	CE  	2005	1	12	CA040323007      	1	20040322	G	3230	PDLM60	CIRCUIT BREAKER 			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	HYD PUMP	TRIPPED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THE 60 AMP BREAKER THAT PROTECTS THE HYDRAULIC LANDING GEAR PUMP MOTOR CIRCUIT TRIPPED WHEN THE GEAR WAS RETRACTED	 AFTER TAKE OFF. THE CREW ELECTED TO BLOW THE GEAR DOWN AND RETURNED TO BASE WITHOUT FURTHER INCIDENT.   HYDRAULIC SYSTE	M ON THIS AIRCRAFT ORIGINALLY HAD A 120 AMP BREAKER IN THIS CIRCUIT BUT IT WAS CHANGED TO 60 AMPS TO COMPLY WITH AD 95-1	3-03. THIS AD WAS INTENDED FOR MECHANICAL RETRACTION SYSTEM. THE HYDRAULIC SYSTEM HAS A 100 AMP MOTOR WHICH RUNS LONGER 	THAN THE MECHANICAL SYSTEM AND IS PRONE TO NUISANCE TRIPS OF THE 60 AMP BREAKER. THE AD SHOULD BE NOTED AS NOT APPLYING 	TO HYDRAULIC SYSTEMS WHICH SHUTS OFF BY VIRTUE OF A HYDRAULIC PRESSURE SWITCH.	1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA
2005011200021	20050112	00021	CE  	2005	1	12	CA040324001      	1	20040324	G	3233	MS28775328	O-RING          	LEAR        		LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG ACTUATOR	SEPARATED       	W				B				EMER. DESCENT           				K			FLUID LOSS                			DE	DESCENT        	1			CA						KL0055					(CAN) RT MAIN GEAR DOWN AND LOCK LIGHT WON'T COME ON. FLIGHT CREW EXTENDED THE GEAR WITH THE BLOW DOWN SYSTEM. MAINTENAN	CE CREW FOUND A HYDRAULIC (O-RING) SEAL SEPERATED IN TWO INSIDE THE RT MAIN LANDING GEAR SIDE BRACE ACTUATOR ASSY. ACTUA	TOR ASSY REPAIRED.				2	L	7	2 	4F	4	F		A10CE   	E6WE
2005011200022	20050112	00022	CE  	2005	1	12	CA040324002      	1	20040315	G	2432		BATTERY         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MASTER	DISCHARGED      	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) PILOT REPORTED COMPLETE ELECTRICAL FAILURE AND LANDED WITH GEAR MANUALLY EXTENDED. INSPECTION FOUND STARTER SWITCH	ES IN THE 'ON' POSITION AND BATTERY DOWN TO 12VOLTS, NO OTHER INDICATION OF FAULT WAS FOUND. I FEEL THAT WITH THE SWITCH	ES IN THE 'ON' POSITION, THE GENERATORS WERE NOT CHARGING THE BATTERY, AND THE BATTERY EVENTUALLY EXHAUSTED ITSELF TO TH	E POINT WHERE IT COULD NO LONGER POWER THE SYSTEMS.			1	L	7	2 	4T	4	T		A24CE   	E4EA
2005011300012	20050113	00012	EU  	2005	1	13	CA040324003      	1	20040307	G	6720	350A33020004	BELLCRANK       			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					TAIL ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR BELLCRANK FOUND WITH WEAR DAMAGE ON INSIDE YOKE AREA AT THE ATTACHMENT BOLT WITH THE TAIL ROTOR PITCH C	HANGE SPIDER. THE WEAR CORRESPONDS TO THE BEARING SURFACE OF BALL END P/N 350A33-2150-01. IT IS SUSPECTED THAT THE ATTAC	HMENT BOLT WAS NOT TORQUED TO SPECIFICATIONS AND CAUSED MOVEMENT AND WEAR.				1	G	7	2 	3U	3	U		H11EU   	E4CE
2005011300013	20050113	00013	EU  	2005	1	13	CA040324004      	1	20040307	G	6220	350A37122823	RING            			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ALL 3 DROOP RING YOKES WERE FOUND WITH WEAR DAMAGE ON OUTSIDE DIAMETER. THIS WEAR CORRESPONDS WITH WEAR FOUND ON T	HE DROOP RING CONTACT FITTINGS P/N 350A31-1852- 20 ON EACH STAR ARM.  SUSPECT THAT THE YOKES WERE AT ONE TIME INSTALLED 	UNDER EACH STAR ARM AND CONTACTED THE DROOP FITTINGS.  BOTH PARTS WERE INSPECTED FOR DEFORMATION AND CRACKING.  NO FURTH	ER DEFECTS FOUND.  THE AS355 MAINTENANCE WORK CARD 62.20.00.401 PARA 3 SIMPLY STATES' POSITION YOKES 120 DEG. APART'.  H	OWEVER WORK CARD 62.20.16.401 PARA 3 STATES 'POSITION EACH YOKE BETWEEN 2 ARMS OF THE ROTOR HUB'.  THE MANUFACTURER HAS 	BEEN CONTACTED TO MODIFY THE STATEMENT IN WORK CARD 62.20.00.401.	1	G	7	2 	3U	3	U		H11EU   	E4CE
2005011300014	20050113	00014	GL  	2005	1	13	CA040324005      	2	20040324	G	7323	2522125	LEVER           								ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CAM LEVER WAS INSTALLED INCORRECTLY.  THE LEVER CAN BE INSTALLED POINTING EITHER UP OR DOWN (THE ORIENTATION O	F THE LEVER ON THE PT6 IS OPPOSITE TO THAT OF ROLLS ROYCE).  THE CALIBRATION PROCESS DONE DURING THE OVERHAUL IS UNAFFEC	TED BY THE ORIENTATION.  THE INCORRECT ORIENTATION WAS NOT NOTICED UNTIL THE PART WAS BEING INSTALLED BY A CUSTOMER WHO 	WAS UNABLE TO CONNECT THE AIRFRAME CONTROL TO THE UNIT.  UNITS WERE RECALLED AND ONE OTHER GOVERNOR WAS FOUND TO HAVE IT	S LEVER INCORRECTLY INSTALLED.  CHANGES HAVE BEEN MADE TO THE COMPANY'S INTERNAL OVERHAUL PROCESS DOCUMENTATION TO ENSUR	E THE LEVER IS CORRECTLY INSTALLED,  AS THE OEM OVERHAUL MANUAL COULD BE MORE DESCRIPTIVE ABOUT THE ORIENTATION.						3	U			E4CE
2005011300015	20050113	00015	EU  	2005	1	13	CA040324007      	1	20040302	G	7830	32726023	ROD END         			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					JACKSCREW ACT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						GRTE1062					(CAN) DURING ROUTINE INSPECTION, NR 1 ENGINETHRUST REVERSER RT TRANSLATING COWL LOWER JACKSCREW ACTUATOR ROD END FOUND S	HEARED IN THREADPORTION OF ROD END. JACKSCREW ACTUATOR ASSEMBLY REPLACED AND SYSTEM VERIFIED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2005011300016	20050113	00016	EU  	2005	1	13	CA040324008      	1	20040320	G	2750	132002260	SWITCH          			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT ARRIVED WITH FLAP UNABLE TO RETRACT PAST THE INTERMEDIATE POSITION OF +-5 DEGREES.UPON INVESTIGATION FOUN	D THE LEFT HAND OUTBOARD VANE JAM DETECTOR UNIT SWITCH SHEARED AND INTERNALLY JAMMED AND BUFFER CRUSHED. THE BRACKET/SWI	TCH ASSEMBLY WAS REPLACED AND SYSTEM VERIFIED SERVICEABLE. FAILURE IS UNDER INVESTIGATION TO DETERMINE IF FATIGUE OR WEA	THER ( ICE ) WOULD BE THE CAUSE.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2005011300017	20050113	00017	EU  	2005	1	13	CA040324009      	1	20040324	G	7830	32726023	ROD END         			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					JACKSCREW ACT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AEX22761C					(CAN) DURING TROUBLE SHOOTING A DEFECT ON NR 2 ENGINE REVERSER, LT LOWER SLEEVE NOT STOWING PROPERLY, FOUND THE LOWER JA	CKSCREW ACTUATORROD END BROKEN. ACTUATOR ASSEMBLY REPLACED AND SYSTEM VERIFIED SERVICEABLE. THIS IS THE SECOND EVENT WIT	H THE SAME FAILURE WITHIN 3 WEEKS. THE FAILURES ARE UNDER INVESTIGATION BY THEENGINEERING GROUP.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2005011300018	20050113	00018	EA  	2005	1	13	CA040324010      	1	20040320	G	3010	GG670800121	CONTROLLER      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										ANTI ICE  LEAK	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN)  ANTI-ICE LEAK CONTROLLER HAS BEEN REPLACED FOLLOWING A FLIGHT SNAG CONCERNING A CAUTION MESSAGE. A NEW AILC WAS S	UPPLIED AND REPLACED ON THE AIRCRAFT. THIS NEW AILC HAD A DIFFERENT PART NUMBER USED ON MODEL CL-600-2D24 BUT WAS INSTAL	LED ON AIRCRAFT CL-600-2C10. THE BOX IS SIMILAR BUT IS NOT APPROVED ON THIS LAST MODEL. AIRCRAFT WAS RELEASED FOR PRODUC	TION FLIGHT IN AN IFR PREVALING WEATHER. NO FAULT WERE FOUND AND THE AIRCRAFT COMPLETED THE FLIGHT WITHOUT A PROBLEM.IT 	COULD HAVE HAD AN HAZARDOUS ENDING (WE DIDN'T KNOW). THE AILC WAS THEN REMOV ED AND REPLACED BY A GOOD PN, THE AIRCRAFT 	RE-TESTED AND THEN FOUND SERVICEABLE.	2	L	7	2 	4F			RT	A21EA
2005011300019	20050113	00019	CE  	2005	1	13	CA040324011      	1	20040324	G	2730	187504	BELLCRANK       			BEECH 	18    	3NM         	1151044	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK WAS DISCOVERED IN THE ELEVATOR BELLCRANK AT THE POINT WHERE IT ATTACHES TO THE CONTROL COLUMN ASSY. THE CR	ACK ORIGINATES AT ONE OF THEHOLES FOR TAPER PINS WHICH ATTACH THE ARM TO THE SHAFT OF THE BELLCRANK. AD 77-19-07 CALLS F	OR PERIODIC INSPECTION OF THIS PART FOR CRACKS. THE BELLCRANK ASSY WAS REPLACED.				1	L	7	2 	3R	3	R		A765    	5E1
2004080600021	20040806	00021	NM  	2004	8	6	CA040325002      	1	20040325	G	2782	269002916	ACTUATOR        			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					LE FLAP	LEAKING         	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH INTO CYVR SELECTED FLAPS 2, AMBER IN-TRANSIT LIGHT STAYED ON. NR 7 SLAT DID NOT EXTEND. HYDRAULIC SYST	EM (A) LOW PRESSURE LIGHTS ILLUMINATED AND HYDRAULIC (A) SYSTEM QUANTITY INDICATED ZERO QUANTITY. AIRCRAFT WAS VECTORED 	AND CREW PERFORMED HYDRAULIC LOSS CHECK LIST AND ONE SLAT INOP. LANDING CHECK LIST. AFTER CHECK LISTS COMPLETED AN EMERG	ENCY WAS DECLARED AND THE AIRCRAFT LANDED AND WAS TOWED TO THE RAMP.  NR 7 SLAT ACTUATOR END CAP THREADS FAILED CAUSING 	A LEAK AND LOSS OF HYDRAULIC FLUID.		2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004042100018	20040421	00018	EA  	2004	4	21	CA040325003      	2	20040322	G	7314	69159	ADAPTER         			PIPER 	PA31  	PA31300     	7103104	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ACC CASE	BROKEN          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) OIL LOSS WAS NOTED BY PILOTS AS THE OIL PRESSURE DROPPED. INFLIGHT SHUTDOWN WAS INITIATED. ON LANDING, MAINTENANCE	 DISCOVERED THAT THE ENGINE DRIVEN FUEL PUMP DRIVE ADAPTER HAD BROKEN AND CAUSED THE LOSS OF OIL FROM THE ACCESSORY CASE	. ALSO NOTED WAS THAT THE EDFP IDLER GEAR HAD BROKEN GEAR TEETH. P/N OF THE IDLER GEAR IS LW-10324. ENGINE HAS BEEN REMO	VED AND SENT FOR REPAIR OR OVERHAUL.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004080600022	20040806	00022	EU  	2004	8	6	CA040325004      	1	20040322	G	2913	704A33690004	DRIVE ASSY      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD PUMP	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) DURING A HOVER FLIGHT HYDRAULIC WARNING LIGHT CAME ON. THE PILOT STABILIZED THE A/C AND RETURNED TO CAMP IN MANUAL	 CONTROL MODE. UPON INSPECTION, AME DISCOVERED BROKEN HYDRAULIC PUMP PULLEY DRIVE BELT.  BELT REPLACED, A/C RETURNED TO 	SERVICE.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004080600023	20040806	00023	WP  	2004	8	6	CA040325005      	1	20040325	G	5230		DOOR            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					CARGO	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, CREW EXPERIENCED A LOSS OF CABIN PRESSURE AND A CORRESPONDING DOOR WARNING LIGHT. THE CREW RETURNED 	TO DEPARTURE, CYCLED THE C1 DOOR, AND RE-DEPARTED WITHOUT FURTHER INCIDENT.					2	L	7	2 	4R	4	T	 	6A6     	E282
2004042100019	20040421	00019	GL  	2004	4	21	CA040326001      	3	20040323	G	6114		PROPELLER       			PIPER 	J3    	J3L65       	7100546	SO  	CONT  	A65   	A658F       	17003	SO  	MCAULY	1B90	1B90CM      	GL  		CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CUSTOMER REQUESTED REPITCH ONLY. ADVISED CUSTOMER TO OVERHAUL DUE TO VISUAL CORROSION ON PROP CORROSION REMOVED IA	W MANUAL 730720.					1	H	7	1 	3O	3	O	 	A698    	E205	5	N	P842
2004080600024	20040806	00024	NE  	2004	8	6	CA040326002      	2	20040319	G	7230		BLADE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	IMPELLER	BENT            	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) ON TAKE OFF, CREW HEARD A STRANGE WHINING SOUND.  SOUND IDENTIFIED AS FROM NR 1 ENGINE. TAKE OFF REJECTED AT 30 KT	S.   MAINTENANCE FOUND BENT BLADE ON LOW PRESSURE COMPRESSOR IMPELLER.  ENGINE REPLACED. CREW ON PREVIOUS FLIGHT HAD REP	ORTED A BIRD STRIKE.  AIRCRAFT HAD BEEN INSPECTED BY MAINTENANCE WITH NO APPARENT DAMAGE FOUND.  ENGINE S/N TSN:23746 HR	S, TSO:10578 HRS,CYCLES:34323. HOURS AND CYCLES ON IMPELLER BLADE TO BE DETERMINED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080600025	20040806	00025	EA  	2004	8	6	CA040326003      	1	20040322	G	7603		GEARBOX         	AERO        		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE CONTROL	BINDING         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			10352	10352		245					(CAN) PILOT REPORTED THROTTLE ACTION STIFF. MAINTENANCE TROUBLESHOT PROBLEM TO NR 1 ENGINE THROTTLE CONTROL GEARBOX BIND	ING.  NR 1 THROTTLE CONTROL GEARBOX REPLACED.  IT IS NOTED THAT AD CF-2004-01, HAS BEEN ISSUED AGAINST GEARBOX P/N 21001	40-007, ALTHOUGH IN THIS CASE IT WAS A PILOT REPORTED DEFECT AND NOT AS A RESULT OF AN INSPECTION IAW THE AD.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080600026	20040806	00026	CE  	2004	8	6	CA040326004      	1	20040322	G	3230		CONTROL VALVE   			CESSNA	500   	550         	2076604	CE  										MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) AIRCRAFT DEPARTED, ON THE FIRST GEAR DOWN SELECTION THE LT MAIN GEAR DOWN LOCK INDICATION DID NOT ILLUMINATE.  AN 	EMERGENCY EXTENSION PROCEDURE WAS PERFORMED WITH NO LT MAIN GEAR SAFE LIGHT VISIBLE. ON SHORT FINAL THE GEAR CIRCUIT BRE	AKERS WERE RESET TO DETERMINE GEAR SAFE CONDITION AND THREE GREEN WERE OBSERVED INITIALLY AND THEN THE LT GEAR SAFE LIGH	T EXTINGUISHED.  GEAR CIRCUIT BREAKERS WERE LEFT IN TO ENSURE POSITIVE HYDRAULIC SYSTEM DOWN PRESSURE TO THE GEAR. THE A	IRCRAFT LANDED SAFELY AND RETURNED TO BASE. MAINTENANCE DETERMINED THAT THE MAIN LANDING GEAR CONTROL VALVE HAD MALFUNCT	IONED AND REPLACED THE UNIT. THE GEAR RETRACTION SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED TO SERVICE.	1	L	7	2 	4F			 	A22CE
2004080600027	20040806	00027		2004	8	6	CA040326005      	4	20040325	G	2565	7A1510110	SLIDE           			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					CABIN	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13305								(CAN) FOLLOWING A SLIDE RAFT DEPLOYMENT TEST, FOUND SLIDE RAFT DEFLATING AT SLOW RATE BY A PIN HOLE.  PIN HOLE LOCATE ON	 FORWARD TUBULAR SECTION AT APPROXIMATELY 4 FEET FROM GROUND.  DEFECT IS UNDER INVESTIGATION WITH ENGINEERING AND VENDOR	.				1	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2004080600049	20040806	00049	SO  	2004	8	6	CA040326006      	1	20040323	G	7120	8401002	MOUNT           			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O550  	TSIO550C    		SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT CRACKED AT AREA DESCRIBED IN MFG SB NR 1103 REV.B NOTE: THIS SHOULD BE NOTIFIED TO ALL OWNERS BY AN A	IRWORTHINESS DIRECTIVE.					1	L	7	1 	3O	3	O	RT	A25SO   	E5SO	5	C	P920
2004080600055	20040806	00055		2004	8	6	CA040329001      	4	20040327	G	2350	G2412	SELECTOR PANEL  			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					VHF COMMS	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, COMMUNICATIONS WERE LOST.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  TH	E FIRST OFFICER'S AUDIO SELECTOR PANEL WAS SUSPECT.  A HOT MIKE SITUATION WAS APPARENT IN VHF 1 AND VHF 2.  THE AUDIO SE	LECTOR PANEL WAS REPLACED IAW MM 23-20-00 AND CHECKED SERVICEABLE.  NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004080600056	20040806	00056	CE  	2004	8	6	CA040329002      	1	20040318	G	5511	115620010325	RIB             	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18824			B247					(CAN) ON INSPECTION OF THE HORIZONTAL STABILIZER THE UPPER SKIN WAS FOUND TO BE OIL CANNING.  UPON FURTHER INSPECTION IT	 WAS FOUND THAT 6 RIBS WERE CRACKED INTERNALLY (PN 115-620010-325, 115-620010-210, 115-620010-355, 115-620010-255, 115-6	20010-215, 115-620010-209).  WE BELIEVE THIS DAMAGE WAS FROM PEOPLE WALKING ON THE STABILIZER.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA
2004080600057	20040806	00057	CE  	2004	8	6	CA040329003      	1	20040302	G	2420	1101912R	GENERATOR       			CESSNA	180   	180F        	2072614	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GENERATOR WAS FOUND TO BE LOOSE AND SLOPPY.  UPON REMOVAL IT WAS DISCOVERED THAT FRONT LUG HOLE HAD BEEN PREVIOUSL	Y DRILLED AND BUSHED. BOTH GEN MOUNTING LUG HOLES WERE SEVERELY WORN AND ELONGATED, BOLTS WORN, AND BUSHING WORN WITHIN 	.1250 INCH OF SIDE OF LUG.  GEN MOUNT BRACKET (P/N539579) HOLES ALSO ELONGATED.  REPAIR REQUIRED NEW GENERATOR AND NEW M	OUNT BRACKET.  OWNER CLAIMS NO KNOWLEDGE OF PREVIOUSLY UNAPPROVED INSTALLATION OF BUSHING IN GENERATOR. UNAPPROVED REPAI	R CAUSED DAMAGE TO MOUNT BRACKET.  OWNERS SHOULD BE WARNED AGAINST INSTALLING BUSHINGS AT GEN ATTACH POINTS.		1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
2004080600058	20040806	00058		2004	8	6	CA040329004      	4	20040316	G	6122	210385	GOVERNOR        			BEECH 	65    	A65         	1152803	CE  	LYC   	O480  	IGSO480A1E6 	41529	EA  	HARTZL	HCB3Z	HCB3Z202    	GL  	PROPELLER	RUPTURED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE OIL LEAK WAS TRACED TO THE PROP GOVERNOR AND ONLY SHOWED UP AT APPROXIMATELY 2500 RPM.  A PIECE OF GASKET .125	0 INCH WIDE WAS FOUND MISSING FROM THE GASKET WHICH CAUSED A LEAK OF AN ESTIMATED 1 QUART OF OIL EVERY 2 MINUTES.  NO AP	PARENT REASON COULD BE FOUND FOR THE DEFECT.  THE GASKET WAS DESTORYED IN THE PROCESS OF REMOVAL. AS IT WAS STUCK, THE M	ATING SURFACES HAD NO DEFECTS AND HOLD DOWN NUTS WERE TIGHT.  NEW GASKET INSTALLED AND GROUND RUNS CARRIED OUT WITH NO L	EAKS.		1	L	7	2 	3O	3	O	 	3A20    	E284	5	C	P907
2005011300021	20050113	00021	NM  	2005	1	13	CA040329005      	1	20040321	G	2910	82950010161	TUBE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	FLT SPOILER	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) HYDRAULIC SYSTEM FAILURE (NR 1 ISO VALVE AND ROLL SPOILER INBOARD HYDRAULIC CAUTION LIGHTS) HYDRAULIC TUBE FOR LT 	INBOARD FLIGHT SPOILER ACTUATOR (UNLOAD) FOUND WITH PINHOLES.  TUBE REPLACED, FUNCTION AND LEAK CHECKS COMPLETED.  NR 1 	HYDRAULIC EDP WAS NOT RUN DRY (APPROX. 1 LITER IN RESERVOIR ON ARRIVAL). NR 1 HYDRAULIC FILTER BYPASS INDICATORS OK.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005011300022	20050113	00022	NE  	2005	1	13	CA040330001      	3	20040326	G	6197		WIRE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROP FEATHER	CHAFED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) AN OPERATOR CARRIED OUT AN UNSCHEDULED LANDING DUE TO UNCOMMANDED NR 2 PROPELLER FEATHER DURING CLIMB, AND SUBSEQU	ENT OVERTORQUE OF THE NR 2 ENGINE. THEY FOUND THE CAUSE OF THIS PROBLEM WAS: CHAFING OF SEVERAL WIRES (HYDRAULIC SYSTEM,	 PROPELLER AUTOFEATHER SYSTEM, AND GALLEY ELECTRICAL POWER) ON A BRACKET IN THE RT WINGROOT CAUSED A 'MIXTURE' OF 28VDC 	AND 115VAC IN THESE SYSTEM, AND SUBSEQUENT MALFUNCTION OF THE NR 2 PROP AUTOFEATHER SYSTEM. THE AFFECTED BRACKET IN THE 	RT REAR WINGROOT HAS P/N 85350711-001.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005011300023	20050113	00023	NM  	2005	1	13	CA040330002      	1	20040329	G	5620	56B2251733	WINDOW          			BOEING	747   	747433      	       	NM  	PWA   	4056  	PW4056      	 	NE  					ROW 31	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT TOTAL TIME 49,175HRS,7715 CYCLES ITEM NOT A TRACKED ITEM.IN FLIGHT, PASSENGER WINDOW AT ROW 31 CRACKED,IT	 WAS THE OUTER PANE, WITH NO DEPRESSURISATION WINDOW REPLACED.					2	L	7	4 	4F	4	F	RT	A20WE   	E24NE
2005011300024	20050113	00024	GL  	2005	1	13	CA040330003      	2	20040327	G	7260	2062301	COMPUTER        			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13      	03004	GL  					ENGINE DRIVE	MALFUNCTIONED   	W				B	H			EMER. DESCENT           	DEACTIVATE SYST/CIRCUITS			W	J		INADEQUATE Q C            	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ON A CARGO FLIGHT FROM CINCINATI TO MONTRIAL NR 2 ENGINE WAS SHUTDOWN. AIRCRAFT WAS DIVERTED  TO TRENTON ONTARIO B	ECAUSE COCKPIT CREW WERE UNABLE TO CONFIRM THAT THE EDC WAS ACTUALLY DISCONNECTED AFTER SELECTING DISCONNECT, DUE TO LOW	 OIL PRESSURE. THE NORMAL WAY ON PASSENGER AIRCRAFT IS AIR FLOW REDUCTION IN COCKPITT AFTER EDC DISCONNECTED. ON CARGO A	IRCRAFT THERE IS NO REDUCTION OF AIR FLOW DUE TO DUCTING MODIFICATION. MAINTENANCE WAS DISPATCHED TO CONFIRM EDC DISCONN	ECTED AND RELEASE AIRCRAFT IAW MEL PROCEDURE. AIRCRAFT RETURN TO MONTRIALWHERE EDC WAS REPLACED AND AIRCRAFT RETURN TO S	ERVICE.	2	L	7	2 	4R	4	T		6A6     	E282
2005011300025	20050113	00025	NE  	2005	1	13	CA040330004      	2	20040322	G	7250		TURBINE BLADES  								PWA   	PW121 	PW121       	52124	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11575					121337			(CAN) ENGINE SUSTAINED AN LPT BLADE FAILURE DUE TO CREEP OF THE LP BLADES. DEBRIS FROM FAILURE OF THE LPT BLADES RESULTE	D IN EXTENSIVE DOWNSTREAM DAMAGE TO THE PT SECTION.  RESIDUAL VIBRATIONS RESULTING FROM THE LPT BLADE FAILURE CAUSED A N	UMBER OF TUBES IN THE REAR PORTION OF ENGINE TO FRACTURE. 1 OF TUBES WHICH FRACTURED WAS NR 6&7 BEARING OIL PRESSURE SUP	PLY TRANSFER TUBE. FRACTURE OF THIS TUBE RESULTED IN OVRBOARD OIL LEAK & REPORTED LOW OIL PRESSURE INDICATIONS. INFLT SH	UTDOWN HAD OCCURRED DUE TO A LOW OIL PRESSURE IND. THESE BLADES WERE INSTALLED NEW DURING 2000 OVERHAUL & HAVE ACCUMULAT	ED 5049.1 HOURS & 6022 CYCLES OF OPERATION SINCE.  TURBOMACHINE RESTORED TO SERVICE. RGB MODULE WAS BORESCOPE INSPECTED.						4	T			E20NE
2005011300026	20050113	00026	CE  	2005	1	13	CA040330005      	1	20040323	G	3230	NA	WIRE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SWITCH	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF THE CREW SELECTED THE LANDING GEAR UP. THE LANDING GEAR DID NOT MOVE AND STAYED EXTENDED. THE CREW 	PUT THE GEAR HANDLE BACK DOWN AND RETURNED TO THE HANGER. AIRCRAFT PUT ON JACKS AND GEAR RETRACTION TRIED AGAIN WITH NO 	MOVEMENT OF THE GEAR. AFTER INSPECTION IT WAS FOUND THAT 1 WIRE HAD COME DISCONNECTED FROM THE EMERGENCY EXTENTION CLUTC	H MICRO SWITH (SCREW CAME OUT). WIRE REINSTALLED WITH LOCKTITE ON THE SCREW. GEAR FUNCTION CHECKED OK.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005011300027	20050113	00027	SO  	2005	1	13	CA040330006      	1	20040330	G	3620	441CC7	DRIVE SHAFT     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					PNEUMATIC PUMP	SHEARED         	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) PNEUMATIC MALFUNCTION LIGHT WAS ON UNTIL 2000 RPM. TROUBLESHOT SNAG AND FOUND THE DRIVE SHAFT OF PUMP SHEARED.						1	L	7	2 	3O	3	O		A20SO   	E14EA
2005011300028	20050113	00028	SW  	2005	1	13	CA040331001      	1	20040323	G	5510	407023801123	DOUBLER         		407023801109	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					HORIZONTAL STAB	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BP588					(CAN) HORIZONTAL STAB. WAS FOUND WITH AN EDGE DELAMINATION BETWEEN THE STAB TOP SKIN AND THE -123 DOUBLER AT 1.85.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2005011300029	20050113	00029	NM  	2005	1	13	CA040331002      	1	20040319	G	2910	82970009387	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK AROUND BEFORE DEPARTURE PILOT NOTED SUBSTANTIAL HYDRAULIC LEAK FROM NR 2 NACELLE.  MAINTENANCE FOUND N	R 1 SYSTEM LIFT DUMP PRESSURE LINE WITH A PIN HOLE LEAK. LINE REPLACED LEAK AND FUNCTION CHECK CARRIED OUT, AND AIRCRAFT	 RETURNEDTO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005011300030	20050113	00030	SO  	2005	1	13	CA040331003      	1	20040326	G	3220	NAS464P427	BOLT            	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360D1A     	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	SHAFT	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE AIRCRAFT WAS ON A ROUTINE TRAINING FLT & HAD JUST LANDED WHEN THE NLG SUDDENLY COLLAPSED DURING LANDING ROLL. 	ONCE ACFT WAS CLEARED TO BE MOVED FROM RUNWAY, IT WAS TOWED TO RAMP AREA WHERE MX PERSONNEL WERE ABLE TO INVESTIGATE FAI	LURE. EXAMINATION OF THE NLG SYS BY AN AME REVEALED THAT THE DRAG LINK PIVOT BOLT HAD SHEARED & SUBSEQUENTLY BACKED OUT 	OF POSITION CAUSING DRAG LINK MECH TO FAIL. FAILURE OF DRAG LINK MECH IN TURN CAUSED THE NLG TO COLLAPSE. AT THE TIME OF	 THE INVESTIGATION THE AME DETERMINED THAT THE BOLT HAD SHEARED ABOUT HALF WAY ALONG THE SHAFT AND THAT THE END WITH THE	 NUT ATTACHED HAD FALLEN FROM THE AIRCRAFT AND THE REMAINING HALF HAD BACKED OUT ENOUGH TO ALLOW THE LINKAGE TO SEPARATE	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P25EA
2005011300031	20050113	00031	EA  	2005	1	13	CA040331005      	2	20040330	G	8530		PUSHROD TUBE    			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	NR 5 CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								BL516303			(CAN) DURING A TRAINING FLIGHT THE CREW OBSERVED THE RT ENGINE LOW OIL PRESSURE LIGHT HAD ILLUMINATED. THE CREW THEN CHE	CKED THE OIL PRESSURE GAUGE AND NOTED A DROP IN OIL PRESSURE. THE ENGINE WAS SHUT DOWNAND THE PROPELLER WAS FEATHERED. T	HE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION MAINTENANCE NOTED THAT THE PUSH ROD TUBES FOR CYLINDER NR 5 WERE BENT A	ND BROKEN. THE MAIN OIL SCREEN WAS REMOVED FOR INSPECTION AND FOUND CONTAMINATED. THE ENGINE IS BEING REMOVED AND WILL B	EREPLACED WITH A SERVICEABLE QCU AND THE AIRCRAFT WILL BE RETURNED TO SERVICE.		2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879
2005011300032	20050113	00032	EU  	2005	1	13	CA040331006      	1	20040315	G	7120	001269004	ISOLATOR        	BARRYCTRLS  		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE MOUNT	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						864894910					(CAN) DURING A SCHEDULED ENGINE CHANGE NEW ENGINE MOUNT ASSEMBLIES WERE BEING INSTALLED. THREE OUT OF FIVE NEW ENGINE MO	UNT FORWARD VIBRATION ISLOATORS HAD A BUSHING DIAMETER TOO SMALL TO ALLOW INSERTING THE NEW ENGINE MOUNT BOLTS. EVEN THE	 OLD ENGINE MOUNT BOLTS COULD NOT BE INSTERED THROUGH THE NEW VIBRATION ISOLATORS. THEDIAMETER OF THE FORWARD ISOLATOR C	OMPARED TO THE REAR ISOLATOR WAS .010 SMALLER. THE ENGINE MOUNT BOLTS FIT THROUGH THE REAR ISOLATORS. SUSPECTING THE NEW	 ENGINE MOUNTS WERE SUBSTANDARD, THEY WERE RETURNED TO STORES WITH UNSERVICEABLE TAGS. NEW ENGINE MOUNTS WERE ORDERED & 	INSTALLED WITH NO DIFFICULTIES.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005011300033	20050113	00033	NM  	2005	1	13	CA040401001      	1	20040401	G	2760		HINGE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FLT SPOILER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION , AN ENGINEER NOTICED THE INBOARD HINGE OF THE RT OTBD FLT SPOILER HAS BEEN BROKEN. THE SPOILER 	PANEL WAS REPLACED .TOTAL TIME ON A/C IS 41510.48 AND TOTAL CYCLES ARE 52560 THE PANEL S/N IS  F1-038 PLEASE VIEW ATTACH	ED FILES FOR PART CONDITION REFER TO ILLUSTRATED PARTS CATALOG FOR DHC-8-100SECTION 57-53-00 FIG 10 FOR ILLUSTRATED DRAW	ING			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005011300034	20050113	00034	SO  	2005	1	13	CA040401002      	1	20040330	G	3220	NAS464P427	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	NLG DRAG LINK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REGULAR MAINTENANCE, IT WAS DECIDED TO INSPECT THE CONDITION OF THE CENTRE BOLT OF THE DRAG LINK ASSY AS A 	RESULT OF THE FAILURE OF THIS BOLT ON THE OTHER COMPANY OPERATED AIRCRAFT. THIS BOLT WAS FOUND IN PLACE, BUT WHEN THE NU	T WAS ROTATED IT WAS FOUND THAT THE BOLT WAS BROKEN IN TWO.				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920
2005011300035	20050113	00035	NE  	2005	1	13	CA040401003      	2	20040313	G	7320	230305204	CONTROLLER      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					2NDARY OVERSPEED	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			10119	10119				LFO5482AC			(CAN) ACFT WAS IN CRUISE WHEN CREW REPORTED THAT THE NR 3 ENGINE LOST POWER & SPOOLED DOWN BY ITSELF, SEVERAL ASSOCIATED	 MWS CAUTION LIGHTS ILLUMINATED. ACFT LANDED SAFELY AT ITS INTENDED DESTINATION. ACFT FERRIED HOME ON THREE ENGINES. MX 	FOUND THE NR 3 ENGINE SECONDARY OVERSPEED CONTROLLER AT FAULT. ACFT RUN WITH NO FURTHER OCCURRENCE OF DIFFICULTY. ACFT S	CHEDULED IN FOR ITS HEAVY CHECK & HONEYWELL THEN REQUESTED THAT WE RING OUT THE ENTIRE OVERSPEED ELECTRICAL SYSTEM ON TH	AT & ALL OTHER ENGINES CONFIRMING THE FUNCTION & SERVICEABILITY OF THE OVERSPEED SYS. NO FAULTS HAVE BEEN FOUND TO DATE.	 OVERSPEED CONTROLLER THAT INITIALLY CAUSED PROBLEM HAS BEEN SENT TO HONEYWELL FOR ANALYSIS.	2	H	7	4 	4F	4	F		A49EU   	E6NE
2005011300036	20050113	00036	CE  	2005	1	13	CA040401004      	1	20040329	G	5544	05310187	ATTACH BRACKET  			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14384								(CAN) RUDDER UPPER ATTACHED BRACKET WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	E274
2005011300037	20050113	00037	CE  	2005	1	13	CA040401005      	1	20040329	G	5510	07321014	REINFORCEMENT   			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REPAIRED HORIZONTAL STABILIZER.  AFT ATTACHMENT POINT REINFORCEMENT BRACKET PN 07321014 REPLACED WITH NEW.  ADJACE	NT RIVETS REPLACED.  TAIL REASSEMBLED.  INDEPENDENT CONTROL CHECK CARRIED OUT.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2004062100121	20040621	00121	EU  	2004	6	21	CA040401006      	1	20040326	G	2742	1291110002	ACTUATOR        	PILATS      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITCH TRIM	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						218					(CAN) AUTO-PILOT TEST FAILED.  ALTERNATE TRIM WAS SELECTED AND TESTED AND FOUND TO BE INTERMITTENT.  PITCH TRIM ACTUATOR	 WAS REPLACED. NO FURTHER ACTION REQUIRED. PITCHTRIM FAILED TO MAKE OVERHAUL LIFE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004062100138	20040621	00138	EU  	2004	6	21	CA040401007      	1	20040329	G	6410	355A12005004	BLADE           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						8296					(CAN) DURING DAILY INSPECTION AND DAILY COMPLIANCE WITH AD 2001-640-089(A),  A CHORDWISE CRACK WAS DETECTED APPROXIMATEL	Y 3 INCHES IB OF THE BLADE-TIP.					1	G	7	1 	3U	3	U	 	H9EU    	E00054EN
2004062100139	20040621	00139	NM  	2004	6	21	CA040401008      	1	20040401	G	3246	LM522546	BEARING         	BENDIX      		BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					WHEEL	CONTAMINATED    	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) WHILE LANDING THE FLIGHT CREW NOTICED A SHIMMY IN THE LANDING GEAR.  BELIEVING THAT THEY HAD BLOWN A TIRE, THEY ST	OPPED ON A TAXIWAY AND CONTACTED MAINTENANCE. MAINTENANCE DROVE TO THE AIRCRAFT AND INSPECTED THE LANDING GEAR. FINDING 	NO OBVIOUS FAULTS, MAINTENANCE HAD THE CREW TAXI THE AIRCRAFT TO THE RAMP. AFTER A THOROUGH INSPECTION OF THE LANDING GE	AR, BRAKES AND TORQUE LINKS THE NR 1 AND NR 4 MAIN WHEEL BEARINGS WERE FOUND WITH WATER CONTAMINATION. BOTH WHEEL ASSEMB	LIES WERE REPLACED.  NR 2 AND NR 3 MAIN WHEEL ASSEMBLIES WERE INSPECTED AND FOUND TO BE SERVICEABLE. AIRCRAFT WAS DECLAR	ED SERVICEABLE AND NO OTHER FAULTS WERE FOUND.  (ALSO: US NR 2004042300081)	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004062100140	20040621	00140	EA  	2004	6	21	CA040401009      	2	20040329	G	8530		CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NR 2	CONTAMINATED    	W				A				UNSCHED LANDING         				C			F.O.D.                    			CL	CLIMB          	1			CA											(CAN) SMALL PIECE OF RUBBER FOUND FLOATING IN AIR SIDE OF NR 2 CYLINDER INJECTOR. THE PIECE APPEARED TO BE VERY DRY AND 	HARD O-RING MATERIAL, MOST LIKELY FROM THE BANJO FITTING SEALS.  NO OTHER FAULTS FOUND ON OTHER BANJO FITTINGS.  REMOVAL	 OF CONTAMINATION AND NEW SPARK PLUGS FOR THIS CYLINDER RETURNED THE AIRCRAFT TO NORMAL OPERATION.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004062100141	20040621	00141	EA  	2004	6	21	CA040402001      	1	20040402	G	5210	601R31974112	BRACKET         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRSTAIR DOOR FREE FELL TO THE GROUND DUE TO THE FAILURE OF BOTH FWD/AFT (BOTH) SWIEL BRACKETS THAT HOLD THE CABLE	S TO THE FUSELAGE. IN THIS CASE THE DOOR WAS OPENED FROM INSIDE THE A/C AND NO HARM OR DAMAGE WAS DONE TO PERSONNEL OR E	QUIPMENT , BUT THERE EXIST A HIGH POSSIBILITY OF PERSONAL INJURY IF THE DOOR WAS TO BE OPENED FROM OUTSIDE. TOTAL DOOR C	YCLES ARE UNKNOWN .			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004062100142	20040621	00142	CE  	2004	6	21	CA040402002      	1	20040401	G	2133	D26D6412	OUTFLOW VALVE   			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					CABIN PRESSURE	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			W	J		INADEQUATE Q C            	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AIRCRAFT AT A CRUISE ALTITUDE CABIN DEPRESSURIZED. O2 SYSTEM ACTIVATED AUTOMATICLY.  EMERGENCY DESCENT DECLARED.						2	L	7	2 	4F	4	F	 	A10CE   	E6WE
2004062100143	20040621	00143	EU  	2004	6	21	CA040402003      	1	20040325	G	5280	25N2612	DOOR            			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					MLG	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON VISUAL INSPECTION AND NDT INSPECTION A CRACK OF 1 INCH WAS FOUND IN THE LT MLG OB DOOR SKIN AREA. IT WAS SUSPEC	TED THAT AT SOME TIME THE DOOR WAS RIGGED IMPROPERLY, DRAG LINK ADJUSTED TOO SHORT AND STRESSES THE AREA.					2	L	7	2 	4F	4	F	RT	A16NM   	E1NM
2004070900006	20040709	00006	NE  	2004	7	9	CA040402004      	2	20040325	G	7230	3020159	RETAINING RING  	PWA         							PWA   	PT6   	PT6A114A    	52043	NE  					HOT SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A0012M8Y					(CAN) THE HOT SECTION WAS GIVEN AN UNSCHEDULED HOT SECTION INSPECTION DUE TO PERFORMANCE SHIFT.  A FEW CT SHROUD SEGMENT	S HAD SHIFTED SLIGHTLY AND WERE RUBBED.  THE RETAINING RING HAD COME OUT OF HTE 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 COLLAPSE OF THE RETAINING RING. THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS S	UCH AS THE -114A ENGINE MODEL TO ALLOW THE MORE ROBUST RETAINING RING TO BE USED.							3	T			E4EA
2004062100146	20040621	00146	NE  	2004	6	21	CA040402005      	2	20040325	G	7250	3020159	RETAINING RING  								PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HOT SECTION WAS GIVEN A SCHEDULED HOT SECTION INSPECTION.  A FEW CT SHROUD SEGMENTS HAD SHIFTED SLIGHTLY AND W	ERE RUBBED.  THE RETAINING RING HAD NO END GAP AND WAS STARTING TO COME OUT OF THE GROOVE.  THIS PROBLEM HAS BEEN DOCUME	NTED ON OTHER ENGINES.  PWA 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 MOD	ELS SUCH AS THE 114A ENGINE MODEL TO ALLOW THE MORE ROBUST RETAINING RING TO BE USED.							3	T			E4EA
2004062100154	20040621	00154	NM  	2004	6	21	CA040402006      	1	20040401	G	1497		WIRE HARNESS    			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AC PACK BAY	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				S	B		AFFECT SYSTEMS            	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START UP, IT WAS OBSERVED THAT AC PACK WATER SEPARATOR CB POPPED FOLLOWED BY A PACK TRIP.  A BURNING ODRO W	AS SENSED.  ENGINES WERE SHUTDOWN.  MAINTENANCE BEGAN INSPECTION AND COCKPIT LIGHTING BEGAN TO FLICKER.  COCKPIT WAS FIL	LING WITH SMOKE.  NR 10 AND NR 11 MAIN DECK CARGO SMOKE DETECTOR LIGHTS ILLUMINATED.  APU WAS SHUT DOWN AND BATTERY POWE	R TURNED OFF. TROUBLESHOOTING WAS CARRIED OUT AND A WIRE BUNDLE IN THE PACK AREA WAS INSPECTED.  A WIRE WAS FOUND TO BE 	HOT CAUSING THE UNSERVICEABILITY.  ONCE ALL THE PAPERWORK HAS BEEN FORWARDED, WILL UPDATE THIS SDR.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004062100155	20040621	00155	NE  	2004	6	21	CA040402007      	2	20040401	G	8550	215P6311018	LINE            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE OIL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AN OIL LEAK WAS DISCOVERED BY MAINT IN THE OB SIDE OF NACELLE. AFTER CLEANING AREA, OIL WAS OBSERVED RUNNING DOWN 	OIL RETURN LINE (COOLER TO TANK)FROM AN AREA WHERE A WIRE BUNDLE WAS LAYING AGAINST LINE. A WIRE HAD BEEN CHAFED THROUGH	 AND BARE WIRE WAS ARCING AGAINST OIL TUBE CAUSING A PIN HOLE IN TUBE. WIRE WAS POWER WIRE FOR THE HYD FIREWALL SHUT OFF	 VALVE. ARCING ALSO DAMAGED WIRE FOR OIL SHUT OFF VALVE. REMAINING AC IN FLEET WERE INSPECTED, ONE ADDITIONAL AIRCRAFT H	AD WIRE BUNDLE UP AGAINST THE OIL RETURN TUBE. DEFECT WAS RECTIFIED. DAMAGED TUBE WILL BE REPLACED WITH A SERVICEABLE UN	IT AND AC WILL BE RETURNED TO SERVICE.	2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2004062100156	20040621	00156	EA  	2004	6	21	CA040403001      	1	20040331	G	2910	AE2464218E01	HYDRAULIC LINE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT WHEEL WELL	PUNCTURED       	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI OFF THE RUNWAY HYD 2 LOW PRESSURE CAUTION POSTED ON EICAS.  PRESSURE SHOWED BETWEEN 100-300 PSI.  MAINTENA	NCE FOUND THE RT IB GROUND SPOILER EXTENSION FLEX LINE P/N AE2464218E0164 IN THE GEAR WELL RUPTURED.  THE LINE WAS FOUND	 TO BE CHAFFING ON THE WING BOX STRUCTURE UNDER THE COVER ASSEMBLY P/N 600-31594-15.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004070900085	20040709	00085	NE  	2004	7	9	CA040403002      	2	20040328	G	7200	412T03G02	ENGINE          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RIGHT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON MARCH 28TH, PILOT REPORTS (AFTER A 5-6 MIN TAXI, THRUST LEVERS ADVANCED FOR T/O BUT PRIOR TO BRAKES RELEASE, RT	 ENGINE FLAMEOUT MSG.  ITT ON RH ENGINE 1012 DEGREES C.  ENGINE STARTED TO RELIGHT BY ITSELFT (FADEC RELIGHT) BUT CREW S	HUT OFF THE FUEL PRIOR TO FADEC RELIGHT.WORK PERFORMED PRIOR TO RELEASE TO SERVICE INCLUDE:   EXTERNAL INSPECTION OF ENG	INE, VG,  BORESCOPE HPT, COMBUSTION SECTION,  POWER ASSURANCE RUNS, FADEC, MDC AND FDR DOWNLOADS SENT TO ASA ENGINEERING	, ON MAR 31ST, PROBLEM RE-OCCURED.  THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004070900086	20040709	00086	EU  	2004	7	9	CA040405001      	1	20040328	G	2797		WIRE            			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					FLAP COMPUTER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) FLAP JAM OCCURRED AFTER TAKE OFF. AIRCRAFT RETURNED TO THE STATION FOR RECTIFICATION. FLAP SFCC COMPUTER WAS RESET	 BY MAINTENANCE. FLAP SYSTEM WAS INSPECTED AND OPERATED SEVERAL TIMES WITH NO FAULT FOUND. AIRCRAFT WAS DISPATCH WITH NO	 FURTHER PROBLEM. AIRCRAFT WAS ROUTED TO THE MAIN BASE FOR FURTHER INVESTIGATION. DURING INSPECTION, FOUND WIRING DAMAGE	D AT REAR SPAR CONNECTOR 37 NVA.  WIRING REPAIRED AND COMPLETE WIRING INSPECTION WAS CARRIED OUT. EO RAISED TO CARRY OUT	 A FLEET INSPECTION ON REAR SPAR WIRING AND MAINTENANCE PROGRAM PERIODIC INSPECTION WILL BE IMPLEMENTED BASE ON RESULT O	F THE INSPECTION EO.	2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2005011300038	20050113	00038	WP  	2005	1	13	CA040405002      	2	20040405	G	7250	31080661	NUT             								GARRTT	TPE331	TPE33110UA  	01514	WP  					TURBINE SHAFT	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON ATTEMPTING TO INSTALL THE REAR TURBINE SHAFT NUT ONTO TURBINE SHAFT IT WAS FOUND THAT THE NUT WOULD ONLY THRE	AD HALFWAY DOWN & THEN THREADS WOULD START TO PILE UP AND BIND. WITH THE TURBINESHAFT IN AN UNSTRETCHED CONDITION, NUT W	OULD WORK FINE & WOULD THREAD ON FREELY BY FINGERS. ONCE THE SHAFT IS STRETCHED UPON INSTALLATION, NUT WOULD NOT THREAD 	ON COMPLETL Y. TO ELIMINATE THE POSSIBILITY OF THE SHAFT BEING A PROBLEM, A DIFFERENT BATCH OF NUTS WERE CHECKED WITH NO	 PROBLEMS BEING INSTALLED ON THE STRETCHED SHAFT. 20 NUTS HAVE BEEN REMOVED FROM COMPANY STORES DUE TO THE FACT THEY ARE	 FROM THE SA ME HONEYWELL LOT NUMBER AS THE DEFECTIVE NUTS. THE LOT NR OF THE DEFECTIVE NUTS IS 0311024140.						4	T			E4WE
2004070900088	20040709	00088	EU  	2004	7	9	CA040405004      	1	20040316	G	2821		O-RING          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					CONNECTOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FUEL WAS OBSERVED LEAKING FROM THE CONNECTOR ON TOP OF THE FUEL FILTER ASSEMBLY. REMOVAL OF THE CONNECTOR PLUG REV	EALED FUEL CONTAMINATION INSIDE THE PLUG. THE  O-RING LOCATED INSIDE THE CONNECTOR HOUSING WAS DAMAGED CAUSING LEAKAGE.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE
2004070900098	20040709	00098	EU  	2004	7	9	CA040405005      	1	20040330	G	2550	145202	RELEASE CABLE   	BREEZE      		BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					CARGO HOOK ASSY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						181					(CAN) WHILE SLINGING OPERATIONS WERE BEING CONDUCTED, THE LOAD WAS INADVERTENTLY RELEASED DUE TO FAILURE OF THE RELEASE 	CABLE ASSEMBLY SWAGING AT THE LOWER END.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE
2004070900101	20040709	00101	EA  	2004	7	9	CA040405006      	2	20040330	G	7510	9091010017	HOSE            			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 PHASE 3 INSPECTION THE RT ENGINE IB INLET ANTI-ICE TUBE WAS FOUND CRACKED. UNIT REPLACED WITH NEW.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004070900102	20040709	00102	CE  	2004	7	9	CA040405007      	1	20040330	G	7110	109910029117	COWLING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING PHASE 3 INSPECTION THE LT ENGINE LOWER AFT COWL WAS FOUND CRACKED A LONG A SEAM WELD. UNIT WAS REPAIRED IAW	 COMPANY PROCEDURE ASSY 681-71-10-0093.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2005011300039	20050113	00039	NE  	2005	1	13	CA040405008      	2	20040403	G	8500		ENGINE          			DOUG  	DC4   	C54A        	3021512	WP  	PWA   	R2000 	R20007M2    	52023	NE  					NR 3	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			CR	CRUISE         	1			CA						P103067					(CAN) DURING CRUISE, THE CREW NOTICED THAT THE NR 3 ENGING WAS STARTING TO OVERSPEED. THE ENGINE WAS SHUTDOWN, PROPELLER	 FEATHERED, AND THE FLT RESUMED WITHOUTANY FURTHER ACTION.					2	L	7	4 	4R	4	R		A762    	5E5
2004100500017	20041005	00017	EU  	2004	10	5	CA040405AAA      	1	20040402	G	3610	F212529300000	DUCT            			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					AIR CON	RUPTURED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED A RUMBLE NOISE HEARD FROM COCKPIT AND CABIN CONTINUOUSLY WITH BLEED AIR / AIR CONDITIONING. U	NABLE TO ISOLATE WITH AIR CONDITIONING PACKS. DURING INVESTIGATION, MAINTENANCE FOUND THE GROUND AIR CONDITIONING DUCT (	 COMPOSITE ) RUPTURED AT THE AIR CONDITIONING PLENUM. DUCTING ASSEMBLY REPLACED.AT THIS TIME WE RE UNABLE TO DETERMINE I	F DUCT WAS DAMAGE DURING PREVIOUS INSTALLATIONOR COMPOSITE MATERIAL FAILURE. DUCTING WILL BE SENT TO AIRBUS FOR EVALUATI	ON.		1	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2004070900103	20040709	00103	NE  	2004	7	9	CA040406001      	2	20040402	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	VIBRATION       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	M	J	VIBRATION/BUFFET          	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			CA								807418			(CAN) MFG HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT.  LT ENG OIL PRESS WARNING MESSAGE POSTED WITH LT EN	GINE OIL QUANTITY DECREASING. LT ENGINE VIBS INCREASED UP TO 3.5 MILS.  ENGINE SHUT DOWN IAW QRH. FLIGHT DIVERTED. CARBO	N SEAL NR 7 (P/N AS1895-7-150) REPLACED. CHIP DETECTOR VERIFIED OK. COMPRESSOR AND TURBINE BOROSCOPED - NO FINDING. ENGI	NE RUN PERFORMED, FOR 20 SECONDS, NORMAL, THEN ENGINE VIB FROM 0.4 TO 2.8 MILS.  OIL LOST THROUGHT JET PIPE. ENGINE REPL	ACED.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004070900104	20040709	00104	EA  	2004	7	9	CA040406003      	2	20040403	G	7314		SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	EDP	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA								807418			(CAN) DURING A ROUTINE ENGINE INSPECTION THE NR 1 ENGINE COWL WAS REMOVED TO FACILITATE THE INSPECTION ON THE ENGINE.   	WHEN THE COWL WAS REMOVED IT WAS NOTED THERE WAS A LARGE BLUE STAIN ON THE BOTTOM OF THE COWL, JUST BELOW THE ENGINE DRI	VEN FUEL PUMP. THIS FUEL PUMP IS OF THE NEW STYLE INSTALLED TO ELIMINATE THE REPETITIVE INSPECTION ON AD 2003-14-03.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004071200175	20040712	00175	EU  	2004	7	12	CA040406004      	1	20040406	G	3020	9787315301	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED A CLACKING NOISE IN FLIGHT COMING FROM THE INSTRUMENT PANEL. DURING TROUBLESHOOTING THE INTERNAL BY	 PASS DOOR WAS FOUND INOP. IN THE CLOSED POSITION. FURTHER INVESTIGATION REVEALED AN INTERNAL FAILURE AS THE STOP BUTTON	 THAT ACTUATES THE INTERNAL  LIMIT MICRO SWITCH HAD FALLEN OUT OF PLACE. THUS ALLOWING THE ACTUATOR TO GO BEYOND THE ALL	OWABLE LIMITS. THE ACTUATOR HAD COMPLETELY UNSCREWED ITSELF FROM THE LINEAR PORTION AND UNDER LOAD WOULD HAVE CONTINUED 	TO OPERATE AND CAUSE A THUMPING SOUND UNTIL THE MOTOR FAILED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004071200183	20040712	00183	EU  	2004	7	12	CA040406005      	1	20040405	G	7820	L24266710000	BAFFLE          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MUFFLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DUE TO PREVIOUS DISCOVERIES OF BROKEN INTERNAL BAFFLES INSIDE THE NR 1 EXHAUST SILENCER ON OTHER AIRCRAFT IN OUR F	LEET, AN INTERNAL INSPECTION HAS BEEN CALLED UP EVERY 100 HOURS TO COINCIDE WITH A 100 HR INSPECTION. THIS PARTICULAR BA	FFLE WAS FOUND BROKEN DURING A WALK AROUND BY A STUDENT.I T WAS NOTICED THAT A PIECE OF METAL WAS HANGING OUT THE NR 2 E	XHAUST SILENCER EXIT. THERE HAS BEEN OTHER SDR'S SUBMITTED ON THIS SUBJECT.			1	L	7	1 	3O	3	O	0	A76EU   	1E10
2004071200184	20040712	00184	SO  	2004	7	12	CA040406006      	2	20040329	G	7314	5367001	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FUEL SYSTEM	INOPERATIVE     	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) AIRCRAFT HAD JUST BEEN RETURNED TO SERVICE AFTER A LONG PERIOD OF STORAGE (ABOUT18 MOTHS). THE AIRCRAFT FLEW 11.7 	AFTER RETURNING FROM STORAGE BEFORE THE FUEL PUMP FAILED.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004071200185	20040712	00185	NE  	2004	7	12	CA040407001      	2	20040406	G	7261		ENGINE          			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					LEFT	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LT ENGINE SHUTDOWN, OIL IND LOW, FOUND OIL IN TAIL PIPES.   REPORT TO FOLLOW.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2004071200186	20040712	00186	SW  	2004	7	12	CA040407008      	1	20040403	G	2435	303001383	BRUSHES         			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						5759					(CAN) ON INSPECTION OF THE START/GEN BRUSHES IT WAS DISCOVERED THAT THE REAR BRUSHES WERE SLIGHTLY SHORTER (MORE WORN) T	HAN THE FORWARD BRUSHES.  REPLACED BRUSHES AND INSPECTED AGAIN AFTER 100 HOURS.  FOUND THE AFT BRUSHES WITH A MUCH HIGHE	R DEGREE OF WEAR IN RELATION TO LAST INSPECTION ALSO ONE OF THE BRUSH WIRES HAD COME OFF THE BRUSH, CHANGED START/GEN.				1	G	7	1 	3U	3	U	NC	H2SW    	E1GL
2004071200187	20040712	00187	EU  	2004	7	12	CA040407009      	1	20040407	G	2910	105456611	HOUSING         			BOLKMS	105   	BO105LSA3   	5626020	EU  										ACTUATOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						31007					(CAN) DURING TESTING THE ACTUATOR SHOWED HIGH INTERNAL LEAKAGE.  AFTER INVESTIGATION IT WAS DISCOVERED THAT THE HOUSING 	WAS CRACKED INTERNALLY.  THE CRACK IS IN THE SERVO VALVE AXIS OF THE HOUSING AND APPEARS TO ORIGINATE FROM A DRILLED PAS	SAGE.  THIS ASSEMBLY RECEIVED FROM AN AIRCRAFT IN THE USA.				1	G	7	2 	3U			 	H3AU
2004120700164	20041207	00164	SW  	2004	12	7	CA040407010      	1	20040407	G	3110	6390016901	PIVOT ASSY      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					INDICATOR MOUNT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ADJUSTABLE PIVOT HAD MOST OF THE ADJUSTMENT SLOT BROKEN AWAY.  PREVIOUS REPAIRER HAD 'FIXED' THE PROBLEM BY FLOODI	NG THE AREA WITH EPOXY TO STOP THE PIVOT FROM ROTATING. THE RETAINING SCREW HAD INSUFFICIENT MATERIAL TO HOLD THE PIVOT 	AS DESIGNED.				1	G	7	1 	4U	4	U		H4SW    	E22EA
2005022300125	20050223	00125		2005	2	23	CA040407011      	4	20040407	G	3420		TAPE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					GYROS	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ADHESIVE BACKED LEAD TAPE HAD BEEN USED TO BALANCE THE PITCH ERECTION VANES.  IAW MANUFACTURER'S SERVICE ADVISORY 	NR 75, DATED JANUARY 25, 1985, LEAD TAPE SHOULD NOT BE USED TO BALANCE AIM GYROS AS IT CAN FALL OFF AND CAUSE THE GYRO T	O BECOME INOPERATIVE.				1	G	7	1 	4U	4	U		H4SW    	E22EA
2004071900016	20040719	00016	NE  	2004	7	19	CA040407013      	3	20040221	G	6111	C792	BEARING         	HARTZL      	HCE4A3I     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROP BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						KX44					(CAN) PROPELLER WAS REMOVED FROM THE AIRCRAFT TO REPAIR DAMAGE TO THE ERROSION SHIELD INSTALLED ON NR 1 BLADE. UPON SPLI	TTING THE HUB 2 OB BLADE BEARINGS WERE FOUND TO BE CRACKED.  ALL 4 BLADE BEARINGS HAVE BEEN REPLACED BY NEW D7745 BEARIN	GS IAW MM NR 143A AND S/B 61-258 .				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004071900017	20040719	00017	NE  	2004	7	19	CA040407014      	3	20040401	G	6111	C0792	THRUST BEARING  	HARTZL      	HCE4A3I     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						HJ799					(CAN) PROPELLER WAS REMOVED FROM AIRCRAFT DUE TO EXCESSIVE GREASE LEAKAGE AND BLADE END PLAY.  UPON SPLITTING THE HUB IT	 WAS FOUND THAT 2 BLADE THRUST BEARINGS HAD CRACKED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004071900018	20040719	00018	NE  	2004	7	19	CA040408001      	2	20040326	G	7320		EEC             			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					RT ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								970146			(CAN) OPERATOR REPORTED A RECENT IN-FLIGHT OCCURRENCE WHERE, AFTER APPROXIMATELY 2 HOURS INTO THE FLIGHT, AT 41,000 FT, 	THE RT ENGINE SHUTDOWN AND AN AMBER FADEC FAIL.					2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN
2004071900019	20040719	00019	EA  	2004	7	19	CA040408002      	1	20040403	G	7830	22850741115	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					THRUST REVERSER	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) THRUST REVERSER UNLOCK LIGHT AND REVERSER ICON ON NR 1 GAUGE CAME ON IN FLIGHT AT FLIGHT LEVEL 210QRH CARRIED OUT,	 LIGHT REMAIN ON FOR THE REST OF THE FLIGHT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071900020	20040719	00020	NE  	2004	7	19	CA040408004      	2	20040407	G	7532		BLEED VALVE     			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				B				EMER. DESCENT           				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FLIGHT LEVEL 390 NO ENGINE BLEED FAULT , BLEED SHUT OFF, 10 MINUTES LATER NR 2 ENGINE BLEED FAULT	.  LOSS OF PRESSURIZATION EMERGENCY DESCENT TO 8000 FT, ABLE TO RESET  BLEEDS  AND CLIMB BACK TO FLIGHT LEVEL 160 NO FAU	LT FOUND, FDR SENT FOR READ OUT.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004071900021	20040719	00021	GL  	2004	7	19	CA040408005      	1	20040402	G	5714	5867001	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENG FUEL	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) INCONSISTENCIES IN FUEL PRESSURE, FUEL PRESSURE WAS CHECKED AND FOUND THAT THE LOW SIDE OF THE ELECTRIC FUEL PUMP 	WAS NEAR NIL. HIGH SIDE WAS 5.5. THE FUEL PUMP FAILURE IS BELIEVED TO BE CAUSED BY THE AIRCRAFT BEING OUT OF SERVICE FOR	 LONG PERIOD OF TIME 15-16 MONTHS.  FUEL TANK WAS HALF FULL DURING THIS TIME.  THE FUEL SYSTEM PRESSURE HAD BEEN CHECKED	 ON ENGINE INSTALLATION AND WAS FOUND TO BE WELL WITHIN LIMITS.			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2004071900022	20040719	00022	SO  	2004	7	19	CA040408007      	1	20040408	G	3230	6716800	SPRING          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	NLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A LANDING GEAR INSPECTION THE NOSE LANDING GEAR INNER ASSIST SPRING WAS FOUND BROKEN AT THE UPPER HOOK.  TH	ERE WAS NO INDICATION OF ANY LANDING GEAR MALFUNCTION IN THE FLIGHT PREVIOUS TO THE INSPECTION.  THE LANDING GEAR INSPEC	TION WAS PART OF AN EVENT NR 2 INSPECTION ON THE AIRCRAFT.  A SIMILAR FAILURE OF THIS SPRING HAPPENED ON ANOTHER AC IN O	UR FLEET.  IT WAS NOTICED BY A PILOT WHEN THE GEAR WAS SELECTED DOWN THE NOSE TOOK APPROX  2 MINUTES TO EXTEND. (THERE W	AS AN SDR SUBMITTED ON THIS NR 20021121004 )THIS SPRING GETS A CLOSE LOOK EVERY 50 HOURS AT EACH EVENT ON THE AIRCRAFT.		1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004071900026	20040719	00026	SO  	2004	7	19	CA040408008      	2	20040404	G	7414		GEAR            	BENDIX      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C403   	GL  	DISTRIBUTER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						E5663					(CAN) DURING A RUN-UP FOR A 50 HOUR INSPECTION THE AME NOTED THAT THE LT MAG WAS TOTALLY DEAD.  UPON INSPECTION IT SHOWE	D THAT 2 TEETH ON THE DRIVE GEAR FOR THE DISTRIBUTOR WERE TOTALLY MISSING.  THESE TEETH BEING MISSING WOULD NOT ALLOW TH	E DISTRIBUTOR ON THE MAG TO FUNCTION CORRECTLY.  THE OLD MAGNETO HAD 47.4 SINCE 500 HOUR INSPECTION AND 93.9 SINCE OVERH	AUL. THE MAGNETO WAS REPLACED AND THE ENGINE WAS GROUND RUN AND LEAK CHECKED, ENGINE FOUND TO BE WORKING AS IT SHOULD WI	TH THE NEW MAG.		1	H	7	1 	3O	3	O	 	3A24    	E3SO	5	C	P47GL
2004071900045	20040719	00045	GL  	2004	7	19	CA040408009      	2	20040430	G	7210	6850209	GEARBOX         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENROUTE, THE A/C HAD A NR 2 RGB CHIP LIGHT INDICATION.  THE ENGINE WAS SHUT DOWN AND FLIGHT CONTINUED.  THE A/C WA	S 3 ENGINE FERRIED,  FOR RGB CHANGE OUT.  THE RGB WAS REPLACED AND THE A/C RETURNED TO SERVICE.					2	H	7	4 	4T	4	T	 	A1SO    	E282	6	C	P906
2004071900046	20040719	00046	NM  	2004	7	19	CA040408010      	1	20040407	G	2760		WARNING LIGHT   			BOEING	727   	7272H3      	138368N	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CONFIGURATION	FALSE ACTIVATION	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE CREW OBSERVED AN AURAL CONFIGURATION WARNING ON TAKE OFF WHEN THE GEAR WAS SELECTED UP AND FLAP 15.  THE A/C R	ETURNED TO BLOCKS WHERE IT WAS DETERMINED THAT THE SPEED BRAKE WARNING SWITCH WAS OUT OF ADJUSTMENT.  THE SWITCH WAS ADJ	USTED AND THE TOW CS CHECKED SERVICEABLE IAW MM31-26-25 AND THE A/C WAS RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004071900047	20040719	00047	GL  	2004	7	19	CA040408012      	1	20040401	G	2780	5910461	TORQUE TUBE     			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					RT SLAT	DISCONNECTED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE CREW SELECTED SLATS TO GO OUT AND GOT A FAIL MESSAGE ON EICAS. POST LANDING INSPECTION REVEALED TH	AT THE LT SLAT PARTIALLY DEPLOYED AND THE RT SLAT WAS STOWED.  MAINTENANCE CREW FOUND THE RT TORQUE TUBE DISCONNECTED FR	OM THE SLAT POWER DRIVE UNIT. THE COUPLING BOLT NOT ENGAGE THROUGH THE PDU SHAFT. NO DAMAGE WAS FOUND ON THE SYSTEM AND 	SURROUNDING STRUCTURE.  BOLT RE-INSTALL IAW MM AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN
2004071900048	20040719	00048	EA  	2004	7	19	CA040408013      	2	20040408	G	8550	L24276000600	TEE FITTING     			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					PICK UP TUBE	SEPARATED       	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ENGINE REMOVAL THE OIL DRAIN TEE FITTING WAS FOUND TO HAVE THE PICK UP TUBE LOOSE IN THE TEE FITTING.  T	HIS PROBLEM WAS PREVIOUSLY REPORTED IN AN SDR.  A MANDATORY SB WAS ISSUED FROM THE MANUFACTURER (MSBZ242L/42A) AND THE F	ITTINGS WERE REPAIRED AND TESTED IAW THE SB.  THIS FITTING WILL BE REPAIRED IAW THE SB AND THEN TESTED IAW THE SB. IF TH	IS FITTING HAD SEPARATED THE RESULT WOULD HAVE BEEN A RESTRICTION IN THE OIL SYSTEM WITH LOW OIL PRESSURE IN THE ENGINE.			1	L	7	1 	3O	3	O	0	A76EU   	1E10
2004071900049	20040719	00049	EU  	2004	7	19	CA040408014      	1	20040402	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) HYDRAULIC PUMP PULLEY BROKE DURING FLIGHT.  UNSCHEDULED LANDING CARRIED OUT WITHOUT INCIDENT.  BELT REPLACED, AIRC	ARFT RETURNED TO SERVICE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004071900050	20040719	00050	SW  	2004	7	19	CA040409001      	1	20040407	G	3230	915019000	TUBE            	MOONEY      		MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	MLG DOWNLOCK	BENT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) RT MAIN GEAR COLLAPSED ON LANDING ROLL OUT.  INITIAL FINDING MAIN GEAR ACTUATING TUBE INSIDE BELLY IS BENT.  IT IS	 UNKNOWN IF THIS TUBE WAS BENT BEFORE OR AS RESULT OF GEAR COLLAPSE.  FURTHER INFORMATION WILL FOLLOW AS MORE DETAIL INS	PECTION/DISASSEMBLY IS REQUIRED FOR ROOT CAUSE.				1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P920
2004071900051	20040719	00051	NM  	2004	7	19	CA040409002      	1	20040404	G	2751		SWITCH          			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT NR 5 KREUGER FLAP INTRANSIT LIGHT ILLUMINATED.  A/C RETURNED ANC. SWITCH REPLACED AND OVERWEIGHT LAND	ING INSPECTION C/W.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004071900052	20040719	00052	EA  	2004	7	19	CA040410001      	1	20040401	G	6300	234D33003	DRIVE ASSY      			BOEING	234   	234         	1385049	EA  	LYC   	AL5512	AL5512      	41581	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION IAW AD 2004-06-51 A CRACK WAS DETECTED IN THE UPPER EXTENSION 37 INCHES FROM THE TOP.  SHAFT WAS	 REMOVED FROM SERVICE AND RETURNED TO MFG FOR INSPECTION.  MFG IS CONDUCTING INSPECTIONS OF ALL IN-SERVICE SHAFTS AND SP	ARES TO ELIMINATE ANY SHAFT FROM THE SYSTEM THAT HAS ARC BURNS.				2	G	7	2 	4U	4	U	 	H9EA    	E4NE
2005022300126	20050223	00126	NM  	2005	2	23	CA040412001      	1	20040406	G	3411		PITOT LINE      	ROSEMOUNT   		BOEING	737   	737200      	1384453	NM  										PITOT TUBE ASSY	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						151720					(CAN) B737-200 PITOT TUBE ASSEMBLY FAILED BENCH CHECK WITH A PITOT LEAK IN EXCESS OF 200 KTS/MIN.  THE LEAK WAS DETERMIN	ED TO BE ORIGINATING WHERE THE PITOT TUBE AIRFRAME ATTACHMENT CONNECTS TO THE BASE OF THE PITOT TUBE ASSEMBLY.  THE COMP	ONENT WAS A USED PART ACQUIRED FROM A DISTRIBUTOR, QWEST AIR PARTS INC, IN MEMPHIS TN.  THE PITOT TUBE HAD BEEN BENCH CH	ECKED  SERVICEABLE BY CROSS-CHECK AVIATION, FAA REPAIR STATION XK8R253Y LOCATED IN RENO, NEVADA.			2	L	7	2 	4F				A16WE
2005022300127	20050223	00127	NM  	2005	2	23	CA040412002      	1	20040406	G	3411		PITOT LINE      	ROSEMOUNT   		BOEING	737   	737200      	1384453	NM  										PITOT TUBE ASSY	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						156586					(CAN) B737-200 PITOT TUBE ASSEMBLY FAILED BENCH CHECK WITH A PITOT LEAK IN EXCESS OF 350 KTS/MIN.  THE LEAK WAS DETERMIN	ED TO BE ORIGINATING WHERE THE PITOT TUBE AIRFRAME ATTACHMENT CONNECTS TO THE BASE OF THE PITOT TUBE ASSEMBLY.  THE COMP	ONENT WAS A USED PART ACQUIRED FROM A DISTRIBUTOR, QWEST AIR PARTS INC, IN MEMPHIS TN.  THE PITOT TUBE HAD BEEN BENCH CH	ECKED  SERVICEABLE BY CROSS-CHECK AVIATION, FAA REPAIR STATION NR XK8R253Y LOCATED IN RENO, NEVADA.			2	L	7	2 	4F				A16WE
2005022300128	20050223	00128	NM  	2005	2	23	CA040412003      	1	20040408	G	3411		PITOT LINE      	ROSEMOUNT   		BOEING	737   	737200      	1384453	NM  										PITOT TUBE ASSY	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						165698					(CAN) B737-200 PITOT TUBE ASSEMBLY FAILED BENCH CHECK WITH A PITOT LEAK IN EXCESS OF 350 KTS/MIN.  THE LEAK WAS DETERMIN	ED TO BE ORIGINATING WHERE THE PITOT TUBE AIRFRAME ATTACHMENT CONNECTS TO THE BASE OF THE PITOT TUBE ASSEMBLY.  THE COMP	ONENT WAS A USED PART ACQUIRED FROM A DISTRIBUTOR, QWEST AIR PARTS INC, IN MEMPHIS TN.  THE PITOT TUBE HAD BEEN BENCH CH	ECKED  SERVICEABLE BY CROSS-CHECK AVIATION, FAA REPAIR STATION NR XK8R253Y LOCATED IN RENO, NEVADA.			2	L	7	2 	4F				A16WE
2004072100071	20040721	00071	CE  	2004	7	21	CA040412004      	1	20040221	G	3010	571531025	TUBE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					BLEED AIR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			10921	10921							(CAN) DURING FLIGHT THE CREW NOTICE AN INTERMITENT WING O/H WARNING. MAINTENANCE WAS CONTACTED AND THE AIRCRAFT INSPECTE	D. INSPECTION REVEALED A CRACK IN BLEED AIR TUBE PN 5715310-25. THE TUBE WAS REPLACE. THERE WAS NO RESULTING DAMAGE FROM	 THE BLEED AIR LEAK.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
2005022300129	20050223	00129	NM  	2005	2	23	CA040412005      	1	20040408	G	3411		PITOT LINE      	ROSEMOUNT   		BOEING	737   	737200      	1384453	NM  										PITOT TUBE ASSY	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						147844					(CAN) B737-200 PITOT TUBE ASSEMBLY FAILED BENCH CHECK WITH A PITOT LEAK IN EXCESS OF 10 KTS/MIN.  THE LEAK WAS DETERMINE	D TO BE ORIGINATING WHERE THE PITOT TUBE AIRFRAME ATTACHMENT CONNECTS TO THE BASE OF THE PITOT TUBE ASSEMBLY.  THE COMPO	NENT WAS A USED PART ACQUIRED FROM A DISTRIBUTOR, QWEST AIR PARTS INC, IN MEMPHIS TN. THE PITOT TUBE HAD BEEN BENCH CHEC	KED SERVICEABLE BY CROSS-CHECK AVIATION, FAA REPAIR STATION # XK8R253Y LOCATED IN RENO, NEVADA.REF SDRS20040412001, 2004	041202, AND 2004041203.		2	L	7	2 	4F				A16WE
2005022300130	20050223	00130	NE  	2005	2	23	CA040412006      	2	20040412	G	7200		ENGINE          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NR 1	BIRD INGESTION  	W				C				ABORTED TAKEOFF         				C			F.O.D.                    			TO	TAKEOFF        	1			CA											(CAN) FAULT: HIT 2 GEESE ON T/O HIGH SPEED REJECTED RETURNED TO GATE.  FOUND EVIDENCE OF BIRD INGESTION AT NR 1 ENG.   S	EVERAL DAMAGED BLADES, A/C ROUTED TO HANGAR FOR ENGINE BOROSCOPE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004080500081	20040805	00081	NM  	2004	8	5	CA040412007      	1	20040412	G	3250		STEERING SYS    			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					NLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ON APPROACH AFTER PUTTING THE LANDING GEAR DOWN, THERE WAS AN ECAM MSG REF. TO NOSE WHEEL STEERING FAULT.  AC CARR	IED OUT A MISSED APPROACH AND WENT THROUGH THE QRH. TOWER CALLED OUT THE EMERGENCY EQUIPMENT FOR THE LANDING. AC LANDED 	ON 24L, AFTER LANDING, THE AC  WAS ABLE TO TAXI TO THE RAMP. (AC REMOVED FROM SERVICE FOR N/W STEERING INVEST.)				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004080500082	20040805	00082	NE  	2004	8	5	CA040412008      	2	20040410	G	8550		GASKET          			DOUG  	DC4   	C54         	3021506	WP  	PWA   	R2000 	R20007M2    	52023	NE  					ENGINE OIL LINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE CREW NOTICED AN OIL LEAK ON THE NR 2 ENGINE. THE ENGINE WAS SHUT DOWN AND PROPELLER FEATHERED. O	N INSPECTION IT WAS NOTICED THAT THE OIL PRESSURE LINE GASKET HAD BLOWN OUT. THE GASKET WAS REPLACED AND THE AIRCRAFT RE	TURNED TO SERVICE.				2	L	7	4 	4R	4	R	 	A762    	5E5
2004080500083	20040805	00083		2004	8	5	CA040412009      	4	20040407	G	6122	R20007M2	GOVERNOR        			DOUG  	DC4   	C54ADC      	3021510	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	PROPELLER	OUT OF RIG      	W				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF THE NR 3 ENGINE ENCOUNTERED AN OVERSPEED. THE AIRCRAFT RETURNED TO THE HANGER.  IT WAS FOUND THAT 	THE PROP GOVENOR WAS OUT OF RIG.  IT WAS RE-RIGGED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	4 	4R	4	R	 	A762    	5E5	6	C	P603
2004080500084	20040805	00084		2004	8	5	CA040412010      	4	20040320	G	2310	14379	ANTENNA         			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					TENSIONER	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) PILOTS REPORTED VIBRATION IN FLOORBOARDS 240 TO 260 KIAS AT ARRIVAL. DURING INSPECTION NOTICED THE HF ANTENNA BROK	EN OFF AT THE TENSIONER UNIT ON FIN, THE COPPER WIRE BROKEN. THIS OCCURRED AT 2638.1 HRES AND 2308 CYCLES. THIS WIRE ANT	ENNA WAS REPLACED DEC 11/ 01 FOR EXACTILY THE SAME PROBLEM AT 1055.2 HRES AND 946 CYCLES. THIS CAUSED ONLY MINOR SCRATCH	ES ON THE TAILCONE. OUR MAIN CONCERN IS THE POSSIBILY OF THIS WIRE INTERFERING WITH THE FLIGHT CONTROLS.  WE ARE EVALUAT	ING THE NEED TO REPLACE THE WIRE ANTENNA ON A REGULAR BASIS (EVERY 500 HOURS) TO PREVENT RE-OCCURRENCE.		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004080500093	20040805	00093	CE  	2004	8	5	CA040412011      	1	20040409	G	2750	1013800001	SHAFT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	TE FLAP CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18075								(CAN) DURING THE REPLACEMENT OF A FLAP ACTUATOR AND DURING TESTING, THE NR 4 FLAP PANEL CEASED TO MOVE.  IT WAS FOUND TH	AT THE FLAP FLEXIBLE SHAFT HAD INTERNALLY CORRODED AND FAILED. THIS ISSUE WAS FOUND ONCE PRIOR UNDER SDR NR 20030825014 	BUT WITHOUT THE EVIDENCE OF CLAMP INTERFERENCE.  WATER HAS ONCE AGAIN FOUND ITS WAY INAND STAYED IN THE LOW POINT OF THE	 CABLE.  THE CABLE WAS REPLACED AND THE SYSTEM CHECKED OK.  MFG HAS ONCE AGAIN BEEN NOTIFIED OF THIS CONDITION.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004080500094	20040805	00094	CE  	2004	8	5	CA040412012      	1	20040409	G	3246	114800893	BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					MLG WHEEL	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF, THE CREW WAS NOTIFIED THAT NR 3 WHEEL HAD SEPARATED FROM THE AIRCRAFT. THE BEARING HAD FAILED WHIC	H ALLOWED THE WHEEL ASSY TO PASS OVER THE RETENTION NUT AND SEPARATE.  DUE TO PAST ISSUES WITH BEARING FAILURES, A GREAS	E ANALYSIS HAS BEEN CONDUCTED SINCE MARCH 19, 2004 DUE TO ON GOING ISSUES WITH AEROSHELL 22 AND 5 WHEEL BEARING GREASE. 	OUR TEST INDICATED THAT A SWITCH TO MOBIL SHC100 IS IN ORDER AND THE FLEET WILL BE SWITCHED OVER EXPEDIOUSLY.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
2004080500095	20040805	00095	NM  	2004	8	5	CA040412013      	1	20040409	G	3246	26010452	WHEEL           			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING AIRCRAFT LOW SPEED TAXI TO RUNWAY, THE INBOARD WHEEL HALF OF THE RT NOSEWHEEL ASSEMBLY SEVERED AND TIRE DEF	LATED.  FUSELAGE AND NLG AREA INSPECTED FOR DAMAGE.  NO FAULTS FOUND.  BOTH NOSE LANDING GEAR WHEEL ASSEMBLIES REPLACED 	IAW MM.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2005022300131	20050223	00131	CE  	2005	2	23	CA040412014      	1	20040407	G	7120		LUG             	LYC         		HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  	HARTZL	HCB3Z	HCB3Z201    	GL  	CRANKCASE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HARD LANDING OCCURRED AND A HARD LANDING INSPECTION WAS CARRIED OUT ON THE ENTIRE A/C.  NO OTHER DEFECTS WERE FOUN	D OTHER THAN THE CRACKED LUG MOUNT.  AN ENGINE CHANGE WAS DONE.  ENGINE MODEL G0-480-G1D6 S/N L-394-37 WAS INSTALLED.					1	H	7	1 	3O	3	O		1A8     	E275	5	C	P907
2004100500018	20041005	00018	NE  	2004	10	5	CA040412BBB      	2	20040412	G	7261	3371535030	LINE            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					ENGINE OIL	LEAKING         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AFTER T/O FROM YYJ NO.1 OIL QUANTITY FELL TO 2.5 QT. REDUCED TO IDLE THRUST,QUANTITY ROSE TO 4.0 AND THEN STARTED 	TO FELL AGAIN. SHUT ENGINE DOWN AT 10,000 FT ON APP TO YVR. ACTION: FOUND OIL LINE FITTING LOOSE. OIL LINE LOCATED IN BE	TWEEN GEAR BOX AND REAR BEARING. FITTING RE-TIGHTENED,ENG. IDLE RUN CARRIED OUT FOR 5 MINS NIL LEACKS FOUND, CONSIDERED 	SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004080500096	20040805	00096	EA  	2004	8	5	CA040413001      	1	20040404	G	2520		SPRING          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					SEAT BELTBUCKLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PASSENGER SEATBELT BUCKLE WAS FOUND TO HAVE NO SPRING TENSION IN THE LOCK POSITION.  THE DRIVE SCREW PIN HAD BACKE	D OFF .0312  WHICH ALLOWED TENSION TO RELEASE.  BELT ASSEMBLY IS SAFTEY PRODUCTS. THE BUCKLE IS STAMPED.  THIS IS A MID 	COAST STC INTERIOR INSTALLATION.  ITEM P/N BL/6-3800BOB54TSA REV. A				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080500097	20040805	00097	EA  	2004	8	5	CA040413002      	1	20040407	G	2424	720846B	VOLT REGULATOR  	SUNDSTRANDAI		CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502R     	41580	NE  					GCU	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA						580					(CAN) IN FLIGHT LOSS OF NR 2 AC BUSS SERVICES CAUSED BY NR 2 GENERATOR DROPPING OFF LINE.  RESET ATTEMPTS FAILED. DUE TO	 AN AD IN EFFECT ON THE REMAINING GENERATOR,  A LANDING AT THE NEAREST AIRPORT WAS CARRIED OUT. DURING FAULT ISOLATION I	T WAS FOUND THAT THE GENERATOR WAS DISPLAYING AN OVER VOLTAGE CONDITION ON THE VOLTAGE CHECK. THE NR 2 GCU WAS SWAPPED W	ITH NR 1 AND THE OVER VOLTAGE CONDITION TRANSFERRED TO THE NR 1 SYSTEM.  AS THE VOLTAGE REGULATOR SECTION OF THE GCU IS 	BELIEVED TO BE AT FAULT, SERVICEABLE GCU WAS INSTALLED AND NORMAL SYSTEM OPERATION WAS RESTORED.		2	L	7	2 	4F	4	F	RT	A21EA   	E6NE
2004080500098	20040805	00098	EU  	2004	8	5	CA040413003      	1	20040407	G	5246	A52475147012	ACCESS DOOR     			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					LAV SERVICING	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT ARRIVED AT THE STATION WITH THE MID LAVATORY SERVICING ACCESS DOOR MISSING.  THE AIRCRAFT WAS DISPATC	HED UNDER CDL AND A NEW DOOR WAS INSTALLED AT THE MAIN BASE.  THE LAVATORY SYSTEM WAS CHECKED SERVICEABLE (NO LEAK).  SU	SPECT PANEL NOT PROPERLY LATCHED AT THE PREVIOUS STATION.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2004080500101	20040805	00101	SW  	2004	8	5	CA040413006      	1	20040325	G	6410	406016100119	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	CONTAMINATED    	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ONE TAILROTOR BLADE FOUND TO HAVE ABSORBED WATER, THROWING THE TAIL ROTOR OUT OF BALANCE AND CREATING EXCESSIVE VI	BRATIONS.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004080500102	20040805	00102	EA  	2004	8	5	CA040413007      	1	20040301	G	5755	2651001011	ACTUATOR        			DHAV  	DHC7  	DHC7*       	       	EA  										SPOILERS	DISLODGED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			15131	15131							(CAN) DURING CRUISE FLIGHT LT ROLL SPOILER ACTUATOR BROKE OFF ITS MOUNTS.   NR 2 HYDRAULIC SYSTEM WAS LOST DUE TO A HYDR	AULIC LEAK FROM THE ACTUATOR. AIRCRAFT LANDED SAFELY.  PROBLEM WAS FOUND TO BE A PRE MOD ROLL SPOILER ACTUATOR WHICH THE	 OPERATOR HAD NOT UPDATED TO THE IMPROVED.				2	H	7	4 	4T			RT	A20EA
2004080500103	20040805	00103		2004	8	5	CA040413008      	4	20040407	G	3460	4043912902	CDU             			AIRBUS	310   	A310300     	3930305	EU  										COCKPIT	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			49995	49995							(CAN) DURING TAXIING TO THE GATE, AIRCRAFT EXPERIENCED SMOKE IN THE FLIGHT DECK CAUSED BY NR 2 FMS CDU.  NR 2 CDU WAS CO	NFIRMED FAULTY AFTER MAINTENANCE INVESTIGATION AND THE AIRCRAFT WAS DISPATCHED UNDER MEL.  CDU WAS REPLACED ON RETURN FL	IGHT AND ROUTED TO VENDOR FOR INVESTIGATION. TSSV: 1861 HRS.				2	L	7	2 	4F			RT	A35EU
2004080500104	20040805	00104	NM  	2004	8	5	CA040413009      	1	20040410	G	3220	658005113	DRAG BRACE      			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			58478								(CAN) NOSE GEAR UPPER DRAG BRACE HAS A CRACK APPROXIMATELY .2500 INCHES IN LENGTH AND .1250 INCHES IN DEPTH,  NEAR LT GE	AR DOOR ATTACHMENT POINT.  UPPER DRAG BRACE REPLACED.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004080500105	20040805	00105	NM  	2004	8	5	CA040413010      	1	20040409	G	3220	658005113	DRAG BRACE      			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			57213								(CAN) NOSE GEAR UPPER DRAG BRACE HAS A CRACK APPROXIMATELY .2500 INCHES IN LENGTH AND .1250 INCHES IN DEPTH, NEAR LT GEA	R DOOR ATTACHMENT POINT.   UPPER DRAG BRACE REPLACED.  TIMES 57213:23 CYCLES 53614.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004080500106	20040805	00106	NE  	2004	8	5	CA040413011      	2	20040409	G	7310	2C68	PUMP            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION ALUMINUM PARTICLES WERE FOUND IN THE AIRFRAME FUEL FILTER DOWNSTREAM OF THE FUEL BOOST P	UMP.  RUNNING THE BOOST PUMP SHOWED THAT WHILE IT MAINTAINED OPERATING PRESSURE AN INTERMITTENT GRINDING NOISE COULD BE 	HEARD. DISSASEMBLY OF THE PUMP SECTION OF THE ASSEMBLY SHOWED THE TWO PIECE IMPELLER ASSEMBLY HAD BECOME DISBONDED.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004080500107	20040805	00107	SO  	2004	8	5	CA040413012      	1	20040412	G	3710		SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					VACUUM PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AT 400 HRS SPECIAL INSPECTION FOUND OIL LEAK ON RT ENGINE, OUT OF VACUUM PUMP SHAFT.  REMOVED PUMP FOUND DRIVE SHA	FT SEAL LEAKING PN: 06A19956. AFTER THE SEAL REMOVAL DURING VISUAL INSPECTION FOUND RUBBER PART OF THE SEAL SCUFFED IN S	OME PLACES CAUSING THE LEAKAGE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2004080600001	20040806	00001	EA  	2004	8	6	CA040413013      	1	20040408	G	2435	230481490	FAN             	LUCAS       		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STARTER GEN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						4835					(CAN) DURING INSTALLATION OF FAN PN 230481490 AT OVERHAUL, THE CENTER PART OF THE FAN BROKE AWAY FROM THE FAN BODY AND B	LADES.  THE CAST ALUMINUM FAN WAS BEING ATTACHED TO THE SHAFT, ARMATURE AND BEARING ASSY WHEN IT BROKE CIRCUMFERENTIALLY	 BEFORE REACHING TARGET TORQUE ON THE SHAFT NUT OF 110 INCH-LBS. THE BREAK APPEARS TO BE A CLEAN BREAK, IE THERE IS NO S	IGN OF A PRE-EXISTING CRACK. PART WAS REPLACED BY AN ALTERNATE P/N 23048-1240.  BROKEN FAN HAS BEEN QUARANTINED.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2004080600002	20040806	00002	NE  	2004	8	6	CA040414001      	2	20040401	G	7230	3020159	RETAINING RING  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COMPRESS SHROUD	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HOT SECTION WAS DISMANTLED FOR A SCHEDULED CT DISK REPLACEMENT.  CT SHROUD SEGMENTS HAD SHIFTED AXIALLY.  THE 	RETAINING RING HAD COME OUT OF THE GROOVE.  THIS PROBLEM HAS BEEN DOCUMENTED ON OTHER ENGINES.  MFG HAS ISSUED P/N 31107	41-02 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 ALLOW THE M	ORE ROBUST RETAINING RING TO BE USED.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL
2004080600003	20040806	00003	SO  	2004	8	6	CA040414002      	1	20040414	G	5730	4065910	SKIN            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15452								(CAN) CRACKING OF RT WING LEADING EDGE SKIN AT STA 160.50 AND 174.50 FROM RIVETS 1 RIVET FORWARD OF STRINGER AHEAD OF TH	E SPAR.  REVIEW OF AIRCRAFT RECORDS DID NOT SHOW ANY RECENT HISTORY OF HARD LANDINGS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004080600004	20040806	00004	EA  	2004	8	6	CA040414003      	1	20040309	G	2750	664901	SOLENOID        			DHAV  	DHC7  	DHC7*       	       	EA  										FLAP DUMP	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			18724								(CAN) SCREWS ON THE SECOND STAGE FLAP DUMP SOLENOID VALVE BROKE AND CAUSED THE TRAILING FLAPS TO MALFUNCTION.  NO FLUID 	WAS LOST.  PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.  PART SENT TO MFG FOR INVESTIGATION.					2	H	7	4 	4T			RT	A20EA
2004080600005	20040806	00005	EU  	2004	8	6	CA040414004      	1	20040406	G	3246	13889	BEARING         			BNORM 	BN2   	BN2         	1520202	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG WHEEL	DESTROYED       	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) NR 4 WHEEL OUTER AND INNER BEARINGS FAILED. THE BRAKE CALIPER SLIPPED FROM THE TORQUE PLATE AND THE BRAKE HYDRAULI	C HOSE BROKE. THE CAPTAIN USED THE AIRCRAFT FIRE EXTINGUISHER TO EXTINGUISH THE SMOKE AT THE WHEEL. SHE SAYS NO FIRE WAS	 SEEN. THE AXLE WAS FOUND DAMAGED DUE TO THE FAILED WHEEL BEARINGS.				1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920
2004080600007	20040806	00007	NM  	2004	8	6	CA040415001      	1	20040327	G	2740	6355C000101	MOTOR           			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					STAB TRIM	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTS WHILE AT LEVEL AT FLIGHT 39,000 FT, (AUTOPILOT DISENGAGED, MASTER CAUTION FLIGHT CONTROL ILLUM	INATED, SPEED TRIM FAIL LIGHT ILLUMINATED, NO ELECTRIC TRIM, NO AUTOPILOT) FOLLOWING IN-FLIGHT TROUBLESHOOTING/NON NORMA	L CHECKLISTS, AC LANDED W/O INCIDENT. MAINT REPLACED ELECTRIC STABILIZER TRIM MOTOR IAW MM AND TESTED SYSTEM IAW MM. NO 	FAULTS FOUND. AC RETURNED TO SERVICE WITH NO FURTHER PROBLEMS TO REPORT. THIS UNIT IS A NEW MFG (C) MODEL WHICH VENDOR H	AS COMPLETELY OVERHAULED BECAUSE OF PROBLEMS WITH THEIR (B) MODEL. THIS WAS FIRST SUCH STAB TRIM PROBLEM WITH NEW (C) MO	DEL AND IS CURRENTLY BEING INVESTIGATED BY MFG. RELIABILITY DEPT IS CURRENTLY WAITING FOR FINAL STRIP REPORT FROM MFG.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2004080600008	20040806	00008	SO  	2004	8	6	CA040415002      	2	20040404	G	8530		VALVE GUIDE     	CONT        		CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1A170	1A170*      	GL  	CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER NR 3, 4 AND 5, EXCESSIVE OIL CONSUMPTION AND LOW COMPRESSION.  ENGINE WAS RETURNED TO OVERHAUL FACILITY W	HERE IT WAS DISCOVERED THAT 3 OF 6 CYLINDERS HAD EXCESSIVE PLAY IN THE EXHAUST VALVE GUIDES WHICH CAUSED THE VALVE TO BE	COME COKED AND STICK IN THE GUIDE. CYLINDERS MFG. S/N: NR 3, 31109,NR 4, 31215, AND NR 5,  31213.				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P857
2004080600009	20040806	00009	CE  	2004	8	6	CA040415003      	1	20040325	G	1430	AN2312	CLEVIS BOLT     			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELEVATOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INCORRECT INSTALLATION OF UPPER ELEVATOR CABLE TO ELEVATOR BELLCRANK. AFTER A RECENT PAINT JOB WHERE THE ELEVATOR 	HAD BEEN REMOVED, THE UPPER BOLT WAS INSTALLED INCORRECTLY. THE AIRCRAFT SERVICE MANUAL MAKES (SPECIAL NOTE) THAT THE UP	PER CABLE MUST BE ATTACHED WITH BOLT HEAD ON RT, THIS SUPPLIES PROPER CLEARANCE BETWEEN BOTH HEAD AND ADJACENT STRUCTURE	 WITH THE BOLT INSTALLATION REVERSED. THE NUT (AN310-3) INTERFERED WITH ADJACENT BULKHEAD, THIS LIMITED UP ELEVATOR TRAV	EL THE POSSIBILITY ALSO EXISTED THAT THE ELEVATORS COULD HAVE JAMMED IN THE FULL UP POSITION. THE AIRCRAFT HAD PREVIOUSL	Y FLOWN A TRAINING FLIGHT DOING INTENTIONAL STALLS AND SPINS.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004080600019	20040806	00019	EU  	2004	8	6	CA040415004      	1	20040408	G	2730	298G3096	BELLCRANK       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	ELEVATOR CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PREFLIGHT INSPECTION, WHEN CHECKING ELEVATOR PLAY, EXCESSIVE MOVEMENT REVEALED THE ELEVATOR CONTROL BELLCRANK P	RIMARY ATTACH LUG WAS CRACKED THROUGH AND ROD END WAS BEING RETAINED BY OVERSIZED SECONDARY LUG RESULTING IN A DECREASE 	OF TRAVEL ON STARBOARD ELEVATOR AND SUBSTANTIALLY INCREASED FREE PLAY. THE ELEVATOR ACTUATOR ROD WAS RETAINED BY THE RES	TRICTING BRACKET, INTRODUCED BY MANDATORY MODIFICATION 2449/SB27-33. THERE IS NO REPORT OF THE AIRCRAFT RECENTLY EXPERIE	NCING ANY GUST LOADS TO THE ELEVATORS.		2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899
2004080600036	20040806	00036	NM  	2004	8	6	CA040415005      	1	20040405	G	3210	6524480412	ATTACH FITTING  			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG UPLOCK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE BY VISUAL INSPECTION OF THE RT LANDING GEAR UPLOCK ATTACH FITTING, A SUSPECTED CRACK WA	S DETECTED AT THE UPLOCK ATTACH LUG.   FITTING WAS REMOVED FROM AIRCRAFT AND SUBMITTED FOR NDT.  NDT INSPECTION BY EDDY 	CURRENT CARRIED OUT AND CONFIRMED THAT THE LUG WAS CRACKED TO APPROXIMATELY 50 PERCENT OF MATERIAL.  FITTING REPLACED ON	 AIRCRAFT.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2005022300132	20050223	00132	EA  	2005	2	23	CA040415006      	2	20040402	G	7200		ENGINE          								PWA   	PT6   	PT6A28      	 	EA  						DAMAGED         	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			15516					50870			ENG REMOVED AFTER A/C DRIFTED TO LT SIDE OF RWY & HIT A 4 FT SNOWBANK. NLG COLLAPSED & ENG HIT BANK AT MAX PWR. EXHAUST 	DUCT & GG CASE HAD OUTER SKIN BUCKLING. 2ND STAGE REDUCTION PLANET GEAR CARRIER BENT, PT RUB DAMAGE ON BLADE TIPS. COMP 	BLADES, STATORS & IMPELLER RUB DAMAGE. PT DISK DISPLACED, COMPRESSOR RUB DAMAGE GG CASE. RGB OIL PRESS XFER TUBE BENT & 	CONNECTING ELBOW BROKEN. IN TEST CELL, DURING TEST FOUND ENG PERFORMANCE ACCEPTABLE, BUT A LOUD RUB NOISE HEARD ON RUNDO	WN, TRACED TO WORN SPLINES ON RGB HOUSING. CHANGED HOUSING. REMOVED FROM CELL TO INVEST 2ND STAGE GEARING, FOUND REAR FA	CE OF 2ND STAGE CARRIER DISTORTED. CARRIER CHANGED, ENG TESTED. NO ADVERSE NOISES ON SHUTDOWN, ENG DECLARED SERVICEABLE.						4	T			E4EA
2004080600037	20040806	00037	WP  	2004	8	6	CA040415007      	2	20040413	G	7250	310117017	PINION GEAR     			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)  AFTER TAKEOFF, FLIGHT CREW HAD CHIP DETECTOR LIGHT ILLUMINATE ON RT ENG. CREW REDUCED POWER AND IMMEDIATELY RETUR	NED TO LAND. MAINT WAS SENT TO INSPECT CHIP DETECTOR, DISCOVERED SEVERAL CHUNKS OF FERROUS METAL ON CHIP DETECTOR PLUG. 	OIL FILTER WAS REMOVED AND INSPECTED, FOUND TO CONTAIN AN ABNORMAL AMOUNT OF METAL. UPON ROTATING PROP, A GRINDING/RATTL	ING NOISE WAS OBSERVED COMING FROM GEAR CASE. ENG WAS REPLACED AND UNSERVICEABLE ENG TORN DOWN.  INITIAL FINDINGS WERE T	HAT HIGH SPEED PINION GEAR HAD SHED A GEAR TOOTH WHICH WAS WHAT WAS FOUND ON CHIP DETECTOR.  NO FURTHER REASON FOR PINIO	N GEAR FAILURE HAS BEEN DISCOVERED. MORE INFORMATION WILL FOLLOW IF ANY CAUSE OR CONTRIBUTING FACTORS CAN BE DETERMINED.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2004080600038	20040806	00038	NM  	2004	8	6	CA040415008      	1	20040328	G	3242	58570	VALVE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PARK BRAKE	SLOW            	W				O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA			37510	37510							(CAN) ON TAXI TO HANGER, BRAKES OVERHEATED CAUSING FIRE ON NR 3 AND NR 4 MAIN WHEEL ASSEMBLIES AND NR 1 AND NR 2 BRAKE A	SSEMBLIES TO GLOW RED HOT. ALL FOUR MAIN WHEEL AND BRAKE ASSEMBLIES REPLACED.  RT MAIN LANDING GEAR SHOCK STRUT REPLACED	. OTHER ITEMS, BRAKE LINES, FIRE EXTINGUISHERS, ETC REPLACED AS REQUIRED. EXTENSIVE TROUBLESHOOTING COMPLETED AND FAULT 	TRACED TO PARKING BRAKE VALVE SLOW TO RELEASE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080600039	20040806	00039	SO  	2004	8	6	CA040416001      	1	20040408	G	3230	4032700	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			13080								(CAN) ON LANDING, THE AIRCRAFT SLOWLY SETTLED WITH THE LT WING LOW ON LANDING ROLL. THE PILOT STOPPED AND SHUT DOWN THE 	ENGINES. THE PILOT CALLED MAINTENANCE AND MAINTENANCE INSPECTED THE AIRCRAFT ON THE RUNWAY. THE AME NOTICED A LOT OF HYD	RAULIC FLUID ON THE GEAR LEG AND FOUND THE CRACK IN THE HOUSING. THE AIRCRAFT WAS TOWED TO THE HANGER. THE HOUSING WAS R	EPLACED WITH A NEW UNIT AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004080600040	20040806	00040	SO  	2004	8	6	CA040416002      	1	20040416	G	8100	LW18302	SUPPORT         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TURBOCHARGER SUPPORT MOUNT FOUND CRACKED ON LOWER LT TUBE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004080600041	20040806	00041	NE  	2004	8	6	CA040416003      	2	20040416	G	8530	153072	CYLINDER HEAD   			DOUG  	DC4   	C54A        	3021512	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE CREW NOTICE A SLIGHT VIBRATION TO THE NR 1 ENGINE, THEY ALSO NOTICED AN OIL LEAK. THE ENGINE WA	S SHUT DOWN AND PROPELLER FEATHERED.  DURING INSPECTION IT WAS NOTICED THAT THE NR 9 CYLINDER HEAD WAS SEPARATING FROM T	HE BARREL, THE ENGINE WILL BE REPLACED FOR COMPANY CONVIENCE.				2	L	7	4 	4R	4	R	 	A762    	5E5	6	C	P603
2004080600042	20040806	00042	EA  	2004	8	6	CA040417001      	1	20040413	G	5510	600220591008	FAIRING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) FLYING THRU SHOWERS AT 10000 FT , ON ARRIVAL, LARGE FLASH WAS OBSERVED.  NO AIRCRAFT SYSTEM AFFECTED.  AFTER LANDI	NG, 2 BLACK MARKS WERE FOUND ON THE LOWER RT HORIZONTAL STABILIZER.  REPAIR EO 670-55-12-153 ALONG WITH NON DESTRUCTIVE 	TEST (NDT) CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080600043	20040806	00043	EA  	2004	8	6	CA040417002      	1	20040414	G	3230	69210	SEQUENCE VALVE  			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			28730								(CAN) ON APPROACH , THE CREW SELECTED GEAR DOWN, NOSE GEAR WOULD NOT COME DOWN, AMBER AND RED CATION AND WARNING LIGHTS 	ON AND LOUD GRINDING NOISE IN NOSE WHEEL AREA WAS HEARD, THE CREW CARRIED OUT AN ALTERNATE GEAR SELECTION (THE ABOVE IS 	EXTRACTS FROM PILOT'S REPORT ) SEVERAL GEAR SWINGS COMPLETED AND WAS UNABLE TO DUPLICATE THE SNAG. SEQUENCE VALVE REPLAC	ED FOR TROUBLE SHOOTING. SEVERAL MORE GEAR SWINGS COMPLETED WITH NO FAULT FOUND. SEQUENCE VALVE WAS SENT FOR TEAR DOWN R	EPORT, WILL UPDATE AS REPORT BECOME AVIALABLE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080600067	20040806	00067	GL  	2004	8	6	CA040419001      	2	20040416	G	7230	23050833	COMPRESSOR      			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA											(CAN) ENGINE FAIL AT APPROX 150 FT. AGL ON CLIMB OUT, PILOT HEARD LOUD BANG ENGINE QUIT.  PRELIMINARY INSPECTION SHOWS C	OMPLETE COMPRESSOR FAILURE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004080600068	20040806	00068	NM  	2004	8	6	CA040419002      	1	20040413	G	7830	BACC2A3A00764CG	CONTROL CABLE   			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					THRUST REVERSER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK, THE LT ENGINE THRUST LEVER CONTROL CABLE (T1A) WAS FOUND TO BE CHAFED AND HAD BROKEN CABLE STRANDS	.  DURING INSTALLATION OF NEW CABLE, IT WAS FOUND THAT THE T1A CABLE HAD BEEN ROUTED UNDER THE CABLE GUARD INSTEAD OF OV	ER, CONTRIBUTING TO THE ABOVE MENTIONED DAMAGE TO THE THRUST LEVER CONTROL CABLE.  TIMES 60322.07   CYCLES 56643.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2005022300133	20050223	00133	SO  	2005	2	23	CA040419003      	1	20040415	G	2421		BRUSH BLOCK     	PRESTOLITE  		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ALTERNATOR	SHORTED         	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											AFTER DEPART, LOW VOLT IND & SELECTED AUX VOLTAGE REG WITH NO IMPROVEMENT. SEVERAL SELECTIONS WERE MADE BETWEEN MAIN & A	UX REG WITH NO IMPROVEMENT. A/C RETURNED TO AIRPORT FOR A LANDING. INVEST REVEALED A SHORT-CIRCUITED BRUSHBLOCK IN RT AL	TERNATOR R, WHICH DESTROYED BOTH MAIN & AUX REGULATORS, WHICH PREVENTED FUNCTIONAL LT ALTERNATOR FROM FUNCTIONING. SHORT	ED BRUSHBLOCK IN THE RT ALTERNATOR REPLACED WITH A FUNCTIONAL BRUSHBLOCK & BOTH REG`S REPLACED WITH NEW UNITS. ENG`S WER	E GROUND RUN & VOLT REGULATORS CHECKED AT 28.5 VOLTS,  A/C RETURNED TO SERV.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004080600069	20040806	00069	NE  	2004	8	6	CA040419004      	2	20040417	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LEFT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DEPARTING, WHILE CRUISING AT 31 000 FT, LOUD BANG COMING FROM LT ENGINE WITH DECREASING  EPR , INCREASING  EGT UP 	TO 575 C. DID NOT HAVE A RE-LIGHT WITH IGNITER  ON INCREASING POWER WAS NOT RESPONDING, SO WE TREATED THAT AS A SEVERE D	AMAGE OR SEPARATION AND THE ENGINE WAS SHUT DOWN.  AIRCRAFT WAS DIVERTED.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004080600070	20040806	00070	EU  	2004	8	6	CA040420001      	1	20040415	G	6321	10541227	STRUCTURE       			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ROTOR BRAKE BOX	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) THE COLLECTIVE FRICTION ASSEMBLY WAS REPORTED FEELING LOOSE. LOOSENESS WAS TRACED TO THE BRAKE BOX, WHICH WAS MOUN	TED WITH 6MM BOLTS IN 10MM HOLES.					1	G	7	2 	3U	3	U		H3EU    	E4CE
2004080600071	20040806	00071	EU  	2004	8	6	CA040420002      	1	20040329	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYDRAULIC PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING BULLETIN ON HYDRAULIC SYSTEM IT WAS NOTICED THAT THE BELT WAS CRACKED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004080600072	20040806	00072	SW  	2004	8	6	CA040420004      	1	20040401	G	5320	206032307	ANGLE           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK WAS FOUND IN A 1200 HR INSPECTION.  THE PART WAS REPLACED AND TB 206L-87-139 WAS C/W TO STOP  MORE DAMAGE						1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004080600073	20040806	00073	GL  	2004	8	6	CA040420005      	2	20040413	G	7250	23033195	TURBINE         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					1ST STAGE NOZZLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN INSTALLING A NEW SMOKELESS LINER A CRACK WAS WAS FOUND IN FIRST NOZZLE. TURBINE WAS REPAIRED AT AN ENGINE SHO	P					1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2005022300134	20050223	00134	EA  	2005	2	23	CA040420007      	1	20040415	G	2820	MS29513326	O-RING          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL COUPLING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE WALK AROUND , MAINTENANCE DISCOVERED FUEL LEAK AROUND RT WING DRYBAY DRAIN.  DRY BAY PANELS WERE RE	MOVED AND DRY BAY FOUND TO HAVE SMALL AMOUNT OF FUEL PRESENT.  THE COUPLING THAT ATTACHES THE AIR SCOOP TO THE FUEL TANK	 VENTLINES ON THE RT WING WAS FOUND TO BE LEAKING INTO THE DRY BAY.  COUPLING PACKINGS WERE REPLACED AND LEAK CHECK WAS 	COMPLETED WITH NO LEAKS FOUND.  AIRCRAFT WAS RETURNED TO SERVICE.  AIRCRAFT HOURS WERE 11178:51 AIRCRAFT CYCLES WERE 910	7		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005022300135	20050223	00135	NE  	2005	2	23	CA040421001      	2	20040419	G	8500		ENGINE          			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	NR 1	VIBRATION       	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA								CP353136			(CAN) DURING TAKEOFF, THE CREW NOTICED THE NR 1 ENGINE HAD A NOTICEABLE VIBRATION, THE TAKEOFF WAS ABORTED.  THE ENGINE 	WILL BE REMOVED AND SENT FOR EVALUATION UNDER WARRANTY.					2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603
2005022300136	20050223	00136	EU  	2005	2	23	CA040421002      	1	20040418	G	3040		TERMINAL        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CB PANEL	BURNED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS HAVING PROBLEMS WITH THE WINDSCREEN DE-ICE SYSTEM.  THE MAIN POWER INPUT LEAD TO THE GENERATOR 2 	BUSS WAS FOUND BURNED AND CORRODED.  A NEW TERMINAL WAS INSTALLED AND THE SYSTEM FUNCTIONED NORMALLY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005022300137	20050223	00137		2005	2	23	CA040421003      	4	20040420	G	3422		CARD            	CESSNA      		CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	DIRECTIONAL GYRO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						T41571E					(CAN) THE CO-PILOT'S DIRECTIONAL GYRO WAS RECENTLY REPLACED WITH THE ABOVE MENTIONED OVERHAULED INSTRUMENT.  UPON COMPLA	INT FROM PILOT, THE INSTRUMENT WAS HARD TO SET, A FUNCTIONAL TEST WAS COMPLETED.  IT WAS FOUND THAT PUSHING THE KNOB IN 	AND TURNING IT DID NOT ROTATE THE CARD WITH EASE.  FOUND THAT IT TOOK ABNORMALLY GREAT AMOUNT OF INWARD PRESSURE WHILE T	URNING THE KNOB TO GET ANY MOVEMENT OF THE CARD ESPECIALLY IN THE CLOCKWISE ROTATION.  THE INSTRUMENT HAS ONLY 37.6 HOUR	S AND 34 CYCLES SINCE OVERHAUL.		1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL
2005022300138	20050223	00138	CE  	2005	2	23	CA040421004      	1	20040421	G	7111	07520144	PAN             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	COWL FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING RIGHT COWL FLAP HINGE REPLACEMENT, FOUND COWL FLAP PAN ASSEMBLY HAS SEVERE CORROSION UNDER HINGE HALF.  THI	S AREA IS ONLY VISIBLE AFTER REMOVING THE HINGE.					1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P47GL
2005022300139	20050223	00139	NM  	2005	2	23	CA040422001      	1	20040420	G	2910	82920010229	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT CREW REPORTED NR 1 AND NR 2 HYDRAULIC QUANTITIES AT MINIMUM LEVELS.  MAINTENANCE FOUND PERMASWAGE FITTING O	N NR 2 LANDING GEAR DOWN LINE IN CENTER FUSELAGE LEAKING.  NEW SECTION OF HYDRAULIC LINE WAS INSTALLED AND SWAGGED IAW A	MM 20-06-13.  LEAK CHECKS AND GEAR SWINGS WERE PERFORMED AND CHECKED SERVICEABLE.  AIRCRAFT HOURS 36612:46 AIRCRAFT CYCL	ES 37042.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005022300140	20050223	00140	CE  	2005	2	23	CA040422002      	1	20040421	G	7722	30739501	THERMOCOUPLE    			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT ENGINE	SHORTED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) IN CLIMB AND CRUISE ALTITUDE THE FLIGHT CREW NOTICED A FLUCTUATION OF THE ITT ON THE RT ENGINE INDICATOR (ITT).  T	ROUBLESHOOTING WAS DONE BY MAINTENANCE PERSONNEL AND THEY FOUND THE RT ITT HARNESS WAS TOUCHING THE OUTER CASE OF THE EX	HAUST SHROUD (POOR ROUTING).  THE HARNESS SHEILD WAS SHORTED.				2	L	7	2 	4F	4	F		A10CE   	E6WE
2005022300141	20050223	00141	CE  	2005	2	23	CA040422003      	1	20040422	G	7120	045100336	MOUNT           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11850								(CAN) AT INSPECTION THE ENGINE MOUNT WHICH ALSO HAS PROVISION FOR MOUNTING THE NOSE LANDING GEAR WAS FOUND DAMAGED.  TWO	 TUBES WERE CRACKED, THREE OTHERS WERE SLIGHTLY BENT.  ALL EVIDENCE POINTS TO A UNREPORTED HARD LANDING.  AIRCRAFT HAS B	EEN THOROUGHLY INSPECTED FOR FURTHER DAMAGE.  NONE FOUND.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2005022300142	20050223	00142	SW  	2005	2	23	CA040422004      	1	20040418	G	6710	2050010461	GRIP            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CYCLIC STICK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE GREASING AND SERVICING OF MAIN ROTOR COMPONENTS AME ATTEMPTED TO MOVE THE PILOT'S CYCLIC STICK.  AS	 THE MOVEMENT WAS ATTEMPTED, THE GRIP BROKE INTO TWO PIECES.  THE FRACTURE OCCURRED BETWEEN THE FORCE TRIM RELEASE SWITC	H AND CARGO RELEASE SWITCH.  NEW GRIP WAS REWIRED AND INSTALLED.  A/C RETURNED TO SERVICE.				1	G	7	1 	4U	4	U		H4SW    	E22EA
2005022300143	20050223	00143	NM  	2005	2	23	CA040422005      	1	20040211	G	3233	46455109	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LT MLG	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											(CAN) AFTER GEAR DOWN SELECTION, NR 2 HYD ISO VALVE' CAUTION CAME ON AND DURING THE WHOLE APPROACH TO LANDING, 'OUTBOARD	 ROLL SPOILER CAUTION LIGHT' CAME ON INTERMITTENTLY.  THIS WAS DUE TO, LOW QUANTITY IN NR 2 HYD SYSTEM.  MADE A GO AROUN	D, AND KEPT GEAR DOWN WITH FLAPS 5.  PERFORMED SYSTEM FAILURE CHECKLISTS AND DECIDED TO COMPLETE ALTERNATE GEAR EXTENSIO	N PROCEDURE AS WELL.  A NORMAL LANDING COMPLETED.  INVESTIGATION/ACTION, EXTENSION HOSE FOR LT MAIN LANDING GEAR EXTENSI	ON/RETRACTION ACTUATOR FOUND LEAKING.  EXTENSION HOSE REPLACED ACCORDING AMM 32-31-11.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005022300144	20050223	00144	NM  	2005	2	23	CA040422006      	1	20040217	G	3297		WIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG PROX SENSOR	SHORTED         	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											GEAR OUT INDICATION AFTER TAKEOFF, NOSE GEAR DOWN, NOSE GEAR UNSAFE AND GEAR IN TRANSIT LIGHT REMAINED ON.  DURING DESCE	NT, THE LIGHTS WENT OUT AND ON FOUR TIMES.  INVESTIGATION/ACTION, THE PROXIMITY SENSOR ELECTRONIC UNIT INTERROGATED FOR 	FAULTS, PSEU FAULT NR 1.  THE NOSE GEAR DOWN SENSOR WIRING WERE FOUND SHORTED.  SENSOR REPLACED ACCORDING AMM 32-61-06.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005022300145	20050223	00145	CE  	2005	2	23	CA040422007      	1	20040421	G	2140	2062071	RECEPTACLE      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CABIN	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHEN THE CABIN CENTER HEADLINER WAS REMOVED DURING ROUTINE MX, RADIANT HEAT RECEPTACLES/SOCKETS WERE FOUND CHARRED	 AND MELTED WITH THE WIRE CONNECTERS INSIDE THE SOCKET LOOSE AND BURNT, PROBABLY FROM THE AMOUNT OF CURRENT BEING DRAWN 	THROUGH THE WIRES WHEN RADIANT HEAT WAS ON FOR LONG PERIODS OF TIME OVER THE YEARS OF OPERATION. RECEPTACLES, SOCKETS, A	ND CONNECTERS WERE REPLACED NEW ON BOTH THE FRONT AND BACK OF THE CABIN CENTER HEADLINER, AND FUNCTION TESTED SERVICEABL	E. ALL OTHER KA 200 S OPERATED BY THE COMPANY WERE INSPECTED AND FOUND TO HAVE SIMILAR DAMAGE, TO SOME DEGREE ON THE RAD	IANT HEAT CONNECTERS.  ALL PARTS WERE REPLACED NEW AND SYSTEMS CHECKED SERVICEABLE.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC
2005022300146	20050223	00146	SO  	2005	2	23	CA040423001      	1	20040413	G	7603	AN37	BOLT            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	POWER LEVER	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											THE PILOT WAS UNABLE TO CHANGE PWR SETTINGS IN FLT AS THE THROTTLE DID NOT RESPOND FROM MOVEMENTS IN THE PWR LVR. THE A/	C IMMEDIATELY RETURNED FOR AN UNEVENTFUL LANDING WITH THE RPM SET AT 2300.  INSPECTION OF A/C FOUND THAT THROTTLE CNTRL 	WAS DISCONNECTED FROM CARBURETOR THROTTLE ARM. THE ATTACHING HARDWARE WAS MISSING AND NOT RECOVERED DUE TO OPEN NATURE O	F LOWER COWING. THE SPHERICAL ROD END ASSY WAS FOUND STIFF AND COULD NOT BE ROTATED BY NORMAL HAND PRESSURE. IT IS SUSPE	CTED THAT BOLT HAD FRACTURED DUE TO FATIGUE OVER TIME AS THIS BOLT IS ON CONDITION ITEM AND THE AGE IS UNKNOWN. ALSO THE	 STIFF ROD END BEARING MAY HAVE AFFECTED THE FAILURE OF THE BOLT.	1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2005022300148	20050223	00148	CE  	2005	2	23	CA040423003      	1	20040423	G	3230	12416432	SPRING          			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	MLG DOWNLOCK	SEIZED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DOWNLOCK SPRING ASSY SLIDING ACTION WAS RESTRICTED BY ACCUMULATION OF DIRT AND DEBRIS. DOWNLOCK WAS UNABLE TO FULLY ENGA	GE RESULTING IN AN 'UNSAFE' GEAR IND.  INSPECT REVEALED WET LUBRICATION ATTRACTED DEBRIS AND DIRT IN THE SPRING ASSY CON	CENTRIC SLEEVE AND SPRING.  CESSNA INSPECTION MANUAL SECTION 2 IS VAGUE REGARDING LUBRICATION TYPE AND APPLICABILITY AND	 STATES IN PART - 'AND ANY OTHER FRICTION POINT OBVIOUSLY REQUIRING LUBRICATION'.  CONFUSION MAY ARISE IN THIS EXAMPLE. 	 SUBMITTER RECOMMENDS A DRY LUBRICATION IN THIS AREA, AND INCREASED AWARENESS IN INDIVIDUAL INSPECTION PROGRAMS FOR A/C 	OPERATING IN 'OFF AIRPORT' LOCATIONS, GRAVEL AND DUSTY STRIPS.  SUBMITTER'S A/C IS MODIFIED BY STC SA 5737SW NO DOOR KIT	1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA
2005022300149	20050223	00149	SO  	2005	2	23	CA040423004      	2	20040423	G	8530	653446	CYLINDER        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								293039R			CYLINDER CRACKED THROUGH 75 PERCENT OF CIRCUMFERENCE AT CYLINDER CROWN FROM A POINT BEYOND THE UPPER SPARK PLUG HOLE, AR	OUND THE EXHAUST VALVE, AND TERMINATING AT A POINT BEYOND THE LOWER SPARK PLUG HOLE (BUT NOT TRANSECTING THE HOLE).					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P36EA
2005022300150	20050223	00150	SW  	2005	2	23	CA040423005      	1	20040423	G	5710	2734023008	SPAR            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311U    	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19156								DURING REPLACEMENT OF A BRACKET ON THE RT AILERON, A CRACK APPOXIMATELY .075 INCH WAS DISCOVERED UNDER THE BRACKET AT ON	E OF THE ATTACH POINT BOLT HOLES ON THE SPAR LEADING EDGE.  THE CRACK WAS REPAIRED IN ACCORDANCE WITH APPROVED DATA AND 	THE FAIRCHILD SRM.				2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE
2004062100122	20040621	00122		2004	6	21	CA040423006      	4	20040422	G	3418	1013646283	SWITCH          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	STALL WARNING	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED THAT THE STALL HEAT APPEARED TO BE ON (HIGH) MODE ON THE GROUND WHEN A WALK-AROUND WAS CONDUCTED.  	MAINTENANCE CONFIRMED BY RESEARCHING WIRING DIAGRAM AND SYSTEM OPERATION.  TROUBLESHOT AND FOUND LT MAIN GEAR SAFETY SWI	TCH P/N 101-364628-3 HAD HIGH RESISTANCE THROUGH THE CONTACTS ON SWITCH WHEN AIRCRAFT WAS ON GROUND. THE SWITCH WAS GIVI	NG FALSE INFORMATION TO STALL HEAT PANEL MAK ING IT THINK THE AIRCRAFT WAS IN FLIGHT AND GIVING MAXIMUM VOLTAGE FOR MAXI	MUM HEAT.  SWITCH WAS REPLACED AND OPERATION FOUND NORMAL.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P10NE
2004062100131	20040621	00131		2004	6	21	CA040423007      	4	20040416	G	3418	600591541	POTENTIOMETER   	CONRAC      		CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					AOA TRANSDUCER	INTERMITTENT    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA						247028					(CAN) DURING TAKEOFF ROTATION, THE STICK SHAKER ACTIVATED ON THE LOW LEVEL, THE STALL PROTECT SYSTEM (SPS) WARBLER  SOUN	DED, THE SPS FAIL LIGHTS WENT TO A FLASH CYCLE AND THE STALL PUSH LIGHTS ACTIVATED. THE LT SPS NEEDLE WAS SWINGING BACK 	AND FORTH INTO THE STALL RANGE OVER AN APPROXIMATELY A 60-DEGREE ARC.  MEANWHILE THE RT INDICATOR WAS INDICATING A NORMA	L AND STEADY FLIGHT REGIME.  WHILE AIRCRAFT WAS RETURNING FOR LANDING THE WARNING CONTINUED WITH OCCASIONAL PAUSES UNTIL	 TOUCHDOWN. TROUBLESHOOTING INDICATED FLUCTUATING RESISTANCE VALUES AT THE INDICATOR WITH NO MOVEMENT OF THE VANE. THE V	ANE ASSEMBLY WAS REPLACED AND THE LATERAL ACCELEROMETERS ADJUSTED WITHIN LIMITS.  THE AIRCRAFT WAS RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE
2004062100132	20040621	00132	EU  	2004	6	21	CA040423008      	1	20040420	G	2197		WIRE            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	COOLING FAN	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION, A PERFORATION WAS DETECTED AT A CARGO NET RECEPTACLE. THE SOURCE WAS DETERMINED TO ELECTRICA	L ARCING. THE SUPPLY CABLE FOR THE NR 2 COOLING FAN HAD SHORTED AGAINST THE NET FITTING HOUSING DUE TO CHAFING. THIS EQU	IPMENT IS PART OF STC SA 02-122 THE REMAINING AIRCRAFT INCORPORATING THIS STC HAVE BEEN REVIEWED WITH NO ANOMALIES.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE
2004062100133	20040621	00133	NM  	2004	6	21	CA040423009      	1	20040421	G	3242	26010425	QUICK DISCONNECT	HONEYWELL   		BOEING	737   	7372Q8      	138448K	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BRAKE SYSTEM	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			CA						BC1009					(CAN) AC LANDED, ON ROLL-OUT, WAS OBSERVED TO HAVE SMOKE ISSUING FROM UNDERSIDE OF AC. TOWER ADVISED CREW AND CALLED OUT	 AFF. RT MAIN GEAR WAS FULLY ENGULFED IN HEAVY SMOKE. SMOKE WAS BROUGHT UNDER CONTROL AND AC PASSENGERS AND CREW EVACUAT	ED ONTO RUNWAY.  MAINT REPORTED THAT A/C HAD A NR 3 BRAKE HYD LINE LEAK, WHICH CREATED A LOT OF SMOKE ON CONTACT WITH BR	AKES. AC HAS APPROXIMATELY 55,500 HOURS AND 49,000 CYCLES.  BRAKE LINE WAS REPAIRED AND A/C FERRIED TO BASE FOR FURTHER 	MAINTENANCE.  MAINTENANCE INVESTIGATION ONGOING.  AIRCRAFT REMAINS OUT OF SERVICE. BRAKE ASSEMBLY WILL BE SENT TO MFG FO	R ANALYSIS, TEARDOWN REPORT AND DETAILS OF INVESTIGATION REQUESTED. WILL FOLLOW UP SDR PENDING VENDOR RESULTS.	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004062100134	20040621	00134		2004	6	21	CA040423010      	4	20040421	G	2297		WIRE            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	AUTOPILOT SYS	CHAFED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN)  PILOT REPORTED THAT FLIGHT CONTROLS WERE (STIFF AND VERY HARD TO MOVE).  DURING RUN-UP PRIOR TO DEPARTURE.  PILOT	 ELECTED TO RETURN TO BASE. AMO FOUND THAT WIRE HARNESS BEHIND RADIO PANEL WAS CHAFING ON THROTTLE MOUNT CAUSING SHORT T	O GROUND. THIS CAUSED THE AUTOPILOT SERVO TO ENGAGE UNCOMMANDED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2004062100135	20040621	00135	EA  	2004	6	21	CA040423011      	1	20040421	G	1430		RIVET           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUSELAGE	BURNED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) UPON DESCENT AIRCRAFT WAS STRUCK BY LIGHTNING ON LT SIDE OF NOSE.  AIRCRAFT LANDED WITHOUT INCIDENT.   MAINTENANCE	 COMPLETED LIGHTNING STRIKE INSPECTION IAW AMM 05-51-05.  INSPECTION OF AIRCRAFT STRUCTURE FOUND 25 RIVETS BURNED ALONG 	THE LENGTH OF THE LT FUSELAGE.  RIVETS WERE REPLACED WITH  FASTENERS IAW MFG REO:601R-53-00-114.  INSPECTION OF AIRCRAFT	 SYSTEMS REVEALED NO DAMAGE.  AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004062100136	20040621	00136	EA  	2004	6	21	CA040425001      	1	20040423	G	5311	601360012930	FRAME           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10579								(CAN) DURING COMPLETION OF AD CF-2003-12/A DVI OF AFT FUSELAGE AND REINFORCING ANGLE AT FS640 ON BOTH LT AND RT SIDES BE	TWEEN STRINGERS 9 AND 12 IAW PART A OF MFG SB601-53-061, RT SIDE REINFORCEMENTS PLATE WAS FOUND CRACKED APPROX  .8750 IN	CH LONG AND CORRESPONDING CRACK WAS FOUND ON THE FRAME AT THE UPPER CORNER OF THE ENGINE SUPPORT BEAM APPROX. .6875 INCH	 LONG. IAW SB601R-53-061 WORK PROGRESSED TO PART B STEP E ITEM NR 4.  EDDY CURRENT HAS BEEN PERFORMED WITH NO CRACKS FOU	ND ON SKIN DOUBLER. WORK IS CONTINUING IAW SB AND WILL BE REPORTED AS SOON AS MORE INFORMATION BECOMES AVAILABLE .		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004062100137	20040621	00137	SW  	2004	6	21	CA040426001      	1	20040424	G	5210		SEAL            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311U    	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CABIN DOOR	PINCHED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED AND RETURNED DUE TO NO PRESSURIZATION.  MAINTENANCE FOUND THE FABRIC DOOR SILL COVER HAD BECOME 	PINCHED IN THE CABIN DOOR SEAL.  FABRIC COVER REMOVED AND AIRCRAFT CHECKED SERVICIBLE FOR PRESSURIZATION.					2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE
2004062100147	20040621	00147	CE  	2004	6	21	CA040426003      	1	20040330	G	5610	1014301835	WINDOW          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	WARPED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE DAILY INSPECTION IT WAS NOTED THE RT AFT CABIN WINDOW HAD A INWARD CONCAVE APPEARANCE ACROSS THE 	CENTER FROM TOP TO BOTTOM. UPON REMOVAL WITH THE USE OF A STRAIGHT EDGE IT WAS WARPED ACROSS THIS AREA. NO FURTHER DEFEC	TS IN THE FORM OF CRACKING OR CRAZING WERE NOTED. INTEGRITY OF WINDOW PANE APPEARED NORMAL. THE WINDOW AND SEAL WEAR REP	LACED WITH NEW IAW B200 MM.  NO FURTHER DEFECTS HAVE BEEN NOTED.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004062100148	20040621	00148	EA  	2004	6	21	CA040426004      	2	20040421	G	7314	RG9080J4AM	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PUMP WAS RECENTLY MODIFIED/OVERHAULED.  IT WAS DISCOVERED THAT ENGINE DRIVEN FUEL PUMP OUTPUT PRESSURE DROPPED RIG	HT OFF AT IDLE POWER BUT WAS FINE AT HIGH POWER SETTINGS. ENGINE DID NOT GIVE ANY INDICATION OF PUMP PRESSURE DIFFICULTI	ES, ROUGH RUNNING, QUITTING,ETC.   PUMP WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT.  SUSPECTED INTERNAL RELIEF VAL	VE AT FAULT.  PUMP IS PRESENTLY AT COMPONENT SHOP.  TEARDOWN REPORT RECEIVED FROM AND FINDINGS WERE AS FOLLOWS:  RELIEF 	VALVE POPPET SEATING AREA UNEVENLY WORN AND NICKED CAUSING POOR SEATING ON RELIEF VALVE HSG.  LOCK RING.  ADJUSTMENT SCR	EW CAME OFF AND WAS LODGED BETWEEN SPRING AND SPRING SEAT.   DRIVE SEAL NUT LOCK SCREW WRONG.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004062100149	20040621	00149	EU  	2004	6	21	CA040426005      	1	20040327	G	3244	266F432	TIRE            			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					MLG	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF THE CREW WAS UNABLE TO RETRACT THE LANDING GEAR. AFTER LANDING AN INSPECTION REVEALED THE NR 2 TIRE TRE	AD CAP HAD PEELED OFF AND BROKEN THE LT SQUAT SWITCH, WHICH PREVENTED RETRACTION OF THE LANDING GEAR.  THE SQUAT SWITCH,	 DANGLING BY ITS ELECTRICAL CORD DAMAGED THE FLAP. MAINTENANCE WAS DISPATCHED TO ASSESS AND REPAIR THE DAMAGE. THE WIRIN	G WAS INSPECTED AND NO VISIBLE DAMAGE FOUND. THE SQUAT SWITCH AND WHEEL ASSEMBLY WERE REPLACED.  THE AIRCRAFT WAS JACKED	, THE SQUAT SWITCH (1791) WAS ADJUSTED AND THE GEAR SWING. THE LT IB FLAP WAS REPLACED, RIGGED AND FUNCTION TESTED. AIRC	RAFT WAS RETURNED FOR FLIGHT.	2	L	7	2 	4F	4	F	RT	A7EU    	E7EA
2004062100150	20040621	00150	EA  	2004	6	21	CA040426006      	2	20040317	G	8520	SL75060	BOLT            								LYC   	O540  	TIO540*     	41532	EA  					CONNECTING ROD	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING ASSEMBLY OF ENGINE, A NEW SUPERIOR CONNECTING ROD BOLT, P/N SL75060 AND LOT NR 574065 WAS BEING USED.  FOUN	D THAT THIS BOLTS MACHINING WAS INADEQUATE AND ALREADY WITHIN THE STRETCH LIMITS OF 2.255 - 2.256 INCHES WITHOUT A LOAD 	ON BOLT.									3	O			E14EA
2004062100151	20040621	00151	CE  	2004	6	21	CA040426007      	1	20040402	G	2497		WIRE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ALTERNATOR	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT, THE ALTERNATOR FIELD CIRCUIT BREAKER POPPED. THE PILOT PUSHED IN THE BREAKER SEVERAL TIMES	 UNTIL THE BREAKER STAYED IN. SMOKE THEN APPEARED AND THE PILOT LANDED SAFELY. THE MAIN POWER WIRE AT THE BACK OF THE AL	TERNATOR WAS FOUND WORN. THE WIRE SHORTED OUT AGAINST THE ALTERNATOR CASE. THE FIELD BREAKER GOT SO HOT THAT IT STAYED C	ONTACTED. THE WIRES FROM THE BREAKER TO THE MASTER SWITCH TO THE VOLTAGE REGULATOR WERE FOUND BURNED. THE WIRES WERE REP	LACED AS REQUIRED. THE 5 AMP ALTERNATOR FIELD CB, MASTER SWITCH, ALTERNATOR BRUSHES, AND VOLTAGE REGULATOR WERE ALL REPL	ACED.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004070900084	20040709	00084	SO  	2004	7	9	CA040426008      	1	20040426	G	3231		RELEASE PIN     			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540D4A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	NLG DOOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ANNUAL INSPECTION, WAS UNABLE TO RELEASE DOOR FOR EMERGENCY GEAR EXTENSION. PIN WAS FOUND WORN, AND RETURNED TO	 MFG FOR REPAIR. PIN REINSTALLED AND PROBLEM REPEATED, INVESTIGATION REVEALED NOSE DOOR SYSTEM WAS RIGGED TOO TIGHT. REP	EATED CALLS TO MANUFACTURER WERE MADE FOR ASSISTANCE OR INSTRUCTIONS. NO REPAIR OR MAINTENANCE MANUAL EXISTS. 'WE JUST U	SE A SHUT ON THE WALL AND RIG IT UNTI L WE'RE HAPPY'.   I WAS TOLD FINALLY WAS GIVEN VERBAL INSTRUCTIONS AND WAS ABLE TO	 RIG THE SYSTEM AND TEST EMERGENCY GEAR EXTENSION SUCCESSFULLY.  TWO PROBLEMS:  WORN PIN MAKING GEAR EXTENSION IMPOSSIBL	E.  NO MANUAL OR TECHNICAL SUPPORT FROM MANUFACTURER.	1	L	7	1 	3O	3	O	 	1A15    	1E4	5	C	P25EA
2004062100152	20040621	00152	EU  	2004	6	21	CA040426009      	1	20040425	G	4920		APU             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					APU BAY	FAILED          	W				E	O			ENGINE SHUTDOWN         	OTHER                   			A	Y	J	FLAME/FIRE                	ENGINE STOPPAGE           	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START OF NR 4 ENGINE, THE APU GENERATOR WENT OFF LINE CAUSING AN ABORTED START.  ON SECOND ATTEMPT FLAMES C	AME OUT OF THE EXHAUST.  THE CREW WAS REPORTED OF THIS INCIDENT AND A/C WAS RETURNED TO GATE FOR INSPECTION BY MAINTENAN	CE.  FOLLOWING THE INSPECTION, THE APU WAS DEFERRED IAW MEL 49-00-1 AND GROUND RUN OF ENGINE C/O BY MAINTENANCE.  A/C WA	S RELEASED FOR SERVICE AND ON THE EVENING OF THIS INCIDENT FURTHER INSPECTION CARRIED OUT BY MEANS OF BOROSCOPE WITH NO 	DAMAGE FOUND.  THE RAMP CREW CALLED THE FIRE DEPT AS PRECAUTIONARY MEASURE.		2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004070900099	20040709	00099	NM  	2004	7	9	CA040427001      	1	20040426	G	2420		GENERATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DC SYSTEM	LIGHTNING STRIKE	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, AIRCRAFT WAS STRUCK BY LIGHTENING . BOTH DC GENERATORS WENT OFF LINE AND RESET IAW QUICK REFERENCE HA	ND BOOK (QRH) .  LIGHTENING ENTERED AT NOSE GEAR DOOR AND EXITED AT TAIL CONE AND THE TAIL SKID . LIGHTENING STRIKE INSP	ECTION CARRIED OUT BY MAINTENANCE IAW MM 5-50-31 AND THE FOLLOWING COMPONENTS FOUND DAMAGED AND REPLACED 1)- RADOME P/N 	4426X-2-10 S/N 0159 2)- STROBE LAMP ASSY. P/N 01-0770417-003- STATIC WICK.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004071200164	20040712	00164	NE  	2004	7	12	CA040427002      	2	20040416	G	7230		BLADE           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10423								(CAN) DURING BOROSCOPE INSPECTION, DAMAGE FOUND ON COMPRESSOR BLADES . MAUFACTURER WAS ADVISED AND GE ADVISED ENGINE REP	LACEMENT.  ENGINE REPLACED IAW MM PROCEDURE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071200165	20040712	00165	EA  	2004	7	12	CA040427003      	1	20040424	G	3230	5323300	PRIORITY VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF CREW SELECTED GEAR UP AND RECEIVED A (GEAR UP DISAGREE) MESSAGE WITH AMBER CAUTION MESSAGE ON THE R	T MAIN GEAR INDICATOR.  AFTER LANDING THE CREW RECEIVED HYD PUMP 3B (HIGH TEMP) MESSAGE .  A/C WAS RETURNED TO DEPARTURE	 AIRPORT. MAINTENANCE PERSONNEL REPLACED THE 3B HYD PUMP AND THE NOSE LANDING GEAR PRIORITY VALVE AND HYD FILTER AND CAR	RIED OUT SEVERAL GEAR RETRACTIONS AND FOUND IT SERVICEABLE A/C HOURS WERE 8810 AND 6799 CYCLES.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071200166	20040712	00166	NM  	2004	7	12	CA040427004      	1	20040422	G	5610	141T480150	WINDSHIELD      			BOEING	767   	767*        	       	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING CRUISE, FIRST OFFICER WINDSHIELD NON STRUCTURAL OUTER PANE SHATTERED. WINDSHIELD TOTAL TIME 9,854 HRS.  AIR	CRAFT TOTAL TIME  50,585 HRS.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2004071200167	20040712	00167	EA  	2004	7	12	CA040427006      	2	20040415	G	7421	REM37BY	SPARK PLUG      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING RUN UP ABNORMAL DROP. RT MAGNETO PROBLEM TRACED TO DEFECTIVE SPARK PLUG.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2004071200168	20040712	00168	EU  	2004	7	12	CA040427007      	1	20040415	G	3097		WIRE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					WINDSHIELD HEAT	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED LT SIDE WINDSHIELD HEAT C/B POPPING.  WINDSHIELD HEAT REGULATOR REPLACED.  FURTHER INVESTIGAT	ION REVEALED AN OPEN WIRE BETWEEN PIN J AND GROUND.  FOUND THE ELECTRICAL RETRACTABLE CORD DAMAGE BELOW THE SLIDING WIND	OW. CORD ASSEMBLY WAS REPLACED. THE MAINTENANCE PROGRAM WAS REVISED TO CARRY INSPECTION OF THE RETRACTABLE CORD ON REGUL	AR BASIS.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA
2004071200177	20040712	00177	EA  	2004	7	12	CA040427008      	2	20040407	G	7421	REM37BY	SPARK PLUG      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CONTAMINATED    	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF, PILOT NOTICED ROUGH RUNNING ENGINE AND POWER LOSS. THREE OF THE FOUR LOWER SPARK PLUGS WHERE LEAD 	CONTAMINATED.   NR 2 SPARK PLUG ELECTRODES WERE (WELDED) OVER WITH LEAD.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2004071200188	20040712	00188	WP  	2004	7	12	CA040427009      	1	20040425	G	2910	S305201	COUPLING        			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B    	 	NE  					HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI TO THE GATE, THE HYD SYS STARTED TO DECREASE RAPIDLY. QRH WAS PERFORMED BY THE CREW. HYDRAULIC LEAK WA	S FOUND AT NR 3 PYLON REAR SPAR AREA.  FOUND CONNECTION WING O-FLEX  COUPLING CRACKED ON SYSTEM D SUCTION LINE FOR EDP. 	NO OBVIOUS DAMAGE WAS FOUND ON TUBE AND FLANGE, AND COUPLING WAS REPLACED.  SUSPECT THE COUPLING WAS DAMAGE BY VIBRATION	 SINCE THE TUBE CLAMP AND HARDWARE WERE FOUND NOT PROPERLY SECURE.  CLAMP AND HARDWARE REPOSITIONED AND SECURED CORRECTL	Y.		2	L	7	3 	4F	4	F	 	A23WE   	E12EU
2004071200189	20040712	00189	GL  	2004	7	12	CA040427010      	1	20040406	G	1430		SCREW           	PARKERHANFIN		BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A110	 	NE  					PITCH TRIM ACT	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0021					(CAN) DURING INCORPORATION OF SERVICE BULLETIN THE SERVICE CENTER TECHNICIAN FOUND GALLING ON THE ACME SCREW AND A SMALL	 PIECE OF THE SCREW THREAD WAS MISSING. THE PITCH TRIM ACTUATOR WAS REMOVED FROM THE AIRCRAFT AND SHIPPED TO THE VENDOR 	FOR INVESTIGATION. NEW UNIT INSTALLED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	T00003NY	E00057EN
2004071200190	20040712	00190	CE  	2004	7	12	CA040427011      	1	20040112	G	3260		SWITCH          			BEECH 	17    	D17S        	1150538	CE  	PWA   	R985  	R985AN1     	52008	NE  					LT MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) LT MAIN LDG GEAR (DOWN) SWITCH OUT OF ADJUSTMENT CAUSING (NOT LOCKED DOWN) INDICATION.   SWITCH READJUSTED, GEAR S	WINGS COMPLETED WITH ALL OPERATIONS AND INDICATIONS NORMAL.					1	Q	7	1 	3R	3	R	 	A649    	5E1
2004071200191	20040712	00191	EA  	2004	7	12	CA040427012      	2	20040426	G	7200		ENGINE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								50326			(CAN) IN CRUISE FLIGHT THE PILOT HEARD A BANG AND THE RT ENGINE STOPPED TURNING.  THE PROP WAS FEATHERED AND THE AIRCRAF	T LANDED WITHOUT INCIDENT. AFTER LANDING, THE PROPELLER COULD NOT BE TURNED BY HAND.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2004071200192	20040712	00192	SW  	2004	7	12	CA040427013      	1	20040312	G	6320	269A510351	SHAFT           			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					M/R GEARBOX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						50603					(CAN) BEARING SIZE DUE TO LACK OF LUBRICATION.  DUE TO INCORRECT INSTALLATION AT REPAIR.						1	G	7	1 	3O	3	O	O	4H12    	E286
2004071200193	20040712	00193	GL  	2004	7	12	CA040427014      	2	20040414	G	7261	9A1424	COUPLING        			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					OIL PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION, SPLINE/COUPLING P/N 9A1424 WAS FOUND WORN.  REMOVED OIL PUMP AND TACH GENERATOR AND MATING COUPLI	NG P/N 9A1424 FOR INSPECTION AND REPAIR.  REPLAC ED WITH NEW GLOBE TACH GEN P/N 22A650 S/N 6209 AND OHC OIL PUMP P/N 206	-140-190-005 S/N SPF82 AS REPLACEMENT OF SPLINE REQUIRES REPLACEMENT OF ALL MATING SURFACES.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004071200194	20040712	00194	SW  	2004	7	12	CA040427015      	1	20040416	G	7120	206032303014	MOUNT           			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CLIP AND FITTING AT RT ENGINE MOUNT LOCATION HAS CRACK DAMAGE. REMOVED CLIP P/N 206-032-303-014 AND FITTING P/N 20	6-031-337-004 AND REPLACED WITH NEW CLIP P/N 206-032-303-230S AND NEW FITTING P/N 206-033-670-104S. RT ENGINE PAN UPPER 	LONGERON FOUND TO HAVE INTER GRANULAR CORROSION.  REMOVED AND ARE PLACED WITH NEW LONGERON P/N 206-031-314-125S. REPAIRS	 CARRIED OUT AMO 100/94 UNDER WORK ORDER NR 24122. APRIL 16, 2004.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004071200195	20040712	00195	SO  	2004	7	12	CA040427016      	1	20040424	G	2400	688219	MASTER SWITCH   			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	WORN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) NEARING FINAL APPROACH THE PILOT NOTICED HE HAD LOST PRIMARY AVIONICS POWER AND THE STANDBY POWER SUPPLY HAD ENGAG	ED TO PROVIDE BASIC POWER. AN UNEVENTFUL LANDING WAS CARRIED OUT. MAINTENANCE DETERMINED THE AVIONICS MASTER SWITCH (PUS	H TO ENGAGE, PUSH AGAIN TO DISENGAGE) HAD DISENGAGED TO THE (OFF) POSITION BY ITSELF. THE INTERNAL LATCHING MECHANISM IS	 NOT VISIBLE FOR INSPECTION AND THE SWITCH IS IN THE PROCESS OF BEING REPLACED.			1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA
2004071200203	20040712	00203	GL  	2004	7	12	CA040427017      	1	20040420	G	3242	201095001	TRANSDUCER      			BOMBDR	BD700 	BD7001A10   	1390006	GL  										BRAKE PEDAL	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						615159					(CAN) AFTER LANDING, DURING ROLL OUT AND TAXI, THE PILOT REPORTED THAT HIS LT BRAKE PEDAL WAS GRINDING AND WOULD NOT SPR	ING BACK UNLESS HE TAPPED IT AND QUICKLY RELEASED THE PEDAL.   ALSO, THE AIRCRAFT PULLED SLIGHTLY TO THE LT WHILE THE PE	DAL WAS STUCK. THE LT BRAKE PEDAL TRANSDUCER (LVDT) WAS REPLACED AND TESTED IAW AIRCRAFT MM.  THE AIRCRAFT WAS RETUNED I	N SERVICE WITH NO FURTHER EVENT.			2	L	7	2 	4F			RT	T00003NY
2004071200210	20040712	00210	CE  	2004	7	12	CA040427018      	1	20040427	G	5510	053200199	RIB             			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF HORIZONTAL STABILIZER ATTACH BOLT HOLES INSPECTION IAW MFG SB04-55-01, FOUND RT AFTER ATTACHM	ENT HOLE ON THE RIB HAS TWO .0937 INCH LONG CRACKS.  THE CRACKS ARE HIDDEN UNDER THE MOUNTING WASHER.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2004071200211	20040712	00211	SW  	2004	7	12	CA040428001      	1	20040427	G	5410	212060822001	ACCESS DOOR     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE DAILY INSPECTION THE COWL INSPECTION DOOR HINGE WAS FOUND LOOSE ALLOWING THE DOOR TO HANG DOWN. UPON RE	MOVAL OF THE COWLING IT WAS FOUND THAT THE ATTACH FLANGE FOR THE COWL ACCESS DOOR HINGE WAS CRACKED ACROSS 75 PERCENT OF	 THE FLANGE LENGTH.  THE DOOR WAS REMOVED AND THE FLANGE REPAIRED.  IF THE CRACK HAD EVENTUALLY CROSSED THE FLANGE THE D	OOR COULD HAVE FALLEN UPON THE MAIN DRIVESHAFT SHAFT,  WHICH ROTATES AT 6600 RPM DURING FLIGHT. THERE WAS POTENTIAL FOR 	SERIOUS DAMAGE.		1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004072900076	20040729	00076	EA  	2004	7	29	CA040428002      	1	20040427	G	5750	6001038841	FAIRING         			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF343B1     	 	NE  					WX RADAR	LIGHTNING STRIKE	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) LIGHTNING STIKE ON APPROACH INTO AIRPORT. LIGHTNING ENTERED LT SIDE OF WEATHER RADAR.  NO OBVIOUS EFFECT TO AIRCRA	FT SYSTEM					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071300001	20040713	00001	CE  	2004	7	13	CA040428003      	1	20040419	G	7810	FA572618R	EXHAUST STACK   			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	LT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION A CRACK WAS NOTED AT THE LIP HEAT WELD TO THE FORWARD SECTION OF THE EXHAUST STACK.  EXH	AUST UNIT WAS ORDERED AND INSTALLED WITHOUT ANY INCIDENT.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004071300002	20040713	00002		2004	7	13	CA040428004      	4	20040419	G	2562	AK450	ELT             			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					CABIN	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UPON ANNUAL RE-INSPECTION FOR RE-CERTIFICATION PURPOSES, AVIOINICS SHOP REPORTED ELT S/N 353494 FAILS TEST PROBABL	Y DUE TO A BAD CRYSTAL. UPON BEING ADVISED THAT A COMPANY DOES NOT SUPPLY PARTS, OPERATOR PURCHASED AND INSTALLED A NEW 	ELT ONTHE AIRCRAFT.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004071900015	20040719	00015	EA  	2004	7	19	CA040428005      	2	20040415	G	7421	REM37BY	SPARK PLUG      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING RUN UP,  ABNORMAL DROP IN RT MAGNETO NOTED.  PROBLEM TRACED TO FAULTY SPARK PLUG. TIME IN SERVICE 1 HOUR.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2004120600072	20041206	00072	CE  	2004	12	6	CA040428006      	1	20040428	G	2710		AILERON         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					WINGS	OUT OF RIG      	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											DURING TROUBLESHOOTING OF A PILOT REPORTED SNAG, THE CONTROL COLUMN IS BANKED SLIGHTLY TO THE LEFT IN ORDER FOR THE AIRC	RAFT TO FLIGHT STRAIGHT AND LEVEL, CHECKED THE AILERON RIGGING AND FOUND THAT IF THE PROCEDURES FROM THE MM ARE FOLLOWED	 THE AIRCRAFT WILL BE INCORRECTLY RIGGED AND THE RESULTS WOULD BE THE SAME AS THE REPORTED SNAG.  THE PROBLEM IS THAT RA	YTHEON HAS ISSUED A MANDATORY SERVICE BULLETIN (SB 27-3459) DELETING WITH THE GUST LOCK INSPECTION/REPLACEMENT.  IN THIS	 SB WE ARE REQUIRED TO COMPLY WITH SERVICE INSTRUCTION NO 0887-155. THIS SI REQUIRES THE REPOSITION THE LOCK PIN HOLE IN	 THE FLIGHT CONTROL COLUMN RESULTING WITH THE COLUMN BANKED 15 DEGREES WHEN THE PIN IS INSTALLED.	1	L	7	2 	3T	4	T		A14CE   	E4EA
2004071900039	20040719	00039	GL  	2004	7	19	CA040428007      	2	20040428	G	7250		TURBINE         			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	T	J	ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   	WARNING INDICATION        	CR	CRUISE         	1			CA								CAE295208			(CAN) THIS MORNING THE PILOT WAS IN CRUISE WHEN A LOUD BANG OCCURRED AND THE TOT INCREASED.   WITH NO ENGINE, THE PILOT 	AUTOROTATED TO A CLEAR SPOT TO THE GROUND.  NO DAMAGE TO AIRCRAFT.  THE ENGINE HAD FAILED.  A VISUAL OF THE TURBINE SECT	ION SHOWS SUBSTANTIAL DAMAGE.  AT THIS TIME UNKNOWN SOURCE OF WHAT CAUSED THIS DAMAGE.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004071900040	20040719	00040	GL  	2004	7	19	CA040429001      	3	20040427	G	6140		WIRE            			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	BETA SWITCH	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE RT ENGINE BETA LIGHT ILLUMINATED. ALL PROPELLER AND ENGINE PERFORMANCE WAS NORMAL. THE FLIGHT C	REW SHUT DOWN THE AFFECTED ENGINE AND FEATHERED THE PROPELLER AS A PRECAUTION. THE AIRCRAFT RETURNED TO THE AIRPORT.  UP	ON INVESTIGATION, MAINTENANCE DISCOVERED THE FAULT WAS WITH THE BETA LIGHT SWITCH WIRE. THE WIRE WAS REPAIRED AND THE SY	STEM FUNCTION CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA
2004071900041	20040719	00041	EA  	2004	7	19	CA040429002      	1	20040429	G	5210	2R595730011	CABLE           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BROKEN STRANDS ON MAIN ENTRANCE DOOR ASSIST CABLE AT THE POINT WHERE THE CABLE STARTS TO OVERLAP  ITSELF ON THE DO	OR ACTUATOR SERVO DRUM FOR THR FIRST TIME.  CABLE REPLACED. IPC REFERENCE : CRJIPC MANUAL CHAPTER 52-11-08, FIGURE 1A , 	ITEM 45. NOTE:  THE CABLE HAD BEEN REPLACED ON PREVIOUS AIRCRAFTS THAT HAS COME THROUGH C-CHECK INSPECTIONS. THE DAMAGE 	TO THIS CABLE HAS BEEN IN THE SAME AREA EVERYTIME.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071900042	20040719	00042	WP  	2004	7	19	CA040429003      	1	20040427	G	3260	833703	PROXIMITY SENSOR			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RT MLG	OUT OF TOLERANCE	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) RT MAIN LANDING GEAR LIGHT (RED) WAS ILLUMINATED WHEN GEAR SELECTED DOWN. VISUAL CHECK CONFIRMED GEAR DOWN AND LOC	KED.  MAINTENANCE FOUND DOWN LOCK PROX SENSOR OUT OF TOLERANCE.  PROX SENSOR REPLACED AND TESTED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004071900043	20040719	00043	NE  	2004	7	19	CA040429004      	2	20040428	G	7261		STRAINER        			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RT ENGINE OIL	CLOGGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) RT ENGINE OIL STRAINER CLOG LIGHT ILLUMINATED IN FLIGHT.  PRECAUTIONARY ENGINE SHUTDOWN IN FLIGHT.  RT ENGINE OIL 	STRAINER FOUND WITH CARBON PARTICLES, FILTER CLEANED AND REINSTALLED. ENGINE RUN-UP CARRIED OUT AND ENGINE RELEASE SERVI	CEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004071900044	20040719	00044	EA  	2004	7	19	CA040429005      	2	20040407	G	8550	75528	FILTER ADAPTER  			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE OIL	MALFUNCTIONED   	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE THE OIL TEMPERATURE CLIMB INTO THE RED ZONE. THE THERMOSTATIC VALVE WAS REPLACED AND A TEST FLIGHT WAS C	ARRIED OUT WITH THE ENGINE STILL OVERHEATING. WE REPLACED THE OIL FILTER ADAPTER P/N 75528 AND THE OIL SCREEN HOUSING P/	N 69510 AND EVERYTHING RETURNED TO NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	E274
2004071900062	20040719	00062	GL  	2004	7	19	CA040429006      	3	20040429	G	6110	1C160DTM755	PROPELLER       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  		CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WAS RECIEVED FOR 5 YR. CORROSION IAW CAR 625, APPENDIX C, PARAGRAPH 5. PROPELLER SPACER WAS VERY DIFFICU	LT TO REMOVE. UPON VISUAL INSPECTION OF SPACER DOWEL HOLES IT WAS FOUND THAT THEY WERE CORRODED BEYOND REPAIR RENDERING 	THE PROPELLER UNSERVICEABLE. THIS PROPELLER HAD BEEN PREVIOUSLY INSPECTED ON JULY 10/96 MAKING IT 3 YEARS OVER DUE FOR S	ERVICE.  IF THE MAINTENANCE SCHEDULE SET OUT IN THE CARS HAD BEEN FOLLOWED, THIS PROPELLER MAY HAVE BEEN REPAIRED AND RE	TURNED TO SERVICE.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004071900088	20040719	00088	CE  	2004	7	19	CA040429007      	1	20040408	G	2916	231707510	RESERVOIR       			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, FLUID LEAK WAS FOUND AROUND FILLER AREA. EDDY CURRENT INSPECTION CONFIRMED A 1INCH CRACK IN THE	 WELD AT FILLER NECK. CRACK WAS WELD REPAIRED IAW MFG INSTRUCTIONS, PENETRANT INSPECTED AND RESERVOIR PROOF PRESSURE TES	TED D TO 30 PSI.				2	L	7	2 	4F	4	F	 	A10CE   	E6WE
2004071900089	20040719	00089	CE  	2004	7	19	CA040429008      	1	20040415	G	3244	0283353	TIRE            			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	MLG	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MECHANIC NOTICED THAT TIRE SIDEWALL HAD RUBBED AGAINST BRAKE HOUSING, CREATING A GROOVE IN THE RUBBER. THERE WAS S	TATIC CLEARANCE BUT WHEN THE TIRE FLEXED ON LANDING IT COULD RUB AGAINST THE BRAKE HOUSING. CLEVELAND WHEELS AND BRAKES 	HAD BEEN INSTALLED IN AUGUST OF 1996 IAW STC SA646GL, OVERSIZE TIRES INSTALLED IAW CAT STC SA00185LA IN JANUARY OF 1997.	 THERE HAD BEEN NO PROBLEMS NOTED UNTIL RECENTLY. ALL CORRECT PARTS WERE IN PLACE. OTHER THREE TIRES WERE ALSO RUBBING, 	SOME WORSE THAN OTHERS. A SECOND COMPANY B100 ALSO HAD THE PROBLEM. REVERTED TO ORIGINAL SMALLER TIRES TO ALLEVIATE THE 	PROBLEM. MFG MAY HAVE CHANGED PROFILE OF TIRE AND THIS HAS CREATED PROBLEM BUT CANNOT CONFIRM THIS.	1	L	7	2 	4T	4	T	 	A14CE   	E2WE	6	C	P40EA
2004071900090	20040719	00090	EU  	2004	7	19	CA040429009      	1	20040427	G	5230		HINGE           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	CARGO DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON OPENING FORWARD BAGGAGE DOOR TO UNLOAD BAGS THE UPPER FORWARD DOOR HINGE BROKE AWAY FROM THE FUSELAGE. THE A/	C WAS THEN SHUTDOWN AND OFFLOADED. SCREWS ATTACHING HINGE TO FUSELAGE BROKE. SCREW PN 6DSS4910 HINGE (UPPER) PN 2D12172H	INGE (LOWER) PN 2D13024PIN PN 4D11535 CORRECT SCREWS WERE INSTALLED.				2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899
2004072100066	20040721	00066	GL  	2004	7	21	CA040429010      	3	20040429	G	6114		HUB             			CESSNA	170   	170A        	2072304	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									76822		(CAN) UPON INSPECTION SEVERE CORROSION IN HUB CAVITY AND IN MOUNTING BORE. DIMENSIONS AT MINIMUM BEFORE REWORK. PROPELLE	R IS UNSERVICEABLE.					1	H	7	1 	3O	3	O	 	A799    	E253	5	N	P910
2004072100067	20040721	00067	NM  	2004	7	21	CA040430001      	1	20040426	G	5711	13017R	RIB             			UNIVAR	415   	415CD       	0420304	NM  	CONT  	C85   	C8512F      	17008	SO  	MCAULY	1B90	1B90CM      	GL  	CENTER WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION TO COMPLY WITH AD 2003-21-01 SEVERE CORROSION FOUND ON FORWARD END OF RIB, AFT OF REAR SPAR, IN 	THE RT CENTER SECTION, BETWEEN THE FUSELAGE AND WING. THE CORROSION WAS NOT READILY NOTICEABLE UNTIL INSTALLATION OF INS	PECTION PANELS SK 80-2 IAW SB 31 REV 1. THIS ALLOWED ACCESS TO THIS AREA WHICH OTHERWISE IS HARD TO SEE, EVEN THOUGH THE	 WINGS WERE REMOVED TO COMPLY WITH THE INSPECTION REQUIREMENTS OF 2003-21-01.			1	L	7	1 	3O	3	O	 	A718    	E233	5	N	P842
2004072100068	20040721	00068	WP  	2004	7	21	CA040430002      	2	20040425	G	7314	30607591	PUMP            			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE7314R    	01518	WP  					FUEL SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) RT ENGINE FUEL FILTER BY-PASS LIGHT FLICKERING AT TAKE-OFF CLIMB POWER SETTINGS. AIRCRAFT RETURN TO MAINTENANCE BA	SE, MAINTENANCE TECHNICIAN FOUND FUEL FILTER CONTAMINATED BY A LOTS OF FINE GREY SEDIMENT. IT WAS DETERMINED THAT THE EN	GINE DRIVEN MOTIVE FLOW PUMP WAS DEFECTIVE. THE PUMP WAS REPLACED AS WELL AS THE FUEL FILTER, FUEL CONTROL UNIT, FLOW DI	VIDER AND FUEL MANIFOLD NOZZLES.  AIRCARFT RETURN TO SERVICE.			2	L	7	2 	4F	4	F	RT	A16NM   	E6WE
2004072100069	20040721	00069	EA  	2004	7	21	CA040430003      	3	20040430	G	6114		HUB             			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER RECEIVED FOR 5 YR. CORROSION INSPECTION IAW CAR 625, APPENDIX C, PARA. 5.  UPON VISUAL INSPECTION OF THE	 HUB, CORROSION WAS FOUND IN ONE OF THE PROP BOLT HOLES. THE MANUFACTURER HAS BEEN CONTACTED TO SUPPLY MINIMUM SPEC'S FO	R THIS AREA.  NOT ENOUGH MATERIAL REMAINS TO REMOVE CORROSION DAMAGE.  PROPELLER IS UNSERVICEABLE.				1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004072100070	20040721	00070	SO  	2004	7	21	CA040430004      	1	20040426	G	2420	2642997	ALTERNATOR      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) AFTER OVERHAUL WAS CONDUCTED, BEARINGS REF X-4130 AND X-4612 WERE NON-APPROVED PARTS.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004080500061	20040805	00061	EU  	2004	8	5	CA040430005      	1	20040417	G	3246	AHA1483	WHEEL           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINEERS RETURNING TO HANGAR FROM LINE, CAME UPON A PIECE OF DEBRIS ON APRON TO HANGAR. THEY RETRIEVED THE OBJECT	 AND FOUND THAT IT WAS A 10-INCH SECTION OF A WHEEL BEAD FLANGE.  AC HAD BEEN OUT FOR ENGINE RUNS AFTER AN ENGINE CHANGE	 AND WAS IN THE HANGAR, IT WAS CHECKED AND FOUND TO HAVE A SECTION OF THE NR 2 MAIN WHEEL P/N AHA1489 OB FLANGE MISSING.	 THE OUTER WHEEL HALF P/N AHA1483 IS FOUND IN THE MFG CMM IPL 32-42-59 FIG NR 1 ITEM NR 160.  THIS WHEEL WAS ON BUILD 17	 AND HAD BEEN NDT AT THAT TIME WITH NO DEFECTS NOTED AT THE TIME. THE WHEEL WAS REPLACED AND THE WHEEL HALF HAS BEEN SEN	T TO MFG FOR ANAYLSIS.  WE WILL FOLLOW-UP ON THE INCIDENT ONCE WE HEAR BACK FROM THE MANUFACTURER WITH THEIR FINDINGS.	2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004080500062	20040805	00062		2004	8	5	CA040430006      	4	20040427	G	6122	321475	SOLENOID        	WOODWARD    		CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	PROP GOVERNOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						121286					(CAN) DURING A TEST FLIGHT THE RT ENGINE WAS SHUT DOWN AND THE PROP FEATHERED AS PART OF THE TEST FLIGHT PROCEDURE. THE 	FLIGHT CREW WAS UNABLE TO UNFEATHER THE PROPELLER. THE AIRCRAFT RETURNED TO THE AIRPORT AND LANDED SAFELY. UPON INVESTIG	ATION BY MAINTENANCE THE FEATHERING SOLENOID ON THE PROP GOVERNOR WAS FOUND TOBE AT FAULT. THE SOLENOID WAS REPLACED AND	 THE SYSTEM FUNCTION CHECKED SERVICEABLE.			2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2004080500063	20040805	00063	CE  	2004	8	5	CA040503001      	1	20040429	G	2823	1013890253	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYSTEM	FAILED          	W				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			CA											(CAN) DURING PILOTS PREFLIGHT CHECK THE RT FUEL SHUTOFF VALVE FAILED.   THE VALVE WAS REPLACED. TSO 75.4 HOURS						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004080500064	20040805	00064	CE  	2004	8	5	CA040503002      	1	20040408	G	3233	508202085	ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING OF A LANDING GEAR PROBLEM WE NOTICED THAT THE NUT ASSEMBLY IN THE NOSE GEAR ACTUATOR COULD 	MOVE A SMALL AMOUNT FROM SIDE TO SIDE PLAY IN THE HOUSING. THE ACTUATOR WAS REMOVED AND WE NOTICED THAT THE MECHANISM WA	S A LITTLE ROUGH WHEN TURNED BY HAND. THE ACTUATOR WAS RETURNED TO THE OVERHAUL SHOP FOR FURTHER INVESTIGATION. THE OVER	HAUL SHOP HAS RESPONDED: UNIT FAILED THE END PLAY TEST AND SCREW/NUT ASSEMBLY SEEMED TO HAVE SOME SIDE TO SIDE PLAY. DIS	ASSEMBLED, INSPECTED, NDT, ECT FOUND: SCREW ASSEMBLY / NUT ASSEMBLY OUT-OF-LIMITS. HOUSING HAS DEEP CORROSION PITTING IN	 BOLT HOLE BOSS .THIS ACTUATOR WAS OVERHAULED IN APRIL 2003 AND ONLY HAD 819 CYCLES SINCE THEN.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004080500065	20040805	00065	EU  	2004	8	5	CA040503003      	1	20040415	G	6210	355A11003000	BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BLADE RETURNED FOR EVALUATION. AT STA 760 MM, AT ROOT END, AN AREA OF SKIN (150 MM LONG BY 2 MM WIDE) WAS MISSING 	FROM THE ROOT MATING FACE.  THIS APPEARS TO BE A MANUFACTURING DEFECT AND HAS BEEN RETURNED TO THE MANUFACTURER FOR EVAL	UATION/REPAIR.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005011300007	20050113	00007	CE  	2005	1	13	CA040503005      	1	20040315	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) ON ROUTINE TIRE CHANGE, NDT INSPECTION REVEALED A CRACK IN THE FLANGE OF THE WHEEL HALF.   WHEEL HALF REMOVED FROM	 SERVICE.					2	L	7	2 	4F	4	F		A10CE   	E6WE
2005011300008	20050113	00008	NM  	2005	1	13	CA040503006      	1	20040430	G	3242	BACB30MT9T15	PIN             			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					BRAKE ASSY	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING  C-CHECK NR 4 BRAKE ASSEMBLY LOCATOR PIN FOUND SHEARED.  PIN REPLACED.  AREA CHECKED AND NO OTHER FAULTS FO	UND. TIMES 58561:01CYCLES 54866.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005011300009	20050113	00009	EU  	2005	1	13	CA040503007      	1	20040430	G	5270		SWITCH          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	MAIN DOOR	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE CREW OBSERVED A DOOR WARNING INDICATION AFTER T/O.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHE	R INCIDENT.  MAINTENACE DETERMINED THE CREW/FREIGHT DOOR WARNING SWITCH TO BE AT FAULT.  THE MICROSWITCH AND PLUNGER WER	E REPLACED, AIRCRAFT TEST FLOWN AND RETURNED TO SERVICE.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005011300010	20050113	00010	SW  	2005	1	13	CA040503010      	1	20040530	G	2910	2781032081	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	BURST           	W				A				UNSCHED LANDING         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED AIRPORT AND SHORTLY AFTER BOTH HYDRAULIC ANNUNCIATOR LIGHTS CAME ON INDICATING LOW HYDRAULIC PRE	SSURE.  AIRCRAFT RETURNED TO ALTERNATE AIRPORT DUE TO WEATHER AT ORIGINAL AIRPORT AND LANDED WITHOUT INCIDENT.  INVESTIG	ATION FOUND THAT THE HYDRAULIC LINE HAD BURST UNDER THE PILOTS FLOOR PANEL.  LINE REPLACED ALONG WITH BOTH HYDRAULIC PUM	PS DUE TO CAVITATION REQUIREMENTS.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2005011300011	20050113	00011	NE  	2005	1	13	CA040503011      	2	20040430	G	7320	8062549	GOVERNOR        			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					FUEL FLOW	INOPERATIVE     	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) LT ENG VALVE LIGHT ILLUMINATED AND EICAS MSG L ENG FUEL VAL DISPLAYED WITH FUEL CONDITION SWITCH IN RUN.  NO FUEL 	FLOW INDICATED.   LT ENG FFG REPLACED C/O IAW AMM 73-21-01. TEST 1, 2, 9 AND 10 CARRIED OUT SATIFACTORY.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2005012400036	20050124	00036	CE  	2005	1	24	CA040503012      	1	20040428	G	5523		TAB             			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING CAP INSPECTION, EXAMINATION OF ELEVATOR T/E AND TRIM TAB FOR CORROSION, DELAMINATION OF FOAM STRU	CTURE, IT WAS DISCOVERED THAT ASSEMBLIES HAD NO FOAM INSIDE. PROPER SKINS WERE THEN ORDERED. UPON THEIR DELIVERY, THEY W	ERE ALSO FOUND NOT TO HAVE ANY FOAM INSIDE THEM. NO INFO WAS AVAILABLE.  ALL SIGNS POINTED TO BOGUS PARTS, WE CALLED MFG	 TECH AND WERE TOLD TO CALL DEALER BECAUSE THEY KNEW NOTHING ABOUT SUBJECT.  DEALER WAS ABLE TO FIND OUT (AFTER SEVERAL 	CALLS) THIS IS A RESULT OF PRODUCT IMPROVEMENT THAT MFG CAME OUT WITH.  IT IS NOT MENTIONED IN ANY MANUAL OR INSPECTION 	CRITERIA THAT THERE CAN BE NON-FOAM FILLED ASSEMBLIES INSTALLED.	1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P47GL
2005012400037	20050124	00037	NE  	2005	1	24	CA040503013      	2	20040429	G	8530		VALVE           	PWA         		CURTIS	C46   	C46DCURTIS  	2622704	SO  	PWA   	R2800 	R280051M1   	52026	NE  	HAMSTD	23E	23E50       	NE  		INOPERATIVE     	W				A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, RT ENGINE STARTED TO BACKFIRE, THE CREW LANDED AND RETURNED TO HANGER WITHOUT INCIDENT.						2	L	7	2 	4R	4	R		3A2     	5E8	6	C	P603
2005012400038	20050124	00038	EU  	2005	1	24	CA040504001      	1	20040430	G	6720	332A27233006	ADJUSTER        			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					PEDAL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT REPORTED PEDAL ADJUSTER JAMMED, AFTER INSPECTION THE SUPPORT WAS FOUND TO BE CRACKED.  AIRCRAFT IS IN NOR	WAY FOR A G-CHECK INSPECTION AND WAS ALSO CHECKED FOR THIS PROBLEM , AND WAS FOUND TO ALSO HAVE A CRACK IN THE SAME AREA	.  FLEET INSPECTION OF THE AIRCRAFT AT BASE RESULTED IN NO DEFECTS FOUND.				2	G	7	2 	4U	4	U		H4EU    	E12NE
2005012400047	20050124	00047	CE  	2005	1	24	CA040504002      	1	20040504	G	2916	55171001	RESERVOIR       			CESSNA	501   	501         	2076603	CE  	PWA   	JD15  	JT15D1A     	 	NE  					BRAKE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC BRAKE RESERVOIR LEAKING.  CRACK WELDED AND RETURNED TO SERVICE.						1	L	7	2 	4F	4	F		A27CE   	E25EA
2005020100031	20050201	00031	CE  	2005	2	1	CA040504004      	1	20040429	G	5520	11552405813	SUPPORT BRACKET 			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEV BELLCRANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AIRCRAFT INSPECTION, IT WAS NOTED THE AFT RT ELEVATOR BELLCRANK SUPPORT BRACKET P/N 115-524058-13 WAS CRACK	ED. THE CRACK EXTENDED APPROX. 1.5 INCHES VERTICALLY AROUND THE BELLCRANK PIVOT BOLT ATTACHMENT.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
2005020100032	20050201	00032	NM  	2005	2	1	CA040504005      	1	20040503	G	2781	756158	SENSOR          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TORQUE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			34832								(CAN) ON CLIMB OUT THE FLAP DRIVE CAUTION LIGHT ILLUMINATED CONTINUOUSLY, AND WOULD NOT EXTINGUISH. TROUBLE SHOOTING BY 	MAINTENANCE SUSPECTED A INTERNAL SWITCH FAILURE OF THE TORQUE SENSOR. A TEAR DOWN REPORT FOR FURTHER DETAILS OF THE REAS	ON FOR FAILURE SO SOON AFTER LAST REPAIR HAS BEEN REQUESTED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080600050	20040806	00050	EU  	2004	8	6	CA040504006      	1	20040428	G	3397	LJILO38	WIRE            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					NAVIGATION LIGHT	SEVERED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROUTINE TROUBLESHOOTING FOR INOPERATIVE NAV LIGHT STARBOARD, DISCOVERED POSITIVE WIRE WAS SEVERED FROM CRIMPED PIN	 BY SLIGHTLY TUGGING ON WIRES FROM THE BACKSHELL.  SINCE NO ACCESS AVAILABLE TO REMOVE BROKEN OFF PIN OUT OF LAMP ASSEMB	LY, A NEW ASSEMBLY HAD TO BE INSTALLED.				1	G	7	1 	3U	3	U	 	H9EU    	E00054EN
2005022400010	20050224	00010	EU  	2005	2	24	CA040505001      	1	20040501	G	3246	AHA1481	WHEEL           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10960								A/C IN HEAVY MX IN YHZ AND HAD JUST BEEN TAKEN OFF THE JACKS WHEN ENGINEERS NOTED THAT NR 3 MAIN WHEEL WAS FLAT.  THE WH	EEL WAS REPLACED ALONG WITH ITS MATE AS PER COMPANY POLICY, THE WHEEL WAS ROUTED TO WHEEL/BRAKE SHOP AND WENT THROUGH A 	BUILD (22) INSPECTION. NDT FOUND THE INNER WHEEL HALF HAD CRACK EMANATING FROM ONE OF THE THREE-FUSE PLUGHOLE.THE INNER 	WHEEL HALF P/N AHA1481 IS FOUND IN THE DUNLOP CMM IPL 32-42-59 FIG 1 ITEM 280.THIS WHEEL WAS ON BUILD 21 AND HAD BEEN ND	T AT THAT TIME WITH NO DEFECTS NOTED AT THE TIME. THIS MATTER HAS BEEN BROUGHT TO THE ATTN OF THE MANUF AND WE HAVE ASKE	D WHAT HAS BEEN THE OCCURRENCE ON THIS TYPE OF FAILURE AND HAVE ASKED WHETHER OR NOT THEY WOULD LIKE TO SEE THE COMPONEN	2	H	7	4 	4F	4	F		A49EU   	E6NE
2004080600051	20040806	00051	CE  	2004	8	6	CA040505002      	1	20040428	G	3080	1013800153	HOSE            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					BRAKE DEICE	RUPTURED        	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) BRAKE DEICE HOSE RUPTURED AND CAUSED BLEED AIR FAILURE SYSTEM TO ACTIVATE LIGHT.  HOSE WAS REMOVED AND LINE CAPPED	, WARNING SYSTEM REPAIRED IAW MFG MM. CH 21 BRAKE HOSE ORDERED AND SYSTEM PLACARDED AND MADE INOPERATIVE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA
2004080600052	20040806	00052	CE  	2004	8	6	CA040505003      	1	20040427	G	5753		SKIN            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	LT TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SMALL CRACK WAS FOUND AT TRAILING EDGE OF THE LT FLAP.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004080600053	20040806	00053	NE  	2004	8	6	CA040505004      	2	20040430	G	7250	3020159	RETAINING RING  								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SHROUD	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HOT SECTION WAS GIVEN A SCHEDULED BORESCOPE INSPECTION.  CT SHROUD SEGMENTS HAD SHIFTED AXIALLY.  DISMANTLE SH	OWED THE RETAINING RING TO HAVE DISTORTED AND BECOME DISLOCATED.  THIS PROBLEM HAS BEEN DOCUMENTED ON OTHER ENGINES.  MF	G HAS ISSUED P/N 3110741-02 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVEN	T THE COLLAPSE OF THE RETAINING RING.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS SUCH AS THE 114A ENGIN	E MODEL TO ALLOW THE MORE ROBUST RETAINING RING TO BE USED.							3	T			E4EA
2004080600054	20040806	00054	NM  	2004	8	6	CA040505005      	1	20040503	G	3230	BACH8B04NN214T	HOSE            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON DEPARTURE THE NOSE GEAR FAILED TO RETRACT WHEN THE LANDING GEAR SELECTOR WAS MOVED TO THE UP POSITION.  RETURNE	D TO BLOCKS.  HOSE REPLACED WITH LOANER HOSE.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2005022400012	20050224	00012	CE  	2005	2	24	CA040506002      	1	20040419	G	3246	3665710	BAR             	EDOAIREXXXXX		CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C201    	GL  	FLOATS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A ROUTINE, CHANGE OVER FROM SKIS TO FLOATS, IT WAS DISCOVERED THAT THE FORWARD SPREADER BAR ASSEMBLY PART NUMBER 	36657-10 WAS BADLY CORRODED AND CRACKED.  THE SPREADER BAR ASSEMBLY WAS REMOVED FROM EDO 249-2870 FLOATS.  NEW PART NUMB	ER 26-32096 INSTALLED IN ACCORDANCE WITH STC SA00066SE AND INSTALLATION GUIDE FORAEROCET 26-32096 SPREADER BAR REPLACEME	NT DOCUMENTA-10013.			1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2005022400013	20050224	00013	CE  	2005	2	24	CA040506003      	1	20040206	G	3221	04425061	TORQUE LINK     			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17425								(CAN) DURING INSPECTION, IT WAS DISCOVERED THE UPPER TORQUE LINK PART NUMBER 0442506-1WAS CRACKED.  NEW PART WAS INSTALL	ED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857
2004101800108	20041018	00108	CE  	2004	10	18	CA040506004      	1	20040504	G	3242	10500900	RIVET           	CLEVELAND   	30162       	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	BRAKE PAD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1606					(CAN) DURING INSPECTION IT WAS NOTICED THAT ONE OF THE RIVETS THAT RETAIN THE BRAKE PAD ON TO THE BRAKE ASSEMBLY WAS BRO	KEN, THE BRAKE ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS IS THE THIRD OCCURRENCE IN THE LAST FEW 	MONTHS, (SDR 20030925005 AND 20040224003) ALL HAPPENED ON NEW BRAKE ASSEMBLIES SUPPLIED BY THE SAME MANUFACTURER.  SUSPE	CT THAT THEY MAY HAVE A BAD BATCH OF RIVETS, AS A PRECAUTION  WILL BE REPLACING THE RIVETS IN THE REMAINING BRAKE ASSEMB	LIES WITH S/N ABOVE 1500.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2005022400014	20050224	00014	EU  	2005	2	24	CA040506006      	1	20040501	G	3260	222D232M88051	SQUAT SWITCH    			DORNER	DO228 	DO228202    	2992030	EU  										NLG	INTERMITTENT    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA						I					AIRCRAFT DEPARTED AND LANDING GEAR WOULD NOT RETRACT.  NOSE WEIGHT SWITCH TESTED AND FOUND TO BE INTERMITTENT.  PART CHA	NGED OUR WITH SERVICABLE UNIT					2	H	7	2 	4T			RT	A16EU
2005022400015	20050224	00015	NE  	2005	2	24	CA040506007      	1	20040412	G	5300	PD6154407003	BUSHING         			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					PYLON	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ON INSTALLATION OF THE BUSHING, WHILE IT WAS BEING PRESSED INTO THE LUG OF THE PYLON, THE TOP OF THE BUSHING SHEARED OF 	THE BODY.  MARKS ON THE BUSHING SHOW A TWISTING ACTION AS THE BUSHING WAS BEING INSTALLED.  AN INDEPENDENT COMPANY, DID 	AN INSPECTION (REPORT ON FILE) ON THE FAILED PART AND COULD NOT FIND ANY MATERIAL OR MANUFACTURING DEFECTS AND FELT THAT	 THE FAILURE WAS 'IT IS PROBABLE THAT THE SUBJECT BUSHING FAILED AS A RESULT OF SOME ANOMALY IN THE INSTALLATION PROCEDU	RE' THIS IS THE FIRST FAILURE AF ANY KIND SINCE WE STARTED MANUFACTURING THESE BUSHINGS.		2	G	7	2 	4U	4	U		1H15    	1E3
2005022400016	20050224	00016		2005	2	24	CA040507001      	4	20040329	G	2215	6225027101	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	LYC   	O360  	O360A1A     	41514	EA  					PITCH CONTROL	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											CAPT REPORTED THE PITCH CONTROL STICKING ( HARD POINT FEELING ) AFTER AP DISCONNECTION.  CPT HAD TO PULL THE CONTROL COL	UMN TO RECOVER THE FLIGHT CONTROL.  PITCH SERVO ACTUATOR WAS REPLACED.					2	L	7	2 	4F	3	O	RT	A21EA   	E286
2005022400017	20050224	00017		2005	2	24	CA040507002      	4	20040423	G	2215	8220260001	SERVO           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ELEVATOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						254					DURING CRUISE FLIGHT, AP TRIM IS RWD POSTED ON AND OFF EVERY FEW SECONDS. AUTO-PILOT DISCONNECTED.  NOTICED THAT AILERON	 IS EXTREMELY HARD TO MOVE ALMOST BLOCKED.  IN DESCENT WITHOUT AUTO-PILOT, WE NOTICED THAT THE ELEVATOR ALSO COULD NOT B	E MOVED (FL310-300 / SAT -50 C).  AROUND FL290 AND AFTER APPLYING STRONG INPUT, THE AILERON CAME FREE WITH A JERK.  AROU	ND FL130 (TAT 0C), ELEVATOR FREE AGAIN.  APPROACH AND LANDING NORMAL.  AILERON AND ELEVATOR SERVO MOUNT CHANGED.  OPERAT	IONAL TESTS ON A/P SERVOS SUCCESSFULLY PERFORMED.  AILERON SERVO CYCLE 18126/ HOURS 23075 ELEVATOR SERVO CYCLE 19592/ HO	URS 24455.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005022400018	20050224	00018	EA  	2005	2	24	CA040507003      	1	20040430	G	3040		HEATER          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										WINDSHIELD	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											DURING CRUISE, SMOKE FROM LEFT WINDOW HEATER.  WHEN LT WINDSHIELD HEAT WAS TURNEDOFF, SMOKE STOP.  DIVERTED FLIGHT.  FOU	ND LOOSE SCREW AND DAMAGED TERMINAL LUG ON LEFT WINDSHIELD HEAT ELEMENT.  LUG REPLACED AND SCREW TIGHTENED.					2	L	7	2 	4F			RT	A21EA
2005022400019	20050224	00019	SW  	2005	2	24	CA040507004      	1	20040506	G	2910		TUBE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CHAFED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											AT FL 200 RT HYDRAULIC PRESSURE ANNUNCIATION WENT FROM INTERMITTENT TO CONTINUOUS.  ON LANDING FLAPS AND GEAR SELECTION 	RESULTED IN FURTHER LOSS OF HYDRAULIC PRESSURE AND THE LT HYDRAULIC ANNUNCIATOR ILLUMINATED AND FLAPS WERE SLOW TO EXTEN	D.  AUXILLIARY GEAR EXTENSION PROCEDURE WAS RUN AND THE GEAR LOCKED DOWN.  POST FLIGHT INSPECTION REVEALED HYDRAULIC OIL	 ON THE UNDER SIDE OF THE AIRCRAFT.  MAINTENANCE DISCOVERED A CHAFFED HOLE IN A HYDRAULIC SUPPLY LINE IN THE RT WING LEA	DING EDGE INBOARD OF THE NACELLE WHICH THEY REPLACED.  THE LEADING EDGE AREA IS CROWDED WITH MANY METAL LINES THAT CAN C	HAFE EACH OTHER.	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
2005022400020	20050224	00020	NM  	2005	2	24	CA040510001      	1	20040509	G	5542	85540001003	SKIN            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING ROUTINE MAINTENANCE WALKAROUND INSPECTION, A CRACK WAS DISCOVERED ON THE UPPER RT SKIN OF THE FORE RUDDER.  REPAI	R IS CURRENTLY BEING ACCOMPLISHED IAW BOMBARDIER RD8-55-335.  MORE INFORMATION WILL BE ADDED AS IT BECOMES AVAILABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005022400021	20050224	00021	EA  	2005	2	24	CA040510002      	1	20040503	G	5341	21531036212	FRAME           			CNDAIR	CL215 	CL2151A10   	1900320	EA  										WING TO BODY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE PERFORMING AD CF-1997-07R2 A CRACK WAS DISCOVERED BY EDDY CURRENT ABOUT ONE AND A HALF INCHES LONG ON THE OUTBOARD	 RT REAR WING TO FUSELAGE FRAME ANGLE.  THE CRACK BECAME VISUALLY APPARENT AFTER BEING DETECTED BY NDT.  THE CRACK START	ED AT THE TOP OF FRAME P/N 215-31036-212 AND EXTENDED PASS THE FIRST HIGH LOCK AND ON TOWARDS THE SECOND.  THE AD WAS PE	RFORMED AT AIRFRAME TIME 1984.2 AND TOTAL WATER DROPS 6843 WHICH IS PRIOR TO THE COMPLIANCE REQUIREMENTS OF AD CF-1997-0	7R.		2	H	7	2 	4R			RT	A14EA
2005022400022	20050224	00022	EA  	2005	2	24	CA040510003      	1	20040503	G	2720	215903812	CONTROL CABLE   			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	R2800*      	52026	NE  					RUDDER CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A STRUCTURAL REPAIR TO THE RT REAR WING-TO-FUSELAGE FRAME ANGLE A PANEL AT WS 60.80, ADJACENT TO REAR SPAR, HAD T	O BE DRILLED OFF TO FACILITATE THE REPAIR.  IT WAS AT THIS TIME CORROSION WAS DISCOVERED ON THE RUDDER/AILERON INTERCONN	ECT CABLE P/N 215-90381-2 WHICH LIES DIRECTLY UNDER THIS PANEL.  THE CORROSION WAS REMOVED AND UPON A CLOSER INSPECTION 	SEVERAL BROKEN STRANDS WERE NOTICED.  THE MM WAS CONSULTED AND IT WAS DETERMINED THAT THE CABLE WAS BEYOND LIMITS.  THE 	CABLE WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT AND THE WING PANEL WAS SEALED WITH AN APPROVED SEALANT.  ITS WORT	H NOTING THAT THE DAMAGE WOULD BE IMPOSSIBLE TO SPOT HAD IT NOT BEEN FOR THE REMOVAL OF THE RIVETED PANEL. THIS IS AN AR	2	H	7	2 	4R	4	R	RT	A14EA   	5E8
2005022400024	20050224	00024	NE  	2005	2	24	CA040510004      	2	20040507	G	7310	MS905820	RING            			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUEL FLOW TRANS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											HAVE HAD SEVERAL OCCURRENCES OF FUEL LEAKS FROM THE JT8D FUEL FLOW TRANSMITTERS. THE LEAKS ARE EVIDENT AT VERY HIGH POWE	R SETTINGS. A FLEET CAMPAIGN HAS BEEN COMPLETED WHICH CHECKED ALL ENGINES FOR LEAKS AND RECTIFIED DEFECTS.  AN EXTENSIVE	 INVESTIGATION IS BEING CONDUCTED BY OUR MAINTENANCE PROVIDER AND PRELIMINARY RESULTS SHOW THE CAUSE TO BE DEFECTIVE TEF	LON BACK-UP RINGS MS9058-20.  ALL STOCK OF THE SUSPECT PART HAS BEEN INSPECTED AND ANY DEFECTIVE BACK-UP RINGS FOUND HAV	E BEEN QUARANTINED.  OUR MAINTENANCE PROVIDER HAS CONTACTED THEIR SUPPLIER OF THE PART WITH THE FINDING.  ADDITIONALLY T	HEY ARE CHECKING FOR OTHER APPLICATIONS FOR THE PART WITHIN THEIR VARIOUS FLEETS.  A FULL REPORT WILL BE ISSUED AND I WI	2	L	7	2 	4F	4	F		A16WE   	E2EA
2005022400025	20050224	00025	EA  	2005	2	24	CA040510005      	1	20040506	G	5511	C2TP57	SPAR            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15271								THE TAILPLANE WAS BEING INSPECTED IAW CF 91-42 ADDITIONAL CRACK WAS DISCOVERED LEADING FROM A PREVOUSLEY CRACK THAT HAD 	BEEN STOP DRILLED.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
2005020100033	20050201	00033	CE  	2005	2	1	CA040510006      	1	20040506	G	5520	11561001S1	FITTING         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	ELEVATOR TORQUE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE INSPECTION THE TAIL CONE WAS BEING REINSTALLED WHEN A CRACK WAS NOTICED ON THE LT TORQUE TUBE.  THE	 CRACK EXTENDS FROM THE TAPER  PIN  HOLE TO THE EDGE OF THE FITTING. THESE FITTINGS ARE NDT EVERY 1000 HRS AND THIS TUBE	 WAS DONE AT 142.5 HRS.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE
2004062100123	20040621	00123	CE  	2004	6	21	CA040510007      	1	20040506	G	5310	50430043867	DOOR FRAME      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE INSPECTION A CRACK WAS FOUND ON THE CABIN DOOR FRAME, WHICH EXTENDED FROM THE CUT-OUT FOR THE UPPER	 FWD BAYONETTE TO THE BAYONETTE SUPPORT BRACKET SCREW HOLE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	3PNE
2004062100125	20040621	00125	EA  	2004	6	21	CA040511001      	1	20040509	G	3411		DRAIN           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PITOT TUBE	CONTAMINATED    	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) ON TAKE-OFF ROLL , THE PILOT NOTICED THAT STANDBY ALTIMETER-AIR SPEED INDICATOR NOT SHOWING ANY AIRSPEED THUS REJE	CTING TAKEOFF.  MAINTENANCE REPLACED THE INSTRUMENT AND NOTED THERE WAS EXCESSIVE AMOUNT OF MOISTURE DRAINED FROM THE PI	TOT DRAIN PLUG .				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004062100126	20040621	00126	CE  	2004	6	21	CA040511002      	1	20040510	G	3211	05411212	SUPPORT BRACKET 			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT MAIN LANDING GEAR OB SUPPORT BRACKET CRACKED AT U BOLT FORWARD HOLE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004062100127	20040621	00127	NE  	2004	6	21	CA040511003      	2	20040422	G	8530	399359	CASTING         	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	VALVE GUIDE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						PCCP2272					(CAN) THE ALUMINUM CASTING IN WHICH THE VALVE GUIDE SLIDES HAD DISINTEGRATED DUE TO CORROSION INSIDE THE EXHAUST PORT. I	T WAS PROBABLY A POOR QUALITY PART THAT WAS INSTALLED DURING THE LAST OVERHAUL.					1	H	7	1 	3R	3	R	 	A815    	E142	6	C	P719
2004062100128	20040621	00128	WP  	2004	6	21	CA040511004      	1	20040509	G	2781		WARNING LIGHT   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LE SLAT	ILLUMINATED     	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXING, DISAGREE AMBER LIGHT REMAINED ILLUMINATED WHEN SLATS RETRACT SELECTED.  AIRCRAFT  WAS FERRIED.  DUR	ING CLIMB OUT, SLAT DISAGREE LIGHT EXTINGUISHED APROX 13000 FT WHILE SLAT RETRACTED.  AT YUL, MAINTENANCE DID FUNCTIONAL	 CHECK IAW MM AND NO FAULT FOUND.  AIRCRAFT RELEASED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004062100129	20040621	00129	NE  	2004	6	21	CA040511005      	2	20040302	G	7230		ENGINE          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					LEFT	FOD             	W				A				UNSCHED LANDING         				C	B	J	F.O.D.                    	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA								UNJ73540			(CAN) AFTER TAKEOFF THE CREW REPORTED SMOKE IN THE CABIN. AN EMEREGENCY WAS DECLARED AND THE AIRCRAFT RETURNED TO BASE A	ND MADE AN UNEVENTFUL LANDING.  BOROSCOPE INSPECTION REVEALED FOD (FOD TYPE WAS NOT IDENTIFIED) FROM 1ST TO 7TH STAGE CO	MPRESSOR OF LT ENGINE.  ENGINE WAS REMOVED.  COMPRESSOR DAMAGE WAS REPAIRED,  ALSO REPLACED 9 BLADES OF 1ST STAGE HPT AN	D BOTH IGNITERS.  ENGINE RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004062100130	20040621	00130	EA  	2004	6	21	CA040511007      	2	20040510	G	7414	1068291013	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON LT ENGINE RUN UP, MAGNETO TEST FOUND RPM DROP BY 400 RPM.  DURING TROUBLESHOOTING FOUND FAULTY MAGNETO, REPAIRE	D ON MAY 3/ 2002, 460.1 HRS IN SERVICE SINCE REPAIR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004062100153	20040621	00153	CE  	2004	6	21	CA040512001      	1	20040330	G	2710	051010516	CONTROL CABLE   			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FRAYED AT PULLEY, PULLEY NOT SEIZED.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
2004070900089	20040709	00089	CE  	2004	7	9	CA040512002      	1	20040503	G	2710	051010513	CONTROL CABLE   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	AILERONS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FRAYED AT PULLEY WING ROOT, PULLEY NOT SEIZED.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA
2004070900090	20040709	00090	CE  	2004	7	9	CA040512003      	1	20040503	G	2710	051010516	CONTROL CABLE   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FRAYED AT WING ROOT PULLEY.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA
2004070900091	20040709	00091	SW  	2004	7	9	CA040512004      	1	20040512	G	6710	206001342001	CYCLIC STICK    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ROUTINE INSPECTION CYCLIC TUBE P/N 206-001-342-001 WAS FOUND CRACKED AT THE UPPER BOLT HOLE ON THE PILOTS S	IDE SLOT ATTACHMENT. THIS TUBE HAD ACCUMULATED408.7 HOURS SINCE ITS LAST INSPECTION MAY 20, 2003. THIS INSPECTION IS A 1	200 HOUR REQUIREMENT IAW MFG BHT-206-A/B SERIES MAINTENANCE MANUAL. WE HAVE RETAINED A COMPANY REQUIREMENT TO ALSO INSPE	CT THIS PART ANNUALLY. A SECOND CYCLIC TUBE P/N 206-001-342-001 REMOVED FROM AN AIRCRAFT ON OVERHAUL WAS ALSO FOUND CRAC	KED IN THE SAME AREA. THIS PART HAD ACCUMULATED 298 HOURS SINCE ITS LAST INSPECTION.  ASSB 206-85-29 AND BHT-206 A/B-SER	IES M/M BOTH REFERENCE THE INSPECTION REQUIREMENTS.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004070900092	20040709	00092	SW  	2004	7	9	CA040512005      	1	20040507	G	5711	1108111	SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  	SNSNCH	74D	74DM        	EA  	WING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON METAL-SPAR WINGS RETROFITTED TO THIS AC THE AFT SPARS HAVE THREE FOOT STIFFENERS RIVETED TO THEM AT AFT STRUT A	TTACH POINT. CLEARANCE BETWEEN FABRIC AND STIFFENER IS MINIMAL, AND INSPECTION HOLE COVER CLIPS CAN CONTACT STIFFENER AN	D CHAFE GROOVES INTO IT AS FABRIC DRUMS OR FLEXES IN FLIGHT, DEPENDING ON LOCATION OF INSPECTION HOLE AND ORIENTATION OF	 THE COVER.  TURBULENCE OFF STRUTS CREATES CONSIDERABLE FABRIC MOVEMENT IN THIS AREA. ON THIS PARTICULAR AC THE STIFFENE	RS WERE DAMAGED ENOUGH TO REQUIRE REPLACEMENT.  RECOMMEND USING A TWO-CLIP COVER AT THIS HOLE, RATHER THAN FOUR-CLIP TYP	E, AND ORIENTING CLIPS TO AVOID INTERFERENCE WITH SPAR. INDEXING AND LABELING OF COVER AND WING MIGHT BE ADVISABLE.	1	H	7	1 	3O	3	O	NC	A759    	E274	5	N	P88614
2004070900093	20040709	00093	EU  	2004	7	9	CA040512006      	1	20040510	G	2997	12TW13	SWITCH          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COLLECTIVE	FAILED          	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) AFTER START UP PILOT TESTED THE HYD SYSTEM IAW FLIGHT MANUAL AND HAD HYD FAIL LIGHT BUT NO  HORN. FLIGHT WAS ABORT	ED.  THE HYD CUTOFF SWITCH ON THE PILOTS COLLECTIVE WAS FOUND TO BE U/S.SWITCH CHANGED A/C RETURNED TO SERVICE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004070900094	20040709	00094	CE  	2004	7	9	CA040512007      	1	20040404	G	1430	NAS130436	BOLT            	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BELLCRANK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SERVICEABILITY CHECK, THE AME FOUND THE ELEVATOR SYSTEM SEEMED LOOSE. HE ALSO FOUND THAT HE COULD MOVE BOTH	 ELEVATORS IN THE OPPOSITE DIRECTION SLIGHTLY.  FURTHER TROUBLESHOOTING REVEALED THAT THE UPPER CONTROL TUBE TO BELL CRA	NK BOLT WAS INSUFFICIENTLY TORQUED AND THE BOLT WAS WORN.  THE BELL CRANK WAS ALSO WORN .003 ON ONE SIDE OF THE MOUNT HO	LE AND .007 ON THE OTHER.  THERE IS NO ALLOWABLE WEAR TOLERANCE GIVEN FOR THIS PART.  AN AIRCRAFT SERVICES CAMPAIGN NOTI	CE WAS ISSUED TO INSPECT THE REST OF THE FLEET.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2005050300200	20050503	00200	EU  	2005	5	3	CA040513001      	1	20040513	G	2700		UNKNOWN         			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  						UNKNOWN         	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) DURING A FULL THRUST TAKEOFF AT APPROX 100 KNTS IAS, ACFT SNAPPED TO THE LT REQUIRED ABRUPT RT RUDDER.   AGAIN AT 	APPROX 130 KNTS IAS, ACFT VEERED LT THOUGH LESS ABRUPT. ALL OTHER INDICATIONS NORMAL AND FLIGHT CONTINUED ON TO DESTINAT	ION.   AC TO BE REMOVED FROM SERVICE ON ARRIVAL FOR MTCE INVEST.  FLT DATA RECORDER TO BE REMOVED, BLUE TAGGED AND SENT 	TO PLAY BACK CENTER. (FLT REC. TO BE QUARANTEENED IN UNTIL ADVISED.)			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004070900095	20040709	00095	NM  	2004	7	9	CA040513002      	1	20040510	G	3246	314802	WHEEL           			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT MLG	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AN OPERATOR EXPERIENCED AN IN-FLIGHT MAIN WHEEL SEPARATION ON TAKE-OFF.  A REQUEST WAS MADE FOR EMERGENCY PERSONNE	L AND EQUIPMENT TO BE ON STANDBY.  AFTER A NORMAL EXTENSION OF THE LANDING GEAR VISUAL INSPECTION CONFIRMED THAT LT INNE	R MAIN WHEEL WAS MISSING.  A/C MADE AN UNSCHEDULED LANDING.  MAIN WHEEL BEARING FAILURE FOUND TO BE THE CAUSE.  INVESTIG	ATION ON-GOING.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004070900096	20040709	00096		2004	7	9	CA040513003      	4	20040513	G	3417	4040800906	COMPUTER        			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					RT  ADC	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER T/O EICAS MSGS (RUDDER RATIO,AILERON LOCKOUT) ALTIMETER, AIRSPEED, IVSI OUTSIDE LIMITS BETWEEN CAPT AND F/O,	 AUTO PILOTS WOULD NOT ENGAGE.  NOTE: MOC REQUESTED F/O ALT ADC BE SELECTED, FAULT CLEARED.  FLT CREW ELECTED TO RTN TO 	YVR. RT ADC FAULT BULB SHOWS AFTER TEST.  ADC REPLACED AND FUNCTION CHECK SERVICE.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2006061200427	20060612	00427		2006	6	12	CA040513004      	4	20040512	G	2565	D31041147	SLIDE           			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					CABIN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											ADDITIONAL PARTS P/N D30854 S/N 0278 AND P/N 61571 S/N 0175, DURING OVERHAUL INSPECTION BY AIR CRUISERS ALL 3 SLIDES WER	E FOUND IMPROPERLY PACKED WITH IMPROPER RESTAINTS.  THIS COULD HAVE A SERIOUS PROBLEM IF UNITS WERE DEPLOYED.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2004070900097	20040709	00097	NM  	2004	7	9	CA040513005      	1	20040512	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			61271								(CAN) DURING ROUTINE CHECK A 2.5 INCH (TWO AND A HALF INCH) CRACK WAS FOUND ON THE OUTER FUSELAGE SKIN AT FS 943 AND 945	.5 STRINGER 24R. CRACK REPAIRED IAW SRM 53-30-3 FIG 48 DETAIL 9 PAGE 284. TIMES 61271:42 CYCLES 59436.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004070900100	20040709	00100	NM  	2004	7	9	CA040513006      	1	20040508	G	2750		FLAP TRACK      			BOEING	727   	72744C      	1384100	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					FLAP SYSTEM	CONTAMINATED    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DEPARTING, THE CREW OBSERVED A DIAGEEMENT BETWEEN IB AND OB FLAP POSITION. THE AIRCRAFT CONTINUED TO YFB BYPASSING	 YSR. MAINTENANCE IN YFB FOUND SIGNIFICANT CONTAMINATION DUE TO POOR RUNWAY CONDITION AT YRB (SLUSH AND MUD) AND SUSPECT	 FLAP SYSTEM FOULED BY THIS CONTAMINATION. THE AIRCRAFT WAS CLEANED AND CHECKED SERVICEABLE, DEPARTURE FOR YOW WAS UNEVE	NTFUL.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004080400213	20040804	00213	CE  	2004	8	4	CA040513008      	1	20040512	G	7603	901187263	SPRING          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER CONTROL	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) ON TAKE OFF ROLL, PWR SET TO 1290 FT LBS.  AFTER ROTATION NOTICED TORQUE INCREASING ON RT ENG.  FO ATTEMPTED TO RE	DUCE PWR BUT PWR LEVER WOULD NOT MOVE.  TORQUE INCREASED TO APPROX 1500 FT LBS FOR ABOUT 90 SECONDS.  AFTER REACHING SAF	E ALTITUDE RT ENG SHUTDOWN AND AC LANDED SAFELY.  ON INSPECT ENG CNTRLS, PWR CNTRL SPRING LINK FOUND TO BE CATCHING ON C	NTRL LEVER MNTG BRKT.  LINK IS AT BASE OF ROD END THAT ATTACHES AIRFRAME PWR CABLE TO INPUT ARM ON CAM CLUSTER.  ACTION 	OF LINK ON CNTRL LEVER BRACKET WOULD BE TO PULL PWR LEVER TOWARDS HIGHER PWR SETTING, ULTIMATELY JAM THERE.  THIS LINK S	HOULD HAVE BEEN MOUNTED 10-15 DEGREES FURTHER IN THE COUNTER CLOCKWISE DIRECTION ON THE POWER CABLE.	1	L	7	2 	3T	3	T	 	A14CE   	E4EA	6	C	P15EA
2004071200178	20040712	00178	EA  	2004	7	12	CA040514001      	1	20040513	G	2150		SHAFT           			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					A/C PACK	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ENGINE START CREW WAS UNABLE TO OBTAIN COLD AIR-CONDITIONED AIR OUT OF THE LT AIR CONDITIONING PACK. ENGINES	 WERE SHUTDOWN AND MAINTENANCE WAS NOTIFIED OF THE SNAG.  MAINTENANCE DISCOVERED THAT THE LOW LIMIT VALVE, BUTTERFLY VAL	VE WAS NO LONGER ATTACHED TO ITS SHAFT. THE BUTTERFLY VALVE WAS LOCATED IN THE DUCT JUST BELOW THE AIR-COOLING TURBINE. 	THE AIR-COOLING TURBINE WAS ALSO REPLACED AS A PRECAUTION DUE TO SUSPECTED FOD DAMAGE. A NEW LOW LIMIT VALVE AND AIR-COO	LING TURBINE WERE INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071200179	20040712	00179	SO  	2004	7	12	CA040514002      	1	20040510	G	2731	110321004	BRACKET         			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AIRCRAFT DI BY MAINTENANCE THE ELEVATOR TRIM TAB WAS FOUND TO HAVE EXCESSIVE PLAY. INVESTIGATION REVEALED T	HE ATTACH BRACKET FOR THE TRIM TAB ACTUATOR WAS CRACKED AND THE ACTUATOR BRACKET WAS MOVING WITH THE ACTUATOR ALLOWING T	HE EXCESSIVE PLAY IN THE ELEVATOR TRIM TAB.				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA	6	C	P15EA
2004071200180	20040712	00180	NM  	2004	7	12	CA040514003      	1	20040511	G	2760		CONTROL CABLE   			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	SPOILER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PLEASE TAKE NOTE THAT FOLLOWING MFG Q400 AOM NR 122 MANY AILERON AND SPOILER CONTROL CABLES WERE FOUND WORN TO OR 	CLOSE TO LIMIT ON OUR A/C WITH ONLY 2038HRS AND 2858 CYCLES SINCE MFG.  SIMILAR FINDING WERE FOUND ON OUR OTHER Q400 S/N	 4004 (1610 HRS AND 2100 CYCLES). THE MAJOR DIFFERENCE BETWEEN THE 2 A/C WAS THAT 4003 CABLES FOUND DIRTY BUT TENSION OK	 AND 4004 TENSION LOWER THAN SPECIFIED IN THE AMM BUT CABLES WERE CLEAN.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004071200204	20040712	00204	NE  	2004	7	12	CA040514004      	2	20040430	G	7323	8210161C	GOVERNOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	OVERSPEED	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA			28638								(CAN) DURING APPROACH AT 8000 FT, NR 2 ENGINE UNCOMMANDED FEATHER . ENGINE SHUT DOWN. NORMAL LANDING.  MAINTENANCE REPLA	CED PROP TRANSFER TUBE , PCU AND FCU, WITHOUT CORRECTING PROBLEM.  OVERSPEED GOVERNOR AND OVERSPEED GOV HYD PUMP REPLACE	D, GROUND RUNS SUCCESSFUL.  AIRCRAFT RETURNED TO SERVICE. OVERSPEED GOV AND OVERSPEED GOV HYD PUMP SENT TO VENDOR FOR IN	VESTIGATION/REPAIR.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004071200206	20040712	00206	EA  	2004	7	12	CA040515001      	1	20040505	G	2721	272613	TRIM SWITCH     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RUDDER	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) RUDDER TRIM GOES FULL RT WITHOUT INPUT COMMAND.  WITH NOSE LT SELECTED, TRIM MOVES FURTHER RT.  AIRCRAFT RETURNED 	AND LANDED WITHOUT FURTHER INCIDENT.  REMOVED AND REPLACED RUDDER TRIM PANEL AND OPS CHECKED.  NO FURTHER DEFECTS NOTED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004071200207	20040712	00207	EA  	2004	7	12	CA040515002      	1	20040510	G	3213	17064103	FITTING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			20873								(CAN) LT MAIN FITTING WAS FOUND CRACKED DURING INSPECTION IAW SB601R-32-079E. THE MAIN FITTING HAD BEEN INSPECTED BY EDD	Y CURRENT ON 22-APR-04 WITH NO FINDINGS (20599 TFH, 16653 TFC).  NO EVIDENCE WAS FOUND OF INCORRECT SHOCK STRUT SERVICIN	G OR STRUCTURAL DAMAGE.  BOTH MLG ASSYS WILL BE REPLACED AND SENT TO MFG FOR INVESTIGATION.  THE A/C HAS NO HISTORY OF H	EAVY LANDINGS OR REJECTED TAKEOFFS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020100133	20050201	00133	EU  	2005	2	1	CA040517001      	1	20040510	G	6520	350A33100021	PINION GEAR     	AEROSP      		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					T/R GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M2519					(CAN) GEAR BOX ASSY HAD OIL SAMPLES TAKEN AFTER OVERHAUL FOR 1160.O HRS AND ALL OIL SAMPLES TAKEN WHERE NORMAL , AFTER I	NTERM REPAIR TO INPUT HOUSING ALL OIL SAMPLES TAKEN SHOWED SIGNS OF WEAR DUE TO ABNORMAL WEAR FOR 188.9 HOURS.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2004071200208	20040712	00208		2004	7	12	CA040517002      	4	20040511	G	2210	62701160	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	AT TRIM SERVO	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE REMOVING AN ELECTIC TRIM SERVO FOR THE STABILATOR SYSTEM, IT WAS NOTICED THAT THE FORWARD STABILATOR TRIM CA	BLE WAS FRAYED AT THE AREA THAT IT WAS WOUND AROUND THE ELECTIC TRIM SERVO PULLEY.  THE CABLE WAS REPLACED WITH A NEW ON	E. THIS AREA SHOULD BE INSPECTED CLOSELY AT THE TWO PULLEYS ON THE SERVO. IT IS DIFFICULT TO SEE ANY DEFECT ON THE CABLE	 UNLESS THE TRIM IS RUN COMPLETELY IN BOTH DIRECTIONS.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004071200209	20040712	00209	CE  	2004	7	12	CA040517003      	1	20040515	G	5340	501200742	FITTING         			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MAIN SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23069								(CAN) DURING A ROUTINE DETAILED INSPECTION,  MAINTENANCE DISCOVERED A CRACK IN THE LT UPPER FORWARD WING FITTING OF THE 	WING CENTER SECTION.  NDT, USING LPI AND EDDY CURRENT CONFIRMED THIS AS A CRACK. THIS AIRCRAFT HAS FLOWN 513.9 SINCE LAS	T NDT IAW MFG SIRM.  AIRCRAFT GROUNDED AND MANUFACTURER NOTIFIED.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA
2004071900027	20040719	00027	CE  	2004	7	19	CA040518001      	1	20040203	G	7920	655601110	MANIFOLD        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ENGINE OIL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL MANIFOLD FLARE FITTING MADE VERY POORLY,  VERY ROUGH/SCRAPPED SURFACE ON FLARE MATING SURFACE, ALLOWING FITTIN	G TO WEEP OIL. REPLACEMENT PART WAS NOT MUCH BETTER BUT NO OIL LEAKS.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2004071900033	20040719	00033	EA  	2004	7	19	CA040518002      	2	20040518	G	7414		MAGNETO         								LYC   	O540  	O540E4C5    	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DUE TO ROUGH RUNNING ENGINE.  MAG WAS DETERMINED TO BE FAULTY, WAS REPLACED.  A/C WAS TEST FLOWN, ENGINE RAN VERY 	ROUGH.  INSP OF ENG AND REPLACED MAG NOTED INTERNAL MAG GEAR WAS DAMAGED WITH MISSING TEETH.   NOTED METAL IN OIL SCREEN	.  ENG WAS REMOVED AND SHIPPED FOR INSPECTION AND REPAIR.  ENGINE WAS DISMANTLED AND CRANKSHAFT GEAR WAS DAMAGED WITH TE	ETH BROKEN OFF.  OTHER INTERNAL DAMAGE INCLUDED A DAMAGED IDLER GEAR, OIL PUMP DRIVE, AND TACH SHAFT.  EXACT CAUSE OF FA	ILURE IS U/K BUT IT IS SUSPECTED THAT WHEN A/C WAS FIRST SERVICED, MAG WAS REPLACED THAT INTERNAL TIMING 10 PENNY NAIL W	AS LEFT INSTALLED AND THUS CAUSED LOCKING UP OF MAG GEARS.  WHEN ENGINE WAS STARTED MAG AND CRANK GEARS WERE BROKEN OFF.						3	O			E295
2004071900034	20040719	00034	EA  	2004	7	19	CA040518003      	2	20040515	G	7220	SCDEETS41446	HOSE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	BREATHER	KINKED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, CABIN BEGAN TO FILL WITH FUMES AND OIL VAPOR. CREW TURNED OFF ENGINE BLEED AIR AND RETURNED TO AIR	PORT. MAINTENANCE FOUND NR 1 ENGINE BREATHER HOSE HAD BEEN KINKED AND PINCHED CAUSING THE ACCESSORY CASE TO PRESSURIZE A	ND FORCE OIL TO PASS THE ENGINE LABYRINTH AND GARLOCK SEALS AND ENTER THE COMPRESSOR. SOME OF THIS OIL ENTERED THE CABIN	 THROUGH THE AIRCRAFT BLEED AIR SYSTEM CREATING FUMES AND VISIBLE OIL VAPOR. ENGINE BREATHER HOSE WAS INSPECTED AND REPO	SITIONED.   SEVERAL SUCCESSFUL GROUND RUNS WERE CARRIED OUT AND AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004071900035	20040719	00035	EA  	2004	7	19	CA040518004      	2	20040518	G	8550		DIPSTICK        								LYC   	O360  	IO360A2B    	41514	EA  					ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) INFLIGHT ENGINE STOPPAGE WAS DUE TO OIL STARVATION.  IT IS SUSPECTED THAT THE OIL DIP STICK WAS REPLACED BUT NOT S	CREWED DOWN THUS PERMITTING OIL TO ESCAPE VIA THE OIL FILL TUBE.  IT WAS NOTED THAT THE FRONT OF THE ENGINE WAS DRY WHIL	E THE AFT PART WAS COATED.									3	O			1E10
2004071900036	20040719	00036	CE  	2004	7	19	CA040518005      	1	20040506	G	2810	2500010071	LINE            	CESSNA      		CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	FUEL CROSSFEED	RESTRICTED      	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						T30300265					(CAN) DURING CRUISE FLIGHT, PILOT SELECTED CROSSFEED FOR RT ENGINE.  SHORTLY AFTERWARDS, THE RT ENGINE LOST POWER/FUEL F	LOW.  SELECTOR WAS RETURNED TO NORMAL, AND ENGINE CONTINUED TO RUN NORMALLY.  MAINTENANCE DISCOVERED UPON INSPECTION THA	T THERE WERE 2 LONG STRINGS, AND NUMEROUS BITS OF PRC SEALANT THAT CAME OUT OF THE LINE WHEN BLOWN OUT WITH COMPRESSED A	IR.  MOST LIKELY SOURCE OF CONTAMINATION WAS WHEN FUEL TANK MAINTENANCE WAS CARRIED OUT, AND NOT ALL REMOVED SEALANT WAS	 CLEANED OUT OF TANK.  AIRCRAFT THOROUGHLY GROUND RUN AND RELEASED.  NO FURTHER OCCURRENCE.		1	L	7	2 	3O	3	O	 	A34CE   	E8CE	5	C	P57GL
2004071900037	20040719	00037	CE  	2004	7	19	CA040518006      	1	20040506	G	7714	C668022101	NEEDLE          			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	TACHOMETER	STUCK           	W				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			CA											(CAN) PILOT REPORTED THAT LT TACH NEEDLE WAS STUCK AT 2400 RPM.  INDICATOR REPLACED AND TESTED SERVICEABLE WITH NEW GAUG	E.  INTERNAL PROBLEM WITH GAUGE, SENT TO REPAIR FACILITY.					1	L	7	2 	3O	3	O	 	A34CE   	E8CE	5	C	P57GL
2004071900038	20040719	00038	CE  	2004	7	19	CA040518007      	1	20040517	G	3020	11891003415	HOSE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	STACK TO COWL	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF CREW OBSERVED SPARKS AND GLOW FROM RT ENGINE COWL. CREW SHUTDOWN RT ENGINE AND RETURNED TO AIRPORT.	  MAINTENANCE FOUND THE FLEXIBLE HOSE FROM THE EXHAUST STACK TO THE LIP HEATER HAD CRACKED AND SEPERATED FROM THE COWLIN	G.  THIS ALLOWED THE EXHAUST THAT WAS INTENDED FOR THE INTAKE HEATER TO ENTER THE FORWARD COWLING.  COWLING WAS REPLACED	 WITH SERVICEABLE UNIT AND FLEXIBLE HOSE WAS REPLACED ON COWL THAT WAS REMOVED.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004071900063	20040719	00063	CE  	2004	7	19	CA040518008      	1	20040508	G	2910	623372	SELECTOR VALVE  			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	HYD POWER	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH THE CREW NOTICED THAT THE LANDING GEAR WAS LOUDER THAN USUAL ANDSLOWER TO EXTEND. MAINTENANCE FOUN	D THE POWER PACK SELECTOR VALVE TO BE INTERMI TTENT AND THE POWER PACK TO BE NOISY. WITH THE AIRCRAFT ON JACKS THERE WER	E TIMES WHEN THE GEAR WOULD FAIL TO EXTEND WHEN SELECTED AND HAD TO BE MANUALLY EXTENDED. POWER PACK ASSY INCLUDING THE 	SELECTOR VALVE WAS REPLACED AND THE LANDING GEAR TESTED SERVICEABLE. AIRCRAFT WAS PLACED BACK INTO SERVICE ON MAY 13TH.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004071900064	20040719	00064	CE  	2004	7	19	CA040518009      	1	20040326	G	3020	1173T423	SWITCH          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					UNDERTEMP	OUT OF LIMITS   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) LT ENGINE ANTI-ICE LIGHT SLOW TO EXTINGUISH. LT UNDERTEMP SWITCH GOES OFF AT 340 DEGREES F,  SHOULD GO OFF AT 300+	/-7 DEGREES F.  NEW SWITCH INSTALLED AND OPERATION CHECKED SATISFACTORY.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2004071900065	20040719	00065	CE  	2004	7	19	CA040518010      	1	20040326	G	2110		DRIVE ASSY      			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					COMPRESSOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						1862					(CAN) AIR CONDITIONER COMPRESSOR DRIVE PULLEY SHAFT OIL SEAL LEAKING OIL.  AIR COMPRESSOR REPLACED.						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2004071900066	20040719	00066	SW  	2004	7	19	CA040518011      	1	20040511	G	6410	2060016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CHORDWISE CRACK, APPROX 2.8 INCHES LONG, OBSERVED TO START AT LEADING EDGE RUNNING TOWARDS TRAILING EDGE.  LOCATED	 0.5 INCHES AWAY FROM THE OB TIP OF DOUBLER. ONLY ONE SIDE OF THE TAIL ROTOR BLADE IS CRACKED.					1	G	7	1 	3U			 	H2SW
2004071900067	20040719	00067		2004	7	19	CA040518012      	4	20040507	G	3457	AVSAT100	ANTENNA         			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	GPS	OUT OF POSITION 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE SERVICING MAINTENANCE OBSERVED THAT THE GPS ANTENNA ON THE CROWN OF THE AIRCRAFT STA 108F-126F BETW	EEN STR O AND 2L TO BE OUT OF POSITION. INSPECTION FOUND FATIGUE CRACKING ALONG BOTH SIDES AND THE FRONT EDGE WAS BEGINN	ING TO LIFT AWAY. THE AIRCRAFT WAS REPAIRED AND RETURNED TO SERVICE. BOTH DOUBLER AND AIRCRAFT SKIN SUFFERED FATIGUE FAI	LURE.			2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899
2004071900068	20040719	00068	CE  	2004	7	19	CA040519001      	1	20040401	G	7830	183238001	SOLENOID        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					THRUST REVERSER	WEAK            	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) SECONDARY THROTTLE RT UNABLE TO ADVANCE PAST FLIGHT IDLE AFTER RT THRUST REVERSER DEPLOYED DUE TO WEAK INTERLOCK S	OLENOID.  SOLENOID ASSEMBLY 183238-001 REPLACED.  OPERATION OF RT AND LT SECONDARY THROTTLE INTERLOCKS CHECK SATISFACTOR	Y.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2004071900069	20040719	00069	NE  	2004	7	19	CA040519002      	2	20040419	G	7530	655551117	TUBE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					BLEED AIR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TUBE CHAFED INSIDE SUPPORTING CLAMP P/N S2894-24 TUBE 6555511-17 AND CLAMP (REVISED P/N 471-24) REPLACED LT AND RT	 ENGINE.  THIS WAS FOUND DURING PERFORMANCE OF SB 560-71-05 WHICH WAS TO INSPECT TUBE AND INSTALL REVISED CLAMP.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2004071900070	20040719	00070	EA  	2004	7	19	CA040519003      	1	20040504	G	3244	95X1612	TIRE            			FRCHLD	F27   	F27F        	3373008	EA  	RROYCE	DART  	DART5297E   	54507	EU  	ROTOL	R4304	R1934304    	EU  	MLG	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) UPON LANDING, THE LT IB TIRE RE-TREAD SEPARATED FROM THE TIRE.						2	H	7	2 	4T	4	T	 	7A1     	E297	6	C	P899
2004071900074	20040719	00074	CE  	2004	7	19	CA040519004      	1	20040512	G	2720	5052432627	RUDDER PEDAL    			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RUDDER PEDAL ATTACH POINT BROKEN AT BUSHING ATTACH.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004071900081	20040719	00081	NE  	2004	7	19	CA040519005      	1	20040506	G	7931	636716	PUMP            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE OIL	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			HO	HOVERING       	1			CA								672516			(CAN) THE FLIGHT CREW WAS ALERTED BY THE ILLUMINATION OF THE ENGINE OIL PRESSURE WARNING LIGHT FOR NR 1 ENGINE.  A CHECK	 OF THE CORRESPONDING OIL PRESSURE INDICATOR RELIEVED ZERO PSI.  THE CREW IMMEDIATELY SHUT DOWN THE SUBJECT ENGINE, RETU	RNED TO THE SERVICE LANDING AND MADE A SINGLE ENGINE LANDING.  A SUBSEQUENT INSPECTION OF THE ENGINE FOR LOW OIL LEVEL, 	CLOGGED FILTER, MALFUNCTIONING OIL PRESSURE REGULATOR, PRESSURE SWITCH, TRANSMITTER AND INDICATOR REVEALED NO FAULT WITH	 ANY.  IT WAS CONCLUDED THAT THE FAULT HAD TO BE WITH THE ENGINE OIL PUMP.  CONSEQUENTLY THE ENGINE WAS REMOVED AND RETU	RNED FOR REPAIR.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA
2004071900082	20040719	00082	SO  	2004	7	19	CA040519006      	1	20040518	G	3040		BOOT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	DE-ICE SYS	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, THE LT PROP LOST A DE-ICE BOOT. THE PILOT HEARD IT AND RETURNED TO THE AIRPORT.  THE REMAINING 2	 DE-ICE BOOTS WERE REMOVED AND THE PROP WAS INSPECTED TO BE SERVICEABLE. THE PROP DE-ICE CIRCUIT BREAKER WAS PULLED AND 	THE COCKPIT PLACARDED (NOT TO BE OPERATED IN KNOWN ICING).				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004071900083	20040719	00083	SO  	2004	7	19	CA040519007      	1	20040510	G	6120	2489407	CABLE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE PROPELLER CABLE WORE WHERE IT ATTACHES TO THE SUPPORT CONNECTED TO THE STARTER JUST BELOW THE GOVERNOR. THIS A	REA OF THE ASSEMBLY CANNOT BE VISUALLY INSPECTED. THE CREW NOTICED ON TAKING OFF, THE LOSS OF PROP PITCH CONTROL, REDUCE	D MANIFOLD PRESSURE, COMPLETED PROP OVERSPEED CHECK AND MADE AN UNEVENTFUL LANDING BACK AT LA RONGE. THE PROP CABLE WAS 	REPLACED AND THE AIRCRAFT WAS GROUND RUN, RIGGED TO SPEC, AND RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004071900084	20040719	00084		2004	7	19	CA040519008      	4	20040519	G	2562	MN1300	BATTERY         	ACK         		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2AF34C	D2AF34C*    	GL  	ELT	LEAKING         	W				K				NONE                    				H	K		ELECT. POWER LOSS-50 PC   	FLUID LOSS                		IN	INSP/MAINT     	1			CA						045329					(CAN) DURING ANNUAL PERFORMANCE TEST IT WAS NOTICED THAT DURACELL MN1300 BATTERIES DATED MAR 2010 WERE LEAKING WHAT APPE	ARED TO BE BATTERY ACID. WHEN THE VOLTAGE OF THE BATTERIES WAS CHECKED IT WAS FOUND THAT THE AFFECTED BATTERIES WERE BEL	OW TWO VOLTS. ELT BATTERY CASE WAS CLEANED AND FULL SET OF NEW BATTERIES WERE INSTALLED. ELT WAS FUNCTIONAL TESTED AND F	OUND TO BE MEET MANUFACTURERS SPECIFICATIONS.			1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P5EA
2004071900085	20040719	00085	EA  	2004	7	19	CA040519009      	2	20040312	G	8530	LW12597	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BROKEN RINGS IN CYLINDER NR 4. FOUND AT ANNUAL INSPECTION. COMPRESSION TEST AND METAL IN OIL FILTER.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614
2004071900086	20040719	00086	NE  	2004	7	19	CA040519010      	2	20040513	G	7261	AS3209114	O-RING          			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RGB TRNS OIL TUB	PINCHED         	W				C	E			ABORTED TAKEOFF         	ENGINE SHUTDOWN         			K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PCEPK0205			(CAN) RT ENGINE SHUTDOWN DUE TO OIL PRESSURE, LIGHT ON AND OIL PRESSURE BETWEEN 60 AND 60 PSI. AFTER INVESTIGATION FOUND	 ONE O-RING LEAKING ON RT ENGINE REDUCTION GEARBOX OIL TRANSFER TUBE, REPLACED O-RING P/N AS3209-114. AFTER DISCUSSION W	ITH PILOTS, DID NOT EXCEED TRANSIENT LIMITS IAW MFG MM 3034342 REV.26 CHAP 71-00-00 TABLE 503, OIL LEVEL ADJUSTED, LOST 	OF 5 QTS OF OIL. ENGINE INSPECTED IAW MFG MM 3034342 REV.26 CHAP 72-00-00 INSP.Q.   RUN-UP CARRIED OUT, OIL FILTER CHECK	ED FOR CONTAMINATION. FOUND SERVICEABLE. NOTE: CHIP DETECTOR TO BE CHECK DAILY FOR ONE WEEK, MIN25 HOURS. (IAW EMM 72-00	-00 P640 Q(2)(B), OIL FILTER TO BE CHECK BETWEEN 25-65 HOURS.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004071900087	20040719	00087	NM  	2004	7	19	CA040519011      	1	20040519	G	5314		KEELBEAM        			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLESHOOTING APU SNAG, MAINT DISCOVERED A CRACK IN THE KEELBEAM WEB (STA 870 LOAD CONTROL VALVE AREA) THE	 DAMAGE IS BEING REPAIRED IAW SRM 53-10-9.CRACK LENGTH APPROX 3.5 INCHES.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004080500085	20040805	00085	WP  	2004	8	5	CA040519012      	1	20040508	G	6120		VALVE           			DOUG  	A26   	A26BSHIELDS 	3020504	WP  	PWA   	R2800 	R280079     	52026	NE  	HAMSTD	23E	23E50       	NE  	PROPELLER	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA									NK140140		(CAN) ON A TRAINING FLIGHT THE RT ENGINE WAS SHUT DOWN.  DURING THE RESTART, THE RT PROP BEGAN TO OVERSPEED.  THE CREW A	CCOMPLISHED THE OVERSPEED PROCEDURE AND RETURNED TO BASE WITHOUT INCIDENT.  MAINTENANCE FOUND IN TROUBLESHOOTING THE DIS	TRIBUTOR VALVE HAD OIL LEAK.				2	M	7	2 	4R	4	R	 	L34     	5E8	6	C	P603
2004080500086	20040805	00086	CE  	2004	8	5	CA040519013      	1	20040515	G	5341	501200735	FITTING         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16063								(CAN) DURING THE ROUTINE COMPLETION OF CF1981-35 SITES NR 1 AND NR 2, A SMALL CRACK WAS DISCOVERED ON THE LOWER RT, IB B	ATHTUB FITTING. THE CRACK APPEARED TO START ON THE FEATHERED EDGE AT THE CENTER OF THE RADIUS AND PROPOGATE TOWARD THE M	ATING SURFACE OF THE FITTING FOR A DISTANCE OF APPROXIMATELY 0.164 INCH.  MFG WAS CONSULTED AND A REPAIR WAS GENERATED T	HROUGH THEIR REPAIR DESIGN OFFICE. IT CONSISTED OF BLENDING OUT THE CRACK TO THE SPECIFIED DIMENSIONS, PERFORMING FPI TO	 ENSURE ALL THE CRACK WAS REMOVED AND SURFACE TREATING THE ALUMINUM TO PREVENT CORROSION. THE WING BOLT WAS REINSTALLED 	IAW SIRM AND THE AIRCRAFT RELEASED FOR SERVICE.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA
2004080500087	20040805	00087	NM  	2004	8	5	CA040519014      	1	20040518	G	2761	65449617	ACTUATOR        			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SPOILER	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) DURING TAXI TO GATE LOSS OF NOSE WHEEL STEERING OCCURRED WITH TOTAL LOSS OF HYDRAULIC A PRESSURE AND QUANTITY AT Z	ERO.  MAINTENANCE FOUND THE NR 8 GROUND SPOILER ACTUATOR TO BE THE CAUSE. THE ACTUATOR BODY HAD STRUCTURAL FAILURE CAUSI	NG FLUID LOSS.  ACTUATOR REPLACED AND AIRCRAFT RETURNED TO SERVICE.  ACTUATOR ROUTED TO OUR MAINTENANCE PROVIDER'S SHOP 	WITH REQUEST FOR FULL REPORT.  WILL ADD FURTHER DETAILS OF THE FAILURE WHEN AVAILABLE.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004080500088	20040805	00088	EU  	2004	8	5	CA040520001      	2	20040511	G	7200		ENGINE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RIGHT	SEIZED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								16375			(CAN) THE AIRCRAFT WAS CLIMBING EN-ROUTE WHEN THE FLIGHT CREW OBSERVED THE RT ENGINE OIL PRESSURE RISING ABOVE LIMITS. T	HE ENGINE CEASED OPERATING AND THE PROPELLER FEATHERED BEFORE THE CREW COULD ACTION THE ENGINE SHUTDOWN CHECKLIST.  SHUT	DOWN AND CLEANUP CHECKLISTS WERE CARRIED OUT AND THE FLIGHT DIVERTED BACK TO MAIN BASE.  THE FLIGHT CREW DECLARED AN EME	RGENCY AND LANDED AT LAKE WITHOUT FURTHER INCIDENT. COMPANY MAINTENANCE FOUND THE ENGINE WAS SEIZED.  THE ENGINE AND PRO	P WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  THE ENGINE WILL BE SHIPPED OUT TO A FACILITY FOR INSPECTION AS SO	ON AS PRACTICAL.	2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899
2004080500089	20040805	00089	NM  	2004	8	5	CA040520002      	1	20040515	G	2760	BACC2A3A01262GG	CONTROL CABLE   			BOEING	727   	72744C      	1384100	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					SPOILERS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) MAINTENANCE FOUND THE WSB2 CABLE BROKEN WHEN INVESTIGATING A REPORT OF SPOILER FLOAT.  THE CABLE WAS REPLACED AND 	THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004080500090	20040805	00090	CE  	2004	8	5	CA040520003      	1	20040520	G	8011	640174	RETAINING RING  			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	STARTER GEAR	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STARTER GEAR RETAINING RING (P/N 6401740) DISENGAGED FROM THE STARTER SHAFT AND LODGED IN THE STARTER GEAR NEEDLE 	BEARING (P/N 639788). THE NEEDLE BEARING FAILED WITH THE BEARING NEEDLES ENTERING THE ENGINE REAR CASE AND OIL SYSTEM.  	THE NEEDLES IN THE OIL SYSTEM DAMAGED THE FOLLOWING PARTS:  OIL PUMP GEARS (2) P/N'S 3562 AND 21343 REAR CASE(1) P/N 640	174STARTER DRIVE AND CLUTCH (1) P/N 641500.			1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918
2004080500091	20040805	00091	SO  	2004	8	5	CA040520004      	1	20040520	G	5312	50090XX	BULKHEAD        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BEHIND FIREWALL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17794								(CAN) MAINTENANCE INSPECTION REVEALED CRACKING IN THE LONGITUDINAL BULKHEADS (BOTH) BEHIND EACH ENGINE.  THESE BULKHEADS	 RUN THE LENGTH OF THE NACELLE, FROM THE FIREWALL TO THE TRAILING EDGE OF THE NACELLE.  THE CRACKS ARE PRESENT WHERE THE	 BULKHEADS NARROW TO ACCOMODATE THE FRONT WALL OF THE NACELLE FUEL TANK AND THE CUTOUTS FOR PLUMBING AND AIR DUCTS. PRES	ENTLY PURSUING A REPAIR DESIGN CERTIFICATE TO ADDRESS THIS PROBLEM.			1	L	7	2 	3T	4	T	 	A8EA    	E4EA	6	C	P15EA
2004080500092	20040805	00092	NM  	2004	8	5	CA040521001      	1	20040519	G	3233	656021123	MODULE          			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG ACTUATOR	FAILED          	W				J	A			DUMP FUEL               	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, CREW NOTICED NOSE (GEAR UNSAFE) LIGHT DID NOT EXTINGUISH. AFTER DUMPING FUEL, CREW RETURNED TO MAINT	ENANCE FACILLITY WHERE THE LANDING GEAR ACCY UNIT WAS REPLACED AND GEAR SWINGS PERFORMED. A/C RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004071900071	20040719	00071		2004	7	19	CA040521003      	4	20040520	G	3418	C771075	TRANSDUCER      			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT WING LIFT	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) CREW REPORTED THAT ON TAXI FOR TAKE-OFF FOR THE SECOND FLIGHT OF THE MORNING THAT THE RT STALL SYSTEM WAS ACTUATED	 ON GROUND WITH STALL IDENT LIGHT RT ON AND CONTINUOUS STICK SHAKER IN FLIGHT CONTROL SYSTEM.  UNABLE TO CANCEL.  AIRCRA	FT RETURNED TO BLOCKS.				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE
2005022400027	20050224	00027	EU  	2005	2	24	CA040521004      	1	20040517	G	2160	959902012	CONTROL VALVE   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN TEMP	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE PILOT REPORTED THAT THE 'OVERTEMP' LIGHT ON THE CAWS PANEL CAME ON DURING FLIGHT. WHEN THE TEMPERATURE CONTROL	 WAS TURNED DOWN, THERE WAS NO CHANGE IN THE CABIN TEMP OR THE INDICATION ON THE CAWS PANEL. THE PILOT SELECTED THE ECS 	SWITCH TO MANUAL, WHICH AGAIN FAILED TO EXTINGUISH THE CAWS INDICATION. THE AIRCRAFT RETURNED TO BASE AND MAINTENANCE FO	UND THAT THE TEMPERATURE CONTROL VALVE WAS SEIZED IN THE FULL HOT POSITION. A NEW VALVE WAS INSTALLED ALONG WITH A SERVI	CEABLE TEMPERATURE SENSOR. THE AIRCRAFT ECS SYSTEM WAS GROUND TESTED AND RETURNED TO SERVICE. THE AIRCRAFT MANUFACTURER 	HAS NO OVERHAUL SCHEDULE FOR THE TEMPERATURE CONTROL VALVE. THIS IS THE SECOND FAILURE WE HAVE HAD OCCUR WHERE THE VALVE	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005022400028	20050224	00028	EU  	2005	2	24	CA040521005      	1	20040515	G	7700		WARNING LIGHT   			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ENGINE	ILLUMINATED     	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											MAY 15TH THE PILOT IN COMMAND NOTED A RED GOV WARNING LIGHT AT 700 FEET ABOVE GROUND.  HE ELECTED TO LAND ON A SAND BAR 	AND NOTED IN THE DESCENT THE MAIN ROTOR RPM EXCEEDED THE MAX LIMIT.  A LANDING WAS CARRIED OUT WITH NO INJURIES TO PERSO	NS.  THE HELICOPTER WAS TRANSPORTED TO AIR SERVICES FACILITY.  THE CAUSE OF THE OVER SPEED IS UNDER INVESTIGATION AT THI	S TIME WITH NO RESULTS AS OF YET.			1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005030800002	20050308	00002	NE  	2005	3	8	CA040521006      	2	20040520	G	7414	11052	COUPLER         	BENDIX      		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	RT MAGNETO	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						452008					ENGINE STARTED TO RUN ROUGH AT CRUISE SETTINGS AND ABOVE.  ENGINE BACKFIRE VIOLENTLY WHEN RIGHT MAG SELECTED .  RUBBER D	ISK COUPLER BETWEEN MAG AND MAG DRIVE FOUND TO BE SEVERLY CRACKED AT EACH COG ON THE DISK, CAUSING THE MAG TO BECOME OUT	 OF TIME AT RPM GREATER THAN 1750.  BELOW 1750 RPM ENGINE OPERATED NORMAL.  THE MAD AND MAG COUPLER WERE REPLACED AND AI	RCRAFT RELEASED FOR RETURN TO SERVICE.			1	H	7	1 	3R	3	R		A815    	E142	6	C	P719
2005030800003	20050308	00003	CE  	2005	3	8	CA040521007      	1	20040203	G	5610	1013840252	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											PILOTS WINDSHIELD INNER PANE SHATTERED WHILE IN FLIGHT						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005030800004	20050308	00004	NM  	2005	3	8	CA040521008      	1	20040521	G	3231	141085	SEQUENCE VALVE  			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					RT MLG DOOR	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			CA											AFTER T/O AND GEAR RETRACTION, CREW NOTICED HYDRAULIC QUANTITY LOW.  CREW MONITORED HYDRAULIC LEVEL FOR DURATION OF FLIG	HT WITH NO CHANGE.  UPON GEAR EXTENSION, HYDRAULIC QUANTITY DROPPED FURTHER, REQUIRING THE A/C TO BE TOWED TO RAMP FROM 	THE ACTIVE TAXIWAY.  MAINTENANCE DISCOVERED THE RT MLG DOOR SEQUENCE VALVE HAD CRACKED.  THE VALVE WAS REPLACED.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005030800005	20050308	00005	SW  	2005	3	8	CA040525001      	1	20040521	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											STAINLESS STEEL CABLES, LT AND RT, FRAYED AT WING ROOT PULLEY.  FLAP DOWN POSITION.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874
2005030800006	20050308	00006	SW  	2005	3	8	CA040525002      	1	20040521	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											STAINLESS STEEL CABLES, LT AND RT, FLAP CONTROL AT WING ROOT PULLEYS FRAYED.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874
2005030800007	20050308	00007	NE  	2005	3	8	CA040525003      	2	20040521	G	7314	SPE31342	DIAPHRAGM       			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	23D	23D30       	NE  	FUEL PUMP	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											PILOT REPORTED FUEL PRESSURE INDICATOR DROPPED INTERMITTENTLY DURING ALL PHASES OF OPERATION.  AIRCRAFT WAS RETURNED TO 	MAINTENANCE BASE.  FUEL FOUND TO BE LEAKING FROM WOBBLE PUMP.   WOBBLE PUMP DIAPHRAGM FOUND TO BE CRACKED.  DIAPHRAGM RE	PLACED, ENGINE GROUND RUN SATISFACTORY.  AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3R	3	R		A806    	5E1	6	C	P719
2004080600028	20040806	00028	GL  	2004	8	6	CA040525004      	3	20040525	G	6114	45C33173472	SEAL            	HARTZL      	HCB3TN3     											HARTZL	HCB3T	HCB3TN3     	GL  	PISTON	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BUA20747					(CAN) PROPELLER WAS SENT IN FOR AN OIL LEAK, AND UPON DISASSEMBLY INNER SURFACE OF THE PISTON SEAL WAS FOUND TO BE CUT. 	THE SEAL WAS REPLACED PROPELLER TESTED FOR LEAKS, AND THE PROPELLER WAS RETURNED TO THE CUSTOMER.															6	C	P15EA
2005030800008	20050308	00008	CE  	2005	3	8	CA040525005      	1	20040525	G	2560		SHOULDER BELT   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	COCKPIT	INADEQUATE      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											IT WAS NOTED DURING INSPECTION, THAT THE REAR SEAT SHOULDER HARNESSES WERE NOT INCOMPLIANCE WITH AIRWORTHINESS DIRECTIVE	 86-26-04.  THIS DIRECTIVE IS SERIAL NUMBER SPECIFIC AND SHOULD NOT APPLY TO THIS AIRCRAFT.  IT APPEARS THAT THESE HARNE	SSES WERE RECYCLED BY BELT MAKERS INC AND INSTALLED IN THIS AIRCRAFT WHEN THE INTERIOR WAS REDONE IN 2003.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL
2004080600029	20040806	00029	EA  	2004	8	6	CA040526001      	1	20040524	G	3230	858601	PSEU            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			17727								(CAN) FLIGHT CREW REPORTED UPON SELECTION OF GEAR DOWN, INITIALLY THREE GREEN INDICATED, SHORTLY AFTER, A FLICKERING OF 	THE NOSE GEAR DOOR (AMBER) AND UNSAFE (RED) AND HORN SOUNDED, THEN CLEARED.  ON TAXI IN SNAG RE-OCCURRED AND GREEN GEAR 	SAFE LIGHT NOW U/S.  ALTERNATE VERIFICATION LIGHTS INDICATED GEAR SAFE.  MAINTENANCE FOUND CARD FAULT ON PSEU.  REPLACED	 AND TESTED UNIT AND COMPLETED GEAR SWINGS WITH NO FAULTS FOUND.  AIRCRAFT WAS RETURNED TO SERVICE.  SNAG RE-OCCURRED FO	UR FLIGHTLEGS LATER WITH INDICATION OF GEAR UNSAFE ON TAXI.  AIRCRAFT IS CURRENTLY IN HANGAR BEING INVESTIGATED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080600030	20040806	00030	WP  	2004	8	6	CA040526002      	1	20040522	G	2410	696233B	CSD             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LT GENERATOR	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) COMPLETE POWER INTERRUPTION ON TAKE OFF ROLL COMPLETED INTERRUPTION DURING 1 TO 3 SEC. WAS CAUSED BY RELAY DURING 	POWER TRANSFER.  AIRCRAFT CAME BACK TO THE GATE.  MAINTENANCE FOUND LT GENERATOR FREQUENCY TO LOW.  AIRCRAFT WAS DISPATC	HED AS IAW MEL 24-1.  THE LT GENERATOR WAS REPLACED THE DAY AFTER.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004080600031	20040806	00031	WP  	2004	8	6	CA040526003      	1	20040522	G	2410	696233B	CSD             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RIGHT	OVERHEATED      	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) RT CSD OIL TEMPERATURE HIGH DURING CRUISE.  CSD DISCONNECTED AND AIRCRAFT DIVERTED.  BECAUSE THE LT GENERATOR WAS 	INOPERATIVE (ACFT DISPATCHED IAW MEL 24-1).  RT CSD , GENERATOR AND CSD OIL COOLER WERE REPLACED AND AIRCRAFT DISPATCHED	 SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004080600032	20040806	00032	SW  	2004	8	6	CA040526004      	1	20040520	G	6320	406040056107	CASE            	BELL        		BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30      	03013	GL  					M/R GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A302					(CAN) A DOZEN STUD HOLES FOUND DEEPLY CORRODED AND NEEDED SPECIAL REPAIR IAW MFG INSTRUCTIONS.  THE CORROSION IS CAUSED 	BY DISSIMILAR METALS AND MOISTURE.  MFG CANNOT SOLVE THE PROBLEM DEFINITELY BUT SUGGEST METHODS TO SLOW IT DOWN AND DIMI	NISH DAMAGE TO CASE.				1	G	7	1 	3U	3	U	NC	H2SW    	E1GL
2004080600033	20040806	00033	NM  	2004	8	6	CA040526005      	1	20040317	G	3260	401020101	PROXIMITY SWITCH			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	NLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER GEAR UP SELECTION, GEAR CAME UP AND LOCKED BUT NOSE GEAR DOOR LIGHT REMAINED ON.  WHEN GEAR WAS SELECTED DOW	N, THE NOSE GEAR DOOR CAUTION LIGHT REMAINED ON. (GEAR DOWN AND LOCKED). UNSCHEDULED LANDING COMPLETED.  NOSE GEAR DOOR 	CLOSED PROXIMITY SENSOR REPLACED IAW AMM 32-61-00.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE
2004080600034	20040806	00034	NM  	2004	8	6	CA040526006      	1	20040412	G	3297		WIRE            	BFGOODRICH  		BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  		SHORTED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE GEAR WOULD NOT RETRACT WHEN GEAR UP WAS SELECTED. GEAR WAS RECYCLED BUT WOULD STILL NOT COME UP.  	THE ONLY INDICATIONS WERE THREE GREEN AND THREE RED LIGHTS.  NO CAUTION OR AURAL WARNINGS. THE FLIGHT WAS RETURNED TO BA	SE.  INVESTIGATION/ACTION, NOSE WHEEL CENTERING SENSOR WIRING FOUND SHORTED.  SENSOR REPLACED IAW AMM 32-61-00.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE
2004080600035	20040806	00035	CE  	2004	8	6	CA040526007      	1	20040519	G	3230		MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) ON APPROACH, CREW SELECTED LANDING TO EXTEND. LANDING GEAR WOULD NOT EXTEND. GEAR HANDLE CYCLED. STILL NO GEAR EXT	ENSION. CREW CARRIED OUT LANDING GEAR EMERGENCY EXTENSION.  NO FURTHER FAULTS.  MAINTENANCE FOUND LANDING GEAR ELECTRIC 	MOTOR PREMATURELY FAILED.  REPLACE ELECTRIC MOTOR . NO FURTHER FAULTS.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA
2005030800009	20050308	00009	CE  	2005	3	8	CA040526008      	1	20040511	G	2121	C4140070101	FAN             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C402   	GL  	E/E BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											SHORTLY AFTER TAKEOFF SMOKE WAS OBSERVED IN THE COCKPIT AND EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED FOR LANDING	.  AT THIS TIME THE AIRSPEED WAS READING EXTREMELY LOW.  INVESTIGATION REVEALED THE STROBE/AVIONICS COOLING FAN CIRCUIT 	BREAKER OPEN.  THE FAN ASSY EXHIBITED A STRONG BURNED ODOR AND THE PITOT LINE FOR THE LAKE AND AIR GEAR ADVISORY WAS FOU	ND MELTED WHERE ROUTED IN CLOSE PROXIMITY TO THE FAN MOTOR.  THE PITOT LINE WAS REPAIRED AND RE-ROUTED AND A NEW BLOWER 	ASSY INSTALLED.		1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P47GL
2005030800010	20050308	00010	EU  	2005	3	8	CA040526009      	1	20040525	G	2750	9742001902	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											AFTER LANDING PILOTS TRIED TO RETRACT THE FLAPS BUT COULD NOT GET THEM TO MOVE.  AIRCRAFT WAS INSPECTED AND FLAP UP RELA	Y WAS FOUND TO HAVE FAILED, P/N 974.20.01.902.  RELAY WAS REPLACED AND FLAP SYSTEM TESTED.  AIRCRAFT RETURNED TO FLIGHT 	LINE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800011	20050308	00011	EU  	2005	3	8	CA040527001      	1	20040512	G	6240	50071550020	TRANSDUCER      			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					M/R GEARBOX	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AFTER MAIN ROTOR GEAR BOX REPLACEMENT GROUND RUN WAS ACCOMPLISHED, HOWEVER NO INDICATION WAS PRESENT.  DISCOVERED AFTER 	CONTINUITY CHECKS THAT THE TRANSDUCER WAS OPEN CIRCUIT.  REPLACED PART INDICATION NORMAL					1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005030800012	20050308	00012	EA  	2005	3	8	CA040527002      	1	20040520	G	2730	C2CF815A	CONTROL CABLE   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING SCHEDULED INSPECTION, THE LT ELEVATOR CONTROL CABLE WAS FOUND TO BE FRAYED AT THE FWD PULLEY LOCATED UNDER THE BA	TTERY BOX.  NO EVIDENCE OF BATTERY ACID FOUND IN LOCATION.  THE CABLE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3R	3	R		A806    	5E1
2005030800013	20050308	00013	NM  	2005	3	8	CA040527003      	1	20040523	G	2400		ELECTRICAL SYS  			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ALL	UNKNOWN         	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											ON THE ROLL IN CYXY, ALL ELECTRICS WERE LOST.  ALL ELECTRICS RESTORED BY THEMSELVES AFTER APPROX 30 SECONDS THEN FAILED 	AGAIN SHORTLY AFTER.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005030800014	20050308	00014	NE  	2005	3	8	CA040527004      	1	20040506	G	2140		DUCT            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					CABIN HEAT	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			HO	HOVERING       	1			CA											A/C WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS IN THE AREA OF POWER RIVER BRITISH COLUMBIA.  DURING THE FIRST LOGGING	 CYCLE OF THE DAY THE FLIGHT CREW NOTICED WHAT APPEARED TO BE SMOKE IN THE COCKPIT.  AN IMMEDIATE A CHECK OF ALL SYSTEMS	 AND CIRCUIT BREAKERS REVEALED NO DISCREPANCIES.  THE FLIGHT CREW ELECTED TO RETURN TO THE SERVICE LANDING FOR FURTHER I	NVESTIGATION BY THE MX CREW.  A SUBSEQUENT INSPECTION AND GROUND RUN OF ALL A/C SYSTEMS RESULTED IN NO FAULT FOUND.  IT 	WAS CONCLUDED THAT SINCE THE AIRCRAFT WAS FRESH OUT OF HEAVY MX AND IT WAS THE FIRST COOL MORNING THAT REQUIRED CABIN HE	AT THAT BRAND NEW DUCTING FROM THE BLEED AIR HEATER WAS THE CAUSE.  THE A/C WAS RETURNED TO SERVICE WITH NO FURTHER RELA	2	G	7	2 	4U	4	U		H4EA    	E15EA
2005030800015	20050308	00015	CE  	2005	3	8	CA040527005      	1	20040518	G	7603	6676101000013	CONTROL MODULE  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					THROTTLE	STIFF           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											RT POWER LEVER 'PIGGYBACK' LEVER VERY STIFF, DIFFICULT TO MOVE TO STOW POSITION. THROTTLE CONTROL MODULE REPLACED.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005030800016	20050308	00016	CE  	2005	3	8	CA040527006      	1	20040430	G	2450	700GC02Y07	CONTROL PANEL   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					POWER DIST	FAILED          	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											RT GENERATOR WILL DROP OFF LINE AFTER OPPOSITE ENGINE START.  RT AFT POWER DISTRIBUTION PANEL REPLACER WITH NEW UNIT.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005030800017	20050308	00017	SO  	2005	3	8	CA040527007      	1	20040524	G	2432	ALU8421R	POST            	ELECTROSYS  		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ALTERNATOR	BROKEN          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						9040609					PILOT RETURNED TO BASE FOR ELECTRICAL AND AVIONICS DIFFICULTIES.  ON RETURN, AIRCRAFT BATTERY DEPLETED CAUSING MULTIPLE 	ELECTRICAL AND AVIONICS PROBLEMS.  PILOTS INITIATED PRECAUTIONARY MANUAL GEAR EXTENSION DUE TO LACK OF POSITIVE GEAR EXT	END INDICATION AT NO TIME DID EITHER ALTERNATOR FAIL LIGHT ILLUMINATE.  UPON INSPECTION, FOUND RT ALTERNATOR BATTERY POS	T BROKEN AND SHORTING ON STARTER CASE INSTALLED BELOW ALTERNATOR.			1	L	7	2 	3O	3	O		A20SO   	E14EA
2005030800018	20050308	00018		2005	3	8	CA040527008      	4	20040520	G	6113	09520046	BULKHEAD        			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											BACK PLATE CRACKS FOUND RADIATING FROM RIVET HOLES.  AT MANUFACTURING THE TALL SIDE OF RIVET AREAS NOT DEBURED PROPERLY.	  HOLES MAY HAVE BEEN PUNCH PRESSED AND SMALL AMOUNTS OF EXCESS MATERIAL REMAINED.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2005030800019	20050308	00019	EU  	2005	3	8	CA040527009      	1	20040522	G	2910	T2C5000605500	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					HYD SYSTEM	CHAFED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											ON APPROACH, THE CREW OBSERVED LOW FLOW INDICATION ON BOTH SYSTEMS AND 1700 PSI.  LANDING WAS CARRIED OUT WITHOUT INCIDE	NT.  MAINTENANCE FOUND THE SUPPLY LINE FROM THE HP FILTER TO THE GEARBOX DRIP TRAY IN THE RIGHT HAND NACELLE CHAFED THRO	UGH.  THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	3T	4	T		A24EU   	A196
2005030800020	20050308	00020	SW  	2005	3	8	CA040527010      	1	20040526	G	7697	C1006	WIRE            			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	POWER LEVER SWIT	BROKEN          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											ON TAKEOFF THE CREW ABORTED DUE TO AN AMBER 'NOSE STEER FAIL' LIGHT WAS 'ON'.  SYSTEM WAS TROUBLESHOT AND A BROKEN WIRE 	WAS FOUND ON THE LT POWER LEVER ENABLE NOSE WHEEL STEERING SWITCH.  THE WIRE WAS REPAIRED AND THE SYSTEM TESTED SERVICIB	LE.  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T			RT	A8SW    		6	C	3PNE
2005030800021	20050308	00021	EU  	2005	3	8	CA040527011      	1	20040526	G	5210	RMRE04UCBBFF	ROD END         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					PAX DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			39734	39734							ON ARRIVAL, CREW UNABLE TO OPEN MAIN FWD LEFT HAND CABIN DOOR.  PASSENGERS DEPLANED USING REAR PASSENGER DOOR.  DOOR MEL	'D AND AIRCRAFT OPERATED TO MAINTENANCE BASE.  MAINTENANCE INSPECTION FOUND DOOR OPERATING MECHANISM DISCONNECTED FROM O	PERATING HANDLE DUE TO FAILED CONNECTING  ROD ROD END. ROD END P/N RMRE04UCBBFF REPLACED AND DOOR FUNCTION TESTED.  AIRC	RAFT RETURNED TO SERVICE.  (PART IS CLASSIFIED AS AN EXPENDABLE IN THE MAINTENANCE TRACKING SYSTEM AND DEFINITIVE PART T	IME NOT AVAILABLE, TIMES PROVIDED ARE AIRCRAFT TIMES, PART BELIEVED TO BE ORIGINAL EQUIPMENT).		2	H	7	4 	4F	4	F		A49EU   	E6NE
2005030800022	20050308	00022	NM  	2005	3	8	CA040527012      	1	20040526	G	3260		LANDING GEAR    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  		UNKNOWN         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											ON TAKEOFF, CREW REPORTED WEIGHT ON WHEELS CAUTION LIGHT ILLUMINATED ON TAKEOFF AND STAYED ON FOR ABOUT 20 MINUTES.  CRE	W DECIDED TO RETURN TO TORONTO.  THE LIGHT HAD GONE OFF BY THEN.  IN TORONTO THE MAINTENANCE ENGINEERS INSPECTED THE AIR	CRAFT RELEVANT SYSTEMS INCLUDING ALL THE WOW SWITCHES/SENSORS, ELECTRICAL CONNECTORS AND THE PSEU(PROXIMATY SWITCH ELECT	RONIC UNIT) AND SEVERAL GEAR SWINGS CARRIED OUT AND THEY COULD NOT DUPLICATE THE FAULT OR ACCERTAIN THE CAUSE OF THIS WA	RNING.  THE AIRCRAFT WAS RETURNED TO SERVICE .		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800023	20050308	00023		2005	3	8	CA040528001      	4	20040527	G	3442	6229302003	TRANSMITTER     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					WX RADAR SYS	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											DURING FLIGHT, UPON SELECTION OF WEATHER RADAR, THE BLUE 'RADAR FAULT' AND AMBER 'RADAR CONTROL FAULT' MESSAGES APPEARED	 ON THE MFD DISPLAY, CREW CYCLED ON AND OFF WITH NO SUCCESS, CREW DETERMINED TO RETURN AIRCRAFT WHERE MAINTENANCE ENGINE	ERS UPON TESTING THE SYSTEM REPLACED WEATHER RADAR RECEIVER TRANSMITTER AND ANTENNA (ALL ONE UNIT) AND RETURNED AIRCRAFT	 TO SERVICE. TIME ON UNIT UNKNOWN TIME ON AIRCRAFT IS 10227.58			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005030800024	20050308	00024	EA  	2005	3	8	CA040528002      	1	20040524	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											FLIGHT EN ROUTE WHILE DESCENDING OUT OF 25,000 FT, FIRST OFFICER'S WINDSHIELD CRACKED.  WINDSHIELD REPLACED.  AIRCRAFT R	ETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005030800025	20050308	00025	EU  	2005	3	8	CA040528003      	1	20040516	G	3240	80197035099	LINE            	PIAGIO      		PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					BRAKE SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THE BRAKE LINE WAS FOUND WITH MECHANICAL DAMAGE DURING THE 600 HOUR INSPECTION.  DAMAGE TO THE LINE WAS ON THE UNDER SID	E AND COULD ONLY BE SEEN WITH A MIRROR.  THE LINE IS LOCATED OVER A FLIGHT CONTROL CABLE WITH ABOUT 3 INCHES OF CLEARANC	E. THE MARKS ON THE LINE ARE 90 DEGREES TO THE MOVEMENT OF THE FLIGHT CONTROL SO THE DAMAGE COULD NOT HAVE BEEN CAUSED B	Y THE CABLE.  THERE WAS NO SIGN OF DEBRIS UNDER THE LINE TO INDICATE DAMAGE.			1	H	7	2 	3O	4	T	RT	A59EU   	E26NE
2005030800027	20050308	00027	NM  	2005	3	8	CA040528005      	1	20040517	G	2910	6590737329	LINE            			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					HYD SYSTEM	BURST           	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											ON GO-AROUND WHEN GEAR SELECTED UP.  RT MAIN GEAR FAILED TO RETRACT AND LOSS OF SYSTEM 'A' HYDRAULIC FLUID.  AIRCRAFT DI	VERTED TO CYFB, DECLARED EMERGENCY.  GEAR UP LINE P/N 65-90737-329 REPLACED, HYDRAULIC SYSTEM SERVICED, FUNCTION CHECK C	ARRIED OUT.  AIRCRAFT SERVICEABLE.  NO OTHER PROBLEMS OR ACTIONS.				2	L	7	2 	4F	4	F		A16WE   	E2EA
2005030800028	20050308	00028	EA  	2005	3	8	CA040528006      	2	20040509	G	8550	204418156	ADAPTER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					OIL FILTER	FAILED          	W				A				UNSCHED LANDING         				K	M	J	FLUID LOSS                	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			CA											IN FLIGHT THE ENGINE OIL TEMPERATURE INDICATION WAS IN THE RED. UPON AIRCRAFT RETURN, THE THERMOSTATIC VALVE P/N SL E196	00 AND THE OIL FILTER ADAPTER 204418-156WAS REPLACED.  RUN UP CARRIED OUT.  TEMPERATURE INDICATION WITHIN LIMITS, P/N 69	510.				1	H	7	1 	3O	3	O	NT	3A12    	E274
2005030800029	20050308	00029	SO  	2005	3	8	CA040528007      	1	20040515	G	3242	MS28775132	O-RING          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	BRAKE SYSTEM	CUT             	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											UPON LANDING, THE LEFT BRAKE DID NOT WORK.  TWO O-RINGS IN THE BRAKE ASSEMBLY WERE DISCOVERED TWISTED AND CUT WHICH CAUS	ED A LARGE BRAKE FLUID LEAK.  THE O-RINGS WERE REPLACED, THE SYSTEM WAS BLED AND TESTED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005030800030	20050308	00030	SO  	2005	3	8	CA040528008      	2	20040511	G	7314	6462125	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE FUEL	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								12698770C			DURING AIRCRAFT 100 HOURS INSPECTION, THE TECHNICIAN DISCOVERED A BLUE COLORED TRACE OF FUEL ORIGINATING FROM THE FUEL P	UMP LOW-METERED ADJUSTMENT SCREW.  PRESSURIZED THE FUEL SYSTEM AND NOTICED MORE FUEL LEAKING FROM THE ADJUSTMENT SCREW O	F THE FUEL PUMP.  THE TECHNICIAN REPLACED THE FUEL PUMP MECHANISM AND RE-PRESSURIZED THE FUEL SYSTEM, NO LEAKS FOUND.				1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
2005030800031	20050308	00031	CE  	2005	3	8	CA040528009      	1	20040525	G	2910	10404900	FITTING         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					HYD SYSTEM	CRACKED         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											AIRCRAFT HAD NO BRAKES AFTER LANDING ON A GRAVEL AIR STRIP.  HYDRAULIC FLUID WAS SEEN LEAKING OUT OF THE BRAKE ASSY.  EN	GINEER WAS FLOWN OUT AND FOUND THE HYDRAULIC FITTING HAD BEEN HIT WITH A ROCK AND WAS BENT AND CRACKED.  FITTING WAS REP	LACED AND BRAKE SERVICED.				1	L	7	2 	3T	4	T		A14CE   	E4EA
2005030800032	20050308	00032	NM  	2005	3	8	CA040531001      	1	20040528	G	2782		ACTUATOR        			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					LT SLATS	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											DURING A SCHEDULED ROUTINE MAINTENANCE CHECK IT WAS OBSERVED THAT THE LEFT HAND OUTBOARD SLAT ACTUATOR WAS DAMAGED. THE 	CORNER OF THE SLAT WAS GROUNDED OFF EXPOSING A SECONDARY STRUCTURAL EXTRUSION.  THE AIRCRAFT WAS GROUNDED A SUSPECTED A 	WING TIP STRIKE ON LANDING.  TSB WAS NOTIFIED AND WITH COMPANY QUALITY ASSURANCE AN INVESTIGATION IS IN PROGRESS.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2005030800033	20050308	00033	EU  	2005	3	8	CA040531002      	1	20040529	G	7722		WIRE HARNESS    			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 1 ENG TGT	CHAFED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											AFTER DEPARTING, THE CREW OBSERVED ABNORMALLY LOW TGT VALUE ON NR 1 ENGINE.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE	.  MAINTENANCE FOUND CHAFED WIRING AT THE TGT JUNCTION BOX, THE EXTERNAL CALIBRATION TEST CONNECTOR ASSY WAS REMOVED AND	 THE AIRCRAFT RETURNED TO SERVICE AFTER OVERWEIGHT LANDING INSPECTION.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005030800034	20050308	00034	NE  	2005	3	8	CA040531003      	2	20040527	G	7230	3400010260	FAN BLADE       			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENGINE	BIRD INGESTION  	W				C				ABORTED TAKEOFF         				C	E		F.O.D.                    	VIBRATION/BUFFET          		TO	TAKEOFF        	1			CA								890811			AIRCRAFT STRUCK ONE, POSSIBLY TWO SEAGULLS ON TAKEOFF, IMMEDIATE VIBRATION FELT.  TAKEOFF ABANDONED AND AIRCRAFT RETURNE	D TO GATE.  MAINTENANCE CONDUCTED 'BIRD STRIKE INSPECTION' PER MM 05-51-18, DAMAGES FOUND AT NR 1 ENGINE FAN BLADES NR 1	1, 12, 13. FURTHER INSPECTION REVEALED BLADES 11 AND 12 DAMAGED BEYOND LIMITS, BLADES 11 AND 12 REPLACED IAW MM72-21-02,	 MATCHING BLADES ALSO REPLACED (23 AND 24).  BLADES PLATFORMS BETWEEN FAN BLADE 11 AND 12, AND 12 AND 13 REPLACED IAW MM	 72-21-02.  BORESCOPE OF NR 1 ENGINE COMPLETED, NO FAULTS FOUND.  ENGINE RUNS COMPLETED, SYSTEM CHECKS SERVICEABLE.  AIR	CRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2005030800035	20050308	00035	NM  	2005	3	8	CA040531004      	1	20040526	G	3260	864202	DOWNLOCK SENSOR 			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	DAMAGED         	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			41196	41196							DURING APPROACH WHEN LANDING GEAR SELECTED DOWN , LEFT MAIN GEAR UNSAFE INDICATION.  ALTERNATE GEAR INDICATION CONFIRMED	 AS THREE GREEN, ALTERNATE EXTENSION PROCEDURE USED.   AIRCRAFT LANDED NORMALLY.  MAINTENANCE INSPECTION FOUND LT MAIN G	EAR SIDESTAY SENSOR DAMAGED.  SENSOR REPLACED. GEAR SWINGS CARRIED OUT.  AIRCRAFT RETURNED TO SERVICE. (PART IS CONSIDER	ED AN EXPENDABLE AND TIMES ON PART ARE NOT TRACKED. TIMES PROVIDED ARE AIRCRAFT TOTAL TIMES.)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800037	20050308	00037	NE  	2005	3	8	CA040531006      	2	20040515	G	7200		ENGINE          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	BIRD INGESTION  	W				O				OTHER                   				C			F.O.D.                    			CL	CLIMB          	1			CA											SHORTLY AFTER TAKEOFF A BIRD STRIKE OCCURRED ON THE RIGHT ENGINE. CREW CONTINUED CLIMB-OUT AND REDUCED POWER TO IDLE.  F	LIGHT CONTINUED  AND MADE AN UNEVENTFUL LANDING.  POST FLIGHT INSPECTION REVEALED SEVERAL FAN BLADES DAMAGED BEYOND LIMI	TS AND DAMAGE TO THE ABRAIDABLE MATERIAL OF THE FAN STATOR CASING.  THE AFFECTED ENGINE WAS REPLACED WITH LOANER AND SEN	T FOR REPAIR TO LOCAL SERVICE CENTER.  NO INFORMATION ON EXTENT OF REPAIRS AVAILABLE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005030800038	20050308	00038	NE  	2005	3	8	CA040531007      	2	20040515	G	7200		ENGINE          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	BIRD INGESTION  	W				O				OTHER                   				C			F.O.D.                    			CL	CLIMB          	1			CA											SHORTLY AFTER TAKEOFF, A BIRD STRIKE OCCURRED ON THE RIGHT ENGINE.  CREW CONTINUED CLIMB-OUT AND REDUCED POWER TO IDLE. 	 FLIGHT CONTINUED TO AND MADE AN UNEVENTFUL LANDING.  POST FLIGHT INSPECTION REVEALED SEVERAL FAN BLADES DAMAGED BEYOND 	LIMIT AND DAMAGE TO THE ABRAIDABLE MATERIAL OF THE FAN STATOR CASING.  THE AFFECTED ENGINE WAS REPLACED WITH LOANER AND 	SENT FOR REPAIR TO LOCAL SERVICE CENTERS INFORMATION ON EXTENT OF REPAIRS AVAILABLE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005030800039	20050308	00039	SW  	2005	3	8	CA040601001      	1	20040528	G	6720	407001732117	BELLCRANK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											BELLCRANK FOUND WITH HOLES (.2495 - .2505 DIA.) OVERSIZE AND OVAL RANGING FROM .253 TO .275. (3 PLACES).						1	G	7	1 	3U			O	H2SW
2005030800040	20050308	00040	SW  	2005	3	8	CA040601002      	1	20040527	G	6720	407001732125	BELLCRANK       			BELL  	427   	427         	1182207	SW  										TAIL ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											BELLCRANK FOUND WITH HOLES (.2495 - .2505 DIA.) OVERSIZE AND OVAL RANGING FROM .253 TO .275. (2 PLACES).						1	G	7	1 	3U				R00001RC
2005030800041	20050308	00041		2005	3	8	CA040601003      	4	20040530	G	3418		COMPUTER        			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					STALL WARNING	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											DURING FLIGHT FROM YUL TO CYO, ACFT DIVERTED TO FLL DUE TO NR 2 STALL INDICATION FAIL ILLUMINATED.  FOLLOWING TROUBLE SH	OOTING, MX FOUND NO SIGNAL BETWEEN HORIZONTAL STAB POSITION SENSOR NR 2 AND STALL WARNING COMPUTER NR 2 CONNECTOR CLEANE	D ON STAB SENSOR AND STALL WARNING COMPUTER.  AIRCRAFT DISPATCHED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005030800042	20050308	00042	EA  	2005	3	8	CA040601004      	2	20040520	G	8520		GEAR            	LYC         		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					CRANKSHAFT	BROKEN          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA						L363861A					RIGHT ENGINE STOP DURING FLIGHT.  FOUND SPRING PIN OF CRANKSHAFT GEAR BROKEN.  WHEN THE CRANKSHAFT WAS REMOVED, THE CHAN	KSHAFT BOLT SHEARED AND BROKE EASILY.  THIS BOLT IS SUBJECT TO AD 2002-23-06AND AD 2004-04-25C. THE NEW BOLT KIT WAS REP	LACED (MARCH 18, 2003 - REFER TO PURCHASE ORDER 11618) 343.4 HOURS BEFORE THE ENGINE STOP INCIDENT.  THE NEW BOLT KIT P#	N 05K19987 WERE SUPPLIED BY AVIALLON PURCHASE ORDER 11600 (01/22/2003)			1	L	7	2 	3O	3	O		1A10    	E14EA
2005030800043	20050308	00043	WP  	2005	3	8	CA040601005      	1	20040530	G	2741		ACTUATOR        			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					STAB TRIM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						1919					DURING CRUISE FROM YYZ,  THE PRIMARY STAB TRIM CB POPPED OUT.  AIRCRAFT LANDED BACK TO YYZ.  MAINTENANCE FOUND THE PRIMA	RY TRIM ACTUATOR IN FAULT. ACTUATOR WAS REPLACED AND AIRCRAFT DISPATCHED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005030800044	20050308	00044	NM  	2005	3	8	CA040601006      	1	20040531	G	3297		WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	INHIBIT SWITCH	LOOSE           	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			38595								ON APPROACH , WHEN CREW SELECTED GEAR DOWN AND GOT 3 RED GEAR LIGHTS.  REVERTED TO ALTERNATE GEAR EXTENSION AND GOT 3 GR	EEN LIGHTS.  MAINTENANCE FOUND LOOSE WIRING CONNECTION TO THE GEAR INHIBIT SWITCH.  PROBABLY WORKED ITSELF LOOSE OVER TI	ME WITH VIBRATION.  SWITCH REPLACED AND WIRING SECURED.  GEAR SWINGS CARRIED OUT AND SYSTEM FOUND SERVICEABLE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800045	20050308	00045	WP  	2005	3	8	CA040601007      	1	20040530	G	4900	696233B	CSD             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					APU	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE FROM VRA TO YYZ, RT CSD OUTLET TEMPERATURE INCREASED.  CSD HAS BEEN DISCONNECTED.  FEW TIME LATER, APU OIL	 TEMP WHEN HIGH AND APU HAS BEEN SHUT DOWN.  AIRCRAFT LANDED AT YYZ AS SCHEDULED.  MAINTENANCE IN YYZ DID DEFER THE RT C	SD AS PER MEL 24-1.  APU OIL RESERVICED AND TESTED/CHECKED SERVICEABLE.  AIRCRAFT DISPATCHED SERVICEABLE WITH RT CSD UND	ER MEL.  DURING CLIMB AFTER DEPARTURE FROM YYZ, APU OIL TEMP WHEN HIGH.  AIRCRAFT LANDED BACK TO YYZ.  RT CSD WAS REPLAC	ED AND APU RECTIFICATION DEFERRED AS PER MEL 49-1.  AIRCRAFT DISPATCHED AS PER MEL 49-1.  TEMPERATURE BULB SENSOR REPLAC	ED AS PRECAUTIONARY MEASURE.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005030800046	20050308	00046	CE  	2005	3	8	CA040601008      	1	20040328	G	1430	AN17642	BOLT            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					NLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											GROUND HANDLING PERSONAL ATTEMPTED TO TOW THE AIRCRAFT INTO THE HANGAR FOR A MAINTENANCE FUNCTION.  THE TOW BAR BECAME D	ETATCHED FOLLOWING HOOK UP.  THERE WAS NO DAMAGE TO THE AIRCRAFT OTHER THAN THE BROKEN LOWER TORQUE LINK BOLT ON THE NOS	E GEAR.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
2005030800047	20050308	00047	WP  	2005	3	8	CA040601009      	1	20040527	G	6210	369D21100523	BLADE           			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPON INSPECTION, A LINE WAS NOTICED EXTENDING CHORDWISE FROM THE LOWER ROOT FITTING.  AFTER REMOVING THE PAINT, THE DOUL	BER HAD ABOUT A 2.5 INCH CRACK THAT EXTENDED BOTH FOR AND AFT OF THE LOWER ROOT FITTING OF THE M/R BLADE.  THE BLADE WAS	 REMOVED FORM SERVICE AND DISASSEMBLED.  THE CRACK HAD GONE THRU THE MAIN SKIN OF THE BLADE AND THE DOUBLER.  THE CRACK 	DID NOT GO THRU THE SPAR OF THE BLADE.			1	G	7	1 	3U				H3WE
2005030800048	20050308	00048	EU  	2005	3	8	CA040601010      	1	20040531	G	2932	9738114304	PRESSURE SWITCH 			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											HYD PRESSURE SWITCH WAS FOUND TO HAVE A SLIGHT SEEPAGE OF HYDRAULIC FLUID AT THE SWITCH BODY SEAM.  SWITCH REPLACED WITH	 NEW, GROUND CHECKS SATISFACTORY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800049	20050308	00049		2005	3	8	CA040601011      	4	20040531	G	2211		ANNUNCIATOR     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AUTOPILOT	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											'FD' ANNUNCIATOR LIGHT INOP.  FLIGHT DIRECTOR COMMAND BARS FUNCTION OK.  UNIT REPAIRED AT LOCAL AVIONICS FACILITY, REINS	TALLED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800050	20050308	00050	EU  	2005	3	8	CA040601012      	1	20040531	G	3030		HEATER          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITOT TUBE	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											P-S 2 FAIL INDICATION.  NR 2 PITOT HEAT FOUND INOP.  PITOT TUBE ASSY REPLACED WITH NEW.  AIRCRAFT TTAF 3710.72576 CYC.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800051	20050308	00051		2005	3	8	CA040601013      	4	20040601	G	2562	MN1300	BATTERY         	ACK         		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ELT	LEAKING         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA						039274					DURING ANNUAL PERFORMANCE TEST, IT WAS NOTICED THAT DURACELL MN1300 BATTERIES DATED MAR 2010 WERE LEAKING WHAT APPEARED 	TO BE BATTERY ACID.  BATTERY VOLTAGE WAS LOW.  ELT BATTERY CASE WAS CLEANED AND A FULL SET OF NEW BATTERIES WERE INSTALL	ED. ELT WAS PERFORMANCE TESTED AS PER CAR 571 APPENDIX G AND FOUND TO BE OK.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2004072900002	20040729	00002	EU  	2004	7	29	CA040601014      	1	20040530	G	7697	MS3476W1419S	CONNECTOR       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENGINE	SHORTED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA								LF05649AC			(CAN) UNCOMMANDED IN-FLIGHT SHUTDOWN OF NR 4 ENG.  DURING FINAL APPROACH.  CONNECTOR IDENT (P52) ON BACK-UP OVERSPEED CO	NTROLLER FOUND TO BE SHORTED INTERNALLY.  VOLTAGE LEAKING ACROSS VARIOUS PINS ON PLUG ALSO OUT TO OVERSPEED FUEL BYPASS/	SHUT-OFF VALVE. THIS IS WHAT ACTIVATED FUEL BYPASS VALVE, CAUSING ENG TO SHUTDOWN.   REPLACING (P52) CONNECTOR (P/N MS34	76W14-19S)  WILL ALSO REPLACE SECONDARY/BACK-UP CONTROLLER AS PRECAUTIONARY MEASURE (TO HAVE IT BENCH CHECKED TO ENSURE 	THERE WAS NO INTERNAL DAMAGE CAUSED BY STRAY VOLTAGE). ONCE SYS IS RE-ASSEMBLED, WILL CARRY OUT FURTHER CHECKS TESTING. 	 GROUND RUNS, CARRIED OUT FUNCTIONING OVERSPEED ON PARTICULAR ENG WITH NO FAULTS AND SYS WAS GROUND CHECKED SERVICEABLE.	2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004072900003	20040729	00003	GL  	2004	7	29	CA040602001      	2	20040602	G	7250		BLADE           	ALLSN       		EMB   	135   	EMB135ER    	3260203	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					TURBINE ROTOR	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								311526			(CAN) AC YAW AND LOUD BANG IN CLIMB AT 21,000 FT.  ENGINE SHUTDOWN UNCOMMANDED.  EMERGENCY DECLARED AND AC DIVERTED. ON 	GROUND INSP FOUND THAT N1 WOULD NOT ROTATE.  DISASSEMBLY OF ENG AT RRC SHOWED SEVERE TURBINE DAMAGE.   SULPHIDATION,  PR	OBABLY CAUSED THE DETERIORATION OF THE HPT 1 AND 2 NGVS.  A SECTION OF THE HPT 2 NGV BROKE AND WENT INTO THE HPT 2BLADES	 WHICH CAUSED A BLADE FAILURE.  ALL THE HPT 2 BLADES BROKE AT THE ROOT AND CAUSED THE FOD DAMAGE TO THE LPT MODULE.  THI	S SITUATION CAUSED THE IFSD.  WHEN WE RECEIVED THE ENGINE, THE HPT MODULE WOU LD NOT TURN AND THE LPT MODULE WAS VERY DI	FFICULT TO ROTATE.  MFG IS EVALUATING IF THE ENGINE WILL BE REBUILT DUE TO THE EXTENSIVE TURBINE DAMAGE.	2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH
2004072900004	20040729	00004		2004	7	29	CA040602002      	4	20040602	G	8300	23056789	BEVEL GEAR      			EMB   	145   	EMB145XR    	3260214	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ACCESSORY G/B	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA								312274			(CAN) FLIGHT LOST POWER NOTICED SHORTLY AFTER TAKE OFF. NR 2 INDICATION WENT TO ZERO. THE CREW REPORTED THE NR 1 ENGINE 	SHUT DOWN IN FLIGHT.  THE SHUT DOWN WAS UNCOMMANDED.  THE AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. DISASSE	MBLY OF THE ENGINE AT RRC REVEALED THAT NR 6 BEARING BEVEL DRIVING GEAR SYSTEM THAT DRIVE MODULE 05 ACCESSORY GEARBOX HA	S FAILED.  BEVEL GEAR HAS BROKEN IN PIECES.  SUSPECT BEVEL DRIVE SHAFT DRIVING GEARBOX IS CAUSING THE FAILURE.  SHAFT RE	TURNED TO INDY FOR INVESTIGATION.		2	L	7	2 	4F	4	F	RT	        	TE6CH
2004072900005	20040729	00005		2004	7	29	CA040602003      	4	20040602	G	8300	23056789	SHAFT           			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					BEVEL GEAR	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA			13130					310066			(CAN) IN CLIMB AT 8000 FT A LOUD BANG WAS HEARD AND UNCOMMANDED ENGINE SHUTDOWN AND AIR RETURN AND UNEVENTFUL LANDING OC	CURRED.  DISASSEMBLY OF THE ENGINE AT RRC REVEALED THAT NR 6 BEARING BEVEL DRIVING GEAR SYSTEM THAT DRIVE MODULE 05 ACCE	SSORY GEARBOX  HAS FAILED.  BEVEL GEAR HAS BROKEN IN PIECES AND HOLED THE FRONT FRAME, THE FRONT FRAME IS SCRAP.  SUSPEC	T BEVEL DRIVE SHAFT DRIVING GEARBOX IS CAUSING THE FAILURE.  SHAFT RETURNED TO INDY FOR INVESTIGATION.  2ND CASE FOR RRC	 OF SAME OCCURANCE REFER TO SDR 20040602002.		2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH
2004072900006	20040729	00006	EA  	2004	7	29	CA040602004      	1	20040602	G	2150	9795804	VALVE           			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					CABIN AIR	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE LOW LIMIT VALVE WAS OBSERVED TO STICK IN AN OPEN POSITION AND WOULD NOT MODULATE. AFTER REMOVAL OF THE VALVE T	HE BUTTERFLY WAS FOUND TO BE SCRAPING AGAINST THE BODY OF THE VALVE.ANOTHER VALVE WITHTHIS CONDITION HAD PREVIOUSLY BEEN	 FOUND TO SHEAR THE BUTTERFLY SHAFT COMPLETLY. REF. SDR 2004051401.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004072900007	20040729	00007	EA  	2004	7	29	CA040602005      	1	20040602	G	4920		TURBINE         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					APU	SEIZED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INITIAL START AN UNUSUAL NOISE WAS HEARD FROM THE APU. THE UNIT WAS RUN FOR APPROXIMATELY ONE HOUR WITH NO 	ABNORMAL INDICATIONS. UPON FURTHER INVESTIGATION OF THE NOISE IT WAS DISCOVERED THAT IT WAS NOT POSSIBLE TO ROTATE THE T	URBINE WHEEL BY HAND.  A PARTIAL TURBINE SEIZURE WAS IDENTIFIED.  THE APU WAS REMOVED AND SENT FOR REPAIR.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004072900038	20040729	00038	GL  	2004	7	29	CA040602006      	2	20040602	G	7530	MS955608	BOLT            			EMB   	145   	EMB145XR    	3260214	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					MANIFOLD	LOOSE           	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								312265			(CAN) COMMANDED IFSD AND AIR RETURN.  CREW REPORTED EMERGENCY WHEN ITT EXCEEDED 950C. UNEVENTFUL AIR RETURN. DISASSEMBLY	 OF ENGINE AT RRC SHOWED THAT OUTER MANIFOLD SERVICE ATTACHMENT BOLTS LOOSEN. BLEED AIR LEAKAGE CAUSED THERMAL DAMAGE TO	 THE SURROUNDING COMPOSITE STRUCTURE OF THE OUTER BYPASS DUCT. REDUCE COOLING AIR TO THE TURBINE HAS INCREASE THE ITT. S	ERVICE BULLETIN 75-025 INTRODUCE A MODIFIED RETAINING BOLT WHICH INCLUDE A LOCKING WIRE HOLE TO PREVENT BOLT TO LOOSEN A	ND SB 75-026 INTRODUCE A SAFETY WIRE. REAR BYPASS DUCT REPLACED AN SB INCORPORATED. BOTH SB ARE OPTIONAL CATEGORY.		2	L	7	2 	4F	4	F	RT	        	TE6CH
2004072900039	20040729	00039	EU  	2004	7	29	CA040602007      	1	20040619	G	5610	NP1653114	WINDSHIELD      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WINDSHIELD OUTER PANE SHATTERED ONLY, AIR TURNBACK WINDSHIELD REPLACED WINDSHIELD HAD 21,599 HRS.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2004072900040	20040729	00040	EA  	2004	7	29	CA040602008      	1	20040602	G	3222	200811218	FITTING         			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502*     	41580	EA  					NLG AXLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DRG10899R					(CAN) 5 YEAR DETAILED INSPECTION REVEALED CORROSION PITTING BEYOND MANUFACTURER'S LIMITS, INTERNAL, BETWEEN NLG SLIDING 	TUBE (P/N 200811707)AND AXLE FITTING. NEW PART INSTALLED.  THE AXLE FITTING WAS PREVIOUSLY REPLACED IN JUNE 1999 DURING 	THE 10 YEAR RESTORATION OF THE GEAR AT 2503 CSN.				2	L	7	2 	4F	4	F	RT	A21EA   	E6NE
2004072900042	20040729	00042	NE  	2004	7	29	CA040603001      	2	20040601	G	7323	230305204	GOVERNOR        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					OVERSPEED	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			29131	17720							(CAN) DURING PILOT OPERATIONAL CHECK, NR 4 ENGINE DID NOT SHUT DOWN WITH THE OVERSPEED STOP.  NR 4 ENGINE OVERSPEED CONT	ROLLER REPLACED AND NR 4 ENGINE OVERSPEED TEST CARRIED OUT IAW AMM 71-00-00 BLOCK 501.  TEST COMPLETED AS SERVICEABLE AN	D AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	4 	4F	4	F	 	A49EU   	E6NE
2004072900043	20040729	00043	EU  	2004	7	29	CA040603002      	1	20040602	G	7120	332A32323300	BOLT            			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					ENGINE MOUNT	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER LAST FLIGHT, DAILY INSPECTION WAS BEING CARRIED OUT ON THE AIRCRAFT,  WHEN THE NR 1 ENG LT UPPER TIE BOLT WA	S FOUND TO BE FRACTURED.  THE OTHER TWO TIE BOLTS WERE REMOVED AND INSPECTED AND FOUND TO BE SERVICEABLE.  THIS TIE BOLT	 ATTACHES THE ENGINE TO THE G/B P/N 332A32-1007-03P.				2	G	7	2 	4U	4	U	 	H4EU    	E12NE
2004080400208	20040804	00208	NE  	2004	8	4	CA040603003      	2	20040520	G	7320	586982	DUMP VALVE      			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE FUEL	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA								1638341			(CAN)  PILOT BEGAN DESCENT, HEARD (WHOOSH) SOUND TYPICAL OF SOFT STALLING ENG. FOLLOWED BY N1 UNDERSPEED AUDIO, INDICATO	R LIGHT WARNING. FLT CREW VERIFIED NR 1 ENG AS BEING AT FAULT. COPILOT SHUTDOWN ENG, BEGAN TO MOTOR TO DECREASE T5 TEMP 	WHILE PILOT RELEASED LOAD. WITH T5 TEMP STABILIZED ENG WAS SECURED, AC RETURNED TO ITS SERVICE LANDING, MADE AN UNEVENTF	UL SINGLE ENG LANDING. COMPLETE VISUAL INSP OF ENG WAS CARRIED OUT BY MAINT CREW WHICH REVEALED NOTHING ABNORMAL. FUEL P	RESS AND DUMP (P&D) VALVE, ENG FUEL FILTER WERE REPLACED AS IS MAINT PROCEDURE AFTER AN ENG SOFT STALL.  LIMITS HAVE NOT	 BEEN EXCEEDED. ENG FCU WAS ALSO REPLACED. FOLLOWING ENG GROUND RUN AND TEST, AC WAS RETURNED TO SERVICE.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA
2004072900044	20040729	00044		2004	7	29	CA040603004      	4	20040603	G	2210	40E228410693	AILERON         			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					AUTO PILOT	MISMANUFACTURED 	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE INVESTIGATING A SNAG,  DISCOVERED AN AILERON A/P QUADRANT ASSEMBLY P/N 40E22-84-1069-1 WHICH DID NOT MEET TH	E MANUFACTURER'S DRAWING IN THE INSTALLATION OF THE NR 1 COLLINS A/P SERVO, LOCATED IN THE LT MLG WHEEL WELL.  FOR THE D	ISABLING OF THE NR1 A/P SYSTEM, PENDING THE MANUFACTURING OF A NEW QUADRANT BY A PRECISION MACHINE SHOP.				2	L	7	2 	4F	4	F	RT	A21AE   	E15NE
2004072900077	20040729	00077	NE  	2004	7	29	CA040603005      	2	20040602	G	7397	EO266QF16	WIRE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					FUEL PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT ARRIVED WITH THE RT OUTER TANK FUEL PUMP NR 1 LOW PRESSURE LIGHT ON.  FOLLOWING TROUBLE SHOOTING, THE WIR	E FOR NR 1 RT OUTER PUMP WAS FOUND SHORTED IN THE CONDUIT AT REAR SPAR WS 915.0.   WIRE WAS REPLACED. MFG WAS ADVISED OF	 THIS PROBLEM.  A CAMPAIGN HAS BEEN INITIATED TO INSPECT REAR SPAR WIRING ON ALL OF THESE MODELS.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2004072900078	20040729	00078	NM  	2004	7	29	CA040603006      	1	20040603	G	3242	260881211	BRAKE           			BOEING	767   	7673Y0      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					MLG	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  NR 5 AFT BRAKE DISINTEGRATED ON T/O.   NR 5 BRAKE ASSY REPLACED IAW J/C 6-232A, NR 5 WHEEL ASSY REPLACED IAW J/C 	6-232B.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE
2004072900079	20040729	00079	GL  	2004	7	29	CA040603007      	2	20040602	G	7250		TURBINE         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					ENGINE	LOCKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE834565			(CAN) TURBINE HAD AN N2 LOCK UP.   SUSPECT UNKNOWN AT THIS TIME.  TURBINE SENT TO OVERHAUL SHOP FOR ASSESSMENT.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004072900080	20040729	00080	WP  	2004	7	29	CA040604001      	1	20040601	G	7160		INLET GUIDE VANE			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2 ENGINE	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P728047			(CAN) CRACK FOUND ON ONE ENGINE INLET GUIDE VANE APROX 3.5 IN LONG (OUT OF LIMITS IAW MM 72-00-00).  AIRCRAFT WAS FERRIE	D,  IAW FLIGHT PERMIT AUTHORIZATION AND THE MANUFACTURER APPROVAL, ENGINE NR 2 HAS BEEN REPLACED.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004080400212	20040804	00212	EA  	2004	8	4	CA040604002      	2	20040519	G	8520	75089LW11775	PISTON          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING NR 1 INSP, A SIG AMOUNT OF NON-FERROUS METAL WAS FOUND IN OIL FILTER ELEMENT.  OIL SUCTION SCREEN WAS PULLE	D AND WAS FOUND TO BE FULL OF NON-FERROUS METAL.  CYL NR 1 WAS PULLED AND FWD PISTON PIN PLUG WAS FOUND TO BE WORN COMPL	ETELY ALLOWING PISTON PIN TO MIGRATE FWD TO POINT AFT PISTON PIN PLUG WAS ONLY PART LEFT IN AFT PISTON BOSS BETWEEN CONN	ECT ROD AND PISTON.  AFT PISTON BOSS HAD 1 INCH PIECE BROKEN OUT OF IT.  NR 3 CYL WAS REMOVED, WAS FOUND THAT  FORWARD P	ISTON PIN PLUG WAS STARTING TO WEAR ABOUT .0625 OF AN INCH.  HEAT AND TIME, ALUMINUM PLUG WORE AGAINST STEEL CYLINDER AN	D ONCE WEAR STARTED, IT WORE RAPIDLY.   NO IND OF OIL PRESS OR POWER LOSS ON PREVIOUS FLIGHT OR DURING RUN UP FOR INSP.	1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920
2004072900081	20040729	00081		2004	7	29	CA040604003      	4	20040603	G	8300	3022376	SEAL            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EPA CAN	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT HAD JUST LANDED AND SHUT DOWN AT IT'S DESTINATION AIRPORT. THE PILOT DISEMBARKED THE AIRCRAFT AND NOTICED	 A LARGE STREAK OF OIL DOWN THE LT SIDE OF THE FUSELAGE. MAINTENANCE INVESTIGATED THE INCIDENT AND FOUND ANOTHER LARGE O	IL STREAK DOWN THE BELLY OF THE AIRCRAFT.  IN ADDITION TO THE TWO OIL STREAKS THE EPA CAN WAS COMPLETELY FULL. THE START	ER-GENERATOR WAS REMOVED, AND MAINTENANCE FOUND THE OIL SEAL WAS SLIGHTLY DAMAGED.  A NEW SEAL WAS INSTALLED AND THE AIR	CRAFT GROUND RUN WITH NO FURTHER DEFECTS NOTED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004072900082	20040729	00082	SW  	2004	7	29	CA040604004      	1	20040602	G	2435	PW203PPC7FS500	BEARING         	LUCAS       		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					STARTER GEN	ROUGH           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						98278					(CAN) STARTER-GEN, UNDERGOING IMPORT INSPECTION.  BEARINGS WERE FOUND TO BE ROUGH AND NOISY WHEN SPUN.  REMOVED BEARINGS	, FOUND THEM TO BE SUP.  ARE MARKED PW203PP C7 FS50000.  IAW DATAPLATE, THEY SHOULD BE P/N 03-6009-23 (MOD B).  THE SOUR	CE OF THE LAST OVERHAUL IN MAY 2002 IS KNOWN.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004080400217	20040804	00217	CE  	2004	8	4	CA040604006      	1	20040526	G	5554	05310186	HINGE BRACKET   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18000								(CAN) DURING ROUTINE INSPECTION OF RUDDER THE BRACKET IN QUESTION WAS FOUND TO HAVE TWO CRACKS BESIDE THE THRUST SURFACE	.  DUE TO THE HIGH HOURS OF THIS ASSEMBLY THE THRUST SURFACE WAS FOUND TO HAVE WORN TO HALF OF ITS ORIGINAL THICKNESS.  	REPAIR TO THE RUDDER ASSEMBLY WAS ACCOMPLISHED BY REPLACEMENT OF ALL SIX HINGE BRACKETS.  SUBSEQUENT INSPECTIION OF SIMI	LAR AIRCRAFT WITH SIMILAR TIME WERE FOUND TO HAVE SAME WEAR PATTERN BUT NO CRACKS PRESENT.  FIVE MORE ASSEMBLIES HAD HIN	GE BRACKET REPLACEMENT DUE TO EXCESSIVE WEAR.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004080400218	20040804	00218	NE  	2004	8	4	CA040604007      	2	20040524	G	7200	430110209	MODULATOR       			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					AIRFLOW	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) PILOT HEARD AND FELT LOUD POPPING NOISE FROM ENGINE ACCOMPANIED WITH LOSS OF POWER.  AIRCRAFT LANDED SUCCESSFULLY.	  FLOW FENCE PROBLEM SUSPECTED.  AIRFLOW MODULATOR REPLACED, AIRCRAFT TEST FLOWN OK.					1	G	7	1 	3U	3	U	 	H9EU    	E5NE
2004080400219	20040804	00219	CE  	2004	8	4	CA040604008      	1	20040525	G	5344		DOOR FRAME      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION LOWER DOOR POST IAW SB 97-1 AND FOUND CRACK AT CORNER IAW SB.  BOTH RT AND LT DOOR POSTS. REPAIRED WITH	 MFG REPAIR KIT.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004080500001	20040805	00001	CE  	2004	8	5	CA040604009      	1	20040602	G	7500		ADAPTER         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	P2.5 BLEED SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE HOT SECTION INSPECTION MAINTENANCE FOUND THE P2.5 BLEED ADAPTER (LOCATED AT APPROXIMATELY 1 O'CLO	CK ON THE GAS GENERATOR CASE) WITH OBVIOUS CRACKS.  THE RETAINING LUGS WERE BOTH CRACKED AND ONE OF THE ADAPTER WELDING 	JOINTS WAS CRACKED ON A LENGTH OF APPROXIMATELY 1.5 INCHES. THE ENGINE WAS SENT OUT FOR REPAIR AND HAS SINCE BEEN REINST	ALLED AND PUT BACK INTO SERVICE.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P40EA
2004080500002	20040805	00002	CE  	2004	8	5	CA040604010      	1	20040527	G	3710		SHAFT           	AIRBORNE    		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	VACUUM PUMP	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						1AE48					(CAN) VACUUM PUMP SHEAR SHAFT BROKE ON START.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA
2004080500003	20040805	00003	CE  	2004	8	5	CA040604011      	1	20040527	G	3710		SHAFT           	AIRBORNE    		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	VACUUM PUMP	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						104361					(CAN) VACUUM PUMP SHEAR SHAFT, BROKE AFTER INSTALLED.  REPLACED PUMP BY OTHER SOURCE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA
2004080500025	20040805	00025	WP  	2004	8	5	CA040604013      	2	20040529	G	7210	31025613	PLANETARY GEAR  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBOX	FLAKING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								P44205C			(CAN) INSTALLED PLANETARY GEAR BRG INTO ENG, DURING ROUTINE ENG CAM INSP. 16.4 HOURS LATER, ACCOMPLISHED 1ST SOAP SAMPLE	 IAW MFG EMM. MAJOR SILVER PARTICLES FOUND IN OIL, MFG RECOMMENDED RESAMPLE. BOTH AGAIN HAD SILVER PARTICLES IN OIL. MFG	 RECOMMENDED TO INSPECT THIS ENG IMMEDIATELY, ENG WAS REMOVED AND REPLACED, ENG TEARDOWN INSP IN ORDER TO DETERMINE CAUS	E FOR METAL IN OIL, DUE TO MAJOR SILVER. ENG HAD 101.7 HRS SINCE CAM AND 129 CYC WHEN IT WAS REMOVED. DURING INSP IT WAS	 FOUND THAT TWO PLANETARY GEARS O/H HAD LARGE AMOUNTS OF SILVER MISSING, FLAKING OFF BRG CAGE SURFACES. OTHER TWO PLANET	ARY GEAR BRGS INSTALLED HAD MINOR AMOUNT OF SILVER WORN OFF WHICH WAS SMALL IN COMPARISON ABOVE MENTIONED BEARINGS.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2004080500027	20040805	00027	NM  	2004	8	5	CA040604014      	2	20040603	G	7321	8953804	VALVE           			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	HP LIMITER	FLUCTUATES      	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P06034			(CAN) DURING CLIMB OUT THROUGH 5000 FEET, ENGINE POWER BEGAN TO FLUCTUATE. ENGINE WAS SHUTDOWN AND SECURED.  AIRCRAFT LA	NDED WITHOUT INCIDENT. INVESTIGATION FOUND THAT THE HORSE POWER LIMITER BYPASS VALVE WAS LEAKING INTERNALLY.  BYPASS VAL	VE WAS REPLACED.				1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA
2004080500028	20040805	00028	SW  	2004	8	5	CA040604015      	1	20040604	G	6720	206010795105	PIN             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R PITCH	DISLODGED       	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) PIN P/N 100-035-187.5-30.5 WAS INSTALLED CORRECTLY. HOWEVER AN ADDITIONAL PIN WAS FOUND FLOATING INSIDE THE SHAFT.	  THE LAST MAINTENANCE PERFORMED IN THAT AREA WAS 27 JUNE 2003.  APPROX 666.1 HOURS.  PIN WAS REMOVED AND THE REST OF TH	E ASSEMBLY WAS INSPECTED FOR DAMAGE.  AIRCRAFT RETURNED TO SERVICE AFTER ACCEPTABLE TEST FLIGHT.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004080500029	20040805	00029	EA  	2004	8	5	CA040604016      	1	20040511	G	3244	H29X901516	TIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE NR 2 MLG TIRE HAD SEPARATED THAT INCURRED DAMAGE TO THE IB FLAP SURFACE, FLAP STUB FAIRING AND 3 FAN BLADES..						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004080500030	20040805	00030	CE  	2004	8	5	CA040607001      	1	20040604	G	3260	20700291	WIRE            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	NLG DOWNLOCK SW	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) PILOT EXPERIENCED NO GEAR DOWN AND LOCK INDICATION LIGHT AFTER GEAR HAD COMPLETED CYCLE.  AFTER AN UN-EVENTFUL LAN	DING AND INSPECTION, FOUND NOSE GEAR DOWNLOCK SWITCH WIRE WAS BROKEN AT BASE OF SWITCH.					1	H	7	1 	3O	3	O	 	A20CE   	1E10	5	C	P7EA
2004080500031	20040805	00031	NE  	2004	8	5	CA040607002      	2	20040604	G	8530		NUT             			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	CA18        	52026	NE  	HAMSTD	23E	23E50       	NE  	PUSHROD TUBE	LOOSE           	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) PILOT NOTICED OIL LEAK AND DID A PRECAUTIONARY ENGINE SHUT DOWN. HE DID A ONE ENGINE OUT LANDING PROCEDURE AT AIRP	ORT WITHOUT INCIDENT.  MAINTENANCE FOUND NR 17 CYLINDER PUSHROD TUBE NUT LOOSE.  THE SEAL WAS REPLACED AND THE NUT TORQU	ED. THE ENGINE WAS GROUND RUN WITH NO EVIDENCE OF AN OIL LEAK.				2	M	7	2 	4R	4	R	 	L34     	E231	6	C	P603
2004080500032	20040805	00032	CE  	2004	8	5	CA040607003      	1	20040302	G	3230		LANDING GEAR    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C652  	NE  		MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING FLIGHT, THE LANDING GEAR TOOK LONGER THAN NORMAL TO RETRACT. COULD NOT DUPLICATE THE PROBLEM IN THE HANGAR 	EVEN WHEN SWINGING THE GEAR.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE
2006061200430	20060612	00430	EU  	2006	6	12	CA040608001      	1	20040606	G	2434	5243212161	DRIVE SHAFT     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			4797 								ON RETURN, PILOT NOTED GEN 2 FAILURE IN CRUISE AND CONT`D ON TO COMPLETE FLT.  NR 1 GEN AUTO COVERS FOR NR 2 GEN WHEN A 	FAILURE OCCURS.  INVESTIGATION BY MX REVEALED SHEARED DRIVE SHAFT FOR NR 2 GEN.  SHAFT BROKE AT PROPER SHEAR POSITION WI	TH NO DAMAGE TO ANY OTHER COMPONENT.  CAUSE IS UNCLEAR, BUT THERE IS SOME SCORING ON DRIVESHAFT AT FWD BEARING INNER RAC	E POSITION.  BEARING APPEARS IN GOOD COND W/NO BINDING OR ROUGH SPOTS.  GEN 2 ALSO APPEARS IN GOOD MECH CONDITION W/NO B	EARING DISTRESS OR DRAG ON ALT SHAFT.  IT IS SUSPECTED THAT CYCLE LIFE COULD HAVE POSSIBLE AFFECTED SHAFT LIFE AS LOADS 	ARE CLOSE TO 100 AMPS AFTER STARTUP TO RECHARGE BATTERIES.  ALIGNMENT OF SHAFT LOOKS GOOD, NO GREAT AMT OF SPLINE WEAR A	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004080500067	20040805	00067	CE  	2004	8	5	CA040608002      	1	20040603	G	2730	1156100103	TORQUE TUBE     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	ELEVATOR	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE INSTALLATION OF A NEW ELEVATOR TORQUE TUBE, IT WAS NOTICED THAT ONE OF THE TAPERED PINS WAS INSTALLED B	EYOND THE MANUFACTURES LIMITS.  THE MM 27-30-00 PAGE 202 A, STATES IN PART THE SMALL END OF THE TAPER PIN BODY SHOULD EX	TEND .000 TO 0.060 INCH BEYOND THE SURFACE OF THE SUPPORT. IF THE DIMENSIONS ARE NOT MET, NEW PARTS WILL BE REQUIRED.  T	HE SMALL END ON THE SUBJECT TUBES EXTENDED 0.125 INCHES BEYOND THE SURFACE. A SECOND TORQUE TUBE FROM OUR STOCK WAS ALSO	 FOUND IN THE SAME CONDITION. BOTH TUBES WERE NEW, SUPPLIED BY THE AIRCRAFT MFG.   A THIRD TUBE FROM THE SAME BATCH WAS 	REMOVED FROM OUR STOCK. MFG WAS CONTACTED AND THEY WILL BE INVESTIGATING THE MATTER FURTHER.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	3PNE
2004080500068	20040805	00068	EU  	2004	8	5	CA040609008      	1	20040607	G	7334	8G12561	PRESSURE SWITCH 			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					FUEL SYSTEM	MALFUNCTIONED   	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK AROUND AFTER COMPLETION OF A FLIGHT, NOTICED FUEL LEAKING OUT OF BOTTOM OF NR 1 ENGINE COWLING.  FOUND	 NR 1 FUEL PRESSURE SWITCH LEAKING OUT OF VENT HOLE. SWITCH WAS REPLACED WITH A NEW UNIT AND TESTED OK.					2	L	7	3 	4F	4	F	RT	A46EU   	E6WE
2004080500069	20040805	00069	CE  	2004	8	5	CA040609009      	1	20040609	G	1420	M817141120D	CONNECTOR       			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	FUEL PROBE	CORRODED        	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) LT WING AUX FUEL TANK INDICATION ALWAYS INDICATING (0).   WHEN TESTING SYSTEM LT QUANTITY CAUTION LIGHT WON'T COME	 ON.  DURING TROUBLESHOOTING, FOUND A LOT WATER TRAPPED UNDER THE ACCESS PANEL AND THE WIRING WAS CORRODED. WATER REMOVE	D AND CONNECTOR WILL BE REPLACED.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004080500070	20040805	00070	NE  	2004	8	5	CA040609010      	2	20040527	G	7200		ENGINE          			AMD   	FALC20	FALCON20D5  	2730003	EU  	GE    	CF700 	CF7002D2    	30010	NE  					NR 1	FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								245U150			(CAN) ON CLIMB OUT THE NR 1 ENGINE (S/N 245U150) EXPERIENCED A FLAME-OUT. CREW WAS ABLE TO RE-LIGHT THE ENGINE AND RETUR	N WITHOUT FURTHER INCIDENTS. ON 26 MAY 04, ANOTHER CREW HAD EXPERIENCED A FLAMEOUT. THE FCU WAS SUBSQUENTLY CHANGED, AIR	CRAFT WAS GROUND RUN AND CHECKED SERVICEABLE.  WITH SECOND FLAMEOUT (ON 27 MAY) ENGINE HAS BEEN REMOVED AND WILL BE ROUT	ED TO OVERHAUL SHOP FOR FURTHER ANALYSIS.  FINDINGS, REPORT TO FOLLOW.			2	L	7	2 	4F	4	F	RT	A7EU    	E7EA
2004080500071	20040805	00071	NE  	2004	8	5	CA040609012      	2	20040606	G	7314	5905587	FILTER          	BFGOODRICH  		AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	FUEL PUMP	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF, THE CREW OBSERVED A FUEL FILTER CAUTION ON NR 1 ENGINE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. M	AINTENANCE REPLACED THE HIGH PRESSURE FILTER ON THE ENGINE PUMP AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE
2004080500072	20040805	00072	SO  	2004	8	5	CA040609013      	1	20040527	G	7603	455360	THROTTLE CABLE  			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	CNTRL LEVER END	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER A PREFLIGHT CHECK, THE PILOT COMPLAINED OF AN EXTREMELY LOOSE THROTTLE CONTROL.  AFTER FURTHER INSPECTION, T	HE CONTROL CABLE WAS DETERMINED TO BE INTERNALLY BROKEN.  THE CABLE WAS REMOVED AND THE CONTROL LEVER END OF THE CABLE P	ULLED OUT OF THE EXTERNAL CASE EXPOSING THE INTERNAL CABLE STRANDS.  TWO OF THESE STRANDS WERE BENT OVER SUGGESTING THEY	 WERE BROKEN FOR SOME TIME. PILOT HAS NEVER COMPLAINED OF A STIFF THROTTLE CONDITION.			1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P9EA
2005012400033	20050124	00033	NM  	2005	1	24	CA040609014      	1	20040609	G	7810	65MK7823113	TAILPIPE        			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			63233								(CAN) DURING ROUTINE MAINTENANCE A 5-6 IN CRACK AT THE 6 OCLOCK POSITION AND A 4 IN CRACK AT THE 12 OCLOCK POSITION,  	OF THE NR 2 ENGINE TAILPIPE WAS FOUND.  BOTH CRACKS REPAIRED IAW MFG MM 78-38-43.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005012400039	20050124	00039	EU  	2005	1	24	CA040609015      	1	20040609	G	3220		LANDING GEAR    			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NOSE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FAULT: THE NOSE GEAR DID NOT RETRACT AFTER DEPARTURE. THE FLT CREW RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHE	R INCIDENT.  NO ADDITIONAL INFORMATION WAS PROVIDED BY THE FLIGHT CREW.  AIRCRAFT OUT OF SERVICE FOR INVEST. NOTE: MORE 	INFO WILL FOLLOW WHEN AVAILABLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005012400040	20050124	00040	EA  	2005	1	24	CA040609016      	1	20040609	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)THE AIRCRAFT PERFORMED A FLAP 0 LANDING.  DURING DESCENT THE FLT CREW RECEIVED A FLAP MSG.  THE AIRCRAFT LANDED  WI	THOUT FURTHER INCIDENT. ALTHOUGH THE FLT CREW DID DECLARE AN EMERGENCY, THEY DID REQUEST THAT THE CFR'S.  SYSTEM RESET  	IAW AOM INSERT 126.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005012400041	20050124	00041	SO  	2005	1	24	CA040609017      	2	20040604	G	8530	401852	STUD            	CONT        	IO240B      	DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ROCKER COVER	BROKEN          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA						635724461					(CAN) ENGINE RAN ROUGH ON FINAL APPROACH AND STOPPED ON ROLL OUT.  ENGINE RESTARTED TO TAXI IN AND RAN VERY ROUGH AND BA	CKFIRED.  EXHAUST VALVE ON CYLINDER NR 3 DID NOT MOVE WHEN ENGINE TURNED OVER.  FOUND ROCKER AND SHAFT LOOSE IN ROCKER C	OVER.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2005012400042	20050124	00042	WP  	2005	1	24	CA040609018      	2	20040601	G	7320	89711019	FUEL CONTROL    			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	MCAULY	4HFR34	4HFR34C660  	NE  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA								P7763			(CAN) DESCENDING THROUGH 7000 FEET ON APPROACH THE RT ENGINE SPOOLED DOWN. WHEN AUTO IGNITION WOULD NOT RELIGHT IT, THE 	CAPTAIN SECURED THE ENGINE AND LANDED WITHOUT FURTHER INCIDENT. THE ENGINE WOULD NOT RESTART ON THE GROUND. MAINTENANCE 	TROUBLESHOT THE PROBLEM TO THE FCU AND REPLACED IT WITH AN OVERHAULED UNIT. THE FAILED UNIT HAD BEEN OVERHAULED 10/24/02	 AND INSTALLED 04/22/03. A TEARDOWN REPORT HAS BEEN REQUESTED.			1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	5	C	3PNE
2005012400043	20050124	00043	WP  	2005	1	24	CA040610001      	1	20040604	G	2910	A10070	CHECK VALVE     			CVAC  	580   	580         	2422806	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) UPON LANDING, CREW DISCOVERED BRAKES INEFFECTIVE AND STEERING UNRESPONSIVE. AFTER STOPPING A/C USING PNEUMATIC BRA	KES, CREW FOUND HYDRAULIC RESERVOIR NEAR EMPTY. AFTER TOWING A/C TO RAMP, MAINTENANCE FOUND THE GROUND BLOWER CHECK VALV	E CRACKED.  MAINTENANCE DE-ACTIVATED THE GROUND BLOWER, SERVICED THE HYDRAULIC SYSTEM, AND DISPATCHED A/C TO A MAINTENAN	CE FACILITY FOR PART REPLACEMENT.			2	L	7	2 	4T	4	T	RT	        	E282	6	C	P898
2005012400044	20050124	00044	EA  	2005	1	24	CA040610003      	2	20040519	G	7230		BLADE           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	1 ST STAGE	BROKEN          	W				E				ENGINE SHUTDOWN         				A	Y		FLAME/FIRE                	ENGINE STOPPAGE           		CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT IN THE MORNING, CREW HEARD A  BANG  FROM ENGINE NR 1. CAPTAIN LOOKED OUT, THE ENGINE HAD STOPPED 	AND THE FIRE WARNING WAS ILLUMINATING.  INSPECTIONS HAVE REVEALED A BROKEN 1ST STAGE LOW PRESS COMPRESSOR BLADE AND THIS	 HAS MOST PROBABLY CAUSED A COMPRESSOR STALL DUE TO SEVERE DAMAGE AND A COMPRESSOR SUDDEN STOPPAGE.  FRACTURE SURFACE IN	DICATES FATIGUE FRACTURE AND THIS WE HAVE REPORTED SEPARATELY TO DIFFERENT MFG.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005012400045	20050124	00045	SW  	2005	1	24	CA040610004      	1	20040531	G	6310	CL422501	CLUTCH          	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					OUTER RACE	CRACKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						BLA50028					(CAN) ON START-UP THE PILOT HAD A CHIP LIGHT INDICATION, IMMEDIATELY SHUTDOWN AND INSPECTED THE FREEWHEEL CHIP DETECTOR.	   METAL CHIPS WERE FOUND.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005020100024	20050201	00024	SW  	2005	2	1	CA040610005      	1	20040607	G	2613	434422123	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	LT WING LE	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, WHILE STILL CLIMBING, THE LT WING LOWER HEAT BEGAN TO FLASH. THE LT BLEED AIR AND THE LT GE	NERATOR WERE TURNED OFF FLIGHT MANUAL PROCEDURES, AND THE AIRCRAFT TURNED BACK FOR THE DEPARTURE POINT. AFTER THREE MINU	TES THE LIGHT CONTINUED TO FLASH SO THE CAPTAIN SHUT DOWN THE LT ENGINE AS REQUIRED, AND LANDED WITHOUT FURTHER INCIDENT	. MAINTENANCE DISCOVERED THAT THE LT WING LEADING EDGE SENSOR SWITCH WAS ACTIVATING AT 140 F INSTEAD OF THE RATED 250 F.	  THE SWITCH WAS REPLACED AND THE SYSTEM TESTED SERVICEABLE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2005020100026	20050201	00026	EA  	2005	2	1	CA040610006      	2	20040609	G	7230		BLADE           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COMPRESSOR	DEPARTED        	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			A	Y	J	FLAME/FIRE                	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA								FA0016			(CAN) AN AIRCRAFT CARRIED AN EMERGENCY LANDING AFTER EXPERIENCING A NR 2 ENGINE FIRE INDICATION.  PRELIMINARY INFORMATIO	N ADVISES LPC BLADE DEPARTURE AND COMPRESSOR SEIZURE.  OIL WAS FOUND IN AND AROUND THE ENGINE AND NACELLE AREA AND HEAT 	DAMAGE WAS ALSO FOUND ON THE WIRING HARNESSES. FIRE BELIEVED TO HAVE BEEN CONTAINED WITHIN ENGINE. MFG INVESTIGATING THE	 ISSUE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005020100027	20050201	00027	EA  	2005	2	1	CA040610007      	1	20040608	G	7997	3043110	WIRE HARNESS    			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) ENGINE TEMPERATURE STARTED TO FLUCTUATE IN FLIGHT, MAINTENANCE TROUBLESHOT AND TRACED PROBLEM TO ENGINE,  SPLIT TH	E ENGINE AND FOUND THE TERMINAL END WAS LOOSE. THE FACTORY HAD NOT SOLDERED THE END ON PROPERLY. REPLACED THE HARNESS AN	D RETURNED PART TO MFG FOR WARRANTY.				1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA
2005020100028	20050201	00028		2005	2	1	CA040610008      	4	20040609	G	6113	055032111	BULKHEAD        	CESSNA      		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CORNER SECTION OF SPINNER AT LEADING EDGE OF PROPELLER BLADE CUT-OUT BADLY BENT (PEELED BACK) BY CENTRIFUGAL F	ORCE. THIS WAS CAUSED BY THE ADJACENT CORNER SECTION OF THE BACKPLATE (AROUND ANCHOR NUT) BREAKING OFF DURING OPERATION.	  NEW BACKPLATE DESIGN USED. (MOST CURRENT PN 0550321-12)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2005020100029	20050201	00029	NM  	2005	2	1	CA040610009      	1	20040606	G	2913	661732	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB FROM AIRPORT, NR 2 ENG HYD PUMP AND ASSOCIATED FLIGHT CONTROL CAUTION LIGHTS ALL ON HYD QTY 75 PERCEN	T.  ACTIVATED PTU, THEN PRESSURE RETURNED TO NORMAL.  AFTER LDG AND FLAPS SELECTED FOR LANDING, HYD QTY DECREASED TO 30 	PERCENT.  FLIGHT CONTROL C/LS ILLUMINATED AGAIN. CONTINUED LANDING WITHOUT FURTHER INCIDENT.  STOPPED ON TAXIWAY FOR TOW	ING TO GATE, AT THAT TIME HYD QTY WAS 0 PERCENT.   FOUND NR 2 EDP HANGER TRUNNION SCREWS, 1 MISSING AND 3LOOSE AND PACKI	NG BLOWN OUT. REPLACED EDP.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005020100030	20050201	00030	CE  	2005	2	1	CA040610010      	1	20040610	G	2820	040031158	LINE            			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			10205								(CAN) FUEL LINE ASSEMBLY LOCATION/LOCATED UNDER FLOOR AND UNDER CENTER CONSOLE. THIS LINE IS DIRECTLY FORWARD OF THE BEL	LY DRAIN. IT IS UP STREAM FROM THE GASCOLATOR AND DOWN STREAM OF THE FUEL SHUT-OFF.  FUEL SMELL WAS DETECTED. FUEL STAIN	ING WAS PRESENT.  THE LINE PASSES THROUGH A BULKHEAD.  THE LINE IS PROTECTED BY A GROMMET WHICH WAS INTACT.  THE LINE HA	D BECOME CORRODED AND PITTED AROUND THE GROMMET AREA AND DEVELOPED A PIN HOLE LEAK.  LINE WAS REPLACED.			1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2005020100052	20050201	00052	NE  	2005	2	1	CA040610011      	3	20040512	G	6110	8173881	SEAL            	HAMSTD      	14SF23      	DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 4 BLADE	INADEQUATE      	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						20010523					(CAN) DURING POST FLIGHT WALK AROUND OF AC FOLLOWING ARRIVAL, CREW IDENTIFIED CONSIDERABLE QTY OF LUBRICATING OIL HAD BE	EN LIBERATED FROM LT PROPELLER.  CREW TERMINATED FLIGHT AND CALLED FOR ENGINEERING ASSISTANCE. ENGINEERING INVESTIGATION	 REVEALED FAILURE OF PROP HUB TO PROP BLADE SEAL AT NR 4 BLADE POSITION.  NEW SEAL INSTALLED, FOLLOWING CONSIDERABLE CLE	AN UP,  AC WAS RETURNED TO SERVICE.  INSP OF REMOVED SEAL REVEALED SEAL TO BE FOR A 14SF TYPE PROP WITH A 14RF TYPE PROP	 GLAND SPRING SUPPLIED. SEAL IS FULLY TRACEABLE AND WAS SUPPLIED TO AIRLINE BY MFG AFTER ALLEGEDLY BEING INSPECTED BY MF	G FOR CORRECT CONFORMANCE OF SPRING ASSY.  14RF GLAND SPRING IS OF SMALLER DIAMETER WHEN COMPARED TO 14SF GLAND SPRING.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100054	20050201	00054	NE  	2005	2	1	CA040610012      	3	20040516	G	6110	8173881	SEAL            	HAMSTD      	14SF23      	DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 4 BLADE	TORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						20030916					(CAN) DURING POST FLIGHT WALK AROUND OF AC FOLLOWING ARRIVAL , CREW IDENTIFIED THAT CONSIDERABLE QTY OF LUBRICATING OIL 	HAD BEEN LIBERATED FROM THE LT PROPELLER. CREW TERMINATED FLIGHT AND CALLED FOR ENGINEERING ASSISTANCE. ENGINEERING INVE	STIGATION REVEALED FAILURE OF PROP HUB TO PROP BLADE SEAL AT NR4 BLADE POSITION.  NEW SEAL WAS INSTALLED, FOLLOWING CONS	IDERABLE CLEAN UP, AC WAS RELEASED TO SERVICE. ON ARRIVAL TO BASE AC  WAS WITHDRAWN FROM SERVICE AND ALL PROP BLADES WER	E REMOVED IN PRESENCE OF THE LOCAL MFG FIELD SERVICE REP.  SEALS WERE FOUND TO BE 14SF TYPE PROP SEALS RELEASED WITH 14R	F TYPE PROP SEAL GARTER SPRINGS INSTALLED.  NONCONFORMING BLADE SEAL WAS REPLACED.  AC HAS BEEN RETURNED TO SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100055	20050201	00055	EA  	2005	2	1	CA040610013      	2	20040520	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	LT MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			226  					L858848			(CAN) AFH: 8900.9 DATE: MAY 20 RT ENGINE -- LT MAGNETO,  DAMAGE WAS DISCOVERED DURING A 100HR INSPECTION.  DECIDED TO RE	MOVE THE LT MAGNETO FOR INSPECTION OF THIS AREA. (HAVE ADDED THIS TO OUR INSPECTION PROGRAM) WHEN THE MAGNETO WAS REMOVE	D THE MAGNETO GEAR RETAINER ASSY AND BEARING PULLED OUT OF THE ENGINE  TOGETHER WITH THE DRIVE COUPLING YET AGAIN. UPON 	FURTHER INSPECTION NO DAMAGE TO ENGINE.  ENGINE WAS REMOVED AND SENT FOR REPAIR TO THE BEARING RECESS AREA (MFG SI-1140)	REPAIR WAS CARRIED OUT.  ENGINE WAS RE-INSTALLED TO AIRCRAFT.  THE BEARING HAS 226. 5 HOURS.  THE ENGINE WAS REPAIRED (C	RANKCASE) BUT NOT OVERHAULED.  ENGINE TOTAL TIME 1337.0	1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA
2005020100056	20050201	00056	EU  	2005	2	1	CA040610014      	1	20040607	G	3231	HC323L0001000	SPRING          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NLG	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			35708								(CAN) UPON DEPARTURE, THE CREW REPORTED LOUD CLUNK NOISE UNDER FLIGHT DECK DURING GEAR RETRACTION.  MAINTENANCE INSPECTE	D AIRCRAFT AND FOUND LT NLG ASSIST SPRING ASSEMBLY HAD FAILED AND CAUSED A 12 X 8 HOLE IN UPPER NOSE WELL.  ASSISTOR SPR	ING WAS REPLACED AND HOLE WAS REPAIRED IAW THE PRINCIPALS OF RIL HC537H9252 AT ISSUE 1 IN REFERENCE TO BARA/AVR/6774/04-	DC.  GEAR SWINGS WERE CARRIED OUT AS SERVICEABLE AND AIRCRAFT WAS RETURNED TO SERVICE.  TIMES FOR THIS PART ARE LISTED A	S AIRCRAFT TIMES.		2	H	7	4 	4F	4	F		A49EU   	E6NE
2005020100057	20050201	00057	NM  	2005	2	1	CA040611001      	1	20040607	G	3310	RV4NBYSD502A	SWITCH          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	READING LIGHT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED BURNING SMELL IN THE COCKPIT.  MAINTENANCE FOUND THE DIMMER SWITCH OF THE CO-PILOTS READING LIGHT B	URNED THE SWITCH  PN RV4NBYSD502A WAS REPLACED AND A FUNCTION CHECK CARRIED OUT.  NO FURTHER PROBLEMS.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005020100058	20050201	00058	SO  	2005	2	1	CA040611002      	2	20040513	G	7414	10357164	COIL            	BENDIX      	S4LN21      	UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  	MCAULY	1B90	1B90CM      	GL  	MAGNETO	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						540710					(CAN) AIRCRAFT HARD TO START WHEN ENGINE IS HOT. CHECKED MAGNETO TO ENGINE TIMING.  COULD NOT GET RT MAGNETO (S/N 540710	) POINTS TO OPEN OR CLOSE. REMOVED MAGNETO FROM ENGINE AND FOUND GROUND ON COIL MISSING SCREW. COIL FOUND TO BE CRACKED 	AND OPAQUE IN COLOR INDICATING AD 94-01-03R2 AND MSB 644 HAD NOT BEEN ACCOMPLISHED.  TECHNICAL RECORDS INDICATE ENGINE J	UST HAD FIELD OVERHAUL. TIME ON ENGINE IS ONLY 14.3 HOURS.			1	L	7	1 	3O	3	O		A718    	E233	5	N	P842
2005020100059	20050201	00059	WP  	2005	2	1	CA040611003      	2	20040607	G	7250	310117015	PIN             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								P54202			(CAN) AC HAD A CHIP LIGHT ILLUMINATE DURING CRUISE.  PREVIOUS DAY A CHIP LIGHT ILLUMINATED AND A SMALL SLIVER OF METAL W	AS FOUND ON CHIP DETECTOR.  AN OIL SAMPLE WAS TAKEN AND SENT FOR ANALYSIS. AFTER ILLUMINATION OF CHIP LIGHT, ENGINE WAS 	REMOVED FOR INSP. UPON INSP IT WAS FOUND THAT HIGH SPEED PINION GEAR HAD COME LOOSE. MOUNTING NUTS WERE FOUND IMPROPERLY	 TORQUED, LOCK PINS HOLDING NUTS WERE FOUND INTACT BUT NUTS COULD STILL BE MOVED FREELY BY HAND.  BEARING RACE AND PINIO	N GEAR HAD INDICATIONS OF EXCESSIVE WEAR: 016 NUT MOVING WIDTH OF LOCK PIN BY HAND. 017 NOTE POSITION OF STAKE COMPARED 	TO 018018, COMPARE TO 017012, CLEARANCE BETWEEN NUT AND RACE. 013 CLEARANCE BETWEEN GEAR AND RACE.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2005020100060	20050201	00060	WP  	2005	2	1	CA040611004      	2	20040611	G	7250	310117017	PINION GEAR     			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54043			(CAN) OIL SAMPLE ANALYSIS FINDING RECEIVED FROM WEAR CHECK TO INSPECT ENG DUE TO SILVER IN OIL SAMPLE. DURING TEARDOWN, 	FOUND PINION GEAR BEARING CAGES, WHICH HAVE SILVER COATING APPLIED DURING MFG.  COATING HAD STARTED TO FLAKE OFF, CONTAM	INATING OIL.  MFG OF BRGS AND VENDOR WHO APPLIES SILVER TREATMENT HAVE BEEN NOTIFIED OF PROBLEM.  OUR STORES DEPT DOES N	OT HAVE ANY BEARINGS OF THIS TYPE IN STOCK, MFG HAS RESOLVED PROBLEM WITH SILVER TREATMENT PROCESS . OTHER BEARINGS OF T	HIS TYPE ARE INSTALLED IN ENGINE FLEET DO NOT APPEAR TO HAVE ANY PROBLEMS.  FURTHER BEARING PROBLEMS WILL APPEAR IN OIL 	SAMPLES AND CAN BE REPAIRED AS NEEDED WITHOUT ANY IMPACT ON SAFETY.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2005020100061	20050201	00061	NM  	2005	2	1	CA040611005      	1	20040608	G	2780	10608197	SWITCH          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					KRUEGER FLAP	INOPERATIVE     	W				A				UNSCHED LANDING         				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF AND DURING CLIMB IT WAS OBSERVED THAT THE LT OB KRUGER FLAP WAS NOT RETRACTED.  BOTH INDICATIONS SH	OWED THE KRUGER WAS STILL EXTENDED.  THE AIRCRAFT MADE AN UNSCHEDULED LANDING WITHOUT INCIDENT.  JUMPER ASSY WAS INSTALL	ED IAW B727-27-80-02, L/E FLAP JUMPER CABLE INSTALLATION, AND CHECKED SERVICEABLE.  THE AIRCRAFT WAS RELEASED FOR SERVIC	E.  NO FURTHER PROBLEMS DURING SUBSEQUENT FLIGHT.			2	L	7	3 	4F	4	F		A3WE    	E2EA
2005020100080	20050201	00080	NM  	2005	2	1	CA040611006      	1	20040518	G	2612	82455014003	FIRE DETECTOR   			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 1 ENGINE	FAILED          	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA			32830	32830							(CAN) DURING CRUISE FLIGHT NR 1 ENGINE FIRE WARNING , NR 1, NR 2 FIRE BOTTLES BLOWN TO NR 1 ENGINE, NO SMELL OR VISUAL I	NDICATION OF SMOKE/FIRE.  FIRE INDICATION PERSISTED, NR 1 ENGINE SHUT DOWN, AIRCRAFT DIVERTED TO NEARBY AIRPORT.  NORMAL	 LANDING CARRIED OUT WITH GROUND FIRE/RESCUE IN ATTENDANCE. NO EVIDENCE OF FIRE.  MAINTENANCE INSPECTION FOUND NO EVIDEN	CE OF FIRE, FIRE DETECTION LOOP FOUND FAULTY.  FIRE DETECTION LOOP AND FIRE BOTTLES REPLACED. AIRCRAFT RETURNED TO SERVI	CE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100082	20050201	00082	EU  	2005	2	1	CA040611007      	2	20040530	G	7510		DEICE SYSTEM    			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RIGHT	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) RT ENGINE DE-ICE FOUND INOPERATIVE, RETURNED TO DEPARTURE, STA NR 2 RELAY P/N CZ105648-2 REPLACED ENGINE INLET DE-	ICE RING COWL REPLACED.  HARNESS, P/N 6V10659 REPLACED FUNCTION TEST, SERVICEABLE					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005020100083	20050201	00083	EA  	2005	2	1	CA040611008      	1	20040608	G	5554	AB4A	BEARING         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	UNSERVICEABLE   	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA			23353								(CAN) PILOT DISCOVERED RUDDER MAKING SNAPPING NOISE WHILE CHECKING FREEDOM OF MOVEMENT AND RANGE FOR TRAVEL DURING PRE F	LIGHT WALK AROUND.  LOWER ATTACH BEARING OF RUDDER, FOUND TO HAVE FAILED ALLOWING RUDDER TO RUB ON ATTACHMENT MOUNT.  RU	DDER REMOVED AND BEARING REPLACED.  LOWER RUDDER ATTACHMENT MOUNT INSPECTED, NO FAULTS FOUND.  RUDDER RE-INSTALLED, RUDD	ER, RUDDER TRIM AND RUDDER GEARED TAB RIGGING CHECKED SERVICEABLE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2005020100084	20050201	00084	NE  	2005	2	1	CA040613001      	2	20040611	G	7260	755469D	IDG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1	INOPERATIVE     	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			2555 								(CAN) NR 1 IDG CAUTION MESSAGE CAME ON DURING TAKEOFF ROLL AND CREW ELECTED TO REJECT TAKEOFF.  ON WEEK PRIOR OR(JUNE 5)	, THE CREW RECEIVED A CAUTION MESSAGE (DURING CRUISE AT 31000 FEET) ON EICAS FOR APPROX 30 SECONDS WITH SYNOPTIC CHANGIN	G FROM GREEN TO YELLOW WHILE THE OUTPUT VOLTAGE REMAINED STEADY.  MAINTENANCE CARRIED OUT A VISUAL INSPECTION AND THEN A	S THE SNAG REOCCURRED, INITIALLY THE SYSTEM WAS DEFERRED IAW AS MEL PROCEDURE AND IDG WAS REPLACED AT THE SAME NIGHT HOU	RS SINCE INSTALLATION OF IDG.   TT 2555.34 AND 1576 CYCLES ON A 381 DAY PERIOD.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020100085	20050201	00085	NE  	2005	2	1	CA040614001      	2	20040610	G	7314	5008269H	PUMP            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) 2 MIN AFTER T/O, NR 2 ENG TORQUE WAS LOCKED AT 64 PERCENT.  NO CHANGE WITH THROTTLE MVMT.  NR 2 ENG FLAMED OUT. CR	EW WENT THROUGH EMERG CHECK LIST, SHUT ENGINE DOWN.  EMERGENCY WAS DECLARED, FLIGHT WAS GIVEN PRIORITY FOR LANDING.  FLI	GHT LANDED WITHOUT FURTHER INCIDENT.  UPON INVEST MAINT ISOLATED FAULT TO MECH FCU AND FUEL PUMP, BOTH REPLACED.  AC WAS	 RELEASED FOR TEST FLIGHT,  WHILE ATTEMPTING TO DO SO THE FLIGHT CREW REJECTED T/O AS THEY COULD NOT GET AUTO FEATHER TO	 ARM.  UPON FURTHER INVESTIGATION, MAINT VERIFIED RIGGING ON NR 2 ENG.  REPLACED BOTH TORQUE SIGNAL CAUTION UNITS P/N 30	005-0000-34 AND THE NR 2 ENG CONTROL UNIT  P/N 798213-2-002 . THE A/C WAS RELEASED FOR SECOND TEST FLIGHT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031000006	20050310	00006	NE  	2005	3	10	CA040614002      	2	20040614	G	7200	9324M70G06	ENGINE          			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					NR 4	FOD             	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			DE	DESCENT        	1			CA								741520			(CAN) APPROX 30 MINS FROM DEPARTURE, NR 4 ENG EGT OVERTEMPED AND CLIMBED TO 946 DEGREES AND WAS SHUT DOWN.  THERE WAS NO	 LOUD NOISE OR SHAKING. THE AC  MADE A NORMAL LANDING AND THE CFR WERE NOT CALLED OUT.  AC  REMOVED FROM SERVICE AND CP 	CONTACTED TO CARRY OUT T/SH.   NR 4 ENG PRELIMINARY BOROSCOPE INSPECTION SHOWS SIGNS OF METAL IN COMPRESSOR.  BORO PICTU	RES BEING E-MAILED TO MOC FOR ENGINEERING EVALUATION.			2	L	7	4 	4F	4	F	RT	A197    	E37NE
2005020100086	20050201	00086	SW  	2005	2	1	CA040614003      	1	20040610	G	6120	8975428	BETA SWITCH     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	INTERMITTENT    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P44663C			(CAN) LT BETA LIGHT ILLUMINATED IN FLIGHT.  AIRCRAFT RETURNED TO BASE, SWITCH REPLACED AND AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE
2005020100123	20050201	00123	CE  	2005	2	1	CA040614004      	1	20040610	G	5751	262400724	BELLCRANK       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AILERON	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPLETION OF MFG BULLETIN CAB03-4 ONE WELD WAS FOUND TO BE MISSING.  THE MISSING WELD WAS ON THE LOWER ARM	 INNER SURFACE DESCRIBED AS ITEM 6 IN FIGURE 1 OF CAB03-4.  ALL OTHER WELDS WERE PRESENT AND THE BELLCRANK SHOWED NO OBV	IOUS DAMAGE OR DISTORTION CAUSED BY THE MISSING WELD.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL
2005020100135	20050201	00135	NE  	2005	2	1	CA040614005      	2	20040612	G	8550	153084	TUBE            			DOUG  	DC4   	C54         	3021506	WP  	PWA   	R2000 	R20007M2    	52023	NE  					OIL DRAIN	INOPERATIVE     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE PILOTS NOTICED A DROP IN OIL QUANTITY ON THE NR 2 ENGINE.  THE ENGINE WAS SHUTDOWN AND PROPELLER	 FEATHERED. MAINTENANCE WAS CONTACTED AT ARRIVAL, THE OIL DRAIN TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	4 	4R	4	R		A762    	5E5
2005020100139	20050201	00139	NM  	2005	2	1	CA040614007      	1	20040611	G	7500		BELLOWS         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	BLEED SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33393	33393							(CAN) WHEN TAXING FOR DEPARTURE BOTH ENGINES WENT TO MANUAL MODE ON ECU. MAINTENANCE INSPECTION FOUND ECU'S HAD GONE TO 	MANUAL DUE TO IN EXCESS OF 49 DEG C ON SAT AIR PROBE.  FURTHER INSPECTION FOUND CROSSOVER BLEED PIPE ABOVE FUESLAGE JUST	 FORWARD OF DORASL FIN HAD CRACKED BELLOWS LEAKING HIGH TEMP BLEED AIR INTO WING CENTER SECTION , HEATING SAT AIR PROBE 	FROM THE BACK SIDE.  BLEED PIPE REPLACED.  AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100140	20050201	00140	EA  	2005	2	1	CA040614008      	1	20040607	G	2460	2TC125	CIRCUIT BREAKER 			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	COCKPIT	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			34992								(CAN) IN ORDER TO INSTALL A LIGHT ASSEMBLY IN THE NOSE COMPARTMENT THE L4 (CB) WAS PULLED IN THE COCKPIT. AFTER INSTALLA	TION WAS COMPLETED, CB WAS PUSHED BACK IN TO TEST SYSTEM, BY THE TIME THE INDIVIDUAL WALKED FROM THE COCKPIT BACK TO THE	 NOSE COMPARTMENT THERE WAS A BURNING ODOR AND THE WIRES GOING TO THE LIGHT WERE HOT.  THE INDIVIDUAL RAN BACK TO THE CO	CKPIT TO PULL THE CB AND FOUND IT SMOKING. AFTER AN UNSUCCESSFUL ATTEMPT TO MANUALLY OPEN THE CB, THE ONLY OTHER OPTION 	WAS TO SHUTOFF THE AIRCRAFT POWER TO STOP THE CURRENT FLOW TO THE SHORTED CIRCUIT.  CB WAS OLD, DIRTY AND CORRODED.  ALT	HOUGH THE SHORT CIRCUIT WAS CAUSED BY HUMAN ERROR THE CB SHOULD HAVE TRIPPED AND STOPPED THE CURRENT FLOW TO THE LIGHT.	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
2005020100141	20050201	00141	NM  	2005	2	1	CA040614009      	1	20040610	G	5751		SKIN            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AILERON TIP	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			31484	31484							(CAN) DURING APPROACH AIRCRAFT STRUCK BY LIGHTNING ,BOTH DC GENERATORS WENT OFF LINE. NR 2 DC GEN RE-SET, AIRCRAFT CONTI	NUED FOR NORMAL APPROACH AND LANDING.   NR 1 DC GENRE-SET AFTER ARRIVAL. INSPECTION FOUND DAMAGE TO THE RT AILERON TIP ,	 LOSS OF MOST OB STATIC WICK , FIBERGLASS T/E SPLIT OPEN APPROX. 6 INCHES, DAMAGE/PITTING TO AILERON OB BEARING.   AILER	ON AND BEARING REPLACED.  AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100142	20050201	00142	EU  	2005	2	1	CA040615001      	1	20040615	G	2750		CONTROL UNIT    			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					TE FLAPS	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) FAULT: ON FINAL APPROACH, WHEN FLAP 1 SELECTED, ONLY SLATS CAME OUT. NO FLAPS, RECYCLED TWICE NOJOY. SLATS ONLY LA	NDING CARRIED OUT.   ACFT OUT OF SERVICE FOR INVESTIGATION.  COMMENTS: FURTHER INFO WILL FOLLOW.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005020100179	20050201	00179	SW  	2005	2	1	CA040615002      	1	20040611	G	5210	206031620101	PIN             			BELL  	206   	206B1       	1181503	SW  										DOOR HANDLE	IMPROPER PART   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CREW AND PASSENGER, INTERIOR (D) SHAPED DOOR HANDLES FOUND TO HAVE LOCKING (SPRING PINS) TOO SHORT INSTALLED BY TH	E MANUFACTURER. MS171525 (.438 INCH LONG) INSTALLED INSTEAD OF MS171526 (.500 INCH LONG).					1	G	7	1 	3U				H2SW
2005020100195	20050201	00195	EU  	2005	2	1	CA040615003      	1	20040603	G	6710	12TW13	SWITCH          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COLLECTIVE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN PILOT PERFORMED THE HYDRAULIC ACCUMULATOR TEST THE HORN MALFUNCTIONED. THEN CARRIED OUT THE PRESSURE ISOLATIO	N CHECK ( NO HORN WHEN HYDRAULICS SWITCHED BACK ON).   ALL TEST WERE PERFORMED AGAIN AND HORN WAS NOT FUNCTIONING.  SWIT	CH ON PILOT COLLECTIVE WAS CHANGED AND AIRCRAFT WAS TESTED SERVICABLE AND RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005020100196	20050201	00196	SO  	2005	2	1	CA040615004      	2	20040610	G	8530		ROCKER BOSS     	CONT        		CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  	HARTZL	HC82V	HC82V*      	GL  	CYLINDER EXHAUST	BROKEN          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						35074					(CAN) ROCKER BOSSES BROKE OFF, FOR ROCKER SHAFT ON EXHAUST VALVE.						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P23EA
2005031000007	20050310	00007	NM  	2005	3	10	CA040615005      	1	20040611	G	3310	RV4NBYSD502A	RHEOSTAT        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LIGHT	UNSERVICEABLE   	W				H				DEACTIVATE SYST/CIRCUITS				B	O		SMOKE/FUMES/ODORS/SPARKS  	OTHER                     		CR	CRUISE         	1			CA			38676								(CAN)  RHEOSTAT (P/N RV4NBYSD502A) F/O OVERHEAD MAP LIGHT HAD SMOKE COMING FROM THE LIGHT AFTER IT WAS SWITCHED ON AND C	B P3 POPPED SHORTLY THERE AFTER.  OFFENDING PART POTENTIO METER 3311-R4 IPC REF 33-11-00 FIG 5 ITEM 75 NHA 82415155-001 	CABLE ASSY, RHEOSTAT WAS REPLACED AND SYS WAS FUNCTIONED WITH NO REOCCURRENCE OF PROBLEM, AND AC WAS RETURNED TO SERVICE	.  INCIDENT HAS BEEN BROUGHT TO THE ATTENTION OF OUR FLEET GROUP AND THEY IN-TURN SENT OUT  EMAIL TO THE MFG, AS THIS HA	S BEEN THE SECOND OCCURRENCE WE HAVE HAD.  INFORMATION WAS REQUESTED AS TO WHETHER OR NOT ANY OF THE OTHER OPERATORS HAV	E BEEN EXPERIENCING THE SAME FAULT AND IF THERE HAS BEEN ANY CHANGE AS OF LATE TO THE VENDOR OF THIS PARTICULAR PART.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100197	20050201	00197	SO  	2005	2	1	CA040615007      	2	20040513	G	7414	10357164	COIL            	BENDIX      		UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  	MCAULY	1B90	1B90CM      	GL  	MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						540756					(CAN) AIRCRAFT HARD TO START WHEN ENGINE IS HOT. CHECKED MAGNETO TO ENGINE TIMING AND COULD NOT GET RT MAGNETO (S/N 5407	10) POINTS TO OPEN OR CLOSE. REMOVED LT MAGNETO (S/N 540756) DUE TO PROBLEMS FOUND IN RT MAGNETO.  FOUND COIL CRACKED AN	D OPAQUE. AD 94-01-03R2 AND SB 644 HAD NOT BEEN ACCOMPLISHED IN LT MAGNETO S/N 540756. TECHNICAL RECORDS INDICATE ENGINE	 JUST HAD OVERHAUL  TTSN 14.3 HOURS.			1	L	7	1 	3O	3	O		A718    	E233	5	N	P842
2005020100198	20050201	00198	EA  	2005	2	1	CA040615008      	1	20040527	G	3244	H29X901516	TIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) NR 2 MLG TIRE SEPARATION/ RUPTURE ENGINE VIBRATION (N1) WAS DEPICTED ON EICAS AND FELT THROUGHOUT THE AIRCRAFT. TH	E FLIGHT CREW RETARDED THE POWER LEVERS TO REDUCE N1 VIB. TO WITHIN LIMITS. (FYI:AT 42 PERCENT N1 = 3.9 MILS). A/C DIVER	TED.  FLIGHT CREW POST FLIGHT CHECK WITNESSED 3 FAN BLADES SEVERELY DAMAGED INDUCED BYTHE NR 2 TIRE SEPARATION AND RUPTU	RE. THE IB FLAP SURFACE HAS SUSTAINED DAMAGE AS WELL.  FYI: THIS IS THE SIXTH OCCURRENCE SINCE MAY 11TH, 2004, ASSOCIATE	D WITH THIS MFG TIRE SEPARATION.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020100199	20050201	00199	EA  	2005	2	1	CA040615009      	1	20040513	G	3244	H29X901516	TIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PASSENGER DEPLANING, A RAMPER REPORTED THE LT IB TIRE SHOWN TIRE SEPARATION (TREAD MISSING) AND THE CORD SE	CTION WAS SHREDDED AND THE TIRE HAD POPED OUT IN SEVERAL AREAS.  UPON A CLOSURE LOOK, THE FLIGHT CREW NOTICED THE LT IB 	FLAP SURFACE HAD SUSTAINED DAMAGED AS WELL. LT NR 1 AND NR 2 TIRES REPLACED.  FLAP SURFACE PN 601R14002-1, SN SB/RJ/777 	REPLACED.  LT ENGINE INSPECTED AND NO DAMAGE WAS FOUND.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031000008	20050310	00008	EA  	2005	3	10	CA040615010      	1	20040520	G	3244	H29X901516	TIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING VIBRATION DETECTED. PILOTS' POST FLIGHT INSPECTION NOTICED NR 3 MLG TIRE HAD SEPARATED AND RUPTURED.  R	T IB FLAP WAS DAMAGED AS A RESULT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031000009	20050310	00009	EA  	2005	3	10	CA040615011      	1	20040504	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	DAMAGED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) SMOKE IN COCKPIT DUE TO LT WINDOW HEATER.  EMERGENCY DECLARED DUE TO DAMAGED INSULATION BLOCK, REPLACEMENT OF LT S	IDE WINDOW AND CONTINUITY CHECK OF SUPPLY WIRES NECESSARY.  TROUBLESHOOTING POINTS TO INTERNAL FAULT OF THE HEATER ELEME	NT TERMINAL BLOCK AT WINDOW 'MPE4HC'.  LT SIDE WINDOW REMOVED ACC. AMM 56-12-01-000-801. LT SIDE WINDOW IAW AMM 56-12-01	-400-801 INSTALLED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031000010	20050310	00010	GL  	2005	3	10	CA040615012      	1	20040615	G	5753	14573002	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGEJUST BELOW THE BOTTOM WING SKIN AB	OVE THE HINGE FAIRING.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2005031000011	20050310	00011	GL  	2005	3	10	CA040615013      	1	20040615	G	5753	14572002	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGEJUST BELOW THE BOTTOM WING SKIN AB	OVE THE HINGE FAIRING.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2005031000012	20050310	00012	GL  	2005	3	10	CA040615014      	1	20040615	G	5753	14571003	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGEJUST BELOW THE BOTTOM WING SKIN AB	OVE THE HINGE FAIRING.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2005031000013	20050310	00013	GL  	2005	3	10	CA040615015      	1	20040615	G	5753	14571004	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WING FLAP HINGE HAS INTERGRANULAR CORROSION ON THE LEADING EDGE OF HINGE JUST BELOW THE WING SKIN AND FLAP HINGE F	AIRING.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA
2005031000014	20050310	00014	NM  	2005	3	10	CA040615016      	1	20040615	G	2120	MS3106R10SL3S	CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	VALVE	OVERHEATED      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF THE CREW NOTED THE NR1 BLEED CONT CIRCUIT BREAKER POPPED.  UPON RETURN TO DEPARTING AIRPORT MAINTEN	ANCE FOUND THAT THE CONNECTOR PLUG CONNECTED TO THE BLEED PRESSURE REGULATING SHUT-OFF VALVE HAD BECOME OVERHEATED AND H	AD LOST IT'S INSULATING PROPERTIES.  THIS PLUG IS SUBJECT TO HIGH HEAT WHEN THE VALVE IS POWERED IN THE OFF SELECTED MOD	E.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800070	20050308	00070		2005	3	8	CA040615017      	4	20040615	G	2562	LR20	BATTERY         	DORNEMARGLN 																ELT	LEAKING         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA						42232					UNIT INSPECTED FOR CERTIFICATION AND BATTERY REPLACEMENT.  FOUND DURACELL BATTERIES (D-CELLS) LEAKING IN BATTERY COMPART	MENT.  BATTERIES REMOVED, AREA CLEANED, ALSO NOTED SURFACE CORROSION ON BATTERY CONTACT SPRING.  CORROSION REMOVED WITH 	ACID BRUSH AND IPA (ALCOHOL).  BATTERY BOX RE-INSPECTED, NEW BATTERIES INSTALLED, UNIT FUNCTION TESTED AND MET SPECIFICA	TIONS.
2005031000015	20050310	00015	SW  	2005	3	10	CA040616001      	1	20040420	G	6410	206016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										TAIL ROTOR	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAILROTOR BLADE OB DOUBLER, NEAR ROOT END OF BLABE, FOUND DEBONDED ON APPROX  6 INCHES.						1	G	7	1 	3U				H2SW
2005030800071	20050308	00071	GL  	2005	3	8	CA040616002      	2	20040615	G	7200		TURBINE WHEEL   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								CAT24288			(CAN) MAIN ROTOR WAS HARD TO TURN BACKWARDS INDICATING CARBON PROBLEMS.  AIRCRAFT WAS GROUND RUN AS PER MANUFACTURES REC	OMENDATIONS AND RELEASED FOR SERVICE AS TURBINE HAD FREED UP.  COMPANY HAD REMOVED AIRCRAFT FROM SERVICE AND RETURNED IT	 TO BASE.  ON REMOVAL OF TURBINE (TO SEND IT IN FOR CLEANING).  IT APPEARED TO HAVE PARTS OF TURBINE BLADES IN BURNER CA	N SECTION.			1	G	7	1 	3U	3	U		H2SW    	E4CE
2005030800072	20050308	00072	EU  	2005	3	8	CA040616003      	1	20040609	G	3230	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FROZEN          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			LD	LANDING        	1			CA											LANDING GEAR MOTOR CONTINUED TO RUN AFTER LANDING GEAR WAS DOWN AND LOCKED.  AIRCRAFT LANDED AND TAXIED TO APRON.  FLIGH	T CREW TURNED OFF MASTER TO STOP MOTOR FROM RUNNING.  MAINTENANCE WAS CALLED TO PULL UNDER FLOOR POWER PACK CIRCUIT BREA	KER.  MAINTENANCE CHECKED POWER PACK FOR A POSSIBLE OVER TEMPERATURE CONDITION BUT FOUND POWER PACK COOL.  AIRCRAFT TAXI	ED TO HANGAR.  LANDING GEAR MOTOR RELAY CONTACTS FOUND FROZEN IN THE CLOSED POSITION.  MAIN GEAR RELAY REPLACED, SYSTEM 	FUNCTION TESTED SERVICEABLE IAW PC12/45 MAINTENANCE MANUAL ATA CHAPTER 29.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800073	20050308	00073	EU  	2005	3	8	CA040616004      	1	20040604	G	2750	9733031216	SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	STICKING        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											FLAP DOWN SWITCH IS STICKING IN ALL ENVIRONMENTAL CONDITIONS CAUSING FLAP FAILURES BOTH IN FLIGHT AND ON THE GROUND.  BE	TTER SEALS OR DUST CAPS MAY SOLVE THE PROBLEM.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800074	20050308	00074	EU  	2005	3	8	CA040616005      	1	20040603	G	3246	15702100	FAIRING         			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			10271								CRACKS FOUND AROUND SCREW HOLES ON MAIN WHEEL FAIRING.  REOCCURRING PROBLEM ON MANY OF OUR AIRCRAFT.  AVERAGING 600 TO 7	00 HOURS PER FAIRING.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800075	20050308	00075	SW  	2005	3	8	CA040616006      	1	20040615	G	3230		UPLOCK HOOK     			SWRNGN	SA227 	SA227*      	       	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	MLG	LACK OF LUBE    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER THE AIRCRAFT TOOK OFF AND THE CREW SELECTED GEAR UP THE 'UNSAFE' GEAR WARNING LIGHTS REMAINED ON.  THE CREW SELECT	ED DOWN AND OBTAINED 3 GREEN LIGHTS AND RETURNED TO BASE.  MAINTENANCE WAS ABLE TO REPEAT THE PROBLEM ON THE GROUND ON G	EAR SWINGS.  THE UPLOCK HOOKS WERE NOT FULLY ENGAGING ON THE UPLOCK ROLLERS.  THE MECHANISMS WERE CLEANED AND LUBRICATED	 AND THE GEAR SWINGS WERE SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T			RT	A5SW    		6	C	3PNE
2005030800076	20050308	00076	EU  	2005	3	8	CA040616007      	1	20040609	G	3220	5322012078	BUSHING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											EXCESSIVE UP AND DOWN MOVEMENT FOUND IN STEERING SECTION OF NOSE LANDING GEAR.  BRONZE BUSHINGS FOUND TO BE WORN (P/N 53	2.20.12.078) IT IS BELIEVED THAT WHEN GREASING THE NOSE GEAR ASSEMBLY, THE CONTACT SURFACES OF THE BUSHINGS ARE NOT GETT	ING PROPER LUBRICATION BECAUSE THE SPLIT PINS THAT ARE USED TO RETAIN THE BUSHINGS ARE ALLOWING GREASE TO ESCAPE AND THE	REFORE GREASE IS NOT GETTING BETWEEN THE SURFACES.  PLUGGING THE HOLES IN THE SPLIT PINS MAY SOLVE THE PROBLEM BECAUSE T	HE GREASE WILL THEN BE FORCED UP TO THE BEARING CONTACT SURFACES.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800077	20050308	00077	EU  	2005	3	8	CA040616008      	1	20040603	G	5210	5521012187	HANDLE          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											INNER PASSENGER DOOR HANDLE BROKE OFF WHEN TRYING TO OPEN DOOR.  THIS IS A REOCCURRING PROBLEM BELIEVED TO BE CAUSED BY 	A COMBINATION OF FACTORS INCLUDING:1) CONDENSATION IN THE DOOR CAUSES TO UNLOCKING MECHANISM CABLE TO FREEZE.2) THE SPRI	NG USED ON THE SECONDARY LOCKOUT IS TOO WEAK.3) AND EXCESSIVE MACHINING OF THE DOOR HANDLE ITSELF.  BY INCREASING THE SP	RING TENSION AND REDUCING THE MACHINING DONE TO THE DOOR HANDLE THIS PROBLEM MAY BE REMEDIED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800078	20050308	00078	EU  	2005	3	8	CA040616010      	1	20040603	G	5210	5521012179	BRACKET         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											COUNTERBALANCE BRACKET ON PASSENGER DOOR FOUND CRACKED ON SCHEDULED INSPECTION.  THE BRACKET IS OFTEN FOUND LOOSE DUE TO	 THE RIVETS USED ON INSTALLATION ARE NOT OF SUFFICIENT STRENGTH.  RECOMMEND USING STRUCTURAL SCREWS OR BOLTS TO SECURE B	RACKET TO PREVENT FURTHER OCCURRENCES.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800079	20050308	00079	CE  	2005	3	8	CA040616011      	1	20040519	G	5220	50111302	DOOR            			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					EMERGENCY EXIT	SEPARATED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											AFTER TAKEOFF A GROWING WHISTLING SOUND DEVELOPED IN INTENSITY OVER PILOTS LEFT SHOULDER.  THERE WAS A LOUD POP OF A NOI	SE AND THE PILOT SAW THE STARBOARD EMERGENCY EXIT SELF EJECT OUT AND BACK FROM THE REST OF THE PLANE.  AIRSPEED WAS REDU	CED 170 MPH.  PLANE WAS CLEARED TO LAND WHICH WAS UNEVENTFUL.				1	L	7	2 	3O	3	O		A7CE    	E8CE
2005030800080	20050308	00080	WP  	2005	3	8	CA040617001      	1	20040610	G	3260		WARNING LIGHT   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					MLG	ILLUMINATED     	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											NOSE GEAR UNSAFE LIGHT ON WITH GEAR HANDLE DOWN DURING APPROACH IN XXX.  AIRCRAFT OVERSHOOT.  GEAR RESELECTED UP AND DOW	N WITH 3 LIGHTS ON.  MAINTENANCE DID A PSEV BITE CHECK AND ALL NOSE GEAR SWITCHES CHECKED FOR CORRECT GAP DISTANCE AND O	PERATION AND NO FAULT FOUND.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005030800081	20050308	00081	WP  	2005	3	8	CA040617002      	2	20040616	G	7250	310117017	BEARING         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54043			AN IMMEDIATE ENGINE INSPECTION WAS REQUESTED BY WEAR CHECK DUE TO MAJOR SILVER CONTENT IN THE OIL SAMPLE.  UPON INSPECTI	ON OF THE ENGINE GEAR CASE THE HIGH SPEED PINION BEARING AND CAGE WERE FOUND TO  HAVE THE SILVER COATING FLAKING OFF.  T	HIS PROBLEM IS IDENTICAL TO SDR20040611003.  ENGINE HAS BEEN REMOVED FROM THE AIRCRAFT FOR REPAIRS.  PICTURES: 019  HOLE	 IN OUTER RACE.020 ROLLERS SCRATCHED. 021 SILVER COMING OFF CAGE .022 SILVER COMING OFF CAGE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005030800082	20050308	00082	WP  	2005	3	8	CA040617003      	2	20040615	G	7250	310117015	BEARING         								GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54019			DURING A SCHEDULED ENGINE INSPECTION OF THE HIGH SPEED PINION ASSY A BRIGHT BLUECOLOR WAS NOTICED ON THE PINION GEAR.  T	HE HIGH SPEED PINION SUFFERED SEVERE HEAT DAMAGE CLOSE TO THE POINT OF FAILURE.  THIS PART WAS PURCHASED THROUGH AN AMER	ICAN PARTS DISTRIBUTOR AND CERTIFIED BY AN AMERICAN GARRETT OVERHAUL FACILITY.									4	T			E4WE
2005030800083	20050308	00083	SW  	2005	3	8	CA040617004      	1	20040614	G	3242	V151000	MASTER CYLINDER 			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					BRAKES	LOCKED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											DURING A MAINTENANCE RUN-UP AND SUBSEQUENT TAXI, THE BRAKES LOCKED UP AND THE AIRCRAFT COULD NOT BE MOVED.  BRAKE PRESSU	RE WAS RELIEVED AT THE BRAKE ASSY AND WAS FOUND THE NR 1 BRAKE MASTER CYLINDER HAD MALFUNCTIONED AND CAUSED THE BRAKES T	O LOCK UP.  REFERENCE AD 2002-08-02 ISSUED FOR THIS PROBLEM.  THIS AIRCRAFT IS IN COMPLIANCE WITH THIS AD.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005030800084	20050308	00084	SW  	2005	3	8	CA040617005      	1	20040614	G	3213	2752529003	PIN             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					SCISSOR LINK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A DAILY INSPECTION, IT WAS NOTICED THAT THE RT MAIN LANDING GEAR SCISSOR LINK UPPER PIN WAS FOUND BROKEN.  THE PI	N BROKE AT THE RETAINING HOLE IN WHICH A ROLL PIN IS INSTALLED.  IT WAS ALSO DETERMINED THAT THIS PIN WAS FOR A NOSE GEA	R INSTALLATION.  ALTHOUGH IT IS THE SAME SIZE AND FIT AS THE MAIN GEAR SCISSOR PIN THIS PART NUMBER PIN IS NOT ELIGIBLE 	FOR INSTALLATION ON THE MAIN GEAR SCISSOR LINK AS PER THE MANUFACTURERS IPC.  THE PIN WAS MOST LIKELY FRACTURED AT SOME 	POINT FROM REMOVAL OR INSTALLATION OF THE ROLL PIN WITH THE USE OF A PIN PUNCH.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005030800085	20050308	00085	EU  	2005	3	8	CA040617006      	1	20040608	G	2530	KR906931	RELAY           			AIRBUS	330   	A330322     	3930325	EU  	PWA   	4168  	PW4168      	 	NE  					COFFEEMAKER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0106					COFFEEMAKER WAS REMOVED DUE TO TRIPPING CIRCUIT BREAKER.  STRIP REPORT REVEALED THAT THE UNAPPROVED RELAY WAS FITTED TO 	THE COFFEEMAKER.  CORRECT P/N KR-90693-1 P/N FOUND KR 14DGE24.					2	L	7	2 	4F	4	F	RT	A46NM   	E36NE
2005030800086	20050308	00086	EA  	2005	3	8	CA040617007      	2	20040610	G	7322	324475319	FUEL CONTROL    			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								PCE86031			SHORTLY AFTER TAKEOFF, ON CLIMBING THROUGH 6,000 FT, PILOT NOTICED OVER TORQUE LIGHT ON FOR ENGINE NR 4.  A QUICK GLANCE	 AT OTHER ENGINE GAUGES TO CONFIRM ENGINE OVERSPEED, AND PULLED BACK THE POWER LEVER FOR NR 4 ENGINE TO SEE IF THERE WAS	 ANY RESPONSE.  PILOT THEN PULLED TEE HANDLE TO SHUT NR 4 ENGINE DOWN.  REST OF FLT AND LANDING UNEVENTFUL.  UPON INSPEC	TION OF ENGINE AND SUBSEQUENT REMOVAL OF FUEL CONTROL UNIT, DRIVE SHAFT BETWEEN THE FCU AND HP FUEL PUMP, FOUND TO BE SH	EARED OFF AND SO CAUSING ENGINE TO OVERSPEED.  DRIVE SHAFT SHEARED OFF WHERE DRIVE SPRING RETAINING CLIP GROOVE WAS ON D	RIVE SHAFT.  ENGINE AND ITS COMPONENTS WERE REPLACED WITH SERVICEABLE UNITS, AND GROUND RUNS CARRIED OUT SERVICEABLE.	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
2005030800087	20050308	00087		2005	3	8	CA040618002      	4	20040617	G	3130	S703100000	RECORDER        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	CABIN	BURNED          	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											CREW ESTABLISHED CRUSIE AT 16000 FEET, AC BUSS DETECTED ERRORS CAUSING SEVERAL AC RELATED COMPONENTS TO BECOME ERRONEOUS	.  CREW NOTED SMELL AND BLUE HAZE.  EVENTUALLY THE FDR 115AC C/B OPENED.  RETURNED TO DEPARTURE AIRPORT FOR INVESTIGATIO	N.  MAINTENANCE FOUND THE POWER SUPPLY BOARD WITHIN THE FDR HAD BLOWN A TRANSORB CAUSING THE ELECTRICAL SMELL AND SMOKE.	  ONCE THE 115AC HAD OPENED, THE VOLTAGE VARIATIONS BEING CREATED STOPPED AND ALL SYSTEMS RETURNED TO NORMAL, SAVE THE F	DR WHICH WAS LEFT UNPOWERED.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005030800088	20050308	00088	CE  	2005	3	8	CA040618003      	1	20040616	G	3340	S21605	SWITCH          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					LANDING LIGHT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											STUDENT PILOT AND INSTRUCTOR NOTED SMOKE COMING FROM LANDING LIGHT SWITCH AREA.  RETURNED TO BASE AND NOTIFIED MAINTENAN	CE.  SWITCH FOUND U/S, CIRCUIT BREAKER HAD NOT POPPED.  THIS HAS HAPPENED NUMEROUS TIMES BEFORE TO THIS TYPE OF SWITCH.					1	H	7	1 	3O	3	O	NT	3A19    	E223
2005030800089	20050308	00089	EA  	2005	3	8	CA040618004      	2	20040616	G	7322		ACCELL PUMP     	MARVELSCHEBX		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA						DT0105					ACCELERATOR PUMP ON THIS CARBURETOR PUSHES FUEL THRU A BRASS TUBE APPROX 3' LONG. TUBE IS PERMANENTLY MOUNTED TO CARB BO	DY AT LOWER SECTION OF VENTURI  ADJACENT TO ACCELERATOR PUMP. TUBE HAS A 90 DEGREE BEND NEAR WHERE IT ATTACHES TO CARB B	ODY & THEN TRAVELS VERTICALLY UP VENTURE APPROX 2'. TIP OF TUBE IS SHAPED TO FORM JET.  PARTS CAT FOR CARB DOES NOT SHOW	 A PN FOR TUBE.   PN 105055 IN THIS INSTANCE, CAME UNFASTENED FROM CARBURETOR & APPARENTLY SUCKED UP VENTURI & BECAME LO	DGED IN THROTTLE VALVE.  PILOT NOTED UNABLE TO PULL THROTTLE CONTROL BACK TO LESS THAN 2000 RPM.  BY CLIMBING, PILOT ABL	E TO SLOW AIRCRAFT ENOUGH TO SELECT FLAPS DOWN & MAKE A RELATIVELY NORMAL LANDING.   CARB REPLACED WITH SERVICEABLE.	1	H	7	1 	3O	3	O	NT	3A19    	E223
2005030800090	20050308	00090		2005	3	8	CA040618005      	4	20040618	G	2562	AK450	ELT             	AMERIKING   																CABIN	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											UPON ANNUAL INSPECTION ELT, IT WAS NOTED THAT THE MODULATION WOULD FAIL AFTER 10 SEC OF USE.  THE SOUND HEARD WOULD REMA	IN AS A ELT WARBLE WITH REDUCED VOLUME.  THIS FAULT HAD BEEN NOTED ON ONE OTHER UNIT EARLIER THIS YEAR.
2005030800091	20050308	00091	SW  	2005	3	8	CA040618006      	1	20040610	G	2710	2771004073	LINK ASSY       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27030								FOUND LEFT AND RIGHT LINK ASSY ON AILERON PUSH PULL TUBES CORRODED AND CRACKED ON ALL FOUR SIDES.  PARTS WERE REMOVED AN	D A NEW LINK ASSY WERE INSTALLED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005030800092	20050308	00092	NE  	2005	3	8	CA040618007      	2	20040617	G	7421	REB37E	SPARK PLUG      			DOUG  	DC4   	C54         	3021506	WP  	PWA   	R2000 	R20007M2    	52023	NE  					NR 4 ENGINE	FOULED          	W				E				ENGINE SHUTDOWN         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											DURING CRUISE, THE PILOTS NOTICED THE NR 4 ENGINE STARTING TO BACKFIRE, THE BACK FIRING WAS GETTING OUT OF CONTROL SO TH	E ENGINE WAS SHUT DOWN AND THE PROPELLER FEATHERED.  DURING THE INSPECTION OF THE NR 4 ENGINE IT WAS FOUND THAT THE FRON	T AND REAR SPARKS FOR THE NR 2 CYLINDER WERE FOULED.  THE PLUGS WERE REPLACED AND ENGINE RUN-UP WAS FINE.				2	L	7	4 	4R	4	R		A762    	5E5
2005030800093	20050308	00093	CE  	2005	3	8	CA040621001      	1	20040618	G	2730		CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ELEVATOR	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ELEVATOR MAIN TRIM CABLE FOUND RIDING BETWEEN ELECTRONIC TRIM SERVO DRUM AND GUARD.						1	L	7	2 	4F	4	F		A22CE   	E00053EN
2005030800094	20050308	00094	EU  	2005	3	8	CA040621002      	1	20040603	G	2750	5275212154	DRIVE ASSY      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											RT INBOARD FLAP DRIVE ARM FOUND CRACKED DURING SCHEDULED MAINTENANCE AT THE ATTACHMENT POINT OF THE FLAP INTERCONNECT CA	BLE.  FREQUENT FREEZING OF THE FLAP INTERCONNECT CABLE BELIEVED TO BE THE CAUSE OF PROBLEM.  PILATUS SB 27-010 STATES TH	AT THE DISCONNECTION OF THE INTERCONNECT CABLE WILL HAVE 'NO EFFECT ON AIRCRAFT SAFETY'.  THEREFORE, THE MAINTENANCE DEP	ARTMENT AND THE FLIGHT CREWS HAVE COME TO THE CONSENSUS THAT THE CABLE SHOULD BE PERMANENTLY REMOVED AND AN AMENDMENT MA	DE TO THE PILOTS OPERATING HANDBOOK.  REMOVAL OF CABLE CANNOT BE ACCOMPLISHED UNTIL APPROVAL IS GIVEN BY PILATUS.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800095	20050308	00095	SO  	2005	3	8	CA040621003      	1	20040616	G	2612	5064200	FIRE DETECTOR   			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					RT ENGINE	SHORTED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			AP	APPROACH       	1			CA											DURING APPROACH FOR LANDING, THE RT ENGINE FIRE WARNING ANNUNCIATOR ACTIVATED. THE PILOT DEPLOYED THE ENGINE FIRE BOTTLE	, SECURED THE ENGINE AND DECLARED AN EMERGENCY. THE LANDING CONTINUED UNEVENTFUL. MX INSPECTED THE ENGINE AND FOUND NO E	VIDENCE OF FIRE. THE FIRE DETECTION SYSTEM WAS INSPECTED AND EACH PROBE (3) WAS INDIVIDUALLY TESTED WITH THE MEGGER. TWO	 OF THE THREE WERE OK BUT ONE SHOWED A FAULT. FIRST ON THE LOW 0-200 OHMS RANGE AND IT SHOWED A RESISTANCE OF ABOUT 1 ME	G OHM AND IT SHOULD BE INFINITE OR OPEN. THEN I CHECKED IT AT THE 250 V SETTING AND THE RESISTANCE DROPPED TO BASICALLY 	NOTHING INDICATING SHORTED OR CORRODED CONTACTS. THE FAULTY PROBE WAS REPLACED NEW AND CIRCUIT TESTS C/O SATISFACTORY. A	1	L	7	2 	4T	4	T		A23SO   	E4EA
2005030800096	20050308	00096	EU  	2005	3	8	CA040621004      	1	20040604	G	2751	9733031215	SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FLAP UP SWITCH STICKING IN ALL ENVIRONMENTAL CONDITIONS CAUSING FLAP FAILURES IN FLIGHT AND ON GROUND.  FLIGHT CREWS SHO	ULD BE AWARE THAT IF FAILURE OCCURS AND FLAPS ARE SET AT 15, 30 OR 40.  THE ONBOARD COMPUTER WILL NOT GIVE THE AIRSPEED 	WARNING AT 165 KTS.  BETTER SEALS OR DUST CAPS MAY SOLVE THE PROBLEM.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800105	20050308	00105	EU  	2005	3	8	CA040621005      	1	20040609	G	2932	9738114304	PRESSURE SWITCH 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11297								LOW PRESSURE HYDRAULIC SWITCH (P/N 973.81.14.304) LEAKING FROM VENT HOLE. SIMILAR PROBLEMS FOUND WITH HIGH PRESSURE SWIT	CH (P/N 973.81.14.306).					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800106	20050308	00106	CE  	2005	3	8	CA040621006      	1	20040617	G	3320	2064862	RECEPTACLE      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					DOOR LIGHT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											COURTESY AND ENTRANCE DOOR LIGHTS REPORTED U/S.  TROUBLESHOOTING LED TO CONNECTOR P406 LOCATED IN THE AIRCRAFT SIDEWALL 	FORWARD OF THE ENTRANCE DOOR.  FOUND CONNECTOR PINS CORRODED, PRIMARILY PIN 7 THATSUPPLIES 28VDC TO THE CIRCUIT.  WIRING	 REPAIRED AND AIRCRAFT RELEASED.				1	L	7	2 	4T	4	T		A24CE   	E4EA
2005030800107	20050308	00107	EU  	2005	3	8	CA040621007      	1	20040604	G	3260	9733033111	PROXIMITY SWITCH			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			CA											NOSE GEAR DOWN PROXIMITY SWITCH NOT GIVING DOWN AND LOCKED INDICATIONS ON NOSE GEAR.  REOCCURRING PROBLEM AROUND THE 900	0-10000 CYCLE RANGE ON PC-12'S.  PC-12'S INCORPORATE THESE SWITCHES IN THE NOSE GEAR UP AND DOWN LOCK INDICATION POSITIO	NS THE MAIN GEAR UPLOCK POSITIONS AND THE MAIN GEAR WEIGHT ON WHEEL POSITIONS.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005030800110	20050308	00110	SW  	2005	3	8	CA040621008      	1	20040618	G	2910	206076022005	POWERPACK       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HYD SYSTEM	FAILED          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											IT APPEARS THAT THE HYDROPACK HAD AN INTERNAL GEAR FAILURE.  THE AIRCRAFT HAD NR INDICATIONS BUT NO HYDRAULIC PRESSURE. 	 HYDROPACK WAS CHANGED AND AIRCRAFT RETURNED TO SERVICE.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005030800112	20050308	00112	CE  	2005	3	8	CA040621010      	1	20040621	G	7603	2520851	THROTTLE CONTROL			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					COCKPIT	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											THROTTLE CONTROL WAS REPLACED AT A SCHEDULED INSPECTION RECENTLY AND HAS ALREADY COME LOOSE AT THE CRIMPED PIVOT END AFT	ER ONLY APPROX 160 HOURS TIS.  THIS PART WAS INSTALLED AS A NEW PART SUPPLIED FROM THE MANUFACTURER.  DEFECTIVE PART REM	OVED AND TO BE REPLACED WITH NEW PART				1	H	7	1 	3O	3	O	NT	3A12    	E274
2005030800124	20050308	00124	CE  	2005	3	8	CA040621011      	1	20040617	G	2752	511523716	ACTUATOR        			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	2D36C	2D36C*      	GL  	TE FLAP	WORN            	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											ON APPROACH, THE FLAPS WERE LOWERED TO 45 DEG BUT ONLY WENT TO 30 DEG.  THE AIRCRAFT LANDED SAFELY.  THE FLAP ACTUATOR I	NTERNAL GEARS WERE FOUND STRIPPED.  THE ACTUATOR WAS REPLACED WITH AN OVERHAULED UNIT.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P901
2004072900008	20040729	00008	NM  	2004	7	29	CA040622001      	1	20040621	G	2910	DSC252B40124	HOSE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE, THE CREW NOTICED SLOW BUT STEADY DEPLETION OF HYDRAULIC SYSTEM 2 . THE QUANTITY DOWN TO 2 QUARTS.  CREW R	ETURNED AIRCRAFT BACK WHERE MAINTENANCE PERSONAL UPON INVESTIGATION FOUND THE HOSE TO THE DRAG STRUT ACTUATOR IN THE NOS	E GEAR BAY LEAKING. THE HOSE WAS REPLACED WITH A NEW UNIT AND TESTS PERFORMED IAW ATA 32-30-31 AND A/C WAS RETURNED TO S	ERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900009	20040729	00009	EA  	2004	7	29	CA040622002      	1	20040608	G	3246		BRACKET         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	LT FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						385					(CAN) LT FLOAT REAR DOCK FITTING SADDLE BRACKETS CRACKED AT BOLT HOLES.						1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2004072900012	20040729	00012	CE  	2004	7	29	CA040622005      	1	20040606	G	2410	539547310	BELT            			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	ALTERNATOR	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ALTERNATOR DRIVE BELT CAME OFF IN FLIGHT.						1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P21EA
2004072900045	20040729	00045	CE  	2004	7	29	CA040622006      	1	20040611	G	5551	04320049	BRACKET         	CESSNA      		CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10465								(CAN) THE BRACKET OF THE STABILIZER ASSEMBLY WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL
2004072900053	20040729	00053	NE  	2004	7	29	CA040622007      	2	20040622	G	7530	311269001	VENTURI         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ADAPTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER SHUTDOWN DUE TO UNSUCCESSFUL TRIM RUNS, IT WAS DISCOVERED THAT THE ADAPTER VENTURI P3 BLEED AIR PIPE LOCATED	 ON THE NR 1 ENGINE (S/N TM123038) THERE WAS 1 INCH X 1 INCH HOLE IN THE PIPE. THERE IS A CRACK THAT HAS PROPOGATED AND 	CAUSED THE PIPE TO FAIL.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900054	20040729	00054	EA  	2004	7	29	CA040623001      	1	20040621	G	1430	AN316	NUT             			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540D4A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	CONTROL CABLE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION THE JAM NUTS THAT SECURE THE PROP CONTROL CABLE TO AN ATTACHMENT BRACKET AT THE PROP G	OVERNOR WERE FOUND LOOSE. THE LOWER JAM NUT HAD BACKED OFF COMPLETELY AND THE CABLE WAS FREE TO MOVE, BUT IN ONE DIRECTI	ON ONLY.  THE CONTROL CABLE IS SECURED TO THE ATTACHMENT BRACKET WITH JAM NUTS THAT ARE SECURED WITH INTERNAL TOOTH LOCK	WASHERS, BUT DO NOT HAVE HOLES FOR SECURING WITH LOCKWIRE.			1	H	7	1 	3O	3	O	 	A7EA    	1E4	5	C	P25EA
2004080400210	20040804	00210	NE  	2004	8	4	CA040623002      	2	20040605	G	7321	586982	DUMP VALVE      			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE FUEL	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA								638341			(CAN) AS COLLECTIVE WAS LOWERED FLIGHT CREW HEARD A (WHOOSH) SOUND FOLLOWED BY AN ENG N1 UNDER-SPEED WARNING AUDIO. FLIG	HT CREW VERIFIED ENG, IMMEDIATELY EXECUTED AN IN-FLIGHT SHUTDOWN OF NR 1 ENG TO PREVENT OVER-TEMP CONDITION. WITH NR 1 E	NG SHUTDOWN, AC RETURNED TO ITS SERVICE AREA WITHOUT FURTHER INCIDENT. INSP OF  ENG,  ITS RELATED CONTROL LINKAGES REVEA	LED NOTHING ABNORMAL.  ENG FUEL PRESSURIZING, DUMP VALVE (P&D VALVE) WAS CHANGED AS A STANDARD PROCEDURE IN A SOFT STALL	 OCCURRENCE. ADDITIONALLY, FCU WAS ALSO CHANGED AS PRECAUTIONARY MEASURE. ENG WAS RESTARTED, GROUND-RUN, FOUND TO BE ACC	EPTABLE AC WAS RELEASED FOR FLIGHT. THE SUSPECT COMPONENTS WERE RETURNED TO MFG FOR INTERNAL INSPECTION, EVALUATION.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA
2004072900055	20040729	00055	NM  	2004	7	29	CA040623004      	1	20040525	G	3250	89925	LINK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE LAYOVER CHECK THE STEERING LINK ON THE NOSE STEERING ACTUATOR WAS DISCOVERED TO HAVE A CRACKED EN	D FITTING WHERE THE CENTER PIVOT PIN PASSES THROUGH AND MATES WITH THE ADJOINING LINK.  THE END FITTING WAS STRETCHED OP	EN AND THE THIN RING END BROKEN AWAY. ALL LINKS AND PINS WERE REMOVED AND INSPECTED WITH NO ADDITIONAL DAMAGE DETECTED. 	THE DEFECTIVE LINK WAS REPLACED. THERE WAS NO INDICATION OF A STEERING PROBLEM REPORTED BY THE FLIGHT CREW.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900056	20040729	00056	EA  	2004	7	29	CA040623005      	1	20040623	G	3242	260414126629	HOUSING         	BFGOODRICH  		CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA18        	52026	NE  	HAMSTD	43E	43E60       	NE  	PISTON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0721					(CAN) HOUSING CRACKS FOUND AT OVERHAUL DURING LPI NDT OF BRAKE UNIT. THERE HAS BEEN PREVIOUS FINDINGS OF CRACKS IN SERVI	CE AND AT OVERHAULS OF OTHER BRAKE UNITS.  LEAKING BRAKE COULD BE INDICATION OF CRACKED BRAKE HOUSING.  EXCESSIVELY WORN	 BRAKE COULD PROMOTE DISTORTION OF HOUSING, CREATING CRACKING.				2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2004072900084	20040729	00084	EA  	2004	7	29	CA040623006      	1	20040604	G	1430	NAS620760D	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED MAIN PASSENGER DOOR DIFFICULT TO OPEN FROM OUTSIDE, HAD TO ENTER FROM SERVICE DOOR TO ACCESS AIRCRA	FT.  TRIED TO OPEN DOOR AND HANDLE WAS DIFFICULT TO TURN. MAINTENANCE FOUND AIRSTAIR PIVOT FITTING ASSEMBLY WAS SEIZED. 	 UPON DISMANTLING THE ASSEMBLY, IT WAS NOTED THAT THE BOLT P/N NAS6207-60D WAS CORRODED AND SEIZED PREVENTING FREE OPERA	TION WITHIN THE PHENLOIC BUSHING. ASSEMBLY WAS REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004072900086	20040729	00086	SW  	2004	7	29	CA040623009      	1	20040623	G	6410	206016201131	BLADE           			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					TAIL ROTOR	PERFORATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT REQUIREMENTS OF AD CF-2004-05(BHTC ASB 206L-04-127 REV A) A PIN HOLE IN THE EPOXY FILLER, APPRO	XIMATELY .012 IN. DIA, INTRUDING INTERNALLY, WAS FOUND.  WATER WAS OBSERVED DRAINING FROM THE HOLE.  BLADE HAS BEEN SCRA	PPED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004072900087	20040729	00087	CE  	2004	7	29	CA040624001      	1	20040617	G	7120	R2070011	MOUNT           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE MOUNT REPLACEMENT IT WAS NOTICED THAT THE NEW MOUNTS WERE MANUFACTURED WITH THE BEVEL ON THE WRONG S	IDE OF THE METAL PART OF THE CORE (R20700-11).  THE CORE IS MADE OF RUBBER SANDWICHED BETWEEN TWO PIECES OF METAL. THE B	EVEL IS THERE TO ALLOW THE INSERTION OF THE HAT BUSHING, THESE PARTS ARE ASSEMBLED WITH AN INTERFERENCE FIT, WITHOUT THE	 BEVEL IT IS VERY DIFFICULT/ IMPOSSIBLE TO INSERT THE BUSHING. STOCK WAS CHECK AND THREE MORE KITS WERE FOUND IN THE SAM	E CONDITION. THE PARTS WERE REJECTED.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC
2004072900088	20040729	00088	EA  	2004	7	29	CA040624003      	2	20040617	G	7313	25245009	INJECTOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	MALFUNCTIONED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE EXPERIENCED POWER LOSS.  MANIFOLD PRESSURE WENT FROM 32 - 20 INCHES.  FLIGHT CREW MADE UNSCHEDULED LANDING 	WITHOUT INCIDENT.  ENGINEER FOUND THAT SERVO FUEL INJECTOR WAS THE PROBLEM AND HAD FLOODED OUT THE ENGINE. ENGINEER REPL	ACED SERVO FUEL INJECTOR WITH SERVICEABLE UNIT. RAN UP A/C ALL CHECKED OUT AND A/C RETURNED WITHOUT FURTHER PROBLEMS. A/	C HAS BEEN FLYING SERVICEABLE SINCE THEN.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004072900089	20040729	00089	EU  	2004	7	29	CA040624004      	1	20040614	G	2572	DHS78212010	HOLDER          			UROCOP	EC155 	EC155B      	8681000	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					FUSE	LOOSE           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AC HAS THREADED TYPE FUSE HOLDERS. IN CRUISE, LOST OIL PRESSURE INDICATION ON NR 2 ENGINE.  LOW PRESSURE LIGHT DID	 NOT COME ON, (IT'S ON A SEPARATE PRESS SWITCH).  PILOT REDUCED NR 2 ENG TO IDLE. TEMP REMAINED NORMAL WITH NO OTHER CHA	NGES IN SYSTEMS. AN UNEVENTFUL LANDING WAS COMPLETED.  INVESTIGATION REVEALED FUSE HOLDER HAD VIBRATED LOOSE AND CAUSED 	FUSE FOR OIL PRESSURE INDICATION TO LOSE CONTACT CAUSING A POWER LOSS FOR THE INDICATOR.  ABOUT 10 OTHER FUSE HOLDER CAP	S WERE ALSO FOUND LOOSE.  FUSE HOLDER HAS NO POSITIVE LOCKING FEATURE AND AS A RESULT, NOW WILL BE CHECKING PERIODICALLY	. THOUGH NOT A TERRIBLY SERIOUS ISSUE IT IS ONE THAT DESERVED MENTION AS OTHER MFG PRODUCTS MAY USE SAME FUSE HOLDER.	1	G	7	2 	3U	3	U		H10EU   	E00054EN
2004072900090	20040729	00090	SW  	2004	7	29	CA040624005      	1	20040524	G	5302	206030329103	FITTING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FORWARD UPPER LT TAILBOOM ATTACHMENT FITTING FOUND CRACKED DURING 200 HOUR INSPECTION.  MFG INSPECTION CALLS FOR S	PECIAL ATTENTION TO THIS AREA DURING THE INSPECTION.  THIS IS A KNOWN PROBLEM AREA.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2004072900091	20040729	00091	CE  	2004	7	29	CA040624006      	1	20040623	G	3230	583800901	MOTOR           			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) UPON REPLACEMENT, TESTING OF LANDING GEAR MOTOR RECEIVED FROM AN APPROVED OH FACILITY IT WAS DETERMINED MOTOR WAS 	SPINNING IN REVERSE DIRECTION.  MOTOR WAS REMOVED AND BENCH TESTED TO ELIMINATE AN AC WIRING PROBLEM.  MOTOR ROTATED IN 	WRONG DIRECTION AGAIN DURING BENCH TEST AS WELL. MAJOR DAMAGE TO LANDING GEAR COMPONENTS CAN OCCUR DUE TO REVERSE OPERAT	ION OF THIS MOTOR.  DUE TO PROPER TESTING BY MAINT MOTOR WAS NOT ALLOWED TO RUN LONG ENEOUGH TO CAUSE ANY DAMAGE TO THE 	LANDING GEAR COMPONENTS. THE OVERHAUL FACILITY WAS CONTACTED AND ADVISED OF THE PROBLEM AND WERE HELPFUL IN DETERMINING 	THE PROBABLE CAUSE OF THE MOTOR MALFUNCTION. THE MOTOR HAS BEEN RETURNED TO OVERHAUL FACILITY FOR TESTING AND REPAIR.	1	L	7	2 	3O	3	O	 	3A16    	1E10	5	C	P920
2004072900092	20040729	00092	EU  	2004	7	29	CA040624007      	3	20040621	G	6111		STRIP           	ROTOL       	R212        	BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	PROP BLADE LE	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA						DRG56567					(CAN) DEPARTING, AN UNUSUAL NOISE WAS DETECTED FROM THE NR 2 ENGINE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. THE LE	ADING EDGE PROTECTION STRIP ON ONE BLADE WAS SEPARATED 6 INCHES AT THE OB END.  MAINTENANCE REMOVED THE STRIPS FROM ALL 	4 BLADES AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER GROUND RUN YIELDED NO VIBRATION OR UNUSUAL NOISE.				2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899
2004080500026	20040805	00026	NE  	2004	8	5	CA040624008      	2	20040622	G	7200		ENGINE          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING TAKE-OFF, THE CREW REPORT THAT THEY HAD HEARD A BANG.  ALL ENGINE PARAMETERS WERE NORMAL.  THE AIRCRAFT MAD	E AN UNSCHEDULED LANDING.  ALL ENGINES WERE PHYSICALLY INSPECTED WITH NO APPARENT DAMAGE.   ALL 3 ENGINES WERE STARTED, 	POWERED UP AND REVERSERS DEPLOYED.  ALL ENGINES WERE CHECKED SERVICEABLE IAW MM 71-00 AND PWA MM 71-00-00.  THE AIRCRAFT	 WAS RELEASED AND NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004101800040	20041018	00040	CE  	2004	10	18	CA040624009      	1	20040513	G	7500	W99124CE	COUPLING        			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					BLEED AIR SYS	FAILED          	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA											(CAN)A/C HAD BEEN MODIFIED AT FACTORY TO REMOVE FLEX COUPLING AND TUBE ARRANGEMENT OF S/N 0001 THRU 0129 BLEED AIR SYSTE	MS (REF. IPC36-10-00-01 SHEET 1 OF 4 DETAIL B) AND INSTALL FLEX COUPLING AND TUBE ARRANGEMENT OF S/N'S 0130 THRU 0184.  	THIS UPGRADED ARRANGEMENT HAS SOME INHERENT ALIGNMENT DIFFICULTIES.  ON TWO OCCASIONS (ONCE ON LT ENGINE AND SECOND ON R	T ENGINE) COUPLING P/N W991-24CE FAILED TO REMAIN LATCHED AND JOINT SPREAD OPEN RESULTING IN A BLEED AIR LEAK.  PILOT NO	TICED A SHARP INCREASE IN ITT WITH POWER LEVER ADVANCES.  ON BOTH OCCASIONS THE FAILURE OCCURRED DURING THE PREFLIGHT RU	N UP.  INSPECTION OF THE COUPLINGS DID NOT REVEAL SIGNIFICANT WEAR.  COUPLINGS AND SEALS WERE REPLACED WITH NEW PARTS.	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL
2004080500033	20040805	00033	NM  	2004	8	5	CA040625001      	1	20040423	G	2910	3158223	CHECK VALVE     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH AND AFTER LANDING GEAR DOWN SELECTION COMPLETED, NR 2 HYDRAULIC SYSTEM INDICATED LOSS OF ALL FLUID. AP	PROACH TO LANDING WAS CONTINUED, FOLLOWING A NORMAL LANDING, CREW INSPECTED AC AND CONFIRMED A SIGNIFICANT HYD LEAK FROM	 AIRCRAFT'S EMPENNAGE AREA. FLIGHT WAS TERMINATED AND ENGINEERING ASSISTANCE REQUESTED. ENGINEERING INVESTIGATION CONFIR	MED METAL FATIGUE FAILURE OF A CHECK VALVE BODY, WHICH ALLOWED LIBERATION OF ALL OF NR 2 HYDRAULIC SYSTEM FLUID TO ATMOS	PHERE.  FAILED CHECK VALVE WAS REPLACED AND FOLLOWING SERVICING OF THE NR 2 HYDRAULIC SYSTEM AIRCRAFT WAS RETURNED TO SE	RVICE. IT WAS NOTED THAT  INSIDE OF THE VALVE SHOWED SIGNS OF CORROSION. TSN=11366.21 HRS	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080500034	20040805	00034	NM  	2004	8	5	CA040625002      	1	20040624	G	2612		FIRE LOOP       			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 3 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, NR 3 ENGINE FIRE WARNING INDICATION WAS ACTIVATED.  BELL WAS INTERMITTENT BUT BECAME A LITTLE MORE 	STEADY.  EMERGENCY PROCEDURES WERE INITIATED AND NR 3 ENGINE WAS SHUTDOWN.  FIRE HANDLE WAS PULLED BUT NOT TO RELEASE EX	TINGUISHING AGENT.  ATC WAS NOTIFIED.  AIRCRAFT LANDED WITHOUT INCIDENT WITH EMERGENCY VEHICLES ON SITE.  AIRCRAFT WAS S	HUTDOWN. MTCE ACCESSED THE SITUATION.  AN ELECTRICAL SHORT WAS FOUND IN THE NR 3 ENGINE FIRE LOOP SYSTEM.  THE AIRCRAFT 	WAS RUN UP WITH NO FURTHER PROBLEMS. THE AIRCRAFT WAS RELEASED.  NO FAULT DURING SUBSEQUENT FLIGHT.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004080500035	20040805	00035	NM  	2004	8	5	CA040625003      	1	20040624	G	5530		CASTING         			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE CHECK A CRACK WAS FOUND ON THE SPIDER CASTING AT RUDDER STATION 23.27 BELOW THE STANDBY RUDDER 	PCU IN THE VERTICAL STABILIZER.   THE CRACK IS 3 INCHES IB OF OUTER EXTREMITIES, 7 INCHES FORWARD OF THE LOWER RUDDER HI	NGE POINT APPROX 1.5 INCHES LONG AND .6250 INCHES FROM THE BASE.  CRACK REPAIRED WITH AN EXTRUSION ANGLE IAW INSTRUCTION	S FROM MFG MESSAGE 1-31239593. TIMES, 61592.12  CYCLES 59677.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004080500036	20040805	00036	NM  	2004	8	5	CA040625004      	1	20040624	G	2782		ACTUATOR        			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SLAT	INOPERATIVE     	W				O				OTHER                   				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CL	CLIMB          	1			CA											(CAN) NR 6 LEADING EDGE SLAT WAS SLOW TO RETRACT ON DEPARTURE. AFTER IT DID RETRACT IT RE-EXTENDED FOR ABOUT 5 MINUTES T	HEN RETRACTED AGAIN. CREW WAS ALERTED BY SLAT INDICATION OF THE REDEPLOYMENT AND VISUALLY CONFIRMED THE EXTENSION AND RE	TRACTION. NO OTHER ACTION TAKEN AND THE CREW CONTINUED TO DESTINATION.  MAINTENANCE REPLACED THE NR 6 SLAT ACTUATOR AND 	THE AIRCRAFT WAS RELEASED FOR SERVICE. ACTUATOR SENT TO SHOP FOR EVALUATION AND A FULL REPORT HAS BEEN REQUESTED.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004080500037	20040805	00037	NE  	2004	8	5	CA040625005      	2	20040622	G	7510	39271611	MODULATING VALVE			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 1 BLEED SYS	LEAKING         	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB IT WAS OBSERVED THAT THE NR 1 ENGINE STRUT OVERHEAT LIGHT CAME ON.  IAW OPS CHECKLIST, SYSTEM CHECK C	ARRIED OUT AND FLIGHT CONTINUED WITHOUT INCIDENT. AFTER LANDING, INSPECTION WAS CARRIED OUT AND THE HIGH PRESSURE MODULA	TING AND SHUTOFF VALVE WAS FOUND LEAKING.  THE VALVE WAS REPLACED.  LEAK CHECK CARRIED OUT AND CHECKED SERVICEABLE IAW M	M 26-12-41.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004080500038	20040805	00038	NE  	2004	8	5	CA040625006      	2	20040624	G	7510	600231	SHUTOFF VALVE   			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					13TH STAGE DUCT	LEAKING         	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB NR 1 ENGINE STRUT OVERHEAT LIGHT ILLUMINATED.  OPS CHECKLIST CARRIED OUT. AIRCRAFT WAS RETURNED TO BA	SE DUE TO SECOND INCIDENT IN 2 DAYS. DURING INSPECTION, NR 1 ANTI ICE VALVE SEALS WERE REPLACED.  NR 1 BLEED SHUT OFF VA	LVE WAS REPLACED IAW MM 36-10-01.  HIGH POWER RUNS WERE CARRIED OUT.  NO LEAKS FOUND AND NR 1 ENGINE STRUT OVERHEAT LIGH	T DID NOT ILLUMINATE AFTER THE 15 MINUTE RUN.  NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004080500039	20040805	00039	GL  	2004	8	5	CA040625007      	2	20040623	G	7200		ENGINE          			EMB   	145   	EMB145XR    	3260214	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					NR 2	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA								CAE312406			(CAN) PRELIMINARY REPORT THE CREW REPORTED THAT ON DESCENT, THE NR 2 ENGINE FAILED (UNCOMMANDED SHUT DOWN). THE AIRCRAFT	 LANDED WITHOUT INCIDENT.  ON GROUND, THE FAN WOULD NOT ROTATE FREELY, BUT CORE COULD NOT BE ROTATED VIA PMA SHAFT.  ENG	INE ALLOCATED TO RRC, FURTHER DETAIL WILL BE SUBMITTED AFTER ENGINE STRIP.				2	L	7	2 	4F	4	F	RT	        	TE6CH
2004080500060	20040805	00060	SO  	2004	8	5	CA040625008      	1	20040624	G	3720	441CC7	DRIVE SHAFT     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	VACUUM PUMP	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						109514					(CAN) ON LT ENGINE WARMING UP, FOUND LIGHT WARNING INDICATION (ON) IN RANGE OF RPM.   WHILE TROUBLESHOOTING FOUND LT VAC	UUM PUMP DRIVE SHAFT SHEARED.  NO OTHER DAMAGE FOUND AT VISUAL INSPECTION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2004080500073	20040805	00073	NM  	2004	8	5	CA040625009      	1	20040623	G	2910	AE2463510E0124	HOSE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			33370	33370							(CAN) ON SELECTING GEAR RETRACTION AFTER TAKE-OFF , LOSS OF 32 SYSTEM HYDRAULIC FLUID.  CAUTION LIGHTS FOR NR 2 HYD ISOL	ATION SYSTEM AND NR 2 HYD PUMP.  AIRCRAFT RETURNED TO DEPARTURE AIRPORT AND USED ALTERNATE GEAR EXTENSION SYSTEM.  NORMA	L LANDING. MAINTENANCE INSPECTION FOUND NLG UP LOCK HYDRAULIC LINE FAILED.  LINE REPLACED, HYDRAULIC SYSTEM SERVICED AND	 AIRCRAFT RETURNED TO SERVICE. THIS PART IS TRACKED AS AN EXPENDABLE AND ACCURATE PART.   COMPANY HAS IN HOUSE TASK TO R	EPLACE THIS LINE AT A C1 CHECK IF MANUFACTURE DATE CODE IS IN EXCESS OF 8 YEARS.  LAST C1 CHECK ON THIS AIRCRAFT NOV/200	3.  HOSE DATE CODE 1/97.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080500074	20040805	00074	NE  	2004	8	5	CA040628001      	2	20040616	G	8500	R1340S3H1G	ENGINE          			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	23D	23D40       	NE  		FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								R327203			(CAN) ENGINE SEIZED IN CRUISE FLIGHT. CASE BROKEN.						1	H	7	1 	3R	3	R	 	A815    	5E2	6	C	P719
2004080500075	20040805	00075	EA  	2004	8	5	CA040628002      	1	20040626	G	2497	AA4N	CONTACTOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ENGINE NACELLE	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ENGINE START AND GPU REMOVAL THE PASS DOOR, BAG DOOR, FWD DOOR, AND SERVICE DOOR LIGHTS WERE FLASHING, WE RE	CONNECTED THE GPU, AND SHUTDOWN THE BOTH ENGINES. LIGHT SMOKE WAS OBSERVED FROM THE LT NACELLE AIRCRAFT WAS DEPLANED. TH	E AMOUNT OF SMOKE INCREASED AND FIRE BOTTLES WERE DICHARGED AND ALL POWER SHUT OFF.  FOUND THE 2431K1 RELAY SHORTED, REL	AY AND STARTER REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080500076	20040805	00076	NM  	2004	8	5	CA040628003      	1	20040624	G	2421	69432851	DUCT            			BOEING	737   	7372T2      	1384491	NM  	PWA   	JT8   	JT8D17      	52049	NE  					GENERATOR COOL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLT CREW FELT A TRANSIENT VIBRATION ON ENGINE SPOOL-UP, WITH NO INDICATION FROM EITHER ENGINE VIBRATION METER. ALS	O SLIGHT VIBRATION IN CRUISE, WITH NO INDICATION ON EITHER ENGINE VIBRATION INDICATOR. FLT CREW ISOLATED THE PROBLEM TO 	NR 2 ENGINE. AC WAS SWAPPED AFTER MAINT DISCOVERED THAT AC GENERATOR COOLING DUCT PLATE WAS BROKEN AND CAUSING A LARGE C	OOLING AIR LEAK. PLATE WAS REPLACED AND GROUND RUNS CONFIRM NO VIBRATION.  OPERATOR WILL ISSUE A FLEET CAMPAIGN TO INSPE	CT AC GENERATOR COOLING DUCT PLATES OF REMAINING AIRCRAFT. THIS FLEET CAMPAIGN WILL BE COMPLETED WITHIN 60 DAYS. THE FOL	LOWING IS AN EXACT FROM THE IPC. ITEM NR 170 PN 69-43285-1 IS THE PART WHICH FAILED.	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004080500077	20040805	00077	CE  	2004	8	5	CA040628004      	1	20040628	G	7603	2520851	CONTROL CABLE   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	THROTTLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS IS THE SECOND OCCURRENCE OF SUCH A DEFECT NOTED BY THE SAME OPERATOR WITHIN THE PAST FEW WEEKS. THE SWAGED SW	IVEL JOINT ON THE THROTTLE CONTROL WAS NOTED TO BE WORN TO THE POINT WHERE THE BALL END COULD BE REMOVED FROM ITS SWAGED	 SOCKET WITH EASE. DEFECT WAS DISCOVERED DURING ROUTINE INSPECTION.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004080500078	20040805	00078	WP  	2004	8	5	CA040628005      	1	20040625	G	7922	315341	DOOR            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					OIL COOLER	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT THE FLT CREW NOTICED THE OIL TEMPERATURE RISING TO THE RED LINE. THE OIL COOLER SWITCH WAS SELECT	ED FROM (AUTO) TO (MANUAL) OPEN WITH NO RESOMNSE. THE OIL TEMPERATURE CONTINUED TO CLIMB. THE ENGINE WAS SHUT DOWN ANDTH	E PROP WAS FEATHERED. THE AIRCRAFT RETURNED TO BASE. DURING TROUBLESHOOTING, MAINTENANCE STAFF FOUND THE OIL COOLER DOOR	 ACTUATOR WAS INOPERATIVE. THE OIL COOLER DOOR ACTUATOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4R	4	T	 	6A6     	E282
2005012400020	20050124	00020	NE  	2005	1	24	CA040628006      	2	20040625	G	8550	493476	O-RING          	PWA         		CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						NK510954					(CAN) DURING A PRESCOOP GEOGRAPHICAL CHECK, THE FIRST OFFICER NOTED A MAJOR OIL LEAK ON THE NR 2 ENGINE. THE ENGINE WAS 	SHUTDOWN, THE PROP WAS FEATHERED AND THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION BY MAINTENANCE, IT WAS NOTED THAT	 ONE OF THE BMEP PLUG O-RINGS HAD FAILED CAUSING THE OIL LEAK. THE O-RING WAS REPLACED ENGINE GROUND RUN AND LEAK CHECKE	D SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2005020100036	20050201	00036	CE  	2005	2	1	CA040628008      	1	20040628	G	5330		SKIN            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMBINATION VHF/GPS ANTENNA DOUBLER AND FUSELAGE SKIN CRACKED UNDER ANTENNA WHICH WAS ENGINEERED AND INSTALLED IAW	 LSTC  NR C-LSA01-625/D.  FUSELAGE REPAIRED AND ANTENNA REMOVED.  NEW REPAIR DOUBLER INSTALLED.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005020100037	20050201	00037	CE  	2005	2	1	CA040628009      	1	20040628	G	5330		SKIN            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMBINATION VHF/GPS ANTENNA DOUBLER AND FUSELAGE SKIN CRACKED UNDER COMANT ANTENNA WHICH WAS ENGINEERED AND INSTAL	LED IAW LSTC  NR C-LSA01-625/D.  FUSELAGE REPAIRED AND ANTENNA REMOVED. NEW REPAIR DOUBLER INSTALLED.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005020100038	20050201	00038	SO  	2005	2	1	CA040628010      	1	20040624	G	2750		HANDLE          			MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	O540J1A5    	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	TE FLAPS	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) UPON DESCENT, THE PILOT PULLED ON THE FLAPS, ONLY TO FIND THAT THE HANDLE BROKE AWAY AFTER THE FIRST KNOTCH WAS AC	HIEVED.  MADE A SLOW TRIP BACK TO BASE, WHERE AFTER EXAMINATION, THE HANDLE WAS FOUND BROKEN AT THE BOTTOM HOLE WHERE TH	E FLAP RATCHET ACTUATING ROD EXITS THE HANDLE.  HANDLE WAS SUBSQUENTALLY REPAIRED AND RETURNED TO SERVICE.				1	H	7	1 	3O	3	O		3A23    	E295	5	C	P920
2005020100039	20050201	00039	GL  	2005	2	1	CA040629001      	2	20040629	G	7200		ENGINE          			EMB   	135   	EMB135ER    	3260203	SO  	ALLSN 	AE300 	AE3007A     	 	GL  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE311394			(CAN) PRELIMINARY REPORT, HIGH OIL TEMPERATURE, LOW OIL PRESSURE AND IMPENDING BYPASS MESSAGE.  PILOT COMMANDED THE IFSD	 DURING CRUISE. EMERGENCY DECLARED AND UNEVENTFUL LANDING.  REPORTED METAL DEBRIS ON OIL TANK CHIP DETECTOR AND NOT ABLE	 TO ROTATE FAN OR CORE.  ENGINE ALLOCATED. FURTHER INFO WILL BE PROVIDED WHEN ENGINE STRIP HAS BEEN COMPLETED.				2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH
2005020100040	20050201	00040	GL  	2005	2	1	CA040629002      	2	20040629	G	7250		BEARING         								ALLSN 	AE3007	AE3007C     	 	GL  					NR 4	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE330102			(CAN) DURING CRUISE AT 43,000 FT, CREW RECEIVED CHIP DETECTOR MESSAGE, FOLLOWED BY AN OIL FILTER BYPASS MESSAGE ON THE R	T ENGINE.  A/C WAS BEING FLOWN FOR MAINTENANCE VISIT TO THE MFG SERVICE CENTER.  CREW ELECTED TO CONTINUE F LIGHT AFTER 	RECEIVING THE ABOVE MESSAGES.  15 MINUTES AFTER RECEIVING THE OIL FILTER BYPASS MESSAGE, OIL PRESSURE BEGAN TO DROP AND 	THE CREW ELECTED TO SHUTDOWN THE ENGINE.  CREW ELECTED TO CONTINUE SINGLE ENGINE FLIGHT TO DESTINATION.  INITIAL INVESTI	GATION INDICATES A NR 4 BEARING FAILURE.  ENGINE SENT TO FOR REPAIR, FURTHER DETAIL WILL BE SUBMITTED UPON DISASSEMBLY O	F ENGINE.						4	F			TE6CH
2005020100041	20050201	00041	EA  	2005	2	1	CA040629003      	2	20040521	G	8530	TISN04OCA	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	PEELING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CERMINIL COATING PEELED OFF OF ABOUT 10 PERCENT OF THE BARREL, SUSPECT CAUSING METAL CONTAMINATION THROUGHOUT THE 	ENGINE.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2005020100042	20050201	00042	WP  	2005	2	1	CA040629004      	2	20040623	G	7321	8978017	FCU             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			TX	TAXI/GRND HDL  	1			CA								P50004			(CAN) DURING THE ATTEMPTED ENGINE START, THE EGT ROSE RAPIDLY TOWARDS REDLINE AND THE ENGINE WAS SHUTDOWN. TOO MUCH FUEL	 WAS BEING INTRODUCED DURING THE START SEQUENCE THEREFORE CAUSING THE OVERTEMP PROBLEM. THE FUEL CONTROL WAS REPLACED.  	ENCOUNTER THIS PROBLEM NUMEROUS TIMES A YEAR WITH DIFFERENT FUEL CONTROL UNITS AND UPON RETURN TO THE MANUFACTURER FOR R	EPAIR THE UNIT TESTS FINE AND IS RETURNED TO SERVICE ONLY TO FAIL AGAIN A SHORT TIME LATER. THE OVERTEMP PROBLEM IS USUA	LLY AN INTERMITTENT FAILURE. HAVE ISSUED SEVERAL SDR'S IN THE PAST ON THIS ISSUE AND WILL CONTINUE TO DO SO AS THEY ARIS	E. A TEARDOWN REPORT FROM THE MFG HAS BEEN ATTACHED.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2005020100043	20050201	00043	NM  	2005	2	1	CA040629005      	1	20040629	G	3233	NAS7512017	BUSHING         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINT INSP AND GREASING OF RT MLG RETRACTION ACTUATOR , ACTUATOR WOULD NOT ACCEPT GREASE.  DURING REMOVAL O	F ACTUATOR IT WAS DISCOVERED THAT UPPER ATTACHMENT BOLT TO NACELLE BRACKET, RETENTION NUT WAS CRACKED.  BOLT WAS RETAINE	D IN PLACE BY COTTER PIN, HOLDING NUT ON. DISASSEMBLY FOUND BUSHING P/N NAS75-12-017 MISSING. THIS ALLOWED BOLT P/N 8321	0090-101 TO MOVE IN BRACKET P/N 85411783-005 CAUSING DAMAGE ( ELONGATION OF HOLE) TO BRACKET, DAMAGE TO RETRACTION ACTUA	TOR ASSY AS IT WAS NOT CENTERED IN BRACKET CORRECTLY.  ACTUATOR ASSEMBLY, BOLT AND MOUNTING BRACKET REPLACED.  INSPECTIO	N OF LT GEAR ON THIS SAME AC FOUND THE SAME CONDITION.  AC HAD TASK 3230/ 18 CARRIED OUT DURING C-CHECK, 1803 CYCLES.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100053	20050201	00053	NM  	2005	2	1	CA040629006      	1	20040626	G	2421	73664E	IDG             			BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					RT GENERATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) RT GEN FAILED ON CLIMBOUT.  COULD NOT RESET, QRH CARRIED OUT.  AIRCRAFT RETURNED TO DEPARTURE.  ETOPS DOWNGRADED T	O 120MIN. OPERATE IAW MEL 24-00-1.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2005020100064	20050201	00064	CE  	2005	2	1	CA040629007      	1	20040625	G	2430	S19151	CAPACITOR       	AERO        		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ALTERNATOR	CHAFED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) INTERMITTANT OCCURRENCE OF ALTERNATOR FAILING TO STAY ON LINE.  INCORRECT POSITIONING OF CAPACITOR ALLOWED UNIT TO	 CHAFE AGAINST ENGINE BAFFLING UNTIL INTERNAL PORTION WAS EXPOSED CAUSED INTERMITTENT SHORT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2005020100067	20050201	00067	EA  	2005	2	1	CA040629008      	2	20040617	G	8520	LW11625	PLUG            			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PISTON PIN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2236815			(CAN) A FEW PIECES OF NON-FERROUS MATERIAL WERE FOUND AT 1375.8 HOURS.  FILTER RE-INSPECT SCHEDULED.  SUBSEQUENT FILTER 	INSPECTION SHOWED HEAVY CONTAMINATION.  ALL CYLINDERS REMOVED, FOUND PISTON PINS AND PLUGS NOT FLOATING.  TWO PLUGS WERE	 WORN EXTENSIVELY.  ALL PISTONS REMOVED FOR INSPECTION AND CLEANING, NO DAMAGE NOTED TO CYLINDER WALLS.  PISTONS RE-INST	ALLED WITH NEW PLUGS.  ACCESSORY DRIVE COVER AND SUMP REMOVED FOR INSPECTION AND CLEANING.  NO FURTHER EVIDENCE OF CONTA	MINATION FOUND.  NO FURTHER DAMAGE FOUND.		1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL
2005020100068	20050201	00068	CE  	2005	2	1	CA040629009      	1	20040628	G	5553		BOLT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	VERTICAL STAB	UNDERTORQUED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IN REFERENCE TO AN MAINTENANCE ALERT, AN INSPECTION WAS CARRIED OUT TO THE VERTICAL STABILIZER FRONT SPAR ATTACHME	NT BOLTS FOR SECURITY AND TORQUE OF AIRCRAFT.  ONE AIRCRAFT WAS FOUND WITH BOLT TORQUE UNDER THE SPECIFIED TORQUE ON THE	 RT SIDE UPPER AND LT SIDE LOWER. THE BOLTS WERE RE-TORQUED AND A CONTINUING INSPECTION WAS SET UP TO THE FLEET AT 1000 	HOUR INTERVALS.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005020100069	20050201	00069	NE  	2005	2	1	CA040629010      	2	20040629	G	8520		MAIN BEARING    			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	RT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								P31501			(CAN) WHILE CLIMBING AWAY FROM A WATER SCOOP, THE CREW NOTICED THAT THE RT ENGINE WAS BECOMING UNCONTROLLABLE, ROUGH RUN	NING AND LOSING POWER.  THE CREW DROPPED THE LOAD AND SHUTDOWN THE RT ENGINE AND FEATHERED THE PROPELLER.  THE AIRCRAFT 	MADE THE SINGLE ENGINE LANDING WITHOUT INCIDENT, AND THE AIRCRAFT RETURNED TO THE HANGER FOR INVESTIGATION.				2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2005020100070	20050201	00070	NM  	2005	2	1	CA040630001      	1	20040624	G	2910	82960010203	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING OPERATION, THERE APPEARED TO BE HYDRAULIC FLUID COMING FROM THE TAIL SECTION OF THE AIRCRAFT.  UPON FURTHER	 INVESTIGATION , IT WAS FOUND THAT THE LINE WAS LEAKING AND IT WAS REPLACED WITH FLEX LINE AE24600160720 IAW MM 20-50-52	.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100124	20050201	00124	SO  	2005	2	1	CA040630002      	2	20040630	G	8520		CRANKCASE       			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) DURING UNSCHEDULED MAINTENANCE 3 CRACKS WERE NOTICED ON CRANKSHAFT NEAR PROP FLANGE. TWO CRACKS WERE APPROXIMATELY	 2 INCHES IN LENGTH PARALLEL TO EACH OTHER WITH SMALLER CRACKS EXTENDING. ONE CRACK IS ALSO APPROXIMATELY 2 INCHES IN LE	NGTH AND ABOUT 1 INCH FROM THE OTHER TWO CRACKS. THESE CRACKS RUN ALONG THE CIRCUMFERANCE OF THE CRANKSHAFT.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
2005020100145	20050201	00145	EU  	2005	2	1	CA040630003      	1	20040629	G	2131	9599091141	CONTROLLER      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	OUTFLOW VALVE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT CABIN PRESSURE WAS LEADING PRESSURE DIFFERENTIAL MORE RAPIDLY AND GREATER THAN NORMAL.  DETERMINED 	THAT THE OUTFLOW VALVE CONTROLLER WAS NOT CONTROLLING OUTFLOW VALVE MOVEMENT PROPERLY.  NO OVERPRESSURES (DIFFERENTIAL) 	WERE NOTED.  PART WAS REPLACED WITH SERVICEABLE CONTROLLER AND ALL SYSTEM FUNCTIONS RETURNED TO NORMAL.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020100147	20050201	00147	EU  	2005	2	1	CA040630004      	1	20040628	G	7810	5781012041	TUBE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK WAS DISCOVERED AT INSPECTION NEXT TO EXHAUST TUBE USED TO SUPPLY ENGINE EXHAUST TO COWLING LIP DEICE.  ABOUT	 ONE INCH FROM ENGINE MOUNTING FLANGE , CRACK WAS ABOUT ONE AND A QUARTER INCH LONG.  REPAIR PERFORMED IAW MM CHAPTER 78	 10-01.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020100148	20050201	00148	EU  	2005	2	1	CA040630005      	1	20040629	G	2910	A5784365500400	FITTING         			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					PRESSURE LINE	LOOSE           	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH, WHEN FLAP/SLAT WERE EXTENDED, THE HYDRAULIC RESERVOIR LOW LEVEL ECAM WARNING CAME ON.  AIRCRAFT	 OVERSHOT AND CHECKLIST PROCEDURE INDICATE A FAILURE OF GREEN HYDRAULIC SYSTEM.   ALTERNATE GEAR EXTENSION PERFORMED.  D	URING INVESTIGATION, FOUND THE GREEN SYSTEM PRESSURE LINE FITTING LOOSE ON THE RT KRUGER FLAP ACTUATOR.  LINE TIGHTENED 	AND SYSTEM WAS VERIFIED SERVICEABLE IAW THE MM.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA
2005020100149	20050201	00149	EU  	2005	2	1	CA040630006      	1	20040628	G	3242	30244	BRAKE ASSY      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE ON TAXI FROM THE HANGER RAMP TO TAXI WAY, THE AIRCRAFT MADE A SUDDEN MOVE TO THE RT AND A LOUD GRINDING META	LLIC SOUND WAS HEARD IN THE AIRCRAFT. THE AIRCRAFT ENGINE WAS SHUT DOWN ON THE TAXIWAY AND AN INVESTIGATION WAS CONDUCTE	D IN THE AREA OF THE RT LANDING GEAR.  THE RT BRAKE UNIT WAS NOTED TO HAVE LOOSE PARTS (BRAKE PAD) BETWEEN THE DISK PLAT	ES. THE AIRCRAFT WAS TOWED BACK TO THE HANGER AND A NEW BRAKE UNIT WAS INSTALLED. THE AIRCRAFT WAS RETURNED TO SERVICE W	ITH NO FURTHER ACTION REQUIRED. THE BRAKE UNIT S/N 1099 WAS FURTHER EXAMINED AND IT WAS NOTED THAT A BRAKE PAD HAD SHEAR	ED ITS RIVETS AND WAS LODGE IN BETWEEN THE PRESSURE PLATES.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020100150	20050201	00150	EA  	2005	2	1	CA040630007      	1	20040628	G	7334	21550724	INDICATOR       			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	PRESS TRANSMITER	DEFECTIVE       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF, THE RT FUEL PRESSURE INDICATOR WAS 1 PSI LOWER THAN PREVIOUS FLIGHTS.  THE CREW ELECTED TO PROCEED	 FOR MAINTENANCE.  AFTER CRUSING FOR AWHILE THEY NOTICED ANOTHER DROP IN FUEL PRESSURE AND ELECTED TO SHUT DOWN THE RT E	NGINE.  THEY LANDED SAFELY FOR MAINTENANCE. MAINTENANCE CHECKED THE RT FUEL SYSTEM FOR LEAKS AND NONE WERE FOUND.  THE F	UEL PRESSURE INDICATING SYSTEM WAS CHECKED AND THE TRANSMITTER WAS FOUND DEFECTIVE.  THE TRANSMITTER WAS REPLACED AND GR	OUND CHECKED SERVICABLE. THE A/C WAS RETURNED TO SERVICE.		2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2005020100180	20050201	00180	WP  	2005	2	1	CA040702001      	1	20040630	G	2421		BEARING         	ELECTROSYS  		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ALTERNATOR     A	WORN            	W				E				ENGINE SHUTDOWN         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						7050657					(CAN) AFTER THE ALTERNATOR BELT BROKE FOR THE SECOND TIME IN 8 HOURS, IT WAS NOTICED THAT THE ALTERNATOR PULLEY, ALTHOUG	H SMOOTH WHEN TURNED BY HAND, WAS ABLE TO MOVE SIDEWAYS ABOUT AN EIGHT OF AN INCH.   WE DID NOT DISSASSEMBLE THE UNIT BU	T IT IS SAFE TO ASSUME THE COMUTATOR BEARINGS ARE WORN OUT.				1	G	7	1 	3O	3	O		H11NM   	E295
2005031000016	20050310	00016	NE  	2005	3	10	CA040702002      	2	20040627	G	7322	C2E2215	BELLOWS         			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN1     	52008	NE  	HAMSTD	2D	2D30        	NE  	CARBURETOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HAVE DETERMINED THAT CARB HEAT BELLOWS P/N C2E2215 AS RECEIVED WAS ACQUIRED DIRECTLY WITHOUT GOING THROUGH QA INSP	ECTION AND CERTIFICATION. PART BEARS DHC-2 PN STAMP AND APPEARS GENUINE. PART PLACED IN QUARATINE.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
2005031000017	20050310	00017	GL  	2005	3	10	CA040702003      	2	20040630	G	7310	6654777	BAR             			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	FUEL FILTER	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE FLIGHT CREW NOTICED SEVERE SURGING ON THE NR 1 ENGINE. THE FUEL FLOW WAS ALSO DROPPING AND SURGI	NG. THE ENGINE WAS SHUT DOWN AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED TO DEPARTURE. DURING INVESTIGATION M	AINTENANCE CREW FOUND THE BAR ASSY THAT SECURES THE FILTER BOWL TO THE HOUSING WAS BROKEN AT THE THREADS. THE BOWL WAS D	ISCOVERED HANGING BY THE LOCKWIRE. GASKET P/N 30865 WAS ALSO MISSING. REF MFG IPC 73-00-00FIG 5 ITEMS 9, 10 AND 16.  THE	 PARTS WERE REPLACED AS REQUIRED AND THE AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898
2005031000018	20050310	00018	WP  	2005	3	10	CA040702004      	1	20040628	G	3233	MS28775212	O-RING          			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	ACTUATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						36					(CAN) DURING CRUISE THE PILOT NOTED A RAPID DROP IN HYDRAULIC PRESSURE ON BOTH THE LT AND RT SIDE. THE AIRCRAFT DIVERTED	 COURSE. THE RETARDANT LOAD WAS JETTISONED AND THE FLAPS AND LANDING GEAR WERE LOWERED USING THE EMERGENCY HAND PUMP. TH	E AIRCRAFT LANDED WITHOUT INCIDENT. DURING INVESTIGATION BY MAINTENANCE IT WAS NOTED THAT THE SEAL IN THE NOSE LANDING G	EAR ACTUATOR HAD FAILED CAUSING THE HYDRAULIC FLUID LOSS. THE ACTUATOR WAS REPLACED, AND A GEAR SWING WAS ACCOMPLISHED A	FTER THE HYDRAULIC SYSTEM WAS PURGED AND REPLENISHED. THE AIRCRAFT WAS RETURNED TO SEVICE.		2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879
2005031000019	20050310	00019	WP  	2005	3	10	CA040702005      	1	20040622	G	8011		SWITCH          			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	AIR STARTER	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA						P15827C					(CAN) DURING CRUISE THE LT STARTER OVERSPEED LIGHT ILLUMINATED. THE ENGINE WAS SHUT DOWN AND THE PROPELLER WAS FEATHERED	 AS A PRECAUTION. THE AIRCRAFT RETURNED TO BASE. THE STARTER WAS REMOVED AND NO DAMAGE WAS NOTED.  THE LIGHT SYSTEM WAS 	CHECKED FOR FAULTS NONE NOTED.  IT WAS DETERMINED THAT THE INTERNAL SWITCH WAS CAUSING THE LIGHT ILLUMINATION. THE START	ER HAS BEEN SENT TO THE REPAIR SHOP FOR INVESTIGATION.  THE STARTER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVIC	E.		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906
2005031000065	20050310	00065	EA  	2005	3	10	CA040704001      	1	20040630	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENROUTE THE F/O'S WINDSHIELD SHATTERED, CREW ELECTED TO DIVERT. MAINTENANCE REPLACED WINDSHIELD.(SEE ALSO: US NR 2	004071600072)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005030800204	20050308	00204	CE  	2005	3	8	CA040705001      	1	20040610	G	3233		NUT             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING RECTIFICATION OF A SNAG GEAR HANDLE LIGHT STAYING ON WHEN GEAR RETRACTED, A/C JACKED UP AND L/G SWINGS WERE COMPL	ETED.  NOTED THAT LT L/G DOORS WAS HANGING OPEN WITH GEAR RETRACTED.  ACT REMOVED DUE TO SUSPICION IT HAD SLIPPED INTERN	ALLY, CAUSING IT TO BE OUT OF SYNC WITH NOSE AND RT MAIN GEAR ACTUATORS. INSPECTION OF ACT AFTER REMOVAL SHOWED ACT TO H	AVE AN EXCESSIVE AMT OF INTERNAL RESISTANCE. SENT TO OVERHAUL FACILITY FOR EVALUATION. OVERHAUL FACILITY HAS DISASSEMBLE	D ACT AND FOUND EXCESSIVE WEAR AND STRIPED THREADS ON NUT AND SCORING ON SCREW THREADS.  THIS UNIT IS BEING SENT TO RAYT	HEON FOR FURTHER ANALYSIS.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE
2005031000066	20050310	00066	CE  	2005	3	10	CA040705002      	1	20040630	G	3040	11418002823	BOOT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LEFT	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CREW NOTICED A TEAR IN THE LT IB DEICE BOOT DURING WALKAROUND. THE AIRCRAFT WAS FERRIED AND THE BOOT WAS REPLACED.	 REASON FOR TEAR UNKNOWN.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005031000067	20050310	00067	CE  	2005	3	10	CA040705003      	1	20040615	G	3231	4532103045002	BELLCRANK       			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BELLCRANK CRACKED AT PIVOT POINT NEW BELLCRANK PT NR 4532103045-004 INSTALLED GEAR SWINGS COMPLETED.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005031000068	20050310	00068	SW  	2005	3	10	CA040705004      	1	20040630	G	3250		STEERING SYS    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON LANDING, WHEN SPEED LEVERS SELECTED TO LOW AT 70 KIAS, NOSE WHEEL STEERING WAS ARMED AND THE AIRCRAFT VEERED 	SHARPLY RT AND DEPARTED THE RUNWAY.  THE ENGINES WERE SHUTDOWN AS A PRECAUTIONARY MEASURE.  NO DAMAGE NOTED.  THE AIRCRA	FT STOPPED ON THE ADJACENT TAXIWAY.  WILL REPORT FURTHER WHEN THE SOURCE OF THE PROBLEM IS DISCOVERED.  AIRCRAFT HAS BEE	N REMOVED FROM SERVICE SINCE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2005030800207	20050308	00207	GL  	2005	3	8	CA040705005      	2	20040624	G	7200		ENGINE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 2	FAILED          	W				O				OTHER                   				X	B		ENGINE FLAMEOUT           	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA								CAT33576			ON STARTING NR 2 ENG THE WIND UP TO FUEL INTRODUCTION WAS NORMAL ENGINE LIGHT-OFF AND INITIAL SURGE WAS NORMAL, THEN THE	 N1 ACTUALLY DROOPED, THE ENG FLAMED OUT MOMENTARILY, CAUGHT AGAIN (WITH A LARGE PUFF OF SMOKE) ACCELERATED A LITTLE, TH	EN DROOPED AGAIN AND THE START WAS ABORTED.  MOTORING THE STARTER AFTERWARDS PRODUCED A LOT OF NOISE WITH VERY RAPID DEC	ELERATION ONCE THE STARTER WAS DISENGAGED.  THE STARTER WAS REMOVED AND CHECKED OK. THE TRANSMISSION COWLING WAS REMOVED	 AND THE COMPRESSOR WAS TURNED BY HAND, IT WAS VERY STIFF AND NOISY. THE NOISE APPEARING TO COME FROM THE TURBINE. THE B	URNER CAN AND LINER WAS REMOVED AND THE COMPRESSOR WAS TURNED BY HAND . IT WAS CONFIRMED THAT THE TURBINE WAS RUBBING.	1	G	7	2 	3U	3	U		H3EU    	E4CE
2005031000069	20050310	00069	CE  	2005	3	10	CA040705006      	1	20040630	G	2823	1013890253	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING PILOTS START CHECKS RT HAND FUEL SHUT-OFF VALVE FAILED IN OPEN POSITION.  UNABLE TO TURN LOW PRESSURE LIGHT	 ON.  REPLACED VALVE.  AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2005031000070	20050310	00070	CE  	2005	3	10	CA040705007      	1	20040622	G	3233	6632303003001	SWITCH          	PNEUDRAULICS		LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ACTUATOR	OUT OF TOLERANCE	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA						0149					(CAN) GEAR WOULD NOT RETRACT ON 1ST ATTEMPT, 2ND ATTEMPT WAS SUCCESSFUL  FOUND ACTUATOR SWITCH OUT OF TOLERANCE ACTUATOR	 REPLACED WITH OVERHAULED UNIT GEAR SWINGS COMPLETED.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005031000071	20050310	00071	CE  	2005	3	10	CA040705008      	1	20040610	G	2750	C1444831	POWER UNIT      			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					TE FLAPS	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP POWER UNIT NOISY/SLOW, REPLACED WITH OVERHAULED UNIT.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2005030800209	20050308	00209		2005	3	8	CA040705009      	4	20040703	G	3442	20675680501	ANTENNA         			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					WX RADAR SYS	INTERMITTENT    	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA											AIRCRAFT DEPARTED AND ONCE AIRBORNE THE CREW FOUND THE WEATHER RADAR TO BE INTERMITTENT WITH INCORRECT READINGS.  DUE TO	 THE WEATHER FORECASTED AT THE DESTINATION THE CREW RETURNED TO BASE.  MAINTENANCE FOUND THAT THE RADAR ANTENNA WAS AT F	AULT.  THE SYSTEM WORKED SERVICEABLE AFTER REPLACEMENT OF THE ANTENNA. THIS UNIT WAS INSTALLED TO CORRECT THE SAME SNAG 	DURING TROUBLESHOOTING ON JUNE 10TH. THIS INTRODUCED THE SAME SNAG AND MADE THE SNAG VERY DIFFICULT TO TROUBLESHOOT AND 	CORRECT. THE RADAR RT, DISPLAY, RADOME, WAVE GUIDE, ADI, CONTROL PANEL WERE REPLACED IN EFFORTS TO TROUBLESHOOT AND CORR	ECT THE SNAG.	2	L	7	2 	4F	4	F		A16WE   	E2EA
2005030800210	20050308	00210	NE  	2005	3	8	CA040706001      	1	20040610	G	7600	37C800410P101	ROD             			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					ACTUATOR	STRIPPED        	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											SVA PILOT VALUE FEEDBACK CABLE ROD THREADS EXCESSIVELY WORN CAUSING ENGINE TO SURGE.						2	G	7	2 	4U	4	U		1H15    	1E3
2005030800222	20050308	00222	EA  	2005	3	8	CA040706002      	2	20040601	G	7322	1060301	CARBURETOR      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											HIGH MANIFOLD PRESSURE.  REPLACED CARBURETOR.						1	G	7	1 	3O	3	O	O	4H12    	E286
2005030800223	20050308	00223	EA  	2005	3	8	CA040706003      	2	20040614	G	7414	S4LN204	MAGNETO         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											HIGH ENGINE RPM.  REPLACED MAGNETO.						1	G	7	1 	3O	3	O		H10WE   	E274
2005030800224	20050308	00224	EA  	2005	3	8	CA040706004      	2	20040616	G	7322	A5224	CABLE           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					CARB HEAT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CARB HEAT CABLE BROKEN.  REPLACED CARB HEAT CABLE.						1	G	7	1 	3O	3	O		H10WE   	E274
2005030800225	20050308	00225	EA  	2005	3	8	CA040706005      	2	20040617	G	7520		BLADE           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE FAN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CRACKED BLADE.  REPLACED FAN WHEEL.						1	G	7	1 	3O	3	O		H10WE   	E274
2005030800226	20050308	00226	SW  	2005	3	8	CA040707001      	1	20040312	G	6520	406340105101	SEAL            			BELL  	206   	206B        	1181511	SW  										T/R GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TAIL ROTOR GEARBOX CHIP DETECTOR HAS ILLUMINATED IN FLIGHT.  THE GEARBOX WAS SUBSEQUENTLY REMOVED FROM AIRCRAFT, REPLACE	D WITH SERVICEABLE UNIT AND AIRCRAFT WAS RETURNED TO SERVICE.  UPON DISMANTLING OF THE GEARBOX IT WAS DISCOVERED THAT TH	E SEALING LIP WORE THROUGH ALLOWING THE TENSION SPRING TO CONTACT WEAR SLEEVE, RESULTING IN THE GENERATION OF METALLIC P	ASTE/SLUDGE.			1	G	7	1 	3U				H2SW
2005030800227	20050308	00227	CE  	2005	3	8	CA040707002      	1	20040701	G	2912	KIT11480221S	FILTER          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					HYD SYSTEM	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING SCHEDULED INSPECTION OF THE INLINE HYD FILTERS (INSTALLED USING RAYTHEON KIT NR 114-8022-1S) IT WAS DISCOVERED TH	AT TWO OF THE FILTERS HAD SEPARATED FROM THERE CONICAL END AND HAD MIGRATED DOWN THE HYD RETURN LINE ABOUT 2 INCHES FROM	 THERE NORMAL POSITION.  IT IS SUSPECTED THAT THIS DEFECT COULD POTENTIALLY BLOCK THE RETURN LINE FOR THE GEAR ACTUATORS	 AND CAUSE THE GEAR TO FAIL IN THE UP POSITION IN WHICH CASE THE MANUAL EXTENSION WOULD ALSO FAIL. THE INLINE HYD FILTER	S WERE REMOVED FROM THIS A/C PENDING FINDINGS OF THIS SDR. OPERATOR NOTE: REFERENCE BEECHCRAFT OPTIONAL SERVICE BULLETIN	 2403 FOR INSTALLATION OF THIS KIT. ACTUAL FILTER PART NUMBER IS NOT KNOWN AT THIS TIME.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2005030800228	20050308	00228	WP  	2005	3	8	CA040707003      	2	20040706	G	7310	31024741	MANIFOLD        			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	FUEL DISTRIBUTIO	CRACKED         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		DE	DESCENT        	1			CA											SLIGHT FUEL ODOR IN CABIN WHEN AIRCRAFT SLOWED FOR LANDING.  THE CREW NOTICED FUEL DRIPPING FROM THE RT ENGINE AFTER SHU	TDOWN.  MAINTENANCE FOUND A CRACKED FUEL MANIFOLD INLET ELBOW.  THE MANIFOLD WAS REPLACED.					1	L	7	2 	4T	3	T		A14CE   	E2WE	6	C	P40EA
2005030800229	20050308	00229	NE  	2005	3	8	CA040707005      	1	20040707	G	6700	S614062122000	BELLCRANK       			SKRSKY	S61   	S61A        	814210C	NE  										FLT CONTROLS	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											BELLCRANK CONTACTING LINK ASSY CAUSING UNWANTED MOVEMENT OF EITHER CYCLIC OR COLLECTIVE CONTROLS. BELLCRANK DIMENSIONALL	Y CHECKED AGAINST SIKORSKY DRAWING  NR S6140-62122 AND FOUND TO BE NONCONFORMING FROM MANUFACTURE.  BELLCRANK ASSEMBLY I	S TRIANGULAR IN SHAPE.  IT HAS ONE BEARING INSTALLED AT ITS AXIS, AND TWO OTHER HOLES ARE MACHINED FOR ATTACHMENT TO OTH	ER FLT CONTROL ITEMS. LOCATION OF THESE HOLES DEVIATES AS MUCH AS .064 FROM THE DRAWING, AND IT IS BELIEVED THAT THIS DE	VIATION CAUSES CONFLICT IN FLT CONTROL SYSTEM. THIS DEVIATION APPEARS TO HAVE BEEN FROM MANUFACTURE AS NO SIGNS OF WEAR 	ARE PRESENT. BELLCRANK IS NOT SERIALIZED YET IS IDENTIFIED WITH A P/N 'S6140-62122-001' AND A VENDOR CODE '782861'.	2	G	7	2 	4U				H2EA
2005030800230	20050308	00230	CE  	2005	3	8	CA040707006      	1	20040701	G	3230	571302	MOTOR           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											GEAR UNSAFE LIGHT CAME ON IN FLIGHT WITH AUTO FEATHER OFF ANNUNCIATOR ALSO.  GEAR HAD TO BE MANUALLY EXTENDED.  REPLACED	 LANDING GEAR POWER PACK MOTOR WITH O/H UNIT.  FUNCTIONAL TEST OF SYSTEM CARRIED OUT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005030800231	20050308	00231	EU  	2005	3	8	CA040708001      	1	20040703	G	7120	10560386	BUSHING         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE MOUNT	DEBONDED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											A SERVICEABILITY INSPECTION WAS CARRIED OUT FOLLOWING THE LAST FLIGHT OF THE DAY AND IT WAS FOUND THAT THE LEFT ENGINE O	UTBOARD MOUNT HAD VISIBLY DROPPED.  THE ELASTOMER MATERIAL WAS COMPLETELY DEBONDED FROM THE METAL INNER PORTION OF THE M	OUNT BUSHING P/N 105-60386 (CHAPTER 60-00-00, FIG. 14, ITEM 280, BO-105 PARTS BOOK) AND WAS EXTRUDING OUT OF THE SHELL.				1	G	7	2 	3U	3	U		H3EU    	E4CE
2005030800232	20050308	00232	NM  	2005	3	8	CA040708002      	1	20040625	G	5310	85320534103	DOOR FRAME      			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	EMERGENCY EXIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			38342								RT EMERGENCY EXIT DOOR REMOVED TO GAIN ACCESS TO LEVELLING DATUM PLATE TO JACK AIRCRAFT, A CRACK WAS DISCOVERED IN FRAME	 ON AFT SIDE OF THE DOOR.  CRACK EXTENDS FROM LIGHTENING HOLE BETWEEN STRINGERS 22P AND 23P THROUGH THE FRAME RETURN ON 	THE INBOARD SIDE.  FRAME WAS REPLACED WITH POST MODSUM 8/0427 FRAME P/NO.85320534-107A.  THE LIGHTENING HOLE IS DELETED 	ON THE POST MOD 8/0427 FRAME.NOTE: MODSUM 8/0427 (FUSELAGE FRAME FLANGES AT OUTBOARD SEAT RAIL BRACKET ATTACHMENT AREA) 	INTRODUCED A NEW FRAME AT THIS LOCATION ALONG WITH NUMEROUS STRUCTURAL IMPROVEMENTS ALONG THE FUSELAGE DUE TO CRACKING O	F FRAMES IN THE FATIGUE SPECIMEN.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800233	20050308	00233	GL  	2005	3	8	CA040708004      	3	20040629	G	6114		DOWEL PIN       			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  	HARTZL	HC82V	HC82V*      	GL  	PROPELLER	MISSING         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA									T2089N		PROPELLER INSTALLED AFTER OVERHAUL USING CESSNA MAINTENANCE MANUAL AS REFERENCE.  AIR TEST AFTER INSTALLATION REFLECTS P	ROPELLER VIBRATION SHORTLY AFTER TAKEOFF.  AIRCRAFT LANDED IMMEDIATELY.  PROPELLER REMOVED.  INSPECTED BY A-1 PROPELLER 	SERVICES.  DETERMINED DOWELS FOUND MISSING UPON RETURN FROM OVERHAUL.  CESSNA MAINTENANCE MANUAL LACKING IN DETAIL WITH 	RESPECT TO DOWEL INSTALLATION.  WRONG DOWELS MISTAKENLY DRIVEN.  CESSNA PARTS MANUAL SHOWS ALL DOWELS AS PART OF PROELLE	R ASSEMBLY.		1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P23EA
2005030800234	20050308	00234	NM  	2005	3	8	CA040708006      	1	20040704	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE, NR 1 HYDRAULIC CAUTION LIGHT ILLUMINATED, CONFIRMED NR 1 HYDRAULIC SYSTEM HAD NO PRESSURE.  FOLLOWED QRH 	AND MADE NORMAL LANDING.  FOUND QUILL SHAFT FOR PUMP COMPLETELY SHEARED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005030800235	20050308	00235	EA  	2005	3	8	CA040708007      	2	20040706	G	7200		ENGINE          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LEFT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING CRUISE FLIGHT, THE CREW OBSERVED THE LT ENGINE T5 TEMPERATURE STARTING TOFLUCTUATE FOLLOWED BY A COMPLETE LOSS OF	 T5 TEMPERATURE INDICATION.  ONCE ON THE GROUND, DURING A TROUBLESHOOTING MAINTENANCE RUN, IT WAS ALSO OBSERVED THAT THE	 ENGINE WAS MAKING ABNORMAL				1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
2005030800236	20050308	00236	NM  	2005	3	8	CA040708008      	1	20040705	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 HYD SYSTEM	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											NR 2 HYDRAULIC SYSTEM CASE DRAIN FILTER BYPASS INDICATOR POPPED SEVERAL TIMES DURING THE DAY.  FOUND FILTER CONTAMINATED	 WITH METAL.  REPLACED HYDRAULIC PUMP AS PRECAUTION DUE TO 2 FAILURES ON OTHER AIRCRAFT.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2004072900013	20040729	00013	CE  	2004	7	29	CA040708009      	1	20040611	G	5753		SKIN            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RT FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SMALL CRACKS AT RIVETS, 4 PLACES, WERE FOUND ON THE RT FLAP.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004072900014	20040729	00014	NM  	2004	7	29	CA040708010      	1	20040706	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING TEST FLIGHT, NR 2 HYD CAUTION LIGHT ILLUMINATED.   CONFIRMED NO PRESSURE ON SYSTEM.  QRH AND DIVERTED TO BA	SE.  VERIFIED PUMP QUILL SHAFT SHEARED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004072900015	20040729	00015	NE  	2004	7	29	CA040708011      	2	20040705	G	8530	28151	SEAL            			DOUG  	A26   	A26*        	       	WP  	PWA   	R2800 	R280079     	52026	NE  	HAMSTD	23E	23E50       	NE  	CYLINDER	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								FPO27892			(CAN) NR 1 ENGINE WAS RUNNING ROUGH AT CLIMB POWER ABOUT FOUR MINUTES AFTER TAKE OFF, THE ENGINE CONTINUED TO RUN ROUGH 	AT REDUCED POWER. THE PILOT SHUT DOWN THE ENGINEAND SECURED IT AND RETURNED TO BASE WITHOUT INCIDENT. MAINTENANCE FOUND 	TRACES OF OIL IN THE INTAKES AND THE CYLINDERS WHICH POINTS TO THE BLOWER SEAL. ENGINE CHANGE SCHEDULED.				2	M	7	2 	4R	4	R	 	L34     	5E8	6	C	P603
2004072900016	20040729	00016	SW  	2004	7	29	CA040708012      	1	20040705	G	2821	222366621	DRAIN VALVE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE GROUND RUN IAW MM-1-5/27, THE ENGINE FLAMED OUT WHEN THE BOOST PUMPS WERE SHUT OFF. THIS FAILUR	E WAS REPEATABLE. TROUBLE SHOOTING REVEALED AIR ENTERING THE FUEL SYSTEM THROUGH THE AIRFRAME FUEL FILTER ASSEMBLY DRAIN	 VALVE. THE AIRFRAME FUEL FILTER ASSEMBLY P/N 222-366-621-001 WAS REPLACED WITH P/N 222-366-621-003 AND THE AIRCRAFT WAS	 RUN IAW MM-1-5/27. THE PROBLEM WAS RECTIFIED.  THE DEFECTIVE PART TRACEABILITY IS BEING REVIEWED.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004072900017	20040729	00017	EA  	2004	7	29	CA040709001      	2	20040629	G	8530	SL32006WA21P	CYLINDER        								LYC   	O320  	O320*       	41508	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NEW CYLINDER ASSEMBLIES (2), REMOVED FROM BOXES AND INSPECTED & MEASURED TO FIT RINGS. BARRELS FOUND TO BE AT SERI	CE LIMIT WITH .010 CHOKE AND .008 TO .010 OUT OF ROUND. NEW CYLINDERS OUT OF LIMITS. NO APPARENT PHYSICAL DAMAGE, QUALIT	Y CONTROL PROBLEM.									3	O			E274
2004072900018	20040729	00018	SO  	2004	7	29	CA040709002      	2	20040623	G	8530	649199P10A1	CYLINDER HEAD   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA								AR34880			(CAN) CRACKED COMPLETELY THROUGH FROM ONE SPARK PLUG HOLE TO THE EXHAUST VALVE SEAT TOTHE OTHER SPARK PLUG HOLE. CYLINDE	R WAS REPAIRED 25.6 HOURS PREVIOUS. (DUE TO EXHAUST VALVE PROBLEMS) NOTE: LOGBOOK INCORRECTLY STATED CYLINDER WAS OVERHA	ULED. CYLINDER WAS ACTUALLY REPAIRED 25.6 HOURS PREVIOUS.  CYLINDER FAILURE OF THIS TYPE IS NOT UNCOMMON ON LARGER 6 CYL	INDER ENGINES.			1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA
2004072900019	20040729	00019	SO  	2004	7	29	CA040709003      	2	20040701	G	8550	642335	SCREW           			CESSNA	206   	U206        	2073306	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	OIL VALVE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ENGINE START, FIRST FLIGHT OF THE DAY, OIL PRESSURE WAS OBSERVED AS BEING TOO HIGH (75 PSI AT IDLE).  SYSTE	M BLOCKAGE WAS SUSPECTED, OIL FILTER INSPECTED (CLEAR), OIL DRAINED AND INSPECTED (CLEAR), PRESSURE CHECKED AT OTHER PRE	SSURE POINTS IAW MFG SERVICE REP. INSTRUCTIONS. (AIRFRAME INDICATOR ACCURACY CONFIRMED.) NIL DEFECT FOUND.  OIL PRESSURE	 RELIEF VALVE REMOVED, VISUALLY INSPECTED (NIL DEFECTS OBSERVED, REINSTALLED.  ENGINE GROUND RUN, NIL CHANGE IN OIL PRES	SURE.  RELIEF VALVE ADJUSTING SCREW TURNED OUTWARD TO STOP. OIL PRESSURE OBSERVED (JUST IN RANGE).  VALVE ASSEMBLY REPLA	CED WITH SERVICEABLE UNIT, OPERATION NORMAL.	1	H	7	1 	3O	3	O	 	A4CE    	E3SO	5	C	P47GL
2004072900046	20040729	00046	SO  	2004	7	29	CA040709004      	1	20040626	G	7797		WIRE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	CHT PROBE	CUT             	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN FLIGHT, THE PILOT NOTICED THAT THE LT ENGINE CYLINCER TEMPERATURE WAS ABNORMALLY HIGH.  ALL OTHER PARAMETERS WE	RE IN THE GREEN.  THE PILOT ASKED FOR A PRIORITY LANDING.  WE DISCOVERED THAT THE WIRING FOR THE CHT PROBE WAS CUT. THE 	TERMINAL WAS REPLACED, EVERYTHING BACK TO NORMAL.				1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA
2005030800237	20050308	00237	SO  	2005	3	8	CA040709005      	1	20040420	G	5730	4065903	SKIN            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPPER SKIN ON RT WING FOUND TO HAVE HAIR LINE CRACKS AT STA 174.50 AND STA 160.50 ONE RIVET FORWARD OF STRINGER IMMEDIAT	ELY FORWARD OF MAIN SPAR.					1	L	7	2 	3O	3	O		A20SO   	E14EA
2004072900047	20040729	00047	SW  	2004	7	29	CA040709006      	1	20040628	G	8200		WATER INJECTION 			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	INOPERATIVE     	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) WATER METHANOL DID NOT WORK ON TAKE OFF ROLL.  LT AND RT PUMP LIGHTS WERE ON.  AIRCRAFT RETURNED TO GATE.  MAINTEN	ANCE BLED AIR FROM SYSTEM AND BELLY DRAINS.  AIRCRAFT RUNUP AND SYSTEM FUNCTIONED NORMALLY.  AIRCRAFT RETURNED TO SERVIC	E.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2005030800238	20050308	00238	SO  	2005	3	8	CA040709007      	1	20040528	G	5730	4065903	SKIN            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT WING	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											LT WING AT STA 174.50 FOUND TO HAVE HAIR LINE CRACK FROM RIVET FORWARD OF STRINGER AHEAD OF THE MAIN SPAR.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004072900048	20040729	00048		2004	7	29	CA040709008      	4	20040708	G	3421		WARNING FLAG    	BFGOODRICH  		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STBY ATTITUDE IN	MALFUNCTIONED   	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA						25109					(CAN) (OFF) WARNING FLAG DOES NOT COMPLETELY GO OUT OF VIEW.  GYRO WAS FUNCTIONING NORMALLY AND FLAG SEEMS TO BE DISLOCA	TED TOO FAR TO THE RIGHT AS COMPARED TO A SERVICEABLE UNIT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004080400209	20040804	00209	EU  	2004	8	4	CA040709009      	1	20040629	G	2750	9787320003	PDU             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS WERE SELECTED UP, RETRACTED NORMALLY. FLAPS WERE SELECTED DOWN, EXTENDED NORMALLY. FLAPS WERE RETRACTED ONCE	 MORE, OPS WERE NORMAL. FLAPS WERE SELECTED DOWN, WHEN THEY REACHED 15 DEGREE POINT, STARTED TO BIND AND FLAP RESET WAS 	PERFORMED. FLAPS WERE SELECTED TO 30 DEGREES. FLAPS OPERATED, BUT CUT IN AND OUT. FLAPS WERE SELECTED TO 40 DEGREES, OPE	RATED NORMALLY.  WHEN SELECTED DOWN, STARTED TO BIND BETWEEN 15 DEGREES, 30 DEGREES, RCCB POPPED.  BINDING NOISE CAME FR	OM RT FLAP.  FLOOR ACCESS PANEL TO FLAP PWR DRIVE UNIT WAS REMOVED. FLAP PWR DRIVE UNIT WAS HOT AND THERE WAS STRONG ELE	CTRICAL SMELL FROM PDU. FLAP PWR DRIVE UNIT WAS REPLACED, FLAPS OPERATED NORMAL.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004072900049	20040729	00049	SO  	2004	7	29	CA040709010      	1	20040614	G	2751	1766903	INDICATOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	TE FLAPS	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA											(CAN) LANDING GEAR LIGHTS WOULD NOT WORK. NOTICED FLAP INDICATOR DARK IN COLOR.  DISCONNECTED WIRE FROM THE  FLAP INDICA	TOR AND GEAR LIGHTS WORKED. REPLACED INDICATOR AND SYSTEM WORKED NORMAL.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA
2004072900050	20040729	00050	EA  	2004	7	29	CA040712001      	1	20040618	G	2810		CAP             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AFT TANK FUEL	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) LANDED BACK TO THE BASE, DUE TO FUEL LEAKAGE FROM FUEL CAP INTO THE CABIN.  ON ARRIVAL FOUND SIGN OF FUEL LEAKAGE 	AT AFT TANK CAP TO THE ADJACENT PAX DOOR INTO THE CABIN.  AFT TANK WAS FULL ON DEPARTURE, SUSPECT FUEL SEEPAGE FROM THE 	TANK CAP DUE TO SEAL WAS NOT IN GOOD CONDITION.  TANK CAP REPLACED.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2004072900051	20040729	00051	NM  	2004	7	29	CA040712002      	1	20040707	G	1420	MS347L2255PN	CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT WING ROOT	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON TAKE OFF ROLL 40-50 KNOTS THE NR 1 PROPELLER GAUGE WENT TO ZERO ON BOTH DIGITAL AND ANALOG DISPLAYS.  ALL OTHER	 ENGINE GAUGES NORMAL. MAINTENANCE CARRIED OUT AN INSPECTION AN FOUND TWO PINS (Z AND FF) IN CONNECTOR 9811-P13 (P/N MS3	476L22-55PN) TO BE CORRODED AND TO BE AT FAULT WHEN MEGGARED.  CONNECTOR REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004072900052	20040729	00052	EU  	2004	7	29	CA040712003      	1	20040630	G	6320	4638302024	BEARING RACE    			BOLKMS	105   	BO105C      	5626005	EU  										TRANSMISSION	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1190					(CAN) TRANSMISSION SENT FOR OVERHAUL DUE TO METAL CONTAMINATION DETECTED WITH A CHIP LIGHT INDICATION.  AFTER DISSASSEMB	LY BEARING OUTER RACE FOUND TO HAVE SPALLING DAMAGE.					1	G	7	2 	3U			 	H3EU
2005030800241	20050308	00241	EU  	2005	3	8	CA040712004      	1	20040708	G	3040	BYLB51824	VALVE           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	DE-ICE SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											PILOTS REPORTED GREEN WING DE-ICE LIGHT CAME ON LEFT SIDE AFTER WING DE-ICE WAS SELECTED OFF AND REMAINED ON FOR FLIGHT.	  THE LEFT WING VALVE WAS REMOVED AND FOUND TO BE NOT COMPLETELY CLOSED.					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE
2004072900085	20040729	00085	EU  	2004	7	29	CA040712005      	1	20040625	G	6730	10546682	SERVO VALVE     			BOLKMS	117   	BK117A1     	5626010	EU  										HYD ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						100821					(CAN) DURING A ROUTINE INSPECTION A MARK WAS DISCOVERED ON THE ATTACHMENT HEAD OF THE SLIDER OF THE SERVO VALVE.  THE SL	IDER INSPECTED WITH LIQUID PENETRANT WHICH INDICATED THAT THE SLIDER WAS CRACKED.					1	G	7	2 	3U			 	H13EU
2004080500004	20040805	00004	EU  	2004	8	5	CA040712006      	1	20040710	G	2160	9599020135	VALVE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TEMP CONTROL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0151					(CAN) TEMP CONTROL VALVE FOUND TO BE AT FAULT AFTER CREW COMPLAINED OF ECS HEAT NOT RESPONSIVE. VALVE REPLACED WITH REPA	IRED UNIT, RETURNED TO SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004080500005	20040805	00005	WP  	2004	8	5	CA040712007      	1	20040707	G	8012	980109000	START VALVE     			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RT STARTER	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) RT START VALVE OPEN ANNUNCIATOR LIGHT CAME ON DURING TAKE OFF ROLL.  TAKE OFF REJECTED AND AIRCRAFT BACK TO THE GA	TE.  AIRCRAFT HAS BEEN DISPATCHED IAW MEL 80-1.  START VALVE HAS BEEN REPLACED ON JULY 09/04.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004080500006	20040805	00006	NE  	2004	8	5	CA040712008      	2	20040711	G	8530	356995	CYLINDER        			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	EXHAUST	CRACKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P30959			(CAN) DURING CLIMB AFTER A RETARDANT DROP ON A FIRE, NR 3 ENGINE BMEP BECAME ERRATIC AND A THUMPING WAS FELT AND BACKFIR	E HEARD.  THE REMAINING RETARDANT LOAD WAS JETTISONED AND THE NR 3 ENGINE WEAS SHUT DOWN AND THE PROPELLER WAS FEATHERED	. THE AIRCRAFT RETURNED TO BASE. DURING INVESTIGATION BY THE MAINTENANCE CREW, IT WAS DISCOVERED THAT NR 14 CYLINDER EXH	AUST EAR WAS CRACKED.  THE CYLINDER WAS REPLACED, ENGINE WAS GROUND RUN AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	4 	4R	4	R	 	6A4     	E264	6	C	P871
2005030800242	20050308	00242	SW  	2005	3	8	CA040712009      	1	20040602	G	5753	240014901	BLOCK           			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	C3D36C	C3D36C41582 	NE  	TE FLAP HINGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											3 HINGE BLOCKS HAD SEVERE EXFOLIATION CORROSION OVER MUCH OF THEIR SURFACE.  ONE BLOCK WAS SPLIT IN HALF AT THE LEADING 	EDGE.  THE FLAP ITSELF HAD MINOR SURFACE CORROSION.  THE LEFT FLAP WAS FOUND IN NORMAL CONDITION.  THE HINGE BLOCKS WILL	 BE REPLACED WITH NEW ONES BY AMO				1	L	7	1 	3O	3	O		2A3     	1E10	5	N	SA645NE
2005020100121	20050201	00121	CE  	2005	2	1	CA040713001      	1	20040712	G	2823	1013890253	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SELECTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FAILED FUNTIONAL TEST IAW PILOTS CHECK LIST. REPLACED						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004080500007	20040805	00007	SO  	2004	8	5	CA040713002      	1	20040630	G	7810	99044004	EXHAUST STACK   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	CRACKED         	W				O				OTHER                   				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		DE	DESCENT        	1			CA											(CAN) UNDISTINGUISHABLE ODOR OF SOMETHING BURNING, FOLLOWED BY STIFF CARB HEAT CABLE AND ENGINE RUNNING ROUGH WITH CARB 	HEAT APPLICATION.  THE RT EXHAUST STACK HAD CRACKED, HIDDEN BY THE CARBURETOR HEAT SHROUD.  DURING FLIGHT, THE HEAT FROM	 THE EXHAUST BEING EXPELLED FROM THE CRACKED STACK, MELTED THE TOP OF THE CARB HEAT SHROUD (APPROXIMATELY .5000 INCH WID	E AND 4 INCHES LONG). THE EXHAUST ESCAPING FROM THE CARB HEAT SHROUD BLISTERED THE PAINT ON THE FIREWALL, MELTED THE CAR	B HEAT CABLE GROMMET LOCATED ON THE FIREWALL AND RENDERED THE CARB HEAT CABLE INOPERATIVE IN THE CLOSED POSITION.		1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2004080500008	20040805	00008	CE  	2004	8	5	CA040713003      	1	20040605	G	3244	173K233	TIRE            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY INSPECTION, FOUND NR 2 MLG WHEEL TIRE CUT.  THE CUT WAS LOCATED ON THE SIDE WALL. WHEEL ASSEMBLY REPL	ACED.					2	L	7	2 	4F	4	F		A10CE   	E6WE
2004080500009	20040805	00009	EA  	2004	8	5	CA040713004      	1	20040630	G	1430	AW46	BOLT            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RT ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTION RT ELEVATOR FOUND SLIGHTLY LOOSE AT TORQUE TUBE.  NUT COULD NOT BE TIGHTENED DUE TO EX	CESSIVELY WORN BOLT AW4-6.  BOLT REPLACED AND NUT AN320-4.  ELEVATORS MUST BE REMOVED EVERY 400 HOURS TO ACCOMPLISH AD 8	0-25.  REPEATED REMOVAL AND INSTALLATION OF ELEVATOR CAUSING PREMATURE WARE OF THESE BOLTS AND POSSIBLE SUBSEQUENT ELONG	ATION OF HOLES TORQUE TUBE.  SUGGEST REVIEW OF AD 80-25 IS IT NECESSARY SO OFTEN.			1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
2004080500010	20040805	00010	EA  	2004	8	5	CA040713005      	2	20040708	G	8530		PUSHROD         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE CYLINDER	BENT            	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) PILOT WAS 10 MILES FROM AIRPORT. WHEN A POWER LOSS AND ENGINE VIBRATION WAS NOTED. PILOT INFORMED ATC OF SITUATION	 AND LANDED AT AIRPORT WITHOUT INCIDENT.  UPON INVESTIGATION NOTICED NO COMPRESSION AND BENT PUSH ROD AND PUSHROD HOUSIN	G ON NR 4 CYLINDER.  NR 4 CYLINDER REPLACED WITH SERVICEABLE CYLINDER AND AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004080500011	20040805	00011	EA  	2004	8	5	CA040713006      	2	20040620	G	7320	32447531917	FCU             			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) AT CRUISE ALTITUDE AT FL110 ON A MEDEVAC FLIGHT DESCENT CHECKS WERE CARRIED OUT. AS TURBULENCE WAS EXPECTED A RATE	 OF 500 RPM AND SPEED OF 170 KIAS WAS BRIEFED AFTER DESCENT. CLEARANCE RECEIVED POWER LEVERS WERE PULLED BACK TO APPROX 	3000 TORQUE.  NR 3 ENG TORQUE, RPM, T5 AND NG REMAINED AT CRUISE POWER. SEVERAL POWER LEVER EXCURSIONS WERE CARRIED OUT 	BUT THERE WAS NO CHANGE. CAPT CALLED FOR QRH ACTION. ENGINE NR 3 SHUT DOWN IAW QRH. ATC NOTIFIED. ERV REQUESTED. A 3 ENG	 LANDING CARRIED OUT. AFTER AC SHUT DOWN ON RAMP, MAINTENANCE STAFF REMOVED NR 3 COWLING TO DETERMINE IF LINKAGE HAD FAI	LED. INITIAL ASSESSMENT WAS FAILURE OF FUEL CONTROL UNIT. SUBSEQUENT APPROVAL RECEIVED TO CONDUCT 3 ENGINE FERRY FLIGHT.	2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE
2004080500012	20040805	00012	NE  	2004	8	5	CA040713007      	2	20040705	G	8530	AE92181ER	CYLINDER HEAD   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK IN HEAD WALL BETWEEN FINS 11 AND 12 COUNTING FROM BARREL, ON EXHAUST SIDE OF CYLINDER.						1	H	7	1 	3R	3	R	 	A815    	E142	6	C	P719
2005020100178	20050201	00178	CE  	2005	2	1	CA040713008      	1	20040712	G	5210	1294000371	SEAL            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PAX DOOR	TORN            	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE CREW NOTED AN INCREASED NOISE FROM THE MAIN DOOR AND WAS UNABLE TO MAINTAIN CABIN PRESSUR	E APPROPRIATE FOR 170 ALTITUDE.  THE AIRCRAFT WAS DESCENDED TO 100 AND THE FLIGHT CONTINUED TO DESTINATION.  MAINTENANCE	 WAS DISPATCHED AND FOUND THE MAIN DOOR PRESSURE SEAL HAD TORN ALLOWING THE SEAL TO COLLAPSE.  DEBRIS IN THE FORM OF GRA	VEL WAS FOUND, WHICH MAY HAVE CONTRIBUTED TO THE SEAL FAILURE. THE SEAL WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVIC	E.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004080500040	20040805	00040	EU  	2004	8	5	CA040713009      	1	20040712	G	7810	5781012041	EXHAUST STACK   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT EXHAUST STACK CRACKED FROM ONE MOUNTING HOLE OUTWARDS.  STACK REPLACED WITH SERVICEABLE UNIT. CRACK DISCOVERED 	DURING ENGINE INSPECTION.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004080500041	20040805	00041	EU  	2004	8	5	CA040713010      	1	20040712	G	3340	9736142510	SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EXTERIOR LIGHTS	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING DAILY INSPECTION AND REPORTED INTERMITTENTLY BY PILOT THAT TWO LIGHT SWITCHES ON CONTROL PANEL.  	OCCASIONALLY WILL NOT SWITCH (OFF) OR SOMETIMES WILL NOT REMAIN IN (ON) POSITION THIS WOULD OCCUR INTERMITTENTLY AND IT 	WAS DISCOVERED. PROBLEM IS AN INTERNAL MALFUNCTION. THIS OCCURRED ON (STROBE/BEACON) SWITCH AND (TAXI/LOGO) LIGHT SWITCH	.  BOTH SWITCHES ARE THE SAME PN.  SWITCHES REPLACED WITH NEW.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004080500042	20040805	00042	NM  	2004	8	5	CA040713011      	1	20040713	G	3260	1EN161RB1	SWITCH          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF WHEN THE GEAR WAS RETRACTED, THE LEFT MAIN GEAR DOOR LIGHT ON THE ENGINEERS PANEL AND THE DOOR UNSAF	E LIGHT REMAINED ILLUMINATED. THE CREW CYCLED THE GEAR AND THE LIGHT REMAINED ON, THE CREW ELECTED TO RETURN TO THE POIN	T OF ORIGIN.  THE SWITCH AND CONNECTOR WERE REPLACED AND THE AIRCRAFT DEPARTED.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA
2004080500043	20040805	00043	EA  	2004	8	5	CA040714001      	2	20040707	G	7314	RG9080J4AM	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE FUEL	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) DURING SCHEDULED MAINTENANCE THE FUEL PUMP WAS NOTED AS LEAKING FUEL. THIS PUMP IS NOT COVERED BY THE AD 2003-14-0	3 AS IT IS MODIFIED.  PUMP REPLACED BEFORE FURTHER FLIGHT.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
2005030800244	20050308	00244		2005	3	8	CA040714002      	4	20040713	G	2215	7002260723	SERVO           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AUTO PILOT	INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			26173			88072197					THE FLIGHT CREW REPORTED A INTERMITTENT BINDING IN ROLL CONTROL ON APPROACH, ESPECIALLY TO THE RIGHT.  MILD FORCE WAS RE	QUIRED TO OVERCOME, THE PILOT NOTED THAT IT DOES NOT APPEAR TO SIMPLY BE HEAVY AERODYNAMIC LOADING.  THE MAINTENANCE AFT	ER TROUBLESHOOTING POINTED THE PROBLEM TO BE THE SERVO AND REPLACED IT				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004080500044	20040805	00044		2004	8	5	CA040715001      	4	20040713	G	2330	50401100003	DISPLAY         			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) FLT UPON ARRIVAL, GUEST INFORMED FLIGHT CREW SMOKE WAS COMING FROM THE (LIVE TV) VIDEO DISPLAY UNIT (TV SCREEN). C	APTAIN IMMEDIATELY TURNED OFF POWER TO SYSTEM AND AIRCRAFT PROCEEDED TO GATE AND DEPLANED GUESTS. LIVE TV TECHNICIAN, TR	AVELING ONBOARD AIRCRAFT AS PART OF INITIAL INSTALLATION SUPPORT PROGRAM REPLACE DVDU SCREEN FROM SEAT BACK IAW LTV-AMM-	23-32-03 AND ISSUED MEL 25-10-5.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.  DURING RON THAT EVENI	NG, LIVE TV TECHNICIAN COMPLETED LIVE TV 1ST LEVEL OPERATIONAL CHECK IAW LIVE TV AMM-23-32-03 -SYSTEM CHECKED SERVICEABL	E. VDU RE-CONNECTED, MEL CLEARED AND AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2005030800247	20050308	00247	NM  	2005	3	8	CA040715002      	1	20040710	G	2752	734181D	BALLSCREW       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE PERFORMING THE REPEAT INSPECTION REQUIREMENTS OF CF-2002-26R1 THE NR 4 RT BALLSCREW ACTUATOR WAS FOUND TO HAVE A T	OTAL FREEPLAY BACKLASH OF .192 INCH.  THE LAST INSPECTION HAD BEEN DONE 997 HRS AND 863 CYC PREVIOUSLY AND AT THAT TIME 	WAS .030 INCH.  THE ACTUATOR WAS REPLACED WITH AN OVERHAULED UNIT FROM HAMILTON SUNDSTRAND.  THE AD REQUIREMENTS INVOLVE	 THE MEASURING OF THE BACKLASH BETWEEN THE SCREW JACK ROD AND THE NUT WHICH WAS STILL FOUND TO BE WITHIN SERVICEABLE LIM	ITS HOWEVER THE TOTAL FREEPLAY BACKLASH WHICH COMPRISES OF THIS BACKLASH MEASUREMENT AS WELL AS THE FREEPLAY BETWEEN THE	 BALLSCREW NUT AND THE ACTUATOR BODY WAS FOUND TO BE EXCESSIVE.  THE INSERVICE LIMIT FOR THIS MEASUREMENT IS .057 INCH.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800251	20050308	00251		2005	3	8	CA040715003      	4	20040714	G	2397		WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COMMS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPON VISUAL INSPECTION OF THE RADIO MANAGEMENT UNITS (RMU) WIRE BUNDLES, A WIRE IN THE NR 1 RMU BUNDLE WAS FOUND TO BE D	AMAGED BEYOND THE POINT OF EXPOSURE OF BARE WIRE AND APPEARS TO BE CHAFED APPROXIMATELY ONE QUARTER THE WAY THROUGH.  TH	E CHAFFING OCCURRED AGAINST A STATIC SOURCE TEE FITTING BEHIND AND TO THE RIGHT OF THE NUMBER ONE RMU.				1	L	7	2 	4F	4	F		A22CE   	E1NE
2005030800254	20050308	00254	CE  	2005	3	8	CA040715004      	1	20040707	G	2432	7624308001001	BATTERY         			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					EMERGENCY	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											DURING ENGINE START WITH GROUND POWER UNIT AND AVIONICS ON, ALL 4 DISPLAY UNITS WENT BLACK AND THEN LIT UP AGAIN AFTER E	NGINE STARTED.  MAINTENANCE DISCOVERED WITH A CAPACITY CHECK ON THE EMERGENCY BATTERY THAT 1 CELL HAD FAILED WHICH CAUSE	D THE VOLTAGE TO DROP BELOW 22 VOLTS UNDER A HEAVY LOAD.  EMERGENCY BATTERY REPLACED.  EMERGENCY BATTERY IS AN ON CONDIT	ION ITEM WITH A CAPACITY CHECK EVERY 3 MONTHS.  AS THIS BATTERY WAS OVER 5.5 YEARS OLD WE WOULD RECOMMEND A LIFE LIMIT O	F NO MORE THAN 5 YEARS PUT ON THESE BATTERIES.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE
2004080500045	20040805	00045	NM  	2004	8	5	CA040715005      	1	20040714	G	1420		CONNECTOR       			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	CONTAMINATED    	W				E	B			ENGINE SHUTDOWN         	EMER. DESCENT           			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA								666325			(CAN) AC RETURNED BECAUSE OF A NR 2 ENG OVERHEAT LIGHT ILLUMINATING AT 23,000 FT. AND WOULD NOT EXTINGUISH. ENG WAS SHUT	DOWN IN FLIGHT IAW QRC AND LANDED WITH INCIDENT, CFR FOLLOWED AC TO THE GATE.  AFTER TAXIING TO GATE, NR 3 AND NR 4 MAIN	 WHEEL FUSE PLUGS LET LOOSE. BOTH MAIN WHEELS REPLACED. ON ENGINE OVERHEAT SYSTEM, MAINT FOUND OIL CONTAMINATION IN ONE 	OF THE ENGINE CONNECTORS. MAINT CLEANED CONNECTORS AND OTHER THAN THAT COULD NOT FAULT SYSTEM. MAINT REPLACED FIRE DETEC	TION UNIT FOR TROUBLESHOOTING PURPOSES.  AC GROUND CHECKS SERVICEABLE AND IS BEING POSITIONED THIS AFTERNOON FOR SCHEDUL	ES FLIGHT PLAN.  WILL KEEP AN EYE ON THIS ONE AND ADVISE OF ANY FURTHER DEVELOPMENT SHOULD THEY RE-OCCUR.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004080500046	20040805	00046	WP  	2004	8	5	CA040715006      	1	20040715	G	1430	65678	BOLT            			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	ROCKER ARM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, AN OIL LEAK WAS DISCOVERED ON THE RT ENGINE CYLINDER POSITION NR 2.  UPON INVESTIGATION AND REC	TIFICATION, THE MAINTENANCE CREW WAS ATTEMPTING TO REPLACE THE O-RINGS ON THE EXHAUST ROCKER ARM RETAINING BOLT. THE RET	AINING NUT AND COTTER PIN CAME OFF AS A COMPLETE UNIT. IT WAS NOTED THAT THE BOLT HAD SHEARED AT THE FIRST ROW OF THREAD	S. THE BOLT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4R	4	R	 	A25WE   	E259	6	C	P8879
2005030800257	20050308	00257	CE  	2005	3	8	CA040716001      	1	20040716	G	5312		PRESSURE BLKHD  			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					FUSELAGE	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18669								AIRCRAFT WAS PARKED ON THE RAMP. MAINTENANCE PERSONNEL WANT TO TOW THE AIRPLANE.  WHEN STARTING TO PULL THE AIRPLANE THE	 NOSE LANDING GEAR ACTUATOR UPPER ATTACHMENT BRACKET FAILED.  AFTER THE INCIDENT THE PRESSURE BULKHEAD FOUND TO BE TORN 	AT THE B.L 0.0 AT THE UPPER SECTIONS.  ALSO, THE ACTUATOR UPPER ATTACHMENT SUPPORT BRACKET WAS TORN AT THE CONNECTION TO	 THE PRESSURE BULKHEAD.  THE PARKING BRAKE WAS LEFT APPLIED.			2	L	7	2 	4F	4	F		A10CE   	E6WE
2005030800259	20050308	00259	NM  	2005	3	8	CA040716002      	1	20040715	G	3234	7SC0143	SELECTOR VALVE  			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						433					AFTER THE ABOVE AIRCRAFT WAS FERRIED DUE TO A GEAR INDICATION PROBLEM, THE LANDING GEAR SELECTOR VALVE WAS FOUND AT FAUL	T.  UPON REPLACING THE INITIAL SELECTOR VALVE (P/N 7SC0143) WITH THE ABOVE (S/N 433) AND GEAR SWINGS WERE CARRIED OUT IT	 WAS DISCOVERED THAT WHEN THE GEAR WAS SELECTED UP THE GEAR WOULD GO DOWN AND WHEN THE GEAR WAS SELECTED DOWN THE GEAR W	OULD GO UP.  A SECOND LANDING GEAR SELECTOR VALVE WAS INSTALLED GEAR SWINGS CARRIED OUT AND THE AIRCRAFT WAS RETURNED TO	 SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005030800262	20050308	00262	SW  	2005	3	8	CA040716004      	1	20040628	G	2460	51509002R	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					DC SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											GENERATOR WOULDN'T COME ONLINE, NR 1 AND NR 1 SWAPPED FOR TROUBLESHOOTING, CONTROL CONFIRMED TO BE AT FAULT.  CONTROL UN	IT REPLACED, GENERATOR BALANCING C/O AND A/C RETURNED TO SERVICE.  THIS UNIT CONTAINED WATER WHEN REMOVED.					1	G	7	1 	4U	4	U		H4SW    	E22EA
2005012400021	20050124	00021	NE  	2005	1	24	CA040716007      	2	20040712	G	8500		DIAPHRAGM       	PWA         		DOUG  	DC4   	C54         	3021506	WP  	PWA   	R2000 	R20007M2    	52023	NE  					ACCELERATOR PUMP	DAMAGED         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE NR 4 ENGINE STARTED TO BACKFIRE AND SHAKE.  THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED.	  THE FLIGHT RESUMED WITHOUT INCIDENT.					2	L	7	4 	4R	4	R		A762    	5E5
2005012400022	20050124	00022	NE  	2005	1	24	CA040716008      	2	20040712	G	8500	R20007M2	ENGINE          			DOUG  	DC4   	C54         	3021506	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	NR 4	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								BP700326			(CAN) DURING CLIMB THE NR 4 ENGINE STARTED TO BACKFIRE AND SHAKE. THE ENGINE WAS SHUT DOWN AND THE PROPELLER FEATHERED. 	THE FLIGHT RESUMED WITHOUT INCIDENT.					2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603
2005012400023	20050124	00023	NE  	2005	1	24	CA040716009      	2	20040714	G	8500		CASE            			DOUG  	DC4   	C54         	3021506	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	NR 4 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE NR 4 ENGINE WOULD NOT GOVERN, THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED.  THE AIRCRAFT 	RETURNED TO BASE WITHOUT FURTHER INCIDENT.					2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603
2004123000131	20041230	00131	SW  	2004	12	30	CA040719001      	1	20040715	G	2432	1656	BATTERY         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MASTER	OVERHEATED      	W				A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			J			WARNING INDICATION        			CR	CRUISE         	1			CA											THE 'BATTERY TEMP' WARNING LIGHT ILLUMINATED ON ROUTE.  THE BATTERY WAS TURNED OFF FOR THE REMAINDER OF THE FLIGHT.  UPO	N LANDING AND SHUTTING DOWN , THE PILOT NOTICED THAT THE BATTERY FELT VERY HOT TO THE TOUCH.  WHILE TALKING TO THE MAINT	ENANCE DEPT ON THE PHONE, THE 'BATTERY HOT' LIGHT CAME ON. THE BATTERY WAS REPLACED WITH A SERVICEABLE ONE BEFORE FURTHE	R FLIGHT. THE VOLTAGE REGULATOR WAS CHECK ED DURING THE GROUND RUN FOUND TO BE WITHIN LIMITS.			1	G	7	1 	3U	3	U		H2SW    	E4CE
2004123000132	20041230	00132	SW  	2004	12	30	CA040719002      	1	20040712	G	5220	2722181	DOOR            			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	EMERGENCY EXIT	OUT OF POSITION 	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											UPON LANDING, THE LT EMERGENCY EXIT HATCH OPENED AND FELL OUT OF POSITION.  MX ENGINEER INSPECTED THE ESCAPE HATCH AND F	OUND NO EVIDENCE OF DAMAGE.  HATCH WAS INSTALLED AND FURTHER INCIDENT HAS OCCURRED.					2	L	7	2 	4T			RT	A8SW    		6	C	3PNE
2004123000133	20041230	00133	CE  	2004	12	30	CA040719003      	1	20040719	G	2731	A41015455400	RELAY           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TRIM	INTERMITTENT    	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											CREWS REPORT THAT DURING CRUISE, THE MAIN ELECTRIC STABILIZER TRIM WOULD NOT TRIM NOSE DOWN.  CREW THEN DEACTIVATED THE 	MAIN TRIM SYSTEM AND ENGAGED STANDBY TRIM SYSTEM.  STANDBY SYSTEM FUNCTIONED NORMAL. AIRCRAFT CONTINUED AND LANDED WITH 	NO FURTHER FAULTS.  MAINTENANCE T/S FOUND REALLY P/N A410-1545654-00 INTERMITTENT.   REPLACED.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
2005030800264	20050308	00264	EA  	2005	3	8	CA040719004      	2	20040716	G	7414	D6LN3200	MAGNETO         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											OIL LEAK WAS DISCOVERED AT MAGNETO MOUNTING FLANGE GASKET.  UPON REMOVAL OF UPPER AND LOWER MAGNETO MOUNT CLAMPS (P/N 66	M19385), WEAR AND FRETTING OF THE MAGNETO MOUNTING FLANGE WAS DISCOVERED.  WHEN CHECKED, THE MAGNETO WAS STILL CORRECTLY	 TIMED TO THE ENGINE AND NO EXPLANATION CAN BE OFFERED AS TO WHY THE MAGNETO DID NOT PARTIALLY ROTATE AND AFFECT IGNITIO	N TIMING.  IN ADDITION, THE NUT AND LOCKWASHER WAS STILL HOLDING THE CLAMP TIGHT TO THE ENGINE.  THE SUBMITTER HAS NEVER	 SEEN A SIMILAR PROBLEM ON MAGNETOS ATTACHED WITH OLDER STYLE (P/N 75965) MOUNT CLAMPS.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P52GL
2005030800265	20050308	00265	EA  	2005	3	8	CA040719005      	2	20040716	G	7414	D6LN3200	MAGNETO         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											OIL LEAK WAS DISCOVERED AT MAGNETO MOUNTING FLANGE GASKET.  UPON REMOVAL OF UPPER AND LOWER MAGNETO MOUNT CLAMPS (P/N 66	M19385), WEAR AND FRETTING OF THE MAGNETO MOUNTING FLANGE WAS DISCOVERED.  WHEN CHECKED, THE MAGNETO WAS STILL CORRECTLY	 TIMED TO THE ENGINE AND NO EXPLANATION CAN BE OFFERED AS TO WHY THE MAGNETO DID NOT PARTIALLY ROTATE AND AFFECT IGNITIO	N TIMING.  IN ADDITION, THE NUT AND LOCKWASHER WAS STILL HOLDING THE CLAMP TIGHT TO THE ENGINE.  THE SUBMITTER HAS NEVER	 SEEN A SIMILAR PROBLEM ON MAGNETOS ATTACHED WITH OLDER STYLE (P/N 75965) MOUNT CLAMPS.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P52GL
2005030800266	20050308	00266	WP  	2005	3	8	CA040719006      	1	20040716	G	7810	NAS27844	TURNBUCKLE      			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					TAIL PIPE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING INSPECTION MAINTENANCE CREW NOTED THAT THE RIGHT HAND ENGINE OUTBOARD EXHAUST SUPPORT TURNBUCKLE HAD SHEARED CAUS	ING THE TAILPIPE TO REST ON THE BOTTOM OF THE EXHAUST SHROUD INSTEAD OF BEING SUPPORTED IN THE CENTER.  THE TURNBUCKLE W	AS REPLACED WITH A SERVICEABLE PART AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4R	4	T		6A6     	E282
2005030800267	20050308	00267	GL  	2005	3	8	CA040720001      	3	20040713	G	6110		SKIN            			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER	LIGHTNING STRIKE	W				O				OTHER                   				C			F.O.D.                    			CR	CRUISE         	1			CA											IN CRUISE OUT OF JFK NOTICED LIGHTNING STRIKE ON LEFT PROP/SITUATION WAS EVALUATED AND ALL PARAMETERS WERE NORMAL.  FLIG	HT WAS CONTINUED AND UPON LANDING ON YOW BASE NOTICED UPON CLOSE INSPECTION: LEFT PROP BLADE DAMAGED, PROP REPLACED.  LE	FT OUTBOARD AILERON TAB DAMAGED, TAB REPLACED.  REAR ELEVATOR QUADRANT DAMAGED, QUADRANT REPLACED.  LOWER ELEVATOR CABLE	 DAMAGED, CABLE REPLACED.  ELEVATOR SERVO CABLE DAMAGED, CABLE REPLACED.  REAR NAV LIGHT DAMAGED, NAV LIGHT ASSEMBLY REP	LACED.  LEFT ENGINE REMOVED FOR INTERNAL INSPECTION, IAW/MM-CH 72-00-27R10 AND PARTS REPLACED AS REQUIRED.		1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA
2005030800268	20050308	00268	SO  	2005	3	8	CA040720002      	1	20040713	G	5711	68621003	SPAR            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RT WING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURNG 100 HOURS INSPECTION, RT WING REAR SPAR ATTACHMENT BOLT P/N NAS464P6LA6 FOUND LOOSE.  BOLT WAS REMOVED AND FOUND S	EVERLY DAMAGED (DEFORMED) AND BOTH SPAR FITTINGS P/N 68621-003 AND 66762-000 BOLT HOLES FOUND ELONGATED.  BOTH SPAR FITT	INGS WERE REPLACED, NEW BOLTS INSTALLED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920
2005030800269	20050308	00269	NM  	2005	3	8	CA040720003      	1	20040717	G	2110		COMPRESSOR      			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					CABIN AIR	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											DURING TAKEOFF, THE CREW REPORTED A RUSH OF HOT AIR IN THE COCKPIT AND A BURNING ODOR.  THE CREW DECIDED TO RETURN TO BA	SE.  AIRCRAFT LANDED WITHOUT INCIDENT.  MX APPLIED MEL 36-06 WITH THE NR 1 BLEED CLOSED AND THE LT NR 2 ENGINE/APU BLEED	 OPENED AFTER TAKEOFF.  THIS IS THE SAME SCENARIO AS THE PILOT'S QRH.  THE AIRCRAFT WAS DISPATCHED AND NO FURTHER INCIDE	NT DURING SUBSEQUENT FLIGHT.  FURTHER TROUBLESHOOTING FOUND THAT THE NR 1 AIR CYCLE MACHINE WAS UNSERVICEABLE, REPLACED 	AND THE MEL CLEARED.		2	L	7	3 	4F	4	F		A3WE    	E2EA
2005030800270	20050308	00270	CE  	2005	3	8	CA040720004      	1	20040710	G	2421	10300B	ALTERNATOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2G     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											IN CRUISE, THE PILOT NOTICED THAT THE ALTERNATOR FAILED.  DECIDED TO LAND AT THE NEAREST AIRPORT.  ON SITE, NOTICED THAT	 THE ALTERNATOR GROUND WIRE WAS CUT AND WAS CONTACTING THE POSITIVE WIRE, WHICH IN TURN CAUSED THE CONTROL BOX TO FAIL. 	 REPLACED THE ALTERNATOR, THE VOLTAGE REGULATOR AND ALL THE ELECTRICAL CONNECTIONS, AIRCRAFT SERVICEABLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005030800272	20050308	00272		2005	3	8	CA040720005      	4	20040717	G	6122	A6441FN606	PROPELLER       			LKHEED	188   	188A        	5262602	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			DE	DESCENT        	1			CA						HC2754					PROPELLER OVERSPEED ON DESCENT INTO XXXX, THE ENGINE WAS SHUT DOWN AND AIRCRAFT LANDED WITHOUT INCIDENT.  PROP ASSEMBLY 	WAS CHANGED, GROUND RUN AND PITCH LOCK TESTED SERVICABLE.  AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	4 	4T	4	T	RT	4A22    	E282	6	C	P898
2005030800274	20050308	00274	SO  	2005	3	8	CA040720006      	1	20040712	G	1430	LW25063	SCREW           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ACCESSORY HOUSIN	SEPARATED       	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA											THESE TWO BOLTS HOLD THE FUEL PUMP IDLER GEAR SHAFT TO THE ACCESSORY HOUSING.  FAILURE OF THE BOLTS ALLOWED THE IDLER GE	AR AND SHAFT TO DROP TO THE BOTTOM OF THE ACCESSORY CASE.  THE FUEL PUMP STOPPED TURNING AND THE ENGINE QUIT.  ENGINE RE	STARTED, USING ELECTRIC PUMP AND AIRCRAFT RETURNED TO XXX.  BOTH BOLTS WERE DISCOLORED AT FRACTURE SITE.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005030900001	20050309	00001	CE  	2005	3	9	CA040720007      	1	20040621	G	3260	YZ2RQ1T	UPLOCK SWITCH   			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360GB     	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	RT MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DISCOVERED SWITCH CRACKED ALONG MATING HALVES.  SWITCH HALVES DO NOT APPEAR TO HAVE BEEN BONDED PROPERLY.						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
2005030900002	20050309	00002	CE  	2005	3	9	CA040720008      	1	20040713	G	3220	04425037	FORK            	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13096								NOSE GEAR FORK WAS FOUND 2 INCH CRACK IN THE RADIUS.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2005030900003	20050309	00003	NM  	2005	3	9	CA040720009      	1	20040717	G	3310	RV4NBYSD502A	RHEOSTAT        			DHAV  	DHC8  	DHC8301     	1386003	NM  						HAMSTD	14SF	14SF23      	NE  	COCKPIT	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOTS REPORTED SMOKE IN COCKPIT DURING FLIGHT, EMERGENCY LANDING CARRIED OUT.  INVESTIGATION FOUND BURNT RHEOSTAT	 FOR THE PILOTS READING LIGHT.					2	H	7	2 	4T			RT	A13NM   		6	C	P7NE
2005030900004	20050309	00004	EA  	2005	3	9	CA040720010      	1	20040718	G	5270	215260994	BRACKET         			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	DOOR SENSOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING FOREST FIRE SUPPRESSION ACTION, THE PILOTS NOTICED THAT THE LT BOMB DOOR INDICATOR LIGHT ON THE ANNUNCIATOR PANEL	 DISPLAYED A 'DOOR UNLOCKED' INDICATION.  FIRE SUPPRESSION ACTION WAS ABORTED AND THE AIRCRAFT RETURNED TO BASE FOR MAIN	TENANCE.  AMES INSPECTED THE WATER DROP SYSTEM AND FOUND THE BRACKET THAT HOLDS THE LT WATER DOOR LOCKED INDICATION MICR	OSWITCH WAS BROKEN.(SEE ITEM 71 IN ATTACHED FIGURE).  A NEW BRACKET WAS INSTALLED, MICROSWITCH ADJUSTED AND THE SYSTEM F	UNCTION TESTED.  AIRCRAFT WAS RELEASED FOR RETURNED TO SERVICE.  IT APPEARS FROM OBSERVING THE LACK OF 'FRESH BREAKAGE M	ETAL' ON THE BROKEN BRACKET THAT THE BRACKET MAY HAVE BEEN CRACKED FOR SOME TIME BEFORE IT FAILED.	2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2005030900005	20050309	00005	CE  	2005	3	9	CA040721001      	1	20040720	G	2150	24192273	DRAIN LINE      			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					AIR CON	BURST           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A SCHEDULE INSPECTION, FOUND AIR CONDITIONING DRAIN LINE BURST.  THE INSPECTION OF THE CHECK VALVE WAS CARRIED AN	D VALVE FOUND TO BE OPERATIVE.  DRAIN TUBE WAS REPLACED.					2	L	7	2 	4F	4	F		A10CE   	E6WE
2005030900006	20050309	00006	SO  	2005	3	9	CA040721002      	1	20040711	G	3230	42042	STRUCTURE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19930								WHILE INSPECTING GEAR A CRACK WAS NOTICED IN THE PAINT.  CRACK EXTENDS FROM INSIDE CURVE HALF WAY TO BOLT HOLE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005030900007	20050309	00007	NE  	2005	3	9	CA040721003      	2	20040716	G	8520	PN15373	PISTON          			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  					NR 1 CYLINDER	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											PILOT EXPERIENCED PARTIAL POWER INTERUPTION ON TAKEOFF.  ABORTED TAKEOFF.  BORESCOPE INSPECTION DISCOVERED BROKEN PISTON	 IN NR 1 CYLINDER.  PISTON REPLACED WITH OVERHAULED ASSEMBLY AND ENGINE RE-ASSEMBLED AND TESTED SERVICEABLE.					1	L	7	1 	3R	3	R		EXPA1L71	E143
2005030900008	20050309	00008	EA  	2005	3	9	CA040722001      	1	20040721	G	1430	711731	BOLT            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG SCISSOR LINK	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING THE DAILY INSPECTION, IT WAS DETECTED THE TOP BOLT IN THE NOSE GEAR SCISSOR LINK WAS SHEARED.  THE GEAR WAS INSPE	CTED AND NO DEFECTS NOTED.  THE BOLT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (HAVE SEEN THIS ONCE BEFORE ON A	NOTHER TWIN OTTER ABOUT 6 MONTHS AGO) THE BOLT SHEARS WHERE THERE IS A GROOVE CUT IN THE SHANK FOR LUBRICATION.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2005030900009	20050309	00009	NM  	2005	3	9	CA040722002      	1	20040719	G	1430	BACB30MT7T23	BOLT            			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					STAB FITTING	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHEN THIRD PARTY AMO WAS INSPECTING THE FWD STABILIZER FITTINGS ATTACHED TO THE AFT SPAR FOR SB737-57A1266 ON A/C 743 FO	UND THE O/B FITTING CRACKED.  ON FURTHER INVESTIGATION, FOUND THAT ALL FOUR BOLT HEADS ON THE AFT O/B FITTING WERE SHEAR	ED OFF, AND THE FITTING BEGINNING TO LIFT OFF THE BEAM.  THIS FITTING IS NOT PART OF THE SB.  AS THE BOLT HEADS ARE MISS	ING CAN ONLY PROVIDE THE PART NUMBERS PER THE IPC.  AS THIS IS NOT PART OF ANY SB THAT CAN FIND, BUT THE SB THEY WERE WO	RKING FROM DESCRIBES SERIOUS MLG FAILURE AND/OR LOSS OF HYDRAULIC FLUID AS A FACTOR, SHOULD A BRACKET FAIL, THOUGHT THAT	 AN SDR WAS APPROPRIATE.  UNFORTUNATELY HAD REMOVED THE BRACKET BEFORE COULD GET ANY BETTER PICTURES, BUT HAVE RETAINED 	2	L	7	2 	4F	4	F		A16WE   	E2EA
2005030900010	20050309	00010		2005	3	9	CA040722003      	4	20040627	G	3418	6005915229	COMPUTER        			CNDAIR	CL601 	CL6013A     	8070802	EA  										STALL WARNING	MALFUNCTIONED   	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											CREW REPORTED ON ROTATION, STICK SHAKER ACTIVATED EVEN THOUGH A/C WASN`T IN A STALL.  SHAKER CONTINUED UNTIL POINT C/B`S	 WERE OPENED AS RECOMMENDED IN AFM.  CREW ELECTED TO RETURN TO AIRPORT & LANDED UNEVENTFULLY.  INVEST REVEALED THAT PRIO	R TO FLT, PILOTS STALL PROTECTION SYSTEM IND NEEDLE SHOWING IN RED (PUSHER) ZONE AS SOON SINGLE CHANNEL SELF-TEST INITIA	TED, WHICH IS NOT PER AFM & SHOULD HAVE INITIATED SOME CONCERNS AT THAT POINT.  IT IS BELIEVED THAT THE PILOTS SPS INDIC	ATOR NEEDLE WAS IN RED POSITION AT ROTATION, WHICH GENERATED THE SHAKER ACTIVATION.  THE SPS COMPUTER WAS REPLACED, FUNC	TIONAL TEST WERE COMPLETED NORMALLY.	2	L	7	2 	4F			RT	A21EA
2004101300018	20041013	00018	NE  	2004	10	13	CA040722004      	2	20040713	G	7250	311899101	TURBINE BLADES  	PWA         	PT6A67D     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4N	HCE4N3      	NE  	HOT SECTION	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						PCEPS0161					(CAN) THE ENGINE HAD LANDED AFTER A FLIGHT AND WAS LOADED WITH FREIGHT.  AFTER AN UNSUCCESSFUL START ATTEMPT (ONLY 5 PER	CENT NG REACHED), A STARTER-GENERATOR WAS REPLACED. THE ENGINE WOULD NOT START SINCE IT WAS SEIZED.  A SUBSEQUENT INVEST	IGATION SHOWED THAT THE AFT SIDE OF THE CT DISK HAD RUBBED AGAINST THE CT STATOR AIR SEAL.  THE ROOT CAUSE WAS BELIEVED 	TO BE TIGHT CLEARANCES BETWEEN THE TWO COMPONENTS DUE TO A STEP AT THE INTERFACE OF THE FIR TREE AND THE BLADE PLATFORM.	   THE STEP APPEARS TO BE MATERIAL LEFT OVER FROM AN INCOMPLETE MACHINING PROCESS DURING MANUFACTURE.  OTHER BLADES OF T	HE SAME PN DO NOT HAVE THE STEP.  CT BLADE PN 3118591-01 IS ALSO BELIEVED TO BE AFFECTED.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004101300021	20041013	00021	NE  	2004	10	13	CA040722005      	2	20040713	G	7210	MS949034	BOLT            	PWA         							PWA   	PT6   	PT6A65AR    	52043	NE  					RGEARBOX	FAILED          	W				E				ENGINE SHUTDOWN         				D	E	W	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	INADEQUATE Q C            	CR	CRUISE         	1			CA						PCE97494					(CAN) THE ENGINE WAS IN FLIGHT WHEN IT SUFFERED A FAILURE.  THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED.  AN INVESTI	GATION FOUND THAT THE BOLT HEAD OF A 1ST STAGE CARRIER MACHINE HEX BOLT HAD FAILED.  IT WAS INGESTED BY THE 1ST STAGE PL	ANETARY GEAR SYSTEM.  THE SUBSEQUENT FAILURE ON THE 1ST STAGE SUN GEAR AND 1ST STAGE PLANETARY GEARS CAUSED EXCESSIVE VI	BRATION AND AN OVERSPEED CONDITION.								4	T			E4EA
2004101300022	20041013	00022	NE  	2004	10	13	CA040722006      	2	20040722	G	8510	519593	NOSE COWL       			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	R2800CA3    	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	K		INADEQUATE Q C            	FLUID LOSS                		CL	CLIMB          	1			CA								NK510954			(CAN) AIRCRAFT WAS ON CLIMB OUT AFTER WATERSCOOPING OPERATION. THE RT ENGINE OVERSPED BEYOND 3400 RPM AT 20.						2	H	7	2 	4R	4	R	RT	A14EA   	5E8	6	C	P871
2005030900011	20050309	00011		2005	3	9	CA040722007      	1	20040702	G	1430	08515591	LOCK TAB        								CONT  	O470  	IO470*      	17026	SO  					ENGINE MT BOLTS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ON THE FOLLOWING CESSNA AIRCRAFTS, FOUND THE LOCK TABS FOR ENGINE MOUNT BOLTS TO BE EITHER MISSING, BROKEN, OR INCORRECT	 HARDWARE USED TO REPLACE THEM.  C-205 IO470C-180  I0470C-182  IO470C-185  IO520C-206  IO550 WOULD LIKE TO NOTIFY ALL AI	RCRAFT OWNERS THAT USE THESE BOLT LOCK TABS TO INSPECT THEM.									3	O			E1CE
2004101300023	20041013	00023	CE  	2004	10	13	CA040723001      	1	20040722	G	2435		BEARING         		23085001    	BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	STARTER GEN	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						Y0195					(CAN) WITH AIRCRAFT IN CRUISE FLIGHT A (LT GEN TIE OPEN) ANNUNCIATOR LIGHT CAME ON.  GENERATOR TIE RESET AS IAW CHECK LI	ST.  SHORTLY THEREAFTER THE (LT GEN TIE OPEN) CAME ON FOLLOWED BY THE (LT GEN FAIL) LIGHT ANNUNCIATOR.  AIRCRAFT SECURED	 IAW CHECK LIST AND AIRCRAFT RETURNED TO BASE.  SHORTLY BEFORE LANDING THE AIRCRAFT EXPERIENCED LT ENGINE VIBRATION AND 	TORQUE FLUCTUATIONS AT LOW POWER SETTINGS.  AIRCRAFT LANDED UNEVENTFUL.  MAINTENANCE REMOVED SUSPECT GENERATOR AND FOUND	 END BEARING FAILED.  GENERATOR REPLACED WITH OVERHAULED UNIT.  AIRCRAFT GROUNDRUN, VIBRATION AND TORQUE APPEARED NORMAL	.  AIRCRAFT RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004101300024	20041013	00024	EU  	2004	10	13	CA040723002      	1	20040719	G	5610	350902001	TRACK           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					WINDOW	DEPARTED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) FORWARD LT WINDOW SLIDER DEPARTED WHILE AIRCRAFT IN FLIGHT.  THE FELT ON THE SLIDER WINDOW WAS WORN OR MISSING, WH	ICH CAUSES AN EXCESSIVE GAP BETWEEN THE SLIDER WINDOW AND THE TRACK.  THE SLIDER WINDOW, NOW LOOSE, VIBRATES WHILE IN FL	IGHT AND CAUSES THE LOWER PORTION OF THE SLIDER WINDOW TRACK TO FRACTURE.  THE SLIDER WINDOW MIGRATES OUT THROUGH THE CR	ACKED TRACK AND DEPARTS THE AIRCRAFT.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101300025	20041013	00025	CE  	2004	10	13	CA040723003      	1	20040712	G	3297		WIRE            			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520B    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	WARNING HORN	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) TAKEOFF, LANDING GEAR FAILED TO RETRACT.  GEAR CB POPPED IMMEDIATELY ON SELECT UP, CAUSED 3 GREEN (SAFE GEAR) LIGH	TS TO GO OUT. THE CB WAS RESET, IMMEDIATELY RE-POPPED.  MOMENTARY 3 GREEN INDICATION OF LIGHTS WHEN BREAKER WAS RESET IN	DICATING GEAR WAS STILL DOWN, LOCKED.  VISUAL, INDICATED DOWN, LOCKED.  VISUAL INSP OF BOTH MAIN, NOSE GEAR WITH IT INDI	CATED GEAR WAS DOWN, LOCKED. THERE WAS AN ELECTRICAL FAULT WITH GEAR,COULD NOT BE RESOLVED IN FLIGHT. GEAR NEVER RETRACT	ED FROM INITIAL GEAR UP SELECT.  FLYBY DETERMINED GEAR LOOKED DOWN, LOCKED, LANDED.  ONE OF CRIMPED CONNECTOR ENDS HAD C	OME LOOSE FROM WIRING CAUSING ELECTRICAL FAULT.  NEW END WAS ATTACHED TO GEAR HORN, PROBLEM RECTIFIED, SERVICEABLE.	1	L	7	2 	3O	3	O		3A10    	E8CE	5	C	P22EA
2004101300026	20041013	00026	EU  	2004	10	13	CA040723004      	1	20040517	G	6220		BUSHING         			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	25OC  	250C20R     	 	GL  					STARFLEX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M495U					(CAN) ALL 3 BUSHINGS FOUND LOOSE ON D.I. STARFLEX WAS REPLACED.						1	G	7	2 	3U	3	U		H11EU   	E4CE
2004101300027	20041013	00027	SO  	2004	10	13	CA040723005      	2	20040710	G	7414	M3590	SPRING          			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1A170	1A170DM     	GL  	RT MAGNETO	BROKEN          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA											(CAN) NO POWER TO RT MAGNETO DUE TO BROKEN IMPULSE SPRING RETARDING TIMING.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P857
2004101300063	20041013	00063	CE  	2004	10	13	CA040723006      	1	20040628	G	7120	075100125	MOUNT           			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A SMALL CRACK (LESS THAN 2MM) WAS DISCOVERED ON THE ENGINE MOUNT DURING SERVICING. THE CRACK IS LOCATED ON THE LT 	SIDE, ON THE UPPER TUBING WHICH RUNS FORE AND AFT IN BETWEEN THE FORWARD AND REAR ENGINE MOUNT PADS. THE EXACT LOCATION 	IS ONE INCH FORWARD OF THE GUSSET PLATE FOR THE REAR MOUNT PAD.				1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
2004101300068	20041013	00068	CE  	2004	10	13	CA040723007      	1	20040722	G	7603	V31	SWITCH          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT POWER LEVER	STUCK           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB THE PILOT REPORTED THE GEAR IN TRANSIT LIGHT WAS ON.  LANDING GEAR WAS EXTENDED WITH NO DIFFICULTIES AND 	MAINTENNACE WAS CONTACTED.  AIRCRAFT RETURNED TO BASE. AIRCRAFT WAS PUT ON JACKS AND THE RT POWER LEVER 70 PERCENT SWITC	H WAS FOUND STUCK.  SWITCH WAS REPLACED AND GEAR SWINGS CHECKED SERVICIBLE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA
2004101300069	20041013	00069	GL  	2004	10	13	CA040726001      	2	20040719	G	7320	23072725	HYDROMECH UNIT  			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING ADVANCING THROTTLE TO 100 PERCENT FOR TAKEOFF,  N2 DECREASED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300070	20041013	00070	SW  	2004	10	13	CA040726002      	1	20040706	G	6320	407040006	TRANSMISSION    			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) TRANSMISSION CHIP LIGHT, TRANSMISSION SENT TO OVERHAUL SHOP.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300071	20041013	00071	WP  	2004	10	13	CA040726003      	2	20040723	G	7250	31070367	BEARING CAGE    								GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON RECEIVING A REQUEST, FROM WEAR CHECK, DUE TO A BAD ENGINE OIL SAMPLE, A TEAR DOWN OF THE SUSPECT ENGINE REVEA	LED THAT THE HIGH SPEED PINION BEARING AND CAGE WERE WORN AND THE SILVER COATING FLAKINGOFF OF THE COMPONENTS. THE PINIO	N HAS BEEN REPLACED. TWO SIMILAR SDR'S HAVE BEEN ISSUED WITH THIS SAME PROBLEM BY PERIMETER.									4	T			E4WE
2004101300072	20041013	00072		2004	10	13	CA040726004      	4	20040704	G	2397	RMU850	WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 1 RMU	CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) THE PILOT REPORTED THAT THE NR 1 RMU FLASHED RED AND THAT THEY COULD SMELL SOMETHING BURNING WITH NO VISIBLE SMOKE	. THE NR 1 RMU WAS REMOVED AND INSPECTED WITH NOTICEABLE DAMAGE APPARENT.  AN INSPECTION OF THE WIRE BUNDLE CONNECTING T	HE UNIT WAS CARRIED OUT AND TWO DC POWER WIRES WERE FOUND CHAFED THROUGH THE INSULATION. THE REQUIRED REPAIRS WERE CARRI	ED OUT AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE
2004101300073	20041013	00073	EU  	2004	10	13	CA040726005      	1	20040719	G	1420	103871501	CONNECTOR       			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					EXCITER BOX	DEBONDED        	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE FLIGHT CREW WAS UNABLE TO START NR 1 ENGINE.   NR 1 IGNITION EXCITER UNIT WAS DETERMINED TO HAVE FAILED. UPON 	INVESTIGATION IT WAS FOUND THAT THE CONNECTOR PLUG ATTACHMENT ON THE EXCITER BOX HAD DEBONDED CAUSING THE FAILURE. THE U	NIT WAS REPLACED.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE
2004101300074	20041013	00074	EU  	2004	10	13	CA040726007      	1	20040719	G	2435		BEARING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				639  		93767					(CAN) GENERATOR HAD BEEN REPAIRED, WO NR 12585, MAR 18,2004.  INSTALLED ON VKC WITH 442.9 TSO AND 0 HOURS SINCE REPAIR. 	 APPARENT BEARING FAILURE. WOULD NOT ENGAGE/TURN ON, AN ATTEMPTED START.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004101300075	20041013	00075	EU  	2004	10	13	CA040726008      	1	20040718	G	6220	350A31191600	STARFLEX        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAIN ROTOR HEAD	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STARFLEX ARM END BUSHING ON YELLOW BLADE ARM BECAME LOOSE AROUND ADHESIVE JOINT OF CARBIDE BUSH AND A GAP, BEYOND 	SERVICEABLE LIMITATIONS, DEVELOPED. STARFLEX REPLACED WITH NEW PART IAW AS 350MWC.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004101300136	20041013	00136	SW  	2004	10	13	CA040726009      	1	20040624	G	6330		SUPPORT         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					PYLON DAMPER	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED THAT THE AIRCRAFT WOULD ENTER INTO PYLON ROCK VERY EASILY. TRANSMISSION MOUNTS AND FRICTION DAMPERS	 WERE BEING REPLACED WHEN IT WAS FOUND THAT THE FRICTION DAMPER MOUNT SUPPORTS WERE CRACKED AND AS A RESULT NOT ATTACHED	 TO THE AIRFRAME. SUPPORTS WERE REPLACED, NEW MOUNTS AND DAMPERS INSTALLED. A/C TEST FLOWN, PYLON ROCK WAS NO LONGER PRE	SENT, A/C RETURNED TO SERVICE.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA
2004101800041	20041018	00041	EU  	2004	10	18	CA040726010      	1	20040611	G	2821	222366621101	BOWL            			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL FILTER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) BOWL ASSEMBLY LEAKING FROM ELECTRICAL CONNECTOR AT TOP OF BOWL. REPLACED WITH NEW BOWL ASSEMBLY.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2005020100014	20050201	00014		2005	2	1	CA040727002      	4	20040721	G	2562	DK100	CASE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ACOUSTIC BEACON	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UNDERWATER ACOUSTIC BEACON DK100, S/N DJ6834, HAS BEEN ALTERED TO REPLACE BATTERY, BY DRILLING HOLES IN BATTERY CO	VER END CAP (TO RECEIVE A SPANNER WRENCH). THIS ALTERATION HAS UNDERMINED INTEGRITY OF BEACON.  REPLACEMENT BATTERY KITS	 SUPPLIED BY OEM ARE APPROVED FOR MODEL DK120 ONLY. MFG OF MODEL DK100, PROHIBITS REPLACEMENT OF BATTERIES IN FIELD, DOE	S NOT PROVIDE INSTRUCTIONS FOR FIELD REPLACEMENT, DK100 MODELS MUST BE RETURNED TO FACTORY FOR SERVICE (REF: MFG TECH MA	NUAL).  INFORMAL INVESTIGATION REVEALED; AMO WHO SERVICED PART DID NOT HAVE AUTHORITY NOR AN UP-TO-DATE CMM FOR PART.  U	NDERWATER ACOUSTIC BEACON DK100, S/N DJ6834, WAS DECLARED UNSERVICEABLE AND IS HELD IN QUARANTINE.	2	L	7	2 	4F	4	F	RT	        	E25NE
2005031000072	20050310	00072	NE  	2005	3	10	CA040727003      	2	20040720	G	7210		BOLT            	PWA         							PWA   	PT6   	PT6A67D     	 	NE  					RGB	FAILED          	W				E				ENGINE SHUTDOWN         				D	E	W	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	INADEQUATE Q C            	CR	CRUISE         	1			CA			15234					PS114332			DURING OVERHAUL ASSY OF THE POWER SECTION AND 1ST STAGE REDUCTION CARRIER MACHINE HEX BOLT P/N MS9490-34 FAILED IN THE T	HREADED PORTION OF THE BOLT UNDER APPLIED TORQUE DURING INSTALLATION.  THE BOLT IS USED IN THE ASSEMBLY OF THE 1ST STAGE	 REDUCTION GEARING CARRIER IAW P&WC O/H MANUAL P/N 3038337, SECTION 72-10-00, PAGE 503, PARAGRAPH NR B.  THERE ARE TOTAL	 QTY. 6 BOLTS INSTALLED IN THE CARRIER WITH KEY-WASHERS AND ARE TORQUED TO 75 TO 85 IN-LBS. THE BROKEN PARTS HAVE BEEN D	ISPATCH TO P&WC FOR FAILURE INVESTIGATION. NOTE: THE ENGINE HAD PREVIOUSLY BEEN INVOLVED IN A PT BLADE FAILURE.							4	T			E26NE
2004101800042	20041018	00042	NE  	2004	10	18	CA040727004      	2	20040724	G	8550	125754	GASKET          			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	MAIN OIL SCREEN	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AC WAS ON A ROUTINE FLIGHT, WHEN SHORTLY AFTER TAKE OFF, CREW NOTICED THE RT ENGINE OIL PRESSURE DROPPING AND OIL 	QUANTITY INDICATION SHOWING A RAPID LOST OF ENGINE OIL. VISUAL CONFIRMATION OF A MASSIVE OIL LEAK FROM NACELLE VENT LINE	 WAS MADE BY THE ENGINEER ON BOARD. CREW SHUT DOWN AND SECURED THE ENGINE AND RETURNED TO DEPARTURE AND LANDED WITHOUT I	NCIDENT. AN INSPECTION OF THE RT ENGINE REVEALED THAT THE MAIN OIL SCREEN GASKET HAD RUPTURED WHICH CAUSED THE LARGE OIL	 LEAK. THE SCREEN WAS REMOVED AND INSPECTED WITH NO FAULT FOUND. THE OLD GASKET WAS REMOVED AND THE SURROUNDING AREA AND	 COVER WAS INSPECTED. A NEW GASKET WAS INSTALLED AND ENGINE GROUND RUNS CARRIED OUT. THE ENGINE WAS CHECKED SERVICEABLE.	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871
2004101800043	20041018	00043	GL  	2004	10	18	CA040727005      	2	20040722	G	7230	23059594	RETAINING RING  	ALLSN       		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR1 BRG HSG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAC91624					(CAN) DURING COMPRESSOR DISASSEMBLY ONE PIECE OF NR 1 BEARING HOUSING RETAINING RING WAS FOUND.  IMPELLER ASSEMBLY WAS B	ADLY DAMAGED DUE TO FOD.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL
2005012100160	20050121	00160	SW  	2005	1	21	CA040727006      	1	20040603	G	7933	206075187001	INDICATOR       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE OIL TEMP	INOPERATIVE     	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) FOUND ON TROUBLESHOOTING THAT NORMAL INDICATION EXISTED WITH GENERATOR OFF. ONCE GENERATOR WAS SWITCHED ON, THE OI	L TEMPERATURE INCREASED CONTINUOUSLY UNTIL OVER THE RED LINE. INDICATOR HAD RECENTLY BEEN REPLACED FOR A PRESSURE INDICA	TION PROBLEM. INDICATOR REPLACED, FUNCTIONALLY TESTED OK AND A/C RETURNED TO SERVICE.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2004101800044	20041018	00044	WP  	2004	10	18	CA040727007      	1	20040723	G	2913	AS664114S666	PUMP            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					HYD SYS	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, RT HYDRAULIC SYSTEM PRESSURE DECREASED TO ZERO WITH APPROPRIATE EOHP ANNUNCIATOR LIGHT ILLUMINATED. 	 AIRCRAFT LANDED BACK TO THE STATION.  THE RT HYDRAULIC SYSTEM FILTERS REMOVED AND INSPECTED.  NO CONTAMINATION FOUND.  	AIRCRAFT DISPATCHED IAW MEL 29-5.  THE RT EDP WAS REPLACED ON THE FOLLOWING DAY TO RECTIFY THE DEFECT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101800076	20041018	00076	SW  	2004	10	18	CA040727008      	1	20040603	G	2550	AN9601016	WASHER          	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					CARRIAGE ROLLERS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER FINDING MISSING CARRIAGE ROLLER WASHERS ON ANOTHER LONG RANGER,  INSPECTED AND FOUND IT TO BE THE SAME,  NO 	WASHERS.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2004101800077	20041018	00077	EU  	2004	10	18	CA040727009      	1	20040528	G	2822		BYPASS SWITCH   			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BOOST PUMP	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A FILTER ASSEMBLY PN 222-366-621-101 WAS RECEIVED ON CHL PO NR 514815 AND INSTALLED.  DURING TESTING IT WAS DISCOV	ERED THE BYPASS LIGHT WAS ON ALL THE TIME. TROUBLESHOOTING DETERMINED THE BYPASS SWITCH IS STUCK CLOSED. AS WELL THE DRA	IN VALVE WAS LEAKING UNDER NORMAL BOOST PUMP PRESSURE.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004101800078	20041018	00078	NE  	2004	10	18	CA040727010      	2	20040428	G	7310	174025120	PRESSURE VALVE  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL SYSTEM	UNSERVICEABLE   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAKING INTO FUEL WHEEL LINE WITH BOOST PUMP PRESSURE. ENGINE LIGHTING OFF FUEL WHEEL. VALVE REPLACED , NOW L	IGHTS OFF AT NEAR 17 PERCENT NG.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101800079	20041018	00079	NE  	2004	10	18	CA040727011      	2	20040401	G	7321	0164448430	FUEL CONTROL    			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NG FLUCTUATIONS OF 2 PERCENT.  FUEL CONTROL REPLACED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101800080	20041018	00080	NE  	2004	10	18	CA040727012      	2	20040423	G	7310	0174025120	PRESSURE VALVE  			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE FUEL	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) FUEL ENTERING WHEEL EARLY, VALVE CHANGED.  LIGHT OFF OCCURING NOW AT 17 PERCENT NG (NORMAL).						1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004101800081	20041018	00081	NE  	2004	10	18	CA040727013      	2	20040520	G	7532	9550161210	BLEED VALVE     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED BLEED VALVE APPEARED TO BE CLOSING LATE.  SNAG CONFIRMED WHEN PLOTTED IN THE 1D1 MAINTENANCE MANUAL	.  BLEED VALVE REPLACED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004101800082	20041018	00082	EU  	2004	10	18	CA040727014      	1	20040715	G	6220	LB412311	SPHERICAL STOP  			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ELASTIMERIC	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEPARATION OF ELASTAMERIC NOTICED VISUALLY DURING (S) TYPE INSPECTION. VERY TOP MOST OB LAMINATION OF THE SHERICAL	 STOP WAS NOTED TO EXCEED PUBLISHED LIMITS.  NO MENTION OF INFLIGHT VIBRATIONS. THE PART WAS REPLACED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2004101800083	20041018	00083	EA  	2004	10	18	CA040728001      	1	20040719	G	2432	601R593251	CHARGER         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					MAIN BATTERY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN BATTERY CHARGER FAILED, NO FAULT CODES, REPAIRED UNIT, INSTALLED F/T OK.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101800084	20041018	00084		2004	10	18	CA040728002      	4	20040727	G	2300	6229852124	CONTROL UNIT    			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					RADIO TUNING	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DISPLAY BLANK.  REPAIRED UNIT, INSTALLED F/T, OK (RADIO TUNING UNIT).						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101800104	20041018	00104	CE  	2004	10	18	CA040728003      	1	20040726	G	2910		B-NUT           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	HYDRAULIC LINE	SEPARATED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) PILOT WAS UNABLE TO HAVE GEAR DOWN INDICATION WITH BOTH ELECTRIC AND MANUAL EXTENSION.  WHEEL RETRACTED BACK INSID	E WHEEL WELL ON LANDING.  INSPECTION FOUND HYDRAULIC LINE INSIDE THE AIRFRAME BELLY TO RT FLOAT HAD BROKEN OFF FROM THE 	B-NUT.  IT APPEARED THE FLARE IS WORN TO PAPER THIN CAUSING THE FLARE TO FAIL WHILE PRESSURIZED.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA
2005031000073	20050310	00073	EU  	2005	3	10	CA040728004      	1	20040528	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					CYCLIC STICK	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											PILOT REPORTED THAT THE CYCLIC WAS STIFF IN LT QUADRANT.  REPLACED THE LEFT HAND SERVO FIRST.  THIS DID NOT SOLVE PROBLE	M.  REINSTALLED LEFT SERVO AND REPLACED RIGHT HAND SERVO.  THE DEFECT WAS CORRECTED.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005031000074	20050310	00074	SW  	2005	3	10	CA040728005      	1	20040506	G	2911	212076007003	ACCUMULATOR     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											0.5 L OF HYDRAULIC FLUID LOST FROM NR 2 SYSTEM IN 1 HOUR OF FLIGHT.  LEAK ISOLATED TO NR 2 ACCUMULATOR.  ACCUMULATOR REP	LACED AND A/C RETURNED TO SERVICE.					1	G	7	1 	4U	4	U		H4SW    	E22EA
2005031000075	20050310	00075	WP  	2005	3	10	CA040728006      	1	20040726	G	3246	34479	BEARING RACE    			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					MLG WHEEL	CORRODED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											DURING LANDING, THE FLIGHT CREW NOTICED A MAIN WHEEL SHIMMY.  UPON INVESTIGATION BY MAINTENANCE, NR 2 MAIN WHEEL MADE RU	MBLING SOUNDS AND AXLE VIBRATED WHEN SPUN BY HAND.  UPON INSPECTION OF THE BEARING, GREASE WAS FOUND TO BE BLACK IN COLO	R.  INNER BEARING RACE WAS FOUND TO BE CORRODED ON THE BEARING SEAT AREA AROUND THE FULL CIRCUMFERENCE.  THE MAIN WHEEL 	WAS REPLACED WITH A SERVICEABLE UNIT.  THE REMAINING AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO OTHER DEFECTS NOTED.			2	L	7	2 	4R	4	T		6A6     	E282
2005031000076	20050310	00076	NE  	2005	3	10	CA040728007      	2	20040422	G	7230		IMPELLER        	TMECA       		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COMPRESSOR	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M824					AFTER REMOVAL OF THE ENGINE COWLING TO DO A 100 HOUR INSPECTION, IT WAS DISCOVERED THAT THE AXIAL COMPRESSOR HAD SUFFERE	D SEVERE FOREIGN OBJECT DAMAGE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005031000077	20050310	00077	WP  	2005	3	10	CA040728008      	1	20040724	G	2420	9068D093	RELAY           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					GENERATOR	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											DURING CRUISE, THE RT GENERATOR DID NOT POWER THE BUSS.  APU STARTED BUT HAD TO SHUT DOWN DUE TO HIGH OIL TEMP.  AIRCRAF	T HAD TO DIVERTED TO XXX.  MAINTENANCE FOUND THE RT GEN POWER RELAY IN FAULT.  RELAY REPLACED AND GENERATOR POWER CHECKE	D SERVICEABLE. THE APU OIL LEVEL FOUND HIGH AND OIL RESERVICED AS PER MM.  AIRCRAFT DISPATCHED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005031000078	20050310	00078	NE  	2005	3	10	CA040728009      	2	20040723	G	7421	70BM031090	MODULE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								416			MODULE 3 SUFFERED IMPACT DAMAGE ON 1ST STAGE BLADES.  THE IGNITER HAD DISINTEGRATED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005031000079	20050310	00079	EA  	2005	3	10	CA040728010      	1	20040727	G	2913	MS2877810	O-RING          			CNDAIR	CL215 	CL2151A10   	1900320	EA  						HAMSTD	43E	43E60       	NE  	HYD PUMP	BLOWN           	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											THE AIRCRAFT WAS ON APPROACH TO THE AIRPORT.  THERE WAS A LOSS OF HYDRAULIC PRESSURE.  THE AIRCRAFT LANDED WITHOUT INCID	ENT.  UPON INVESTIGATION BY MAINTENANCE STAFF THE RT ENGINE DRIVEN HYDRAULIC PUMP O-RING AT THE PRESSURE LINE FITTING HA	D BLOWN ALLOWING THE HYDRAULIC FLUID TO LEAK OUT UNDER PRESSURE.  THE FAILED O-RING WAS REPLACED WITH A SERVICEABLE O-RI	NG AND THE HYDRAULIC SYSTEM WAS REPLENISHED.  THE RT HYDRAULIC PUMP CHECKED SERVICEABLE.  THE LT PUMP WAS REPLACED AND T	HE AIRCRAFT WAS RETURNED TO SERVICE.		2	H	7	2 	4R			RT	A14EA   		6	C	P871
2005031000080	20050310	00080		2005	3	10	CA040729001      	4	20040726	G	6122	7897501	GOVERNOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											IN CLIMB-OUT, WHILE SETTING PROP LVRS FROM 1200 TO 900 RPM, TQ INCREASED TO 105 PERCENT.  DETERMINED THAT THE NR 1 ENGIN	E WAS THE SOURCE OF THE PROBLEM.  MX REPLACED THE NR 1 PROP CONTROL UNIT, ENG ECU HARNESS, AND TQ SIGNAL CONDITION UNIT.	  GROUND RUNS WERE COMPLETED WITH NO FAULTS AND THE A/C WAS RETURNED TO SERV.  TEARDOWN REPORTS HAVE BEEN REQUESTED FOR 	THE REPLACED COMPONENTS AND AN UPDATE WILL BE PROVIDED WHEN AVAILABLE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031000081	20050310	00081	EA  	2005	3	10	CA040729002      	1	20040727	G	2420		GENERATOR       			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					AC SYS	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				L			NO TEST                   			CR	CRUISE         	1			CA											DURING A ROUTINE POST MAJOR MAINTENANCE FLIGHT CHECK OF THE AIR DRIVEN TURBINE GENERATOR SYSTEM, THE SYSTEM FAILED TO TA	KE THE ELECTRICAL LOAD, AS INDICATED BY THE AMMETER AND THE VOLTMETER, WHEN THE TURBINE WAS MANUALLY DEPLOYED.  MAINTENA	NCE FINDINGS:- ADG OUTPUT WIRING AT CONNECTOR P1XC WAS FOUND TO BE ENTIRELY BURNT OFF AND ALSO THE BACKSHELL PRONG FOR P	ROVIDING STRAIN RELIEF FOR THE WIRING WAS PARTIALLY DESTROYED BY ARCING. THE WIRING WAS BURNT OFF FLUSH WITH THE CONNECT	OR PINS. CONTINUITY CHECKS WERE CARRIED OUT BETWEEN THE PINS AND NO		2	L	7	2 	4F	4	F	RT	A21AE   	E15NE
2005031000082	20050310	00082	GL  	2005	3	10	CA040729003      	2	20040528	G	7230		STATOR          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			11399					CAE802180A			AIRCRAFT HAD ENGINE DECEL IN FLIGHT AND AUTOROTATION.  INITIAL FIELD INSPECTION FOUND DAMAGE AS FOLLOWS: - ENGINE COMPRE	SSOR FOD FOUND COULD BE SEEN ON 2ND, 3RD AND 4TH STAGES- KAFLEX DRIVE SHAFT CONTACTED ISOLATION MOUNT-TXMN DRAG PIN CONT	ACTED STRIKER PLATE, 2 OF 8 RIVETS FOUND SHEARED - LT CHIN BUBBLE CRACKED.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2005031000083	20050310	00083	NM  	2005	3	10	CA040730001      	1	20040729	G	5260	85217051101	GOOSENECK ASSY  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					AIRSTAIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FORWARD AIRSTAIR DOOR GOOSENECK FOUND CRACKED.  THIS IS THE FIFTH OCCURRENCE OF THE GOOSENECK CRACKING.  IT WAS ALSO FOU	ND 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.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005031000084	20050310	00084	EU  	2005	3	10	CA040730002      	1	20040725	G	2160	959902013	CONTROL VALVE   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TEMP	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											DURING CRUISE, THE AIR TEMP SELECTOR WHILE IN AUTO MODE WAS MOVED TO A MORE COOL POSITION, WITH NO EFFECT.  ECS SWITCH W	AS MOVED TO MANUAL MODE AND MORE COOL WAS TOGGLE WITH THE MANUAL SWITCH.  AIR TEMP STILL NOT GETTING COOLER.  MINUTES LA	TER THE ECS CAUTION AMBER ADVISORY LIGHT LIT AND FLIGHT WAS RESUMED TO HOME BASE AS PER FLIGHT MANUAL.  THIS PROCEDURE W	AS TRIED A FEW TIMES WHILE EN ROUTE WITH THE SAME RESULT.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005031000085	20050310	00085	SO  	2005	3	10	CA040730003      	2	20040123	G	8530	631619	EXHAUST VALVE   			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	ENGINE	DEFORMED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											ON 200 HOUR INSPECTION, BOTH LEFT SIDE EXHAUST VALVES FOUND TO BE DEFORMED AT TOP OF STEM BELOW VALVE SEAT CYLINDERS 2 A	ND 4, JAN 12/04.  ENGINE TIME AT INSPECTION 1506.5. ENGINE OVERHAULED SEPT. 20/90 BY VOWELL AVIATION. TTSB 4724,5. EXHAU	ST VALVES REPLACED.  CYLINDERS AND ONGOING INSPECTED BEFORE INSTALLATION IN AIRCRAFT MAY 19/00.  ENGINE GIVEN COMPLETE O	VERHAUL AS PER ENGINE MANUFACTURER OVERHAUL MANUAL DUE TO CRACKED CRANKCASE.  CRANKCASE REPLACED WITH SERVICEABLE ONE OB	TAINED FROM VALLEY AERO ENGINES LANGLEY.  ENGINE RETURNED TO SERVICE ZERO TIME SINCE OVERHAUL.		1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2005020100112	20050201	00112	CE  	2005	2	1	CA040730004      	1	20040727	G	3242	1338931	STATOR          	BFGOODRICH  		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						2386					(CAN) DURING TAXI PILOT NOTICED MORE THRUST THAN NORMAL WAS NEEDED TO TAXI AND AIRCRAFT WAS DIFFICULT TO TURN TO THE RT.	  MAINTENANCE INSPECTION DISCOVERED CRACKED STATOR WHICH WARPED CAUSING BRAKE TO BIND UP.					1	L	7	2 	4F	4	F		A22CE   	E1NE
2005020100116	20050201	00116	SO  	2005	2	1	CA040730005      	2	20040523	G	8520		CRANKCASE       			CESSNA	337   	337D        	2075717	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								513309C			(CAN) ENGINE OIL LEAK DETECTED ON REAR ENGINE SUCTION INSPECTED FOUND 1.5 INCH LONG CRACK IN CASE BETWEEN NR 3 AND NR 5 	CYLINDER.  NO OTHER REPORTED DAMAGE. ENGINE REMOVED.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
2005020100117	20050201	00117	NE  	2005	2	1	CA040730006      	2	20040717	G	8530	12973	ROCKER          			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	BROKEN          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) IN CLIMB, ABOUT 60-70 FEET ABOVE WATER (OTTER ON FLOATS) A LOUD BANG WAS HEARD, ENGINE LOST POWER. PILOT DESCENDED	 RAPIDLY, AND LANDED SAFELY. GROUND RUN LATER, ENGINE WOULD NOT GO OVER 1400 RPM, AND VERY ROUGH BETWEEN 1200 AND 1400. 	LATER INVESTIGATION SHOWED NR 4 CYLINDER EXHAUST ROCKER ARM BROKEN, NOT ALLOWING EXHAUST VALVE TO OPEN.   ALL EXHAUST FR	OM NR 4 WAS GOING INTO INTAKE VALVE, CAUSING ENGINE TO QUIT OVER 1400 RPM.			1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719
2005020100118	20050201	00118	CE  	2005	2	1	CA040730007      	1	20040727	G	2731		TRIM SYSTEM     			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEV TRIM WHEEL	CONTAMINATED    	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) ELEVATOR TRIM WHEEL WOULD ONLY MOVE .5 INCH.  FOUND DEBRIS CONSISTING OF GRASS, PEANUT SHELLS ETC.   A SQUIRRELS N	EST JAMMING THE CHAIN (CABLE ATTACHED TO CHAIN) ON THE GEAR WHICH ACTIVATES THE WORM GEAR TO MOVE THE ELEVATOR UP AND DO	WN.  BECAUSE OF THE LOCATION UNDER THE CENTER OF THE ELEVATOR, BETWEEN TWO BULKHEADS.  IT WAS DIFFICULT TO REMOVE.  IT W	AS COMPLETELY (ALL) REMOVED, USING MIRRORS, VACUUM CLEANER. ALL PARTS WHERE IN EXCELLENT CONDITION.			1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2005031000086	20050310	00086		2005	3	10	CA040730008      	4	20040621	G	3425	066302710	HSI             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	DME DISPLAY	OVERHEATED      	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			B	N		SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             		CL	CLIMB          	1			CA											(CAN) ON CLIMB, BURN ODOR, SMOKE WHERE DETECTED IN COCKPIT. PILOT ADVISED ATC, DIVERTED TO ALTERNATE AIRPORT WHICH HAD V	FR CONDITIONS AT TIME.  WHILE FLYING INTO HEAVY RAIN, TURBULENT AIR, RT ENG FIRE WARNING LIGHT ILLUMINATED. RT ENG WAS I	MMEDIATELY SHUTDOWN. AC LANDED WITHOUT INCIDENT.  INSP OF RT ENG DID NOT SHOW ANY SIGNS OF FIRE, SMOKE, OR BLEED AIR LEA	K. FIRE DET SYS WAS TESTED USING AC FIRE DETECTOR TEST SWITCH. FIRST TIME, RT NR2 FIRE DET INDICATED U/S. MALF COULD NOT	 BE DUPLICATED.  BURN ODOR AND SMOKE WAS FOUND TO BE COMING FROM DISTANCE MEASURING EQUIPMENT (DME) DISPLAY SECTION OF H	ORIZ SITUATION INDICATOR (HSI) CIRCUIT BOARDS. DME CB WAS PULLED, GROUND RUN CARRIED OUT, AC FERRIED FOR REPAIR.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE
2005031000087	20050310	00087	EU  	2005	3	10	CA040730009      	1	20040727	G	5540	555401203	SKIN            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE UPPER ATTACHMENT HOLE WAS FOUND WORN.  THE HOLE WAS SO LARGE THAT IT COULD NOT BE REPAIRED IAW MFG TECH MEMO E	CE-12-TM-02-327.  IN ORDER TO SEE THE BOLT AND DAMAGE AREA, PANEL 32AT HAD TO BE REMOVED TO SEE THE DEFECT. THIS PANEL I	S NOT NORMALLY CALLED UP FOR REMOVAL ON ANY INSPECTIONS, BUT ONLY TO REMOVE THE RUDDER.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020100143	20050201	00143	EU  	2005	2	1	CA040730010      	1	20040729	G	2710	9408328011	BEARING         	PILATS      		PILATS	PC6T  	PC6BH2      	7090210	EU  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PUSHROD ASSY	LOOSE           	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HR INSPECTION, RT AILERON OUTER PUSHROD WAS FOUND TO HAVE A LOOSE BEARING, ALLOWING ROD END TO FLOAT SI	DEWAYS ON BEARING.  BEARING REMOVED, ROD END INSPECTED FOR DAMAGE, NONE FOUND.  NEW BEARING INSTALLED AND CHECKED SERVIC	ABLE.  PUSH ROD ASSY FOUND TO HAVE 86 HRS TSN.  PUSHROD ASSY SUPPLIED FROM AN APPROVED VENDOR.				1	H	7	1 	3T	4	T		7A15    	E4EA	6	C	P15EA
2005020100181	20050201	00181	EU  	2005	2	1	CA040730011      	1	20040729	G	2710	9408328011	BEARING         	PILATS      		PILATS	PC6T  	PC6BH2      	7090210	EU  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BELLCRANK	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HR INSPECTION - LT IB AILERON CONTROL BELLCRANK WAS FOUND TO HAVE LOOSE FITTING BEARING.  ALLOWING AILE	RON CONTROL ROD TO FLOAT UP AND DOWN, CONTACTING THE BELLCRANK ASSEMBLY.  BEARING REMOVED, BELLCRANK AND CONTROL ROD CHE	CKED FOR DAMAGE, NONE FOUND.  NEW BEARING INSTALLED AND CHECKED SECURE.  BELLCRANK ASSEMBLY FOUND TO HAVE 86 HRS TSN.  B	ELLCRANK ASSEMBLY SUPPLIED FROM APPROVED VENDOR.			1	H	7	1 	3T	4	T		7A15    	E4EA	6	C	P15EA
2005020100182	20050201	00182	NM  	2005	2	1	CA040801001      	1	20040731	G	3411		STATIC WICK     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AILERON	BURNED OUT      	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING DECENT AND THROUGH APPROX 17000 FEET , THE A/C WAS APPARENTLY HIT BY LIGHTNING.  NR ONE DC GENERATOR WAS KN	OCKED OFF-LINE. THE CREW RECYCLED THE SWITCH IAW QRH (QUICK REFERENCE HANDBOOK) AND THE DC GENEARATOR CAME BACK ON LINE.	  FURTHER INVESTIGATION BY MAINTENANCE REVEALED LT AILERON OB STATIC WICK WAS BURNED OUT.  ALL STATIC WICKS ON BOTH AILE	RONS WERE REPLACED. ALSO,  A BURNED RIVET FOUND ON RT IB FLAP AT ABOUT 10 INCHES FWD OF THE TRAILING EDGE WHICH WAS REPL	ACED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100183	20050201	00183	EA  	2005	2	1	CA040802001      	1	20040730	G	5512		SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZ STAB	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) THE FLIGHT CERW REPORTED A POSSIBLE LIGHTINING STRIKE , UPON INSPECTION BY MAINTENANCE IT WAS FOUND THAT THERE WAS	 DAMAGE TO NR 2 DME ANTENNA , NR 2 COMM ANTENNA AND NR 1 AND 2 ATC ANTENNES WHICH WERE REPLACED AND TESTED . ALSO FOUND 	STRUCTURAL DAMAGE ON RT HORIZONTAL STABLILIZER WHICH WAS REPAIRED IAW MFG EO 601R-55-11-129.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020100184	20050201	00184	EU  	2005	2	1	CA040803001      	1	20040723	G	2432		BATTERY         			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	MASTER	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, THE CREW OBSERVED THAT THE STBD CHARGE RATE WAS NOT DECLINING BELOW 10 AMPS.  THE AIRCRAFT RETURN	ED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE STBD BATTERIES AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005020100185	20050201	00185	SO  	2005	2	1	CA040803002      	1	20040727	G	6120	582855	VALVE           			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	PROPELLER	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) ON DESCENT,  NR 4 PROP INDICATED 97 PERCENT PITCH LOCK CHECK WAS CARRIED OUT AND ENGINE SHUTDOWN.  PROPELLER VALVE	 WAS REPLACED,  AIRCRAFT GROUND RUN AND RETURNED TO SERVICE.					2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906
2005020100186	20050201	00186	NE  	2005	2	1	CA040803004      	2	20040713	G	7200		ENGINE          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4532			(CAN) ENGINE START CYCLE INCONSISTANT AFTER OVERHAUL. MANY FUEL SYSTEM COMPONENTS CHANGED WITH NO CONSISTANT RESULTS.						1	G	7	1 	3U	3	U		H9EU    	E19EU
2005020100187	20050201	00187	EU  	2005	2	1	CA040803005      	1	20040719	G	2916	350A25103000	RESERVOIR       			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC RESERVOIR PN 350A25-1030-00 ( PLASTIC TYPE ) WAS FOUND TO CONSTANTLY WEEP FLUID.  IT WAS DETERMINED TO H	AVE A CRACK NEAR THE BOTTOM OUTLET PORT THAT FEEDS THE HYDRAULIC FLUID TO THE PUMP. A NEW METAL RESERVOIR WAS INSTALLED.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005031400075	20050314	00075	EU  	2005	3	14	CA040803006      	1	20040724	G	2432	15700	BATTERY         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MASTER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A/C BATTERY IS WEAK. IT WILL NOT START THE A/C TWICE WITHIN 5 MINUTES. BATTERY HAS ONLY AVERAGED 115 HOURS OF LIFE	 IN THE LAST 6 INSTALL					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005031400100	20050314	00100	NE  	2005	3	14	CA040803007      	2	20040712	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION IT WAS DISCOVERED THE TIP OF THE IGNITER WAS MISSING.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005031400101	20050314	00101	CE  	2005	3	14	CA040803008      	1	20040730	G	7120	44911601	CASTING         	BARRYCTRLS  		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE MOUNT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE WAS FOUND SAGGING.  UPON INVESTIGATION THE UPPER ENGINE MOUNT WAS FOUND BROKEN OFF.  ALL 3 MOUNTS REPLACED 	AND CHECKED OK NOTE THESE MOUNTS WERE INVOLVED IN A SUDDEN STOPPAGE,  243 HOURS PRIOR.					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC
2005031400102	20050314	00102	NE  	2005	3	14	CA040803009      	2	20040729	G	7310	A69351039	VENT LINE       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					RT WING	DISCONNECTED    	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DEFECT WAS RECORDED,  RT FUEL LEAK REPORTED FROM RT NACA FUEL VENT . THIS WAS SECOND OCCURRENCE.  AFTER INSPECTION	, MAINT DISCOVERED THAT FUEL VENT LINE WAS DISCONNECTED (SEPARATED) AND NOT LINED UP, (TO SHORT). PROBLEM WAS RELATED TO	 THE MFG NOT DELIVERING VENT LINES IAW DRAWING SPECIFICATIONS. AFTER MEASURING VENT LINES AND FIT CHECKS OF SEVERAL AC. 	 IT APPEARED THAT BUILDING TOLERANCES WERE IN FACT CAUSING THE VENT LINES TO BE INSTALLED UNDER STRAIN AND IN COMBINATIO	N WITH AC WING DYNAMICS DURING ITS OPERATION, THE VENT LINES MAY DISCONNECT FROM THEIR COUPLINGS, RESULTING IN FUEL LEAK	ING THROUGH VENT LINE FLAME ARRESTER.  A REPAIR TO THE FUEL VENT LINE WAS CARRIED OUT IAW MFG LETTER TS04.52975. FO100.	2	L	7	2 	4F	4	F	RT	        	E25NE
2005041400124	20050414	00124	EA  	2005	4	14	CA040803010      	1	20040723	G	5311		FRAME           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING INSPECTION AS PER AD CF-2003-12, MAINTENANCE FOUND CRACKS IN THE LT AND RT FRAME AND REINFORCING ANGLE AT STATION	 FS 640 BETWEEN STRINGER 9 AND STRINGER 12.  REPAIR WORK IS CURRENTLY IN PROGRESS, AND SDR WILL BE UPDATED UPON COMPLETI	ON OF REPAIR.  AIRCRAFT HOURS WERE 11985 AIRCRAFT CYCLES WERE 9553				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031400103	20050314	00103	WP  	2005	3	14	CA040804001      	1	20040803	G	2610	24346300C	GASKET          			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	LT ENGINE	MISSING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT THE LT ENGINE ZONE 2 FIRE ALARM ACTIVATED.						2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898
2005031400104	20050314	00104	SW  	2005	3	14	CA040804002      	1	20040728	G	6410	206016201131	BLADE           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAIL ROTOR	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRAILING EDGE SKIN WHERE THE BALANCE WEIGHTS ARE ATTACHED, WAS FOUND DISPLACED APPROXIMATELY 0.080 INCH FROM THE C	HORD-LINE.   DISCREPANCY WAS DETECTED WHEN A BONDING FAILURE WAS NOTICED IB FROM THE WEIGHTS ON THE BLADE ROOT CLOSE-OUT	.  THERE WAS NO INDICATION THAT THIS AREA WAS SUBJECT TO IMPACT DAMAGE, WHICH LEADS TO THE POSSIBILITY THAT THE DAMAGE W	AS CAUSED AT THE INSTALLATION OF THE BALANCE WEIGHTS.			1	G	7	1 	3U	3	U		H2SW    	E1GL
2005031400105	20050314	00105	NE  	2005	3	14	CA040804003      	2	20040723	G	8530	R985	CYLINDER HEAD   		R985        	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14BM1 	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	BROKEN          	W				B				EMER. DESCENT           				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			CA											(CAN) NR 5 CYLINDER STUDS BROKE AND CYLINDER THEN DETACHED FROM CASING, RESULTING IN EMERGENCY LANDING AND LOSS OF OIL.						1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
2005031400106	20050314	00106	EU  	2005	3	14	CA040804004      	1	20040721	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					OIL PRESS	ERRATIC         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) ENGINE OIL PRESSURE WAS ERRATIC THEN IT WENT FULLSCALE.  TRANSMITTER REPLACED WITH UNIT FROM FPBA.  NEW ONE ORDERE	D AND INSTALLED IN PBA.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041400125	20050414	00125	GL  	2005	4	14	CA040804005      	2	20040514	G	7250	23074872	CHECK VALVE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TURBINE SECTION	OUT OF RIG      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING 100 HOUR INSPECTION ITEMS DUE TO ENGINE SWAP TO ALTERNATE A/C,  FOUND THAT THE TURBINE CHECK VALVE 230	74872 WAS SEIZED WHEN THE CLAMP MS 122911 WAS TIGHTENED.  VALVE/CLAMP CONFIGUATION IS CORRECT IAW IPC/CEB1349. CHECK VAL	VE WOULD FUNCTION WITH CLAMP LOOSE.   A NEW CLAMP (P/O 360804) WAS TRIED WITH THE SAME RESULT.  THESE CLAMPS ARE FLATTEN	ED IN SHAPE, BY REWORKING CLAMP TO A ROUNDER FORM, THE VALVE WOULD THEN FUNCTION NORMALLY WHEN INSTALLED.  THIS WAS VERI	FIED BY REMOVAL OF THE OIL SUPPLY LINE TO THE VALVE.		1	G	7	1 	3U	3	U		H2SW    	E4CE
2005041400126	20050414	00126	EA  	2005	4	14	CA040804006      	2	20040727	G	7322	30804	FLOAT           	PRECISION   	MA4SPA      	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	CARBURETOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DC0244					(CAN) A FLOAT FOUND IN A PRECISION FACTORY REMAN CARB WAS FOUND TO BE FLOODED WITH FUEL IN ONE OF THE PANTOONS. THIS CAU	SED THE ENGINE TO RUN RICH BECAUSE OF THE FLOAT SINKING. THE FLOAT IS MFG NEW STYLE THAT IS AVAILABLE ON MA CARBURETOR. 	 THIS DEFECTIVE ONE HAS A CODE OF (5346) ON IT.				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2005041400127	20050414	00127	NE  	2005	4	14	CA040804007      	2	20040717	G	7532	9550158260	BLEED VALVE     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BLEED VALVE NOT CLOSING.   REPLACED BLEED VALVE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005041400128	20050414	00128	EU  	2005	4	14	CA040804008      	1	20040717	G	7714	0177555150	TACH GENERATOR  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TACH BOX INTERNAL MALFUNCTION.  REPLACED TACH BOX.  CAUSE PROBLEM: DUE TO BLEED VALVE UNSERVICEABLE SHORTED THE TACH BOX	.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005041500001	20050415	00001	NE  	2005	4	15	CA040804009      	2	20040625	G	7532	4020T35G04	REGULATOR       			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30015	NE  					BLEED AIR SYSTEM	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								807136			APPROX 1 - 2 MINUTES AFTER ENGINE START, CREW NOTED SMOKE IN THE CABIN. ENGINES AND APU WERE SHUTDOWN AND A/C EVACUATED.	  SMOKE WAS TRACED TO THE BLEED AIR OF THE RT ENGINE.  MX FOUND A DEFECTIVE CARBON SEAL PRESSURE REGULATING VALVE. THE V	ALVE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005041500002	20050415	00002	CE  	2005	4	15	CA040804010      	1	20040715	G	5344	071103720	HINGE           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DOOR HINGE WAS NOTED AS CRACKED.  UPON REMOVAL OF DOOR TO REPLACE HINGE, CRACKS WERE ALSO FOUND IN THE MATING PART OF TH	E HINGE (0711037-11) AND IN THE UPPER AFT HINGE (0711037-16).  THE DOOR RIGGING IS SUCH THAT THE EDGES OF THE DOOR AND A	IR FRAME SKINS COME INTO CONTACT WHEN CLOSING, AND PLACE UNDUE FORCES ON THE HINGES.				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA
2005041500003	20050415	00003	EA  	2005	4	15	CA040804011      	2	20040803	G	7321	25244394	FUEL CONTROL    			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA								21928			(CAN) WHEN THE FLIGHT CREW REDUCED POWER ON FINAL APPROACH, NR 1 ENGINE FAILED TO RESPOND TO POWER LEVEL INPUT, AND REMA	INED AT 15 LBS TORQUE. THE TORQUE THEN SLOWLY DROPPED TO IDLE WITHOUT ANY  POWER LEVER INPUT AND A LANDING WAS COMPLETED	 WITHOUTFURTHER INCIDENT. INVESTIGATION REVEALED THAT THE F.C.U. HAD FAILED INTERNALLY.				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA
2005041500004	20050415	00004		2005	4	15	CA040804012      	4	20040804	G	2562	BS2173	BATTERY PACK    																	ELT	LEAKING         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) IN THIS LAST WEEK WE HAVE FOUND TWO REPLACEMENT BATTERY PACKS FOR THE DORNE& MARGOLIN DM ELT6, DM ELT 6.1, AND DM 	ELT8 SERIES OF ELTS, LEAKING CAUSING INTERNAL CASE CORROSION. IN ONE CASE ONE OF THE POWER WIRES COMING OUT OF THE BATTE	RY HAD CORRODED OFF THE BATTERY PACK.  ONE BATTERYHAS A MANUFACTURING DATE OF MAY 2003, (EXPIRY DATE OF JUN 2005) AND SE	COND ONE, HAS A MANUFACTURING DATE OF JUNE2003(EXPIRY DATE JUL 2005).
2005041500005	20050415	00005	NE  	2005	4	15	CA040805001      	2	20040721	G	7220	UL16113	FAIRING         			BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA			52914					30534			(CAN) ENGINE EXPERIENCED A SPINNER FAIRING FAILURE ON THE T/O ROLL. PILOT ADVISED BY TOWER OF SPARKS AND FLAMES FROM JET	 PIPE AS REPORTED BY ANOTHER A/C & THE TAKE OFF WAS ABORTED. SPINNER FAIRING IS OF THE OLD FABRICATED SHORT FAIRING STAN	DARD & FAIRING UNZIPPED ABOUT 40 PERCENT AROUND STITCH WELD DUE TO A CRACK WHICH PROPAGATED REARWARDS FROM ONE OF THE BO	LT H OLES. CRACKING OF THE SPINNER FAIRING IS A KNOWN PROBLEM WHICH WAS MANAGED BY ROUTINE INSPECTIONS FOR CRACKING. NMS	B 72-C322 CALL FOR REPETITIVE INSPECTION OF THE NOSE CONE FAIRING FOR CRACK. THE ENGINE HAS SUFFERED EXTENSIVE FAN BLADE	 AND ATTRITION LINER DAMAGE. THE FAILURE WAS FULLY CONTAINED AND THE UNZIPPED MATERIAL SEEMS TO HAVE GONE DOWN THE BY-PA	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2004101300019	20041013	00019	CE  	2004	10	13	CA040805002      	1	20040804	G	8011	539785	GEAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	STARTER ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT COMPLETED ITS FIRST FLIGHT OF THE DAY WITHOUT INCIDENT. ON THE SECOND START OF THE DAY THE PILOT HEAR	D THE STARTER MOTOR RUNNING BUT THE ENGINE WAS NOT ROTATING.  INSPECTION AND TROUBLESHOOTING PROCEDURES WERE CARRIED OUT	. THE  MECHANIC FOUND THE STARTER ADAPTER GEAR P/N 539785 BROKEN AND SOME DAMAGE INSIDE THE ADAPTER HOUSING. THE ENGINE 	OIL FILTER WAS REMOVED AND INSPECTED WITH NO INDICATION OF METAL CONTAMINATION. THE ENGINE OIL WAS CHANGED AND A NEW FIL	TER INSTALLED AS A PRECAUTIONARY MEASURE.		1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL
2004101300030	20041013	00030	NM  	2004	10	13	CA040805003      	1	20040715	G	3246		WHEEL           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN OPERATOR HAS EXPERIENCED CRACKING OF THE 32-INCH MAIN LANDING GEAR WHEEL ASSEMBLY  P/N 3-1575. THE CRACKS START	  AT THE WHEEL BOLT HOLES (FAYING SURFACE) AND EXTEND TO THE CUT-OUTS.  THE CAUSE OF THE CRACKING IS NOT KNOWN AND IS CU	RRENTLY UNDER INVESTIGATION BY MANUFACTURERS.  AOM NR 133 HAS BEEN ISSUED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004101300031	20041013	00031	EU  	2004	10	13	CA040805004      	1	20040730	G	2421	23085024	GENERATOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AC SYSTEM	DAMAGED         	W				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) GENERATOR WAS OVERHAULED AND INSTALLED ON THE AIRPLANE ON JULY 13TH 2004. ON JULY 30TH, (85.2) FLIGHT HOURS LATER 	THE STARTER DID NOT TURN DURING A ATTEMPTED ENGINE START AND AFTER TROUBLESHOOTING IT WAS DISCOVERED THAT THE STARTER HA	D FAILED. THIS IS THE 2ND FAILURE IN LESS THEN A MONTH THAT WE HAVE HAD ON THIS TYPE OF GENERATOR OVERHAULED BY THIS FAC	ILITY.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004101300032	20041013	00032	NE  	2004	10	13	CA040805005      	2	20040804	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  						ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AUGUST 04, AIRCRAFT, EN ROUTE, DIVERTED TO NEAREST ALTERNATE AIRPORT.  WHEN THE CABIN CREW REPORTED A BURNING SMEL	L (PLASTIC) IN THE AFT RT CABIN NEAR THE LAVATORY.   MAINTENANCE PERSONNEL OPENED THE AISLE CEILING, REMOVED THE TOILET 	SHROUD (BOLSTER), OPENED THE LAVATORY CEILING AND THEN CARRIED OUT A HIGH POWER RUN WITH PACKS ON, IN ORDER TO DUPLICATE	 THE SMELL, NO BURNING SMELL WAS DETECTED.  AS A PRECAUTIONARY MEASURE A TECHNICIAN BOARDED THE AIRCRAFT FOR THE REMAIND	ER OF THE FLIGHT.   NO FINDINGS WERE REPORTED.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101300033	20041013	00033	EU  	2004	10	13	CA040805006      	1	20040510	G	6730		ACCUMULATOR     		AC67246     	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ROTOR SERVO	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA						PC438					(CAN) CYCLIC OSCILLATION WHEN ACCUMULATORS BLED DOWN.						1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300034	20041013	00034	NE  	2004	10	13	CA040805007      	2	20040409	G	7313	0283317500	INJECTOR        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA											(CAN) POOR STARTS REPORTED.  SPRAY PATTERN ON START INJECTORS FOUND POOR. NEW INJECTORS INSTALLED AND SHIMMED.						1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300035	20041013	00035	EU  	2004	10	13	CA040805008      	1	20040317	G	6420	350A3321501	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING A 100 HOUR INSPECTION THE TAIL ROTOR SPIDER WAS DISCONNECTED FROM THE INPUT BELLCRANK TO CHECK TH	E SPIDER SWASHPLATE BEARING.  NOTICED THAT THE BALL END BEARING ON THE SWASHPLATE INPUT WAS WORN OUT. ( IPC 65.20.30 FIG	 1A ITEM 95 ) MEASUREMENT WITH A DIAL INDICATOR SHOWED AN AXIAL PLAY OF APPROXIMATELY 1.4MM.				1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300036	20041013	00036	NE  	2004	10	13	CA040805009      	2	20040308	G	7322		LINE            			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL CONTROL	SPLIT           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						C658B					(CAN) OVERHAULED FUEL CONTROL RECEIVED FROM MFG ON PS CC/F01782. FOUND TO  BE LEAKING AT HOUSING SPLIT LINE HALVES DURIN	G GROUND RUN/ LEAK CHECK.  PART REMOVED AND RENTAL UNIT REINSTALLED.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300037	20041013	00037	CE  	2004	10	13	CA040805010      	1	20040831	G	2612		WARNING LIGHT   			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT ENGINE	ILLUMINATED     	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) ON START-UP, THE LT FIRE WARNING LIGHT ILLUMINATED BEFORE FUEL WAS INTRODUCED TO THE ENGINE.  PILOT ABORTED START.	  MAINTENANCE CHECKED ALL APPLICABLE SYSTEMS AND FOUND NO FAULTS.  NO EVIDENCE OF FIRE WAS FOUND. MULTIPLE STARTS WERE C	ARRIED OUT AND NO FAULTS FOUND.  A/C WAS RETURNED TO SERVICE.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
2004101300038	20041013	00038	EU  	2004	10	13	CA040805011      	1	20040801	G	2150		CASTING         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  						CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON WEB CASTING DURING A 100 HOUR INSPECTION. (BUTTERFLY) PLATE VERY LOOSE (WORN OUT END BUSHINGS).						1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300096	20041013	00096	WP  	2004	10	13	CA040805012      	1	20040804	G	2750		CONTROL UNIT    			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					TE FLAPS	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) FLAPS WERE SELECTED AT 24, FOR TAKE OFF ON RUNWAY 24 (6150 FT). WHEN FLAPS WERE INITIALLY SELECTED, THE SLATS EXTE	NDED TO LAND. THE FLAPS WERE CYCLED AND 24/24 TAKE OFF WAS DISPLAYED.  WHEN THROTTLES WERE ADVANCED FOR T/O, THE SLATS E	XTENDED TO LAND AND THE CHIME WAS HEARD. THE T/O WAS ABORTED AT LESS THEN 60 KNOTS. THE FLAPS WERE CYCLED AGAIN AND THE 	THROTTLES WERE ADVANCED SLIGHTLY TO ENSURE THE SLATS REMAINED AT TAKE OFF. THROUGH 90 KNOTS THE SLATS EXTENDED AND THE T	AKE OFF WAS REJECTED. MAINTENANCE ADJUSTED THE FLAP SWITCH (S1-467) IAW THE AMM AND CHECKED SERVICEABLE. ALSO AN AUTOPIL	OT CHECK CARRIED OUT IAW AMM 22-10-00.  AIRCRAFT WAS RELEASED WITH NO FURTHER FAULTS.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101300097	20041013	00097	EU  	2004	10	13	CA040805013      	1	20040727	G	8012	350A67511001	RELAY           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER	FAULTY          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN START BUTTON PRESSED THE STARTER RELAY WOULD ONLY CHATTER. TROUBLESHOOTING DETERMINED A FAULTY RELAY 23K.  PR	INTED CIRCUIT BOARD REPLACED.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300098	20041013	00098	EU  	2004	10	13	CA040805014      	1	20040628	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					OIL PRESSURE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) NO OIL PRESSURE INDICATION ON DASH GAUGE (ENGINE PRESSURE WARNING LIGHT GOES OUT).						1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300099	20041013	00099	NE  	2004	10	13	CA040805015      	3	20040726	G	6114	660710840	HUB             			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	RT PROPELLER	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA									DRG869386		(CAN) ON LANDING, PILOTS FELT A LIGHT VIBRATION ON THE RT PROPELLER WHEN FEATHERING.  AFTER INVESTIGATION FOUND PROPELLE	R HUB MATING FACE AND PGB FLANGE WITH A LIGHT PLAY. 6 ATTACH BOLTS OUT OF 12 WERE FOUND TO BE 1 TURN LOOSE ALTHOUGH THE 	SAFETY WIRE WAS STILL INTACT.  SOME BOLTS WERE JAMMED AND COULD NOT BE REMOVED.  PROPELLER REMOVED AND FOUND STRETCHED T	HREADS IN HOLES AND ALSO 3 CRACKS FOUND BY NDT AROUND DOWEL PIN HOLE.   WE ARE ASSUMING THAT THE HUB BOLT HOLES STRETCHE	D, THERE ARE SOME SB'S REGARDING THIS ISSUE THAT WERE ALREADY ACCOMPLISHED. NOTE THAT THIS HUB WAS NEW AND INSTALLED AT 	LAST OVERHAUL.	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE
2004101300100	20041013	00100	CE  	2004	10	13	CA040805016      	1	20040804	G	2612	3001129	SENSOR          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	FIRE DETECTOR	FAULTY          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA								PCE94792			(CAN) UPON REGULAR PHASE INSPECTION, THE FIRE DETECTION SYSTEM FAILED TO TEST CORRECTLY ON RT ENGINE.  TROUBLESHOT AND F	OUND SENSOR AT FAULT.  REPLACED SENSOR, OPERATION RESTORED TO NORMAL.					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE
2004101300101	20041013	00101	CE  	2004	10	13	CA040805017      	1	20040805	G	5320	97430000150	CROSS TIE       			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FUSLEAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVING THE LT EMERGENCY EXIT FOR UNRELATED ROUTINE MAINTENANCE, PERSONNEL DISCOVERED A CRACK IN THE LT FUSE	LAGE CROSSTIE AT STATION 201.775.  THE CRACK LOCATION IS NEAR THE LOWER AFT CORNER OF THE LT EMERGENCY EXIT HATCH.  CRAC	K IS APPROX .375 INCH IN LENGTH AND TRAVELS FROM THE MATERIAL EDGE TO THE NEAREST RIVET HOLE AND SLIGHTLY PAST.  CROSSTI	E TO BE REPLACED.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2004101300102	20041013	00102	CE  	2004	10	13	CA040805018      	1	20040826	G	2722	991444014	PCU             			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					RUDDER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, A SMALL LEAK WAS NOTICED COMING FROM THE RUDDER.						2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH
2004101300103	20041013	00103	WP  	2004	10	13	CA040806001      	1	20040803	G	7921	315341	ACTUATOR        			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	OIL COOLER DOOR	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE FLIGHT CREW NOTICED THAT THE OIL TEMPERATURE ON THE LT ENGINE WAS CLIMBING.  THE CREW TRIED TO M	ANUALLY CONTROL THE OIL TEMP BUT WAS UNSUCCESSFUL.  THE ENGINE WAS SHUT DOWN AND THE PROP WAS FEATHERED AS A PRECAUTION.	  THE AIRCRAFT RETURNED TO BASE.  OIL COOLER DOOR ACTUATOR WAS REPLACED WITH A SERVICEABLE UNIT, AND THE AIRCRAFT WAS RE	TURNED TO SERVICE.			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898
2005041500006	20050415	00006	EU  	2005	4	15	CA040806002      	1	20040703	G	6730	F1688	SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FLIGHT CONTROL	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			HO	HOVERING       	1			CA											DURING HYD TESTS PRIOR TO FLTS IAW CF-2003-15R1, CYCLIC CONTROL FOUND COMPROMISED. AT 100 PERCENT NR, 'HYD TEST' SELECTE	D, CYCLIC TESTED FOR PROPER CNTRL MOVEMENTS ON ACCUMULATOR PRESS PRIOR TO HYD ASSIST DEPLETION.  LATERAL ACCUMULATORS DE	PLETED AFTER APPROX 8 CYCLES, CYCLIC ENCOUNTERED A VIOLENT UNCOMMANDED RT MOVEMENT.  SUBSTANTIAL FORCE REQUIRED TO KEEP 	CYCLIC IN PLACE & GREATER FORCE REQUIRED TO CENTER CONTROL.  AFTER FORCING CONTROL THRU CENTER POSITION, INTO LT AREA & 	RE-CENTERING CONTROL, PHENOMENON DISAPPEARED. DURING RE-CHARGING OF ACCUMULATORS, CYCLIC VIOLENTLY MOVED LT UNTIL HYD AS	SIST SUPPLIED. RT INPUT PHENOMENON WOULD ONLY SHOW UP WHEN 'HYD TEST' USED. COLLECTIVE DUMP YIELDED NO DISCREPANCIES.	1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101800047	20041018	00047	CE  	2004	10	18	CA040806003      	1	20040805	G	5610	1013840212	WINDSHIELD      			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT CRUISE ALTITUDE THE LT WINDSHIELD SHATTERED. FLIGHT CREW DESCENT TO 16000 FEET ALTITUDE AND LANDED AT SAFELY.  	 WINDSHIELD ASSY WILL BE REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004101800048	20041018	00048	EA  	2004	10	18	CA040806004      	2	20040722	G	8520	SL78027	BOLT            		SL78027     	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	CONECTING ROD	FAILED          	W				A				UNSCHED LANDING         				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) THE PILOT DEPARTED AIRPORT: AT 2100 FT AND 4 MILES SOUTH OF DEPARTED AIRPORT, ENGINE STARTED TO RUN ROUGH, PARTIAL	 POWER LOSS. THE PILOT LANDED AT SAME AIRPORT WITHOUT ANY DIFFICULTY. UPON INVESTIGATION OF ENGINE, FOUND THAT THE CONNE	CTING ROD BOLTS P/N SL78027 FAILED AND SEPARATION OF CONNECTING ROD CUP.  ENGINE SENT FOR FURTHER INVESTIGATION.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004101800049	20041018	00049	EU  	2004	10	18	CA040806005      	1	20040517	G	6220		BUSHING         			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	25OC  	250C20R     	 	GL  					STARFLEX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M495U					(CAN) ALL 3 BUSHINGS FOUND LOOSE ON D.I. STARFLEX WAS REPLACED.						1	G	7	2 	3U	3	U		H11EU   	E4CE
2004122900166	20041229	00166	SO  	2004	12	29	CA040806006      	2	20040726	G	8520		SADDLE          			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	CRANKCASE	FAILED          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											CRANKCASE FAILURE (7TH STUD CRANKCASE) CRANKCASE FRETTING ON NR 2 & 3 INTERMEDIATE BEARING SADDLE THRU-BOLT PADS. THE OI	L SUPPLY TO THE NR 2 CONNECTING ROD JOURNAL WAS EITHER CUT OFF COMPLETELY OR DRASTICALLY REDUCED CAUSING OIL STARVATION 	TO THE CONNECTING ROD BEARINGS. THIS IN TURN CREATED EXCESSIVE FRICTION AND HEAT CAUSING THE CONNECTING ROD TO FAIL AND 	EXIT THROUGH THE CRANKCASE RESULTING IN A CATASTROPHIC FAILURE OF THE ENGINE.			1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA
2004101800050	20041018	00050	SW  	2004	10	18	CA040806007      	1	20040417	G	7120	206063110001	FITTING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					GEARBOX MOUNT	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A VISUAL INSPECTION, ENGINE GB MOUNT FITTING 206-063-110-003 (RT) AND FITTING 206-063-110-001 (BOTTOM) WERE 	FOUND INTERMIXED.  BOTTOM FITTING IS 0.4 INCH LONGER THAN THE SIDE ONES.  REINSTALLED THE FITTINGS PROPERLY AFTER  INSPE	CTION OF THE A/F ENGINE MOUNT ATTACHMENT POINTS (VISUAL WITH BOROSCOPE).  NO CRACK OR DAMAGE FOUND.   ALSO INSPECTED THE	 SHORT STEEL SHAFT TOMMAS COUPLINGS.  NO DAMAGE FOUND.  A/C RETURNED TO SERVICE, MAINTENANCE LOG ENTRY.			1	G	7	1 	3U	3	U		H2SW    	E4CE
2004101800085	20041018	00085	SO  	2004	10	18	CA040806009      	1	20040810	G	3230	4032705	HOUSING         			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	DRAG BRACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15000								(CAN) DURING A WALKAROUND, THE PILOT NOTICED THE LT OLEO WAS LOWER THAN THE RT. AT THE MAINTENANCE BASE THE AME INSPECTE	D THE LT OLEO WHICH WAS COMPLETELY FLATNOW.  UPON FURTHER INSPECTION BY THE AME, FOUND HYDRAULIC FLUID IN THE WHEEL WELL	 AND DOWN THE GEAR LEG.  IT WAS ALSO FOUND A 6 INCH VERTICAL CRACK ALONG SIDE THE DRAG BRACE ATTACHMENT POINT.  THE AME 	CLEANED THE PAINT OFF TO MAKE SURE IT WAS A CRACK IN THE HOUSING AND NOT IN THE PAINT. NITROGEN WAS ADDED BUT LEAKED OUT	 THROUGH THE CRACK.  A SERVICEABLE HOUSING WAS INSTALLED AND THE AIRCRAFT WAS PUT BACK IN SERVICE.		1	L	7	2 	3T	4	T	RT	A8EA    	E4EA	6	C	P15EA
2004102000189	20041020	00189	EU  	2004	10	20	CA040806010      	1	20040805	G	5340	350A35101700	SUPPORT         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC PUMP SUPPORT HOUSING HAD A CRACK ON FLANGE, CAUSING PUMP AND BEARING ASSEMBLY TO VIBRATE.  HYDRAULIC BEA	RING (704A33-651-206) FOR THE POLY (V) BELT WAS REPLACED AT THIS TIME TO ENSURE THAT NO DAMAGE MAY HAVE BEEN CAUSED TO T	HIS BEARING DUE TO VIBRATION.   AIRCRAFT RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101800086	20041018	00086	CE  	2004	10	18	CA040809001      	1	20040803	G	2820		LINE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) APPROXIMATELY 1-5 INCH CRACK ALONG FLANGE.  FUEL STAINING NOTED IN AREA.  ROUGH RUNNING ENGINE.   PIPE ASSEMBLY RE	PLACED.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2004101800087	20041018	00087	WP  	2004	10	18	CA040809002      	1	20040802	G	7430	A1661	IGNITION SWITCH 			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					INSTRUMENT PANEL	OVERHEATED      	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, AN ENGINEER ONBOARD SMELLED ODOR OF BURNING ELECTRICAL WIRES. THE AIRCRAFT LANDED WITHOUT FURTHER	 INCIDENT. FURTHER INVESTIGATION FOUND IGNITION SWITCH WAS THE CULPRIT. THE CONTACTS OVERHEATED CAUSING THE PLASTIC TO S	LIGHTLY BURN. ONE MAG CONTACT WAS FOUND GROUNDED DURING FUNCTION TEST OF SWITCH. THE SWITCH WAS REPLACED AND NO FURTHER 	DEFECTS WERE NOTICED, FLIGHT CONTINUED. THE COMPANY HAS NOTIFIED MFG AND INCORPORATED AN INSPECTION ON THE IGNITION SWIT	CHES.  IGNITION SWITCH P/N A166-1, ALT P/N 10-357200-1.		1	G	7	1 	3O	3	O		H11NM   	E295
2004102000190	20041020	00190	WP  	2004	10	20	CA040809003      	1	20040802	G	2510	C6284	BUCKLE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					PILOT SEAT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING A 100 HOUR INSPECTION, ENGINEER FOUND CRACKS PROPAGATED FROM TWO RIVETS UNDER BUCKLE.  PLASTIC COVER WAS MO	VED BACK AND FURTHER CRACKS WERE FOUND ALONG RIVET LINE OF THE STAINLESS ADAPTER TO PIVOT POINT OF THE BELT ASSEMBLY. TW	O OTHER CASES HAVE BEEN FOUND SINCE. THE CAUSE COMES FROM WHEN PILOTS TRY TO INSERT TONGUE IN TO BUCKLE ASSY.  BUCKLE AS	SY IS FLEXED TO ACCOMPLISH THE FASTENING OF THE SEAT BELT.  OVER TIME THE STAINLESS ADAPTER IS STRESSED AND CRACKS OCCUR	.  PARTICULAR CARE HAS BEEN TAKEN REGARDING INSPECTION CRITERIA.   A LETTER HAS BEEN SENT TO MFG, HOPING TO GET SOME INP	UT/CHANGE TO ACCESSIBILITY TO BUCKLE ASSEMBLY.	1	G	7	1 	3O	3	O		H11NM   	E295
2004101800088	20041018	00088	CE  	2004	10	18	CA040809004      	1	20040802	G	2701		SPACER          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CONTROL YOKE BRG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) YOKE FOUND TO HAVE EXCESSIVE MOVEMENT DURING INSPECTION. SOURCE DETERMINED TO BE LACK OF WELDING AT LT SIDE OF LOW	ER BEARING CONTROL YOKE SPACER ASSEMBLY TO THE CONTROL YOKE SHAFT ITSELF.  MFG HAS PROVIDED APPROPRIATE DATA TO COMPLETE	 THE WELDMENTS.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004101800089	20041018	00089	CE  	2004	10	18	CA040809005      	1	20040802	G	3251	C109	ROD END         	CESSNA      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STEERING ARM	WORN            	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) ON GROUND ROLL, THE PILOT WAS UNABLE TO TURN THE AIRCRAFT TO THE RT. AFTER INSPECTION OF THE STEERING SYSTEM, DISC	OVERED A STEERING ARM DISCONNECTED IN LOCATION OF THE PEDALS. THE ROD END THAT ATTACHES TO THE PEDALS WAS WORN, WHICH CA	USED THE STEERING ARM TO DISCONNECT. THE ROD END WAS REPLACED.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004101800090	20041018	00090	CE  	2004	10	18	CA040809006      	1	20040809	G	5210	50430043547	HINGE           			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION OF THE CABIN DOOR HINGE REVEALED CRACKING OF THE DOOR HALF AFT TWO SECTIONS. FUSELAGE HINGE HALF UNDAMA	GED.  DOOR HINGE HALF AND PIN TO BE REPLACED NEW.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2004101800105	20041018	00105	EU  	2004	10	18	CA040809007      	1	20040807	G	6320		PINION GEAR     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TRANSMISSION	VIBRATION       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA						M1571					(CAN) AIRCRAFT HAD 3 PER VIBRATION APPEAR DURING FORWARD FLIGHT. PILOT LANDED AT DESTINATION AND PHONED IN FOR A PRECAUT	IONARY MEASURE. COMPANY DISPATCHED ANOTHER AIRCRAFT AND ENGINEER TO ACCESS THE PROBLEM.  TRANSMISSION WAS CHANGED AND AI	RCRAFT WAS RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005021400200	20050214	00200	NM  	2005	2	14	CA040810001      	1	20040809	G	3230	841005	PSEU            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FALSE INDICATION	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			20510								(CAN) DURING APPROACH , THE NOSE GEAR FAILED TO EXTEND , THE CREW CARRIED OUT ALTERNATE GEAR EXTENSION AND A/C LANDED SA	FELY . DURING THE SAME FLIGHT , AFTER TAKEOFF(ABOUT 5 MINUTES) THE LANDING GEAR CAUTION LIGHT CAME ON AND WENT OUT AFTER	 ONE MINUTE.  MAINTENANCE CREW FOUND ERRONIOUS FAULT CODES ON THE PSEU( PROXIMITY SENSING ELECTRONIC UNIT ) AND REPLACED	 THE UNIT . SEVERAL GEAR RETRACTIONS CARRIED OUT ON JACKS AND THE FAULTS COULD NOT BE DUPLICATED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005021400201	20050214	00201	CE  	2005	2	14	CA040810002      	1	20040804	G	2612	24412886	FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RT ENGINE	BROKEN          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) CREW NOTED THAT THE RT FIRE LOOP WOULD NOT TEST. MAINTENANCE FOUND THE FWD FIRE WIRE LOOP PARTIALLY BROKEN PREVENT	ING CONTINUITY.  THE WIRE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005021400202	20050214	00202	EU  	2005	2	14	CA040810003      	1	20040807	G	2910		O-RING          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ENROUTE, (GREEN SYS) LOW LEVEL PRESS INDICATION OBSERVED. THE CREW ACCOMPLISHED THE CHECK LIST AND CONTINUED TO YZ	F.  THE AIRCRAFT LANDED WITHOUT INCIDENT AND WAS TOWED FROM THE RUNWAY. THE O-RING AND BACK-UP RING AT THE ACCUMULATOR F	ITTING WERE REPLACED, THE AIRCRAFT WAS LEAK CHECKED AND RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE
2005021400209	20050214	00209	EA  	2005	2	14	CA040810004      	2	20040806	G	7310	11492000023	LINE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE FUEL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35350								(CAN) WHEN INSTALLING INSPECTION PANEL ON LT OB NACELLE FOUND FUEL LINE FROM FUEL BOWL FORWARD TO ENGINE WAS CHAFING ON 	BULKHEAD IN SIDE OF NACELLE. THE LINE WAS WORN ABOUT A QUARTER OF ITS WALL THICKNESS.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2005021400214	20050214	00214	CE  	2005	2	14	CA040810005      	1	20040719	G	3252	26430096	SHIMMY DAMPENER 			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) SHIMMY DAMPENER BARREL END ENTIRELY BROKE OFF AT CIRCLIP GROOVE. ALL FLUID LOST,CIRCLIP MISSING, BROKEN PIECE MISS	ING. NO EVIDENCE OF PRIOR OVERSTEER.					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL
2005021400215	20050214	00215	NE  	2005	2	14	CA040810006      	2	20040809	G	7414	SB9RU3	MAGNETO         			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								1784N			(CAN) DURING A LOCAL FLIGHT THE PILOT ENCOUNTERED A ROUGH RUNNING CYCLE,  RETURNED TO BASE AND LANDED EVENTUALLY.  MAINT	ENANCE INVESTIGATION RELEALED THAT THE RT MAGNETO HAD FAILED INTERNALLY.  MAGNETO WAS REPLACED AND THE AIRCRAFT RETURNED	 TO SERVICE. TEARDOWN REPORT TO FOLLOW.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA
2005021400216	20050214	00216	CE  	2005	2	14	CA040810007      	1	20040806	G	3242	1338932	DISK            	BFGOODRICH  		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE STATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2393					(CAN) WHILE PUSHING THE AIRCRAFT WITH A TUG THE LT BRAKE LOCKED UP.  ON INSPECTION IT WAS DISCOVERED THAT ONE OF THE STA	TOR DISKS HAD BROKEN AND JAMMED THE BRAKE. THE BRAKE WAS REPLACED WITH AN OVERHAULED UNIT. AD2004-09-05 WHICH ADDRESSES 	MFG BRAKE STATORS BREAKING HAD BEEN ACCOMPLISHED RECENTLY AND PASSED THE INSPECTION AS CALLED OUT. BOTH STATORS ARE STAM	PED 'CHANGE D', SO NO FURTHER ACTION WAS REQUIRED. IN LIGHT OF THIS INCIDENT THE REPLACEMENT CRITERIA SHOULD POSSIBLY BE	 CHANGED.		1	L	7	2 	4F	4	F		A22CE   	E1NE
2005021400217	20050214	00217	EA  	2005	2	14	CA040811001      	1	20040727	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			10219								(CAN) CAPTAINS WINDSHIELD SHATTERED, OCCURRED AT FL330, CREW DESCENDED TO FL100, W/S HEAT ON LOW, MFG P: 7.2 WHEN WINDOW	 SHATTERED.  WINDSHIELD REPLACED.  (SEE ALSO: US NR 2004081200104)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020400001	20050204	00001	EA  	2005	2	4	CA040811002      	1	20040729	G	2612	47259701	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1 ENGINE	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			20493								(CAN) FLT DIVERTED, EMERGENCY DECLARED. ON CLIMBOUT RECEIVED NUMEROUS FIRE FAIL MSGS., CAUTION MSG, THEY ALL DISAPPEARED	. WE THEN RECEIVED A LH ENG FIRE WARNING AND WE SHUT DOWN NR 1 ENGINE. ON APPROACH WE RECEIVED A RH ENGINE FIRE WARNING 	MSG, ON LANDING WE RECEIVED A APU FAIL MSG, WHICH DISCHARGED THE BOTTLE. MTCE R/R THE FIREX CONTROLLER AND APU FIRE BOTT	LE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020400002	20050204	00002	EA  	2005	2	4	CA040811003      	1	20040725	G	5414	22850080158	NOSE COWL       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NACELLE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LOUD NOISE AND SOME LOSS OF ENGINE POWER ON THE RT ENGINE AT CRUISE.  UPON LANDING, THE TOWER INFOR	MED THE AIRCRAFT THAT A COWLING FELL OFF AT LANDING. ENGINE LOWER NOSE COWLING PANEL WAS RECOVERED.MTC LOOKED AT THE AIR	CRAFT AND FOUND THE RT ENGINE UPPER AND LOWER NOSE COWLINGS MISSING. LOWER WAS RECOVERED FROM THE RUNWAY. UPPER WHERE AB	OUTS STILL UNKNOWN. MANY OF THE CAM LOCK FASTENERS ARE STILL IN PLACE. SOME ARE MISSING AND 1 OR 2 FEMALE SOCKETS ARE NO	T DAMAGED.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031400034	20050314	00034	NE  	2005	3	14	CA040811004      	2	20040721	G	7310	0301007720	LINE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE FUEL	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) FUEL LEAK DISCOVERED AT LT INJECTOR ON START UP.  START ABORTED.  UPON INSPECTION, FUEL SUPPLY LINE WAS FOUND CRAC	KED AT FLARE.  LINE REPLACED, A/C RETURNED TO SERVICE.  A NUMBER OF THIS PARTICULAR P/N LINES HAVE FAILED IN THE PAST.  	RECOMMEND USING ADDITIONAL CLAMPING OR DIFFERENT LINE ALTOGETHER.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005031400035	20050314	00035	EU  	2005	3	14	CA040811005      	1	20040809	G	3244	85010	TIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TIRE WAS LOOSING AIR PRESSURE, ON INVESTIGATION IT WAS NOTED THAT THE AIR WAS LEAKING FROM HOLES THAT ARE LOCATED 	JUST UP FROM THE BEAD/SEAT AREA, APPARENTLY TO VENT AIR FROM BETWEEN THE LAYERS OF THE RUBBER.  THIS IS THE THIRD TIME T	HAT WE HAVE CHANGED A MFG TIRE FOR THIS REASON.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005031400036	20050314	00036	EU  	2005	3	14	CA040811006      	1	20040724	G	5240	HC524H0344002	ARM             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					SERVICE DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40117	40117							(CAN) CABIN CREW REPORTED RT FORWARD SERVICE DOOR DIFFICULT TO CLOSE. MAINTENANCE INSPECTION FOUND DOOR 1R UPPER HINGE A	RM ASSEMBLY CRACKED. UPPER HINGE ARM ASSEMBLY REPLACED.  AIRCRAFT RETURNED TO SERVICE.					2	H	7	4 	4F	4	F		A49EU   	E6NE
2005020100152	20050201	00152		2005	2	1	CA040811007      	4	20040702	G	2216	62701135	CABLE           			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	AUTOPILOT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STAB TRIM STIFF WHEN COLD, PILOT SUSPECTED AFT TRIM DRUM INSPECTION OF COMPLETE CONTROL SYSTEM. FOUND CABLE (NR 62	701-135) FRAYED OVER 60 PERCENT AT AREA OF ELECTRIC AUTOPILOT MOTOR. SUSPECTED LOW TEMP AND LOW CABLE TENSION CAUSED CAB	LE TO JAM AROUND THE SEVERED PULLEY WINDINGS AT THE TRIM MOTOR.  NEW CABLE INSTALLED TO CORRECT TENSION AND SYSTEM FUNCT	IONS NORMAL.  ELECTRIC TRIM MOTOR HIDDEN FROM DIRECT VIEW UNDER AFT EDGE OF CARGO AFT WALL.			1	L	7	1 	3O	3	O		A3SO    	E14EA	5	C	P9EA
2005020100188	20050201	00188	EU  	2005	2	1	CA040811008      	1	20040805	G	6322	355A340109	BLOWER          			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					OIL COOLER	DAMAGED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING OPERATION A NOISE WAS HEARD FROM THE BACK OF THE AIRCRAFT, AIRCRAFT WAS LANDED AND DURING INSPECTION TO DET	ERMINE THE ORIGIN OF THE SOUND IT WAS NOTED THAT THE OIL COOLER BLOWER ASSY WAS DAMAGED AND HAD SEVERAL PIECES MISSING. 	THE AIRCRAFT WAS RETURNED TO BASE BY ROAD AND WAS DISASSEMBLED TO THE EXTENT REQUIRED TO INSPECT FOR OTHER DAMAGE. ONCE 	THE BLOWER WAS REMOVED IT WAS NOTED THAT THE FIRST STAGE OF THE ASSY HAD 2 SMALL NICKS ON 2 OF THE ROTATING BLADES.  THE	 FIRST STAGE STATOR CASE, THE SECOND STAGE ROTATING AND STATIONARY COMPONENTS HAD EXTENSIVE DAMAGE AND WERE FOUND IN SEV	ERAL PIECES.   SUSPECT DAMAGE COULD HAVE BEEN CAUSED BY FOD.	1	G	7	2 	3U	3	U		H11EU   	E4CE
2005020100190	20050201	00190	SW  	2005	2	1	CA040811009      	1	20040726	G	6720		CLAMP           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR PEDAL	MISSING         	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		DE	DESCENT        	1			CA											(CAN) ON DECENT PILOT FELT A TAP ON THE TAIL ROTOR PEDALS, AND LOOKED INTO HIS SLINGING MIRROR AND DETERMINED THAT THE L	T BEAR PAW WAS MISSING.  AFTER LANDING HE NOTICED DAMAGE TO TAIL ROTOR BLADES, AND VERTICLE FIN.  ON INSPECTION, IT WAS 	FOUND THAT A CLAMP THAT WOULD PREVENT THE BEAR PAW FROM SLIPPING OFF WAS MISSING FROM THE INSTALLATION.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2005020100191	20050201	00191	NM  	2005	2	1	CA040812001      	1	20040729	G	2910	65178444440	B-NUT           			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYDRAULIC LINE	CRACKED         	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CREW REPORTED 'A' SYSTEM HYDRAULIC FLUID LOSS IN FLIGHT.  MAINTENANCE FOUND LEAK AT B-NUT END FITTING AT 'A' SYSTE	M MODULE. LINE REPLACED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005020100192	20050201	00192	EU  	2005	2	1	CA040812002      	1	20040602	G	2822	P94C16612	PUMP            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					FUEL BOOST	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ALUMINUM PARTICLES FOUND IN FUEL LINE AND MAIN FILTER.  PUMP REPLACED (EXCHANGE WITH MFG).						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2005020100193	20050201	00193	SW  	2005	2	1	CA040812003      	1	20040719	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) BULKHEAD FRAME CRACKED ADJACENT TO RT UPPER TAILBOOM ATTACH BOLT. FRAME REPLACED.						1	G	7	1 	4U	4	U		H4SW    	E22EA
2005020100194	20050201	00194	EU  	2005	2	1	CA040812004      	1	20040620	G	3246	431304	BOLT            	BFGOODRICH  	31530       	AIRBUS	320   	A320214     	3930316	EU  	CFMINT	CFM56 	CFM565B4    	 	NE  					MLG WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2550					(CAN) ON WALK AROUND PILOT FOUND 2 TIE BOLTS (P/N 43-1304) BROKEN ON THE NR 1 MAINWHEEL ASSY, TOTAL CYCLES ON MAIN WHEEL	 ASSY SINCE LAST RE-FURB 427, TOTAL TIME ON TIE BOLTS UNKN.					2	L	7	2 	4F	4	F	RT	A28NM   	E38NE
2005031400076	20050314	00076	SW  	2005	3	14	CA040812005      	1	20040723	G	5320	206031200118S	STRAP           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND STRAP CRACKED AT 100 HOUR INSPECTION. PART REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2005041500007	20050415	00007	SW  	2005	4	15	CA040812006      	1	20040719	G	2810	205031709052S	ANGLE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL CAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17470								(CAN) DURING IMPORT INSPECTION, RT FUEL CELL CAVITY AFT CAP ANGLE FOUND BADLY CORRODED (EXFOLIATION).  PART REPLACED.						1	G	7	1 	4U	4	U		H4SW    	E22EA
2005041500008	20050415	00008	SW  	2005	4	15	CA040812007      	1	20040720	G	5302	206031004113	SKIN            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BCJN06506					(CAN) DURING 100 HOUR INSPECTION, CRACK IN PAINT FORWARD OF NR3 HANGAR SUPPORT BRACKET.  BRACKET REMOVED, PAINT REMOVED 	AND AREA FLUORESCENT PENETRANT INSPECTED. CRACK APPROXIMATELY 1.5 INCH.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005041500009	20050415	00009	NE  	2005	4	15	CA040812008      	2	20040805	G	7310	0319738340	MANIFOLD        			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					FUEL INLET	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING RECEIVING INSPECTION A 0.010 (DAMAGE TO FUEL MANIFOLD),						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2005041500010	20050415	00010	NM  	2005	4	15	CA040812009      	1	20040621	G	2910	114087005	BYPASS VALVE    			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYD SYSTEM	LEAKING         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) GREEN HYDRAULIC LOW LEVEL, LOST ALL GREEN HYDRAULIC PRESSURE WHILE TAXING, DOOR BY-PASS VALVE LEAKING MPN 11408700	5 S/N CWDDDH8197					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005041500011	20050415	00011	NM  	2005	4	15	CA040812010      	1	20040625	G	7334	41817054	TRANSMITTER     			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					FUEL PRESSURE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) NR 1 ENGINE FUEL PRESSURE TRANSMITTER FOUND LEAKING TOTAL TIME ON PART 20349.7HRS TOTAL TIME SINCE INSTALL 3445.2 	HRS					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2005041500012	20050415	00012	SO  	2005	4	15	CA040813001      	1	20040813	G	2910	4085400	LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HYD HAND PUMP	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) A/C WAS UNABLE TO EXTEND GEAR. FOUND HYDRAULIC HAND PUMP PRESSURE LINE WAS CRACKED JUST ABOVE FIRST CHECK VALVE. A	LL HYDRAULIC FUEL LEAKED OUT.					1	L	7	2 	3O	3	O		A20SO   	E14EA
2005041500013	20050415	00013	NE  	2005	4	15	CA040813002      	2	20040731	G	7230		BLADE           			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					COMPRESSOR	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								13348			(CAN) ENGINE 11348 HAD A COMMANDED IFSD AT 33,000 FT WHEN LEFT ENGINE SURGE IN FLT. ENGINE WAS SHUT DOWN AS IT CONTINUE 	TO SURGE. BOROSCOPE REVEALED SEVERE HPC DAM AGE FROM STAGE 2 TO STAGE 10, WITH BLADES HEAVILY DAMAGED AND MISSING. ENGIN	E ENROUTE FOR RRC, FURTHER REPORT WILL BE SUBMITTED UPON ENGINE DISASSEMBLY.				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN
2005041500014	20050415	00014	NM  	2005	4	15	CA040813003      	1	20040628	G	5610	N141T480149	WINDSHIELD      			BOEING	767   	767375      	1385217	NM  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			24333								(CAN) WHILE IN CRUISE CAPT'S WINDSHIELD CRACKED.						2	L	7	2 	4F			RT	A1NM
2005041500015	20050415	00015	NM  	2005	4	15	CA040813004      	1	20040628	G	3240	058002003	SELECTOR        			AIRBUS	A319  	A319114     	3930350	NM  										PARK BRAKE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE STARTING ENG NR 1, PARKING BRAKE WOULD NOT SET. FOOT BRAKES WERE FINE, JUST PARK BRAKE HANDLE WOULD NOT SET 	UNTIL ENG NR 1 FULLY STARTED. CARRIED OUT OPERATIONAL TEST AS PER AMM.  CONFIRMED NO POWERFROM 'NORMAL' SOURCE. REPLACED	 PARK BRAKE CONTROL VALVE-NIL FIX. REPLACED PARK BRAKE SELECTOR SWITCH-OPS CHK'D SERV.				2	L	7	2 	4F			RT	A28NM
2005041500016	20050415	00016	EA  	2005	4	15	CA040813005      	1	20040813	G	2731		ARM             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					RUDDER TRIM	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS UNDERGOING A GENERAL INSPECTION MAINTANCE OBSERVED THE VIKING AIR FLUTTER PREVENTION MODIFICATION	 RUDDER TRIM TAB ARM WAS MISSING THE AIRCRAFT HAD BEEN INSPECETED SOME 50.0 HOURS EARLER WITH NO DEFECTS NOTED					1	H	7	1 	3R	4	T		A815    	E4EA
2004101300020	20041013	00020	EA  	2004	10	13	CA040814001      	1	20040813	G	7110	40S16111AA	CAMLOCK         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COWL	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						C0484					(CAN) UPON INSPECTION OF AIRCRAFT DURING ROUTINE MAINTENANCE, THE LT ENGINE FORWARD LOWER COWL WAS FOUND TO HAVE 3 CAMLO	CK FASTENERS UNDONE ON THE FORWARD IB SIDE.  THE COWL WAS REMOVED, INSPECTED AND THE THREE CAMLOCKS (ONE LONG PN:40S5-11	, THE REST SHORT PN: 40S161-1-1AA) AND GROMMETS AS WELL AS SELECTED OTHERS WERE REPLACED, AS THEY WERE FOUND TO WORN OUT	.  THE COWL WAS REINSTALLED AND THE AIRCRAFT WAS RETURNED TO SERVICE. AIRCRAFT HOURS: 8758, CYCLES: 6474.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101300047	20041013	00047	EA  	2004	10	13	CA040814002      	1	20040813	G	1430	40G15160S	FASTENER        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CAMLOCK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11474	11474							(CAN) UPON INSP OF AC DURING ROUTINE MAINTENANCE, THE RT ENGINE FORWARD LOWER COWL WAS FOUND TO HAVE 3 CAMLOCK FASTENERS	 PULLED THROUGH THE COWL WHILE STILL LOCKED IN THEIR RECEPTACLES, ON THE IB TRAILING EDGE.  THE COWL WAS REMOVED, INSPEC	TED, AND THE THREE AS WELL AS OTHER CAMLOCKS, AND GROMMETS WERE REPLACED.  CLOSER INSPECTION REVEALED GROMMETS TO BE WOR	N, WHICH ALLOWED THE CAMLOCKS TO PULL THROUGH.  THE COWL WAS REINSTALLED AND THE AIRCRAFT WAS RETURNED TO SERVICE. AIRCR	AFT HOURS: 11489, CYCLES: 8993		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101300048	20041013	00048	EA  	2004	10	13	CA040815001      	1	20040808	G	5610	601R330311	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					LT SIDE	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT'S SIDE WINDOW CRACKED DURING CRUISE. SIDE WINDOW WAS REMOVED AND REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004101300049	20041013	00049	SW  	2004	10	13	CA040816001      	1	20040816	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FLAP CONTROL	FRAYED          	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT CABLES FRAYED AT WING ROOT PULLEYS. CABLES REPLACED WITH GALVANIZED.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874
2004101300050	20041013	00050	EA  	2004	10	13	CA040816002      	2	20040816	G	7200	PW150A	ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1	FAILED          	W				A				UNSCHED LANDING         				Y	D	B	ENGINE STOPPAGE           	INFLIGHT SEPARATION       	SMOKE/FUMES/ODORS/SPARKS  	CL	CLIMB          	1			CA											(CAN) ON TAKE-OFF FROM BASE, AT 1000 FT, THE NR 1 ENGINE OIL PRESSURE CAUTION LIGHT CAME ON, THE PILOT WENT FOR MANUAL A	ND BEFORE GETTING TO IT THE NR 1   ENGINE OIL TEMP BEGAN TO RISE RAPIDLY SO HE IMMEDIATELY STARTED TO PERFORM THE EMERGE	NCY SHUT DOWN PROCEDURE. BUT BEFORE HE COULD PERFORM THE TASK THERE WAS A LOUD BANG AND FLAMES SHOT OUT OF THE INTAKE AN	D THE ENGINE SHUT DOWN.  THE PILOT DECLARED AN EMERGENCY AND LANDED.  UPON LANDING THERE WAS A CDS MESSAGE FOR NL SHAFT 	SHEARED AND ALL THE CHIP DETECTORS WERE FLAGGED.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004101300051	20041013	00051	EA  	2004	10	13	CA040816003      	1	20040701	G	3234	750006000	VALVE           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						0044					(CAN) THE NOSE GEAR WOULD NOT RETRACT AFTER TAKEOFF ACCOMPANIED BY A (GEAR DISAGREE) WARNING.  NOSE LANDING GEAR DOOR SE	LECTOR VALVE REPLACED LANDING GEAR OPERATION CHECK SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101300052	20041013	00052	GL  	2004	10	13	CA040816004      	2	20040427	G	7240	23064570	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847080			(CAN) CRACK FOUND DURING REMOVAL FOR UNRELATED SCHEDULED MAINTENANCE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300053	20041013	00053	GL  	2004	10	13	CA040816005      	2	20040304	G	7240	23064570	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847297			(CAN) COMBUSTION LINER FOUND CRACKED DURING TURBINE REMOVAL.  NO CRACKS ALLOWED IN THIS AREA.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300054	20041013	00054		2004	10	13	CA040816006      	4	20040811	G	3497		WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ADI	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE CARRYING OUT COMPANY CAMPAIGN NOTICE 851-34-10-24, FOUND NO DAMAGE ON THE WIRE BUNDLE FOR THE HSI.  HOWEVER 	THERE WAS DAMAGE FOUND ON THE ADI WIRE BUNDLE. SEVERAL WIRES IN THE BUNDLE SHOWED EVIDENCE OF SHIELD DAMAGE AND ONE SING	LE WIRE SHOWED EXPOSED CORE.  ALL NECESSARY WIRES WERE REPAIRED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	2 	4F	4	F		A22CE   	E1NE
2004101300104	20041013	00104	GL  	2004	10	13	CA040816007      	2	20040406	G	7240	23064570	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847194			(CAN) CRACK FOUND IN COMBUSTION LINER WHEN REMOVED FOR TURBINE INSPECTION. NO CRACKS ALLOWED IN THIS AREA.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300105	20041013	00105	GL  	2004	10	13	CA040816008      	2	20040127	G	7240	23030911	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847194			(CAN) CRACKS FOUND IN OUTER COMBUSTION CASE ARMPIT AREA ON NORMAL DAILY INSPECTION.  NO CRACKS ALLOWED IN THIS AREA.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300106	20041013	00106	CE  	2004	10	13	CA040816009      	1	20040812	G	3246	950476	BEARING         			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT IB WHEEL ASSY  INNER BEARING FAILED, ALLOWING WHEEL TO MOVE SUFFICIENT TO ALLOW CONTACT OF THE INNER RIM TO NON	 ROTATING BRAKE COMPONENTS DAMAGING INNER HALF OF WHEEL ASSY.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
2004101300108	20041013	00108	NE  	2004	10	13	CA040817002      	2	20040730	G	7532		SWITCH          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BLEED VALVE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA						47					(CAN) BLEED VALVE LIGHT MICROSWITCH CAME APART. THE BROKEN PIECES OF THE ROLLER JAMMED BETWEEN THE PLUNGER AND HOUSING P	REVENTING SMOOTH BLEED VALVE BUTTERFLY OPENING AND CLOSING. BUTTERFLY WAS FOUND PARTIALLY CLOSED CAUSING COMPRESSOR STAL	L WHEN ATTEMPTING THROTTLE INCREASE. BUTTERFLY WAS OPENING ENOUGH FOR BLEED VALVE LIGHT TO BE ON INDICATING IT WAS FULLY	 OPEN.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101300109	20041013	00109	EU  	2004	10	13	CA040817003      	1	20040714	G	6210	355A11002009	BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION A 5.500 INCH (138MM) CRACK WAS DISCOVERED ON THE UPPER SURFACE IN ZONE C OF ONE MAIN 	ROTOR BLADE.  THE CRACK WAS BEYOND THE LIMIT OF 100 MM FOR THIS AREA.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004101300110	20041013	00110	EU  	2004	10	13	CA040817004      	1	20040812	G	2913	S40	SPLINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NO LUBRICATION FOUND ON PUMP SPLINES.  PUMP SPLINES WORN . NO SPLINES FOUND INSIDE THE S40 PUMP DRIVE DUE TO POOR 	LUBRICATION.  HYDRAULIC PUMP AND S 40 DRIVE REPLACED.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2004101300111	20041013	00111	EU  	2004	10	13	CA040817005      	1	20040811	G	2510	9593001131	SEAT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE CREW SEATS IAW MFG SB 25-031, THE SEAT PANS WERE FOUND TO BE CRACKED ON THE OB FWD CORNER	 AREA.  MFG SL 072 COVERS REPAIRS OF THE SEAT PANS IN QUESTION BUT IN A DIFFERENT AREA FOR CRACKING.  BOTH THE CAPTAINS 	AND CO-PILOTS SEATS WERE FOUND LIKE THIS PN 959.30.01.131 AND .132 RESPECTIVELY.  VENDOR PN ARE 5PC41000-505 AND -506.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004101300137	20041013	00137	SW  	2004	10	13	CA040817006      	1	20040816	G	5740	31692	ATTACH FITTING  			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235K2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	WING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE STRUT ATTACH FITTING ON FORWARD SPAR OF THE RH WING WAS CHAFED BY THE LEADING EDGE SKIN, WHICH HAD NOT BEEN TR	IMMED ADEQUATELY DURING MANUFACTURE.  THE CHAFING LEFT A SMALL DIMPLE THAT COULD LEAD TO CRACKING OF THE FITTING.					1	H	7	1 	3O	3	O		A759    	E223	5	N	P9045
2004101800055	20041018	00055	GL  	2004	10	18	CA040817007      	2	20040807	G	7314	68992253	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) ON STARTUP OF THE ENGINE THERE WAS A HOWLING NOISE COMING FROM THE ENGINE. THE NOISE WOULD ONLY BE ON STARTUP AND 	WOULD GO AWAY ONCE THE ENGINE WAS RUNNING.  IT WAS DETERMINED THAT THE NOISE WAS COMING FROM THE FUEL PUMP AND WAS REPLA	CED.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2004101800056	20041018	00056	EA  	2004	10	18	CA040817008      	1	20040811	G	5710	600151103	STRUCTURE       	CNDAIR      		CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					WINGLET TIP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE POST FLIGHT INSPECTION THE RT AND LT WINGLET TIPS WERE FOUND TO BE DAMAGED BY STATIC DISCHARGE. THE RES	IN MATERIAL WAS WAS BLOWN AWAY EXPOSING THE CARBON FIBERS AND LEAVING THE TRAILING EDGE FRAYED. CREW DID NOT EXPERIENCE 	LIGHTNING ON THE LAST TRIP BUT DID FLY IN LIGHT PRECIPITATION.  THE STATIC WICKS TESTED SERVICEABLE. THE TIPS HAD EXTRA 	STATIC WICKS INSTALLED PREVIOUSLY IAW SB 23-006.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101800057	20041018	00057	CE  	2004	10	18	CA040818001      	1	20040813	G	3244	178K235	TIRE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOTS NOTICED ON THEIR WALK AROUND, DURING A FUEL STOP THAT THE RT IB MAIN TIRE HAD LOST ITS TREAD AROUND THE COM	PLETE CIRCUMFERENCE OF THE TIRE AT THE SIDEWALL.					2	L	7	2 	4F	4	F		A10CE   	E6WE
2004101800058	20041018	00058		2004	10	18	CA040818002      	4	20040721	G	3418	3995100208	COMPUTER        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					STALL WARNING	INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			12401								(CAN) DURING APPROACH AT 2500 FEET, THE STICK SHAKER AND STICK PUSHER WERE ENGAGED SIMULTANEOUSLY, FOLLOWING BY THE DE-C	ONNECTION OF THE AUTOPILOT. THIS INDUCED A LITTLE VARIATION OF THE AIRCRAFT NOSE DOWN.  THE FIRST OFFICER IMMEDIATELY CO	MPENSATED THIS VARIATION.  THE FLIGHT CREW PROCEEDED WITH THE LANDING WHICH OCCURRED WITHOUT FURTHER INCIDENT.  STALL CO	MPUTER WAS REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101800059	20041018	00059	NE  	2004	10	18	CA040818003      	2	20040818	G	8510	260483	SHAFT           	PWA         							PWA   	R2800 	R2800*      	52026	NE  					REDUCTION GEAR	SHEARED         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) TWO PINION SHAFTS FOUND SHEARED WHEN REDUCTION GEAR SECTION REMOVED.   ALL BROKEN PARTS FOUND AND ENGINE CLEANED F	OR REASSEMBLY.  GEAR SECTION SENT TO OVERHAUL SHOP FOR REPAIR.										4	R			5E8
2004101800091	20041018	00091	WP  	2004	10	18	CA040818004      	1	20040817	G	5230		DOOR            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	C1 CARGO	OPEN            	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, CREW NOTICED A (CARGO DOOR UNSAFE) LIGHT AND THE A/C WAS NOT PRESSURIZING. THE A/C RETURNED TO THE 	AIRPORT WHERE THE UPPER FWD CARGO DOOR WAS FOUND UNLOCKED. DOOR WAS LOCKED AND A/C CONTINUED ON  FLIGHT.					2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898
2004101800095	20041018	00095	EU  	2004	10	18	CA040818005      	1	20040511	G	3260	UC702322	LEVER           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NLG	OBSTRUCTED      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE NOSE U/C INDICATOR LIGHT REMAINED GREEN DURING ALL PHASES OF U/C OPERATION.  INVESTIGATION REVEALED A SMALL ST	ONE WEDGED UNDER THE SWITCH OPERATING LEVER.  WITH THE STONE REMOVED THE INDICATION SYSTEM WORKED NORMALY.					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2004101800096	20041018	00096	EU  	2004	10	18	CA040818006      	2	20040517	G	8560	AGS6056	CLAMP           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	SUPERCHARGER	LOOSE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AN INTERMITTENT BURNING SMELL WAS NOTICED BY THE FLIGHT CREW. INVESTIGATION REVEALED THE RT AIR CONDITIONING SUPER	CHARGER OUTLET DUCT SLEEVE CLAMP WAS LOOSE. SINCE THE CLAMP WAS RESECURED THERE HAVE BEEN NO FURTHER REPORTS OF BURNING 	ODORS IN THE COCKPIT.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2004101800097	20041018	00097	NE  	2004	10	18	CA040818008      	2	20040812	G	7230	305309CL1	SEGMENT         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COMPRESSOR TURB	SHIFTED         	W				A				UNSCHED LANDING         				J	M		WARNING INDICATION        	OVER TEMP                 		CL	CLIMB          	1			CA											(CAN) WHILE INCREASING POWER FOR CLIMB, THE PILOT NOTICED AN ITT OVERTEMP INDICATION. AIRCRAFT RETURNED TO AIRPORT UNDER	 REDUCED POWER TO REMAIN BELOW MAXIMUM CONTINUOUS ITT. MAINTENANCE SPLIT THE ENGINE AND FOUND THAT A SHROUD SEGMENT HAD 	SHIFTED AND CONTACTED THE COMPRESSOR TURBINE BLADES CAUSING CONSIDERABLE LOSS OF BLADE TIP MATERIAL AND DISCOLORATION. E	NGINE REMOVED FOR OVERHAUL AND FURTHER INVESTIGATION.			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL
2004101800098	20041018	00098	NE  	2004	10	18	CA040818009      	2	20040817	G	7420	10878451	LEAD            		R2800CB3    	DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA						P33489					(CAN) DURING TAKEOFF FOR A PRACTICE, NR 2 ENGINE BACKFIRED. THE LOAD OF WATER WAS JETTISONED, THE ENGINE WAS SHUTDOWN AN	D THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION BY MAINTENANCE CREW, A BROKEN LOW TENSI	ON IGNITION LEAD WAS FOUND. THE LEAD WAS REPLACED. THE AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	4 	4R	3	R		6A4     	ATC14	6	C	P871
2004101800099	20041018	00099	SO  	2004	10	18	CA040819001      	2	20040610	G	7322	MA3SPA	CARBURETOR      			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE REPORTED RUNNING INTERMITTENTLY. MIXTURE OPERATES ONLY THROUGH LIMITED RANGE. INSPECTION REVEALS LARGE MOUS	E NEST IN AIR BOX AND CARBURETOR AS FAR AS VENTURI.  SEVEN DEAD INFANT MICE FOUND IN NEST.   ENTRY TO CARB THROUGH CABIN	 HEATER DUCTING. AIRCRAFT LAST FLOWN APRIL 3, 2004.  SOLUTION: ENSURE CABIN HEAT CONTROL IN CLOSED POSITION.				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
2004101800100	20041018	00100	SW  	2004	10	18	CA040819002      	1	20040808	G	6220	206011139001	RESTRAINT       	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ROTOR HEAD	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AAB05286					(CAN) DURING DAILY INSPECTION IT WAS NOTED THE FLAP RESTRAINT HAD BECOME DELAMINATED AT BEARING HOUSING.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2004101800101	20041018	00101	NM  	2004	10	18	CA040819003      	1	20040729	G	3232	69378776	FITTING         			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50515	36641							(CAN) CRACKED FITTING FOUND DURING CPCP INSPECTION.  RT MAIN LANDING GEAR ACTUATORS WING LINK FORWARD ATTACH FITTING (TO	 WING REAR SPAR ATTACH).					2	L	7	2 	4F	4	F		A16WE   	E2EA
2004101800121	20041018	00121	CE  	2004	10	18	CA040819004      	1	20040807	G	5210	NAS51733	SCREW           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	DOOR LATCH	BENT            	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE OF FL270 THE PILOT HEARD A BANG AND EXPERIENCED A PARTIAL LOSS OF PRESSURIZATION. HE INITIATED AN 	EMERGENCY DESCENT AND LANDED AT DESTINATION WITHOUT INCIDENT. UPON INVESTIGATION IT WAS NOTED THAT THE FORWARD UPPER LAT	CH PLATE HAD SHIFTED AND THAT ONE OF THE FOUR ATTACH SCREWS WAS MISSING.  THE REMAINING THREE SCREWS, ONE WAS BENT. THER	E WERE NO VISIBLE IDENTIFICATION MARKINGS ON THE REMAINING SCREWS BUT THEY APPEAR TO BE AN507 SCREWS RATHER THAN THE REQ	UIRED NAS517. THE FORWARD UPPER LATCH HOOK BELLCRANK, P/N 50-430031-15, WAS ALSO DAMAGED.		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE
2005031100013	20050311	00013	EU  	2005	3	11	CA040819005      	1	20040721	G	7931	704A37642043	PRESSURE SENSOR 			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE OIL	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) OIL PRESSURE NO READING.  REPLACED ENGINE OIL PRESSURE SENSOR.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005031100023	20050311	00023	NM  	2005	3	11	CA040819006      	1	20040818	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) DURING ROUTINE CHECK A 2.7500 INCH CRACK WAS FOUND ON THE OUTER FUSELAGE SKIN AT FS 847 STRINGER 24L.  CRACK REPAI	RED IAW SRM REV 85.53-30-3,FIG 48 SHT 33. TIMES 59257.06 CYCLES 55392.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041500017	20050415	00017	SO  	2005	4	15	CA040819007      	2	20040812	G	8520	654101A7R	CRANKCASE       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								291429R			A/C ENG CRANKCASE FAILURE AS A RESULT OF A RECENT FAILURE DESCRIBED IN SDR CA040806006 SUBMITTED 08/6/2004, A VOLUNTARY 	INSPECTION CARRIED OUT BY OPERATOR AT REQUEST OF OVERHAUL FACILITY. CYLINDERS NR 1 & 3 REMOVED SO THAT NR 2 & 3 INTERMED	IATE BEARING SADDLE COULD BE VIEWED.  INSPECTION CONCLUDED THAT MOVEMENT OF BEARINGS HAD OCCURRED & TEAR DOWN OF ENG WOU	LD BE REQUIRED FOR FURTHER INVESTIGATION.  UPON TEAR DOWN, FOUND FRETTING OF CRANKCASE ON NR 2 & NR 3 INTERMEDIATE MAIN 	BEARING THRU-BOLT PADS.		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA
2005031400065	20050314	00065	EA  	2005	3	14	CA040819008      	2	20040809	G	8530	LW11485	HOUSING         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	PUSHROD	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								L2037340A			(CAN) ON INSPECTION, LT ENGINE SIDE FOUND VERY OILY, AFTER CLEANING, RUN UP TEST C/O AND OIL LEAK FOUND ON NR2 INTAKE VA	LVE PUSH ROD HOUSING.  A SMALL PIN HOLE FOUND ON THE TUBE (VISIBLE ONLY WITH A MAGNIFYING GLASS).  NEW TUBE P/N LW11485 	INSTALLED, OPERATIONAL TEST C/O AND NO LEAK NOTED.				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA
2005041500018	20050415	00018	EA  	2005	4	15	CA040819009      	2	20040804	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23405					86034GG			ENG REMOVED FROM WING WHEN OPERATOR FOUND BETA CONTROL SYSTEM JAMMED.  ENG SHIPPED TO ENGINE AMO FOR INVESTIGATION & REP	AIR. SEIZED BETA CONTROL LINKAGE RESULT OF HEAVY CONTACT WEAR BETWEEN REAR SEALING LAND OF BETA TRANSFER SLEEVE & PROP S	HAFT.  REASON FOR SEIZURE WAS A LACK OF LUBE.									4	T			E4EA
2005031400066	20050314	00066	EU  	2005	3	14	CA040819010      	1	20040818	G	3411	853BR	PROBE           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PITOT	UNSERVICEABLE   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) NO AIRSPEED INDICATION ON F/O SIDE DURING T/O. T/O REJECTED. MAINTENANCE DID A PITOT/STATIC TESTED AND SYSTEM FOUN	D NORMAL. BOTH ADC COMPUTER INTERCHANGED FORT/S. THE FOLLOWING T/O WAS ALSO REJECTED FOR THE SAME REASON.  MAINTENANCE F	OUND THE RT F/O INTERNAL PITOT PROBE CONTAMINATED WITH RUST.  THE PITOT PROBE WAS REPLACED AND AIRCRAFT DISPATCHED SERVI	CEABLE.			2	L	7	2 	4F	4	F	RT	        	E25NE
2005031400067	20050314	00067	NM  	2005	3	14	CA040819011      	1	20040813	G	2910	SM601BA20A1	RCCB            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) THE NR 2 STANDBY HYD PUMP WOULD NOT COME ON LINE WHEN SELECTED. THE CAUSE WAS DETERMINED TO BE A FAILED REMOTE CON	TROL CIRCUIT BREAKER. THE UNIT HAD ONLY 24.7 HOURS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031400068	20050314	00068	WP  	2005	3	14	CA040819012      	1	20040805	G	3150		WARNING SWITCH  			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					TAIL CONE	INCORRECT       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, TAIL CONE ANNUNCIATOR UNSAFE LIGHT WENT ON.  AIRCRAFT LANDED BACK TO DEPARTING AIRPORT.  MAINTENANCE	 FOUND THE TAIL CONE SAFETY LOCK CABLE BALL END NOT SEATED PROPERLY TO CONTACT THE WARNING SWITCH.  THE INVESTIGATION RE	VEALED THAT AN INSPECTION/TEST OF TAIL CONE RELEASE MECHANISM WAS PERFORMED ON THE PREVIOUS DAY.  IT HAS BEEN CONCLUDED 	THAT THE WARNING SWITCH WAS NOT PROPERLY ENGAGED.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005031400069	20050314	00069	WP  	2005	3	14	CA040819013      	1	20040817	G	2910	9036261	LINE            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	HYD PRESS	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AC WAS ORBITING OVER FIRE.  A LOUD SURGING SOUND WAS HEARD. A CHECK OF HYDRAULIC RESERVOIR INDICATED THAT NO HYDRA	ULIC FLUID WAS REMAINING. FLAPS WERE SELECTED FROM 15 TO 0 DEGREES. HYD BYPASS WAS SELECTED UP.  RETARDANT LOAD WAS JETT	ISONED. AC RETURNED TO BASE. FLAPS WERE SELECTED TO 15 DEGREES, GEAR WAS SELECTED DOWN. UPON LANDING A VIOLENT NOSE WHEE	L SHIMMY WAS EXPERIENCED. EMERGENCY AIR BRAKE SYS WAS USED TO BRING AC TO A STOP. NO DC PUMP PRESSURE WAS AVAILABLE DUE 	TO FLUID LOSS. AC STOPPED SAFELY. UPON INVESTIGATION BY THE MAINT, MAIN HYDR PRESS LINE WAS FOUND BURST CAUSING FLUID LO	SS. LINE WAS REPLACED WITH A SERVICEABLE COMPONENT. AC SYSTEM WAS LEAK CHECKED AND THE AC WAS RETURNED TO SERVICE.	2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898
2005031400070	20050314	00070	CE  	2005	3	14	CA040820001      	1	20040818	G	3510	2519C5912	LINE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					OXYGEN SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE SERVICING THE TAIL MOUNTED OXYGEN BOTTLE, AFTER REPLACEMENT OF THE FILLER FITTING, AT ABOUT 300 PSI A LEAK W	AS HEARD AND SMALL FLAME SEEN AT THE LINE LEADING TO THE CABIN, FORWARD OF THE BOTTLE.  SYSTEM TURNS OFF.  THE LINE HAD 	THREE CRACKS ON THE B-NUT FITTING. LINE REPLACED.				2	L	7	2 	4F	4	F		A10CE   	E6WE
2005031400078	20050314	00078		2005	3	14	CA040820002      	4	20040815	G	2397	FIN6208VC	CONNECTOR       			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					LCD MONITOR	BURNED          	W				K				NONE                    				H	M		ELECT. POWER LOSS-50 PC   	OVER TEMP                 		IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT ARRIVED WITH AN INOPERATIVE LCD MONITOR FOR PASSENGER ENTERTAINMENT SYSTEM.  AFTER INVESTIGATION, FOUND O	NE OF THE ENTERTAINMENT CONNECTORS BADLY BURNED WITH SEVERAL PINS COMPLETELY GONE, IN THE PASSENGER COMPARTMENT CEILING.	  CONNECTOR WAS REPLACED AND COMPLETE SYSTEM WAS VERIFIED.  A FLEET CAMPAIGN WAS INITIATED AND A ROUTINE INSPECTION WAS 	INTRODUCED IN THE A CHECK MAINTENANCE PROGRAM.			2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2005041500019	20050415	00019	SW  	2005	4	15	CA040820003      	1	20040818	G	6100		SHAFT           			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	SEIZED          	W				A				UNSCHED LANDING         				E	D	J	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	WARNING INDICATION        	CR	CRUISE         	1			CA								P40355			(CAN) RETURNING FROM A FIRE ACTION, IN CRUISE AT 9500 FEET ASL, THERE WAS A LOSS OF POWER FROM THE RT ENGINE ACOMPANIED 	BY VIBRATION AND NOISE.  THE RT ENGINE SHUT DOWN, THE PILOT COMPLETED THE EMERGENCY CHECK LIST AND ACCOMPLISHED AN UNEVE	NTFUL LANDING.  MAINTENANCE FOUND THE PROP SHAFT SEIZED AND A HOLE IN THE PROP REDUCTION GEARBOX.				1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA
2005041500020	20050415	00020	WP  	2005	4	15	CA040820004      	1	20040817	G	6320	C0066	TRANSMISSION    			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	NOISY           	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) DURING LANDING THE HEARD GRINDING NOISE.  FURTHER INVESTIGATION REVEALED NOISE WAS COMING FROM MAIN ROTOR TRANSMIS	SION. TRANSMISSION WAS REPLACED AND NO FURTHER OCCURRENCES AND WILL SUBMIT FURTHER INFORMATION WHEN TEAR DOWN OF TRANSMI	SSION REPORT BECOMES AVAILABLE.				1	G	7	1 	3O	3	O		H11NM   	E295
2005041500021	20050415	00021	NE  	2005	4	15	CA040820005      	2	20040818	G	8530		CYLINDER        			DOUG  	A26   	A26CSHIELDS 	3020506	WP  	PWA   	R2800 	R280079     	52026	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								FP028246			(CAN) DURING A FOREST FIRE ACTION, THE PILOT NOTICED AN OIL LEAK COMING FROM THE TOP OF THE LT ENGINE.  SHUT THE ENGINE 	DOWN AND RETURNED TO THE FIELD MAINTENANCE BASE WITH OUT INCIDENT. MAINTENANCE FOUND TWO CRACKED CYLINDERS. THEY CHANGED	 THE CYLINDERS AND GROUND CHECKED THE ENGINE AND FOUND IT TO BE SERVICEABLE.				2	M	7	2 	4R	4	R		L34     	5E8	6	C	P603
2005041500022	20050415	00022	WP  	2005	4	15	CA040820006      	1	20040726	G	2410		GENERATOR       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RIGHT	OVERHEATED      	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) RT GEN FAILED DURING TAXI TO GATE.  GEN DISCONNECTED & QRH PROCEDURE COMPLETED BY CREW.  FOR FOLLOWING FLT, A/C DI	SPATCHED IAW MEL 24-1.  4 HOUR FLT CONDUCTED TO NEXT STA & ON ARRIVAL, MX NOTICED SMOKE COMING FROM NR 2 ENG.  INVEST RE	VEALED PAINT BLISTERING ON LOWER COWL IN VICINITY OF GEN.  A/C GEN FOUND SMOLDERING & EMITTING HIGH LEVELS OF HEAT & GEN	 HOUSING FOUND DISCOLORED. CSD NOT DISCONNECTED & IS NOT REQUIRED TO BE DISCONN IAW QRH & MEL PROCEDURES.  WITHOUT DISCO	NNECTING DRIVE, GEN WILL CONTINUE TO SPIN. TO AVOID SUCH THIS, OPS WILL REVISED QRH & MEL PROCEDURES IN ORDER TO DISCONN	ECT CSD FOLLOWING GEN DISCONNECT.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041500023	20050415	00023	NE  	2005	4	15	CA040820007      	2	20040729	G	7261		FILTER          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ENGINE OIL	CLOGGED         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			36699								(CAN) DURING TAKE OFF ROLL, RT ENG OIL FILTER CLOG LIGHT ILLUMINATED. TAKE OFF WAS REJECTED. ENGINE RUN UP CONDUCTED WIT	H NO LIGHT REILLUMINATED.  AIRCRAFT TOOK OFF AND THEN FLOWN TO THE SCHEDULED STATION ( MAIN BASE ) WITHOUT LIGHT REILLUM	INATING.  AT THE MAIN BASE, THE OIL FILTER WAS REMOVED AND FOUND WITH CARBON DEPOSIT. NEW OIL FILTER INSTALLED.  THE ENG	INE HAS BEEN SCHEDULED TO BE REPLACED AS PRECAUTIONARY BECAUSE THIS PROBLEM IS RECURRENT.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041500024	20050415	00024	SW  	2005	4	15	CA040821001      	1	20040820	G	6420	212010783101	SPHERICAL BEARIN			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					T/R PITCH LINK	FAILED          	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) A/C WAS CLIMBING AFTER FILLING THE WATER BUCKET WHEN HE LOST COMPLETE TAIL ROTORAUTHORITY.THE A/C MADE SEVERAL 360	 DEGREE TURNS AFTER COMING TO REST IN A CON FINED AREA. SUBSTANTIAL DAMAGE WAS DONE TOTHE MAIN ROTOR BLADES AS THEY STRU	CK A TREE UPON LANDING.ONE OF THE TAIL ROTOR PITCH LINKS WAS FOUND TO HAVE AN EXTREMELY WORN OFF SPHERICAL BEARING WHICH	 LED TO THE PITCH LINK SHIFTING CLOSE TO THE TRUNNION. THE PITCH LINK LEFT SEVERAL MARKS ON THE TRUNNION BEFORE IT WAS J	AMMED BETWEEN THE PITCHHORN AND THE TRUNNION DURING T/R PITCH CHANGE WHICH LED TO THE PITCH LINK BREAK ING CLEAN OFF.		1	G	7	1 	4U	4	U		H1SW    	E17EA
2005041500025	20050415	00025	NM  	2005	4	15	CA040823001      	1	20040820	G	2910	82910009123	LINE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH, PILOT REPORTED SMOKE IN COCKPIT AND PERFORMED AN UNEVENTFUL EMERGENCY LANDING. THE 'SMOKE' 	REVEALED TO BE HYDRAULIC FLUID MIST, WHICH SPREAD ALL OVER IN THE COCKPIT. ON GROUND WE FOUND A HYDRAULIC LINE BELOW THE	 COCKPIT CRACKED NEAR THE BEND RADIUS. BOMBARDIER AEROSPACE IS INVESTIGATING THIS EVENT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101300028	20041013	00028	WP  	2004	10	13	CA040823002      	1	20040819	G	7921	D6752110	CIRCUIT BREAKER 			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					OIL COOLER DOOR	STICKING        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE OIL TEMPERATURE ON THE LT ENGINE CLIMBED TO LIMITS. THE OIL COOLER DOOR WAS NOT OPERATING. THE E	NGINE WAS SHUT DOWN AND THE PROPELLER WAS FEATHERED AS A PRECAUTION. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION B	Y MAINTENANCE THE CIRCUIT BREAKER WAS EXERCISED AND THE SYSTEM OPERATED NORMALLY. A CIRCUIT BREAKER WAS SHIPPED AND THE 	BREAKER WAS REPLACED. THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4R	4	T		6A6     	E282
2004101300076	20041013	00076	WP  	2004	10	13	CA040823003      	1	20040820	G	2150	20495055	ACM             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LEFT	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLOW LIGHT (PRESSURIZATION) CAME ON AFTER TAKEOFF.  AIRCRAFT LANDED BACK FROM DEPARTURE.  MAINTENANCE FOUND ONE CL	AMP NOT PROPERLY INSTALLED ON OUTLET OF LT ACM.  ACM WAS PREVIOUSLY REPLACED FOLLOWING DISCREPANCY.   CLAMP HAS BEEN SEC	URED  FOLLOWED WITH PRESSURIZATION TEST AND AIRCRAFT DISPATCHED SERVICEABLE.  A SECOND AIR TURNBACK HAPPENED THE FOLLOWI	NG DAY FOR THE SAME REASON (PRESSURE FLOW LIGHT ON).  MAINTENANCE FOUND THE LT ACM SEIZED.  ACM HAS BEEN REPLACED.  ACM 	IS UNDER INVESTIGATION.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101300077	20041013	00077	EA  	2004	10	13	CA040823004      	2	20040820	G	7322	MA4SPA	CARBURETOR      			SLNSBY	T67   	T67C        	       	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	FAILED          	W				B				EMER. DESCENT           				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING A LOCAL FLIGHT, PILOT REPORTED THAT THE THROTTLE WAS BINDING. AIRCRAFT LANDED SAFELY. THE MAINTENANCE INVES	TIGATION INDICATED THAT THE CARBURETOR BUTTERFLY VALVE WAS EXTREMELY STIFF. THIS CARBURETOR WAS INSTALLED PRIOR TO THIS 	FLIGHT AND UPON RUN UP SHOWED NO STIFFNESS OR BINDING. THE CARBURETOR IN QUESTION AND THE ONES IN STORES FROM THE SAME R	EPAIR/OVERHAUL SHOP WERE SENT BACK FOR INVESTIGATION AND CONFIRMATION OF AIRWORTHINESS. WE WILL SUBMIT AN ATTACHMENT TO 	THIS SDR, AS SOON AS WE GET THE RESULTS FROM THE REPAIR/OVERHAUL SHOP.		1	L	7	1 	3O	3	O	NT	A73EU   	E274	5	N	P88614
2004101300078	20041013	00078	NE  	2004	10	13	CA040823005      	2	20040804	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  						ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AUGUST 04, AIRCRAFT, EN ROUTE, DIVERTED TO NEAREST ALTERNATE AIRPORT.  WHEN THE CABIN CREW REPORTED A BURNING SMEL	L (PLASTIC) IN THE AFT RT CABIN NEAR THE LAVATORY.   MAINTENANCE PERSONNEL OPENED THE AISLE CEILING, REMOVED THE TOILET 	SHROUD (BOLSTER), OPENED THE LAVATORY CEILING AND THEN CARRIED OUT A HIGH POWER RUN WITH PACKS ON, IN ORDER TO DUPLICATE	 THE SMELL, NO BURNING SMELL WAS DETECTED.  AS A PRECAUTIONARY MEASURE A TECHNICIAN BOARDED THE AIRCRAFT FOR THE REMAIND	ER OF THE FLIGHT.   NO FINDINGS WERE REPORTED.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101300079	20041013	00079	NM  	2004	10	13	CA040823006      	1	20040709	G	2910		LINE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYD SYSTEM	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER ENGINE SHUT DOWN AT THE GATE, HYDRAULIC FLUID WAS NOTED LEAKING FROM THE NOSE GEAR AREA. NOSE GEAR DRAG STRU	T ACTUATOR HOSE REPLACED DUE TO LEAKING P/N DSC252B40124.  DAMAGE FOUND TO BRAIDING JUST AFT OF THE COLLAR DEFECT NR 416	542.  GEAR RETRACTION CHECKS COMPLETED AND NO LEAKS DETECTED.  AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101300080	20041013	00080	EA  	2004	10	13	CA040823007      	2	20040810	G	7414	D4RN3000	MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	MIGRATED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ATTACH NUTS ON CLAMP BLOCK WERE TIGHT.  MAGNETO ROTATED TO CAUSE RPM DROP.  THE MAGNETO HAD 386.6 HOURS SINCE LAST	 REMOVAL.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005020700005	20050207	00005	CE  	2005	2	7	CA040823BB       	1	20040820	G	5343	1216012	FITTING         			CESSNA	206   	U206B       	2073322	CE  						MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE 100 HOUR INSPECTION THE RH MAIN GEAR OUTBOARD FITTING WAS FOUND CRACKED AT THE UPPER AFT RADIUS OF THE 	FITTING OPENING.THE FITTING WAS REPLACED IN ACCORDANCE WITH CESSNA'S RECOMMENDATIONS (OBTAINED FROM CESSNA) WITH A USED 	SERVICEABLE CUSTOMER SUPPLIED UNIT AFTER NDT INSPECTION.				1	H	7	1 	3O				A4CE    		5	C	P21EA
2004101300081	20041013	00081	NM  	2004	10	13	CA040824001      	1	20040427	G	3297	461515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	MLG	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) UNABLE TO RETRACT NOSE GEAR AFTER TAKE OFF.  GEAR RECYCLED, WITH UNSUCCESSFUL RESULT.  NO AMBER GEAR DOOR LIGHT PR	ESENT FOR NOSE GEAR DOORS WHEN GEAR IN TRANSITION.  HARNESS ASSY WOW NR 2/CENTER REPLACED ACC AMM 32-21-11. OPERATIONAL 	TEST OF THE LANDING GEAR SYSTEM PERFORMED ACC 32-31-00-710-801.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE
2004101300082	20041013	00082	NM  	2004	10	13	CA040824002      	1	20040505	G	3234	483001	SELECTOR VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	LANDING GEAR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF WHEN SELECTING GEAR UP, ALL GEAR INDICATIONS WAS TRANSIT, RED AND YELLOW. GEAR SELECTED DOWN, GAVE 3	 GREEN SAFE INDICATIONS. GEAR SELECTED UP AGAIN GAVE MAIN GEAR UP INDICATIONS, BUT NOSE GEAR WAS STILL SHOWING TRANSIT, 	RED AND YELLOW. GEAR WAS AGAIN SELECTED DOWN, GIVING 3 SAFE INDICATIONS, AND A/C RETURNED TO BASE FOR NORMAL LANDING. TA	XI TO GATE REVEALED NO UNUSUAL INDICATIONS. LANDING GEAR SELECTOR VALVE REPLACED ACC AMM 32-31-06.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE
2004101500079	20041015	00079	NM  	2004	10	15	CA040824003      	1	20040512	G	3260	401020101	SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG LOCKED	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ON GROUND, WHILE PREPARING FOR THE RETURN FLIGHT WITH ENGINES OFF AND GPU CONNECTED, GEAR UNSAFE LIGHT FOR NOSEWHE	EL AND LANDING GEAR SELECTOR LIGHTS FLASHED ONCE OR TWICE AND WENT OUT.  NOSE GEAR WAS EXAMINED DURING PFI WITH NO REMAR	KS.  DURING START UP NOSE GEAR ADVISORY LIGHT AND GEAR UNSAFE LIGHT CAME ON INTERMITTENTLY SEVERAL TIMES AND WE COULD HE	AR THE GEAR DOORS OPEN AND CLOSE. THIS WAS CONFIRMED BY THE GROUND PERSONAL.  NOSE GEAR LOCK NR 1 SENSOR REPLACED ACC AM	M 32-61-06.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004101800060	20041018	00060	NM  	2004	10	18	CA040824004      	1	20040519	G	3260	401020101	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	OPEN            	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) AFTER GEAR UP SELECTION PILOTS RECEIVED BOTH SAFE AND UNSAFE LIGHTS (GREEN/RED) ON GEAR INDICATION PANEL BUT NO DO	OR LIGHTS (ORANGE).  AFTER ONE RECYCLE PILOTS LEFT THE GEAR DOWN WITH 3 GREEN LIGHTS AND PROCEEDED TO DESTINATION.  PROX	IMITY SENSOR ELECTRONIC UNIT (PSEU) CONSULTED FOR FAULTS. (NWCENT PROX SENSOR OPEN) FOUND PRESENT.  NOSE WHEEL CENTERING	 PROXIMITY SENSOR REPLACED ACC AMM 32-61-06.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004101800061	20041018	00061		2004	10	18	CA040824005      	4	20040824	G	2312	6226152001	TRANSCEIVER     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	NR 1 COMMS	UNSERVICEABLE   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER CLEARING RUNWAY AND PROCEEDING WITH AFTER LANDING CHECKS COMM  NR 1 STARTED TO SMOKE.  CAPTAIN STOPPED THE A	IRCRAFT AND CALLED FROM ELECTRICAL SMOKE CHECKLIST.  LIST COMPLETED, THE AVIONICS WAS SHUT DOWN, AND THE SMOKE CEASED.  	COMM  NR 1 ISOLATED BY PULLING THE CIRCUIT BREAKER AND THE AVIONICS WAS RESTORED TO CONTACT ATC.   EMERGENCY VEHICLES ES	CORTED A/C TO GATE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2004101800062	20041018	00062	CE  	2004	10	18	CA040825001      	1	20040817	G	7120	04112816	BRACKET         			CESSNA	170   	170B        	2072306	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1A175	1A175DM     	GL  	ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CHANGED LT UPPER ENGINE RAIL BRACKET.  PN 0411281-6 REPLACED WITH NEW PART.  NEW HARDWARE USED.						1	H	7	1 	3O	3	O		A799    	E253	5	N	P857
2004101800063	20041018	00063	CE  	2004	10	18	CA040825002      	1	20040406	G	5551	07321014	BRACKET         			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											(CAN) REPAIRED HORIZONTAL STABILIZER.  AFT ATTACHMENT POINT REINFORCEMENT BRACKETS 0732101-4 AND 0732106 REPLACED WITH N	EW PARTS.  ADJACENT RIVETS REPLACED.   TAIL REASSEMBLED.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA
2004101800094	20041018	00094	CE  	2004	10	18	CA040825003      	1	20040506	G	5510	07321014	BRACKET         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL REMOVED TO CHANGE BROKEN BRACKETS.  PN 0712302-1 LT BRACKET AND 0732101-4 REINFORCEMENT REPLACED WITH NEW PAR	TS.  ADJACENT RIVETS REPLACED. TAIL REASSEMBLED AND DUAL INSPECTED.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2005012400034	20050124	00034	CE  	2005	1	24	CA040825004      	1	20040805	G	5520	051042	BRACKET         			CESSNA	170   	170B        	2072306	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A200	1A200DFA    	GL  	LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELEVATOR REMOVED TO CHANGE BRACKET.  CHANGED LT ELEVATOR BRACKET.  PN 051042 REPLACED WITH NEW PART.  ADJACENT RIV	ETS REPLACED.  REASSEMBLED AND DUAL INSPECTED.					1	H	7	1 	3O	3	O		A799    	1E10	5	N	P874
2005012400035	20050124	00035	NE  	2005	1	24	CA040825005      	2	20040824	G	7261		CAP             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					OIL FILTER	DEBONDED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						723					(CAN) WHEN (OIL) FILTER WAS RUN THROUGH THE BACK FLUSH MACHINE - ON THE FIRST CYCLE OF AIR AGITATION, THE FILTER SCREENS	 EXPANDED AND THE TOP BECAME DETACHED. THERE WAS NO SIGN OF EXCESSIVE CONTAMINATION NOR WAS THE MACHINE MALFUNCTIONING. 	ANOTHER FILTER WAS INSTALLED IN THE BACK FLUSH MACHINE AND OPERATED NORMALLY. IT APPEARED THAT THE BOND JOINT BETWEEN TH	E FILTER SCREENS AND THE FILTER CAP FAILED LEAVING NO ADHESIVE ON THE CAP. THE NEW FILTER INSTALLED IN THE ENGINE WAS CO	NSTRUCTED WITH A MACHINED CAP UNLIKE THE FAILED FILTER WHICH HAD A PRESSED ON CAP.		1	L	7	2 	4F	4	F		A22CE   	E1NE
2005020100025	20050201	00025	NE  	2005	2	1	CA040825006      	2	20040811	G	8550	177770	CASE            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	RT ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								P32623			(CAN) AFTER A DROP DURING FIRE BOMBING OPERATIONS, THE CAPTAIN AND FO PERFORMED ENGINE VISUAL CONDITION CHECK.  THE FO N	OTED A LARGE AMOUNT OF OIL LEAKING FROM THE RT ENGINE.  OIL TEMPERATURE, PRESSURE AND QUANTITY WERE CLOSELY MONITORED ON	 THE 20 MIN.   FLIGHT BACK TO THE MAINTENANCE BASE.  MAINTENANCE FOUND OIL LEAKING FROM AN INSERT ON THE FRONT NOSE CASE	.  THE NOSE CASE WAS REPLACED AND THE A/C RETURNED TO SERVICE.			2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871
2005041500026	20050415	00026	EA  	2005	4	15	CA040825007      	2	20040712	G	8520		CRANKSHAFT      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	OUT OF ADJUST   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA						1387815		1387815			(CAN) ON ENGINE RUNUP, AFTER ENGINE OVERHAUL, THE OIL PRESSURE WAS NOTED TO BE BELOW THE PRESCRIBED LIMIT.  ENGINE WAS D	ISASSEMBLED.  THE CRANKSHAFT MAIN JOURNALS WERE NOTED TO HAVE BEEN PREVIOUSLY GROUND TO .010.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2005041500027	20050415	00027	NE  	2005	4	15	CA040825008      	2	20040812	G	8500	R280079	ENGINE          			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	R280079     	52026	NE  	HAMSTD	23E	23E50       	NE  	RIGHT	FAILED          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								FP063306			(CAN) ON TAKEOFF ROLL THE RT ENGINE STARTED TO BACKFIRE AND LOOSE POWER, AT 90 KTS THE TAKEOFF WAS ABORTED MIXTURES TO I	DLE CUT OFF,THE LOAD WAS DUMPED. THE A/C WENT OFF THE END OF THE RUNWAY, AT 1000 FEET BEYOND THE RUNWAY THE A/C IMPACTED	 A DITCH. THE PILOT GOT OUT OF THE A/C AND WAITED FOR ASSISTANCE. THE A/C HAS BEEN DISMANTLED AND TRANSPORTED TO RED DEE	R,THE ENGINES ARE SCHEDULED FOR INVESTIGATION.			2	M	7	2 	4R	4	R		L34     	5E8	6	C	P603
2005041500028	20050415	00028	NM  	2005	4	15	CA040825009      	1	20040818	G	2761	66227741	CAP             	BOEING      		BOEING	737   	7372Q8      	138448K	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ACTUATOR	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA						1029					(CAN) AIRCRAFT TURN BACK DUE TO LOSS OF HYDRAULIC FLUID SYSTEN B IN FLIGHT. ON INSPECTION FOUND PLUG ON NR2 SPOILER ACTU	ATOR LEAKING.  REPLACED PLUG P/N 66-22774-1 IAW CMM OVH 27-60-41.  B SYSTEM CASE DRAIN FILTER TO B SYSTEM PRESS FILTERS 	CHECKED FOR CONTAMINATION.  NO CONTAMINATION FOUND.  FUNCTION CHECKED SPOILERS AND LEAKED CHECKED.  OK FOR SERVICE. CARR	IED OUT RII INSPECTION. OK.			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2005041500029	20050415	00029	NM  	2005	4	15	CA040825010      	1	20040821	G	2910	BACH8B04NN02	LINE            			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					HYDRAULIC SYS	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) HYDRAULIC QUANTITY INDICATOR SHOWED RAPID DEPLETION TO 1 GAL AFTER TAKEOFF. FOUND RUPTURED HYDRAULIC LINE P/N BACH	8B04NN0214T IN NOSE LANDING GEAR WHEEL WELL.LINE REPLACED IAW 20-10-52. ENGINE HYDRAULIC CASE DRAIN FILTERS CHECKED FOR 	METAL CONTAMINATION, NO CONTAMINATION FOUND. ENGINE RUN REQUIRED TO LEAK CHECK CASE DRAIN FILTERS AND CONFIRM PROPER HYD	RAULIC PUMP OPERATION. HYDRAULIC PUMP OPERATION NORMAL ON BOTH ENGINE DRIVEN PUMPS.			2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041500030	20050415	00030	NM  	2005	4	15	CA040825011      	1	20040824	G	5542		SKIN            	BOEING      		BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					RUDDER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						ZH5540001007					(CAN) DURING A B-CHECK, WALKAROUND FOUND LT SIDE OF THE RUDDER DELAMINATED. FURTHER INSPECTION FOUND DELAMINATION TO BE 	BEYOND LIMITS OF SRM 55-40-1 FIG 1,K. THE DELAMINATION IS CENTERED AT THE BAYAPPROX. RUDDER STATION 121. FERRY FLIGHT AU	THORIZED FROM XXX TO XXX WITH NO STOPS IAW THE RESTRICTIONS CONTAINED IN THE SPECIAL FLIGHT PERMIT, TO ACCOMPLISH PERMAN	ENT REPAIR PER SRM.			2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041500031	20050415	00031	EA  	2005	4	15	CA040825012      	2	20040825	G	7200		ENGINE          			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					LEFT	SHUTDOWN        	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			13780					PCE20891			(CAN) THE AIRCRAFT WAS ON THE TAKE OFF ROLE IN LUTSLE KE (SNOWDRIFT) TO FLY TO EKATI (YOA).  AT 80 KNOTS A LARGE DROP IN	 POWER WAS FELT ON THE LEFT SIDE WITH A YAW TOTHE LEFT.  THE TAKE OFF WAS REJECTED ANDTHE AIRCRAFT BROUGHT TO A STOP SAF	ELY ON THE RUNWAY. THE ENGINE WAS SHUT DOWN AT THAT TIME AS THE EGT WAS OBSERVED TO BE CLIMBING TO 1050. PRELIMINARY INV	ESTIGATIONS INDICATE AN INTERNAL FAILURE. MORE INFORMATION WILL BE ATTACHED AS WE HAVE IT.			1	L	7	2 	3T	3	T		3A20    	E4EA
2004101300029	20041013	00029	WP  	2004	10	13	CA040825013      	1	20040825	G	6510	369D25430	SHAFT           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) PILOT REPORTED THAT WHEN DESCENDING RAPIDLY, COLLECTIVE BOTTOMED OUT AND RT PEDAL INPUT, THE PEDALS WOULD VIBRATE 	AND THE AIRFRAME WOULD VIBRATE AND WITH A LITTLE COLLECTIVE INPUT AND LT PEDAL THE VIBRATION WOULD GO AWAY. THE SAME COU	LD BE INDUCED ON THE GROUND WITH RT PEDAL INPUT AND NR BEEPED TO MAX.  UPON INVESTIGATION OF TAIL ROTOR GEARBOX THE OUTP	UT SHAFT HAD BROKE OFF WHERE THE INNER RACE FOR THE ALIGNMENT ROLLER BEARING IS PRESSED ONTO THE IB END OF THE OUTPUT SH	AFT.		1	G	7	1 	3U	3	U		H3WE    	E4CE
2004101300084	20041013	00084	EU  	2004	10	13	CA040826001      	1	20040824	G	5311		FRAME           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27343								(CAN) DURING INSPECTION, AD 2001-21-04 WAS PERFORMED ON FUSELAGE FRAME STRIPS AT STA 3820 THRU STA 3870 AT THE AFT SIDE 	OF THE NLG BAY IAW NDTM PART 6 AND AD2001-21-04.   2 CRACKS WERE FOUND, RT 0.650 LONG AND LT 0.600 INCH LONG.					2	L	7	2 	4F	4	F	RT	        	E25NE
2004101300085	20041013	00085	NM  	2004	10	13	CA040827001      	1	20040826	G	5230		DOOR            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MAIN CARGO	OUT OF ADJUST   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE, CREW NOTICED THE MAIN CARGO DOOR UNSAFE LIGHT ILLUMINATED. IAW CHECKLIST, CREW DEPRESSURIZED AND DESCEN	DED INTO NEAREST AVAILABLE MAINTENANCE BASE. DOOR WAS VISUALLY INSPECTED AND A/C RETURNED TO SERVICE. UPON COMPLETION OF	 FINAL LEG, MAINTENANCE CHECKED AND ADJUSTED RIGGING OF DOOR SAFETY LOCK/SWITCHES.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2004101300086	20041013	00086	NM  	2004	10	13	CA040827002      	1	20040827	G	5620		WINDOW          			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CABIN	DISLODGED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AT TOP OF CLIMB, A LENGTH OF WINDOW SEALANT FROM THE R1 WINDOW BECAME DISLODGED AND BEGAN SLAPPING THE GLASS. CREW	 ELECTED TO RETURN,  WHERE THE WINDOW WAS INSPECTED AND LOOSE SEALANT REMOVED.  A/C RETURNED TO SERVICE AND WINDOW WAS R	ESEALED AT THE NEXT MAINTENANCE FACILITY.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2004101300087	20041013	00087	CE  	2004	10	13	CA040827003      	1	20040825	G	7120	05131323	RAIL            			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175*      	GL  	LT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14120								(CAN) THE LT UPPER ENGINE RAIL WAS FOUND TO BE CRACKED DURING SCHEDULED MAINTENANCE.  PN 0513132-3 WAS REPLACED WITH NEW	 PART.  NEW HARDWARE WAS INSTALLED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857
2004101500080	20041015	00080	NE  	2004	10	15	CA040827005      	2	20040823	G	7300		CONNECTOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL PILOT VALVE	MISINSTALLED    	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) DURING TAKE OFF, TOWER REPORTED VAPOR TRAILING FROM WING.  AC BACK FROM DEPARTURE.  APROX 2000 LBS OF FUEL LOST.  	MAINT FOUND AUTO FEED SYS IN FAULT, CAUSING FUEL FROM CENTER TANK TRANSFERRED TO WING.  A CONNECTOR AT REAR SPAR FOR PIL	OT VALVE FOUND NOT PROPERLY INSTALLED.  ALSO SUSPECT THAT POWER SWITCH AT FUEL CONTROL PANEL KEPT ENERGIZED WITH ACCESS 	PANEL CLOSED, (SWITCH SHOULD BE FLIPPED OFF BY A CAM AT ACCESS DOOR IF SWITCH NOT MANUALLY PUT OFF IN ORDER TO PREVENT F	UEL SPILLAGE FROM WINGS DURING TAKE OFF, IAW SL ).  THE SAME EVENT REOCCURRED ON AUG 27.  TAKE OFF WAS REJECTED. THE FUE	L CONTROL PANEL WAS REPLACED FOR TROUBLESHOOTING AND AS PRECAUTIONARY MEASURE, AUTO FUEL FEED SYSTEM WAS DEACTIVATED.	2	L	7	2 	4F	4	F	RT	        	E25NE
2004101500082	20041015	00082	SO  	2004	10	15	CA040827006      	1	20040709	G	5753	AN33A	BOLT            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLAP DEFECTOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A WALK AROUND INSPECTION ONE OF FOUR BOLTS FOR THE OB LT FLAP DEFECTER WAS FOUND TO HAVE BACKED OFF.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
2004101500083	20041015	00083	SO  	2004	10	15	CA040827008      	1	20040825	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYDRAULIC	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) THE PUMP FAILED OPERATIONAL CHECK, GEAR SELECT. HANDLE DID NOT RETURN TO NEUTRAL POSITION. PUMP WAS OVERHAULED REC	ENTLY, WAS IN SERVICE FOR 423.7 HRS.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004101500084	20041015	00084	NE  	2004	10	15	CA040829001      	2	20040827	G	7200		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1	MAKING METAL    	W				D				RETURN TO BLOCK         				Y	E		ENGINE STOPPAGE           	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA			37148	30728							(CAN) DURING ENGINE START, THE PILOT WAS UNABLE TO START THE NR 1 ENGINE.  A RUMBLING NOISE WAS HEARD FROM THE ENGINE AN	D IT WOULD NOT SPOOL GREATER THAN 16 PERCENT NH.  MAINTENANCE REPLACED THE STARTER GENERATOR WITH NO FIX.  FURTHER INVES	TIGATION REVEALED THE NR 1 ENGINE OIL TANK CHIP DETECTOR FLAGGED. THE CHIP DETECTOR AND OIL PUMP SCREEN WERE REMOVED AND	 CATEGORY 2 DEBRIS (LARGE FUZZ), AND CATEGORY 3 DEBRIS (LARGE CHIPS AND FLAKES) WERE DISCOVERED.  THE ENGINE WAS REMOVED	 FROM SERVICE AND RESULTS FROM TEAR DOWN REPORTS WILL BE SUBMITTED WHEN AVAILABLE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101500085	20041015	00085	EA  	2004	10	15	CA040829002      	1	20040826	G	2197	MS220735	WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PRSOV	BURNED          	W				O				OTHER                   				B	S		SMOKE/FUMES/ODORS/SPARKS  	AFFECT SYSTEMS            		DE	DESCENT        	1			CA											(CAN) IN DESCENT THROUGH 20-25, 000A STRONG TOXIC SMELL WAS PRESENT.  SIMULTANEOUSLY, NR 1 JET OVHT FAIL CAUTION MESSAGE	 APPEARED FOR 10 SECONDS AND DISAPPEARED.  ECS PAGE WAS SELECTED, IT WAS NOTICED THAT NR 1 PACK WAS NOT OPERATING.  NR 1	 PACK WAS SELECTED OFF AND SMELL DISSIPATED.  MAINT FOUND CIRCUIT BREAKER AT POSITION J1 ON PANEL CB1 BURNED (LT AIR CON	D UNIT).   CIRCUIT BREAKER WAS REPLACED BUT WOULD NOT RESET.  FURTHER INVESTIGATION REVEALED 4 DAMAGED WIRES AT LT ENGIN	E PYLON CLOSE TO THE NR 1 PRSOV TWO WIRES WERE CHAFFED, TWO WIRES WERE SHORTED OUT ON THE LT PRESSURE TRANSDUCER P2H6 AN	D P7H6 HARNESS, WIRES WERE REPAIRED.  AC WAS RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004101500086	20041015	00086	SO  	2004	10	15	CA040830001      	2	20040827	G	8530	646612	EXHAUST VALVE   			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								251443A48			(CAN) ENGINE PLACED ON (PISTON ENGINE ON CONDITION PROGRAM). DURING  ON-CONDITION 100 HOUR INSPECTION, THE NR 2 CYLINDER	 COMPRESSION TEST WAS LOW AND LEAKING FROM VALVES. ON FURTHER INSPECTION, EXHAUST VALVE STEM WAS FOUND TO BE ERODED TO A	BOUT HALF OF DIAMETER OF STEM. THE OTHER 3 CYLINDERS WERE INSPECTED AND FOUND EXHAUST VALVE STEMS TO BE ERODED AS WELL. 	OPERATOR OF THIS AIRCRAFT, HAS A STANDARD PRACTICE TO LEAN  THE AIRCRAFT DURING TAXI AND IN FLIGHT. THIS MAY HAVE LEAD T	O THIS FAULT FROM IMPROPER LEANING PROCEDURES FROM STUDENT PILOT'S.  INSTRUCTORS HAVE BEEN MADE AWARE OF PROPER LEANING 	PROCEDURES.  THE ENGINE WAS OPERATED 282.5 HOURS BEYOND TBO.  AIRCRAFT WAS REMOVED FROM SERVICE.	1	H	7	1 	3O	3	O		3A19    	E252
2004101500087	20041015	00087	SO  	2004	10	15	CA040830002      	1	20040826	G	1430		NUT             			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RT FWD TRUNNION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISCOVERED RT FWD TRUNION FITTING ATTACH BOLT ANCHOR NUT NOT RETAINING TORQUE DURING INSPECTION OF LANDING GEAR.  	LANDING GEAR REMOVED TO FACILITATE ANCHOR NUT REPLACEMENT.  ALL ANCHOR NUTS REPLACED ON BOTH MLG FWD FITTINGS.  ALSO FOU	ND HEAVY CORROSION ON INNER BORE OF LT AND RT RETAINER ASSEMBLIES (P/N 67502-00).  BOTH WERE REPLACED.				1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920
2004101500088	20041015	00088	GL  	2004	10	15	CA040830003      	2	20040816	G	7230		COMPRESSOR      			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	STALLED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT WAS EQUIPPED WITH A MIST ELIMINATOR THAT WAS REMOVED IN THE SPRING OF 2003.  WHAT REMAINED WAS THE WEATHE	R STRIPPING THAT SEALED THE MIST ELIMINATOR TO THE BACK OF THE PARTICLE SEPARATOR. THE WEATHER STRIPPING HAS A SELF ADHE	SIVE AND WAS ATTACHED TO THE BACK OF THE PARTICLE SEPARATOR.  ON A 26 DEGREE CELSIUS DAY, SEVERE COMPRESSOR STALL WAS EX	PERIENCED WHEN THE ENGINE INJESTED ABOUT A 1.5 METER LENGTH OF WEATHER STRIPPING. THE COMPRESSOR WAS GUMMED UP AND THE B	LEED VALVE SLOT WAS PLUGGED.		1	G	7	1 	3U	3	U		H3WE    	E4CE
2005020700004	20050207	00004		2005	2	7	CA040830004      	4	20040803	G	2350	7511001915	PANEL           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					AUDIO CONTROL	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) FRONT PANEL OF AUDIO CONTROL UNIT DOES NOT ILLUMINATE ON NIGHT SETTING.						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005012400032	20050124	00032	CE  	2005	1	24	CA040830005      	1	20040408	G	3320	M835369024	RELAY           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					CABIN LIGHTS	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) CABIN INDIRECT LIGHTING WOULD NOT SHUT OFF.  REPLACEMENT OF RELAY K162 RECTIFIED PROBLEM.						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005020100035	20050201	00035	CE  	2005	2	1	CA040830006      	1	20040709	G	3246	49330	PLUG            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					MAIN WHEEL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN WHEEL/TIRE ASSEMBLY LEAKING AIR 2-4 PSI PER DAY.  REPLACED THERMAL RELIEF PLUG ASSEMBLY. THIS IS THE SECOND P	LUG ASSEMBLY TO BE REPLACED ON THIS WHEEL (THERE ARE THREE PLUGS PER WHEEL ASSEMBLY).					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005041500032	20050415	00032	CE  	2005	4	15	CA040830007      	1	20040811	G	2130	471319X	VALVE           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					CABIN PRESSURE	FAILED          	W				O				OTHER                   				D	P		INFLIGHT SEPARATION       	NO WARNING INDICATION     		DE	DESCENT        	1			CA											(CAN) EMERGENCY PRESSURIZATION VALVE CAME ON UNCOMMANDED ONCE FOR SEVERAL SECONDS IN FLIGHT. VALVE WAS REPLACED.NOTE: MF	G REPORTS THIS IS A FLEET WIDE PROBLEM AND A NEW VALVE IS UNDERGOING CERTIFICATION.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005041500033	20050415	00033		2005	4	15	CA040830008      	4	20040713	G	3160		DISPLAY         	HONEYWELL   		CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RMU	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA						02113663					(CAN) DISPLAY SCREEN WENT INCREASINGLY BRIGHT.   BLUE AND THEN DIMMED TO GREEN.  REPLACED RADIO MANAGEMENT UNIT.   BEFOR	E COMPLETE FAILURE OF DISPLAY.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005041500034	20050415	00034	GL  	2005	4	15	CA040830009      	3	20040604	G	6114		SEAL            			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROPELLER HUB	LEAKING         	W				O				OTHER                   				W	K	E	INADEQUATE Q C            	FLUID LOSS                	VIBRATION/BUFFET          	CR	CRUISE         	1			CA								282942R			(CAN) IN CRUISE, PRIOR TO DESCENT, AUDIBLE AND INDICATED.  PROP SURGE AND RPM DECREASE OF APPROXIMATELY 200 RPM OCCURRED	. PROP PITCH WAS ADJUSTED TO FULL FINE POSITION.  NO RESPONSE TO BLADE CHANGE WAS NOTED.  DURING DESCENT PRIOR TO APPROA	CH, PROP SLOWLY INCREASED PITCH APPROXIMATELY 100 RPM. APPROACH WAS CONTINUED AND LANDING WAS COMPLETED SUCCESSFULLY. MA	INTENANCE INSPECTION REVEALED ENGINE OIL LEAKING FROM PROP GREASE FITTINGS.  AN INTERNAL HUB SEAL LEAK WAS DETERMINED AN	D CONFIRMED BY PROP OVERHAUL FACILITY.  PROP REMOVED.		1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P36EA
2005041500035	20050415	00035	SO  	2005	4	15	CA040830010      	2	20040812	G	8530	6524518	PUSHROD         			CESSNA	320   	320A        	2074506	CE  	CONT  	O470  	TSIO470B    	17026	SO  	HARTZL	HCA2V	HCA2VF2     	GL  	RT ENGINE	BROKEN          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	E		FLUID LOSS                	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT PARKED THE AIRCRAFT BECAUSE OF OIL LEAKING AND RT ENGINE RUNNING ROUGH. THE RT ENGINE NR4 CYLINDER WAS FOUND	 TO HAVE A BROKEN INTAKE PUSHROD,  BROKEN EXHAUST PUSHROD AND BROKEN PUSHROD TUBE THAT CAUSED OIL TO LEAK FROM ENGINE.  	IT WAS FOUND THAT BOTH PUSHROAD TUBES WERE SLIGHTLY DENTED CAUSING THE PUSHRODS TO RUB AND OVER TIME WEAKEN AND BREAK. W	HEN THE PUSHRODS BROKE THEY PUNCHED HO LES INTO THE PUSHROD TUBES AND OIL LEAKED OUT OF THE ENGINE.THE ENGINES ARE INSTA	LLED VERY CLOSE TO BOTTOM COWLINGS, BOTTOM COWLINGS ARE NOTREMOVABLE MAKING IT VERY DIFFICULT TO WORK WITH HAND TOOLS.		1	L	7	2 	3O	3	O		3A25    	3E3	5	C	P24EA
2005041500036	20050415	00036	EA  	2005	4	15	CA040830011      	1	20040806	G	2434	1381	GENERATOR       			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING PILOT NOTICED VOLTAGE READING WAS AT 0. GENERATOR WAS REPLACED ANDAIRCRAFT WAS RETURNED TO SERVICE.						1	H	7	1 	3R	3	R		A806    	5E1
2005041500037	20050415	00037	NE  	2005	4	15	CA040830012      	2	20040815	G	8520	27056	PISTON          			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN CARRYING OUT COMPRESSION TEST #3 CYLINDER WAS FOUND TO HAVE LOW COMPRESSION. #3 CYLINDER WAS REMOVED AND PIST	ON WAS FOUND CRACKED. SERVICEABLE PISTON AND CYLINDER WERE INSTALLED AND AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3R	3	R		A806    	5E1
2004111500084	20041115	00084	SO  	2004	11	15	CA040830013      	2	20040824	G	8520	654101A7R	CRANKCASE       			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								282615R			(CAN) CRANKCASE FAILURE (7TH STUD CRANKCASE) INSP WAS CARRIED OUT.  CYLS NR1, NR3 WERE REMOVED SO NR2, NR3 INTERMEDIATE 	BRG SADDLE COULD BE VIEWED.  MOVEMENT OF BRGS HAD OCCURRED, TEAR DOWN WOULD BE REQUIRED FOR FURTHER INVEST.  IT WAS FOUN	D THAT THERE WAS FRETTING OF CRANKCASE ON NR2, NR3 INTERM MAIN BRG THRU-BOLT PADS.  PINCH FIT IS LOST ON MAIN BRGS IN TH	ESE POSITIONS, BECOME LOOSE.  BRGS ON BOTH SIDES OF CRANKCASE WERE MOVING IN NR2, NR3 INTERM BRG POSITIONS. BRG IS ABLE 	TO MOVE BACK AND FORTH IN BRG SADDLE (NOT ROTATIONAL).  OPER WOULD HAVE ALLOWED INCREASED MOVEMENT OF BRG, BLOCKING OR R	ESTRICTING OIL FEED GALLERY IN SADDLE AND CAUSE OIL STARVATION. THIS WOULD LEAD TO CATASTROPHIC FAILURE.	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA
2004101300090	20041013	00090	SO  	2004	10	13	CA040830014      	1	20040824	G	2710	40599003	CONTROL ROD     			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13529								(CAN) ON INSPECTION, FOUND THE RT AILERON CONTROL ROD CRACKED ON THE OUTER THREADED PORTION OF THE ROD WHERE THE ROD END	 THREADS INTO THE ROD.  THE CRACK WAS APPROXIMATLEY 1 INCH IN LENGTH LONGITUDINALY WITH THE ROD.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004101300091	20041013	00091	NE  	2004	10	13	CA040830015      	2	20040808	G	7230		BLADE           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COMPRESSOR WHEEL	DAMAGED         	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN)  DURING TAKEOFF ROLL, CREW NOTED VIBRATION FROM NR 2 ENGINE, FOLLOWED BY ENGINE SURGE AND UNCOMMANDED POWER ROLL-B	ACK. THE NR 1 ENGINE WENT INTO APR MODE AND THE TAKEOFF WAS ABORTED.  BORESCOPE INSPECTION OF THE NR2 ENGINE COMPRESSOR 	REVEALED MOST BLADES BETWEEN 1ST AND 5TH STAGES TO BE DAMAGED, POSSIBLE BY FOD ALTHOUGH THIS HAS NOT BEEN ESTABLISHED.  	THE NR 2 ENGINE HAS BEEN REPLACED, THE FDR REMOVED FROM THE AC FOR ANALYSIS AND THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2004101300092	20041013	00092	EU  	2004	10	13	CA040831001      	1	20040823	G	3230	9740926112	RELAY           			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	POWER PACK	BURNED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) UPON APPROACH GEAR DOWN POSITION WAS SELECTED AND THE POWERPACK FAILED TO OPERATE THE MAIN GEAR EXTENDED FULLY AS 	DESIGNED AND THE NOSE GEAR FAILED TO GIVE A GREEN DOWN AND LOCKED POSITION INDICATION.  THE APPROACH WAS ABORTED AND A G	O AROUND WAS CARRIED OUT.  THE MANUAL GEAR EXTENSION PUMP WAS USED TO EXTEND THE NOSE GEAR WITH SUCCESS.  INSPECTION REV	EALED THE POWER PACK RELAY HAD FAILED TO MAKE CONTACT DUE TO EROSION OF THE CONTACTS.  A NEW UNIT WAS INSTALLED AND FUNC	TION TESTED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004101400006	20041014	00006	GL  	2004	10	14	CA040831002      	2	20040824	G	7397	23065805	WIRE HARNESS    			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FADEC	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			DE	DESCENT        	1			CA								CAE847044			(CAN) PRIOR TO FINAL APPROACH, FADEC FAIL WARNING HORN AND LIGHTS ACTIVATED. ENGINE AUTOMATICALLY REVERTED TO MANUAL MOD	E. PILOT SELECTED AUTO/MANUAL SWITCH TO SILENCE WARNING HORN, RETARDED THROTTLE TO PREVENT NP OVERSPEED. CONTINUED APPRO	ACH, LANDING IN MANUAL MODE WITHOUT INCIDENT.  ANALYSIS USING MAINT TERMINAL SOFTWARE INDICATED (AUTO/MANUAL SOLENOID FA	ULT) (AMSOLFIT).  TRACED DEFECT TO DEGRADED CIRCUIT CONTINUITY IN ENG HARNESS ASSY P/N 23065805. HARNESS WAS REPLACED P/	N 23072014. TEST USING MAINT TERMINAL SHOWED ALL FAULTS CLEARED. SATISFACTORY START, GROUND RUN, MANUAL MODE TEST, AUTOM	ATIC MODE SHUTDOWN AND FADEC INDICATION CHECK COMPLETED WITH NO ANOMALIES OR DEFECTS. AIRCRAFT RETURNED TO SERVICE.	1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2004101300093	20041013	00093	EA  	2004	10	13	CA040831003      	1	20040813	G	5521	C2TE29ND	RIB             			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22875								(CAN) DURING REGULAR 100 HOUR INSPECTION AD CF-80-25 COMPLETED AND CRACK FOUND ON LT ELEVATOR IB RIB AT ATTACHMENT BOLT.	  CRACK WAS LARGER AND MORE VISIBLE ON DOUBLER.  REMOVAL OF DOUBLER REVEALED CRACK ON RIB AS WELL.  RIB REPLACED AND DOU	BLER TOO.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
2004122900179	20041229	00179	EA  	2004	12	29	CA040831004      	1	20040817	G	2497		WIRE HARNESS    			NOORDN	UC64  	UC64AS      	6330208	EA  	PWA   	R1340 	S3H1        	52016	NE  	HAMSTD	3D	3D40        	NE  	ALTERNATOR	FAILED          	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA						0502232					THE AREA OF DIFFICULTY APPEARS TO HAVE ORIGINATED WITHIN A WIRE BUNDLE THAT SERVICES THE ALTERNATOR. THIS BUNDLE OF WIRE	S (4 WIRES OF AWG 20 SIZE EACH, APPROX 4 FT), RUNS FROM THE VOLT REG LOCATED ON THE UPPER LT SIDE OF THE FIREWALL, TO TH	E ALTERNATOR, WHICH IS LOCATED ON THE UPPER PORTION OF THE REAR CASE ON A P&W 1340 ENG. TO FURTHER DESCRIBE THE WIRE BUN	DLE, THE 4 WIRES WITHIN HAD BEEN LIGHTLY TWISTED TOGETHER AND THIS ASSY HAD BEEN PLACED WITHIN A SLEEVE/TUBING OF SHIELD	ING- GROUNDING BRAIDED WIRE. IT APPEARS VIBRATION HAD CAUSED SOME CHAFING TO OCCUR WITHIN THE BUNDLE AND , POWER WENT TO	 GROUND AND THE WIRES MELTED, CAUSING THE SMOKE AND ODOR.	1	L	7	1 	3R	3	R		A2578   	E143	6	C	A815
2004101300094	20041013	00094	EA  	2004	10	13	CA040831005      	2	20040819	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					POWER SECTION	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	D		ENGINE STOPPAGE           	INFLIGHT SEPARATION       		HO	HOVERING       	1			CA			10031					CPPS60404			(CAN) DURING HIGH HOVER (LONG LINE) TO PICK UP LOAD, NR1 POWER SECTION FAILED. INITIAL COMPRESSOR INLET INSPECTION (PLEN	UM AREA) REVEALED MOLTEN PARTICLES. FURTHER INVESTIGATION ON POWER SECTION REMOVAL/TEARDOWN INSPECTION.					1	G	7	1 	4U	4	U		H4SW    	E22EA
2004101300095	20041013	00095	WP  	2004	10	13	CA040831006      	1	20040829	G	5610	5912290506	WINDSHIELD      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, AIRCRAFT HAD TO TURNED BACK TO DEPARTURE DUE TO F/O WINDSHIELD CRACKED.  WINDSHIELD HAS BEEN REPLAC	ED AND THE WINDOW HEAT CONTROLLER WAS REPLACED AS PRECAUTIONARY.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101500081	20041015	00081	SO  	2004	10	15	CA040831008      	1	20040820	G	1430	AN546	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	DOWNLOCK	SEIZED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) WHEN THE PILOT SELECTED GEAR DOWN, THE RT GEAR LIGHT DID NOT ILLUMINATE.AFTER NUMEROUS RETRACTIONS AND EXTENSIONS 	NEAR THE AIRPORT, THE LIGHT NEVER CAME ON. AFTER LANDING THE RT DOWNLOCK HOOK WAS NOT COMPLETELY ENGAGED. WERE MOVED THE	 BOLT AND REPLACED WITH NEW AND LUBRICATED, CARRIED OUT RETRACTIONS AND EVERYTHING WAS SERVICEABLE.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004101800064	20041018	00064	EU  	2004	10	18	CA040831009      	1	20040831	G	3251	Z4242170001	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI A STUDENT PILOT NOTICED THAT THE AIRCRAFT WAS DIFFICULT TO STEER.  IT WAS ALSO NOTICED THAT THE RUDDER	 PEDALS FELT DIFFERENT.  MAINTENANCE WAS NOTIFIED AND IT WAS FOUND THAT THE RT STEERING SPRING WAS BROKEN.  THE SPRING W	AS REPLACED IAW THE MM WITH THE PROPER GAP BETWEEN THE SPRINGS.  THE STUDENTS WERE REMINDED OF THE PROPER TAXI TECHNIQUE	S WITH THE AIRCRAFT, STARTING THE ROLL BEFORE TURNING THE NOSE GEAR TO REDUCE STRESS ON THE SPRINGS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE
2004101800065	20041018	00065	NM  	2004	10	18	CA040831010      	1	20040830	G	5753		ATTACH BRACKET  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ACTUATOR	MISSING         	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING DELIVERY FLIGHT FROM THE AIRCRAFT MANUFACTURER, TECHNICAL LOG ENTRY FOR THIS AIRCRAFT STATED (FLAP POWER CA	UTION LIGHT ON) DURING TAXI IN WHEN FLAPS SELECTED ZERO.  FLAPS STOPPED AT ABOUT 8 DEGREES.  ON FURTHER INVESTIGATION OU	TER RT FLAP SEEN TO BE AT ABNORMAL ANGLE.  RT FLAP ACTUATOR NR 4 (PN C148661-2) WAS FOUND TO HAVE MIGRATED REARWARDS.  F	URTHER INVESTIGATION REVEALED THE ACTUATOR UPPER ATTACHMENT BRACKET IS MISSING.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2004101800066	20041018	00066	NE  	2004	10	18	CA040831011      	2	20040829	G	7230		FAN BLADE       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				C	E		F.O.D.                    	VIBRATION/BUFFET          		CR	CRUISE         	1			CA								P728045			(CAN) DURING CRUISE, NR 1 ENGINE HAD VIBRATION AND SURGE. AIRCRAFT LANDED BACK TO DEPARTURE AIRPORT WITH ENGINE RUNNING 	AT IDLE. FOUND SPINNER AND 3 FAN BLADES DAMAGED BY FOD.  THERE WAS NO TRACE OF BLUE ICE OR BIRD STRIKE. ENGINE HAS BEEN 	REPLACED.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004101800067	20041018	00067	EA  	2004	10	18	CA040831012      	2	20040618	G	8520	LW72877	TAPPET          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L1149739A			(CAN) HEAD OF CAM FOLLOWER (TAPPET BODY) CRACKED OFF AND FELL INTO SUMP. VALVE COULD NOT ACTIVATE, SO LOST POWER FROM TH	AT CYLINDER. ON ENGINE TEAR DOWN, 3 OTHER FOLLOWERS WERE FOUND PARTIALLY CRACKED OR PIECES MISSING.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2004101800068	20041018	00068	NM  	2004	10	18	CA040831013      	1	20040829	G	2910		LINE            			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYDRAULIC SYS	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) LOST (A) SYSTEM HYDRAULICS.  FOUND RT MLG UPLOCK HYDRAULIC LINE LEAKING AT ACTUATOR.  LINE REPLACED IAW AMM 32-32-	11 P/N BACH8A0LEE0260T.  RT MLG UPLOCK LINE PRESSURIZED AND LEAK CHECKED SERVICEABLE. NR 1,2 ENG PRESS FILTERS CHECK OK 	IAW MM 29-11-71 NR 1 ENG CASE DRAIN FILTER CHECKED OK NR 2 ENGINE CASE DRAIN FILTER FOUND CONTAMINATED. LINE FLUSHED IAW	 MM 29-11-0 FILTER REPLACED IAW 29-11-41. NR 2 ENGINE HYDRAULIC PUMP REPLACE IAW MM 29-11-31 PN ON/OFF 55098-08 S/N OFF 	101752A S/N ON 124354K8G HJKYZ.  NR 1, 2 ENGINE PRESSURE FILTERS AND CASE DRAIN FILTER LEAK CHECKED, NO LEAKS NOTED.  CA	SE DRAIN FILTERS REPLACED IAW MM 29-11-41 P/N ON 65-90305-12. NO LEAKS NOTED.	2	L	7	2 	4F	4	F		A16WE   	E2EA
2004101800069	20041018	00069	EU  	2004	10	18	CA040831014      	1	20040828	G	2797	9714231712	TERMINAL BLOCK  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AILERON TRIM SYS	SHORTED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) THE AILERON TRIM FUNCTIONED ONLY IN ONE DIRECTION.  THE TERMINAL BLOCK ON THE ELECTRIC CIRCUIT WAS FOUND BURNED (S	HORTED) AND WAS REPLACED.  AN OPERATIONAL TEST WAS CARRIED OUT OLD PART WAS REPLACED BY A NEW PART AND THE SYSTEM WAS FO	UND SATISFACTORY.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004101800122	20041018	00122	NE  	2004	10	18	CA040831015      	2	20040830	G	7200	CFM567B22	ENGINE          			BOEING	737   	737724      	13844BY	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					NR 2	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT RETURNED TO GATE.  NR 2 ENGINE FAULT 77-10852 (749.5) SENSOR OUT OF RANGE.  CARRIED OUT FIM TASK 77-21 TA	SK 802.  PERFORMED EEC TEST IAW 73-21-00-700-804-FO FAULT IS NOT ACTIVE, MEASURED 7.852 AT CONNECTOR DP0909. CLEANED CON	NECTORS DP0909 AND DP0913.  SYSTEM TESTS SERVICEABLE.  DMI CLEARED.  ENGINE NR 2 HAD FLASHING WHITE EGT BOX ON STARTUP. 	ABORTED ENGINE START.  FIM TASK 77-21 T. 801 CARRIED OUT.  LONGTIME EGT FAULT 77-10852 INDICATED. DEFERED TO MCC N/R TO 	BE RECTIFIED WITHIN 42.5 HOURS.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2005012400030	20050124	00030	EU  	2005	1	24	CA040831016      	1	20040830	G	3230	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LIGHT IN THE CAWS PANEL ILLUMINATED INDICATING TO THE PILOT A PROBLEM OF LAND GEAR.  PILOT LANDED AND AWAITED A FL	IGHT PERMIT TO ALLOW GEAR DOWN RETURN TO BASE.  AFTER INVESTIGATION, THE RELAY OF THE HYDRAULIC PUMP WAS FOUND INOPERATI	VE AND REPLACED.  A TEST OF RETRACTION /EXTENSION WAS CARRIED OUT AND FOUND SATISFACTORY.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005012400031	20050124	00031	CE  	2005	1	24	CA040831017      	1	20040828	G	5347	05112421	STOP            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SEAT TRACK	MISINSTALLED    	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE CREW REPORTED THAT THE PILOTS SEAT HAD FALLEN OFF THE RAILS WHEN ADJUSTED AFT.  THE TECHNICIAN INVESTIGATING T	HE REPORTED DEFECT NOTICED THAT THE AFT SEAT STOP WAS NOT INSTALLED IN ITS USUAL POSITION.  THE MOUNTING SCREW AND HALF 	OF THE STOP WERE LOCATED UNDER THE CARPET ADJACENT TO THE NORMAL INSTALLATION AREA.   THE STOP HAD APPARENTLY FRACTURED 	ACROSS THE THREADED SCREW MOUNTING HOLE PROBABLY FROM FREQUENT USE. THE STOP WAS REPLACED WITH A NEW PART AND NEW SCREW 	INTO THE AFT POSITION ON THE LT OB SEAT RAIL.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005020100044	20050201	00044	WP  	2005	2	1	CA040831018      	1	20040824	G	7603		CONTROL CABLE   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LT THROTTLE	KINKED          	W				K				NONE                    				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) FOLLOWING ONE FLIGHT, LT THROTTLE WAS VERY STICKY ON GROUND, NO PROBLEM IN FLIGHT.  MAINTENANCE FOUND THE REAR CAR	GO CEILING PANEL OBSTRUCTING THE LT ENGINE PUSH/PULL CABLE QUADRANT.  THE CEILING PANEL WAS KINKED BY LUGGAGE.  STILL UN	DER INVESTIGATION FOR THE PANEL/INSTALLATION CONFORMITY.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041500038	20050415	00038	EA  	2005	4	15	CA040831020      	2	20040830	G	8500		ENGINE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2476640A			MAINTENANCE WAS CONDUCTING A 50 HR INSPECTION AND EXCESSIVE METAL IN FILTER.  THE ENGINE WAS REMOVED FROM THE AIRCRAFT A	ND SENT TO AN OVERHAUL FACILITY.  THE ENGINE WAS TORN DOWN AND INTERNAL COMPONENTS REVEALED THAT THE MAIN BEARING HAD FA	ILED DUE A OVERSPEED CONDITION.  THE ENGINE DRIVETRAIN SHOWED HEAVY DAMAGE TO THE CRANKSHAFT.  THE A/C WILL NOW GO THROU	GH A SUSPECT OVERSPEED CONDITION.			1	G	7	1 	3O	3	O		H11NM   	E295
2005041500039	20050415	00039		2005	4	15	CA040831021      	4	20040830	G	3457	066040340204	GPS             			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTS GPS 60 DEGREES OFF TRACK.  T/S INDICATES CALIBRATION OF UNIT 60 DEGREES OUT.  RECALIBRATED.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005041500040	20050415	00040	EA  	2005	4	15	CA040831022      	2	20040825	G	8560		LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 1 ENGINE	UNSERVICEABLE   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								L8323			(CAN) CLIMB AFTER TAKE-OFF, CREW NOTED THAT THE NR 1 ENGINE LOST TURBO BOOST ABD THE AIRCRAFT YAWED TO THE LT. PILOT RET	URNED TO AIRPORT. FOUND MANIFOLD PRESSURE SENSE LINE FROM ENGINE INDUCTION TO DIFFERENTIAL PRESSURE CONTROLLER SHEARED O	FF ANDTHE SENSE LINE SENSING AMBIANT AIR PRESSURE AND NOT BOOSTED PRESSURE. LINE DAMA GED DUE TO HEAT STRESS NEAR EXHAUS	T SYSTEM. LINE REPLACED. NO FURTHER FAULTS.			1	L	7	2 	3O	3	O		A20SO   	E14EA
2005041500041	20050415	00041	SO  	2005	4	15	CA040901001      	1	20040818	G	3222	9572000	TUBE            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					NLG	OUT OF TOLERANCE	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) TUBE PURCHASED NEW. INSTALLED NEW. TEE SHOOTING AT VARIOUS REPAIR STATIONS DISCOVER CIRCLIP GROOVE TOO SMALL TO AC	COMODATE FULL CLIP SEATING.  (GROOVE UNDERSIZED)NEW TUBE PURCHASED AND REPLACED. NO FAULT TO DATE. INITIAL RECURRING FAU	LTS INC LUDED, LOSS OF FLUID, PRESSURE AND TOTAL COLLAPSE OF NOSE OLEO DURING DIFFERENT PHASES OF OPERATIONS.  REPAIRS I	NCLUDED REPLACEMENT OF CIRCLIP, N2 SERVICING, O-RING INSPECTION ETC.			1	L	7	2 	3O	3	O		A7SO    	E9CE
2005041500042	20050415	00042	SW  	2005	4	15	CA040901002      	1	20040820	G	6310	206040015103	DRIVE ASSY      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	DAMAGED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) TWICE WITHIN A 20 HOUR PERIOD,THE YELLOW TEMP INDICATERS CHANGED COLOUR, AND GREASE WAS LEAKING FROM THE FWD. END 	OF THE DRIVE SHAFT. THE SHAFT WAS REPLACED AND NO FURTHER PROBLEMS HAVE BEEN REPORTED.THE SPHERICAL COUPLING WAS REPLACE	D ON THE PROBLEM SHAFT,AND WAS INSTALLED ON ANOTHER HELICOPTER, WITHOUT AND REOCCURENCE.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2004101300039	20041013	00039	SW  	2004	10	13	CA040901003      	1	20040704	G	6210	204011250113	BLADE           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN ROTOR BLADE FOUND CRACKED ON THE TOP SURFACE 90 INCHES FROM THE TIP. ABOUT 70 HOURS BEFORE, A CRACK ON THE BL	ADE PAINT WAS FOUND, AT THAT TIME NO CRACK WAS FOUND IN THE BLADE SKIN.  IAW ASB204-49-96 PT I AND II, THE BLADE WAS INS	PECTED DAILY (PART I) AND EACH 25 HOURS (PART II).  8 FLIGHT HOURS BEFORE THE BLADE WAS FOUND SERVICEABLE WITH NO APPARE	NT CHANGE. THE PILOT REPORTED, FLEW IN TURBULENT CONDITIONS THAT DAY.  IN THE DAILY INSPECTION THE HAIRLINE CRACK ON THE	 PAINT WAS EXTENDED ALMOST ALL ACROSS THE BLADE.		1	G	7	1 	4U	4	U		H1SW    	E17EA
2004101300121	20041013	00121	NM  	2004	10	13	CA040901004      	1	20040830	G	2720	682015	SWITCH          			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	RUDDER TRIM	HUNG UP         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			31490								(CAN) DURING FLIGHT, CREW REPORTED HAVING A RUDDER TRIM ACTUATOR RUNAWAY CONDITION.  CREW FOLLOWED THE ABNORMAL PROCEDUR	ES CHECKLIST AND CONTINUED THE FLIGHT WITHOUT FURTHER INCIDENT.  MAINTENANCE FOUND THE RUDDER TRIM SWITCH TO BE HANGING 	UP WHEN SELECTED TOWARDS THE LT POSITION. SWITCH WAS REMOVED AND REPLACED.  SYSTEM WAS OPERATIONAL CHECKED.  ALL CHECKS 	GOOD.  AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101300122	20041013	00122	SW  	2004	10	13	CA040901005      	1	20040718	G	2424	15891F	VOLT REGULATOR  			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					ELECTRICAL	FAILED          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		TO	TAKEOFF        	1			CA											(CAN) VOLTAGE REGULATOR DELIVERING OVER 30 VOLTS. THE AIRCRAFT WAS READY TO TAKE OFF WHEN THE PILOT SMELLED A STRONG ODO	R IN THE COCKPIT. ASSUMING IT WAS THE BATTERY, HE SHUT DOWN THE ENGINE. IN THE INSPECTION THE BATTERY WAS FOUND TOO HOT 	AND THE VOLTAGE DELIVERED BY THE VOLTAGE REGULATOR WAS OVER 30 VOLTS.  THIS HIGH VOLTAGE MADE THE INVERTER NR 1 FAIL TO 	(WAS DELIVERING OVER 150 VOLTS).  WITH THIS HIGH VOLTAGE IN BOTH SYSTEMS (28VDC AND 115VAC) THE AUDIO BOX WAS BURNED OUT	, THE BATTERY HAD THE VOLTAGE BUT NOT THE CAPACITY AND THE RMI FAILED. NO CIRCUIT BREAKER STRIPPED AT THE TIME.		1	G	7	1 	4U	4	U		H1SW    	E17EA
2004121000054	20041210	00054	NE  	2004	12	10	CA040901006      	3	20040831	G	6111	SFA13M1R0AD	BLADE           			DHAV  	DHC8  	DHC8*       	       	NM  						HAMSTD	14SF	14SF7       	NE  	PROPELLER	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA									900946		(CAN)   BLADE RECEIVED FOR REPAIR OF FIBERGLASS DAMAGE ON THE OUTER SURFACE. DURING INITIAL INSPECTION, THE PLUG FOR THE	 BLADE TAPER BORE WAS REMOVED, FOUND THAT THE TAPER BORE WAS PRESSURIZED AS THE PLUG POPPED OUT WHEN RETAINING RING WAS 	REMOVED.  FOUND CORROSION BY PRODUCTS, AND CORROSION DAMAGE INSIDE OF THE TAPER BORE. PER CMM 61-13-02, REPAIR 5-5, ZONE	 4 IS ALLOWED 0.014 INCHES OF CORROSION DAMAGE DEPTH, THAT MUST BE REMOVED, THIS DEPTH WAS NOT MEASURED, BUT APPEARS TO 	EXCEED THE MAXIMUM DEPTH.		2	H	7	2 	4T			RT	A13NM   		6	C	P7NE
2004101300123	20041013	00123	EA  	2004	10	13	CA040901007      	2	20040719	G	8550	77517	SUMP            								LYC   	O540  	IO540L1A5   	41532	EA  					ENGINE	LEAKING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								L2954548A			(CAN) AT A RECEIVING INSPECTION OF A NEW, ZERO TIME ENGINE, NUMEROUS VOIDS IN THE CASTING WERE DISCOVERED ON THE ENGINE 	SUMP.  PORT SIDE NEAR PLUG AREA.  THE TWO BIGGER ONES HAD A DEPTH MEASUREMENT OF .110 AND .070 RESPECTIVELY. ENGINE MANU	FACTURER WAS CONTACTED AND IT WAS DETERMINED TO REPLACE THE SUMP PRIOR TO ENGINE BEING INSTALLED. A NEW SUMP WAS OBTAINE	D FROM THE MANUFACTURER AND INSTALLED IAW APPLICABLE MANUAL INSTRUCTIONS.  NOTE: THERE WAS NO VISUAL EVIDENCE OF CASTING	 VOIDS ON THE INTERNAL WALLS OF THE OIL SUMP CASE.							3	O			1E4
2004101300124	20041013	00124	SW  	2004	10	13	CA040901008      	1	20040929	G	5302	2050328193	PANEL           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION AME DISCOVERED A CRACK SURROUNDING ELEVATOR CONTROL SUPPORT (P/N 205-001-920-001) IN A F	WD AND AFT SKIN OF TAILBOOM  PANEL (205-032-819-3).  PANEL REPLACED, A/C RETURNED TO SERVICE.					1	G	7	1 	4U	4	U		H4SW    	E22EA
2004101300125	20041013	00125	CE  	2004	10	13	CA040901009      	1	20040916	G	2752	100384040	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER AIRCRAFT DEPARTURE, THE AIRCRAFT RETURNED DUE TO FLAP PROBLEMS. THE FLAP MOTOR WAS REPLACED AND THE 	AIRCRAFT WAS RETURNED TO SERVICE.					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC
2004101300126	20041013	00126	NE  	2004	10	13	CA040902001      	2	20040902	G	7250		TURBINE         			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					HPC	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								13266			(CAN) ENGINE WAS REMOVED DUE TO TURBINE AND HPC FAILURE. THIS ENGINE IS BEING ROUTED CANADA (MONTREAL) MFG FOR INVESTIGA	TION AND REPAIR. EVENT: 8/22/04, AIRCRAFT, NR 2 POSITION.  WHILE SPOOLING THE ENGINES UP FOR THE TAKOFF ROLL, A LOUD BAN	G WAS HEARD FROM THE REAR OF THE AIRCRAFT. AN AIRCRAFT BEHIND IMMEDIATELY REPORTED FLAMES COMING FROM NR 2 ENGINE TAILPI	PE. THE ENGINE WAS SHUTDOWN ON THE RUNWAY AND TAKEOFF ABORTED. MCD WAS CHECKED AND FOUND CLEAN.  THE N1 ROTOR WAS SPUN A	ND SPUN FREELY.  THE N2 ROTOR COULD NOT BE TURNED BY HAND CRANKING.  INSPECTION OF THE TAILPIPE REVEALED METAL PARTICLES	 AND DAMAGE TO LPT 3RD STAGE BLADES.	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN
2004101300127	20041013	00127	NM  	2004	10	13	CA040902002      	1	20040902	G	3230	656021132	ACCESSORY UNIT  			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					LANDING GEAR	FAILED          	W				J	A			DUMP FUEL               	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) UPON SELECTION OF GEAR UP, CREW NOTICED THE RT MLG INDICATION SHOWED BOTH (DOWN AND LOCKED) (GREEN LIGHT) AND (UNS	AFE) (RED LIGHT) AT THE SAME TIME.  FOLLOWING THEIR CHECKLIST, THE CREW DUMPED FUEL AND RETURNED TO BASE WHERE THE GEAR 	WAS INSPECTED, THE LANDING GEAR ACCY UNIT WAS REPLACED AND THE A/C RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2004101300128	20041013	00128	SW  	2004	10	13	CA040902003      	1	20040812	G	5302	206031403001	FITTING         	BELL        		BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						52149					(CAN) TAIL BOOM FITTINGS P/N 206-031-403-001 AND 206-032-409-001 LT SIDE TOP AND BOTTOM CRACKED.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL
2004101800106	20041018	00106	SO  	2004	10	18	CA040902004      	1	20040823	G	1430		BOLT            	PRESTOLITE  		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	STARTER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A164921					(CAN) STARTER, ALL BOLTS LOOSE AND TWO MISSING.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005030300146	20050303	00146	SO  	2005	3	3	CA040902005      	1	20040625	G	1430	AN522	BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	SCISSOR LINK	SHEARED         	W				A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			CA			16432								(CAN) BOLT SHEARED ON TAKEOFF. THIS IS BOLT FROM OTHER GEAR HAS SAME TOTAL TIME.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2005030300147	20050303	00147	NE  	2005	3	3	CA040902006      	2	20040827	G	7250		TURBINE BLADES  								PWA   	JD15  	JT15D1A     	 	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								76509			DISCOVERED HPT BLADE DAMAGE.  CONFIRMED HPT BLADES DAMAGED WITH 1 BLADE MISSING ENTIRE TIP SECT. GAS GEN DEFLECTOR SEG F	OUND MISSING SECTIONS & SIGNIFICANT NR OF RIVETS.  EXAM OF FRACTURED BLADE SHOWED HIGH STRESS RAPID YIELD FRACTURE WITH 	NO EVIDENCE OF FATIGUE. FRONT SECT OF BLADE  CONVEX SIDE (SUCTION SURFACE) ADJACENT TO FRACTURE BENT TOWARDS PRESSURE SU	RFACE AWAY FROM DIRECTION OF ROTATION AS WOULD OCCUR IF BLADE SUSTAINED A SIGNIFICANT IMPACT. BLADE NOT PRIMARY FAILURE 	& 2NDRY DAMAGE CAUSED FROM LIBERATED MATERIAL. MATERIAL  BECAME DISLODGED & ENTERED THROUGH COMBUSTION CHAMBER LINER & T	RAVELLED THROUGH GAS PATH CAUSING SEVERE HPT BLADE DAMAGE, AND MINOR IMPACT DAMAGE ON DOWNSTREAM COMPONENTS.						4	F			E25EA
2005030300148	20050303	00148	EU  	2005	3	3	CA040902007      	1	20040831	G	5523	1G3161	TRIM TAB        			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PREFLIGHT INSPECTION THE RT IB ELEVATOR TRIM TAB HINGE WAS FOUND TO BE LOOSE AND WOULD FLEX UNDER SIDE LOAD.  U	PON FURTHER INSPECTION IT WAS NOTICED THAT THE TRIM TAB SPAR WAS CRACKED ALONG THE LOWER EDGE BESIDE THE BOLTED ON HINGE	 POINT.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005030300150	20050303	00150	CE  	2005	3	3	CA040902009      	1	20040802	G	5610	1013840252	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ON DECENT, THE CREW HEARD A BANG AND THE PILOTS SIDE WINDSHIELD WAS CRACKED. THE CREW CONTINUED THE DECENT AND LAN	DED NORMALLY.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005030300151	20050303	00151	CE  	2005	3	3	CA040902010      	1	20040830	G	3221	B66	BEARING         	RAYTHN      		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CHAIN SPROCKET	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											WHEN MLG EXTENDED ON ARRIVAL, GEAR CAME OUT OF WW & STOPPED.  CREW EXTENDED MLG WITH THE EMERGENCY EXTENTION SYSTEM. CRE	W FOUND IT VERY HARD TO MOVE HANDLE FOR 1ST FEW STROKES. WERE ABLE TO KEEP GOING UNTIL 3 GREEN LIGHTS.  LANDED A/C NORMA	LLY.  A/C PUT ON JACKS & 60 AMP C/B UNDER FLOOR FOUND BLOWN.  C/B RESET & GEAR SELECTED UP.  GEAR WENT UP NORMALLY.  GEA	R SELECTED DOWN & GEAR MOVED SAME AMOUNT & STOPPED.  MLG MOTOR STILL TRYING TO MOVE GEAR, BUT FRICTION CLUTCH IN GEARBOX	 SLIPPING.  NLG CHAIN REMOVED IN ABLE TO SPLIT UP SYS FOR TROUBLESHOOTING. MLG FUNCTIONED NORMALLY.  NLG SYSTEM TALKEN A	PART & A BEARING IN 1 OF CHAIN SPROCKETS FOUND FAILED.  A NEW SPROCKET & BEARING INSTALLED & MLG FUNCTIONED NORMALLY.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005030300152	20050303	00152	CE  	2005	3	3	CA040902011      	1	20040901	G	5610	1013840252	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ON DECENT, THE CREW NOTICED A CRACK IN THE PILOTS WINDSHIELD. THE CREW CONTINUEDAND LANDED NORMALLY.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005041100210	20050411	00210	EA  	2005	4	11	CA040903003      	2	20040826	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			24535					86084			ENG REMOVED WHEN BETA CONTROL SYS JAMMED.  SEIZED BETA CONTROL LINKAGE RESULT OF HEAVY CONTACT WEAR BETWEEN THE REAR SEA	LING LAND OF BETA TRANSFER SLEEVE AND PROP SHAFT. A PREVIOUS SIMILAR FAILURE INVESTIGATION HAD CONCLUDED THAT FAILURE RE	LATED TO LACK OF LUBRICATION SO A CHECK MADE TO SEE IF ANY OIL SUPPLY ROUTES WERE BLOCKED.  AGAIN TWO SMALL HOLES IN PRO	P SHAFT THAT FEED CENTER PART OF BETA CONTROL SLEEVE WITH OIL WERE FOUND TO BE PLUGGED WITH SOME SOFT MATERIAL.								4	T			E4EA
2004101300129	20041013	00129	CE  	2004	10	13	CA040904001      	1	20040820	G	5551	12120031	DOUBLER         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	HS BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BULKHEAD DOUBLER REINFORCES THE HOLE WHERE THE HORIZONTAL STAB ATTACHES.  DOUBLER SPLIT IN TWO THROUGH ANCHOR 	NUT RIVET HOLE. THIS DOUBLER ONLY FOUND ON THE FIRST MODELS.  LATER MODELS HAD TWO DOUBLERS. OLDER MODELS HAVE THE SAME 	SINGLE DOUBLER INSTALLED.				1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P25EA
2004101300130	20041013	00130	CE  	2004	10	13	CA040907001      	1	20040901	G	5551	0432001646	RIB             			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	EMPENAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PART NUMBER 0432001-46 & 0432001-6 LEADING EDGE RIB ASSEMBLIES (FIGURE 18, ITEM 18 & 17 CESSNA PARTS MANUAL) ARE V	ERY DIFFICULT TO SEE. THE USE OF A MIRROR THROUGH THE HORIZONTAL SPAR AND RIB LIGHTNING HOLES IS THE ONLY WAY TO SEE THE	 CRACKS ALONG THE TABS. WE BELIEVE THE RIBS ARE CRACKING DUE TO IMPROPER GROUND HANDLING. THE PRACTICE OF PUSHING THE AI	RCRAFTS TAIL DOWN BY ITS SPAR IN ORDER TO ROTATE THE AIRCRAFT IN POSITION MAY BE DAMAGING THESE RIBS. BOTH RIBS WERE REP	LACED WITH NEW. THE TAIL SURFACES WERE REMOVED AND RE-INSTALLED.		1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2004101300131	20041013	00131	CE  	2004	10	13	CA040907002      	1	20040825	G	2421	X660007	ALTERNATOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE	DAMAGED         	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA											(CAN) ALTERNATOR CHARGING SYSTEM WOULD NOT COME ONLINE. TROUBLESHOOTING REVEALED THAT EVERYTHING SHOULD BE WORKING NORMA	LLY.  HOWEVER SYSTEM WOULD NOT CHARGE.  ALL VOLTAGES (IAW M.M.) APPEARED TO BE NORMAL BUT STILL THE CHARGING SYSTEM WAS 	SHOWING A DISCHARGE.  VOLTAGE WAS CHECKED AT THE OUTPUT SIDE OF THE ALTERNATOR CONTACTOR AND WAS FOUND TO BE NORMAL. HOW	EVER THERE WAS LITTLE TO KNOW CURRENT FLOW.   ASSUMED THAT THE CONTACTOR (INTERNALLY) HAD A BUILT UP LAYER OF CARBON FRO	M ARCHING.   REPLACED THE ALTERNATOR CONTACTOR X66-0007 AND THE SYSTEM BEGAN TO OPERATE WELL WITH-IN ITS OPERATING RANGE	. CHECKS OK.  WE ALLOWED THE AIRCRAFT TO FLY A FEW DAYS AND IT CONTINUED TO CHARGE NORMALLY.	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857
2004101300132	20041013	00132	EA  	2004	10	13	CA040907003      	1	20040906	G	7921	10750F	OIL COOLER      			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ENGINE	LEAKING         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			30284								(CAN) THICK WHITE SMOKE COMING FROM THE RT ENGINE BREATHER TUBE.  ENGINE OIL FOUND CONTAMINATED BY FUEL.  FUEL COOLED OI	L COOLER (PN 10750F SN 440) REPLACED IAW MM GROUND RUNS CARRIED NO AICRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004101300133	20041013	00133	EA  	2004	10	13	CA040907004      	1	20040906	G	7921	10750F	OIL COOLER      			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ENGINE	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			30284								(CAN) AFTER ENGINE START THICK WHITE SMOKE NOTICED COMING FROM THE ENGINE NR 2 BREATHER TUBE.  OIL FOUND CONTAMINATED WI	TH FUEL.  FUEL COOLED OIL COOLER (PN 10750F SN 440) REPLACED IAW MM AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004121000066	20041210	00066		2004	12	10	CA040907005      	4	20040907	G	3416	7000700647	ADC             			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE CO-PILOT ALTIMETER SHOWED A GRADUAL LOSS OF 60' - 80'COMPARED TO THE PILOT'S ALTIMETER. I	T REMAINED AT THE LOWER ALTITUDE FOR SEVERAL MINUTES BEFORE MATCHING UP WITH THE PILOT'S SIDE. THIS OCCURRED INTERMITTEN	TLY OVER SEVERAL MONTHS. BOTH AIR DATA COMPUTERS WERE REPLACED, ALTIMETERS EXCHANGED SIDE TO SIDE AND FULL OPERATIONAL T	ESTS AND LEAK TESTS OF BOTH PITOT-STATIC SYSTEMS WERE CARRIED OUT. NO FAULTS WERE FOUND AND THE PROBLEM REMAINED. WHEN T	HE FAULT WAS PRESENT ATC CONFIRMED THE DIFFERENCE BETWEEN THE SYSTEMS THROUGH TRANSPONDER ENCODER SELECTION. AFTER SEVER	AL CONTACTS WITH THE HONEYWELL ENGINEERING DEPARTMENT A TECHNICAL NEWSLETTER (A23-1980-04) CAME TO LIGHT WHICH PINPOINTE	2	L	7	3 	4F	4	F	RT	A46EU   	E6WE
2004101300134	20041013	00134	WP  	2004	10	13	CA040907006      	2	20040907	G	7261		ENGINE          			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  						LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING INSPECTION (OVERHAUL) OF ENGINES, OIL WAS SEEN DRIPPING FROM THE BREATHER VENT AFTER ENGINES SAT FOR 3-4	 DAYS. AT REQUEST OF OVERHAUL AGENCY AND THE MFG, A PROCEDURE WAS FOLLOWED TO ENSURE CORRECT OIL LEVELS IN ENGINES.  ENG	INES WERE FOUND TO BE SERVICED TO CORRECT LEVEL BUT PROBLEM PERSISTED.  THE OIL LOSS CAN BE SUBSTANTIAL (UP TO 500 ML. O	VERNIGHT IAW ENGINE) AND POSSIBLE PROBLEMS DUE TO THE FLOODING OF THE GEARBOX WITH OIL PRIOR TO ENGINE START, HAVE NOT B	EEN ASSESSED.   INFORMED BY THE MFG THAT AT LEAST 10 ENGINES HAVE SEEN PROBLEM BUT TO DATE NO COMMON THREAD HAS BEEN IDE	NTIFIED TYING THEM TOGETHER, IE. SAME REPAIR AGENCY, SAME DATE OF REPAIR, MOD STATUS.	2	L	7	3 	4F	4	F	RT	A46EU   	E6WE
2004101300135	20041013	00135	NM  	2004	10	13	CA040907007      	1	20040829	G	3411		PITOT TUBE      			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					PITOT STATIC SYS	CONTAMINATED    	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											(CAN) F/O'S AIRSPEED INDICATED 0 KNOTS DURING TAKEOFF ROLL.  UPON RETURN TO RAMP, MAINTENANCE INSPECTED F/O PITOT TUBE A	ND FOUND DEBRIS INSIDE.  LINE AND TUBE BLOWN OUT WITH DRY NITROGEN.  PITOT STATIC TESTS CARRIED IAW M/M.  AIRCRAFT DECLA	RED SERVICEABLE.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2004101800107	20041018	00107	EU  	2004	10	18	CA040908001      	1	20040904	G	1420		CONNECTOR       			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					POWER UNIT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, FLIGHT ATTENDANT HAS REPORTED SPARK COMING OUT OF THE FASTEN SEAT BELT/NO SMOKING SIGN AT ROW 31 D	EF.  AFTER INVESTIGATION, FOUND THE READING LIGHT POWER UNIT BURNED AT ROW 31 DEF.  POWER UNIT WAS DEACTIVATED AND REPLA	CED AT NEXT MAINTENANCE STATION. DURING INVESTIGATION, FOUND A LOT OF CONDENSATION IN THE CABIN CEILING ABOVE THE POWER 	UNIT. INSULATION WAS ALSO FOUND WET.  PROBLEM IS UNDER REVIEW WITH ENGINEERING AND MFG.			2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2005031100052	20050311	00052	EU  	2005	3	11	CA040908002      	1	20040903	G	6120	580500018	CONTROL UNIT    			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	LT PROPPELLER	FROZEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) LT CONDITION LEVER FROZEN, BECAME INOPERABLE AT ALTITUDE.						1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE
2005012400024	20050124	00024		2005	1	24	CA040908003      	4	20040907	G	3432		GLIDE SLOPE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	ERRATIC         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) RT GLIDESLOPE INDICATION VERY ERRATIC AND NO WARNING FLAP IN VIEW TELLING PILOT SIGNAL INVALID.  MEL'ED SYSTEM AND	 TROUBLESHOOTING IN PROGRESS.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005020100045	20050201	00045	EA  	2005	2	1	CA040908004      	2	20040903	G	8530	05K21108	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L91568A			(CAN) DURING CRUISE FLIGHT MANIFOLD PRESSURE DROP WAS NOTICED.  THROTTLE WAS INCREASED BUT PRESSURE WAS STILL DROPPING. 	 A VIBRATION WAS NOTICED IN THE ENGINE AND AIR FRAME.  THE ENGINE WAS SHUTDOWN AND SECURED AND A NORMAL LANDING CARRIED 	OUT.  NR ONE CYLINDER ON THE RT ENGINE WAS FOUND TO HAVE ALL THE STUDS BROKEN ON IT EXCEPT FOR THE THROUGH BOLTS.  THE C	YLINDER HAD PULLED SLIGHTLY AWAY FROM THE ENGINE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005031000088	20050310	00088	EA  	2005	3	10	CA040908005      	2	20040819	G	7250		TURBINE         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	D		ENGINE STOPPAGE           	INFLIGHT SEPARATION       		HO	HOVERING       	1			CA			10031								DURING HIGH HOVER (LONG LINE) TO PICK UP LOAD, NR 1 POWER SECTION FAILED.  INITIAL COMPRESSOR INLET INSPECTION (PLENUM A	REA) REVEALED MOLTEN PARTICLES.  FURTHER INVESTIGATION WILL COMMENCE ON POWER SECTIONREMOVAL/TEARDOWN INSPECTION. (ALTSN	-6421.0).				1	G	7	1 	4U	4	U		H4SW    	E22EA
2005041500229	20050415	00229		2005	4	15	CA040909004      	4	20040906	G	2200	3905300101	CONTROL UNIT    			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					NR 5 SPOILER	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE, NR 5 SPOILER EXTENDED MOMENTARY FOLLOWED BY  SPOILER 5FAULT ON ECAM.  SPOILER PANEL RETRACTED ON IT S O	WN. SPOILER RESET AFTER LANDING AND CHECKED OK.TROUBLING SHOOTING INDICATED NR 2 EFCU AT FAULT. NR 2 EFCU REPLACED AND D	FDR REMOVED AND SENT FOR READ OUT.  FLIGHT CREW CONFIRMED MOMENTARY ROLL OF THE AIRCRAFT.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2005041500230	20050415	00230	EU  	2005	4	15	CA040909005      	1	20040905	G	6220	350A37150802	PITCH LINK      			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					MAIN ROTOR HEAD	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT PILOT FELT SUDDEN VIBRATION IN THE M/R FLIGHT CONTROLS SYSTEM.  A/C LANDED AT FIRST SUITABLE 	SITE.  UPON INSPECTION, AME DISCOVERED THAT THE 'SCREW IN' RETAINING CUPS ON ONE OF THE M/R PITCH LINKS LOWER ROD ENDS D	ISINTEGRATED THUS ALLOWING THE BEARING INNER RACE TO SLIP OUT OF THE OUTER RACE.THE ANTI-ROTATION PINS IN ROD END WERE I	NTACT(REFER TO ATTACHED PHOTOS.  SOME DAMAGETOTHE ROTATING SWASHPLATE HORNS WAS ALSO SUSTAINED.THIS PARTICULAR P/N ROD E	 ND IS SUBJECT OF EUROCOPTER AS355 SB 05.19. IT HAS BEEN FURTHER DETERMINED THAT THE ANTI-ROTATION RIVET WAS NOT ENGAGED	 IN N EITHER THE OUTER RACE' NOR ROD END'STHREADS - THUS NO LOCKING ACTION.	1	G	7	2 	3U	3	U		H11EU   	E4CE
2004101300040	20041013	00040	NE  	2004	10	13	CA040909006      	1	20040611	G	6230	SB1562101	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					M/R SWASHPLATE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE 3 YEAR INSPECTION OF THE MAIN ROTOR SWASHPLATE DUPLEX BEARING AME DISCOVERED ONE OF THE BALLS TO BE	 SEVERELY SPALLED, BEARING WAS REPLACED AND A/C RETURNED TO SERVICE.  SUBSEQUENTLY THE OUTER RACE WAS CUT OPEN REVEALING	 NO OTHER DAMAGE TO EITHER THE INNER OR OUTER RACES.				1	G	7	2 	3U	3	U		H1NE    	E1GL
2005011100018	20050111	00018		2005	1	11	CA040909008      	4	20040828	G	3457	KLN90B	GPS             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	INTERMITTENT    	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) SECOND OCCURENCE OF GPS SCREEN MOMENTARILY GOING BLANK, THEN BACK ON NORMAL.GPS UNIT WAS REPLACED WITH SERVICEABLE	 UNIT.FUNCTION CHECKS NORMAL.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005012100162	20050121	00162	EU  	2005	1	21	CA040909009      	1	20040903	G	3242		PISTON          	PARKERHANFIN		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA						1028					(CAN) WHILE TOWING AIRCRAFT INTO HANGAR, FLUID WAS OBSERVED ON THE RT MAIN WHEEL TIRE.  INSPECTION REVEALED THE FLUID WA	S COMING FROM ONE OF THE BRAKE PISTONS. BRAKE ASSY WAS REPLACED.  NOTE: THERE WAS STILL 9MM OF THE WEAR INDICATOR SHOWIN	G.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005031100041	20050311	00041	EU  	2005	3	11	CA040909010      	1	20040908	G	3060	4E305110	BOOT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) PILOT REPORTED A PROP DEICE MALFUNCTION AS INDICATED ON THE CAWS PANEL.  ONE PROP BOOT WAS FOUND WITH AN OPEN CIRC	UIT.  BOOT REPLACED WITH NEW, RETURNED TO SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041500231	20050415	00231	EA  	2005	4	15	CA040910000      	2	20040908	G	7314	RG9080J4AM	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE FUEL	LEAKING         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT FOUND THAT FUEL PRESSURE IN CRUISE WAS FLUCTUATING AND AT IDLE THE FUEL PUMP DID NOT MAINTAIN RATED PRESSURE	.  DURING INSPECTION OF THE PUMP FOUND FUEL STAINS ON PRESSURE RELIEF VALVE, THE VALVE WAS LEAKING AT ITS FLANGE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005041500232	20050415	00232	CE  	2005	4	15	CA040910001      	1	20040909	G	3320	1015307641	FIXTURE         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN LIGHT	MELTED          	W				O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA											PLASTIC HOUSING OF THE LIGHT SHIELD P/N 101-530764-1 HAS MELTED DUE TO THE HEAT PRODUCED BY THE HIGH WATTAGE RESISTOR MO	UNTED ON THE LIGHT ASSY PRINTED CIRCUIT BOARD P/N PW2014. IT HAD MELTED ENOUGH TO DISFIGURE THE SHIELD AND PRODUCE AN EL	ONGATED HOLE THE LENGTH OF THE RESISTOR. APPROX 2 INCHES. THE PROBLEM WAS DISCOVERED ON THE REPLACEMENT OF THE FLOURESCE	NT BULB P/N 5108WW. THERE HAD BEEN NO REPORT OF A BURNING SMELL BY ANY OF THE VARIOUS AIRCREWS, WHO HAVE FLOWN THIS AIRC	RAFTI NSPECTION OF OTHER LIGHTS IN THE SAME AIRCRAFT AND ANOTHER SIMILAR AIRCRAFT REVEALS THAT THERE EXISTS A FLEETPROBL	EM.  RAYTHEON BEECH KINGAIR ENGINEERING HAS BEEN ADVISED OF THE PROBLEM.  REFERENCES:- IPC 33-20-00-01 PAGES 0 AND 1 ITE	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2005041500233	20050415	00233	SW  	2005	4	15	CA040910002      	1	20040824	G	2910	7012J220W234	HOSE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYD SYSTEM	BURST           	W				D				RETURN TO BLOCK         				K	F		FLUID LOSS                	FLT CONT AFFECTED         		TX	TAXI/GRND HDL  	1			CA											BEFORE FIRST FLIGHT DURING HYDRAULIC TESTING, PILOT SWITCHED 'OFF' NR 2 HYDRAULIC SYSTEM.  AFTER THE SYSTEM WAS SWITCHED	 BACK 'ON' PRESSURE INDICATION FELL OFF TOZERO.  A/C WAS SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED THAT THE BRAIDED NR 2	 HYDRAULIC HOSE FROM THE PUMP TO MIXING VALVE WAS BURST AT THE 45 DEGREE FITTING (SEE ATTACHED PHOTO).  HOSE REPLACED, A	/C RETURNED TO SERVICE.			1	G	7	1 	4U	4	U		H4SW    	E22EA
2005041500234	20050415	00234	EA  	2005	4	15	CA040910003      	2	20040908	G	8500		ENGINE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2599340A			(CAN) DURING AN SCHEDULED INSPECTION, THE OIL FILTER WAS LITTERED WITH METAL CONTAMINATION. THERE WAS EVIDENCE OF BRASS,	 ALUMINUM AND FERRIOUS METAL. THE ENGINE WAS REMOVED AND WILL BE SENT TO THE OVERHAUL SHOP FOR FURTHER INVESTIGATION. TH	E PISTON PIN PLUGS ARE A DEFINITE SUSPECT IN REGARDS TO THE BRASS FLAKES. ONCE THE ENGINE IS DISASSEMBLED, FURTHER REASO	NS FOR THE CONTAMINATION WILL BE AVAILABLE.			1	G	7	1 	3O	3	O		H11NM   	E295
2005041500235	20050415	00235	EU  	2005	4	15	CA040910004      	1	20040907	G	2750		CONTROL SYSTEM  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHILE RETRACTING FLAPS AFTER TAKEOFF , 'FLAPS' CAUTION ILLUMINATED , FLAP OPERATION STOPPED.AIRCRAFT RETURNED FOR 	LANDING , FLAP ASSYS INSPECTED FOR OBVIOUS DEFECTS , FLAPSMEASURED FOR POSSIBLE ASSYMETRY , SATISFACTORY.  GROUND RESET 	FUNCTIONED NORMAL .  AFTER RETURNING TO BASE , FLAP SYSTEM WAS FUNCTION TESTED , A ZERO SET WAS ALSO PERFORMED. NO ADDIT	IONAL FAULTS DETECTED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041500236	20050415	00236	NE  	2005	4	15	CA040910005      	2	20040910	G	7250		TURBINE BLADES  			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					NR 1 ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		TO	TAKEOFF        	1			CA			64195					655161			(CAN) AFTER TAKEOFF POWER WAS SET A LOUD BANG AND VIBRATION WAS EXPERIENCED FROM THE NR 1 ENGINE. TAKEOFF REJECTED. ENGI	NE SECURED AND AIRCRAFT RETURNED TO RAMP. VISUALINSPECTION UP TAILPIPE REVEALED ENGINE HAD FAILED INTERNALLY. TURBINE BL	ADES MISSING.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2004101300041	20041013	00041	EU  	2004	10	13	CA040910006      	1	20040827	G	2912	P1110	FILTER          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED INSPECTION AME ATTEMPTED TO REMOVE HYDRAULIC FILTER ELEMENT.  THE SREW IN PLUG PORTION SEPARATE	D FROM THE FILTER ELEMENT THAT REMAINED IN THE FILTER BOWL.  THE SYSTEM WAS FLUSHED, FILTER REPLACED AND A/C RETURNED TO	 SERVICE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004123000122	20041230	00122	EU  	2004	12	30	CA040910007      	1	20040827	G	7400		IGNITION UNIT   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UNCOMMANDED DISCHARGE OF ENG IGNITERS DURING ROUTINE 100 HR MX WHILE PERFORMING FUNCTION CHECK OF PROBES ELEMENTS, AN UN	COMMANDED DISCHARGE OF THE IGNITERS OCCURRED.  GROUND POWER WAS APPLIED AND ON, PROBES SWITCH TURNED ON AT PANEL FOR APP	X 30 SECS. BY PILOT IN COCKPIT WHILE MX CONDUCTED A WALK AROUND TO VERIFY PROBES ELEMENT HEAT.ONFINAL STAGE OF CHECK AT 	OR BEYOND TIME PROBES SWITCH SET TO OFF A D DISSIPATING DISCHARGE SOUND WAS HEARD FROM/AROUND THE ENG (APPX 5-6 FLASHES)	THEN STOPPED. THE ENG WAS COMPLETELY DE-COWLED. ENGINE MX PERFORMED EARLIER IN THE DAY, COMPLETE WITH A FUNCTION CHECK O	F THE IGNITERS. THEY WERE SECURELY INSTALLED AT THE TIME OF THE INCIDENT. THIS ANOMALY HAS OCCURRED 3 TIMES PREVIOUSLY.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041800001	20050418	00001	NM  	2005	4	18	CA040911001      	1	20040910	G	2400		ELECTRICAL SYS  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  		DAMAGED         	W				K				NONE                    				G	S		MULTIPLE FAILURE          	AFFECT SYSTEMS            		IN	INSP/MAINT     	1			CA											(CAN) WHILE AIRCRAFT PARKED ON APRON , UPON CREW ARRIVAL TO GET READY FOR DEPARTURE , THE CREW NOTICED SEVERAL CIRCUT BR	EAKERS WERE POPPED AND THE ATTEMPT TO RESET WAS NOT SUCCESFUL . MAINTENANCE SUSPECT THE FAULT TO BE WITH THE GROUND POWE	R UNIT WHICH WAS ATTACHED TO AIRCRAFT , HOWEVER THE FOLLOWING PARTS NEEDED TO BE REPLACED PIROR TO RETURN AIRCRAFT TO SE	RVICE 1- BOTH FUEL FLOW INDICATORS P/N SEL-OC8J 2- CABIN PRESSURE CONTROLLER P/N SET LOCH20F 3- FLIGHT. GUIDANCE CONTROL	LER  P/N 7003975-901		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031100090	20050311	00090	CE  	2005	3	11	CA040911002      	1	20040910	G	2752	A31691	ACTUATOR        			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAPS	BENT            	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) FLAPS STOPPED AT APPROACH POSITION AND COULD NOT BE LOWERED ANY FURTHER. SINCE AIRCRAFT WAS LANDING NO OTHER ACTIO	N WAS TAKEN WHILE IN FLIGHT.  ON GROUND IT WAS DETERMINED THAT FLAPS WOULD NOT LOWER OR RETRACT.  FURTHER INVESTIGATION 	DETERMINED THE FLAP ACTUATOR HAD INTERFERED WITH THE RT IB FLAP WHILE IT WAS BEING LOWERED. SINCE THE LIMIT SWITCHES ARE	 LOCATED ON THE IB RT FLAP THE FLAP MOTOR AND DYNAMIC FLAP RELAY OVERHEATED BEFORE THE CIRCUIT BREAKER TRIPPED.  THE FLA	P ACTUATOR WAS RETURNED TO ITS PROPER POSITION AND THE FLAP MOTOR AND FLAP RELAY WERE REPLACED WITH SERVICEABLE UNITS.		1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC
2005041800002	20050418	00002	EU  	2005	4	18	CA040913002      	1	20040901	G	7712		TORQUEMETER     			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RESULTS FROM A ROUTINE POWER CHECK ON ENGINE SHOWED A BAD TORQUE MARGIN.  OTHER PARAMETERS WERE CONSISTENT WIT	H PREVIOUS POWER CHECKS. TROUBLESHOOTING REVEALED A MISPLACED OR MISSING PIN ON TORQUEMETER REFERENCE SHAFT.  DURING TRO	UBLESHOOTING, WASHER WAS FOUND IN MODULE 01 SCAVANGE OIL STRAINER. ENGINE WAS REMOVED FROM AIRFRAME AND POWER SHAFT ASSY	 REPLACED.  UPON REMOVAL, ALTHOUGH NOT MISSING ANY PINS, IT WAS CONFIRMED THAT TORQUEMETER REFERENCE SHAFT HAD PLAY, THU	S GIVING ERRATIC TORQUE READING.  WASHER FOUND IN SCAVANGE OIL STRAINER WILL BE ANALYZED BY ENGINE MFR LABORATORY TO DET	ERMINE ITS ORIGIN.   ENGINE WAS REINSTALLED AND A POWER CHECK PERFORMED. ALL PARAMETERS WERE NORMAL.	1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005041800003	20050418	00003	CE  	2005	4	18	CA040913003      	1	20040911	G	2710	07606331	BLOCK           			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	AILERON CONTROL	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AILERON SYSTEM CONTROL TUBE ASSEMBLY FORWARD SHAFT P/N 1260141-6/10 WAS WORN 25-30% DUE TO A FAILED CORRODED SUPPO	RT BEARING P/N 0760633-1. SOME NEEDLES FROM THE BEARING ASSEMBLY WERE MISSING.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
2005032400022	20050324	00022	EA  	2005	3	24	CA040913004      	1	20040904	G	5510	F5131	HINGE           			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	TRIM HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A ROUTINE MX INSPECTION, CRACK WAS DISCOVERED ON THE STABILIZER TRIM HINGE ASSY, (PORT SIDE) P/N: F513-1.  TOTAL 	TIME ON AIRFRAME (AND PART) WAS 802 HOURS.  THE CRACK WAS LOCATED BETWEEN THE RADIUS OF THE HINGE ARM AND LIGHTENING HOL	E OF HINGE BODY.  REPLACEMENT PARTS WERE INSTALLED AS PER MANUF INSTRUCTIONS PRIOR TO NEXT FLT.  A/C MANUF HAS ISSUED S/	B SB-55-02  HORIZ STABILIZER HINGE MOD  FOR ALL MODELS FAC 2C1 A/C. THIS IS A 2-PART SERVICE BULLETIN. THE FIRST PART IS	 AN IMMEDIATE INSPECTION PRIOR TO NEXT FLT AND RE-INSPECTION EVERY 50 HOURS THEREAFTER UNTIL REPLACEMENT OF HINGES.  THE	 SECOND PART OF THE SB IS IMMEDIATE REPLACEMENT OF HINGES IF CRACKS ARE DISCOVERED OR MANDATORY REPLACEMENT ON OR BEFORE	1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA
2005032400023	20050324	00023	NE  	2005	3	24	CA040913005      	2	20040901	G	8530	399353	CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ENGINE	SEPARATED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											CYLINDER HEAD CRACKED 360 DEGREES WHILE AIRCRAFT WAS IN CRUISE FLIGHT.  AIRCRAFT WAS ABLE TO MAKE IT BACK TO BASE.  CYLI	NDER WAS CHANGED BY KOBY'S AIRCRAFT.  IT WAS THEN GROUND RUN AND FOUND TO BE SERVICEABLE AND RETURNED TO SERVICE.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
2005041800004	20050418	00004	EU  	2005	4	18	CA040913006      	1	20040830	G	2750	U2801	STARTER UNIT    			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AFTER LANDING, THE CREW WAS ABLE TO RETRACT FLAPS BEYOND 22 DEGREES. THE AIRCRAFT WAS MOVED TO XXX FOR FERRY PERMI	T. MAINTENANCE REPLACED THE FLAP STARTER UNIT AND THE AIRCRAFT WAS RETURNED TO SERVICE					2	L	7	2 	3T	4	T		A24EU   	A196
2004101300042	20041013	00042	NM  	2004	10	13	CA040913007      	1	20040905	G	2782		BEARING         			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					SLAT ACTUATOR	SEPARATED       	W				J	A			DUMP FUEL               	UNSCHED LANDING         			F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA						DA4735					(CAN) DURING DEPARTURE, THE CREW OBSERVED A CONTINUOUS SLAT PROBLEM INDICATION. THE AIRCRAFT RETURNED TO POINT OF DEPART	URE.  MAINTENANCE FOUND THE NR 5 SLAT ROD END BEARING SEPARATED FROM THE PISTON, AND THE SLAT DAMAGED BY THE PISTON. THE	 ACTUATOR AND SLAT ASSYS WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ATTACH POINT OF THE ROD END BEARING TO 	THE PISTON ON THIS UNIT WAS ENCLOSED IN SHRINK SLEEVE AND THE CONDITION WAS NOT READILY EVIDENT. A FLEET INSPECTION HAS 	BEEN INITIATED.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2004101800142	20041018	00142	EA  	2004	10	18	CA040913008      	2	20040910	G	8530	LW16740	VALVE           	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A CYLINDER CHANGE ON THE ENGINE THE EXHAUST RISERS WERE REMOVED TO ALLOW FOR INSTALLATION.  WHILE CHECKING 	THE EXHAUST PORTS FOR FOD IT WAS NOTICED THAT THERE WAS ABNORMAL WEAR ON THE NR 3 EXHAUST VALVE JUST ABOVE THE MUSHROOM.	  FURTHER INSPECTION FOUND THAT THE EXHAUST VALVE ON THE NR 6 CYLINDER HAD THE SAME PROBLEM.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005020100047	20050201	00047	NE  	2005	2	1	CA040914001      	2	20040914	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								12367			(CAN) AIRCRAFT EXPERIENCED AN UNCOMMANDED IN-FLIGHT SHUTDOWN OF THE NR 2 ENGINE, UNEVENTFUL SINGLE ENGINE LANDING WAS PE	RFORMED.  MECHANICS FOUND PLENTY OF CHIPS IN THE OIL COOLER AND AT THE POWER TURBINE.  POWER TURBINE AND LPC 1 IS JAMMED	 WHILE THE PROPELLER CAN STILL BEING TURNED (WITH A SQUEAKING NOISE) SEEMS THE POWER TURBINE SHAFT IS FRACTURED, MAYBE D	UE TO A BLOWN BEARING.  THE OVERHAULED ENGINE WAS INSTALLED ON 11.OCT 2001.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800005	20050418	00005		2005	4	18	CA040914002      	4	20040806	G	2562	BS2173	BATTERY PACK    	DORNEMARGLN 	ELT81       															ELT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						23160E					(CAN) UPON YEARLY INSPECTION, BATTERY PACK REFERENCED ABOVE WAS FOUND TO BE LEAKING ON MAIN CIRCUIT BOARD CAUSING THE BO	ARD TO SHORT CIRCUIT AND MALFUNCTION. NOTE TH AT THIS WAS A PASSIVE FAILURE AND THAT THE ELT WAS NOT TRANSMITTING UNCOMM	ANDED. PREVIOUS CERTIFICATION ON AUGUST 5, 2003 REFERENCE.
2005032400025	20050324	00025	NE  	2005	3	24	CA040914003      	2	20040903	G	7314	P94C16612	PUMP            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENGINE	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											DURING START SEQUENCE, ELECTRIC BOOST PUMP TRIPPPED CIRCUIT (3A) BREAKER.  PUMP REPLACED.AF FUEL SYSTEM FILTER CONTAINED	 APPROXIMATELY 10 SMALL, NON-FERROUS, METAL SLIVERS.  PRESUMED TO BE ALUMINUM. (PRIOR START PUMP CHANGED DUE TO NON-FERR	OUS METAL GENERATION.)				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2005032400026	20050324	00026	EU  	2005	3	24	CA040914004      	1	20040910	G	2421	B3508	GENERATOR       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	PORT SIDE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											PORT GENERATOR WON'T COME ON LINE.  PORT GENERATOR REPLACED S/N OFF 1878.  GROUND RUN CHECK SERVICEABLE.						2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005041800006	20050418	00006	EU  	2005	4	18	CA040914005      	1	20040908	G	5610	C561S1101202	WINDSHIELD      			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					COCKPIT	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WINDOW LT UPPER PN C561S3101202, DEBONDING 11.						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2005041800007	20050418	00007	NE  	2005	4	18	CA040914006      	2	20040831	G	7200		ENGINE          								PWA   	JT15  	JT15D4      	52112	NE  						FAILED          	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			CA								70884			(CAN) ENGINE WAS REMOVED FROM THE WING AFTER REPORTED HIGH VIBRATIONS.  ENGINE SUFFERED AN IMPELLER FAILURE CAUSING SECO	NDARY DAMAGE TO DOWNSTREAM COMPONENTS. WITH THE MISSING MATERIAL FROM THE IMPELLER AND THE DAMAGE FOUND THE HIGH TURBINE	 BLADES, HIGH ROTOR BALANCE WOULD BE ADVERSELY AFFECTED AND THIS WAS LIKELY THE CAUSE OF THE HIGH VIBRATIONS.THE IMPELLE	R INSTALLED IN THIS ENGINE WAS P/N 3028345, PRE SB 7187. THESE IMPELLERS ARE PRONE TO FAILURE SIMILAR TO THE FAILURE ON 	THIS ENGINE. NO DAMAGE UP STREAM OF THE IMPELLER WAS FOUND TO INDICATE FOD DAMAGE.THE ENGINE WILL REQUIRE HPT BLADE AND 	IMPELLER REPLACEMENT, AND WILL UNDERGO A HSI TO DETERMINE WHICH COMPONENTS MAY BE RE-INSTALLED, REPLACED OR REPA IRED PR						4	F			E1NE
2004101300043	20041013	00043	EU  	2004	10	13	CA040914007      	1	20040913	G	3210		LANDING GEAR    			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  						OUT OF POSITION 	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) MAIN GEAR UNSAFE APPEARED ON MFDS AFTER GEAR RETRACTION.  AIRCRAFT LANDED BACK TO DEPARTURE AIRPORT.  MAINTENANCE 	FOUND THE LANDING HYDRAULIC TEST VALVE LT IN (GROUND ONLY) POSITION.  THE VALVE WAS LEFT IN THAT POSITION FOLLOWING A GE	AR RETRACTION/EXTENSION TEST AND WAS OMITTED TO BE RE-POSITIONED TO NORMAL.  THE (GROUND ONLY) POSITION RESTRICTS THE HY	DRAULIC FLOW FOR A SAFE GROUND OPERATION.			2	L	7	2 	4F	4	F	RT	        	E25NE
2004101800136	20041018	00136	GL  	2004	10	18	CA040914008      	3	20040908	G	6114		FLANGE          			CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									G7462		(CAN) PROPELLER REMOVED FOR CORROSION INSPECTION UNDER CAR 625, APPENDIX C, PARA 5.  MOUNTING FLANGE CORRODED BEYOND REP	AIR.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2004102000195	20041020	00195	NE  	2004	10	20	CA040914009      	1	20040910	G	6520	7665005801112	SERVO           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					TAIL ROTOR	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AIRCRAFT IS CURRENTLY ON THAI REGISTRY BUT WE HAVE SUBMITTED THIS SDR AS THIS IS THE SECOND OCCURRENCE OF THIS TYP	E IN THE PAST 2 YEARS.   A/C RETURNED TO BASE REPORTING HYDRAULIC SYSTEM LIGHT.  INVESTIGATION REVEALED TGB  (OVERFILLED	) IT WAS CONCLUDED THAT TAIL ROTOR SERVO HAD MASSIVE INTERNAL LEAK THAT CONSEQUENTLY FILLED UP TGB.  TAIL ROTOR SERVO WA	S REPLACED.  QUICK RIGGING CHECK WAS CARRIED OUT AIRCRAFT WAS TEST FLOWN SATISFACTORY AND RETURNED TO SERVICE.			1	G	7	2 	3U	3	U		H1NE    	E1GL
2004101800137	20041018	00137	EA  	2004	10	18	CA040915001      	1	20040913	G	2720	SDBA6709340001	LIMITER         			CNDAIR	CL600 	CL6002C10   	1390015	EA  										RUDDER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA							10166				(CAN) RUDDER LIMITER CAUTION MESSAGE POSTED IN FLIGHT WITH FLAP AT 1220 KNOTS WHILE CONDUCTING RUDDER LIMITER CHECK IAW 	MANUFACTURING FUNCTIONAL TEST PROCEDURE, RTL REDUCED TO .1250 BEFORE OPENING FULLY.					2	L	7	2 	4F			RT	A21EA
2005041800008	20050418	00008	EU  	2005	4	18	CA040915002      	1	20040910	G	1430	HL720PN1630	LOCK BOLT       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RT WING	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			39581	39581							(CAN) DURING REPAIR OF RIGHT WING FUEL LEAK, THE HEAD OF THE LOWER HYLOCK BOLT ATFUSELAGE TO WING ATTACHMENT ASSEMBLY AT	 STATION 29 WAS DISLODGED BY A PLASTIC P RC SCRAPER (REF IPC 53-30-01-15 PAGE 0 ITEM 75).FURTHER INVESTIGATION FOUND THE	 HEAD OF THE BOLT SEPARATED FROM THE SHANK DUE TOSEVERE CORROSION, AND THE BOLT HOLE PITTED. THE BOLT HOLE WAS CLEANED O	UT, NDTINSPECTED, AND A NEW FASTENER INSTALLED PER SRM 51-45-00 WITH NO FURTHER FAULTS.			2	H	7	4 	4F	4	F		A49EU   	E6NE
2005041800009	20050418	00009		2005	4	18	CA040915003      	4	20040914	G	3418	9754421421	SENSOR          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AOA VANE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) VANE/WING HEATING SECTION HAD FAILED, AOA VANE ASSEMBLY REPLACED WITH NEW						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041800010	20050418	00010	NM  	2005	4	18	CA040915004      	1	20040911	G	2913	570717570729	COUPLER         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYD PUMP	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA						MX425297D					(CAN) THE CREW OF OVERSHOT RUNWAY DUE TO AN UNSPECIFIED PROBLEM. THE CREW ADVISED THATERS WAS NOT REQUIRED AND LANDED 20	 MINUTES LATER WITHOUT INCIDENT. NO OPERATION AL IMPACT. ENTRY FROM MAINTENANCE OPS SUMMARY  DURING GEAR EXTENSION CREW 	REPORTED THEY HAD A YELLOW GEAR DOOR LIGHT AND PRESSURE DROPPED TO ZERO. CREW ELECTED TO CARRY OUT ALTERNATE GEAR EXTENS	ION AND NOTICED NR 2 EDP CAUTION LIGHT ILLUMINATED J/L NR 2 DEFECT 414058  LANDING GEAR WOULD NOT EXTEND NORMALLY AMBER 	DOOR LIGHTS AND A LOUD GRINDING NOISE. NO NR 2 STANDBY OR MAIN PRESS. COMPLETED EMERG. CHKLIST & ALT GEAR EXT.RECTIFICAT	ION  REPLACED NR 2 ENGINE DRIVEN HYD PUMP DUETO SHAFT SPLINE WEAR. A/C GRD RAN, HYDRAULICS FUNCTIONED & LEAK CHECKED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800011	20050418	00011	NE  	2005	4	18	CA040915005      	2	20040915	G	8530	399359	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								6447			(CAN) CYLINDER EXHAUST VALVE EAR BROKEN OFF. CRACK INITIATED FROM THE ROCKER SHAFT BUSHING AREA AND CRACKED AROUND TO OP	POSITE SIDE. COMPLETE TOP CAME OFF FROM BUSHING TO BUSHING.					1	H	7	1 	3R	3	R		A815    	5E2
2005041800012	20050418	00012	CE  	2005	4	18	CA040915006      	1	20040910	G	2752	505212223	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH FOR A MX CHECK, FLAPS WERE EXTENDED IAW CHECKLIST.  A RUDDER CORRECTION REQUIRED TO KEEP ACRFT ON APPR	OPRIATE TRACK. AN UNEVENTFUL LANDING COMPLETED AND ACRFT SNAGGED. UPON INSPECTION IT WAS DETERMINED THAT THE FLAP ACTUAT	OR FOR THE LT, I/B FLAP HAD FAILED IN THE DRIVE AREA. IT WAS DETERMINED THAT THE 90 DEGREE DRIVE IN THE ACTUATOR HAD FAI	LED AND INPUT TO THE ACTUATOR WAS TURNING BUT IT WAS NOT DRIVING THE ACTUATOR DOWN. AS A RESULT, THERE WAS AN ASYMETRIC 	FLAP CONDITION ON LANDING REQUIRING THE RUDDER CORRECTION. IT SHOULD BE NOTED THAT THERE IS NO INDICATION OR OTHER SYSTE	M TO SHOW AN ASYMETRIC FLAP SITUATION OR TO STOP THE FLAPS FROM EXTENDING BEYOND A CERTAIN POINT IN THE AIRCRAFT.	1	L	7	2 	3T	4	T		A14CE   	E4EA
2005041800013	20050418	00013	EA  	2005	4	18	CA040915007      	1	20040806	G	2140	576	EXHAUST STACK   	DHAV        		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CABIN HEATER	BULGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   UNIT IS CALLED A COFFEE CAN TYPE CABIN HEATER, CRACK ONLY VISIBLE WHEN THE UNIT WAS REMOVED FROM THE AIRCRAFT EX	HAUST SYSTEM (C2EE249). THE DEFECT WAS NOTED DIRECTLY BEHIND THE TRIANGULAR AIR DEFLECTOR AT THE AIR INLET TO THE CABIN 	HEATER. THE CRACK WAS NOT VISIBLE WHILE THE EXTERNAL HEAT SHROUD WAS REMOVED FOR INSPECTION (CF-90-03-R2). RECOMMEND A D	ETAILED INTERNAL INSPECTION OF THE EXHAUST STACK FOR FUTURE INSPECTIONS OF THIS STYLE OF DHC2 CABIN HEATER.			1	H	7	1 	3R	3	R		A806    	5E1
2004101300044	20041013	00044	CE  	2004	10	13	CA040915008      	1	20040430	G	3246	16449	STRAP           			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	FLOAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1113					(CAN) SLIGHT BULGE WAS NOTED ON EDGE OF STRAP (PN 16449) EXTERIOR OF FLOAT SKIN.  FURTHER INVESTIGATION INVOLVED REMOVIN	G STRAP ASSY FROM FLOAT SKIN, INVESTIGATION REVEALED EXTENSIVE CORROSION, TO POINT THAT FLOAT HULL SKIN WAS SEVERELY DEF	ORMED(BEING PUSHED INWARD FROM CORROSION PROCESS HAPPENING UNDER STRAP).  VERY FEW VISUAL CLUES WERE PRESENT ON EXTERIOR	 OF FLOAT.  ONLY WAY POSITIVE ID WAS PREFORMED WAS TO REMOVE SPREADER BARS FROM FLOATS AND CONDUCT DETAILED VISUAL INSP 	ON UNDER SIDE OF STRAP ATTACHING POINTS.  RECOMMEND THIS DETAILED INSP AT TIME OF MAJOR OVERHAUL.  NOTE: THIS SET OF FLO	ATS HAD OPERATED FOR MOST OF THEIR LIFE IN FRESH WATER ENVIRONMENT, FOR LAST 8 YEARS HAVE BEEN OPERATED IN SALTWATER.	1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2004101800133	20041018	00133	EA  	2004	10	18	CA040915009      	1	20040826	G	5521		GUSSET          	DHAV        		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						SA397LH					(CAN) LT TOP ELEVATOR TIP GUSSET (LOCATED BETWEEN ELEVATOR TIP SKIN AND ELEVATOR SPAR) WAS FOUND CRACKED DURING INSPECTI	ON.  NOTE: THE PROPELLER WAS REMOVED AND OVERHAULED,  AFTER 30.0 HRS SMOH,THE PROPELLER WAS REMOVED FOR REBALANCING DUE 	TO VIBRATION ISSUES.  THIS WAS A MAJOR CONTRIBUTING FACTOR IN THIS INCIDENT.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
2004101800134	20041018	00134	CE  	2004	10	18	CA040915010      	1	20040902	G	7120		TUBE            	CESSNA      		CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT LT LONGITUDINAL TUBE CRACKED AND DEFORMED AT THE REAR ATTACH CLUSTER.  DAMAGE CONSISTENT WITH THAT FO	UND AFTER A HARD LANDING, AIRFRAME AND ENGINE INSPECTED FOR RELATED DAMAGE AND NONE FOUND.  NO REPORT OF A HARD LANDING 	FORTH COMING FROM FLIGHT OPERATIONS.				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2005041800014	20050418	00014	CE  	2005	4	18	CA040916002      	1	20040915	G	3246	99800311	WHEEL           			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) R/H OUTBOARD MAIN WHEEL ASSEMBLY. THE INNER HUB HAD A LONG 4 INCHES CRACK. AS WELL 6 OF THE 9 BOLT HOLES HAD CRACK	S AROUND THEM. THE LONG CRACK APPEARED TO BE AN OLD CRACK. THE TUBE WAS EVENTUALLY PINCHED WHICH CAUSED A FLAT TIRE.					1	L	7	2 	3T	4	T		A14CE   	E4EA
2005041800015	20050418	00015		2005	4	18	CA040916003      	4	20040801	G	2565	D17926101	RESERVOIR       	AIRCRUISERS 		AIRBUS	310   	A310304     	3930339	EU  										ESCAPE SLIDE	DISCHARGED      	Z				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA						0356					(CAN) FL320, AROUND 2 HRS PRIOR TO ARRIVAL IN YYZ, LT OVERWING EMERGENCY EVACUATION SLIDE HAD STARTED TO PARTIALLY INFLA	TE IN FLIGHT. CREW DECIDED TO LAND AT CLOSEST SUITABLE AIRPORT WITH MX. AFTER ALL PAX DEPLANNED, DISARMED LT OVERWING DO	OR & OPENED IT NORMALLY. AFTER INVESTIGATION FOUND MAIN AUTOMATIC INFLATION CO2 BOTTLE ON LT OVERWING DOOR PARTIALLY DIS	CHARGED IN THE RED BAND WITHOUT ANY VISUAL SIGN OF BOTTLE RUPTURE OR ANY EXTERNAL SIGN OF BOTTLE DAMAGE. SLIDE REMOVED I	AW AMM AND A/C DISPATCHED IAW CZECH AIRLINES MEL BOOK. CSA STILL INVESTIGATE ON THIS INCIDENT BUT SUSPECT THE VALVE REGU	LATOR ASSEMBLY INSTALLED ON THE RESERVOIR WHICH IS SUPPOSE TO RETAINS THE GAS PRESSURE WHEN THE SLIDE IS UNDER NORMAL CO	2	L	7	2 	4F			RT	A35EU
2005041800016	20050418	00016	SO  	2005	4	18	CA040916004      	1	20040904	G	2740	3839903	TRIM TAB        			PIPER 	PA44  	PA44180     	7104402	SO  										RIGHT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ROUTINE INSPECTION THE LOWER INBOARD SIDE OF THE RIGHT TRIM TAB WAS FOUNDCRACKED ABOUT 0.750 INCHES LONG. U	PON REMOVAL THE TAB WAS FOUND TO BE CRACKED ALSO IN T HE RIB AS WELL AS THE SKIN.					1	L	7	2 	3O				A19S0
2005041800017	20050418	00017	NE  	2005	4	18	CA040916005      	2	20040902	G	8530	71167	EXHAUST VALVE   	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					CYLINDER	DESTROYED       	W				A				UNSCHED LANDING         				B	R		SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA						619					(CAN) ENGINE RAN ROUGH AND SMOKING IN FLIGHT, LANDED ON LAKE,  INSPECTION REVEALED EXHAUST VALVE FAILURE AND RESULTED IN	 SEVERE PISTON DAMAGE. CYLIDER REPLACED AND AIRCRAFT RETURNED TO MAIN BASE.					1	H	7	1 	3R	3	R		A815    	E142
2005041800018	20050418	00018	NE  	2005	4	18	CA040916006      	2	20040904	G	8500		ENGINE          			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  						FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) FOLLOWING INSPECTION AND REPAIRS AS A RESULT OF EXHAUST VALVE FAILURE AIRCRAFT TAXIED ON WATER FOR TAKEOFF AND OIL	 PRESSURE DROPPED BELOW LIMITS. TAKEOFF ABORTED AND ENGINE REMOVED.					1	H	7	1 	3R	3	R		A815    	E142
2004120900133	20041209	00133	EU  	2004	12	9	CA040916007      	1	20040903	G	2915	NE15FBATI1TFGNO	SWITCH          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	MALFUNCTIONED   	W				B				EMER. DESCENT           				J	F	I	WARNING INDICATION        	FLT CONT AFFECTED         	FLT. ATTITUDE INST.       	CL	CLIMB          	1			CA											SHORTLY AFTER T/O, WARNING HORN & NOTICED 'HYD CAUTION LIGHT' ON.  A FEW SECONDS LATER, ERRATIC CYC MOVEMENT FELT.  RETU	RNED & LANDED W/O INCIDENT. MX INSPECT DID NOT ISOLATE CAUSE FOR MALFUNCTION.  HYD SYS CK APPEARED TO BE NORM. HYD PUMP 	SPLINES INSPECTED & FOUND LUBED & SERVICEABLE.  ELECT CHECKS CARRIED OUT SAT.  VISUAL INSPECT OF WIRE HARNESS REVEALED N	O DISCREPANCY. GROUND RUN CARRIED OUT.  ALL TESTS TURNED OUT NORM, HYD PUMP REPLACED.  ACCUMULATOR'S PRESS CHECKED AT 17	0 PSI FOR 18 DEG C.  ACCUMULATORS RE-CHARGED TO CORRECT PRESS.  HYD TEST 'PUSH BUTTON' SWITCH REPLACED.  ANOTHER GROUND 	RUN REVEALED NO DISCREPANCY.  COLLECTIVE DUMP SWITCH REPLACED, GROUND RUN, NO DISCREPANCY.  A/C RETURNED TO SERVICE.	1	G	7	1 	3U	3	U		H9EU    	E19EU
2004123000093	20041230	00093	EU  	2004	12	30	CA040916008      	2	20040729	G	8550		LINE            								ROTAX 	914   	ROTAX914UL  	 	EU  					OIL PRESSURE	CRACKED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING NORMAL FLIGHT, PILOT SMELLED SMOKE IN THE COCKPIT, FOLLOWED SHORTLY AFTER BY A LOW OIL PRESSURE WARNING LIG	HT ILLUMINATING. AN UNSCHEDULED LANDING WAS MADE WITH NO DAMAGE OR INJURIES. UPON EXAMINATION THE TURBO OIL PRESSURE LIN	E WAS FOUND CRACKED AT THE TURBO FITTING.  5 CLAMPS DESIGNED TO SUPPORT THE TURBO OIL LINES WERE FOUND MISSING.  THE ABS	ENCE OF THESE CLAMPS ALLOWED VIBRATION TO HARDEN THE PRESSURE OIL LINE AND A CRACK FORMED AT THE TURBO FITTING CAUSING A	N OIL LEAK AND AN OIL PRESSURE LOSS.							3	O			EXPE3I
2004102700077	20041027	00077	NE  	2004	10	27	CA040916009      	1	20040914	G	6420	S611033003000	HUB             	SKRSKY      		SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A126581					(CAN) DURING NDT INSPECTION THE HUB WAS FOUND TO HAVE A CRACK INDICATION ON ONE OF THE EARS.  THE INDICATION WAS BLENDED	, WITH APPROX. .010-.015 INCH OF MATERIAL BEING REMOVED.  THE HUB WAS THEN RE-INSPECTED AND INDICATIONS OF THE DEFECT WE	RE STILL EVIDENT UNDER BLACK-LIGHT CONDITIONS.				2	G	7	2 	4U	4	U		1H15    	1E3
2004101800135	20041018	00135	CE  	2004	10	18	CA040916010      	1	20040916	G	3340	CM35895	SWITCH          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	LANDING LIGHT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING ROUTINE MAINTENANCE ON THE AIRCRAFT, IT WAS NOTED THAT THE LANDING LIGHT SWITCH WAS FUNCTIONING I	NTERMITTENTLY.  PREVIOUS EXPERIENCE WITH THIS TYPE OF DEFECT URGED US TO REPLACE THE SWITCH WITH A NEW PART.  THE OLD SW	ITCH WAS OPENED UP TO DETERMINE THE CAUSE OF THE MALFUNCTION WHICH REVEALED ONE OF THE COPPER BRAIDS SEPARATED FROM ITS 	POINT OF ATTACHMENT.  THIS DEFECT HAS PROBABLY OCCURRED TWO OR THREE TIMES WITH THIS ORGANIZATION.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2005012100161	20050121	00161	CE  	2005	1	21	CA040916011      	1	20040914	G	5344	504300431329	CHANNEL         	RAYTHN      		BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	CABIN DOOR	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) THE CREW REPORTED THAT THE CABIN DOOR APPEARED TO BE LEAKING AROUND ITS LOWER AFT CORNER.  MAINTENANCE DISCOVERED 	A 1-INCH CRACK IN THE CABIN DOOR SKIN AT THE LOWER AFT CORNER.  THE CRACK RUNS THROUGH THE AFT-MOST HINGE ATTACHMENT RIV	ET.  WHEN THE DOOR WAS DISASSEMBLED TO REPAIR THE CRACK, THEY DISCOVERED THAT THE DOOR HINGE ALSO HAD A ONE-INCH CRACK A	T THAT SAME LOCATION.  THE DOOR HINGE SUPPORT CHANNEL HAS AN .1250 INCH CRACK AND DEFORMATION ALONG THE HINGE RIVET LINE	. THE CRACK RUNS THROUGH 9 OF THE RIVET HOLES IN THE CHANNEL.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2005041800019	20050418	00019	WP  	2005	4	18	CA040917001      	1	20040914	G	2421		GENERATOR       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					AC SYSTEM	FAILED          	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FLT CREW DECIDED TO LAND BACK TO DEPARTURE AIRPORT FOLLOWING 3 DISCREPANCIES:  TAIL COMPARTMENT OVERTEMP LIGHT CAM	E ON AFTER ROTATION.THE LT PACK WAS SELECTED OFF TO CONTINUE FLIGHT.  LATER ON THE LT CSD OIL OUTLET TEMP WENT HIGH.THE 	CSD WAS DISCONNECTED AND THE APU WAS STARTED AS REQUESTED BY PROCEDURES AND SHUT DOWN DUE TO GENERATOR OUT OF FREQUENCY.	ALL 3 DISCREPANCIES WERE RECTIFIEDAS FOLLOW:SOME DUCT CLAMPS WERE FOUND LOOSE IN TAIL COMPARTMENT LT PACK ANDSECURED.THE	 CSD OIL LEVEL WAS FOUND OVER SERVICED AND OIL LEVEL WAS RE SERVICED AS PER MM.APU GENERATOR FREQUENCY ADJUSTED AS REQUI	RED.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041800020	20050418	00020		2005	4	18	CA040917002      	4	20040915	G	2230		AUTOTHROTTLE SYS			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 2	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, AIRCRAFT HAD NR 2 AUTO THROTTLE (A/T) AFCAS FAULT, FOLLOWED BY NR 1 AND 2 STAB TRIM DOUBLE CHANNEL I	N FAULT.  AIRCRAFT LANDED BACK TO DEPARTUREAIRPORT. THE A/T DEFECT WAS DISPATCHED AS PER MEL AND RECTIFIED THE DAY AFTER	 B Y ADJUSTING THE  NR 2 POWER LEVER ANGLE SWITCH LOCATED IN PEDESTAL.  THE STAB TRIM WAS FUNCTIONAL TESTED AS PER MM AN	D FOUND SATISFACTORY			2	L	7	2 	4F	4	F	RT	        	E25NE
2005041800021	20050418	00021	CE  	2005	4	18	CA040917003      	1	20040830	G	2432	32638002	CELL            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					BATTERY	REVERSED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						10001681					(CAN) AIRCREW REPORTED LOAD METERS NOT INDICATING BATTERY CHARGE FOR NORMAL PERIOD OF TIME OR NORMAL LEVEL OF CHARGE. UP	ON INSPECTION NR 9 CELL FOUND INSTALLED IN REVERSE POLARITY ORIENTATION.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA
2004101300045	20041013	00045	CE  	2004	10	13	CA040917004      	1	20040830	G	3234	1013841377	SWITCH          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CONTROL HANDLE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LANDING GEAR FAILED TO EXTEND WHEN SELECTED DUE TO FAILURE OF SWITCH IN LANDING GEAR CONTROL HANDLE.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004102000191	20041020	00191	SW  	2004	10	20	CA040917005      	1	20040831	G	6700		MOUNT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					LOWER BASE	MISALIGNED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOWER MOUNTING BASE WAS FOUND TO BE INSTALLED 90 DEGREES FROM CORRECT ALIGNMENT TO ALLOW ENGAGEMENT OF LOCK PIN.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2004101800128	20041018	00128	CE  	2004	10	18	CA040917006      	1	20040903	G	3213	07416011	LEG ASSY        			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	IO470D      	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	LT MLG	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN TURNING TO ALIGN AIRCRAFT FOR TAKEOFF ON THE GRASS STRIP AT CPE7 THE LT MAIN LANDING GEAR LEG SNAPPED OFF AT 	THE OB CHANNEL.  THE AIRCRAFT COLLAPSED, THE ENGINE WAS STOPPED WITHOUT A PROP STRIKE BUT THE WING EXTENSION AND TIP WER	E DAMAGED AS WELL AS THE TAIL PLANE.  NO PREVIOUS EVIDENCE OF CRACKING OR CORROSION IN THIS AREA.				1	H	7	1 	3O	3	O	NT	3A13    	3E1	5	C	P3EA
2004102000192	20041020	00192	CE  	2004	10	20	CA040918001      	1	20040916	G	2120	24192273	TUBE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					WHEEL WELL	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13557								(CAN) CLEAR FLUID WAS SEEN RUNNING FROM LT WHEEL WELL AFTER EXTENDED GROUND RUNNING WITH AIR CONDITIONING OPERATING.  IT	 WAS DETERMINED TO BE WATER THAT WAS DRAINING FROM THE AIR CONDITIONING EVAPORATOR INTO WHEEL WELL INSTEAD OF THROUGH OV	ERBOARD DRAIN. CHECK/DRAIN VALVE WAS FOUND TO BE INOPERATIVE (FAILED CLOSED - CORRODED).  THIS HAD ALLOWED CONDENSATION 	TO COLLECT IN ALUMINUM TUBE ASSY, WHICH HAD FROZEN AT ALTITUDE, RUPTURING TUBE  IN TWO PLACES.  THIS DRAIN TUBE IS OUTSI	DE PRESSURE VESSEL, UPSTREAM OF CHECK/DRAIN VALVE WHICH IS NORMALLY CLOSED IN FLIGHT (OPEN ON GROUND WHEN A/C IS NOT PRE	SSURIZED).  FAILURE OF TUBE RESULTS IN AN EXCESSIVE CABIN PRESSURIZATION LEAK. PARTS REPLACED WITH NEW.	2	L	7	2 	4F	4	F		A10CE   	E6WE
2004101800129	20041018	00129	EA  	2004	10	18	CA040918002      	1	20040916	G	2740	70744	CONTROL UNIT    			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C1     		NE  					MACH TRIM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING THROUGH 7200 FEET, THE CAPTAIN WAS MAKING SMALL INPUTS TO STAB TRIM. MACH TRIM CAUTION MESSAGE APPE	ARED FOLLOWED RIGHT AFTER BY A STAB TRIM CAUTION.  THE STAB WAS NOT RESPONDING TO INPUTS.  PILOT TRIED TO RE-ENGAGE THE 	STAB AND NEITHER CHANNEL WOULD.  AIRCRAFT RETURNED TO BASE.  THE LANDING WAS UNEVENTFUL. FOLLOWING TROUBLESHOOTING, MAIN	TENANCE REPLACED THE MCU AND THE NR 1 SSCU.   AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005020100051	20050201	00051	NM  	2005	2	1	CA040920001      	1	20040617	G	2742	251T43101	ACTUATOR        			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					STABILIZER TRIM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			63979								(CAN) WATER INGRESS INTO GEAR BOX CAUSED EXTENSIVE CORROSION, INVESTIGATION ON GOING WITH MFG (STAB TRIM ACTUATOR).						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2005041200041	20050412	00041	SO  	2005	4	12	CA040920002      	2	20040913	G	7421	URHB32E	SPARK PLUG      			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NR 4 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN REMOVING NR 4 CYLINDER LOWER SPARK PLUG, BROKE COMPLETELY OFF, JUST ABOVE BASE AND BELOW HEX DRIVE PORTION.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA
2005041800022	20050418	00022	SW  	2005	4	18	CA040920003      	1	20040906	G	2435		DRIVE SHAFT     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	STARTER GEN	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						14311					(CAN) PILOT ATTEMPTED TO START LT ENGINE, PROP STARTED TO ROTATE THEN STOPPED. UPON OPENING THE ENGINE COWL, IT WAS FOUN	D THAT THE FRICTION DISC WAS IN PIECES IN THE BOTTOM OF THE COWL.  WHEN THE STARTER WAS REMOVED, THE DRIVE SHAFT WAS FOU	ND SHEARED. THE TORLON INSERT WAS ALSO FOUND DAMAGED EXTENSIVELY ALONG WITH THE DRIVE GEAR IN THE ENGINE.  THE DRIVE HAD	 TO BE REPLACED DUE TO THE STARTER DRIVE SHAFT CAUSING DAMAGE WHEN THE TORLON INSERT WAS NOT LONGER DOING IT'S JOB.  STA	RTER TURNED OVER BY HAND AND IT WAS NOT SEIZED. STARTER SENT TO OVERHAUL FACILITY FOR FURTHER INVESTIGATION.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2005041800023	20050418	00023	SW  	2005	4	18	CA040920004      	1	20040916	G	7714	2719157005	INDICATOR       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT RPM	INOPERATIVE     	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE OFF THE LH RPM INDICATION WENT TO ZERO.  THE RPM INDICATOR WAS JUST INSTALLED AND HAD TESTED SERVICIBL	E DURING THE GROUND RUNS.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2005041800024	20050418	00024	SO  	2005	4	18	CA040921001      	1	20040408	G	5540	40040009	TORQUE TUBE     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13722								(CAN) INTERNAL INSPECTION OF RUDDER REVEALED SURFACE CORROSION AND SURFACE PITTING. TORQUE TUBE REPLACED WITH NEW P/N 40	040-009.					1	L	7	2 	3O	3	O		A20SO   	E14EA
2005041800025	20050418	00025	SO  	2005	4	18	CA040921002      	1	20040504	G	2752	475212	MOTOR           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TE FLAP CONTROL	BURNED OUT      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ROUTINE MAINTENANCE THE FLAP OPERATION WAS OBSERVED TO BE NOISY. MOTOR WAS FOUND TO BE INTERNALLY BURNED. M	OTOR WAS REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
2004101300064	20041013	00064	SO  	2004	10	13	CA040921003      	1	20040719	G	3246	40141	WHEEL           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16219								(CAN) LT TIRE WENT FLAT WHILE PARKED. FURTHER INVESTIGATION REVEALED A CRACKED WHEEL IN FLANGE AREA. WHEEL, TIRE AND TUB	E WERE REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004101800125	20041018	00125	SO  	2004	10	18	CA040921004      	1	20040704	G	3210	CH20261	TORQUE LINK     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE MAIN LANDING GEAR TORQUE LINK WAS FOUND CRACKED.  THESE P/N CH2026-1 TORQUE LINKS AR	E PART OF BOUNDARY LAYER RESEARCH HEAVY LANDING GEAR KIT FOR STC  NR SA00202SE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004101800126	20041018	00126	SO  	2004	10	18	CA040921005      	2	20040903	G	8530	CNF71ER	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER ASSEMBLY FOUND CRACKED FROM SPARK PLUG HOLE.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA
2005041800026	20050418	00026		2005	4	18	CA040921006      	4	20040827	G	6122		BEARING         	WOODWARD    		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					GOVERNOR	DESTROYED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						1490162B					(CAN) PILOT REPORTED MINOR DIFFICULTY IN MAINTAINING A CONSTANT:  RPM SELECTION, RPM WOULD WANDER +/- 50 RPM (RT SIDE.  	PROPS NEW. CONTROL LINKAGE AND GOVERNORS INSPECTED, NIL DEFECTS FOUND.  GOVERNOR SENT TO O/H SHOP FOR REPAIR.  O/H SHOP 	STATES BEARING DESTROYED. HOUSING, BODY, BASE IDLER AND DRIVE GEARS ALL DAMAGED DUE TO FAILED BEARING.  PARTS AVAILABLE 	AT THE FACILITY.  GOVERNOR REPLACED WITH O/H UNIT.			1	L	7	2 	3O	3	O		A7SO    	E9CE
2005041800027	20050418	00027	GL  	2005	4	18	CA040921007      	2	20040916	G	7532	23053190	BLEED VALVE     			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					COMPRESSOR	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE FLAMED OUT TWICE DURING TEST FLIGHT FOR BLEED VALVE CHANGE AND RELIGHT ON BOTH OCCATIONS BY AUTO RELIGHT.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2005012100170	20050121	00170	CE  	2005	1	21	CA040921008      	1	20040920	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN FLIGHT WINDSHIELD INNER PANE SHATTERED, PLANE RETURNED TO BASE.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005012100171	20050121	00171	CE  	2005	1	21	CA040922001      	1	20040921	G	3230	NAS5150	SNAP RING       			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	OUT OF POSITION 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENDPLAY CHECK (1000 CYCLES) ON LT MAIN GEAR ACTUATOR, INPUT GEAR WAS FOUND TO HAVE 0.090 INCH ENDPLAY. THIS	 CHECK USED TO VERIFY THAT THRUST BEARING IS PROPERLY INSTALLED,  MAXIMUM ENDPLAY IS 0.050. THESE ACTUATORS ARE OVERHAUL	ED AT 7500 CYCLES, TSO FOR THIS ONE WAS ONLY 894. FURTHER INVESTIGATION REVEALED THAT THE SNAP RING P/N NAS 51-50 WAS NO	T IN ITS GROOVE ALLOWING THE INPUT GEARS TO MOVE MORE THAT NORMAL. UNKNOWN IF THE SNAP RING WAS IMPROPERLY INSTALLED AT 	OVERHAUL OR IF IT CAME OUT LATER, SINCE THERE IS A POSSIBILITY THAT OTHER INTERNAL PARTS WERE DAMAGED, THE ACTUATOR WAS 	REMOVED FROM SERVICE AND WILL BE RETURNED TO THE OVERHAUL FACILITY FOR FURTHER INVESTIGATION.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC
2005041800028	20050418	00028	NM  	2005	4	18	CA040922002      	1	20040915	G	5230		ROD END         			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CARGO DOOR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE OPENING OF THE CARGO DOOR FOR LOADING OF THE AIRCRAFT, A WIND GUST BLEW THE DOOR FULLY OPEN, AND SH	EARED ALL FOUR ACTUATOR LINK RODS. THE DOOR ENDED UP IN A VERTICAL POSITION. THE WIND VELOCITY AND GUSTS WERE CHECKED WI	TH THE CONTROL TOWER PRIOR TO OPENINGTHE DOOR SO AS NOT TO EXCEED GUST LIMITS. THE GUSTS WERE WITHIN THE MANUFACTURE RS 	MAXIMUM GUST LIMITS. A THOROUGH INSPECTION OF THE ACTUATORS AND STRUCTURE WAS CARRIED OUT, NO FURTHERDAMAGE FOUND. THE D	OOR WAS LOWERED AND WAS FOUND TO OPERATE NORMALLY. THE BROKEN LINK RODS WERE REPLACED.		2	L	7	3 	4F	4	F		A3WE    	E2EA
2005041800029	20050418	00029	CE  	2005	4	18	CA040922003      	1	20040724	G	5753	0512128	PULLEY BRACKET  			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF, WHEN RAISING FLAPS FROM 100 TO 00, PILOT FELT A RELEASE OF TENSION AND A/C BANKED LT, UNTIL FLAP H	ANDLE LOCKED IN AT 00 POSITION. PILOT CHECKED FLT CONTROLS & ALL APPEARED NORMAL, PILOT SUSPECTED SOMETHING WRONG WITH F	LAPS. A/C FLOWN TO BASE, & BEFORE LANDING, PILOT DECIDED TO CHECK FLAPS. AS SOON AS FLAP HANDLE MOVED FROM 00 LATCH TOWA	RDS 100 LATCH A/C WANTED TO BANK LT AGAIN, SO PILOT SET FLAPS BACK TO 00 & DID AN UNEVENTFUL FLAPLESS LANDING. MX NOTIFI	ED & UPON INSPECTION OF FLAP SYSTEM, FOUND TABS OF A PULLEY BRACKET ON A MAIN BULKHEAD AT STA 65.33, HAD BROKEN AWAY.		1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL
2005041800030	20050418	00030	EA  	2005	4	18	CA040922004      	2	20040922	G	7412	312241307	EXCITER         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 ENGINE	FAILED          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) DURING A TEST FLT REQUIRED FOR JAPANESE ANNUAL C OF A RENEWAL,  AT APPROX 12,500 FT, THE NR 2 ENGINE WAS SHUT DOWN	 AND A ALTERNATE LANDING GEAR EXTENSION WAS CARRIED OUT. THE CREW THEN ATTEMPTED TO RESTART THE NR 2 ENGINE IN FLT, BUT 	WERE UNSUCCESSFUL. THE AIRCRAFT MADE A SUCCESSFUL SINGLE ENGINE LANDING. FAULT CODES REPORTED WERE 910 & 969. NR 2 ENGIN	E IGNITION EXCITER WAS REPLACED, FAULT CODESCLEARED AND ENGINE STARTS NORMALLY.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005012100172	20050121	00172	CE  	2005	1	21	CA040922005      	1	20040921	G	3233	508202085	ACTUATOR        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	NLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE 1000 CYCLE ENDPLAY CHECK OF THE NOSE GEAR ACTUATOR, THE ACTUATOR FAILED WITH 0.020 OF AN INCH ENDPL	AY THE MAX ALLOWABLE IS 0.016. THIS UNIT ONLY HAD 997 CYCLES SINCE OVERHAUL (OVERHAUL DUE AT 7500 CYCLES).  THE ACTUATOR	 WAS REMOVED FROM SERVICE AND WILL BE RETURNED TO THE OVERHAUL FACILITY FOR FURTHER INVESTIGATION. THE ACTUATOR ALSO HAD	 CORROSION ON THE HOUSING UNDER THE BEARING JOURNAL.			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC
2005041800031	20050418	00031	NM  	2005	4	18	CA040922006      	1	20040629	G	3260	401020101	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG WHEEL CENTER	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UNABLE TO SELECT GEAR UP.  RECEIVED THREE GREEN INDICATION LIGHTS ALONG WITH THREE RED INDICATION LIGHTS AND AMBER	 GEAR HANDLE LIGHT. PERFORMED RETURN TO LANDING CHECKLIST.  NORMAL LANDING PERFORMED.  NLG CENTERING PROXIMITY SENSOR FO	UND SHORTED.  SENSOR REPLACED AND ADJUSTED TO 8.602 MH IAW AMM 32-61-03.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2004101300065	20041013	00065	NM  	2004	10	13	CA040923001      	1	20040627	G	6120	699018002	CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AUTO FEATHER	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) AUTO FEATHER SYSTEM FAILED TO ARMED WHEN TAKE-OFF POWER WAS APPLIED. TAKE-OFF ABORTED AT APPROX 60 KTS.  RETURNED 	TO GATE.  AC GROUNDED.  RT PROPELLER ELECTRONIC CONTROL UNIT (PECU) REPLACED IAW AMM 61-20-36.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2004101800123	20041018	00123	SO  	2004	10	18	CA040923002      	2	20040916	G	8530	AEC631397ST712B	CYLINDER        			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								514517			(CAN) AT THE 50 HRS INSPECTION OF THE AIRCRAFT, DURING ENGINE CYLINDER COMPRESSION TEST,  MADE ENGINE SB M91-6, AND THE 	TEST FAILED BECAUSE FOUND AIR LEAK AT THE JUNCTION OF THE CYLINDER BARREL AND THE TOP CYLINDER HEAD (BETWEEN FINS).  THE	 ENGINE AND CYLINDER HAD ONLY 90.5 HRS.  REPLACED CYLINDER AND RETURNED AIRCRAFT TO SERVICE AFTER THE INSPECTION.				1	L	7	2 	3O	3	O		A7CE    	E8CE
2005021400190	20050214	00190	EA  	2005	2	14	CA040923003      	1	20040922	G	7933	523281	INDICATOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	OIL SYSTEM	READS HIGH      	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA			30718	30718							(CAN) DURING CRUISE FLIGHT NR 2 ENGINE OIL TEMP CLIMB ABOVE RED LINE ON INDICATOR TO 125 DEG C.   NR 2 ENGINE SHUTDOWN A	S PRECAUTION .  FLIGHT CONTINUED TO SCHEDULED DESTINATION FOR NORMAL LANDING.  MAINTENACE REPLACED NR 2 OIL PX/TEMP GAUG	E , AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005050300199	20050503	00199	EA  	2005	5	3	CA040923004      	1	20040904	G	3246	AN679AC6000	TIE ROD         			DHAV  	DHC3  	DHC3        	2800202	EA  	WALTER	M601  	M601E11     	 	EU  					RT MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) PILOT NOTICED TIE ROD BROKEN UPON RETURN TO BASE. NO DIFFICULTY WITH THIS LANDING OR PREVIOUS LANDINGS WHERE NOTED	 BY PILOT. PART WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. PLEASE ADVISE WHERE PARTS CAN BE SENT FOR EXAMINATION	.  HAVE NOT SEEN A FAILURE OF THIS TYPE IN NORMAL OPERATION IN OVER 30 YEARS OF AIRCRAFT MAINTENANCE.				1	H	7	1 	3R	3	T		A815    	E00048EN
2005041800032	20050418	00032	NM  	2005	4	18	CA040923005      	1	20040917	G	7333	30B350604	TRANSMITTER     			DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					FUEL FLOW	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) FUEL FLOW TRANSMITTER END CAP CRACKED WITH RESULTANT FUEL LEAKAGE INTO NACELLE.						2	H	7	2 	4T	4	F	RT	A55NM   	E35NE
2005041800033	20050418	00033	NM  	2005	4	18	CA040923006      	1	20040725	G	3260	401020101	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG CENTERING	SHORTED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) UNABLE TO RETRACT LANDING GEAR DURING CLIMB. GEAR DOORS LOCKED. NO TRANSITION, NO YELLOW LIGHTS. THREE GREEN LIGHT	S REMAINED CONSTANT ON. RECYCLED WITHOUT SUCCESS. RETURNED TO BASE. NLG CENTERING PROXIMITY SENSOR FOUND SHORTED. SENSOR	 REPLACED ACC AMM 32-61-03.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041800034	20050418	00034	NM  	2005	4	18	CA040923007      	1	20040923	G	3220	B273201201	DRAG BRACE      			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG	LACK OF LUBE    	W				O				OTHER                   				W	J		INADEQUATE Q C            	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) ON FINAL APPROACH,  SELECTED GEAR DOWN. NOSE GEAR DOORS DID NOT OPEN AND THE NOSE GEAR RED LIGHT REMAINED ILLUMINA	TED WITH THE NOSE GEAR GREEN LIGHT OUT. EXECUTED A MISSED APPROACH AND THE GEAR RETRACTED NORMALLY. RESELECTED GEAR DOWN	 AND GEAR EXTENDED NORMALLY AND LANDED UNEVENTFULLY. AIRCRAFT WAS GROUNDED UNTIL A NLG INSPECTION AND GEAR SWINGS COULD 	BE ACCOMPLISHED. THE NLG INSPECTION FOUND THE NLG DRAG BRACE KNUCKLE HAD VERY LITTLE LUBRICANT. NLG DRAG BRACE KNUCKLE L	UBRICATED AND NUMEROUS GEAR SWINGS ACCOMPLISHED, NLG SYSTEM COULD NOT BE FAULTED.  AIRCRAFT RETURNED TO SERVICE.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005041800035	20050418	00035		2005	4	18	CA040923008      	1	20040923	G	2497	U384U	CONNECTOR       																	ELECTRICAL	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PRIOR TO REPLACING CONNECTOR, WE VERIFIED WITH A DMM CONTINUITY FROM CONNECTOR END TO SOLDER TERMINALS.  (6) CONNE	CTORS WERE FOUND INPROPERLY MANUFACTURED, THE ORIENTATION OF THE SOLDER TERMINALS DID NOT MATCH THE CONNECTOR.  I HAVE C	ONTACTED THE QUALITY CONTROL MANAGER AT NEXUS AND NOTIFIED HIM OF THE FINDING. PARTS REMOVED FROM QUARANTINED AND SHIPPE	D TO NEXUS FOR ANALYSIS.
2005041800036	20050418	00036	EU  	2005	4	18	CA040924001      	1	20040918	G	2120	A28110280000	VAPOR BARRIER   			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					LT A/C PACK	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INVEST OF A PNEUMATIC LEAK AT LT A/C PACK DISCHARGE DUCT HEAT EXCHANGER CONNECTOR, FUEL VAPOR BARRIERS FOUN	D DAMAGED ABOVE THIS AREA.  METAL FUEL VAPOR BARRIER HAD DAMAGE OF APPROX 2 SQ FT.  FIBER FUEL VAPOR BARRIER PUNCTURED 2	 SQ. IN.  FUEL VAPOR BARRIER REPLACED & PNEUMATIC DUCT COUPLING ALSO REPLACED.  FIBER FUEL VAPOR BARRIER REPAIRED IAW MM	.  A FLEET CAMPAIGN IN PROGRESS TO REPLACE ALL COUPLINGS IN A/C BAY AREA BUT ACRFT HAD NOT YET BEEN DONE.  UNABLE TO DET	ERMINE IF FUEL VAPOR BARRIER DAMAGE CAUSED BY PNEUMATIC LEAK AT HEAT EXCHANGER COUPLING.  A VISUAL INSPECT OF BARRIERS C	ARRIED OUT IN 08/04 DURING ROUTINE A-CHECK & NO FAULT NOTICED. AIRBUS CONTACTED & ASSIST REQUESTED IN EVAL OF FAILURE.	2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2004101300066	20041013	00066	EU  	2004	10	13	CA040924002      	1	20040908	G	2750	SP10CCH614301	LEVER           			HWKSLY	DH125 	DH125400A   	4230140	EU  										TE FLAPS	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFTER AIRCRAFT STRIPPED AND BEFORE PAINT, THIS INCIDENT OCCURRED. WHEN SELECTING FLAPS TO DUMP MODE WE FOUND THE F	LAPS WOULD NOT MOVE AT ALL. INVESTIGATION FOUND THAT THE BAULK VALVE LATCH LEVER WOULD NOT MOVE. TECHNICIAN TOOK BAULK V	ALVE LATCH LEVER ATTACH PIN APART AND FOUND EXTENSIVE CORROSION UNDER CLEVIS PIN WASHER.   WE DETERMINED THAT THE CORROS	ION PREVENTED THE BAULK LEVER FROM MOVING WHEN THE FLAPS WERE SELECTED TO DUMP MODE. THE PARTS WERE REMOVED, CLEANED, LU	BRICATED AND REASSEMBLED BACK TO SERVICEABLE CONDITION.		2	L	7	2 	4J				A3EU
2005041800037	20050418	00037	NM  	2005	4	18	CA040924003      	1	20040617	G	3260	401020101	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG CENTERING	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UNABLE TO SELECT MLG GEAR UP DURING CLIMB.  AFTER CONSULTING THE TECHNICAL DEPARTMENT WE TRIED RECYCLING BUT WITH 	NO SUCCESS. RETURNED TO BASE.  NOSE GEAR CENTERING PROXIMITY SENSOR REPLACED ACC AMM 32-61-06.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2004101800131	20041018	00131	NE  	2004	10	18	CA040924004      	2	20040919	G	7310	FK20824	LINE            			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					LP FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK DISCOVERED IN THE AREA COVERED BY AD (CAMPAIGN) NR 9-0065.						2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2004111000058	20041110	00058	NM  	2004	11	10	CA040924005      	1	20040521	G	3260	401020101	SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG CENTERING	SHORTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UNABLE TO SELECT MLG GEAR UP DURING CLIMB.  GEAR RECYCLED ONCE WITHOUT SUCCESS.  RETURNED TO LAND AT OUR BASE.  NW	C SENSOR FOUND SHORTED. NOSE WHEEL CENTERING PROXIMITY SENSOR REPLACED ACC AMM 32-61-06.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005012100169	20050121	00169	CE  	2005	1	21	CA040924006      	1	20040924	G	1430	AN34A	BOLT            	CESSNA      		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	TE FLAP	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10029								(CAN) AN3-4A BOLTS ATTACHING IB BRACKET TO FLAP FOUND STRIPPED.  BOLTS REPLACED WITH NEW AN3-4A.  END OF DEFECT.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA
2005021400191	20050214	00191	SO  	2005	2	14	CA040924007      	2	20040913	G	8530	537296	TUBE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PUSHROD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 5 CYLINDER PUSH ROD TUBE HOUSINGS FOUND 1 CRACKED, AT CYLINDER HEAD END, THE OTHER WAS BENT AT OB END OF SPRING	 RETAINER.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA
2005031100031	20050311	00031	CE  	2005	3	11	CA040924008      	1	20040924	G	3211	12116013	FITTING         	CESSNA      	12910606    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10029								(CAN) LT MAIN LANDING GEAR OB FITTING FOUND CRACKED.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA
2005020100159	20050201	00159	EU  	2005	2	1	CA040927001      	1	20040924	G	2161	5829C000	CONTROL VALVE   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TEMP  CONTROL	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AUTO TEMP.  FUNCTION OF ECS NOT WORKING PROPERLY DURING FLIGHT AND MANUAL SIDE INTERMITTENT.  AIRCRAFT FINISHED FL	IGHT AND TEMPERATURE CONTROL VALVE ASSY (PN 5829C000) TESTED AND REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020100160	20050201	00160	CE  	2005	2	1	CA040927002      	1	20040921	G	5320	97430000115	CROSS TIE       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSLEAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14205								(CAN) DURING MAINTENANCE, A CRACK WAS DISCOVERED IN A FUSELAGE CROSS TIE FOR THE UPPER RT FUSELAGE, IMMEDIATELY AFT OF T	HE EMERGENCY EXIT WINDOW. NEW PART HAS BEEN ORDERED AND WILL BE INSTALLED TO RECTIFY THIS DEFECT.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005020100161	20050201	00161	EU  	2005	2	1	CA040927003      	1	20040922	G	2161	9599020135	CONTROL VALVE   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TEMP CONTROL	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CONTROL VALVE FOUND INOPERATIVE AFTER CREW COMPLAINED OF TROUBLE CONTROLLING HEAT. THE VALVE WAS REPLACED AND AIRC	RAFT RETURNED TO SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004101800132	20041018	00132	EU  	2004	10	18	CA040927004      	1	20040922	G	3060	4E305110	BOOT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER DEICE	MALFUNCTIONED   	W				J	A			DUMP FUEL               	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CREW REPORTED PROP DEICE MALFUNCTION.  ONE BOOT WAS FOUND FAILED. BOOT REPLACED AND AIRCRAFT RETURNED TO SERVICE.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004111000059	20041110	00059	EU  	2004	11	10	CA040927005      	1	20040922	G	3397	L40B16L41A16N	WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LANDING LIGHT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAXI LIGHT FOUND TO BE UNSERVICEABLE.  INVESTIGATION REVEALED BROKEN WIRES L40B16 AND L41A16N AT THE PIVOT AREA OF	 THE NLG.  THE WIRES WERE REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005012100175	20050121	00175	SW  	2005	1	21	CA040927006      	1	20040920	G	8200	2767030389	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WATER METHANOL SYSTEM WAS MEL'D ON LT ENGINE.  LATER INVESTIGATION REVEALED A BROKEN RIGID LINE IN THE LT ENGINE N	ACELLE.  LINE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2005021400197	20050214	00197	CE  	2005	2	14	CA040927007      	1	20040924	G	5210	50430043663	DOOR            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT AFT FUSELAGE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH, AT 20 MILES OUT AND 2500 FT ASL THE CABIN DOOR OPENED. FLIGHT SERVICES WAS INFORMED AND THE AIRCRAFT 	LANDED UNEVENTFULLY. THE COPILOT CLOSED THE DOOR AFTER LANDING. THE DOOR AND SURROUND WERE INSPECTED NO DAMAGE FOUND.					1	L	7	2 	3T	3	T		A14CE   	E4EA	6	C	P15EA
2005020100101	20050201	00101	CE  	2005	2	1	CA040927008      	1	20040927	G	3242	224110213	PIVOT ASSY      	CESSNA      		CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  	MCAULY	2D34C	B2D34C219   	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT BRAKE CONTINUALLY LOOSING FLUID. CENTER SECTION AT GEAR PIVOTS ALWAYS WET. BRAKE SWIVEL NOT LEAKING.  PIVOT ASS	EMBLY REMOVED AND CHECKED BY DYE PENETRATE INSPECTION FOUND TO BE CRACKED.  INSTALLED NEW PIVOT ASSEMBLY IAW MAINTENANCE	 MANUAL.				1	H	7	1 	3O	3	O		3A13    	E295	5	C	P7EA
2005020100162	20050201	00162	EA  	2005	2	1	CA040927009      	1	20040917	G	5510	C2TP159	ATTACH BRACKET  			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	LT STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK LOCATED ON THE REAR FACE OF THE LT STAB ATTACH BRACKET, THE CRACK PARALLELS THE OB ATTACH FLANGE (ANCHOR NUT	 ATTACH SIDE) FOR 1.3750. THE CRACK HAD STARTED AT THE TOP OF THE STAB ATTACH BRACKET AND HAD WORKED ITS WAY DOWN. THE C	RACK ON THE BRACKET WAS ONLY VISIBLE ONCE THE BRACKET WAS REMOVED FROM THE FRONT SPAR FOR SPECIAL INSPECTION CF-91-42.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA
2005021400198	20050214	00198	NE  	2005	2	14	CA040928001      	2	20040912	G	7200		ENGINE          			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	E	J	OVER TEMP                 	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA								13355			(CAN) IN FLIGHT SHUT DOWN AND AIR TURN BACK. IN CLIMB LOUD BANG AND TGT INCREASED TO 1000 DEG C. PILOT SHUT DOWN ENGINE 	AND RETURNED TO ORIGIN. ON GROUND, DEBRIS FOUND IN TAIL PIPE. ENGINE WILL BE INDUCTED  IN OCTOBER.  SUSPECT ED HPT BLADE	 FAILURE, FURTHER INFO WILL BE PROVIDED AT ENGINE STRIP.				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN
2005020100163	20050201	00163	NE  	2005	2	1	CA040928002      	2	20040723	G	8530	11768	CAM             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	EXHAUST	WORN            	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								P325832			(CAN) DURING FLIGHT ENGINE DEVELOPED UNUSUAL DRONING NOISE FROM ENGINE. SUSPECT WORN CAM LOBE.  CAM REMOVED AND FOUND TO	 BE WORN ON SEVERAL EXHAUST CAM LOBES.  SERVICEABLE CAM, ROLLERS AND PINS INSTALLED.   ENGINE GROUND RUN SATISFACTORY.  	AIRCRAFT RELEASED.  SATISFACTORY FLIGHT TEST CONDUCTED.				1	H	7	1 	3R	3	R		A815    	E142	6	C	P719
2005020100164	20050201	00164	NE  	2005	2	1	CA040928003      	2	20040826	G	7414	383021	SEAL            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	MAG DRIVE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						201831					(CAN) DURING INSPECTION,  OIL WAS FOUND DRIPPING FROM THE MAG DRIVE ON LT MAG.  MAG DRIVE SEAL FOUND TO BE LEAKING.  REP	LACED SEAL.  ENGINE GROUND RUN SATISFACTORY.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
2005041800038	20050418	00038	NE  	2005	4	18	CA040928004      	2	20040925	G	7250		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2	FAILED          	W				A				UNSCHED LANDING         				Y	D		ENGINE STOPPAGE           	INFLIGHT SEPARATION       		CL	CLIMB          	1			CA			18420					728098			(CAN) A LOUD BANG WAS HEARD DURING CLIMB AT 100 AGL.  NR 2 ENGINE FAILED AND RELIT AUTOMATICALLY.  AIRCRAFT RETURNED BAC	K FOR LANDING WITH ENGINE NR 2 AT IDLE WITH ALL PARAMETERS AT NORMAL EXCEPT THAT EGT REACH LIMITS WHILE THROTTLE WAS ADV	ANCED.  THE TURBINE WAS FOUND DAMAGED.  THE ENGINE ASSY WILL BE REPLACED.  AN ENGINE INVESTIGATION WILL FOLLOW.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005021400199	20050214	00199	NE  	2005	2	14	CA040928005      	2	20040908	G	8520	19559	IMPELLER        			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								201831			(CAN) DURING CLIMB THE ENGINE LOST POWER AND HAD MAJOR OIL LEAKAGE. THE AIRCRAFT LANDED WITHOUT INCIDENT AND WAS RETURNE	D TO DOCK. INSPECTION FOUND THAT THE IMPELLER ASSY HAD FAILED RESULTING IN ENGINE POWER LOSS AND OIL LEAKAGE. ENGINE REM	OVED AND IS TO BE SENT TO OVERHAUL FACILITY FOR TEARDOWN AND REPAIR.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
2005041800039	20050418	00039	WP  	2005	4	18	CA040928006      	1	20040924	G	3244		TIRE            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) HIGH VIBRATION REPORTED FROM NOSE WHEEL DURING TAKE OFF ROLL.  THE TAKE OFF WAS ABORTED.  BOTH NOSE WHEELS FOUND O	UT OF ROUND.  BOTH WHEELS REPLACED AND AIRCRAFT DISPATCHED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004121000036	20041210	00036	EA  	2004	12	10	CA040928007      	1	20040920	G	2731	C3CF4205	ROD END         			DHAV  	DHC3  	DHC3        	2800202	EA  										ELEVATOR SERVO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT ROD END ON PUSH ROD PN F3I-14 WORN OUT AND STC ROD END PN M34-14.  ALSO, FOUND WORN OUT PLUS ELEVATOR HINGE PI	N C2TP199 AND HINGE PIN C3TF7-5 AND OUTER BEARING KP5A, ALL FOUND WITH EXCESSIVE WEAR AFTER ONLY 100 HOURS OF OPERATION 	UNDER STC SA01059SE.				1	H	7	1 	3R				A815
2005041800040	20050418	00040	EU  	2005	4	18	CA040928008      	1	20040927	G	2913	40165	PUMP            			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					HYD SYSTEM	NOISY           	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY INSPECTION PILOT NOTICED AN UNUSUAL WHINING NOISE COMING FROM THE NR 1 HYDRAULIC PUMP WHILE HE WAS TU	RNING THE MAIN ROTOR BLADES. THE HYDRAULIC PUMPS ARE DRIVEN BY THE MAIN TRANSMISSION AND WILL BE DRIVEN WHENEVER THE ROT	OR SYSTEM IS TURNED.  THE PILOT CONTACTED ENGINEERING AND THE AIRCRAFT WAS GROUNDED.  RESEARCH SHOWED THAT THIS PUMP WAS	 ONLY 78.4 HRS,  8 CALENDAR MONTHS TIME SINCE REPAIR BY VENDOR.  A REPLACEMENT PUMP WAS ORDERED AND THE FAULTY PUMP SENT	 BACK FOR INSPECTION/REPAIR. AWAITING EVALUATION.		1	G	7	2 	3U	3	U		H13EU   	E5NE10
2005012100182	20050121	00182	SW  	2005	1	21	CA040928009      	1	20040927	G	5302	206031314037	LONGERON        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAILBOOM SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE MAINTENANCE CREW WERE DOING A 600 HOUR INSPECTION ON THE AIRFRAME AS PART OF THE INSPECTION.  THE FUSELAGE TO 	TAILBOOM SUPPORT REQUIRES A VISUAL INSPECTION.  FOUND A SLIGHT BLACK MARK NEAR THE UPPER FUSELAGE SUPPORT FOR THE TAILBO	OM. THE AREA WAS CLEANED UP AND INSPECTED AGAIN AND WITH A MAGNIFYING GLASS IT WAS DETERMINED THAT THE CHANNEL OR LONGER	ON WAS CRACKED.			1	G	7	1 	3U	3	U		H2SW    	E1GL
2005041800041	20050418	00041	EA  	2005	4	18	CA040928010      	2	20040927	G	7230	3024211	COMPRESSOR      								PWA   	PT6T  	PT6T6       	52045	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE COMPRESSOR TURBINE DISK WAS INSTALLED ON AGUSTA BELL AB212.  A CRACK INDICATION WAS FOUND DURING OVERHAUL NDT.	  PWC WILL CONDUCT INVESTIGATION TO ESTABLISH ROOT CAUSE.										4	U			E22EA
2005041800042	20050418	00042		2005	4	18	CA040928011      	3	20040927	G	6110	310703601	SHAFT           			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE PROP SHAFT FOUND TO HAVE CRACKED ADJACENT TO A PREVIOUSLY REPAIRED DIAMETER (OVERHAUL, NOV 2001). PWC WILL INV	ESTIGATE TO ESTABLISH ROOT CAUSE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
2005012100184	20050121	00184	EA  	2005	1	21	CA040928012      	1	20040520	G	2730	C2CF815A	CONTROL CABLE   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	LT ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							1236				(CAN) DURING INSPECTION THE LT ELEVATOR CONTROL CABLE WAS FOUND FRAYED AT FWD PULLEY (LOCATED UNDER BATTERY BOX COMPARTM	ENT).  BATTERY ACID CORROSION NOT EVIDENT AT LOCATION OF FRAYED CABLE.  REPLACED CABLE.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
2004122900148	20041229	00148	EA  	2004	12	29	CA040928013      	1	20040730	G	2432		WIRE            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ALTERNATOR	GROUNDED        	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING VFR FLIGHT THE ELECTRICAL CHARGING SYSTEM FAILED. AIRCRAFT LANDED AT MAINTENANCE FACILITY. VOLTAGE CONTROLL	ER FOUND TO BE BURNED INTERNALLY PROBABLY DUE TO GROUNDED FIELD WIRE IN ALTERNATOR. FIELD WIRE IN ALTERNATOR REPAIRED. I	NSTALLED NEW VOLTAGE CONTROLLER.GROUND RUN SATISFACTORY. AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3R	3	R		A806    	5E1
2005041800043	20050418	00043	EA  	2005	4	18	CA040928014      	2	20040927	G	7200		ENGINE          			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  					LEFT	FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			CA											(CAN) ON DESCENT TO LAND, THE PILOT HEARD A LOUD BANG AND LOSS OF TQ IN THE LT ENGINE. ALL OTHER INDICATIONS WERE NORMAL	. THEY SECURED THE LEFT ENGINE AND MADE A NORMAL LANDING.					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA
2004101300067	20041013	00067	GL  	2004	10	13	CA040928015      	2	20040928	G	7261		CHECK VALVE     								ALLSN 	250B  	250B*       	 	GL  					ENGINE OIL	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								CAT34998			(CAN) OIL CHECK VALVE INSTALLED BACKWARDS RESULTING NR 8 BEARING FAILURE.											3	T			E10CE
2004101800109	20041018	00109	EA  	2004	10	18	CA040928016      	2	20040719	G	7250	3017393	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					AFCU	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) UNCOMANDED DECEL TO IDLE. PART CHANGED, ENGINE RETURNED TO NORMAL OPS.						1	G	7	1 	4U	4	U		H4SW    	E22EA
2005020700001	20050207	00001	NE  	2005	2	7	CA040929001      	2	20040924	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2	INOPERATIVE     	W				A				UNSCHED LANDING         				D	Y		INFLIGHT SEPARATION       	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								873018			(CAN) AT 500 FT THERE WAS A LOUD BANG AND THE NR 2 ENGINE SHUT DOWN, DECLARED AN EMERGENCY.  LANDED WITHOUT INCIDENT.  E	NGINE REPLACED.  OVERWEIGHT LANDING INSPECTION ALSO REQUIRED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005020700002	20050207	00002	CE  	2005	2	7	CA040929002      	1	20040928	G	5343	2310537	WEB             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19903								(CAN) DURING A SCHEDULE INSPECTION, (AIRFRAME 3 MONTHS HUMP IRN G3200000) LOOSENESS WAS FOUND ON THE NOSE LANDING GEAR A	CTUATOR UPPER ATTACHMENT POINT. THE ACTUATOR WAS REMOVED FOR ACCESS.  DETAIL EXAMINATIONON THE UPPER ATTACHMENT BRACKET 	AND ACTUATOR HOUSING WAS COMPLETED. THE TWO WEBS P/N 2310532-11 AND -12 WERE FOUND CRACKED. THE TWO CHANNELS P/N 2410510	-8 AND -9 WERE ALSO FOUND CRACKED. THE PARTS ATTACH ON THE FORWARD PRESSURE BULKHEAD (FRAME 5).			2	L	7	2 	4F	4	F		A10CE   	E6WE
2005012100177	20050121	00177	EU  	2005	1	21	CA040929003      	1	20040927	G	6710	350A37150803	ROD END         	SNIAS       		SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					PITCH LINK	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) VIBRATION ANALYSIS EQUIPMENT WAS INSTALLED ON THE AIRCRAFT AFTER THE PILOT COMPLAINED IT WAS GETTING ROUGH. THE FI	RST FLIGHT REVEALED THE A/C WAS INDEED ROUGH AND WHEN A PITCH LINK ADJUSTMENT WAS MADE, THE LOWER ROD END ON THE BLUE PI	TCH LINK WAS FOUND TO HAVE SEPARATED FROM THE SPHERICAL BEARING. THE SWASH PLATE ASSY SUFFERED OUT OF LIMIT DAMAGE DUE T	O THE ROD END RUBBING ON IT. THE SWASH PLATE ASSY AND THE THREE PITCH LINKS ARE IN THE PROCESS OF BEING REPLACED.			1	G	7	1 	3U	3	U		H9EU    	E5NE
2004111000060	20041110	00060	CE  	2004	11	10	CA040929004      	1	20040925	G	7921	509102751229	SCOOP           	BEECH       		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	OIL COOLER	DEPARTED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA			30318								(CAN) ON APPROACH TO AIRPORT THE LT OIL SCOOP DEPARTED THE AIRCRAFT.  THE SECURING FASTENERS WERE FOUND STILL ATTACHED T	O THE BOTTOM OF THE NACELLE.  PIECES OF FIBERGLASS WERE STILL UNDER THE HARDWARE.  THERE WAS SLIGHT SHEET METAL DAMAGE T	O THE BOTTOM OF THE NACELLE.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
2004101800110	20041018	00110	NE  	2004	10	18	CA040929005      	2	20040723	G	7310	31J251302	MANIFOLD        			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					FUEL SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	X	J	FLUID LOSS                	ENGINE FLAMEOUT           	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) INVESTIGATION OF AN UNCOMMANDED ENGINE IFSD REVEALED FUEL LEAKAGE AT THE ENGINE FUEL MANIFOLD.  THE MANIFOLD IS UN	DER INVESTIGATION AT MFG. THIS REPORT WILL BE SUPPLEMENTED TO PROVIDE ROOT CAUSE, ONCE ESTABLISHED.					1	L	7	2 	4F	4	F		A22CE   	E00053EN
2004101800111	20041018	00111	GL  	2004	10	18	CA040929006      	3	20040929	G	6114	D613276C0	HUB             	MCAULY      		MAULE 	M5    	M5210C      	5460134	SO  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						774272					(CAN) PROPELLER WAS REMOVED FROM AIRCRAFT FOR 10 YR. CALENDAR O/H.  UPON INSPECTION THE HUB WAS FOUND TO BE CORRODED EXT	ERNALLY BEYOND REPAIR LIMITS.  BLADE S/N K32294YS WAS FOUND TO BE CORRODED IN THE BLADE THREADS IN A LOCATION WHERE NO R	EPAIR IS ALLOWED. THE MANUFACTURER  RECOMMENDED CALENDAR O/H IS 60 MONTHS.				1	H	7	1 	3O	3	O		3A23    	E1CE	5	C	P3EA
2004101800112	20041018	00112	GL  	2004	10	18	CA040929007      	3	20040929	G	6114	D6132	HUB             			MAULE 	M5    	M5210C      	5460134	SO  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						774272					(CAN) PROPELLER WAS REMOVED FOR 10 YR. CALENDAR O/H. UPON INSPECTION THE HUB WAS FOUND TO BE CORRODED BEYOND REPAIRABLE 	LIMITS. ALSO DURING THIS INSPECTION BLADE M/N76C-0, S/N K32294YS WAS FOUND TO HAVE CORROSION BELOW THE BLADE THREAD PITC	H LINE IN AN AREA WHERE NO REPAIR IS ALLOWED.  THIS PROPELLER HAS EXCEEDED THE MANUFACTURERS RECOMMENDED CALENDAR TBO OF	 60 MONTHS BY 60 MONTHS.			1	H	7	1 	3O	3	O		3A23    	E1CE	5	C	P3EA
2005031100042	20050311	00042	EA  	2005	3	11	CA040929008      	2	20040913	G	7250		COVER           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NR 3 BEARNG	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOTS NOTED THE ENGINE OIL GETTING DARKER AND THE ENGINE ITT GETTING HIGHER.  MAINTENANCE INSPECTED THE ENGINE AN	D FOUND THAT THE NR3 BRG COVER HAD TURNED AND CAUSED THE EXHAUST DUCT TO CRACK AND SEPARATE INTERNALLY. THE PT BLADES HA	D RUB MARK AND ALSO THE PT DISK WAS SCRAPPED. PARTS WERE REPLACED AND RETURNED TOO SERVICE. THE EXHAUST DUCT DID NOT HAV	E SB1430 ACCOMPLISHED WHICH STOPS THIS FROM HAPPENING.			1	L	7	2 	3T	4	T		A14CE   	E4EA
2005041800044	20050418	00044	SO  	2005	4	18	CA040930001      	1	20040922	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								L787161A			(CAN) AFTER A SCHEDULED LANDING THE PILOTS FOUND A POOL OF OIL UNDER THE RIGHT HAND ENGINE.  MAINTENANCE FOUND THE NEWLY	 INSTALLED TURBOCHARGER HAD THE OIL SEAL FAIL IN THE INTAKE SIDE PUMPING EXCESSIVE OILINTO THE ENGINE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005020100128	20050201	00128	CE  	2005	2	1	CA040930002      	1	20040929	G	5730	14220006	SKIN            			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, CRACKS WERE DISCOVERED AT THE IB END OF THE LT AND RT UPPER OB WING SKINS WHERE THEY UNDERLAP T	HE FUEL TANK BAY COVERS. THE CRACKS ARE LOCATED IN THE RADIUS OF CUTOUT AREAS IN THE SKINS WHERE THE STINGERS JOIN AT WI	NG STATION 150.0.  THE AIRCRAFT IS EQUIPPED WITH FLINT WING TIP FUEL TANKS THAT WERE INSTALLED APPROXIMATELY 800 HOURS A	GO. IT IS NOT KNOWN IF THIS IS A CONTRIBUTING FACTOR.			1	H	7	2 	3O	3	O		A6CE    	E9CE	5	C	P5EA
2005041800045	20050418	00045	EU  	2005	4	18	CA040930003      	1	20040929	G	5610	1379628C402	WINDOW          			BAG   	JETSTM	JETSTM3212  	1500217	EU  										COCKPIT	CRAZED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT 21000 FT IN CRUISING CONFIGURATION, THE RT WINDSHIELD SUDDENLY CRAZED. THE WINDSHIELD RETAINED ITS SHAPE AND TH	ERE WAS NO CHANGE IN CABIN PRESSURE. DESCENT WAS COMMENCED AND THE CABIN ALTITUDE WAS INCREASED TO REDUCE DIFFERENTIAL P	RESSURE. QRH WAS CONSULTED AND A NORMAL DESCENT AND LANDING WAS CARRIED OUT AT FORT SMITH AIRPORT WITH NO FURTHER CHANGE	 IN THE STATUS OF THE WINDSHIELD.  A MAINTENANCE INSPECTION CONFIRMED THE OUTER AND INNER PLY TO BE INTACT.  THIS WINDSH	IELD HAD BEEN REPAIRED JANUARY 2004 AND INSTALLED IN THE AIRCRAFT MARCH 2004.		2	L	7	2 	4T			RT	BA15CAA
2005041800046	20050418	00046	EA  	2005	4	18	CA040930004      	2	20040914	G	8530	74636	ROCKER          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CYLINDER	SPLIT           	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA								L3418227A			ON CLIMB-OUT, ENG RUNNING ROUGH, BACKFIRING, SHAKING VIOLENTLY. INSTRUCTOR LEVELED OFF & REDUCED POWER, ENG SMOOTHED OUT	 BUT STILL RAN ROUGH. A/C RETURNED & LANDED W/O INCIDENT. ENGINEERS IDENTIFIED A PROBLEM WITH NR 2 CYLINDER. INVEST CYLI	NDER FOUND EXHAUST ROCKER ARM SPLIT & BENT ACROSS UNDERSIDE BY OIL LUBE HOLE. EXHAUST VALVE LEFT IN CLOSED POSITION BY R	OCKER FAILURE. INTAKE AIR INLET SCREEN FOUND BULGED OUT BUT NO OTHER DAMAGE FOUND. ENG SHOP INFORMED & NEW PARTS INSTALL	ED. ENG HAS 2343 HRS SINCE O/H. AFFECTED CYLINDER HAD BEEN REPLACED RECENTLY WITH AN OVERHAULED ONE & HAD ONLY FLOWN 28.	0 HRS.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005020100129	20050201	00129	GL  	2005	2	1	CA040930006      	3	20040924	G	6111	P5855BSW	PAD             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP DEICE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									842046		(CAN) AFTER FLIGHT, PILOT SAW ON RT PROPELLER, ONE PROP DE-ICE PAD MISSING ON ONE BLADE.  AFTER INSPECTION OF THE DEFECT	, WE SAW THE GLUE WAS NOT HARD. THE DE-ICE PAD WAS INSTALLED AT O/H SHOP WITH NEW KIND OF GLUE.  WE REMOVED THE OLD GLUE	 AND REINSTALLED A NEW DE-ICE PAD WITH CONTACT GLUE (3M 1300L). AIRCRAFT RETURNED TO SERVICE AFTER REPAIR.NOTE: IT'S NOT	 THE FIRST TIME THIS PROBLEM APPEAR DUE TO THIS NEW KIND OF GLUE.			1	L	7	2 	3O				A7CE    		5	C	P22EA
2005012100178	20050121	00178	GL  	2005	1	21	CA040930007      	1	20040928	G	2750	763077J	CONTROL UNIT    			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					SLAT/FLAPS	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE, THE CREW REPORTED THAT THE NR 2 SFCU CIRCUIT BREAKER POPPED TWICE AND WERE RESET TWICE	.  THEY THEN SMELLED SMOKE COMING FROM THE AVIONICS BAY.  THE SOURCE OF SMOKE WAS TRACED BACK TO THE SFCU. THE SFCU WAS 	REMOVED AND WAS FOUND TO HAVE TWO (2) HOLES BURNED THROUGH ON THE SIDE. THE BOX WAS REMOVED FROM THE RACK.				2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN
2005012100165	20050121	00165	SO  	2005	1	21	CA041001002      	1	20040921	G	3230	4194902	DOWNLOCK ARM    			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MLG	STUCK           	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) LT GEAR DOWN LOCK ROD FOUND STUCK IN RETACT POSITION.  REMOVED ROD, CLEANED LUBRICATED AND CYCLED LANDING GEAR.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005020100104	20050201	00104	SO  	2005	2	1	CA041001003      	1	20040928	G	5311	6269504	FRAME           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11251								(CAN) FUSELAGE FRAME, PN 62695-04 AT STA 73.04 FOUND CRACKED, BUCKLED 4.5 IN FROM OUTER EDGE ON RT SIDE. THIS CHANNEL IS	 IN SHAPE OF A HAT SECTION AND WAS COMPLETELY CRACKED FROM FLANGE TO FLANGE. THIS CHANNEL SUPPORTS WING FWD ATTACHMENT L	UG, IB OF FITTING PBN 62448-03. FRAME IS 6.75 FT WIDE AND WAS BUCKLED FROM TOP TO BOTTOM. CRACK EXTENDED THROUGH BOTTOM 	FLANGE RIVETED TO OUTER SKIN AND ROSE 2' UP WEB OF FRAME. THIS FRAME SUPPORTS WING REAR ATTACHMENT LUGS THROUGH FITTINGS	 PN 62448-03 AND 62448-02. FITTINGS ARE STEEL AND RIVETED TO ALUMINUM CHANNEL. RIVETS WERE CORRODED TO POINT MANY HEADS 	FELL OFF.  AC OPERATED IN SALT WATER, WINDOWS ABOVE STRUCTURE LEAKED ALLOWING WATER AND SALT TO ENTER CABIN AREA.	1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
2005020100134	20050201	00134	NE  	2005	2	1	CA041001004      	2	20040929	G	7230		ENGINE          			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					NR 1	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA								891269			(CAN) AIRCRAFT REPORTED STRONG ODOR THROUGHOUT THE CABIN AND FLIGHT DECK IN CLIMB. NO SMOKE VISIBLE. CREW RAN AIR CONDIT	IONING IN MANUAL/AIR MIX VALVES COLD, SMELL DISSIPATED. AIRCRAFT RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT.  NO 	EMERGENCY WAS DECLARED. MAINTENANCE CONDUCTED ENGINE RUNS ON BOTH ENGINES AT 70 PERCENT N2 FOR 10 MINUTES WITH EACH CORR	ESPONDING PACK RUNNING IN HOTMODE. ODOR DISSIPATED GRADUALLY.  SYSTEM CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE	 WITH NO FURTHER INCIDENTS TO REPORT.  NOTE: PREVIOUS NIGHT MAINTENANCE INCLUDED NR 1 ENGINE FAN BLADE LUBE/INSPECTION T	ASK NR 95-072-00-01.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2005012100179	20050121	00179	NM  	2005	1	21	CA041001005      	1	20040913	G	2751	2061131	INDICATOR       			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					FLAP POSITION	FAILED          	W				J				DUMP FUEL               				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF DURING FLAP RETRACTION, BOTH IB AND OB FLAPS STOPPED BETWEEN FLAP POSITION 5 AND 2.  AIRCRAFT DUMPE	D FUEL AND RETURNED TO STATION.  RECTIFICATION AFTER SEVERAL SUCCESSFUL ATTEMPTS, FAULT DUPLICATED ON GROUND FAULTING TH	E IB FLAP POSITION INDICATOR.  POSITION INDICATOR REPLACED, SYSTEM CHECK SERVICEABLE IAW MM27-52-1-11.  SUBSEQUENT RIGGI	NG OF FLAP CONTROLS WAS CARRIED OUT.			2	L	7	3 	4F	4	F		A3WE    	E2EA
2004111000062	20041110	00062	SW  	2004	11	10	CA041001006      	1	20040921	G	2842	206063613003	DETECTOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K	P		FLUID LOSS                	NO WARNING INDICATION     		IN	INSP/MAINT     	1			CA											(CAN) WHILE RESEARCHING ASB 206L-04-132, FOUND LOW FUEL DETECTOR SEEPING. DRAINED FUEL SYSTEM TO CHECK LOW LEVEL INDICAT	OR OPERATIONS AND QUANTITY. LOW FUEL LIGHT FOUND DISCONNECTED. UPON CONNECTING, LOW FUEL LIGHT WOULD NOT GO OUT AFTER 11	0LBS FUEL ADDED TO TANK. DETECTOR REMOVED, FOUND TO HAVE POOR REPAIRS. ITEM SEALED WITH SILICONE LEAKED. SUBSEQUENTLY TH	E SWITCH FELL APART WHEN HANDLED. NEW SWITCH INSTALLED AND OPERATIONS CHECKED FOR CORRECT INDICATION.			1	G	7	1 	3U	3	U		H2SW    	E1GL
2004111000063	20041110	00063	SO  	2004	11	10	CA041001007      	1	20040927	G	5320	4177100	BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NG UP SWITCH	BENT            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER GEAR UP SELECTED, FLT CREW DISCOVERED THE GEAR IN TRANSIT IND. ILLUMINATED. A/C RETURNED WITH 3 GREENS. A/C 	WAS PUT ON JACKS, GEAR CYCLED AND NOTICED THE NLG TORQUE TUBE SWITCH BRACKET WAS BENT RESTRICTING THE UP-LOCK SWITCH FRO	M CONTACTING.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004111000064	20041110	00064	EA  	2004	11	10	CA041001008      	1	20040929	G	1430	B42624	BARREL NUT      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE MOUNT	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN TORQUE CHECK OF ENGINE MOUNT BOLTS PERFORMED OB BOLT CORRECT TORQUE COULD NOT BE ACHIEVED.  BARREL NUT REMOVE	D AND FOUND TO HAVE DAMAGED THREADS AND WAS OF FIBER LOCK STYLE.  BARRREL NUT AND BOLT REPLACED WITH IPC REQUIRED PARTS.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2005020100146	20050201	00146	SO  	2005	2	1	CA041001011      	2	20040913	G	7414	6310	MAGNETO         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	RIGHT	ARCED           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED A 200 RPM DROP ON RT MAGNETO. TROUBLESHOOTING REVEALED THAT TOP IGNITION WIRE ON NR 5 CYLINDER WAS 	UNSERVICEABLE.  WHEN HARNESS WAS REMOVED FROM MAGNETO, EVIDENCE OF HEAVY ARCING WAS NOTED IN THE NR 5 LEAD OUTLET AREA O	F THE DISTRIBUTOR BLOCK.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL
2004122300025	20041223	00025	NE  	2004	12	23	CA041001012      	2	20040921	G	7200		ENGINE          								PWA   	JD15  	JT15D1A     	 	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								77128			ENGINE WAS REMOVED FROM THE WING AFTER THE CUSTOMER THOUGHT THAT THE ENGINE HAD SUSTAINED A HIGH TURBINE BLADE FAILURE. 	 THE ENGINE WAS SHIPPED TO ATLANTIC TURBINES FOR INVESTIGATION AND REPAIR.  NO SIGNIFICANT DAMAGE WAS FOUND UPSTREAM OF 	THE HIGH PRESSURE TURBINE IT HAS BEEN CONCLUDED THAT THIS ENGINE DID SUSTAIN A HIGH TURBINE BLADE FAILURE.  IT IS ATLANT	IC TURBINES OPINION THAT THIS ENGINE DID SUFFER AN HP TURBINE BLADE FAILURE SINCE THERE WAS NO UPSTREAM DAMAGE PRIOR TO 	THE HPT DISK.  ALL DAMAGE DOWNSTREAM IS THOUGHT TO BE SECONDARY DAMAGE CAUSED BY THE LIBERATED MATERIAL FROM THE HIGH TU	RBINE BLADES.  THE SECONDARY DAMAGE IS CONCENTRATED MAINLY TO THE 2ND STAGE STATOR AND ROTOR.						4	F			E25EA
2004111000065	20041110	00065	CE  	2004	11	10	CA041001013      	1	20040928	G	5740	351150582	FITTING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE WING BOLT INSPECTION, THE LT LOWER AFT BATHTUB FITTING WAS FOUND TO HAVE CHAFE MARK FROM CONTACT WITH T	HE CLIP ON THE WING FITTING COVER. ONE MARK EXTENDED INTO THE FITTING RADIUS. MFG WAS CONSULTED AND SENT OUT A FIELD REP	AIR TO REMOVE THE DAMAGE. EACH BATHTUB FITTING COVER IS HELD IN PLACE BY A SPRING STEEL CLIP THAT GRIPS THE WING FITTING	 AT ONE END WHILE THE OTHER END IS HELD IN PLACE BY A SCREW.  IT APPEARS THAT THE COVER MAY HAVE BEEN A LITTLE LOOSE ALL	OWING IT TO FLUTTER OR VIBRATE AND CAUSING THE CLIP TO CHAFE THE WING FITTING.		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005012100163	20050121	00163	EA  	2005	1	21	CA041001014      	1	20040928	G	7110	A33721	STRUT           			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					UPPER CORE COWL	UNSECURE        	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) DURING A FLIGHT AFTER MAINTENANCE, AIRCRAFT WAS IN CLIMB TO FL330 WHEN THROTTLES WERE PULLED BACK.  CREW WAS UNABL	E TO RETARD LT ENGINE THROTTLE.   AIRCRAFT DESCENDED TO FL100 WHERE AN EMERGENCY WAS DECLARED AND THE LT ENGINE FIRE SHU	TOFF, PBA WAS PUSHED.   AN UNEVENTFUL LANDING WAS MADE.  MAINTENANCE FOUND THE UPPER COWL SUPPORT STRUT NOT SECURED AND 	FOULING THE FUEL CONTROL UNIT LEVER ARM.  THE AIRCRAFT THROTTLE SYSTEM WAS CHECKED FOR DAMAGE.  AIRCRAFT RETURNED TO SER	VICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004121000047	20041210	00047	NM  	2004	12	10	CA041004001      	1	20041002	G	2932	7G772	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 45 NAUTICAL MILES NORTH EAST OF BASE, THE 'NR 2 RUD HYD' CAUTION LIGHT ILLUMINATED. FOLLOWING COMPLE	TION OF QRH DRILLS THE CREW ELECTED TO RETURN THE AIRCRAFT TO BASE WHERE A NORMAL APPROACH AND LANDING WAS CARRIED OUT. 	ENGINEERING INVESTIGATION REVEALED THAT THE NUMBER TWO RUDDER HYDRAULIC PRESSURE SWITCH HAD FAILED. THE PRESSURE SWITCH 	WAS REPLACED AND FOLLOWING REQUIRED FUNCTIONAL CHECKS THE AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. AIR	CRAFT STATISTICS:TTSN = 12504 HRSTCSN = 11315 CYC.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005012100164	20050121	00164	EA  	2005	1	21	CA041004002      	2	20041001	G	8520	LW18402	CRANKCASE       			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								1067239A			(CAN) RT CRANKCASE IS CRACKED AT THE ALTERNATOR TENSIONING ARM ATTACHMENT BOSS.  CRACK APPROX .5 IN LONG BEGINS AT THE B	OLT HOLE WHERE TENSIONING ARM ATTACHES TO CRANKCASE AND EXTENDS IN AN AFT DIRECTION.  ENGINE REMOVED FOR REPAIR.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005021400193	20050214	00193	CE  	2005	2	14	CA041004003      	1	20040926	G	3242	114800817	DISC            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	BRAKES	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AUG951916					(CAN) ON PUSH BACK INTO THE HANGAR AN UNUSUAL NOISE WAS HEARD FROM NR 2 MAINWHEEL. ON REMOVING THE MAIN WHEEL, A SECTION	 OF THE STATIONARY DISC FELL OUT OF THE BRAKE ASSEMBLY.  WHEN THE BRAKE ASSY WAS REMOVED THE REST OF THE STATIONARY DISC	 WAS REMOVED WITHOUT DISSAMBLY OF THE BRAKE. THE INNER HALF OF THE MAIN WHEEL WAS SCORED BY THE BRAKE DISC AND WAS REPLA	CED ALONG WITH THE BRAKE ASSEMBLY. WHEN THE BRAKE WAS LAST REPAIRED THE DISC WAS EXAMINED AND FOUND TO BE SERVICABLE TO 	CONTINUE IN SERVICE WITHOUT REPLACING THE PADS.  THEREFORE NDT WAS NOT REQUIRED. THE BRAKE HAD COMPLETED 963.2 HRS AND 8	51 CYCLES DURING THIS INSTALLATION.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
2005021400192	20050214	00192	GL  	2005	2	14	CA041004004      	2	20040921	G	7314		PUMP            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	FUEL PRESS	OUT OF ADJUST   	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			59552								(CAN) AIRCRAFT DISPATCH LIKE USUAL FROM HANGAR WITH 28 PASSENGER ONBOARD AND CAME BACK DUE TO FUEL UNBALANCE AND ONE PAS	SENGER HAD REPORT SEEING FUEL COMING OUT OF RT HAND TANK OVERWING FUEL CAP AND CREW REALIZED IT HAD TAKEN OFF WITH FUEL 	CROSS-FEED OPEN.  MAINTENANCE TRANSFERED SOME FUEL FROM RT TO LT USING TRANSFER HOSE. OVERWEIGHT LANDING INSPECTION C/O.	 AIRCRAFT RETURN TO SERVICE FOR THE FLIGHT.  ON RETURN MAINTENANCE INVESTIGATION REVEAL , LT PUMP PRESSURE WAS AT 21 PSI	 AND RT WAS AT 16 PSI. C/O FUEL PUMP PRESSURE ADJUSTMENT ON BOTH SIDES IAW APJCB 10-21.		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898
2005031100026	20050311	00026	GL  	2005	3	11	CA041004006      	1	20040908	G	2497	770699A	CONNECTOR       			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					P1	BURNED          	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			CA											(CAN) THE CREW SMELLED SMOKE IN THE COCKPIT AND RETURNED TO THE AIRPORT JUST AFTER TAKEOFF.  THEY HAD SEVERAL CIRCUIT BR	EAKER TRIPPED FOR THE DC BUS 1 ON THE EMSCDU AND EVENTUALLY THE DC BUSS 1 FEED 4, WHICH FEED SPDA 4 TRIPPED AS WELL.  SE	VERAL ANOMALIES WERE NOTED IN THE COCKPIT, SUCH AS LIGHTS AND SOME AVS EQUIPMENT GOING OFF.  UPON INSPECTION, THE P1 CON	NECTOR WAS FOUND BURNED ON SPDA 4.  THE CONNECTOR SEEMED TO BE WELDED TO THE SPDA. THE SPDA WAS REMOVED WITH THE CONNECT	OR STILL ATTACHED.   A NEW SPDA AND P1 WERE INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN
2005031400038	20050314	00038	NE  	2005	3	14	CA041005001      	2	20041002	G	8520	11768	CAM             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								89046			(CAN) THE ENGINE DEVELOPED A NOISE INDICATING A WORN CAM LOBE OR ROLLER.  SMALL AMOUNT OF METAL (STEEL ) FOUND IN ENGINE	 SUMP. TRACE AMOUNT OF METAL FOUND IN OIL SCREEN.  CAM REMOVED AND FOUND TO BE DAMAGED ON ONE EXHAUST LOBE.  INSTALLED N	EW CAM AND ROLLERS ON EXHAUST TAPPET ASSY.   ENGINE GROUND RUN SATISFACTORY.  FLIGHT TEST WAS SATISFACTORY.  SUMPS AND S	CREENS RECHECKED NO METAL PRESENT.			1	H	7	1 	3R	3	R		A815    	E142	6	C	P719
2004121000044	20041210	00044	WP  	2004	12	10	CA041005002      	1	20040908	G	5230		DOOR            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					CARGO	OUT OF RIG      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DISPATCH WITH 29 PASSENGER ABOARD AT 13:32 GMT AND CAME BACK AT 14:14 WITH C2 DOOR OPEN. MAINTENANCE DISC	OVERED THAT THE C2 DOOR COULD BE CLOSE IMPROPERLY IN SOME OCCASION AND NO DAMAGE WAS FOUND. MAINTENANCE CLOSE THE DOOR A	ND CONFIRM THE LOCK HAD ENGAGED, AIRCRAFT RETURN TO XXX NORMALLY. A VISUAL INSPECTION WAS C/O AGAIN OF THE DOOR AND DOOR	 FRAME, NO DAMAGE WAS FOUND. COMPLETE RIGGING OF DOOR WAS C/O IAW MAINTENANCE MANUAL AND AIRCRAFT RETURN TO SERVICE.			2	L	7	2 	4R	4	T		6A6     	E282
2005020100113	20050201	00113	SW  	2005	2	1	CA041005004      	1	20040923	G	6420	406012102109	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR HEAD	OVERSIZED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) T/R HUB FOUND TO HAVE 1.6255 - 1.6260,  INTERNAL DIAMETER FOR ELASTOMERIC FLAPPING BEARING INSTALL, OVERSIZE FROM 	.0002 TO .0007.					1	G	7	1 	3U			O	H2SW
2005020400006	20050204	00006	WP  	2005	2	4	CA041005005      	1	20041002	G	5230		SEAL            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CARGO DOOR	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, PRESSURE FLOW LIGHT CAME ON THRU 9000 FT AND COULD NOT PRESSURIZE THE AIRCRAFT.  AIRCRAFT LANDED BAC	K TO DEPARTURE AIRPORT.  MAINTENANCE FOUND THE MID CARGO DOOR SEAL AND THE EE COMPARTMENT DOOR SEAL NOT PROPERLY INSTALL	ED AND DAMAGED.  BOTH SEALS REPAIRED AND AIRCRAFT DISPATCHED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005020100136	20050201	00136	SW  	2005	2	1	CA041006001      	1	20040928	G	2741	A21810064603	TRIM SWITCH     			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					STABILIZER	STICKS          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) TRIM SWITCH STICKS WHEN PULLED FOR REAR ACTIVATION.  REPLACED SWITCH.						1	G	7	1 	3O	3	O	O	4H12    	E286
2004111000066	20041110	00066	NM  	2004	11	10	CA041006002      	1	20040921	G	2750	65404494	CONTROL VALVE   			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF DURING FLAP RETRACTION, BOTH IB AND OB FLAPS STOPPED BETWEEN FLAP POSITION 5 AND 2.  RECTIFICATION 	AFTER EXTENSIVE TROUBLESHOOTING CARRIED OUT. BOTH FLAP CONTROL VALVES WERE REPLACED. THE AIRCRAFT WAS TEST FLOWN WITHOUT	 ANY FURTHER PROBLEMS.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2005012100166	20050121	00166	EA  	2005	1	21	CA041006003      	1	20040917	G	2435	03600923	BEARING         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	STARTER GEN	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA						Y20071R					(CAN) NR 2 STARTER GEN CAUTION LIGHT ILLUMINATED DURING FLIGHT.  STARTER GEN REMOVED AND SENT TO COMPONENT SHOP.  UPON D	ISASSEMBLY THE BEARING FAILURE WAS CONFIRMED ON THE ANTI-DRIVE END HOUSING.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031400039	20050314	00039	SW  	2005	3	14	CA041006004      	1	20041004	G	5313	206032308003	LONGERON        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IN THE TASK OF CHANGING THE LONGERON, IT WAS VISUALLY NOTED THAT THIS FRAME WAS CRACKED IN TWO PLACES.  THE CRACKS	 WERE NEAR THE UPPER TWO ATTACHMENT POINTS OUT OF THE 4 ATTACHMENT POINTS.					1	G	7	1 	3U	3	U		H2SW    	E1GL
2005020100125	20050201	00125	SO  	2005	2	1	CA041006005      	2	20040922	G	7261	5100106236	LINE            			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT ENG OIL	CORRODED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT AND AME FLYING HOME TO BASE OBSERVED THE LT ENGINE OIL PRESSURE DECREASING AT A SLOW RATE, UNTIL DECISION MA	DE TO SHUT DOWN THE ENGINE AND LAND AT THE NEAREST AIRFIELD.  INVESTIGATION ON THE GROUND REVEALED OIL TO BE LEAKING FRO	M THIS LINE.  LINE REPLACED AND CONDITIONS RETURNED TO NORMAL. CONTINUED ON HOME.  NO FURTHER ACTION REQUIRED.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA
2004111500103	20041115	00103	NM  	2004	11	15	CA041006006      	1	20041005	G	2742	251T43101	ACTUATOR        			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					STABILIZER TRIM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			63609								(CAN) INSPECTION OF HORIZONTAL STABILIZER SCREWJACK DURING M01CHECK REVEALED EVIDENCE OF INTERNAL CORROSION AS A RESULT 	OF DISCOLORATION IN LUBRICANT.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004122200173	20041222	00173	EA  	2004	12	22	CA041006007      	2	20040928	G	7200	PT6A27	ENGINE          								PWA   	PT6   	PT6A27      	52043	EA  						FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA			22317								(CAN) ENG REMOVED FROM WING DUE TO INFLT SHUTDOWN CAUSED BY A POWER SECTION SEIZURE. ENG SENT TO ATLANTIC TURBINES FOR I	NVEST. POWER SECTION, POWER TURBINE & RIB, SUFFERED DAMAGE. POWER TURBINE DISK WAS NO LONGER COUPLED TO RIB INDICATES TH	AT A POSSIBILE PT OVERSPEED AFTER IT DECOUPLED. THIS WOULD BE SUFFICIENT TO CAUSE PT BLADES TO FRACTURE & DEPART DISK. T	HIS WOULD RESULT IN FRACTURES AT SIMILAR LOCATIONS ON ALL BLADES WHICH IS NOT SEEN HERE. EVIDENCE OF SUDDEN STOPPAGE CAU	SED BY 1ST STAGE GEARING. DAMAGE TO SUN GEAR & 1ST STAGE PLANET GEARS RESPONSIBLE FOR AMOUNT OF METAL CONTAMINATION. ATL	ANTIC TURBINES IS CONTINUING ITS INVESTI TO ATTEMPT TO DETERMINE WHAT THE PRIMARY FAILURE THAT CAUSED OTHER DAMAGE.						4	T			E4EA
2005031400040	20050314	00040	CE  	2005	3	14	CA041006008      	1	20040917	G	7603	MCC29950501	THROTTLE CABLE  			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ENGINE	BROKEN          	W				B				EMER. DESCENT           				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) PILOT MAKING AN APPROACH TO SCHEDULED LANDING WHEN ENGINE POWER WENT TO IDLE WITH NO RESPONSE TO ACTIONS OF THROTT	LE CONTROL.  PILOT ELECTED TO LAND IN FIELD SHORT OF RUNWAY AND EXPERIENCED NO DIFFICULTY. AIRCRAFT EQUIPPED WITH TUNDRA	 TIRES.  MAINTENANCE DETERMINED THE THROTTLE CABLE AT THE ENGINE CONNECTION HAD FAILED.  THROTTLE CABLE WAS REPLACED AND	 AIRCRAFT FLOWN FROM FIELD.  NO FURTHER ACTION REQUIRED.  P/N MCC299505-01 IS A PMA PART.			1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P25EA
2005031400041	20050314	00041	NM  	2005	3	14	CA041007001      	1	20041005	G	4997		WIRE            	GARRTT      		BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) JUST PRIOR TO ENGINE START AT AN OUTBASE, THE A/C APU SHUT DOWN ON ITS OWN.  GROUND EQUIPMENT WAS USED TO POWER AN	D START THE A/C, AND THE FLIGHT CONTINUED. AT THE TERMINATING BASE, MAINTENANCE PERSONNEL FOUND 2 WIRES AT THE APU THAT 	HAD CHAFED AND SHORTED AGAINST EACH OTHER. THE WIRES WERE REPAIRED AND THE A/C RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2005071200027	20050712	00027	SW  	2005	7	12	CA041007002      	1	20041006	G	6420	206011810117	TAIL ROTOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						MISRIGGED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR FLAPPING ANGLE FOUND SET TO 18 DEGREES INSTEAD OF THE CORRECT ANGLE OF 12 DEGREES ALLOWING POSSIBLE COT	ACT WITH TAILBOOM					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005031400042	20050314	00042	NE  	2005	3	14	CA041007003      	2	20040929	G	7261	DSC3912	HOSE            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE OIL	RUPTURED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			15305								(CAN) THE NR2 ENGINE OIL PRESSURE WARNING LIGHT ILLUMINATED WITH A CORRESPONDING FALLING OIL PRESSURE GAUGE READING.  US	ING QRH PROCEDURES THE NR2 ENGINE WAS SHUT DOWN AND A PAN DECLARED.  THE CREW THEN RETURNED THE AIRCRAFT TO BASE WHERE A	 SINGLE ENGINE APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT.  A LARGE QUANTITY OF ENGINE OIL LOSS WAS IDENTIFIE	D ON THE ENGINE AND ENGINEERING INVESTIGATION REVEALED A RUPTURE, FAILURE OF THE OB ENGINE OIL TANK TO OIL COOLER FLEXIB	LE HOSE ASSEMBLY. THE FAILED HOSE ASSEMBLY WAS REPLACED AND FOLLOWING SATISFACTORY COMPLETION OF REQUIRED MAINTENANCE CH	ECKS THE AIRCRAFT WAS RELEASED BACK TO SERVICE WITHOUT FURTHER INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100126	20050201	00126	GL  	2005	2	1	CA041007004      	2	20040927	G	7261	3579501200	GEAR            			BELL  	206   	206BELL     	1181502	SW  	ALLSN 	250C  	250C18      	03011	GL  					OIL PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS IS THE OIL PUMP GEAR THAT DRIVES THE HYDRAULIC PUMP ON THE AC, GREASING INTERVAL IS 300 HRS.  THIS SHAFT WAS 	GREASED EVERY 100 HRS AND HAS TOTALLY WORN OUT.  THIS SHAFT ALSO WEARS OUT THE COUPLING IT ATTACHES TO, AS WELL.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2004111500104	20041115	00104	CE  	2004	11	15	CA041007005      	1	20041006	G	3243	98820125	PISTON          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MASTER CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10460								(CAN) PISTON BROKE IN THREADED PORTION, OUTSIDE OF MASTER CYLINDER, IMMEDIATELY BELOW JAM NUT. NO EVIDENCE OF FRETTING T	HAT WOULD INDICATE AN EARLIER PARTIAL BREAK.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005020100132	20050201	00132	NE  	2005	2	1	CA041007006      	2	20040922	G	7322	7423461	SLEEVE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					THROTTLE CABLE	WORN            	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING GROUND RUN OPERATIONS CHECK AFTER STARTER GENERATOR CHANGE THROTTLE WAS ADVANCED TO 70 PERCENT THEN RETARDE	D TO IDLE QUICKLY (1 SEC.). ENGINE FLAMED OUT. ENGINE RIGGING WAS CHECKED, THEN THE INNER CABLE OF THE AFT THROTTLE CABL	E WAS REMOVED AND INSPECTED.  FOUND THAT THE OUTSIDE SLEEVE ASSEMBLY COULD BE REMOVED EVEN WITH THE LOCK BOLT TIGHT AND 	THAT THE INNER CABLE WAS BEING PULLED OUT WHEN THE THROTTLE WAS QUICKLY RETARDED TO IDLE.			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA
2004111500105	20041115	00105	NM  	2004	11	15	CA041007007      	1	20041006	G	5751	NAS427K23	GUARD           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AILERON	MISSING         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT DEPARTED AIRPORT AND REPORTED AILERON CONTROLS STIFF. THE AIRCRAFT RETURNED TO WITHOUT FURTHER INCIDE	NT. UPON INVESTIGATION IT WAS FOUND THAT AN AILERON CABLE IN THE LT WING WAS DISLODGED FROM THE PULLEY. FURTHER INVESTIG	ATION SHOWED THE CABLE GUARD WAS MISSING. THE CABLE WAS INSPECTED AND REPOSITIONED ON THE PULLEY. WHEN CABLE TENSION WAS	 VERIFIED IT WAS FOUND BELOW LIMITS. THE ENTIRE AILERON CABLE SYSTEM WAS INSPECTED, RIGGED AND TENSIONED. NO OTHER FAULT	 S WERE FOUND AND THE AIRCRAFT WAS RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100167	20050201	00167	SW  	2005	2	1	CA041007008      	1	20041007	G	6710	212076101001	CONTROL TUBE    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WE ARE PRESENTLY DOING A 3000 HOUR AIRFRAME INSPECTION.  THIS VERTICAL UPPER SERVO CONTROL TUBE WAS SENT TO A  NDT	 SHOP FOR INSPECTION. THE NDT SHOP STATED THAT THEIR WAS A LONGDITUDANAL CRACK ON THE UPPER END OF CONTROL TUBE. SINCE T	HE LAST INSPECTION THE TUBE HAS 2617 HOURS ON IT. THE AIRFRAME TIME IS 28,644 HOURS.				1	G	7	1 	4U	4	U		H4SW    	E22EA
2005012100168	20050121	00168	SW  	2005	1	21	CA041007009      	1	20040929	G	5302	222035115103	SKIN            	BELL        		BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CARRYING OUT A DAILY CHECK IT WAS OBSERVED THAT A VERTICAL LATERAL CRACK HAD DEVELOPED ON THE LOWER SKIN OF TAILBO	OM JUST 5 INCHES AFT OF THE HORIZONTAL STABILIZER. THE SKIN IS 2024 T3 .032 IN.					1	G	7	2 	3U	3	U		H9SW    	E5NE
2004111500106	20041115	00106	WP  	2004	11	15	CA041008001      	1	20041005	G	2510	C3485	ANCHOR          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					SEAT BELT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION THE PILOTS IB SEAT BELT ATTACHMENT POINT HAD BEEN FOUND CRACKED. THE ANCHOR HAD BEEN P	ULLED SLIGHTLY AND THE ANCHOR BROKE COMPLETELY OFF. DURING INSPECTION SCHEDULES, THE CONCERNED AREA IS BEING CLOSELY MON	ITORED.				1	G	7	1 	3O	3	O		H11NM   	E295
2004111500107	20041115	00107	SW  	2004	11	15	CA041008002      	1	20041006	G	7334	8944416	REGULATOR       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	FUEL SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) UPON LANDING THE FLIGHT CREW NOTICED FUEL RUNNING OUT OF THE ENGINE COWLING AND DRIPPING FROM THE LT WHEEL WELL.  	MAINTENANCE WAS INFORMED AND DISCOVERED THAT THE START FUEL PRESSURE REGULATOR WAS LEAKING FUEL OUT OF THE ELECTRICAL CO	NNECTOR PORTION OF THE VALVE.  MAINTENANCE REPLACED THE REGULATOR VALVE AND GROUND RUN AND LEAK CHECKS WERE COMPLETED.  	THE NATURE OF THIS PROBLEM IS THE SAME AS A THE PROBLEM IDENTIFIED IN SB TPE331-73-026, UNFORTUNATLY THIS VALVE DOES NOT	 FALL WITHIN THE PN OR SN APPLICABILITY RANGE OF THIS SERVICE BULLETIN.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2004111500108	20041115	00108	NE  	2004	11	15	CA041008003      	2	20041005	G	7200		ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	545   	PW545A      	 	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL 410 THE N1 BEGAN FALLING BELOW 92 PERCENT.  CREW SECURED ENGINE WITH N1 AT 20 PERCENT AND 6000	 FT AGL.  PILOT DIVERTED AND LANDED WITHOUT INCIDENT.  UPON LANDING PILOT NOTED SMOKE COMING FROM THE INLET AND EXHAUST 	OF THE ENGINE.  THE ENGINE WILL BE INVESTIGATED BY MFG TO ESTABLISH ROOT CAUSE OF THE INCIDENT.  THIS SDR WILL BE UPDATE	D ONCE CAUSE HAS BEEN ESTABLISHED.			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2005041800047	20050418	00047	EA  	2005	4	18	CA041010001      	1	20041007	G	5610	NP1393211	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE AT FL360 AND 0.74 MACH, THE PILOT'S WINDSHIELD CRACKED.  DIVERTED FOR MAINTENANCE.  WINDSHIELD REPLACED,	 AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005041800048	20050418	00048	NE  	2005	4	18	CA041010002      	2	20041006	G	7230		COMPRESSOR      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RT ENGINE	STALLED         	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								965296			(CAN) DURING TAKE-OFF, THE RT ENGINE EXPERIENCED COMPRESSOR STALLS.  MAINTENANCE BORESCOPED THE RT ENGINE AND FOUND FOD 	DAMAGE IN THE COMPRESSOR SECTION.  ENGINE WAS THEN REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005041800049	20050418	00049	EA  	2005	4	18	CA041010003      	1	20041006	G	3230	533415	VALVE           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					DOWNLOCK	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CREW REPORTED HYD 2 LOW PRESS, NR 2 EDP FAIL, IB AND OB SPOILERS FAIL,  NR 2 HYD QUANTITY READING ZERO.  AIRCRAFT 	DIVERTED, DUE TO WEATHER.  MAINTENANCE FOUND THE MLG DOWNLOCK ASSIST VALVE LEAKING.  MAINTENANCE REPLACED THE DOWNLOCK A	SSIST VALVE, THE SYSTEM WAS TESTED AND THE AIRCRAFT WAS DECLARED SERVICEABLE.  NOTE: THE BYPASS VALVE (P/N 53342-3) WAS 	ALSO REPLACED AS A PRECAUTION DUE A MINOR LEAK.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005041800050	20050418	00050	NM  	2005	4	18	CA041012001      	1	20041011	G	2422	DH103024600C	INVERTER        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PRIMARY	FAILED          	W				G	A			O2 MASK DEPLOYED        	UNSCHED LANDING         			B	H	J	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        	CL	CLIMB          	1			CA											APPROXIMATELY 150 NM FROM BASE, CRUISING AT FL 230, WHEN CO-PILOT NOTICED A SUDDEN PUFF OF SMOKE FROM BEHIND CAPTAIN'S S	EAT.  A LOUD BANG & PRIMARY & AUXILIARY INVERTER LIGHTS ILLUMINATED.  ADDITIONAL WARNING LIGHTS ASSOCIATED WITH THESE FA	ILURES ALSO ILLUMINATED.  OXYGEN DRILL CARRIED OUT FOLLOWED BY FUSELAGE FIRE OR SMOKE DRILL.  IDENTIFIED PROBLEM AS PRIM	ARY INVERTER & AFTER COMPLETING THAT DRILL FROM QRH, AUX INVERTER RE-INSTATED.  UNSCHEDULED LANDING CARRIED OUT.  MX PER	SONNEL INSPECTION A/C & PERFORMED TROUBLESHOOTING ON INVERTER SYS.  FROM THIS, PRIMARY INVERTER CONFIRMED AT FAULT.  PRI	MARY INVERTER THEN REPLACED.  AIRCRAFT HAS RETURNED TO SERVICE WITHOUT FUTHER INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800051	20050418	00051	NM  	2005	4	18	CA041012002      	1	20041009	G	2910	65448917	HYDRAULIC SYSTEM			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					A-SYSTEM	INOPERATIVE     	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LOSS OF SYSTEM A-HYDS AT FL270, INDICATED BY SYSTEM A-FLT CONTROL LOW PRESSURE & FEEL DIFF PRESSURE LIGHT AND A-QT	Y AT .5 GALLONS.  ACRFT RETURNED TO AIRPORT. FLT CONTROL MODULE A-SYS REPLACED.  ALSO BOTH A & B CASE DRAIN FILTERS & BO	TH A-SYS HYD EDPS REPLACED.  TIMES- 58129.50  CYCLES- 54334.				2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041800052	20050418	00052	CE  	2005	4	18	CA041012004      	1	20040930	G	5610	0413419201	WINDSHIELD      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											DURING A ROUTINE TRAINING FLT FOR A-CLASS IV INSTRUCTOR RATING, WINDSHIELD CRACKED AND BLEW IN.  PRIOR TO WINDSHIELD BRE	AKING, INSTRUCTOR CANDIDATE HAD BEEN PERFORMING SPIRAL DIVE LESSON DEMONSTRATION WHEN THE WINDSHIELD BROKE, AND HAD JUST	 COMPLETED A RECOVERY.  DURING FLIGHT, AIR SMOOTH & MAXIMUM SPEED ESTIMATED AT 140 MPH (WELL BELOW THE VNE OF 162 MPH) A	ND AT NO TIME WERE ANY EXCESS G FORCES EXERTED ON THE AIRFRAME.  PRIOR TO THE BREAKAGE, THERE WAS NO EVIDENCE OF A CRACK	 OR DAMAGE TO THE WINDSHIELD.  AIRCRAFT WAS INSPECTED FOR OVERSTRESS OF THE AIRFRAME WITH NO FAULT FOUND.  PIECES RECOVE	RED OF THE WINDSHIELD SHOWED NO SIGN OF HEAVY CRAZING OR STRESS.  WINDSHIELD REPLACED AND AIRCRAFT RETURNED TO SERVICE.	1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2004122300026	20041223	00026	NM  	2004	12	23	CA041012005      	1	20040907	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	RT WING SPOILER	CRACKED         	W				D				RETURN TO BLOCK         				K	F		FLUID LOSS                	FLT CONT AFFECTED         		TX	TAXI/GRND HDL  	1			CA			35120								PILOT REPORTED THAT WHILE CARRYING OUT PRE FLIGHT FULL AND FREE MOVEMENT OF FLT CONTROL SURFACES THAT RT OUTBOARD ROLL S	POILER ACTUATOR POSITION INDICATOR WAS NOT INDICATING MOVEMENT WHEN THE FLIGHT CONTROLS WERE MOVED. A/C RETURNED TO THE 	BAY FOR FURTHER INVESTIGATION.  PILOTS REPORTED THAT HYD FLUID WAS RUNNING THE RT SIDE OF THE #2 ENGINE NACELLE AND CONT	ACTED ENGINEERING'. ENGINEERING CONDUCTED AN INVESTIGATION OF THE DEFECT AND DISCOVERED THAT THE RT OUTBOARD ROLL SPOILE	R ACTUATOR WAS LEAKING EXCESSIVE AMOUNTS OF FLUID DUE TO A FAILURE OF THE HOUSING. ROLL SPOILER ACTUATOR WAS REMOVED AND	 THE ACTUATOR END CAP ITEM 560 OF CMM 27-60-02 WAS FOUND TO HAVE SEPARATED THE HOUSING DUE TO A FAILURE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005012100180	20050121	00180	CE  	2005	1	21	CA041012006      	1	20041004	G	3340	CM358910	SWITCH          			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	MLG LIGHT	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SWITCH WAS HOT TO THE TOUCH DURING GROUND FUNCTIONAL TEST.  SWITCH DID NOT TRIP.  SWITCH WENT OPEN CIRCUIT AFTER C	OUPLE MINUTES.					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C
2005012100181	20050121	00181	NM  	2005	1	21	CA041012007      	1	20041008	G	2134	7G959	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	CABIN AIR	OUT OF TOLERANCE	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			16890								(CAN) CABIN ALTITUDE CLIMBED DURING DESCENT WITH LOW ENGINE POWER SELECTED. CABIN ALTITUDE WARNING (CABIN PRESS) LIGHT I	LLUMINATED AND CREW USED FIXED OXYGEN SYSTEM UNTIL CABIN ALTITUDE WAS RESTORED. OPERATIONAL CHECK OF ENGINE HP VALVES CA	RRIED OUT IAW AMM 21-00-00 UNABLE TO FAULT.   BOTH LT AND RT ENGINE 55 PSI BLEED AIR PRESSURE SWITCHES REPLACED AND SYST	EM TEST CARRIED OUT.  AIRCRAFT SERVICEABLE, NO FURTHER DEFECTS EVIDENT.  PRESSURE SWITCHES OUT OF TOLERANCE SUSPECTED TO	 BE CAUSING DEFECT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031400086	20050314	00086	EA  	2005	3	14	CA041013001      	1	20041010	G	2760	270007	PCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					SPOILER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) RT FLT SPOILER DEPLOYED MOMENTARILY DURING FLIGHT CAUSING ROLL.  FLT SPOILER FAULT MSG APPEARED. REMOVED AND REPLA	CED RT IB FLT SPOILER PCU.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005041800053	20050418	00053	SW  	2005	4	18	CA041013002      	1	20041013	G	3220	315434	LEAF SPRING     			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TAIL WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN LEAF SPRING BROKEN AT TOW BRIDLE CAGING BOLT. APPROX. 4 INCHES AFT OF SPRING ASSYU BAR. THESE ARE RECENTLY PU	RCHASED, NEW BATCH TYPE, LEAF SPRINGS.					1	H	7	1 	3O	3	O		A21CE   	E286
2005041800054	20050418	00054	SW  	2005	4	18	CA041013003      	1	20041013	G	3220	31543456	LEAF SPRING     			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TAIL WHEEL	BROKEN          	W				E				ENGINE SHUTDOWN         				P			NO WARNING INDICATION     			TX	TAXI/GRND HDL  	1			CA											(CAN) 4, MAIN LEAF SPRING, BROKEN APPROX 4 INCHES AFT OF U BAR. -5 AND -6 SPRINGS BROKEN AT AFT EDGE OF U BAR AND -6, TO	P SPRING, PUSHING UP AGAINST BOTTOM OF RUDDER HORN. THESE ARE RECENTLY PURCHASED NEW BATCH TYPE LEAF SPRINGS.					1	H	7	1 	3O	3	O		A21CE   	E286
2005031400087	20050314	00087	SW  	2005	3	14	CA041013004      	1	20041013	G	3220	315434	LEAF SPRING     			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TAIL WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN LEAF SPRING BROKEN AT TOW BRIDLE CAGING BOLT. APPROX 4 INCHES AFT OF SPRING ASSY U BAR. THESE ARE RECENTLY PU	RCHASED NEW BATCH TYPE SPRINGS.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874
2005031400088	20050314	00088	CE  	2005	3	14	CA041013005      	1	20040924	G	3246	49330	PLUG            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					WHEEL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN WHEEL ASSEMBLY LEAKING 1-2 PSI PER DAY. REPLACED 2 THERMAL RELIEF PLUGS AND LEAK CHECKED. OK.						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005020100156	20050201	00156	WP  	2005	2	1	CA041013006      	1	20040928	G	6210	369D21100517A	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HELICOPTER WAS FLYING WITH EXTERNAL LOAD WHEN THE PILOT FELT A (BUMP) IN THE CONTROLS. THE WEATHER WAS DETERIOATIN	G WHERE HE WAS OPERATING SO HE RETURNED TO THE STAGING AREA. THE PILOT INSPECTED THE BLADES AFTER SHUTDOWN AND FOUND A 4	.5 INCH CRACK 19 INCHES OUTBOARD FROM THE ROOT END, ONE BLADE ON THE BOTTOM STARTING FROM THE TRAILING EDGE. THE BLADE W	AS REMOVED AND REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT RETURNED TO SERVICE. THE SAFETY BOARD WAS NOTIFIED AND 	THE UNSERVICEABLE BLADE WAS SENT TO THEM FOR INSPECTION.		1	G	7	1 	3U	3	U		H3WE    	E4CE
2005020100157	20050201	00157	SO  	2005	2	1	CA041013007      	1	20040916	G	2910		FITTING         	CONT        		PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	FUEL PUMP	CRACKED         	W				E				ENGINE SHUTDOWN         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA						H069709BR					(CAN) BRASS OUTLET ANGLE FITTING ON FUEL PUMP CRACKED CAUSING FUEL TO LEAK OUT IN FLIGHT.						1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P25EA
2005031400081	20050314	00081	EA  	2005	3	14	CA041013008      	1	20041005	G	2913	6305402	PUMP            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	HYDRAULIC SYS	FAILED          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) WHILE THE AIRCRAFT WAS IN CRUISE AT 15,000 FEET, NR 4 HYDRAULIC PUMP CAUTION LIGHT ILLUMINATED, FOLLOWED 5 MINUTES	 LATER BY NR 3 HYDRAULIC PUMP CAUTION LIGHT COMING ON.   ALL HYDRAULIC PRESSURE WAS LOST ON NR 2 HYDRAULIC SYSTEM AND AL	TERNATE LANDING GEAR EXTENSION WAS CARRIED OUT AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  HYDRAULIC PUMP P/N 63054-02/05	  NR 4 HYDRAULIC PUMP P/N 225961-  NR 4 PUMP PRESSURE DROP TO ZERO.   NR3 HYDRAULIC PUMP P/N 167136-  NR 3 PUMP SHAFT BR	OKEN PRESSURE DROP TO ZERO.		2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
2005031400082	20050314	00082		2005	3	14	CA041013009      	4	20041007	G	2300	M880511104	SWITCH          	SCHLER      		HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					GRIP	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN)TRIGGER SWITCH MALFUNCTION, NO TRANSMISSION.  REPLACED SWITCH P/N M8805/111-04.						1	G	7	1 	3O	3	O	O	4H12    	E286
2005031400083	20050314	00083	NM  	2005	3	14	CA041013010      	1	20041013	G	5755	65449617	ACTUATOR        			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					SPOILERS	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) A SYSTEM HYDRAULIC LIGHTS ILLUMINATED, A SYSTEM QTY READ ZERO.   NR 8 SPOILER ACTUATOR FOUND CRACKED.  ACTUATOR RE	PLACED MM 27-62-91.  CARRIED OUT RII INSPECTION.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041800055	20050418	00055	SW  	2005	4	18	CA041013011      	1	20041013	G	3211	ES12404	ARM             			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING ACCOMPLISHEMENT OF TWIN COMMANDER SL376 INSPECTION OF MLG CLEVIS AND DRAGBRACE, 2 CRACKS WERE NOTED DURING COMPLE	TION OF EDDY CURRENT INSPECTION OF THE LEFT HAND MLG.  THE CRACKS ARE LOCATED AT THE MOUNTING HOLE FOR THE EYE BOLT P/N 	330085-43.  ATTACHED 3 PHOTOS FOR REVIEW.  THE AIRCRAFT HAS ACCUMULATED 165.5 HRS AND 146 CYCLES SINCE THE LAST COMPLIAN	CE WITH THE SERVICE LETTER.			1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA
2005041800056	20050418	00056	EU  	2005	4	18	CA041014001      	1	20041013	G	6520	7052A3632279	MAGNETIC PLUG   	UROCOP      		UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					T/R GEARBOX	CRACKED         	W				K				NONE                    				N	W		FALSE WARNING             	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA						M195					PILOT REPORTED INTERMITTENT INDICATION OF GEARBOX CHIP DETECTOR. ON INSPECTION NO CHIP FOUND.  A LOOSE CONNECTION BETWEE	N ELECTRICAL PORTION OF CHIP PLUG & MAGNETIC PART ALLOWED FOR A FALSE INDICATION.  THE SWAGGED CONNECTION BETWEEN THE TW	O PARTS CRACKED & BROKEN.  IN 2002 A SIMILAR PROBLEM HAD OCCURRED, BUT THIS PARTICULAR PLUG MANUFACTURED IN 2003.  NEW P	LUG ORDERED & UPON RECEIVING NEW PART IT TOO WAS CRACKED. EUROCOPTER CANADA CONTACTED AND A THIRD PLUG SENT.  AGAIN UPON	 INSPECTION IT TOO WAS CRACKED IN SAME SWAGED LOCATION. A CONTINUED LACK OF Q/A BETWEEN MANUFACTURER & EUROCOPTER HAS AL	LOWED THIS KNOWN PROBLEM TO PERSIST FOR OVER TWO YEARS. CURRENTLY WE ARE WAITING FOR YET ANOTHER CHIPPLUG.	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE
2005031400084	20050314	00084		2005	3	14	CA041014002      	4	20040926	G	2311	W31M30	MASTER SWITCH   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ON RADIO PANEL	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) RADIO MASTER SWITCH CONTROLLING POWER TO ALL RADIOS E.G. DUAL NAV COM, VDR, TRANSPONDER, BECAME INTERMITTENT THEN 	FINALLY FAILED SHUTTING POWER OFF TO ALL THE RADIOS.  MINIMAL PLAY IN TOGGLE SWITCH EVIDENT.  REPLACED SWITCH AND NO MOR	E FAULT. TIME ON ORIGINAL PART UNKNOWN BUT AIRCRAFT BASED IN FLYING SCHOOL, THEREFORE MANY CYCLES SUSPECTED PERHAPS INTO	 THE THOUSANDS.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005041800057	20050418	00057	NM  	2005	4	18	CA041014003      	1	20041008	G	6120	699018002	CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R4304	R4304*      	EU  	PROPELLER	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, AN AIRCRAFT EXPERIENCED AN UNCOMMANDED AUTOFEATHER CAUSED BY NR 1 ENGINE TORQUE FLUCTUATIONS. WITH T	HE NR 1 PROP FEATHERED AND ENGINE STILL RUNNING AT REDUCED POWER, THE PILOT RETURNED TO BASE. PEC REPLACED. ENGINE RUNS 	CARRIED OUT. A/C RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P890
2005041800058	20050418	00058	SO  	2005	4	18	CA041014005      	2	20041011	G	8530		CONNECTING ROD  			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 2 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 2 CYLINDER REMOVED DUE TO LOW COMPRESSION. NOTED WRIST PIN BEARING BROKEN AND CONNECTING ROD TIGHTER THAN NORMA	L ON CRANKSHAFT. AFTER FURTHER INVESTIGATING, FOUND NR 2 MAIN BEARING LOOSE IN BEARING SADDLE AND WAS ABLE TO MOVE FORE 	AND AFT INTHE CRANKCASE. ENGINE REMOVED AND SENT TO OVERHAUL FACILITY.				1	H	7	1 	3O	3	O		A4CE    	E5CE
2005041800059	20050418	00059	CE  	2005	4	18	CA041014006      	1	20041007	G	2810	121640719	RESERVOIR       			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					FUEL CELL	CRACKED         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) COULD SMELL STRONG FUEL ODOR IN COCKPIT AND ALSO NOTED FUEL STAIN ON BELLY OF AIRCRAFT DURING INSPECTION.  SUSPECT	ED RESEVOIR QUICK DRAIN LEAKY BUT FURTHER INVESTIGATION REVEALED A 1 INCH CRACK ON FORWARD LOWER WELD SEAM ON RESEVOIR. 	 RESEVOIR REMOVED, REPAIRED AND REINSTALLED.				1	H	7	1 	3O	3	O		A4CE    	E5CE
2005041800060	20050418	00060	CE  	2005	4	18	CA041014007      	1	20041007	G	2810	121640720	RESERVOIR       			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					FUEL CELL	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON 1000 HR FUEL SYSTEM INSPECTION AS REQUIRED BY CESSNA, THE FUEL WAS COMPLETELY DRAINED FROM THE AIRCRAFT.UPON 	REMOVING THE LOWER R/H RESEVOIR QUICK DRAIN,IT WAS REVEALED IT WAS QUITE LOOSE BUT NOT LEAKING.  UPON REINSTALLATION OF 	QUI CK DRAIN VALVE IT COULD NOT BE TORQUED AS THE THREADS WERE COMPLETELY STRIPPED. SUSPECTED QUICK DRAIN WAS OVERTORQUE	D ON PREVIOUS REMOVAL/INSTALLATION.  RESEVOIR WAS REMOVED, REPAIRED AND REINSTALLED.			1	H	7	1 	3O	3	O		A4CE    	E5CE
2005041800061	20050418	00061	CE  	2005	4	18	CA041014008      	1	20040921	G	3246	D30256	HUB             			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) DISSASSEMBLY FOR CLEANING / CORROSION / REPAINT FOUND 3 CRACKS IN HUB WEB BY FLANGE BOLT THREADS IN CASTING. INSPE	CTION OF OTHER HUB FOUND SIMILAR DAMAGE.INSPECTION WITHOUT PART BEING VERY CLEAN WOULD MAKE IT VERY DIFFICULT TO SEE THE	SE CRACKS.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005041800062	20050418	00062	CE  	2005	4	18	CA041015001      	1	20041013	G	2430	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) HIGH VOLTAGE LIGHT CAME ON DURING FLIGHT. ALTERNATOR INSPECTED AND FOUND THE BRUSHES WORN TO LIMIT. BRUSHES REPLAC	ED. A/C GROUND RUN AND FOUND HIGH VOLTAGE LIGHT REMAINED ON. FUTHER TROUBLESHOOTING FOUND ALTERNATOR WIRE SHORTED TO SHI	ELD WIRE. BATTERY CONTACTOR AND STARTER CONTACTOR HAD FAILED, VOLTAGE REGULATER FAILED, AND STARTER WAS NO FULLY DISENGA	GING. ALL WIRING INSPECTED AND FOUND NO OTHER FAULTS. BATTERY FOUND WITH NO FAULTS. CONTACTORS, REGULATER, AND ALT WIRE 	REPLACED. A/C GRD RUN SERVICEABLE.		1	H	7	1 	3O	3	O	NT	3A12    	E274
2005041800063	20050418	00063	EU  	2005	4	18	CA041015002      	1	20040928	G	6700	LN9038	BOLT            			BOLKMS	105   	BO105S      	5626006	EU  										BEARING SUPPORT	MISSING         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) PILOT NOTED THAT IT TOOK A MOMENT FOR THE COLLECTIVE PITCH CHANGES TO BECOME EFFECTIVE. WHEN INVESTIGATING THE ENG	INEER FOUND APPROXIMATELY 7/16OF PLAY AT THECOLLECTIVE GRIP. FURTHER INVESTIGATION OF THE COLLECTIVE FLIGHT CONTROL SYST	EM, REVEALED THAT THE COLLECTIVE PITCH SHAFT ASSEMBLY P/N 105-41221, WAS LOOSE IN T HE BEARING ASSEMBLY P/N 105-41210-18	. ONE OF THE ATTACHING BOLTS P/N LN9038-05010 HAD FALLEN OUT AND THE THREE REMAINING BOLTS REQUIRED THREE COMPLETE TURNS	 TO TIGHTEN. THE DRAG TORQUE OF THE NUT PLATES WAS SUFFICIENT. THE MISSING BOLT WAS REPLACED AND THE AIRCRAFT WAS RETURN	ED TO SERVICE.QUALITY ASSURANCE DEPARTMENT HAS OPENED AN INVESTIGATION OF THIS OCCURRENCE.	1	G	7	2 	3U				H3EU
2005041800064	20050418	00064	CE  	2005	4	18	CA041015003      	1	20041012	G	5410	55120416	CAP             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					DUCT	WORN            	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) FRESH AIR DUCT PN 6515317-12 FRETTED ON THE OUTBOARD FLANGE OF THE TEE SECTION CAP.						1	L	7	2 	4F	4	F		A22CE   	E1NE
2005041800065	20050418	00065	CE  	2005	4	18	CA041015004      	1	20041015	G	3230	508100352	TORQUE KNEE     			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 8000 CYCLE TORQUE KNEE NDT INSPECTION IT WAS DETECTED THAT THE RT LOWER TORQUE KNEE ATTACH PIN, PN 50-810	035-2 WAS CRACKED IN NUMBER OF PLACES. THE TORQUE KNEE IS POST S/B 32-3116 - IMPROVED STEEL. PRESENTLY THE PIN IS PLACED	 IN QUARANTINE. THERE IS A FLEET WIDE INSPECTION IN PROGRESS.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA
2005041800066	20050418	00066	EA  	2005	4	18	CA041015005      	2	20040927	G	7414	1068291218	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								L56568A			(CAN) RT ENGINE DEVELOPED 'MISSING OR SURGING' IN POWER AT HIGH POWER SETTINGS. RAN FINE AT LOW POWER. AIRCRAFT RETURNED	 FOR MAINTENANCE. AMO REMOVED MAGNETO AND FOUND DISTRIBUTOR BLOCK CRACKED AND BEARINGROUGH. MAGNETO REPLACED AND GROUND 	RUN, SERVICEABLE. MAGNETO PN 10-682912-18, SN H259310.				1	L	7	2 	3O	3	O		A20SO   	E14EA
2005041800067	20050418	00067		2005	4	18	CA041015006      	4	20040923	G	3400		BULB            	COLLINS     		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	CONTROL HEAD	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA						14659					(CAN) UPON COMPLETION OF ENG START & TURNING ON AVIONICS IN PREPARATION FOR DEPARTURE ON A CHARTER TRIP, CREW OBSERVED S	MOKE COMING FROM THE RT AVIONICS. CREW SHUTDOWN ENGINES & MASTER SWITCH & DEPLANED ALONG WITH PAX. MX RESPONDED & AFTER 	LOCATING SOURCE OF SMOKE & ATTENDED FUMES, REPLACED NAV CONTROL HEAD SET WITH A SERVICEABLE SET & CHARTERED DISPATCHED. 	 NAV CONTROL HEAD - FACE PLATE LIGHT BULB BURNED OUT.  REPAIRED & PROVIDED A MAINTENANCE RELEASE (DATED 24 SEPT 04). MAT	CHING UNIT (OTHER 1/2 OF SET)WAS INSPECTED & TESTED & PROVIDED A MAINTENANCE RELEASE.		2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL
2005041800068	20050418	00068	NE  	2005	4	18	CA041015007      	2	20041014	G	7230	6A7379	BLADE           			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					COMPRESSOR	FAILED          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA			33906					V0314			(CAN) ON TAKE OFF WITH THROTTLES BETWEEN IDLE AND FLEX MCT. LOUD BANG FROM LT ENGINE HEARD IN THE COCKPIT. TAKE OFF ABAN	DONED AT 115 KTS. ACRFT RETURNED WITH ENGINE RETARDED TO IDLE. NO UNUSUAL PARAMETERS. BORESCOPE INSPECTION REVEALED ONE 	FAILED HPC STAGE 4 BLADE WITH RESULTANT IMPACTS TO OTHER STAGE 4 BLADES.				2	L	7	2 	4F	4	F	RT	A28NM   	E311NE
2005041800069	20050418	00069	GL  	2005	4	18	CA041015008      	3	20041015	G	6114	D4530	HUB             			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	IO360CONT   	17025	SO  	MCAULY	2A34C	2A34C*      	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									810199		(CAN) PROPELLER RECEIVED FOR 10 YR. O/H. UPON INSPECTION IT WAS FOUND THAT THE HUB, BLADE BEARINGS (C3411),PISTON ROD (B	2345), SPLIT RETAINERS (C3903) AND PISTON (C3418) WERE UNSERVICEABLE DUE TO WEAR AND/OR CORROSION. MANUFACTURERS RECCOME	NDED TBO AS PER S/B 137Y IS 2000 HRS OR 72 MONTHS. THIS PROPELLER HAS EXCEEDED THE CALENDAR TIME BY 48 MONTHS.				1	L	7	1 	3O	3	O		2A3     	E1CE	5	C	P3EA
2005041800070	20050418	00070	SO  	2005	4	18	CA041017001      	2	20041002	G	8500		CRANKCASE       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA								175076R			(CAN) THE CESSNA 185 WAS RETURNING TO HOME BASE FROM THE HUNTING CAMP, WHEN IN CRUISE,WITH ALL ENGINE PARAMETERS INDICAT	ING NORMAL,THE ENGINE STOPPED IN FLIGHT AND T HE SEASONED PILOT WAS ABLE TO LAND WITHOUT INCIDENT. THE ENGINE SUFFERD TW	O CRACKS TO THE CRANKCASE HALVES IN THE AREA OF NR 1 AND 2 CYLINDERS. ALL CYLINDERS WERE FOUND INTACT AND UNDAMAGED. ALL	 CYLINDERS WERE REMOVED AND NEW RINGS INSTALLEDAT 902.0 HRS. SUBJECT ENGINE TO BE SENT TO ANOTHER OVERHAULER FOR ANALYSI	S.		1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA
2005041800071	20050418	00071	EA  	2005	4	18	CA041018001      	1	20041017	G	5610	601R3303310	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED ELECTRICAL ARCING FROM THE RT WINDSHIELD DURING APPROACH WHILE THE WINDSHIELD HEAT WAS SELECTED 	TO LOW . UPON INSPECTION THE WINDSHIELD WAS FOUND CRACKED AND CONSEQUENTLY REPLACED .PLEASE NOTE THE AIRWORTHINESS DIREC	TIVE CF-2001-35R1 WAS COMPLIED WITH ON 26 OCTOBER 2002 AND SB601R-56-004 WAS COMPLIED WITH ON APRIL 10 2004 .				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005041800072	20050418	00072	EA  	2005	4	18	CA041018003      	1	20041015	G	5311	21531036212	FRAME           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACRFT IN FOR ITS ANNUAL B-CHECK WHEN A VISUAL INSPECTION OF THE REAR  SKI SLOPEAREA REVEALED A CRACK IN THE LT REA	R OUTBOARD WING-TO-FUSELAGE FRAME ANGLE AT BL 51.00 FS 434.00.AD CF-1997-07R2 WAS NOT REQUIRED AT THIS TIME BUT THE MX P	ERSONAL DECIDED TO DO A QUICK VISUAL INSPECTION ANYWAY. CRACK ORIGINATED AT THE TOP OF BRACKET & CONTINUED PASS THE FIRS	T FASTENER AND MAKING ITS WAY TO THE SECOND. THE REPEAT INSPECTION REQUIREMENTS OF THE AD WERE CARRIED OUT ON NOV. 5, 20	02 AT A/F HRS 2163.6 AND WATER DROPS 7516. THE SUBSEQUENT INSPECTION WAS NOT DUE UNTIL A/F HRS 2578.6 OR 9016 WATER DROP	S. THE AIRCRAFT NOW HAS AN A/F TIME OF 2331.1 AND WATER DROPS 8147.REPAIRS TO THE AREA WERE CARRIED OUT AS PER THE SRM.	2	H	7	2 	4R	4	R	RT	A14EA   	E231
2005041800073	20050418	00073	SO  	2005	4	18	CA041018004      	2	20040930	G	8530	ACE631397	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					NR 4	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								284784R			(CAN) DURING A 50 HOUR INSPECTION, NR 4 CYLINDER WAS FOUND TO HAVE ZERO COMPRESSION.CLOSER EXAMINATION FOUND CRACKS EXTE	NDING FROM BOTH SPARK PLUG HOSE INTO THE EXHAUST PORT AND CYLINDER HEAD.A FOLLOW-UP ISPECTION INCLUDING COMPRESSON TEST 	AND SOAP LEAK TEST WILL BE CONDUCTED TO INSURE CONTINUED AIRWORTHINESS.				1	H	7	1 	3O	3	O		A4CE    	E3SO
2005041800074	20050418	00074	SO  	2005	4	18	CA041018005      	2	20041004	G	8530	ACE631397	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					NR 5	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								284784R			(CAN) DURING THE FOLLOW-UP INSPECTION, COMPRESSION WAS FOUND WITHIN LIMITS BUT A SOAP LEAK TEST FOUND NR 5 CYLINDER LEAK	ING.THE CYLINDER ASSY WAS REMOVED WITH NO DEFECTS VISIBLE. THE LEAK SEAMS TO BE FROMBETWEEN THE CYLINDER BARREL AND HEAD	 WHERE THEY SCREW TOGETHER. THERE IS ANOTHER FOLLOW-UP INSPECTION BOOKED. 6 NEW CYLINDERS TO BE INSTALLED IF ANY PROBLEM	S FOUND.			1	H	7	1 	3O	3	O		A4CE    	E3SO
2005041800075	20050418	00075	NE  	2005	4	18	CA041018007      	3	20040909	G	6110	582855	HOUSING         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	PROP VALVE	DAMAGED         	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) INBOUND, NR 4 PROP RPM DROPPED BELOW LIMIT ACOMPANIED BY RPM FLUCTUATION AND TORQUE ROLL.THE ENGINE WAS SHUTDOWN A	S A PRECAUTION. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE NR 4 VALVE HOUSING AND AIRCRAFT WAS RETUR	NED TO SERVICE.				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906
2005041800076	20050418	00076	NM  	2005	4	18	CA041018008      	1	20041004	G	2910		LINE            			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	LEAKING         	W				D				RETURN TO BLOCK         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER START-UP AT PUSH BACK THE PURSER NOTIFIED THE FLT DECK CREW OF FUMES IN THE CABIN. THE PASSENGERS WERE DEPLA	NED AND THE AIRCRAFT WAS RETURNED MAINTENAN CE TO IDENTIFY AND DETERMINE THE SOURCE OF THE PROBLEM. MAINTENANCE FOUND A 	PIN HOLE IN THE TAIL SKID ACTUATOR SUPPLY LINE. THE LINE WAS REPAIRED AND THE AIRCRAFT GROUND CHECKED WITH ENGINES, PACK	S AND GASPER OPERATING WITH NO INDICATION PRIOR TO RETURN TO SERVICE			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005041800077	20050418	00077	EA  	2005	4	18	CA041018009      	2	20041007	G	7261		PLANETARY GEAR  								PWA   	PT6   	PT6A28      	 	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								40111100			(CAN) ENG REMOVED DUE TO METAL IN OIL. ENG SENT IN FOR INVEST & REPAIR. CUSTOMER DECIDED TO SEND ALL PARTS OF ENG TO OUR	 AMO FOR REVIEW.  SOURCE OF METAL FROM A 2ND STAGE PLANETARY GEAR BEARING SLEEVE FAILURE. BRONZE PARTICLES GENERATED FRO	M SLEEVE BEARING BRONZE FACE DURING SEIZURE. SLEEVE SEIZED ONTO THE SHAFT - GEAR OVERCAME RESISTANCE OF GEAR/SLEEVE TIGH	T FIT & GEAR STARTED TO TURN AROUND SLEEVE ON SLEEVE OUTSIDE SURFACE. ROTATION GENERATED METAL PARTICLES FROM GEAR BORE 	AND SLEEVE. ALL OF THE OIL STRAINERS IN BOTH 1ST & 2ND STAGE CARRIERS FOUND TO BE PARTIALLY BLOCKED. SEIZURE RELATED TO 	OIL STARVATION CAUSED BY THE BLOCKED STRAINERS.						4	T			E4EA
2005041800079	20050418	00079	EU  	2005	4	18	CA041019001      	1	20041010	G	6320	RA13212	BOLT            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS OPERATING AWAY FROM BASE WITHOUT A MAINTENANCE CREW ABOARD. THE FOLLOWING OCCURRENCE WAS REPORTED	 UPON RETURN TO BASE.AFTER THE LAST FLIGHT OF THE DAY THE PILOT NOTICED A TRANSMISSION OIL LEAK ON THE RIGHT SIDE DRAIN 	AT THE CROSS TUBE. INVESTIGATION DETERMINED THAT THE BANJO FITTING BOLT ON THE TRANSMISSION OIL PUMP HAD LOST TORQUE EVE	N THOUGH IT WAS LOCK WIRED. THE BANJO BOLT WAS TIGHTENED A PART OF A TURN AND LOCK WIRED. THE AIRCRAFT WAS GROUND RUN FO	R 20 MINUTES WITH NO LEAKS. THE AIRCRAFT WAS RETURNED TO SERVICE. THE TRANSMISSION HAD BEEN REPLACED TWO MONTHS EARLIER 	AND HAD ACCUMULATED 50 HOURS OF OPERATION BEFORE THE LEAK APPEARED.	1	G	7	2 	3U	3	U		H3EU    	E4CE
2005041800080	20050418	00080	NM  	2005	4	18	CA041019002      	1	20041012	G	3233	464557	HOSE            	BFGOODRICH  		BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG RETRACT	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) RT MLG RETRACT ACTUATOR HOSE RUPTURED IN-FLIGHT, AIRCRAFT LANDED WITH NO INCID ENT. LOST ALL HYD FLUID ON NR 2 SYS	TEM HOSE REPLACED.  RUPTURED RETRACT ACTUATOR FLEX LINE, P/N 46455-7, REPLACED AND GEAR SWINGS CARRIED OUT.  A/C RTSRUPT	URED HOSE TO BE RETURNED TO BOMBARDIER FOR INVESTIGATION.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041800081	20050418	00081	CE  	2005	4	18	CA041019003      	1	20041007	G	7120	265102319	MOUNT           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT ENGINE REPLACEMENT, THE CLAMP WAS FOUND TO BE LOOSE AROUND THE ENGINE MOUNT TUBING. THE CLAMP HAD CHAFFED INTO 	THE TUBE SIGNIFICANTLY. THE MOUNT WAS REMOVED AND SENT FOR REPAIR IAW THE SRM FOR THE C208B. THE CLAMP AND HARDWARE WAS 	REPLACED AND SECURED.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL
2005041800082	20050418	00082	GL  	2005	4	18	CA041019004      	3	20041019	G	6114	D4190305	HUB             			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	TSIO360G    	17025	SO  	MCAULY	2AF34C	D2AF34C305  	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									734518		(CAN) PROP RECEIVED FOR O/H. UPON INSPECTION CORROSION PITS WERE FOUND IN THE PROP MOUNTING FLANGE. THIS DAMAGE WAS TOO 	DEEP TO BE REMOVED WITHIN MANUFACTURERS SPECIFICATIONS. PROP HAS EXCEEDED THE MANUFCTURERS RECCOMENDED CALENDAR TBO BY 3	1 MONTHS.				1	H	7	2 	3O	3	O		A6CE    	E9CE	5	C	P5EA
2005041800083	20050418	00083	GL  	2005	4	18	CA041019005      	3	20041019	G	6114	D7292203	HUB             			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									840316		(CAN) PROP RECEIVED FOR 10 YR. CALENDAR O/H. AFTER PAINT REMOVAL FROM HUB CORROSION WAS FOUND ON THE EXTERNAL SURFACES. 	THIS CORROSION CANNOT BE REMOVED WITHIN THE MANF.'S MINIMUM SPEC'S. THIS PROPELLERHAS EXCEDED THE MANF'S RECOMMENDED CAL	ENDAR TBO BY 60 MONTHS.				1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA
2005041800084	20050418	00084		2005	4	18	CA041019006      	4	20041018	G	2360	17472	MOUNT           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					STATIC WICK	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RUDDER AND AILERON STATIC WICK BASE FOUND LOOSE. PARTS REMOVED CORROSION WAS FOUND ON MATING SURFACE WHICH WAS CLE	ANED AND BASES ATTACHED SEALED AND PAINTED.					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE
2005041800085	20050418	00085	CE  	2005	4	18	CA041019007      	1	20041008	G	7931	6320622	ROD             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					OIL GAUGE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IMPROPER INSTALLATION OF THE OIL GAUGE ROD TUBE ADAPTER SPIGOT INTO THE CRANKCASE SUCH THAT IT EXTENDS TOO FAR INT	O THE CASE ALLOWING THE OIL GAUGE ROD TO PROTRUDE TOO FAR INTO THE OIL SUMP AND CAUSING IT TO MAKE CONTACT WITH THE OIL 	SUMP. THE CONTACT CAN LEAD TO WEAR, WITH ENGINE VIBRAITON, AND IF PROLONGED COULD EVENTUALLY WEAR COMPLETELY THROUGH THE	 OIL SUMP RESULTING IN LOSS OF ENGINE OIL WHICH COULD LEAD TO OIL STARVATION AND ENGINE FAILURE.RECOMMENDATION: THE OIL 	GAUGE ROD, P/N 632062-2, COULD BE DESIGNED SO THAT IT ISONE INCH SHORTER IN OVERALL LENGTH. NOTE: SEVERAL OTHER ENGINE M	ODELS COULD BE AFFECTED BY THIS IMPROPER INSTALLATION.	1	H	7	1 	3O	3	O		A4CE    	E3SO
2005041800086	20050418	00086	NE  	2005	4	18	CA041019009      	3	20041004	G	6111	31025751	SHAFT SEAL      			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311151A 	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROP BLADE	SEIZED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) PROP SHAFT SEAL WAS FOUND LEAKING.DURING DISASSEMBLY THE SHAFT SEAL WAS FOUND WITH ABNORMAL WEAR AND DETERIATION I	N THE SLOTS OF THE CARBON PORTION OF THE SEAL.THE SLOTS WERE WORN HEAVILY AND THE METAL TABS APPEARED TO BE JAMBED INTO 	THE SIDES OF THE SLOTS.  THESE WOULD NORMALLY BE CENTERED WITHIN THE SLOTS.  THIS CAUSED THE SEAL TO SEIZE WHICH RESTRIC	TED THE FREEDOM OF THE SEAL TO TRAVEL AGAINST THE ROTOR SEAL WHICH CAUSED A MAJOR OIL LEAK. NORMALLY THESE SEALS WILL RU	N 7000 HOURS WITHOUT A PROBLEM.		2	L	7	2 	4T	4	T	RT	A8SW    	E3WE	6	C	3PNE
2005041800087	20050418	00087		2005	4	18	CA041020001      	4	20040725	G	3418	C16177AC	VANE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ANGLE OF ATTACK	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) SHORTLY AFTER TAKEOFF POWER WAS APPLIED, 'PUSHER SYSTEM FAIL' WAS ANNOUNCED FOR 1-2 SECONDS, AND THEN WENT OFF. TA	KEOFF ROLL WAS ABORTED AT APPROXIMATELY 50-60 KNOTS.  AOA VANE WAS FOUND HARD TO MOVE WHEN HOT AND IT WAS THEREFORE REPL	ACED IN ACC. AMM TASK 27-33-26.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041800088	20050418	00088	NM  	2005	4	18	CA041020002      	1	20041016	G	3260	65244809	FITTING         			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG UPLOCK	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			60571								(CAN) DURING ROUTINE MAINTENANCE A CRACK WAS FOUND IN THE LEFT HAND MLG UPLOCK FITTINGIN THE FORWARD RADIUS. NDT CONFIRM	ED THE CRACK. FITTING WAS REPLACED AND GEAR RETRACTIONS CARRIED OUT.					2	L	7	3 	4F	4	F		A3WE    	E2EA
2005041800089	20050418	00089	EU  	2005	4	18	CA041020003      	1	20041016	G	3213	C2310961013	STRUT           			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					NLG DOWNLOCK	LACK OF LUBE    	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO AIRPORT, FLIGHT CREW WAS UNABLE TO OBTAIN POSITIVE NOSE LANDING GEAR DOWN LOCK INDICATION EVEN AFTE	R SEVERAL CYCLES. A LANDING GEAR GRAVITY EXTENSION WAS CARRIED OUT SUCCESSFULLY.TROUBLE SHOOTING OF THE ELECTRICAL INDIC	ATION SYSTEM DID NOT REVEAL ANY FAULTS. A FULL PHYSICAL INSPECTION WAS CARRIED OUT AND GEAR SWING OF NOSE LANDING GEAR. 	MAINTENANCE WAS UNABLE TO DUPLICATE THE FAULT. NOSE LANDING GEAR LUBRICATION WAS PERFORMED AND THE AIRCRAFT WAS RELEASE 	FOR RETURN TO SERVICE PENDING SATISFACTO RY TEST FLIGHT. AS PRECAUTIONARY MEASURE FROM TROUBLE SHOOTING AND AIRBUS TFU 3	2-31-24  .002 THE NOSE LANDING GEAR TELESCOPIC STRUT ASSEMBLY WAS REPLACED AS UNIT IS SUSCEPTIBLE TO MOISTURE INGRESS AN	2	L	7	2 	4F	4	F	RT	A35EU   	E13NE
2005041800090	20050418	00090	NE  	2005	4	18	CA041020004      	2	20041018	G	7322	8063041	FUEL CONTROL    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	OUT OF RIG      	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PCE0106			(CAN) WHILE CRUISING AT 25000 THE FLIGHT CREW NOTICED A SMALL SURGE IN POWER, THEN THE ENGINE RETURNED TO THE POWER SETT	ING. THIS OCCURRED ONCE MORE ON DESCENT, BUT O NCE AGAIN CLEARED UP. AFTER LANDING AIRCRAFT WAS GROUND RUN AND SURGES IN	 NG AND TORQUE WERE NOTICED . AIRCRAFT WAS GROUNDED AND FUEL CONTROL WAS REPLACED, THIS CORRECTED THE NG PROBLEM BUT WE 	STILL HAD TORQUE SURGES WE THEN REPLACED THE PR OP GOV P/N 8210-137 AND ENGINE WAS RIGGED AND GROUND RUN. PROBLEM WAS CO	RRECTED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041800091	20050418	00091	NE  	2005	4	18	CA041020005      	2	20041019	G	7314	8256015	PUMP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE FUEL	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE0106			(CAN) WHILE AIRCRAFT WAS AT MAINTENCE BASE IT WAS DECIDED TO DO THE FUEL PUMP INLET SCREEN INSPECTION. WHEN THE OUTLET F	ILTER WAS REMOVED TO GAIN ACCESS TO THE SCREEN WE FOUND METAL IN THE FILTER AND ALSO LOT OF METAL FILLINGS  IN THE FILTE	R HOUS ING. OVERHAUL SHOP WAS NOTIFIDED AND NEW PUMP IS BEING SHIPPED. NO METAL WAS FOUND IN AIRFRAME FILTER, INLET SCRE	EN ON PUMP OR INLET SCREEN IN FCU.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041800092	20050418	00092	CE  	2005	4	18	CA041020006      	1	20041020	G	3243	99121661	SHAFT SEAL      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HYD BRAKE PWRPK	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER THE FIRST FLIGHT OF THE DAY THE CREW NOTICED FLUID ON NOSE WHEEL. MORE FLUID WAS FOUND IN THE NOSE WHEEL WEL	L. FLUID LEAKAGE WAS TRACED TO THE HYDRAULIC BRAKE POWER PACK SEALS BETWEEN THE PUMP AND THE MOTOR. THE HYDRAULIC BRAKE 	POWER PACK ASSEMBLY WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	2 	4F	4	F		A22CE   	E1NE
2005041800093	20050418	00093		2005	4	18	CA041020007      	4	20041018	G	3140	4055900905	SYMBOL GENERATOR			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 1 PFD	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAS BEEN DIVERTED TO AN ALTERNATE AIRPORT DUE TO A COMPLETE LOST OF NR 1 PRIMARY FLIGHT DISPLAY AND NAV D	ISPLAY.  MAINTENANCE FOUND NR 1 SYMBOL GENERATOR AT FAULT, AIRCRAFT DISPATCHED SERVICEABLE FOLLOWING THE REPLACEMENT.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041800094	20050418	00094	NM  	2005	4	18	CA041020008      	1	20040707	G	7712	304725201	PROBE           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ENG TORQUE	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) POWER PLANT CAUTION MESSAGE ON ENGINE DISPLAY DURING DESCENT. A/C COMPLETED AN UNEVENTFUL LANDING. AFTER SUCCESSFU	L RESET OF THE SYSTEM WITH TCC CONTACT, ENGINES STARTED. JUST AFTER ENGINE SPOOL-UP WEGOT 'POWERPLANT' ONCE AGAIN. FLIGH	T WAS THEN CANCELLED. FAULT CODE 166, QB (P12) SPEED INCONSISTENT, WAS FOUND LOGGED IN THE CENTRAL DIAGNOSTIC SYSTEM ON 	RT ENGINE.TORQUE PROBE QB WAS CONSEQUENTLY REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041800095	20050418	00095	EA  	2005	4	18	CA041020009      	2	20041019	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						FAILED          	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								FA0106			(CAN) AT TOP-OF-DESCENT (23K FEET) THE BLUISH SMOKE BECAME EVIDENT ON THE FLIGHT DECK AND IN THE CABIN .PILOTS DONNED OX	YGEN MASKS, DECLARED AN EMERGENCY AND DIVERTED TO AN ALTERNATE AIRPORT.  DURING THE SUBSEQUENT RAPID DESCENT, THE PILOTS	 REPORTED HEARING A 'BANG' WITH AN ASSOCIATED YAW ALTHOUGH NO SHIFT IN ENGINE PARAMETERS WAS EVIDENT.  THE ENGINE WAS NO	T SHUTDOWN DURING THE EVENT.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041800096	20050418	00096	NE  	2005	4	18	CA041020010      	2	20041011	G	7261	P1010	OIL FILTER      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE OIL	CLOGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE94087			(CAN) ON ROUTINE INSPECTION IT WAS DISCOVERED THAT A PIECE OF THE SCREEN SECTION WAS SEPERATING FROM THE EXTERNAL SECTIO	N OF THE FILTER. NOT SURE IF IT IS A MANUFACTURING DEFECT OR IF THE FILTER WAS COMING APART IN USE.					1	L	7	2 	4T	4	T		A24CE   	E4EA
2005041800097	20050418	00097	CE  	2005	4	18	CA041020011      	1	20041019	G	3246	AN36A	BOLT            	CESSNA      		CESSNA	337   	337A        	2075704	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	LT WHEEL	MISSING         	W				D				RETURN TO BLOCK         				D	B		INFLIGHT SEPARATION       	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXING TO PARK, THE LEFT WHEEL STARTED TO SMOKE AND THE AIRCRAFT STARTED TO SHAKE. AFTER APPLYING BRAKES EVE	RYTHING WENT BACK TO NORMAL. UPON INSPECTION THE TIRE HAD WORN ALMOST THROUGH AND ONE OF THE THREE WHEEL BOLTS WAS MISSI	NG. AFTER THE WHEEL WEAS REMOVED IT WAS OBVIOUS WHERE PART OF THE MISSING BOLT HAD TEMPORARILY LODGED ITSELF TO CAUSE TH	E WHEEL TO LOCK UP. A NEW TIRE AND BOLT WAS INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. IF THE BOLT HAD FALLEN OUT B	ECAUSE THE NUT WENT MISSING THERE WOULD HAVE BEEN DAMAGE TO THE WHEEL HALF, BUT THERE WAS NONE. THEREFORE, IT LOOKS LIKE	 THE BOLT BROKE.  WE COULD NOT FIND THE BOLT.	1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
2005041800098	20050418	00098	NE  	2005	4	18	CA041021001      	2	20041018	G	7200		POWERPLANT      			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  		FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA			31530					367302			(CAN) ENG FLAMED OUT AT 13,000 FT DURING DESCENT WHEN THEY TRIED TO REAPPLY HIGHER POWER & RESTARTED SUCCESSFULLY AFTER 	FOLLOWING PROCEDURES. ACRFT LANDED. MX DISPATCHED, EVALUATION CARRIED OUT IAW GE MM. INTERNAL ENG INSPECTED NO FAULT FOU	ND, EXTERNAL INSPECT CARRIED OUT NO FAULT FOUND. RUNS CARRIED OUT AT HIGH POWER, AIR VALVE LITE COMING ON MEANING NOT EN	OUGH AIRFLOW TO THE ANTI-ICING SYSTEM. AFTER TROUBLESHOOTING FOR THE BLEED AIR VALVE TO BE DEFECTIVE. VALVE REPLACED, DE	FECT REPAIRED. THIS ALONE COULD HAVE NOT CAUSED THE FLAME OUT. AFTER DISCUSSION WITH CREW THEY USED QRH PROCEDURE FOR AI	R VALVE LIGHT ON, BUT AUTOCOARSEN SWITCH ON AT ALL TIMES	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE
2005041800099	20050418	00099		2005	4	18	CA041021002      	4	20041019	G	2562	BS2173	BATTERY         	DORNEMARGLN 		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ELT	CORRODED        	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA						48183					(CAN) BATTERY LEAK CAUSING CORROSION EATING THE CASING AND DESTROYING THE TRANSMITTER.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2005041800100	20050418	00100	EU  	2005	4	18	CA041021003      	1	20040826	G	6123		PUMP            			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	PROP FEATHERING	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED AND THE PILOT ELECTED TO SHUT DOWN THE ENGINE BEFORE PER	FORMING AN UNEVENTFUL SINGLE ENGINE LANDING. GROUND MAINTENANCE FOUND AN OIL LEAK AT THE FEATHERING PUMP FROM A DAMAGED 	O'RING.				2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG
2005041800101	20050418	00101	EU  	2005	4	18	CA041021004      	1	20040915	G	6123		PUMP            			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	PROP FEATHERING	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) FOLLOWING AN IFSD AND RESULTING EMERGENCY LANDING, GROUND MAINTENANCE FOUND AN OIL LEAK AT THE FEATHERING PUMP ACC	OMPANIED BY THE SEIZURE OF THE LOW AND HIGH PRESSURE COMPRESSOR ROTORS.					2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG
2005041800102	20050418	00102		2005	4	18	CA041021005      	4	20041013	G	3425	7926355001	INDICATOR       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FLT DIRECTOR	FAILED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER START-UP AND SELECTION OF THE AVIONICS MASTER ON, THE CREW NOTED THAT THE INSIDE OF THE FLIGHT DIRECTOR INDI	CATOR, BEHIND THE GLASS FACE, APPEARED TO HAVE SMOKE INSIDE OF THE INSTRUMENT. THE AVIONICS MASTER WAS SELECTED TO OFF A	ND THE ENGINES SHUT DOWN. MAINTENANCE WAS CONTACTED AND INSPECTED THE INDICATOR. AN EL ECTRICAL TYPE SMELL WAS PRESENT A	T THE UNIT. THE INDICATOR WAS REPLACED AND THE UNSERVICEABLE UNIT HAS BEEN SENT TO THE VENDOR FOR INSPECTION AND OVERHAU	L.		1	L	7	2 	4T	4	T		A24CE   	E4EA
2005041800103	20050418	00103	NE  	2005	4	18	CA041021006      	2	20040919	G	7314	6055T19P14	HMU             			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F26 	NE  	ENGINE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING A SCHEDULED ENGINE CHANGE AND DURING COMPLETION OF THE GROUND RUN OPERATIONAL CHECKS, THE BOTTOM GOVERNI	NG FUNCTION OF THE ENGINE COULD NOT BE ENABLED. THE HMU WAS REPLACED AND RETURNED TO THE MANUFACTURER FOR INSPECTION AND	 REPAIR. THE SHOP REPORT CONCLUDED THAT A DEFECTIVE LINEAR TRANSDUCER IN THE HMU WAS AT FAULT.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE
2005041800104	20050418	00104	NE  	2005	4	18	CA041021007      	2	20040914	G	7314	6055T19P14	HMU             			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F26 	NE  	ENGINE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			35795								(CAN) DURING COMPLETION OF ENGINE GROUND RUNS AFTER AN ENGINE CHANGE, THE ENGINE BOTTOM GOVERNING FUNCTION COULD NOT BE 	CONSISTENTLY ENABLED AS REQUIRED BY THE CHECK.  IT WOULD INTERMITTENTLY FAULT TO A LOWER THAN SELECTED RPM. THE HMU WAS 	REPLACED AND SENT TO THE MANUFACTURER FOR INSPECTION AND REPAIR.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE
2005041800105	20050418	00105	NM  	2005	4	18	CA041021008      	1	20041018	G	3310	BV031120333	FIXTURE         			BOEING	757   	757256      	1384925	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					COCKPIT LIGHT	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) BURNING SMELL NOTICED IN FORWARD CABIN AFTER DEPARTURE.  CREW ELECTED TO RETURN TO AIRPORT. ON ARRIVAL, MTX NOTICE	D CEILING LIGHTING NOT WORKING AT ROW 2DEF FOUND CONNECTOR ON LIGHTING FIXTURE HAD ARCED/BURNED AND EMITTED STRONG ODOUR	. FIXTURE REMOVED, INCLUDING BALLAST (PN 05939-3, SN 4515				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2005031400098	20050314	00098	CE  	2005	3	14	CA041022001      	1	20041019	G	3230	MS166551031	RETAINING RING  			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	MISSING         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) AIRCRAFT WAS ON APPROACH AND SELECTED LANDING GEAR DOWN.  LANDING GEAR FAILED TO EXTEND.  THE FLIGHT CREW THEN SEL	ECTED THE EMERGENCY LANDING GEAR EXTENSION SYSTEM.  THE LANDING GEAR LOCKED DOWN AND THE AIRCRAFT LANDED SAFELY.  UPON I	NSPECTION OF THE LANDING GEAR SYSTEM MAINTENANCE FOUND THE RETAINING RING INSTALLED IN THE SHAFT COUPLER MISSING.  THIS 	CAUSED THE COUPLER TO SLIDE TO THE MOTOR SIDE OF THE SPLINED SHAFT, WHICH CAUSED THE MOTOR TO DISENGAGE FROM THE PUMP.			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC
2005041800106	20050418	00106		2005	4	18	CA041022002      	4	20041021	G	2210	6224717004	CONTROL PANEL   			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					MODE CONTROL	FAILED          	W				A				UNSCHED LANDING         				H	G		ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          		CR	CRUISE         	1			CA											(CAN) AFTER DEPARTURE YVR ENROUTE LAX, CREW NOTICED NUMBEROUS FAILURES IN AUTOFLIGHT MODE CONTROL PANEL.NOT ABLE TO SELE	CT SPECIFIC HEADING. HEADING INDICATIONS ON CAPT/FO EHSI DIFFERENT.  UNABLE TO SELECT ALTITUDE, ALSO AUTOPILOT WOULD NOT	 CONTROL AIRCRAFT TO SELECTED HEADING OR ALTITUDE.  CREW ELECTED TO RETURN TO YVR.UPON ARRIVAL YVR, MAINTENANCE REPLACED	 THE MODE CONTROL PANEL, AIRCRAFT DISPATCHED. NO FURTHER INCIDENT.			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
2005041800107	20050418	00107	NE  	2005	4	18	CA041022003      	2	20040801	G	7250		TURBINE WHEEL   			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12736					42704268			(CAN) DURING A SCHEDULED CHECK OF THE SECOND STAGE TURBINE BLADES (T2 ) IAW TURBOMECA ASB 292-72-0807 AND AD2004-047 IT 	WAS DETERMINE THE BLADE SHIFT HAD FAILED THE CHECK. THE GAS GENERATOR WAS REPLACED					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041800108	20050418	00108	EU  	2005	4	18	CA041022004      	1	20040909	G	7722		INDICATOR       			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					EGT/TIT	FAILED          	W				E				ENGINE SHUTDOWN         				M	N		OVER TEMP                 	FALSE WARNING             		NR	NOT REPORTED   	1			CA											(CAN) DURING NORMAL FLIGHT CONDITIONS, ENGINE ITT APPROACHED 900C ACCOMPANIED BY A REDUCTION IN TORQUE ANDN1 AND N2 SPEE	DS.  THE PILOT REDUCED POWER SETTING TO IDLE AND SUBSEQUENTLY SECURED THE ENGINE IN FLIGHT. AN SINGLE ENGINE LANDING WAS	 ACCOMPLISHED.  SUBSEQUENT ENGINE RUNS AND ASSOCIATED TROUBLESHOOTING WERE UNABLE TO REPRODUCE THE CONDITION.  DURING IN	VESTIGATION, THE EEC GROUND STRAP WAS FOUND LOOSE.			1	G	7	2 	3U	3	U	O	H88EU   	E42NE
2005041800109	20050418	00109	EU  	2005	4	18	CA041022005      	1	20041004	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT WAS DOING HIS PREFLT HYD TESTS AND THEY FAILED. AFTER TROUBLESHOOTING HYDRAULIC SYSTEM  FOUND THAT ONE LATER	AL SERVO WAS THE CAUSE OF THIS MOVEMENT EVEN THOUGH DURING OUR TROUBLESHOOTING THE LATERAL SERVOS WERE SWAPPED OVER BUT 	THE PROBLEM STAYED GOING TO THE RIGHT. REMOVED FAULTY SERVO AND INSTALLED FRESHLY OVERHAULED SERVO.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005041800110	20050418	00110	CE  	2005	4	18	CA041025001      	1	20041020	G	3231	05411066	BELLCRANK       	CESSNA      		CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					GEAR DOOR	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LANDING GEAR IDLER BELCRANK PN 0541106-6 ON NR 2 MAIN LANDING GEAR, GEAR DOOR CONTROL LOBE FOUND SEVERED RESULTING	 IN GEAR DOOR HANGING DOWN. UPON INSPECTION OF RT LANDING GEAR SYSTEM FOUND A CRACKED WELD ON THE NR 2 TORQUE TUBE ASSEM	BLY RESULTING FROM BINDING CONTROL ROD THAT WAS PREVIOUSLY ATTACHED PN 504510-18 AT THE GEAR DOOR CONTROL LOBE				1	L	7	2 	3O	3	O		A7CE    	E8CE
2005031400099	20050314	00099	CE  	2005	3	14	CA041025002      	1	20041014	G	2460	70HF10	DIODE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	DUAL FEED BUSS	BURNED          	W				O				OTHER                   				F	H	I	FLT CONT AFFECTED         	ELECT. POWER LOSS-50 PC   	FLT. ATTITUDE INST.       	CL	CLIMB          	1			CA											(CAN) EXPERIENCED NR1 DUAL FED BUS FAILURE IN FLT.  NR 1 DUAL FEED BUSS EQUIP BECAME DE-ENERGIZED.  AC LANDED WITHOUT IN	CIDENT.  MAINT DISCOVERED BOTH DIODES BURNED OPEN ON NR1 DUAL FEED BUSS SYS.  REPLACED DIODES WITH NEW, PERFORMED DUAL B	USS CONFORMITY CHECK IAW MM TO CHECK BUSSES NR 1 THRU NR 4.  AC CERTIFIED AND RELEASED FOR FLT.  SUSPECTED 1 OF 2 DIODES	 ORIGINALLY FAILED, CAUSING SECOND DIODE TO TAKE REMAINING LOAD, CAUSING ITS LIFE TO BE SHORTENED.  IT ALSO APPEARED THA	T THESE DIODES HAD BEEN CHANGED IN PAST.  SUSPECTED THAT DIODES MAY HAVE BEEN INCORRECTLY INSTALLED, DID NOT APPEAR TO B	E VERY SECURE IN DIODE ASSY (50-354308-21).  VERY POOR INFO ON CORRECT INSTALLATION OF DIODES.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE
2005041800111	20050418	00111	NM  	2005	4	18	CA041025003      	1	20041025	G	5730	DHC8102	SKIN            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE HEAVY MAINTENANCE INSPECTION WIDESPREAD LEVEL ONE CORROSION WASFOUND ON THE UPPER WING SKIN AT TH	E MATIN SURFACES OF THE FORWARD AND REAR SPARS. INITIALLY LEVEL ONE CORROSION WAS FOUND JUST AHEAD OF THE REAR SPAR AND 	JUST AFT OF THE FORWARD SPAR. FURTHER INVESTIGATION THROUGH CUTTING SAMPLES OUT OF THE SKIN, AT BOTH THE FORWARD AND REA	R SPARS, REVEALED THAT LEVEL ONE CORROSION WAS ALSO PRESENT AT THE SPAR TO SKIN MATING SURFACE. THE CORROSION THAT WAS F	OUND WAS ISOLATED TO THE DRY BAY PORTIONS OF THE WING (STN. YW171.200 PORT TO STA YW171.200 STARBOARD AND OUTBOARD OF ST	A. YW405.00 ON BOTH WINGS). CORROSION WAS LIMITEDTO THE SKIN ONLY AND WAS NOT EVIDENT ON THE SPARS.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100078	20050201	00078	EU  	2005	2	1	CA041025004      	1	20040929	G	5310	350A38101891	CROSSBEAM       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BI-DIRECTIONAL CROSSBEAM WAS IN FOR NDT INSPECTION IAW AD96-156-071(B)R1.  THE NDT AMO FOUND THE CROSSBEAM CRA	CKED IN THE CUP OR AS INDICATED IN SB05-00- 28 'R' REGION.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041800112	20050418	00112	NE  	2005	4	18	CA041026001      	2	20041022	G	7200		ENGINE          			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1	MALFUNCTIONED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			18532					AG0049			(CAN) FROM A PILOT REPORT RECTIFICATION, A GROUND RUN OF THE NR 1 ENGINE WAS REQUIRED FOLLOWING A COMPONENT CHANGE. DURI	NG THE START CYCLE OF THE GROUND RUN. THE LAME CONDUCTING THE GROUND RUN IDENTIFIED AN ENGINE VIBRATION THROUGH THE FLIG	HT DECK CONTROL CONDITION LEVER. NO FLIGHT CREW HAD WRITTEN UP AN ENGINE VIBRATION DEFECT PRIOR TO THIS GROUND RUN. FURT	HERMORE WITH THE ENGINE AT IDLE SPEED THE VIBRATION COULD BE INCREASED/DECREASED WITH SOME MANIPULATION OF THE CONDITION	 LEVER. FOLLOWING EXTENSIVE COLLABORATION WITH THE ENGINE MANUFACTURER AND FOLLOWING SUGGESTED TROUBLESHOOTING, ON ADVIS	E FROM THE MANUFACTURER THE ENGINE WAS REMOVED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800113	20050418	00113	NE  	2005	4	18	CA041026002      	2	20041023	G	7200		ENGINE          			AGUSTA	A109  	A109        	0260109	EU  	PWC   	PW206C	PW206C      		NE  					NR 1 ENGINE	FLUCTUATES      	W				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA								BC0391			(CAN) ON A 'CAT A' TAKE-OFF (DURING THE REVERSING PHASE) THE PILOT REPORTED TORQUE FLUCTUATIONS ON THE NR 1 ENGINE. ALL 	ENGINE PARAMETER THEN WENT TO ZERO (ENGINE OUT). THE PILOT LOST CONTROL OF THE A/C, ITTURNED LT AND THE TAIL HIT AN OBST	ACLE. THE PILOT COMPENSATED BY TURING RIGHT AND THE TAIL HIT THE SAME OBSTACLE AGAIN AFTER WHICH THE A/C FLIPPED ON ITS 	SIDE.IT WAS ALSO REPORTED THAT THE PILOT HA D DIFFICULTIES STARTING THE NO. 1 ENGINE BEFORE THE FLIGHT.  P&WC WILL INVES	TIGATE THE INCIDENT AND UPDATE THIS SDR ONCE ROOT CAUSE HAS BEEN ESTABLISHED.		1	G	7	2 	3U	3	U		H7EU    	E42NE
2005041800114	20050418	00114	NM  	2005	4	18	CA041026003      	1	20040928	G	3270	141169	ACTUATOR        			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					TAIL SKID	CRACKED         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) DURING CLIMB A SYSTEM HYDRAULIC QUANTITY DROPPED TO 1.5 GALLONS LOW LEVEL LIGHT ILLUMINATED. AIRCRAFT RETURNED TO 	STATION.TROUBLE SHOOTING REVEALED TAIL SKID ACTUATOR BODY CRACKED.RECTIFICATION: TAIL SKID ACTUATOR REPLACED IN ACCORDAN	CE WITH M/M.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2005041800115	20050418	00115	NM  	2005	4	18	CA041026004      	1	20041025	G	2510	1B11071	TUBE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	SEAT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			29378			070					(CAN) CRACKS FOUND ON BOTH TUBE-WELDED BASE OF CO-PILOT'S SEAT ASSY P/N 1108-3AA. TUBE P/N 1B1107-1 AS PER AMI SEATING S	YSTEMS COMPONENT MAINTENANCE MANUAL CHAP 25-11-08 , FIGURE 5 , ITEM 540 ON PAGE 1062.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800116	20050418	00116	WP  	2005	4	18	CA041026005      	1	20041022	G	5270		TARGET          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					DOOR WARNING SYS	BENT            	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT ABORTED TAKE OFF DUE TO FWD CARGO DOOR ANNUNCIATION CAME ON. MAINTENANCE FOUND THE CARGO DOOR PROXIMITY T	ARGET BENT.  PROX TARGET ADJUSTED AS PER AMM AND AIRCRAFT RELEASED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041800117	20050418	00117	NM  	2005	4	18	CA041026006      	1	20041025	G	2510	1B11071	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SEAT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						049					(CAN) BOTH WELDED TUBE ASSEMBLIES P/N 1B1107-1FOUND CRACKED IN ROLLER RADIUS AT THE BASE OF THE CAPTAIN'S SEAT ASSY . DE	FECTS WERE NOTED DURING  ROUTINE INSPECTION PROCESS IN THE SEAT SHOP , WHEN THIS SEAT WAS REMOVED OFF THE  AIRCRAFT DURI	NG AHEAVY MAINTENANCE CHECK.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800118	20050418	00118	NM  	2005	4	18	CA041026007      	1	20041025	G	2510	1B11071	TUBE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	SEAT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			32256			068					(CAN) BOTH WELDED TUBE ASSY P/N 1B1107-1 OFF THE PILOT'S SEAT ASSY FOUND CRACKED DURING AN INSPECTION OF THE SEAT IN THE	 SEAT SHOP DURING A SHOP VISIT WHILE THE AIRCRAFT WAS UNDERGOING A HEAVY MAINTENANCE CHECK.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800119	20050418	00119	SO  	2005	4	18	CA041026008      	2	20041020	G	8530	TIST712ACA	CYLINDER HEAD   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	NR 3 CYLINDER	SEPARATED       	W				C				ABORTED TAKEOFF         				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		AP	APPROACH       	1			CA						1350622					(CAN) NR 3 ALUMUNUM HEAD SEPERATED AT 3RD FIN ABOVE BARRIER. ALL 6 CYLINDERS REPLACED. CYLINDERS THAT WERE REMOVED SENT 	BACK TO MFG FOR MATERIAL EXAMINATION.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL
2005041800120	20050418	00120	NE  	2005	4	18	CA041026009      	2	20041004	G	7314		SEAL            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	FUEL PUMP DRIVE	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) PILOT DISCOVERED EXCESSIVE OIL LEAK AFTER FLIGHT.  MAINTENANCE WAS DISPATCHED TO INVESTIGATE.FUEL PUMP OIL SEAL WA	S FOUND TO BE DISLODGED FROM ITS CARRIER AND HAD MOVED DOWN THE SHAFT INTO THE ENGINE CASE.					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	5	C	P60GL
2005041800121	20050418	00121	EU  	2005	4	18	CA041026010      	1	20041025	G	2121	ETV3454G	FAN             			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					E/E BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			36493								(CAN) DURING FLT THE ACRFT HAD BEEN DIVERTED DUE TO FUMES DETECTED IN THE COCKPIT & CABIN. AIRFRAME VIBRATIONS FROM RT W	ERE REPORTED IN CONJUNCTION WITH THE FUMES. CAPTAIN HAD SELECTED OFF PACK NR 2 AND ECAM MESSAGE VENT BLOWER FAULT OCCURR	ED SIMULTANEOUSLY, FUMES DISSIPATED RAPIDLY & ACRFT LANDED SAFELY. FURTHER INVESTIGATIONS CARRIED OUT BY TECHNICAL STAFF	 REVEALED THAT THE AVIONICSFAN WAS THE SOURCE OF FUMES AND VIBRATIONS (CIRCUIT BREAKER FOUND POPPED OUT).			2	L	7	2 	4F	4	F	RT	A28NM   	E311NE
2004120900135	20041209	00135	WP  	2004	12	9	CA041026011      	1	20041025	G	6320	369D25102SN006	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEVERE CORROSION FOUND IN OIL GALLERY BEHIND M/R XMSN UPPER BEARING LINER FOR 369D25149 AND 369D25148 BEARINGS.  P	ROBLEM INITIALLY INDICATED BY LACK OF FLOW FROM OIL ORFICES.  CORROSION FOUND BY REWORK FACILITY DURING LINER REMOVAL, A	ND WAS UNDETECTABLE WITHOUT REMOVAL OF LINER.				1	G	7	1 	3U	3	U		H3WE    	E4CE
2004123000004	20041230	00004	CE  	2004	12	30	CA041026012      	1	20041026	G	2720		SHAFT           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RUDDER PEDAL	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											PILOTS LT RUDDER PEDAL BROKE AT THE UPPER PEDAL SHAFT.  THE PEDAL WAS FOUND BROKEN AFTER COMPLETION OF A FLIGHT.  RUDDER	 PEDAL WAS REPLACED.  INSPECTION OF THE PEDAL REVEALED WORN SHAFT ATTACHMENT HOLES.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920
2004123000005	20041230	00005	SW  	2004	12	30	CA041027001      	1	20041025	G	6320	206031509005	DRAG PIN        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GEARBOX YOKE	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						BKW10299					AFT CAST SURFACE OF DRAG PIN ASSY THAT IS PART OF M/R GEARBOX CONTACTED YOKE OF ISOLATION MOUNT. CONTACT DUE TO EXCESSIV	E CASTING MATERIAL AFT OF BEARING BORE. COMPONENT SHOP  RECEIVED AN ISOLATION MOUNT FOR REPAIR THAT HAD FRETTING/CONTACT	 MARKS ON YOKE. MARKS WERE CONSISTENT WITH DRAG PIN RUBBING/CONTACTING. BASE THAT ISOLATION MOUNT RECEIVED FROM INFORMED	, & DRAG PIN & GEARBOX WERE REMOVED & FORWARDED TO US. WHEN RECEIVED DRAG PIN, WAS APPARENT THAT DRAG PIN BEARING BORE W	AS NOT SYMMETRICAL IN CASTING.		1	G	7	1 	3U	3	U		H2SW    	E4CE
2005031100022	20050311	00022	NM  	2005	3	11	CA041027002      	1	20041020	G	5510	4472R170	BRAKE           	BOEING      		BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					STAB TRIM	CONTAMINATED    	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA						6937171					(CAN) DURING DECENT, WHEN LEVELING AT 6000FT CREW EXPERIENCED DIFFICULTY IN CAPTURING ALTITUDE. PROBLEM WAS QUICKLY DETE	RMINED TO BE HORIZ STABILIZER TRIM.  TRIM WHEEL WAS VERY STIFF TO MOVE BOTH MANUALLY AND ELECTRICALLY WHEN TRIMMING NOSE	 UP. AC LANDED WITHOUT FURTHER INCIDENT AFTER CARRYING OUT STABILIZER JAM CHECKLIST. MAINT FOUND  LARGE QUANTITY OF WATE	R IN THE AUX  BRAKE SHOE HSG.  STABILIZER BRAKE, HIGH SPEED ACTUATOR AND LOW SPEED ACTUATOR REPLACED IAW AMM.   STABILIZ	ER TRIM TESTED WITHOUT FURTHER DIFFICULTY, AIRCRAFT RETURNED TO SERVICE.  IN LITE OF THESE FINDINGS, WE ARE INITIATING A	 FLEET CAMPAIGN TO INSPECT THE ENTIRE FLEET FOR SIMILAR DEFECTS, AND CORRECT AS NECESSARY.	2	L	7	3 	4F	4	F		A3WE    	E2EA
2005041800122	20050418	00122	NM  	2005	4	18	CA041027003      	1	20041026	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, AN AIRCRAFT HAD A HYDRAULIC FAILURE CAUSED BY CRACKED NR 2 ENGINEDRIVEN PUMP. UNSCHEDULED LANDING CO	MPLETED. AIRCRAFT WAS CHECKED AFTER REPLACEM ENT OF PUMP, A TESTFLIGHT WAS DONE, BEFORE PUT BACK INTO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041800123	20050418	00123	WP  	2005	4	18	CA041028001      	2	20041026	G	7230	TVT10728H3	COMPRESSOR      			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PRIOR TO DEPARTURE NOISE AND VIBRATION WAS OBSERVED COMING FROM THE AREA OF THE TURBOFAN. THE AIR CONDITIONING WAS	 SHUT DOWN AND THE PROBLEM DISAPPEARED. THE TURBOFAN WAS CHANGED AND THE FAULT CLEARED. THE FAILED UNIT EXHIBITED TURBIN	E BLADE TIP RUB PROBABLY DUE TO A FAILED BEARING IN THE FAN SHAFT.				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE
2005031400094	20050314	00094		2005	3	14	CA041029001      	4	20041028	G	2562	ELT200	ELT             			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) APPROXIMATELY 3 HOURS AFTER LANDING, ATC INFORMED THE COMPANY THAT THEY HAD A STRONG ELT SIGNAL.  AFTER CHECKING A	LL AIRCRAFT IT WAS NOTICED THAT THE ELT ON THIS AIRCRAFT WAS ACITVATED.  THE SWITCH WAS IN THE ARM POSITION AND THE INDI	CATOR LIGHT WAS ON.  SEVERAL ATTEMPTS WERE MADE TO RESET THE ELT.  THE ELT WAS REMOVED.  AS SOON AS IT WAS MOVED IT QUIT	 TRANSMITTING AND WOULD NOT START AGAIN.  REMOVED THE COVER AND FOUND A SUBSTANTIAL AMOUNT OF WATER INSIDE, BOTH AROUND 	THE BATTERY AND THE SEALED SWITCHES AND BOARDS.  THE ELT HAS BEEN SENT FOR REPAIR.THE ELT WAS DUE FOR RECERTIFICATION DE	CEMBER 19/04, THE BATTERY WAS DUE FEB/06.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
2005041800124	20050418	00124	EA  	2005	4	18	CA041029002      	1	20041018	G	7830	SM141038	BEARING         			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502L2    	41580	NE  					THURST REVERSER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING 600 HRS INSPECTION OF NR 1 ENGINE AME NOTICED THAT THE LT THRUST REVERSER STRUT LOWER ATTACHEMENT WAS CHAFI	NG AGAINST BRACE UPPER, AFTER CARRYING OUT AN INVESTIGATION WE NOTICED THAT THE BRACE UPPER BEARING HAD MIGRATED .110 PA	RT SENT FOR REPAIR TO BAS.				2	L	7	2 	4F	4	F	RT	A21EA   	E6NE
2005031400095	20050314	00095	EA  	2005	3	14	CA041029003      	2	20040910	G	7200		ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AN OIL PRESSURE FLUCTUATION WAS OBSERVED IN FLIGHT FOLLOWED BY A LOUD NOISE ACCOMPANIED BY A LOSS-OF-GENERATOR AND	 FIRE INDICATION.  THE ENGINE WAS SECURED IN-FIGHT AND THE FIRE WARNING ABATED.  A SINGLE-ENGINE LANDING PERFORMED.  SUB	SEQUENT INSPECTION REVEALED A FRACTURED REDUCTION GEARBOX SUN GEAR, FRACTURED POWER TURBINE AND COMPRESSOR TURBINE BLADE	S AND ASSOCIATED CASING DAMAGE. MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL AMEND THIS SDR TO REFLECT ROOT	 CAUSE ONCE IT HAS BEEN ESTABLISHED.		1	L	7	2 	4T	4	T	RT	A21SO   	E4EA	6	C	P15EA
2004121000001	20041210	00001	NE  	2004	12	10	CA041029004      	2	20041026	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  		LEAKING         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB A LOUD BANG WAS HEARD ACCOMPANIED BY YAW AND INDICATIONS OF ENGINE STOPPAGE. AN EMERGENCY WAS DECLARED AN	D THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. THE CREW REPORTED THE PROPELLER DID NOT FEATHER ON SHUTDOWN AND ALTERNATE	 FEATHER PROCEDURES WERE EMPLOYED. AN EXTERNAL OIL LEAK WAS VISIBLE DURING POST FLIGHT INSPECTION.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004122900201	20041229	00201	SW  	2004	12	29	CA041029005      	1	20041024	G	6230	206040036101	BEARING         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R MAST	SPALLED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						FAJF56564					THE AIRCRAFT WAS ON A FLIGHT WHEN A TRANSMISSION CHIP LIGHT OCCURRED, APPROPRIATE ACTION WAS TAKEN. THERE WAS FERROUS ME	TAL FOUND ON THE TRANSMISSION OIL MONITOR AND TRANSMISSION CHIP DETECTORS.  THE TRANSMISSION AND MAST WERE REMOVED FOR I	NVESTIGATION.  THE M/R MAST ASSEMBLY WAS DISASSEMBLED, THE INNER RACE OF THE MAST BEARING WAS FOUND TO HAVE SPALLED AND 	WAS CREATING THE FERROUS METAL. NOTE: THE M/R TRANSMISSION WAS ALSO DISASSEMBLED AND NO DISCREPANCY WAS FOUND FOR THE CH	IP LIGHT.		1	G	7	1 	3U	3	U		H2SW    	E4CE
2004122900202	20041229	00202	SW  	2004	12	29	CA041029006      	1	20041029	G	7714	2514022A649	TACH GENERATOR  	RROYCE      		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GEARBOX	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAG36424					OUT OF THE FOUR MOUNTING PAD EARS, ONE EAR WAS FOUND COMPLETELY BROKEN OFF.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2004122900203	20041229	00203	GL  	2004	12	29	CA041029007      	3	20041029	G	6114	D2483	HUB             	HARTZL      		PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BG3218					PROPELLER REMOVED FROM AIRCRAFT FOR 10 YR O/H.  UPON VISUAL INSPECTION OF HUB, CORROSION BEYOND REPAIRABLE LIMITS WAS FO	UND IN THE BLADE 'O' RING GROOVES.  MANUFACTURERS RECOMMENDED TBO IS 2000 HRS OR 72 MONTHS.  THIS PROPELLER HAS EXCEEDED	 THE CALENDAR TBO BY 48 MONTHS.				1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA
2005020100074	20050201	00074	GL  	2005	2	1	CA041029008      	3	20041029	G	6114	D2483	HUB             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									BG2075		(CAN) PROPELLER REMOVED FROM AC FOR 10 YR. O/H.  UPON VISUAL INSPECTION OF THE HUB CORROSION WAS FOUND ON THE MOUNTING F	LANGE AND  O-RING GROOVE OF THE REAR HUB HALF. THIS CORROSION IS BEYOND REPAIRABLE LIMITS. MANUFACTURERS RECCOMENDED TBO	 IS 2000 HOURS OR 72 MONTHS. THIS PROPELLER HAS EXCEDED THE RECOMMENDED CALENDAR TBO BY 48 MONTHS.				1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA
2005041800125	20050418	00125	NE  	2005	4	18	CA041029009      	2	20041026	G	7200	3038300	ENGINE          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 2	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA			28991					TM123112			(CAN) DURING CLIMB AT 11,000 FT FLIGHT CREW HEARD A 'BANG' FOLLOWED BY AIRCRAFT YAW.  NR 2 ENGINE FAILED AND WAS SHUT DO	WN AND FEATHERED USING ALTERNATE FEATHER. AIRCRAFT RETURNED FOR NORMAL SINGLE ENGINE LANDING AT DEPARTURE AIRPORT. NR 2 	ENGINE ASSEMBLY REPLACED. AIRCRAFT RETURNED TO SERVICE. ENGINE RETURNED TO OVERHAUL FACILITY. TEARDOWN REPORT WILL BE FO	RWARDED TO TSB WHEN AVAILABLE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800126	20050418	00126	NM  	2005	4	18	CA041029010      	1	20041025	G	2611	3023143	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CARGO BAY	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) DURING DESCENT , INTERMITTANT BAGGAGE SMOKE WARNING. CREW ELECTED TO DON OXYGEN MASKS AND ADVISE AIRPORT EMERGENCY	 RESPONSE. UPON ARRIVAL NO EVIDENCE OF SMOKE OR FIRE FOUND. BAGGAGE SMOKE DETECTOR REPLACED. REMOVED UNIT TESTED AS NO F	AULT FOUND. AIRCRAFT RETURNED TO SERVICE WITH REPLACEMENT SMOKE DETECTOR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800127	20050418	00127	NE  	2005	4	18	CA041031001      	2	20041026	G	7314	6078TP04	PUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED CHECKS ON ENGINE, WE FOUND FUEL LEAK COMING FROM 'MAIN FUEL PUMP INLET PORT BODY' OF RT ENGINE. L	EAK WAS DETECTED ACTIVATING THE FUEL BOSST PUMP. LEAK CAN BE DESCRIBED AS FOLLOW:  CAPILLARY LEAK,  LEAK JET ABOUT 3 INC	HES LONG VAPOURIZING AT THE END. PART WAS REPLACED A/C IS BACK IN SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031400096	20050314	00096	EA  	2005	3	14	CA041031002      	1	20041027	G	5610	NP13932211	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE PILOT SIDE WINDOW CRACKED WHILE IN CRUISE. THE WINDOW WAS REPLACED IN ACCORDANCE WITH AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005031400097	20050314	00097	EA  	2005	3	14	CA041031003      	1	20041025	G	5610	NP1393221	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			20389								(CAN) THE PILOT SIDE WINDOW CRACK WHILE IN APPROACH. THE WINDOW WAS REPLACED IAW AMM.						2	L	7	2 	4F			RT	A21EA
2004121000002	20041210	00002	NM  	2004	12	10	CA041101001      	1	20041024	G	3230		ROD END         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG ACTUATOR	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA						DCL12086					(CAN) UPON GEAR DOWN SELECTION ON APPROACH A LOUD THUMP AND THE AIRCRAFT JOLTED. 3 GREEN AND LANDED WITHOUT INCIDENT. UP	ON INSPECTION BY MAINTENANCE FOUND THE RT MLG RETRACTION ACTUATOR ROD END BROKEN. RT MLG RETRACTION ACTUATOR REPLACED GE	AR SWINGS CARRIED OUT WITH NO FATHER FAULTS FOUND.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004123000010	20041230	00010	CE  	2004	12	30	CA041101002      	1	20041025	G	2910	2307006101	HOSE            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					HYD SYSTEM	LOOSE           	W				B				EMER. DESCENT           				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											AT CRUISING ALTITUDE, FLIGHT CREW NOTICED A DROP IN MAIN HYDRAULIC PRESSURE.  WHEN CREW START TO APPROACH THE HYDRAULIC 	WAS PRESSURE LOW.  LANDING GEAR WERE SELECTED DOWN AND ALL PRESSURE WAS LOST.  MAINTENANCE FOUND THE B-FITTING LOOSE ON 	THE NOSE LANDING GEAR ACTUATOR HYDRAULIC UPPER PORT.  FITTING TIGHTENED, GEAR SWING COMPLETED.  NO LEAKS FOUND. REFER TO	 LR35 IPC 32-31-05 FIG 5 ITEM 140-141.			2	L	7	2 	4F	4	F		A10CE   	E6WE
2004123000011	20041230	00011	EA  	2004	12	30	CA041101004      	2	20041020	G	8520	10360BIE	CRANKCASE       			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L445051A			THE ENGINE HAD AN OIL LEAK AT THE LT FRONT OF THE CRANKCASE.  IT WAS CLEANED.  A CLOSE CHECK FOUND TWO CRACKS LEAVING OI	L.  THE ENGINE WAS REMOVED AND SENT OUT FOR REPAIRS.					1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920
2005031100014	20050311	00014		2005	3	11	CA041101005      	4	20040907	G	3418	25147A7L1T2	TRANSDUCER      			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					AOA	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING A LINEARITY CHECK IAW MFG TASK JIC NR 27-35-04-101 (SEE ALSO S/B A604-27-011, REV 1, PART A, B) B	OTH LT AND RT AOA TRANSDUCERS WERE FOUND TO BE BEYOND SERVICE LIMITS.   BOTH ASSEMBLIES WERE REPLACED WITH IMPROVED TRAN	SDUCER ASSEMBLIES, P/N 600-59154-5.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031400090	20050314	00090	EA  	2005	3	14	CA041101007      	1	20041031	G	2422	DH103024600CS11B	INVERTER        			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	COCKPIT	FAILED          	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, FLIGHT CREW DETECTED SMOKE IN THE COCKPIT , PRIMARY INVERTER CAUTION LIGHT ILLUMINATED, AIRCRAFT DI	D EMERGENCY DESCENT AND DIVERSION TO NEAREST ALTERNATE AIRPORT FOR NORMAL LANDING.  SMOKE HAD DISSIPATED PRIOR/ON ARRIVA	L.  MAINTENANCE INSPECTION FOUND PRIMARY INVERTER UNSERVICEABLE, INVERTER REPLACED.  AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031400091	20050314	00091	EA  	2005	3	14	CA041101008      	1	20041020	G	5740	600913563	BRACKET         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					TRANSMITTER	MISINSTALLED    	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ATTEMPT, THE GREEN TAKE-OFF CONFIGURATION WARNING CAME ON.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004121000003	20041210	00003	NE  	2004	12	10	CA041101009      	2	20041026	G	7200	MS949034	BOLT            								PWA   	PT6   	PT6A65AR    	52043	NE  					ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENG SHUTDOWN IN FLT DUE TO TORQUE FLUCTS & LOW OIL PRESS. 6 BOLTS USED TO ASSEMBLE 1ST STAGE CARRIER ASSY. 2 OF 6 	BOLTS FAILED DURING OPS. 1 BOLT HEAD FOR 1ST STAGE CARRIER ASSY FRACTURED IMMEDIATELY UNDER BOLT HEAD. HEAD OF BOLT LODG	ED INTO 1ST STAGE REDUCTION GEAR TRAIN, RESULTING IN DEBRIS & FRACTURING OF 1ST STAGE RING GEAR. DEBRIS IN LAST CHANCE F	INGER STRAINER IN RGB, PREVENTING OIL SCAVENGING. RESULTED IN RGB FILLING WITH OIL, & NO OIL BEING RETURNED TO REPERISH 	OIL TANK. OIL TANK RAN LOW ON OIL CAUSING LOW OIL PRESS.  TORQUE FLUCTS RESULT OF DAMAGED RING GEAR & LOW OIL PRESS. 2ND	 BOLT FRACTURED IN ASSY, BUT STAYED IN ASSY & DIDN`T CAUSE SHUTDOWN. BOLTS WERE RE-INSTALLED DURING OVERHAUL.						4	T			E4EA
2004122900196	20041229	00196	NE  	2004	12	29	CA041101010      	2	20041030	G	7261	304544901	CHIP DETECTOR   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RGB	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING INSPECTION IT WAS NOTICED THAT THE CHIP DETECTOR CONNECTOR WAS SITTING AT AN ANGLE.  THE PLUG WAS LOCKWIRED BUT W	HEN THE LOCK WIRE WAS REMOVED.  THE CONNECTOR WAS LOOSE.  WHEN THE CONNECTOR WAS REMOVED, NOTICED THAT THE THREADS ON TH	E CHIP DETECTOR WERE DAMAGED AND ONE OF THE PINS WAS BROKEN.  THE CHIP DETECTOR WAS REMOVED AND NEW UNIT WAS ORDERED AND	 INSTALLED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020100079	20050201	00079	EU  	2005	2	1	CA041102001      	1	20041102	G	1430	NAS6605D136	BOLT            			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					RT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13548								(CAN) MSN 419 WAS UNDERGOING A C2 CHECK IN YUL.  IN PREP FOR DOING A SEAL CHANGE ON RT MLG MAINT DISCOVERED SM9 PIN MIGR	ATED APPROX. 1INCH OUT IN THE IB DIRECTION.  GEAR WAS SPLIT,AND IT WAS DISCOVERED THAT THE SM9 PIN RETENTION BOLT (NAS66	05D136) HAD SHEARED AT THE HEAD.  THE BOLT RETAINS THE PIN END CAPS.  CAMPAIGN NR 9-0066 WAS LAUNCHED ON NOV 1 2004 TO I	NSPECT ALL ACFT IN FLEET A330/A340.			2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2005032400030	20050324	00030	SW  	2005	3	24	CA041102002      	1	20041102	G	6330	269A5193001	CARRIAGE        			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					M/R TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						S0602					DURING A SCHEDULED 4200 HR O/H THE ABOVE DESCRIBED CARRIER WAS FOUND TO HAVE 3 CRACKS AT 3 SEPARATE LOCATIONS IN THE CAR	RIER TO COUPLING MOUNTING HOLE LOCATIONS.  THESE CRACKS WERE DETECTED DURING FLUORESCENT PENETRANT INSPECTION.  FOR THE 	FUTURE A MIDLIFE INSPECTION MAY BE AN OPTION TO DETECT THESE CRACKS, AS THIS AREA HAS BEEN PRONE TO CRACKS IN THE PAST.				1	G	7	1 	3O	3	O	O	4H12    	E286
2005041800128	20050418	00128	NM  	2005	4	18	CA041102003      	1	20041118	G	5753		CARRIAGE        			BOEING	737   	737248C     	1384415	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPONENT REPLACEMENT AT HEAVY CHECK, A TYPICAL CRACK WAS DETECTED AT THE SPINDLE JOURNAL FORWARD END ON FL	AP CARRIAGE NR 7.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2005041800129	20050418	00129	CE  	2005	4	18	CA041102004      	1	20041123	G	2560	S21994	SEAT BELT       			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					CABIN	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING AN ACCEPTANCE INSPECTION, SEAT BELTS WERE REMOVED FOR 10 YEAR REWEBBING.  BELTS WERE REINSTALLED & TESTED. 	ACRT RETURNED TO SERVICE & WENT ON ITS FIRST CHARTER, FRONT RT PAX WENT TO PLACE HIS SEAT BELT ON AND BELT HAD COME OUT 	OF REEL ASSY. PILOTS REEL TESTED FURTHER & IT WAS DETERMINED THE POSSIBILITY OF SAME DEFECT HAPPENING EXISTED.  AIRCRAFT	 REMOVED FROM SERVICE.  BELTS WERE SENT BACK TO THE VENDER TO INVESTIGATE. DURING THE INVESTIGATION STAGE IT ALSO FOUNDT	HAT SOME PILOTS COULD NOT REACH FUEL SELECTOR DEPENDING ON PILOTS SEAT LOCATION.THE VENDER WILL VERIFY BELT LENGTH. ONE 	MUST REMEMBER TO TEST ALL SEAT LOCATION FOR APPROPERIATE BELT LENGTH TO ENSURE PILOTS ARE ABLE TO REACH FUEL SELECTOR.	1	H	7	1 	3O	3	O		A4CE    	E5CE
2005041800130	20050418	00130		2005	4	18	CA041102005      	1	20041028	G	1430	J4RF284001E2029	SCREW           																	FUSELAGE	SHORT           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN) TRANSISTOR SHORTED DUE TO WRONG (METAL) SCREWS INSTALLED IN PLACE OF THE NYLON SCREWS P/N JYRF284-001. HISTORY IND	ICATES THAT THE EL SHORT CAUSED BY METAL SCREWS CAN PRODUCE SMOKE IN CABIN. PHOTO ATTACHED.
2005041800131	20050418	00131	EA  	2005	4	18	CA041102006      	1	20041101	G	3411		PITOT LINE      			DHAV  	DHC8  	DHC8311     	1386006	EA  										PITOT/STATIC SYS	OBSTRUCTED      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ACCOMPLISHMENT OF DEHAVILLAND SB 8-34-221,WHICH PROVIDES INSTRUCTIONS TO MODIFY THE ROUTING OF THE STATIC L	INES CONNECTION, IT WAS NOTICED DURING THE LEAK CHECK THAT THE MAIN STATIC SOURCE LINE WAS INVERTED WITH THE ALTERNATE S	TATIC SOURCE. THIS SB GIVES INTRUCTION TO CONNECT THE NR 3 STATIC SOURCEDIRECTLY TO THE STANDBY ALTIMETER, BYPASSING A S	ELECTOR VALVE AND A MANIFOLD. AS A CORRECTIVE ACTION, THE LINE WERE RECONNECTED PROPERLY AND THE SYSTEM WAS CHECKED SERV	ICEABLE.		2	H	7	2 	4T			RT	A13NM
2004121000004	20041210	00004	NM  	2004	12	10	CA041102007      	1	20041018	G	2435	03600923	BEARING         	LUCAS       		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	STARTER GEN	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			13733			119					(CAN) DURING CRUISE NR 2 DC GENERATOR CAUTION LIGHT ILLUMINATED , UNABLE TO RESET. NORMAL LANDING AT INTENDED DESTINATIO	N. MAINTENANCE INSPECTION FOUND STARTER DRIVE UNABLE TO ROTATE. STARTER/GEN REPLACED. SHOP TEARDOWN FOUND FAILURE OF C.E	, END BEARING.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004122900180	20041229	00180	NM  	2004	12	29	CA041102008      	1	20040904	G	2435	03600923	BEARING         	LUCAS       		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	STARTER GEN	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			27210			694A					AIRCRAFT NR 2 DC GENERATOR CAUTION LIGHT ILLUMINATED, CREW ELECTED TO RETURN FOR NORMAL LANDING AT DEPARTURE AIRPORT.  M	AINTENANCE FOUND NR 2 STARTER GENERATOR END BEARING FAILED CAUSING COOLING FAN TO RUB ON HOUSING.  SHOP TEARDOWN FOUND B	EARING FAILURE AT ANTI-DRIVE END.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004122900181	20041229	00181	NM  	2004	12	29	CA041102009      	1	20041020	G	2435	03600923	BEARING         	LUCAS       		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	STARTER GEN	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			28684			0322					PRIOR TO TAKEOFF, NR 2 DC GEN HOT CAUTION LIGHT ILLUMINATED.  AIRCRAFT RETURNED TO GATE.  STARTER/GEN REPLACED.  SHOP TE	ARDOWN INSPECTION FOUND DRIVE END BEARING FAILED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004122900182	20041229	00182	NE  	2004	12	29	CA041102010      	2	20041102	G	7261	9520011653	RECEPTACLE      			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					CHIP DETECTOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											WHILE CHECKING THE ENG MODULE 05 CHIP PLUG DURING ROUTINE D.I., THE SELF CLOSING VALVE OF RECEPTACLE WAS LEAKING. BY PUS	HING THE CHIP PLUG IN AND OUT SEVERAL TIMES, THE VALVE WOULD CLOSE TIGHT, STOPPING LEAK. A NEW RECEPTACLE WAS THEN ORDER	ED. DUE TO DELAY IN RECEIVING THE PART, THE ENG WAS OPERATED FOR APPROX 75 HRS BEFORE THE RECEPTACLE WAS REPLACED. UPON 	REMOVAL OF THE FAULTY RECEPTACLE, IT WAS OBVIOUS THAT TWO WASHERS WERE CAUSING SELF CLOSING VALVE NOT TO CLOSE PROPERLY,	 ALLOWING IT TO LEAK. THE MANUF WAS CONTACTED AND IT WAS DECIDED TO REMOVE THE ENG FROM SERV UNTIL FURTHER INVEST.  A SI	MILAR WASHER WAS FOUND IN THE MODULE 01 SCAVENGE OIL STRAINER AT 99.9 HOURS.	1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005041800132	20050418	00132	WP  	2005	4	18	CA041102011      	1	20041029	G	1420		PIN             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CONNECTOR	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE PIN 'K' ON THE RECEPTACLE OF THE INDICATOR IS TOO BIG. WHEN THE INDICATOR WAS REMOVED FOR INSPECTION, THE SOCK	ET IN THE PLUG (ACFT SIDE)BROKE IN HALF, LEAVING A PORTION OF THE SOCKET ON THE INDICATOR. AFTER INVESTIGATION WE FOUND 	THE PIN 'K' ON THE INDICATOR WAS TOO BIG, IN A TAPER SHAPE, LIKE A CONE. THE SOCKET INTHE PLUG HAS BEEN REPLACED AND A N	EW INDICATOR INSTALLED. NOTE: PART TSN AND TSOARE UNKNOWN			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041800133	20050418	00133	GL  	2005	4	18	CA041102012      	2	20041026	G	7210		ENGINE          								ALLSN 	250C  	250C20B     	03013	GL  						MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) AFTER CLOSE INSP. OF THE BOTTOM CHIP PLUG, IT WAS FOUND TO HAVE A LARGE AMOUNT OF FERROUS METAL ON IT. THE ENGINE 	WAS REMOVED FROM SERVICE AND SENT TO A REPAIR FACILITY FOR FURTHER INVESTIGATION.										3	U			E4CE
2005041800134	20050418	00134	CE  	2005	4	18	CA041103001      	1	20041102	G	3230	NAS464P538	BOLT            	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					UPLOCK HOOK	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) HYDRAULIC PRESSURE LIGHT AND GEAR UNLOCKED LIGHT REMAINED ON AFTER GEAR RETRACTION. RT MAIN GEAR UPLOCK WAS FOUND 	TO BE STIFF WHEN RETURNING AT IS ORIGINAL POSITION. BOLT AT THE UPLOCK PIVOT WAS FOUND TO BE SEIZED AND CORRODED. BOLT R	EPLACED WITH NEW.				1	L	7	2 	4F	4	F		A22CE   	E00053EN
2005041800135	20050418	00135	EA  	2005	4	18	CA041103002      	1	20041101	G	2410		STATOR          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ALTERNATOR	OPEN            	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						GJAHN677					(CAN) WHILE IN THE CLIMB, CREW REPORTED AN UNCOMMANDED RT ENGINE OVERSPEED. AIRCRAFT RETURNED TO DEPARTURE STATION. TROU	BLESHOOTING TRACED FAULT TO AN OPEN CIRCUIT IN THE RT ENGINE STATOR-ALTERNATOR. STATOR-ALTERNATOR REPLACED. ENGINE OVERS	PEED INSPECTIONS COMPLETED SATISFACTORY. IPC REF 73-21-07-01-040A.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004121000005	20041210	00005	EA  	2004	12	10	CA041103003      	2	20041025	G	8530	72877	TAPPET          			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2003640A			(CAN) METAL FOUND IN OIL SUCTION SCREEN. AFTER REMOVAL OF NR 1 & 2 CYLINDER FOR INSIDE INVESTIGATION. BOTH HYDRAULIC TAP	PET ON THAT CYLINDERS FOUND CORRODED WITH PARTS MISSING ON THE EDGE OF THE BODY.  ENGINE REMOVED. FURTHER REPORTS WILL F	OLLOW BY THE OVERHAUL SHOP.				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA
2004122900186	20041229	00186	SW  	2004	12	29	CA041103004      	1	20041102	G	3230	2751008018	BELLCRANK       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					MLG	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											DURING EXTENSION OF MLG, NOTICED RT MLG WOULD NOT EXTEND. NO INTRANSIT OR DOWN & LOCKED IND. CREW ATTEMPTED A VISUAL TO 	CONFIRM MLG EXTEND BUT COULD NOT SEE IT FROM INSIDE A/C. CREW MANUALLY EXTENDED MLG. MLG PROCEEDED TO COME DOWN & REMAIN	ED LOCKED. MX CONTACTED & FLT PERMIT ISSUED FOR FLT BACK TO BASE. MLG REMAINED DOWN & LOCKED FOR REMAINDER OF FLT. MX SW	UNG MLG & FOUND RT OB MLG POSITIONING BELLCRANK BEARING RIDING ON THE BELLCRANK DUE TO WEAR IN BELLCRANK TRUNNION PIN BU	SHING & PIN CAUSING SIDE TO SIDE 'ROCKING' OF BELLCRANK. MINOR EVIDENCE OF POSITIONING CAM RIDING ON BELLCRANK & NOT BEA	RING, CAN BE SEEN ON BELLCRANK. MX REPLACED BELLCRANK & INSP REMAINING MLG COMPONENTS & SWUNG MLG WITH NO PROBLEMS.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2005021400194	20050214	00194	CE  	2005	2	14	CA041103005      	1	20041025	G	5210	05170281	PUSHROD         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	LT DOOR LATCH	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT DOOR WOULD NOT OPEN AND CLOSE PROPERLY.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005041800136	20050418	00136	NE  	2005	4	18	CA041103006      	2	20041020	G	7321	312267804	FUEL CONTROL    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON ENGINE START UP PRIOR TO DEPARTURE THE ENGINE NG STOPPED ACCELERATING AT 48 PERCENT AND THERE WAS NO RESPONSE T	O POWER LEVER MOVEMENT. THE ENGINE RESPONDED TO THE SELECTION OF HIGH IDLE AND THEN IDLED AT THE CORRECT NG OF 52 PERCEN	T. POWER LEVER RESPONSE WAS THEN NORMAL. AFTER A SHORT TAXI IT WAS NOTICED THAT IDLE HAD DROPPED TO 48 PERCENT AGAIN AND	 THERE WAS NO RESPONSE TO POWER LEVER MOVEMENT. THE ENGINE WAS SHUTDOWN. MAINTENANCE COULD NOT REPRODUCE THE DEFECT DURI	NG SEVERAL STARTS BUT THE FUEL CONTROL WAS REPLACED AS A PRECAUTION. DURING REMOVAL IT WAS NOTICED THAT BLUE DYE WAS IN 	EVIDENCE ON THE DRIVE. THE AIRCRAFT HAS FLOWN SEVERAL TIMES SINCE WITH NO PROBLEMS.	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL
2005041800137	20050418	00137	NM  	2005	4	18	CA041103007      	1	20041019	G	3234	574295	SELECTOR VALVE  			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, LANDING GEAR WOULD NOT EXTEND, ALTERNATE MLG EXTENSION USED.  TROUBLE SHOOTING REVEALED THAT LDG 	SELECTOR VALVE EXTENSION SOLENOID COIL WAS OPENED.  LDG SELECTOR VALVE WAS REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800138	20050418	00138	NM  	2005	4	18	CA041103008      	1	20041103	G	7933	523281	INDICATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 ENGINE	READS LOW       	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA			25384								(CAN) DURING CRUISE NR 1 OIL PRESSURE DROPPED, PRECAUTIONARY SHUTDOWN OF & FEATHER OF NR 1 ENGINE , AIRCRAFT RETURNED TO	 ORIGINATING AIRPORT. MAINTENANCE INSPECTION FOUND OIL PRESSURE, TEMP INDICATOR AT FAULT . INDICATOR REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041800139	20050418	00139	SW  	2005	4	18	CA041103010      	1	20041027	G	7120	206064105102	MOUNT           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION AN AME WAS PERFORMING A VISUAL INSPECTION ON THE ENGINE MOUNTS AND FOUND AN AREA ON THE	 RT MOUNT THAT LOOKED SUSPICIOUS. UPON FUTHER INVESTIGATION (LIGHT SANDING) IT WAS DETERMINED THAT THERE WERE CRACKS & H	OLES IN 2 AREAS OF THE TUBE 180 DEGREES APART. THIS IS THE 2ND CRACKED ENGINE MOUNT WE HAVE FOUND ON 206 L-3'S.				1	G	7	1 	3U	3	U		H2SW    	E1GL
2004121000006	20041210	00006	WP  	2004	12	10	CA041104001      	1	20041102	G	2170		DRAIN           			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					WATER SEPARATOR	OBSTRUCTED      	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, CARGO SMOKE DETECTOR LIGHT CAME ON WITH NO ODOR OR SMOKE IN COCKPIT. EMERGENCY DECLARE AND RETURNED 	AFTER 10 MINUTES AIR TIME. LIGHT EXTINGUISH DURING TAXI. CARGO CONTAINER AND A/C INSPECTED, NOTHING UNUSUAL DETECTED. PR	OBLEM TREATED LIKE A FAULTY DETECTION SYSTEM BY MX PERSONNEL. 1 TEST SWITCH AND 1 SMOKE DETECTOR REPLACE DUE TO SMALL SU	SPECTED DISCREPANCY FOUND. A/C RETURN TO SERVICE. AT FOLLOWING DEPARTURE 1 MX PERSON ON BOARD LOOKED IN CABIN BEFORE TAK	E-OFF AND SAW WATER VAPOR COMING OUT OF AIR CON SYS, INCREASE THE TEMP AND MIST DISAPPEAR. AFTER ARRIVAL, MX PERSONNEL D	ISCOVER THE WATER SEPARATOR DRAIN WAS OBSTRUCTED BY FOD. SYS CLEANED AND A/C RETURN TO SERVICE WITH NO FURTHER REPORT.	2	L	7	2 	4R	4	T		6A6     	E282
2004122900189	20041229	00189	WP  	2004	12	29	CA041104002      	1	20041102	G	2612		FIRE DETECTOR   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											TAKEOFF REJECTED DUE TO MASTER CAUTION LIGHT ILLUMINATED.  MAINTENANCE FOUND BREAKER B1-191 FOR RT ENGINE FIRE LOOP POPP	ED.  ENGINE FIRE LOOP INSPECTED FOR CONDITION, NO FAULT FOUND.  BREAKER RESET AND AIRCRAFT DISPATCHED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004122900190	20041229	00190	SW  	2004	12	29	CA041104003      	1	20041104	G	3220	315435	LEAF SPRING     			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TAIL WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CENTER LEAF SPRING FOUND BROKEN AT ASSY ALIGNMENT DIMPLE.  ALL FLEET A/C LEAF SPRINGS WHERE REPLACED APPROX JUNE 2003. T	HIS IS THE 4RTH A/C SPRING ASSY FAILURE IN 3 MONTHS.  SUSPECT ALL FLEET AIRCRAFT LEAF SPRINGS ARE DEFECTIVE AND SPLAYING	/STRAINING TO FAILURE.				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874
2004122900191	20041229	00191	NM  	2004	12	29	CA041104004      	1	20041104	G	2422	DH103024600	INVERTER        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ELECTRICAL	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											DURING CLIMB-OUT, FLIGHT CREW IDENTIFIED A BURNING SMELL (NO SMOKE) IN CABIN AND COCKPIT.  AIRCRAFT CONDUCTED AN AIR RET	URN BACK BATEAUX INVERTER REPORTED TO FLICK ON BRIEFLY.  PRECAUTIONARY REPLACEMENT OF AUX INVERTER CARRIED OUT.  INVERTE	R ASSEMBLY SENT FOR INVESTIGATION AND REPAIR.  QUANTITY 3 CAPACITORS REPLACED AND UNIT TESTED SERVICEABLE.  INVERTER PN.	 DH-1030-24-600-CS11B			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005021400195	20050214	00195	EU  	2005	2	14	CA041104005      	1	20041102	G	3242	16104700	WHEEL           			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MLG	CRACKED         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) CREW FELT LOSS OF BRAKE PRESSURE ON RT SIDE.  RETURN TO RAMP.  MAINT FOUND NR 3 IB  WHEEL HALF BROKEN CAUSING BRAK	E UNIT TO DETACH FROM BRAKE DISK.  BRAKE UNIT FOUND ON TAXIWAY BY AIRPORT OPS. GIVEN TO TC OUTSIDE OF THEIR SOPS. LOCAL 	TC OFFICE, RETAINED POSSESSION OF BRAKE UNIT AND WILL NOT RETURN UNIT, DESPITE ENDEAVORS TO RETRIEVE FOR OWNER. THEREFOR	E UNABLE TO DETERMINE ORIGINAL CAUSE OF FAILURE WHETHER WHEEL HALF OR BRAKE UNIT FAILED FIRST.			1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920
2005041800140	20050418	00140	CE  	2005	4	18	CA041104007      	1	20041103	G	3251	1158200557	SUPPORT         			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE SUPPORT BRACKET FOR THE STEERING IN THE UPPER LT CORNER WAS FOUND CRACKED.						1	L	7	2 	3T	4	T		A14CE   	E4EA
2005041800141	20050418	00141		2005	4	18	CA041104008      	4	20041104	G	2562	BS2173	BATTERY PACK    	DORNEMARGLN 		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ELT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						12401E					(CAN) UPON ROUTINE 12 MONTH INSPECTION OF TH SUBJECT ELT, IT WAS OBSERVED THAT THE BATTERY HAD LEAKED, SHORTED OUT THE E	LT MAIN BOARD AND HAD PRODUCED MAJOR AMOUNTS OF BURNING. ELT BATTERY WAS MANUFACTURED ON JUNE/03.  BATTERY EXPIRY DATE I	S JULY/05.  THIS UNIT IS NOW DEEMED BEYOND ECONOMICAL REPAIR.PICTURES ARE ATTACHED.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2005041800142	20050418	00142	EA  	2005	4	18	CA041104009      	1	20041026	G	2430	MS3505923	SWITCH          			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					GENERATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLESHOOTING A RECURRENT DC GENERATION SNAG, THE GENERATOR BUSS-TIE SWITCH WAS FOUND TO BE FAILING INTERM	ITTENTLY. THE SWITCH WAS REPLACED AND THE SNAG CLEARED.  THIS SWITCH IS NOT A TRACKABLE ITEM AND THERE ARE NO EXISTING R	ECORDS OF IT EVER HAVING BEEN CHANGED. TTAF29,120.9TCAF50,033				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA
2005041800143	20050418	00143	NM  	2005	4	18	CA041104010      	1	20041025	G	6210	369D21102523	BLADE           			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) M/R BLADE FOUND WITH CHORDWISE CRACK AT STA 90.0 DURING ROUTINE 100 HOUR INSPECTION.PILOT THOUGHT HE FELT A SLIGHT	 CHANGE IN AIRCRAFT VIBRATION LEVELS DURING FLIGHT TO MAINTENANCE FACILITY.  THE CRACKEXTENDED 4 INCHES FROM THE TRAILIN	G EDGE OFTHE BLADE SKIN TOWARD THE CENTER OF THE BLADE.WE HAVE PICTURES OF THE BLADE THAT CAN BE EMAILED IF REQUIRED.YOU	 NEED TO CHANGE THE SIZE OF THE MODEL/PN BOX TO ACCOMODATE LARGER PART NUMBERS. THE RIN COUNT ON THIS BLADE WAS 515,664 	AT THE TIME OF REMOVAL.		1	G	7	1 	3U	3	U	NC	H3WE    	E1GL
2004122300040	20041223	00040	EA  	2004	12	23	CA041104012      	1	20041101	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											RIGHT SIDE COCKPIT WINDOW REPLACED ACCORDING AMM PROCEDURE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004122300041	20041223	00041	WP  	2004	12	23	CA041105001      	1	20041105	G	5260	591885323	HAND RAIL       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					AIRSTAIR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WITH VENTRAL AIR STAIR EXTENDED, BOTH LT AND RT HANDRAIL AFT VERTICAL TUBES ARE CORRODED-RUSTED AT THEIR LOWER END.  COR	ROSION CAN BE SEEN AS A RING OF RUST POWDER AROUND THE JUNCTION OF THE TUBE INTO THE FITTING ASSEMBLY SUPPORT (P/N 39366	673-501 OR -502).  RETAINING BOLT HAS TO BE REMOVE AND THE TUBE PULLED FROM THE FITTING ASSEMBLY SUPPORT FOR A PROPER EV	ALUATION OF THE TUBE CONDITION.  THESE ARE BELIEVED TO BE THE ORIGINAL TUBES.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2004122300042	20041223	00042	NE  	2004	12	23	CA041105002      	2	20041101	G	7314	378200	PUMP            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE FUEL	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA			39630								DURING CLIMB, THE NR 2 ENGINE FLAMED OUT.  THE AIRCRAFT RETURNED TO THE AIRPORT.  MAINTENANCE TROUBLESHOOTING FOUND THAT	 METERED FUEL WAS NOT BEING DELIVERED TO THE ENGINE, BUT FUEL WAS PRESENT UP TO THE FCU/FUEL PUMP ASSY.  THE FCU/FUEL PU	MP ASSY WAS REPLACED AND SEVERAL GROUND RUNS WERE CARRIED OUT.  THE AIRCRAFT WAS RETURNED TO SERVICE.  THE FUEL PUMP APP	EARS TO BE BINDING WHEN INSPECTED.  THE REMOVED FCU/FUEL PUMP ASSY WAS SENT TO AN APPROVED FACILITY FOR FURTHER INSPECTI	ON AND TESTING.		2	L	7	2 	4F	4	F		A16WE   	E2EA
2005021400218	20050214	00218	NM  	2005	2	14	CA041105003      	1	20041104	G	2612	894093	FIRE LOOP       			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 1 ENGINE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ENGINE NR 1 FIRE WARNING AT 8000 ASL ON APPROACH.  FIRE BOTTLES AND SQUIBS REPLACED IAW MM.  NR 1 LOWER FIRE LOOP 	REPLACED AND CONNECTOR D1098 IAW MM.  SYSTEM TESTED SERVICEABLE.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041800144	20050418	00144	CE  	2005	4	18	CA041105004      	1	20041104	G	5311	05120111	FRAME           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 200 HR INSPECTION FUSLAGE FRAME PN 0512011-1, STA 108.0 WAS FOUND TO HAVE 4 CRACKS APPROXINATLY 1/2 - 1 I	NCH IN LENGTH ORIGINATING FROM THE INBOARD FLANGE OF THE FRAME AT EACH OF THE 4 CORNERS.					1	H	7	1 	3O	3	O	NT	3A12    	E274
2005041800145	20050418	00145	GL  	2005	4	18	CA041105005      	2	20041105	G	7320		FUEL CONTROL    			LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  					NR 3 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) ON TEST FLIGHT A/C WAS WEST OF OF THE AIRFIELD IN THE PRACTICE AREA. NR 3 ENGINE WAS SHUTDOWN AND SECURED DUE TO L	ACK OF RESPONSE WITH THE POWER LEVER. THE A/C RETURNED TO BASE WITHOUT INCIDENT. FCU IS SUSPECTED.					2	L	7	4 	4T	4	T		4A22    	E282
2005041800146	20050418	00146	NE  	2005	4	18	CA041105006      	2	20041029	G	7320	164448620	FUEL CONTROL    			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ON P2 CHAMBER INSPECTION AND CLEANING OF FCU. WHEN BELLOWS WERE REMOVED WE FOUNDTHAT THE PIN THAT HOLDS THE METERI	NG VALVE IN PLACE WAS BROKEN OFF AND HALF OFTHE PIN WAS FOUND IN THE CHAMBER.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041800147	20050418	00147	CE  	2005	4	18	CA041107001      	1	20041026	G	5270	V31	SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					PAX DOOR	INTERMITTENT    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF THE CABIN DOOR WARNING LIGHT ILLUMINATED, WITH THE DOOR REMAININGIN THE CLOSED POSITION. THE AIRCRA	FT RETURNED TO BASE FOR LANDING WITHOUT INCID ENT. UPON LANDING AND TAXI TO THE RAMP THE CREW CONFIRMED THAT THE DOOR WA	S INDEED IN THE CLOSED AND LOCKED POSITION AS CONFIRMED BY THE OVERCENTER MECHANICAL PLUNGER AND LOCK, AND THE FOUR GREE	N VISUAL INDICATORS ON THE DOOR BAYONET LATCHES. MAINTENANCE INSPECTION DETERMINED THAT THE DOOR LATCHING MECHANISM WAS 	FUNCTIONING NORMAL AND THE FALSE INDICATION WAS CAUSED BY AN INTERMITTENT DOOR WARNING SWITCH.		1	L	7	2 	4T	4	T		A24CE   	E4EA
2004122200116	20041222	00116	EU  	2004	12	22	CA041108001      	1	20041029	G	3210	5321012123	PIN             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT MLG	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) PINS ON SPECIAL WASHER SHEARED ALLOWING BODY OF HYDRAULIC SWIVEL FITTING TO ROTATE ON GEAR RETRACTION/EXTENSION BR	EAKING HYDRAULIC LINE TO THE BRAKES P/N 5324412053. THIS APPEARS TO BE CAUSED BY TO THICK OF A SPACER WASHER P/N 532.10.	12.136 WHICH CAUSES THE ASSEMBLY TO APPLY TO MUCH FORCE TO THE SPECIAL WASHER AND ITS PINS. FOUR THICKNESS'S OF WASHERS 	ARE AVAILABLE IN THE IPC BUT NO PROCEDURE I S SPELLED OUT IN THE MM FOR THE TECHNICIAN TO HELP HIM/HER DETERMINE IF THE 	PROPER GAP IS THERE ON ASSEMBLY.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004122900155	20041229	00155	CE  	2004	12	29	CA041108003      	1	20041025	G	3230	07416011	SPRING          			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											LEFT HAND MAIN LANDING GEAR SPRING ASSEMBLY BROKE OF AT FUSELAGE WHILE TAXIING FOR FLIGHT.  THERE WAS NO VISUAL EVIDENCE	 OF A PREVIOUS CRACK. THE GEAR LEG WAS SENT TO TRANSPORT SAFETY BOARD TO BE ANALYZED.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
2004122900156	20041229	00156	NM  	2004	12	29	CA041108004      	1	20041030	G	2760	BACC13AP3D30	CONTROL CABLE   			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT WING SPOILER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING AN 'A' CHECK INSPECTION, FOUND THE CONTROL CABLE FOR NR 7 FLT SPOILER FRAYED, AS A RESULT OF CHAFING THROUGH A FA	IRLEAD.  CABLE WAS REPLACED, FAIRLEAD RE-POSITIONED, FUNCTION CHECKED.  AIRCRAFT RETURNED TO SERVICE.  NO OTHER PROBLEMS	 OR ACTIONS.				2	L	7	2 	4F	4	F		A16WE   	E2EA
2005020100081	20050201	00081	CE  	2005	2	1	CA041108005      	1	20041101	G	5532	07310041	SKIN            			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL STABILIZER REMOVED TO ACCESS FUSELAGE SIDE SKIN REPLACEMENT (COSMETIC)  WITH STABILIZER ON WORKBENCH, VIS	IBLE ACCESS TO INTERNAL STRUCTURE REVEALED CONSIDERABLE SURFACE CORROSION EVERY WHERE INTERNALLY.  EXTERNAL UNIT LOOKS F	INE.  RECOMMEND REMOVAL OF VERTICAL AND HORIZONTAL STABILIZERS ON A REGULAR BASIS. IE. 400 HRS/5 YEARS.				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2005041800148	20050418	00148	CE  	2005	4	18	CA041108006      	1	20040807	G	5753	C145350	MOUNT           	CESSNA      		CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FLAP ACTUATOR	LOOSE           	W				D				RETURN TO BLOCK         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						747					(CAN) MOUNTING STUD NUTS ON FLAP MOTOR BACKED OFF TO THE POINT WHERE THE DRIVE COUPLING DISENGAGED BETWEEN THE FLAP MOTO	R AND THE ACTUATOR.					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL
2005041800149	20050418	00149		2005	4	18	CA041108007      	4	20041105	G	2215	15600088	CABLE           			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	AUTOPILOT SYS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION THE AUTOPILOT ROLL SERVO BRIDLE CABLE WAS FOUND TO BE FRAYED WHERE IT RUNS OVER IT'S PULLEYS.						1	H	7	2 	3O	3	O		A6CE    	E9CE	5	C	P5EA
2005041800150	20050418	00150	EU  	2005	4	18	CA041108008      	1	20041101	G	5523	SD3076011XA	BRACKET         			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					TRIM TAB BALANCE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH ELEVATOR TRIM TAB MASS BALANCE BRACKETS WERE FOUND CRACKED DURING 9600 HOUR STRUCTURAL INSPECTION. THESE BRAC	KETS WERE RECENTLY REPLACED TO COMPLY WITH MAN DATORY S/B SD360-55-20. (REFERENCE AD 009-06-2003)					2	H	7	2 	4T	4	T		A41EU   	E4EA
2005041800151	20050418	00151	NM  	2005	4	18	CA041108009      	1	20041104	G	3230		ISOLATION VALVE 			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF, GEAR HANDLE INITIALLY WOULD NOT COME UP AND ASSOCIATED OVERHEAD ISOLATION VALVE ILLUMINATED. AFTER FLA	P RETRACTION TOCWS SOUNDED FOR TWO MINUTES, THEN STOPPED AND GEAR CAME UP NORMAL.AIR SAFETY SENSOR REPLACED AND TESTED S	ERV. GROUND SPOILER INTERLOCK VALVE CABLE ADJUSTMENT TESTED SERV.  GEAR SWINGS CARRIED OUT.  AIRCRAFT GEAR OPERATED NORM	ALLY.			2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041800152	20050418	00152	NM  	2005	4	18	CA041108010      	1	20041106	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) FUSELAGE CRACK FOUND ON OUTER SKIN AT STN 767 STR 18L, 0.875 INCHES LONG. CRACK REPAIRED IAW SRM 53-30-3 FIG 48 SH	EET 32 DETAIL X REV.90. TIMES  61643.42 CYCLES 57682.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2004122200120	20041222	00120	EU  	2004	12	22	CA041108011      	1	20041108	G	1420		WIRE HARNESS    			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					LIGHT	CHAFED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) FOUND DAMAGE TO 932 HOUSING ASSEMBLY AT 12 AC.  THE STOWAGE CLOSET IS LOOSE AT THE TOP.  FOUND LCD HARNESS INSIDE 	CLOSET CHAFED AND SHORTING OUT.  DISCONNECTED THE HARNESS AT 6208VC112 (WIRE DIAGRAM). TO FIX THE PROBLEM RED S HOUSING 	ASSY/ STOWAGE CLOSET REPLACEMENT BEFORE THE HARNESS CAN BE REPAIRED OR REPLACED.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE
2004122900175	20041229	00175	EA  	2004	12	29	CA041109001      	2	20041021	G	8520		CRANKCASE       								LYC   	O540  	O540E4C5    	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											POSSIBLE CRACK FOUND DURING 100 HR INSPECTION.  ENGINE REMOVED AND SENT TO AEROTER ENGINES IN HALIFAX.  ENGINE SHOP CONF	IRMED CRACK BETWEEN NR 2 AND NR 4 CYLINDER ON BOTTOM SIDE.  IT ALSO HAD EXCESSIVE FRETTING ON THE CENTER MAINS.										3	O			E295
2004122900176	20041229	00176	EU  	2004	12	29	CA041109002      	1	20041024	G	2140	1379219L401	DUCT            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	CABIN HEAT	CONTAMINATED    	W				C	H			ABORTED TAKEOFF         	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											AFTER T/O CREW ADJUSTED TEMP CONTROL TO WARM UP CABIN.  SHORTLY AFTER CABIN STARTS TO FILL WITH SMOKE.  TEMP WAS REDUCE	D, ATC NOTIFIED OF PROBLEM, QRH DRILL FOLLOWED.  SMOKE CLEARED, A/C LANDED BACK IN 4 MM WITHOUT INCIDENT.  MX INSPECTION	 REVEALED, INSULATION ON THE UNDERSIDE OF HEAT DUCT BENEATH FLOOR HAD ABSORBED HYD FLUID FROM A PREVIOUS HYD LEAK.  TEMP	 INCREASE WITHIN DUCTING C CAUSED OIL SOAKED INSULATION TO EMIT A HAZE OR SMOKE CONDITION.  HEAT DUCT WAS REPLACED AND F	UNCTION TEST SERVICEABLE.		2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL
2005021500001	20050215	00001	CE  	2005	2	15	CA041109003      	1	20041101	G	5610	MS250852BB5	GROUND WIRE     	PPG         		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	WINDSHIELD HEAT	BURNED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA						03042R6137					(CAN) DURING CRUISE FLT AT FL210, THE FLIGHT CREW DETECTED AND ODOR FOLLOWED BY SMOKE EMANATING FROM THE DASH AREA. THEY	 DONNED MASKS AND REQUESTED PRIORITY LANDING . THEY RAN THRU THEIR EMERGENCY PROCEDURES AND AFTER THE WINDSHIELD HEAT WA	S SELECTED OFF THE SMOKE DISSIPATED.  AN UNEVENTFUL LANDING WAS COMPLETED AND AIRCRAFT BROUGHT TO MAINTENANCE.  MAINTENA	NCE FOUND THAT THE GROUND WIRE HAD CONTACTED THE DASHBOARD EYEBROW AND THE HEAT HAD CAUSED IT TO SMOLDER.  THE WIRE WAS 	REPLACED AND ROUTED TO ENSURE NO CONTACT CAN BE MADE WITH ANYTHING.  A FLEETWIDE INSPECTION IS BEING CARRIED OUT AT THIS	 TIME AND WILL LEAVE SDR OPEN UNTIL TOTAL RESULTS.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005041800153	20050418	00153	CE  	2005	4	18	CA041109004      	1	20041003	G	2710	040010741	CONTROL CABLE   			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	AILERON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON CONTROL CABLE FOUND CORRODED AT COPILOT FOOT AREA. THIS PROBLEM HAS BEEN NOTICED ON OTHER CESSNA 150. SUSP	ECT DIRT FROM SHOES CAUSING CORROSION. TO SEE THE CABLE YOU NEED TO REMOVE COVER (YOKE) AND MOVE AILERON TO TRAVEL LIMIT	S.				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2005041800154	20050418	00154	EU  	2005	4	18	CA041109005      	1	20041109	G	6340		WARNING SYSTEM  			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					LOW ROTOR RPM	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) WHEN PILOT OR COPILOT TRANSMIT, THE LOW ROTOR RPM AUDIO WARNING & GONG ARE MUTED. THESE INPUTS SHOULD BE UNMUTED W	HEN TRANSMITTING.					1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005041800155	20050418	00155	SW  	2005	4	18	CA041109006      	1	20040915	G	6320	206031633105	DRAG PIN        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE DRAG LINK BEARING WAS FOUND SMOKING. THIS A NEW STYLE IN WHICH BEARING AND NOT WHOLE ASSEMBL	Y IS REPLACED. NEW BEARING INSTALLEDNOTE: THIS STYLE OF BEARING WAS INTRODUCED THROUGHT B206-00-173 TO ELIMINATE THE PRO	BLEM WITH THE STAKING COMING LOOSE. SUBJECT BEARING WAS NOT KEPT FOR WARRANTY SUBMISSION.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2004121000008	20041210	00008	SW  	2004	12	10	CA041109007      	1	20040907	G	2810	6895171	CHECK VALVE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON TROUBLESHOOTING FOR STARTING SNAG, FOUND THAT FUEL WASN'T BEING DELIVERED TO THE FUEL NOZZLE. REPLACED CHECK 	VALVE. THE REMOVED VALVE WAS FOUND TO HAVE A CRACKING PRESSURE OF APPROXIMATELY 15 PSI.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2004122300023	20041223	00023	SW  	2004	12	23	CA041109008      	1	20040927	G	2897		WIRE            	SIMMONDS    		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL QTY IND	ARCED           	W				O				OTHER                   				A			FLAME/FIRE                			CR	CRUISE         	1			CA						642C					(CAN) FUEL QUANTITY REPORTED AS FLUCTUATING.  DURING TROUBLESHOOTING PROCESS ONE OF THE WIRES ON THE RT TANK FORWARD FUE	L PROBE WAS FOUND ARCING.  PROBE REPLACED.					1	G	7	1 	4U	4	U		H4SW    	E22EA
2005020100088	20050201	00088	NM  	2005	2	1	CA041110001      	1	20041108	G	2781		PROXIMITY SENSOR			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LE SLAT	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) UPON SELECTION OF FLAPS 15 ON LANDING CHECKLIST THE L/E FLAP TRANSIT REMAINED ILLUMINATED AND THE NR 4 SLAT INDICA	TOR WAS SHOWING IN TRANSIT. REPLACED AND ADJUSTED NR 4 SLAT PROX SENSOR IAW MM 27-88-11.  NR 4 SLAT FOUND DENTED ON UPPE	R SURFACE, REPLACED NR 4 SLAT IAW MM 27-81-21.  RII CARRIED OUT.  UPON FURTHER INVESTIGATION IT WAS FOUND THAT DAMAGE FR	OM A PREVIOUS BIRD STRIKE WAS FOUND TO THE SLAT CURTAINS WHICH CAUSED THE DAMAGE TO THE PROX SENSOR. THIS DAMAGE WAS NOT	 VISIBLE WITHOUT REMOVING L/E PANELS.		2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041800156	20050418	00156	NE  	2005	4	18	CA041110002      	2	20040911	G	7230		COMPRESSOR WHEEL			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MO 2/3 FIRST STAGE WHEEL RUBBING ON THE PLASMA SPRAY IN LINER.. (PLASMA LIFTINGOFF IN TO THE BLADE PATH.)						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005041800157	20050418	00157	SW  	2005	4	18	CA041110003      	1	20040729	G	6210	206011016201133	BLADE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14121								(CAN) DURING DI, THE TIP BLOCK WAS FOUND CRACKED ADJACENT TO IMPACT MARK.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2005041800158	20050418	00158	CE  	2005	4	18	CA041110004      	1	20041029	G	5712	042650720	RIB             			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21695								(CAN) THE RIB WAS FOUND CRACKED AROUND ONE OF THE STRENGTHENING DIMPLES OF THE RIB, ABOUT 1.5 INCHES IN LENGTH. A NEW PA	RT WAS INSTALLED AS REQUIRED.					1	H	7	1 	3O	3	O		3A19    	E252
2005031400077	20050314	00077	CE  	2005	3	14	CA041110005      	1	20041029	G	5753	05232113	FLAP TRACK      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	RT WING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21695								(CAN) ON INSPECTION FLAP TRACK GROOVES WERE FOUND BADLEY WORN.  PARTS WERE REPLACED AS REQUIRED.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2005041900001	20050419	00001	CE  	2005	4	19	CA041110006      	1	20041029	G	5753	0523113	FLAP TRACK      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					LT WING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21695								(CAN) ON INSPECTION FLAP TRACK GROOVES FOUND BADLEY WORN,PARTS WERE REPLACED AS REQUIRED.						1	H	7	1 	3O	3	O		3A19    	E252
2004121000009	20041210	00009	CE  	2004	12	10	CA041110007      	1	20041029	G	5310	04118685	DOOR FRAME      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21695								(CAN) ON INSPECTION FOUND CRACKED AT UPPER FWD RADIUS ABOUT 1.0 INCH IN LENGTH.  PART WAS REPLACED AS REQUIRED.						1	H	7	1 	3O	3	O		3A19    	E252
2004122300024	20041223	00024	EU  	2004	12	23	CA041110008      	1	20040930	G	6720	350A27118120	PLATE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAILBOOM	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											DURING AN INSPECTION OF THE CABLE ASSEMBLY, THE BACKING PLATE FOR THE CABLE SUPPORT BEARING AT THE TAIL BOOM/AIRFRAME JU	NCTION WAS FOUND TO BE MISSING.  AIRCRAFT GROUNDED AND A PLATE INSTALLED.  THE MISSING PLATE RESULTED IN EXCESS PLAY IN 	THE TAILROTOR PEDAL CONTROL.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2004122300027	20041223	00027	NE  	2004	12	23	CA041110009      	2	20041108	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TROUBLESHOOTING A SLOW STARTING ENGINE, THE LT IGNITER PLUG WAS REMOVED FOR INSPECTION.  AN OPERATIONAL (SPA	RK) CHECK WAS CARRIED OUT WITH NO DEFECTS FOUND.  UPON A SECOND LOOK AT THE IGNITER, IT WAS NOTICED THE SEMI CONDUCTOR S	URROUNDING THE CENTRAL ELECTRODE WAS EXTENDED 1/16 OF AN INCH AND LOOSE. THE MAINTENANCE LOG SHOWS THE IGNITER WAS INSTA	LLED NEW ON SEPT 22 2003 AT AIRFRAME HOURS 11959.5A NEW IGNITER WAS INSTALLED AND A/C RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005021500006	20050215	00006	EU  	2005	2	15	CA041110010      	1	20040820	G	2497		CONNECTOR       			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					BATTERY	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						F2103					(CAN) WHEN INSTALLING A REPLACEMENT BATTERY, NOTICED THE TEMP SENSOR WIRING HARNESS DID NOT HAVE A JUMPER WIRE.  FURTHER	 INSPECTION REVEALED THAT THERE WAS NO SHUNT INSTALLED IN THE CONNECTOR.  A REVIEW OF THE CHR SHOWED THAT THE ENTRIES WE	RE MADE REGARDING THE SHUNT AD AND WIRING HARNESS MOD BUT WERE CROSSED OUT (ENTERED IN ERROR).  A WIRE JUMPER WAS INSTAL	LED ON THE HARNESS PRIOR TO BATTERY INSTALLATION.			1	G	7	1 	3U	3	U		H9EU    	E5NE
2005041900002	20050419	00002	EU  	2005	4	19	CA041110011      	1	20040722	G	6720	350A33105803	BELLCRANK       			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BELL CRANK WAS REMOVED TO DETERMINE THE SOURCE OF RADIAL PLAY. UPON REMOVAL OF THE BELLCRANK FROM THE GEARBOX 	TWO BUSHINGS FELL OUT OF THE BELLCRANK.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2005041900003	20050419	00003	CE  	2005	4	19	CA041110012      	1	20041025	G	3222	NAS464P5A42	BOLT            	CESSNA      		CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					NLG STRUT	SHEARED         	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) BOLT SHEARD ON LANDING CAUSING NOSE GEAR TO PIVOT FORWARD.NOTE - THIS BOLT WAS LAST CHANGED SEPT.9/94 AT 2875.1 T.	T. (AIRCRAFT PRESENT T.T. IS 6238.7 HRS) THIS AIRCRAFT HAS OPERATED ON SKIS (SUSPECT THAT BOLT WAS OVERSTRESSED IN THIS 	CONFIGURATION) THIS BOLT WAS CRACKED PRIOR TO FAILURE AS HALF OF FRACTURE IS BLACK & TOTAL FAILURE IS WHITE. SOME DAMAGE	 TO AIRFRAME WAS ENCOUNTERED. BOLT WILL BE DELIVERED TOT.C. IN WHITEHORSE. IT SHOULD BE NOTED THAT INSPECTION OF THIS BO	LT IS NOT REFE RENCE IN INSPECTION SCHEDULE.		1	H	7	1 	3O	3	O		A4CE    	E5CE
2005041900004	20050419	00004	NE  	2005	4	19	CA041110013      	2	20041109	G	7321	8063005B	FUEL CONTROL    			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PS0157			(CAN) PILOTS REPORTED THAT WHEN LT POWER LEVER WAS ADVANCED, THE LT FUEL CONDITION LEVER WOULD MOVE AFT FROM HIGH IDLE T	OWARD LOW IDLE. THIS COULD BE REMEDIED BY SETTING THE FRICTION TO A HIGHER VALUE THAN NORMAL. THE LT ENGINE WAS INSPECTE	D BY MAINTENANCE AND EVEN WITH BOTH COCKPIT LEVERS DISCONNECTED FROM THE UNIT, IF YOU MANUALLY MOVED THE INPUT ARM OF TH	E FCU, THE FUEL CUTOFF PORTION WOULD ALSO BE AFFECTED. THE BINDING WAS INTERNAL AND INPUTS TOHIGHER POWER LEVER SETTINGS	 WOULD ALSO MOVE FUEL CUTOFF TOWARDS CUTOFF POSTION. THE FCU WAS REPLACED AND AIRCRAFT GROUND TESTED SERVICABLE.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005041900005	20050419	00005		2005	4	19	CA041110014      	4	20041101	G	3445	F23B22	WIRE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					COMPUTER	MISUSED         	W				O				OTHER                   				F	H		FLT CONT AFFECTED         	ELECT. POWER LOSS-50 PC   		LD	LANDING        	1			CA											(CAN) DURING A FLT, PILOT REPORTED AILERON AUGMENTATION MODE SYS INOPERATIVE. A LEARJET GPWS/WINDSHEAR SYS INSTALL COMPL	ETED ON 09/30/94 REMOVED & A NEW TAWS 8000 SYS UPGRADE INSTALLED ON 05/29/04.  FURTHER INVESTIGATION REVEALED THAT DURIN	G GPWS/WINDSHIELD UPGRADE TO TAWS 8000, GPWS AUX BOX (E374) HAD BEEN REMOVED AS REQUIRED BY DRAWING WHILE REMAINING WIRE	S CAPPED & STOWED & DID NOT TAKE INTO CONSIDERATION USEFULNESS OF WIRES F23B22, TW89A22, F25B22, TW91A22 TO SPOILERON CO	MPUTER.  A REQUEST FOR ENGINEERING SUPPORT WAS FORWARDED & A REVISED DRAWING 1003421 REV B PROVIDED TO CORRECT ORIGINAL 	DRAWING AND WIRE OVERSIGHT INCLUDING DATA APPROVAL DOCUMENTED ON  10/22/04.	2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
2004121000012	20041210	00012	CE  	2004	12	10	CA041110015      	1	20041101	G	5510	07122071	REINFORCEMENT   			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) HORIZONTAL STABILIZER WAS REMOVED TO ACCESS RT FUSELAGE SIDE SKIN REPLACEMENT (COSMETIC) WITH STABILIZER REMOVED V	ISIBLE ACCESS TO AFT FUSELAGE STRUCTURE REVEALED A CRACK AT THE LT AFT STABILIZER ATTACH LONGERON PN 0712207-1 - REF. CE	SSNA 180-C I.P.C. FIG 35 ITEM 35.  NOTE AIRCRAFT HAS BEEN OPERATED ON SKIS AND HANDLING OF THE HORIZONTAL STAB MAY BE A 	CONTRIBUTING FACTOR.  THOUGH NOT CALLED FOR IN THE CESSNA INSPECTION CHECK SHTS, IT WOULD BE PRUDENT TO REMOVE BOTH VERT	ICAL AND HORIZONTAL STABILIZERS FOR BETTER VISUAL/INTERNAL INSPECTION ON A REGULAR BASIS. IE. 400 HRS/5 YEARS.		1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
2004122300034	20041223	00034	EU  	2004	12	23	CA041110016      	1	20041028	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CYCLIC STICK	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											WHEN HYDRAULIC POWER IS RE-ESTABLISHED AFTER DOING HYDRAULIC ACCUMULATOR PREFLIGHT CHECK, THE CYCLIC STICK WOULD GO HARD	 LEFT, BUT WAS ABLE TO BE OVERCOME AND WOULD ONLY LAST BRIEFLY.  LEFT HAND SERVO WAS REPLACED FOR TROUBLESHOOTING AND PR	OBLEM WAS RECTIFIED.  ALL FUNCTIONS NORMAL.				1	G	7	1 	3U	3	U		H9EU    	E19EU
2004122300035	20041223	00035	EU  	2004	12	23	CA041110017      	1	20040904	G	2822	P94B12203C	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUEL BOOST	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											BOOST PUMP FOUND LEAKING DURING DI.  UPON FURTHER INVESTIGATION FOUND PUMP LEAKING INTERNALLY.  PUMP REPLACED.						1	G	7	1 	3U	3	U		H9EU    	E19EU
2004122300036	20041223	00036	GL  	2004	12	23	CA041110018      	3	20041110	G	6111	83867	CLAMP           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											PROPELLER RECEIVED FOR INSPECTION UNDER AD 88-24-15.  DURING ROUTINE VISUAL INSPECTION OF THE BLADE CLAMP ASSEMBLES, A C	RACKED WAS DETECTED IN ONE OF THE OUTBOARD CLAMP BOLT HOLES ON S/N EE1910.  CLAMP HAS BEEN REMOVED FROM SERVICE AND REPL	ACED WITH AN OVERHAULED ASSY.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
2005020100089	20050201	00089	CE  	2005	2	1	CA041110019      	1	20041108	G	5751	57150021	SUPPORT BRACKET 			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	MCAULY	3G34C6	3GFR34C601  	GL  	BELLCRANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON BELLCRANK SUPPORT BRACKET WAS DISCOVERED TO BE CRACKED. PART WAS REPLACED WITH A NEW BRACKET AND THE AIRCR	AFT RETURNED TO SERVICE.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P54GL
2005041900006	20050419	00006	CE  	2005	4	19	CA041112001      	1	20041108	G	3230		POWERPACK       			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A27      	52043	EA  					RT MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A/C WAS SITTING ON RAMP PARKED, RT MAIN LANDING GEAR COLLAPSED. SUSPECT HYDRAULIC POWER PACK AT FAULT.						1	L	7	2 	3T	4	T		A14CE   	E4EA
2005041900007	20050419	00007	EU  	2005	4	19	CA041112002      	1	20041109	G	2612	D237060	FIRE LOOP       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					NR 2 ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) FIRE BELL AND LIGHT ON NR 2 ENGINE CAME ON IN CRUISE. ENGINE NR 2 SHUTDOWN. LANDED WITHOUT INCIDENT.  FOUND FIRE L	OOP P/N D2370-60 DAMAGED, REPLACED LOOP WITH NEW PART TESTED SERVICEABLEGROUND RUN. NO FAULTS FOUND RETURNED AIRCRAFT TO	 SERVICE				2	L	7	2 	3T	4	T		A24EU   	A196
2005041900008	20050419	00008	NM  	2005	4	19	CA041112003      	1	20040816	G	3234	574205A	SELECTOR        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) UNABLE TO EXTEND GEAR DURING APPROACH. THE THREE INDICATIONS LIGHTS REMAINS IN RED AND THE LG SELECTOR HANDLE WAS 	AMBER. EMERGENCY LANDING GEAR EXTENSION CARRIED OUT.LANDING GEAR SELECTOR VALVE, STRIPREPORT FOUND CORE ASSY. HAD MUSHRO	OMED & WAS OUT OF ROUND AT THE TOP. UNIT OVERHAULED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041900009	20050419	00009	CE  	2005	4	19	CA041112004      	1	20041112	G	2913	1153800025	PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	HYD SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA						2652					(CAN) ON TAKE OFF, GEAR WOULD NOT RETRACT. NOSE GEAR GREE LIGHT WENT OUT, AND RED INTRANSIT LIGHT REMAINED ON. GEAR WOUL	D NOT RETRACT OR EXTEND.PRIOR TO LANDING THE BACKUP EXTENSION SYSTEM WAS USED, AND ALLGEAR INDICATIONS WERE THAT THE GEA	R WAS DOWN AND LOCKED. SUBSEQUENT INVESTIGATION REVEALED THAT THE HYDRAULIC PUMP MOTOR WAS UNSERVICEABLE.THE PUMP MOTOR 	IS A TIME TRACKED ITEM WITH A 1200 HOUR TBO.			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC
2004121000013	20041210	00013	WP  	2004	12	10	CA041112005      	1	20041110	G	6310	369D25351SN58	SPRAG CLUTCH    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CLUTCH REMOVED FOR GREASE BEARING REPLACEMENT.  UPON INSPECTION 2 SPRAGS FOUND BROKEN.						1	G	7	1 	3U	3	U		H3WE    	E4CE
2004122900168	20041229	00168	NE  	2004	12	29	CA041115001      	2	20041111	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			12145					807618			DURING CRUISE, THE RT ENG OIL PRESSURE SLOWLY DROPPED BELOW 25 PSI AND OIL TEMPERATURE SLOWLY DROPPED FROM 106 TO 81 DEC	 C.  PERFORMED PRECAUTIONARY SHUTDOWN OF RT ENG.  PERFORMED DRY MOTOR AND SERVICED ENGINE OIL.  PERFORMED OIL CONSUMPTIO	N RUN: 2.5 QTS USED IN 1 HR OIL CONSUMPTION TOO HIGH.  ENGINE REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004122900169	20041229	00169	NE  	2004	12	29	CA041115002      	3	20041112	G	6111	SFA13MIROADE	BLADE           			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29896						8910089347		DETAILS EXTRACTED FROM MAJOR DEFECT REPORT: DAMAGE IN THE FORM OF SLASH TYPE CUTS TO THE DE-ICE BOOT WAS FOUND ON THE RI	GHT PROPELLER, NR 3 BLADE, WHICH AS A RESULT REQUIRED THE PROPELLER BLADE TO BE REPLACED.  DURING REPLACEMENT OF THE NR 	3 BLADE SERIAL NUMBER 851372 ENGINEERS DISCOVERED THAT THE BLADE COLLARS WERE MISSING FROM THE NR 4 BLADE ASSY.  SEPARAT	ION OF THE BLADE COLLARS IS CURRENTLY UNDER INVESTIGATION BY THE TSB DUE TO A PREVIOUS COLLAR SEPARATION AND IMPACT DAMA	GE ON ANOTHER AIRCRAFT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005031100011	20050311	00011	NE  	2005	3	11	CA041115003      	2	20041101	G	7321	32447594	FCU             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ENGINE START CARRIED OUT NORMAL, AIRCRAFT TAXIED FOR TAKEOFF.  POWER SETTINGS WERE SET AND RT ENGINE DID NOT ACCEL	ERATE.  MAX TURBINE SPEED WAS 56 PERCENT (37 PERCENT FAN) CREW ABORTED TAKE OFF AND RETURNED TO BASE.  MAINTENANCE PERFO	RMED THE TROUBLESHOOTING PROCEDURES INDICATED IN PWA MM AND DETERMINED FAULT WAS FUEL CONTROL UNIT.  FCU 3244759-4  (S/N	 A58173N) REPLACED AND AIRCRAFT ENGINE RUNS AND RIGGING CARRIED OUT SATISFACTORY.  AIRCRAFT RELEASED BACK TO SERVICE NOV	. 05.		1	L	7	2 	4F	4	F		A22CE   	E1NE
2005020700003	20050207	00003	CE  	2005	2	7	CA041115004      	1	20041111	G	2434		GENERATOR       			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELECTRICAL	INTERMITTENT    	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THE PILOT OBSERVED THAT ONLY ONE GENERATOR WAS ACCEPTING LOAD.  DECIDED TO RETURN TO DEPARTURE AERODR	OME WITHOUT CARRYING OUT ANY CONFIRMATION CHECKS.  A SUBSEQUENT MAINTENANCE INSPECTION DETERMINED THAT AT LIGHT ELECTRIC	AL LOADS BOTH GENERATORS DO NOT ALWAYS STAY ON LINE. BOTH GENERATORS WERE CONFIRMED TO BE WORKING. BOTH GENERATOR INDICA	TING SYSTEMS WERE CONFIRMED TO BE FUNCTIONAL.			1	L	7	2 	3T	3	T		A14CE   	E4EA	6	C	P15EA
2005041900010	20050419	00010		2005	4	19	CA041115005      	4	20041111	G	3197		WIRE HARNESS    			CNDAIR	CL601 	CL6013A     	8070802	EA  										INSTRUMENT PANEL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT'S EFIS EADI WIRE BUNDLE CHAFING 12 INCHES FROM CONNECTOR 1P3FH. WIRE BUNDLE CONSISTS OF SEVERAL SHIELDED TWI	STED PAIR. SOME WIRE FOUND TO HAVE ABRADED INTO CENTER CONDUCTOR. WIRES FH215D24, FH216D24, 1FH108A24, 1FH109A24, FH230D	24, FH231D24, 1FH116A24, FH117A24, 1FH275A24, AND 1FH276A24 REPAIRED BY SPLICING IAW WM. THERE WERE NO PREVIOUS FAULT IN	DICATION, BUT WIRING COMPROMISED TO THE EXTENT THAT FAILURE WAS FORTHCOMING. IT WAS DETERMINED THAT WIRING WAS RUBBING O	N EHSI CONNECTOR WHICH IS INSTALLED DIRECTLY BELOW EADI. THERE WAS NO WIRE PROCTION SLEEVE INSTALLED AT THE DAMAGED AREA	. CO-PILOTS EADI AND EHSI WIRING INSPECTED AND FOUND ONLY MINOR CHAFING, WITH THE POTENTIAL TO DEGRADE OVER TIME.	2	L	7	2 	4F			RT	A21EA
2005041900011	20050419	00011	EU  	2005	4	19	CA041115006      	1	20041111	G	2913	704A34310006	HOUSING         			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					HYD PUMP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						80645856					(CAN) DURING A ROUTINE 100 HRS INSPECTION, IT WAS NOTICED THAT THE HYDRAULIC FILTER WAS CONTAMINATED WITH NON-FERROUS ME	TAL SHAVINGS. THE PUMP HOUSING IS MADE OF ALUMINIUM THEREFORE WE SUSPECT THE GEAR ROTORS STARTED TO WEAR THROUGH THE SOF	TER HOUSING.THE PUMP WAS REPLACED WITH A NEW ONE AND THE SYSTEM FLUSHED. THE A/C WAS RETURNED TO SERVICE.				1	G	7	1 	3U	3	U		H9EU    	E5NE
2004121000014	20041210	00014	SO  	2004	12	10	CA041115007      	1	20041111	G	3220	4027300	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION TWO CRACKS WERE FOUND IN THE UPPER CENTER AREA OF THE TRUNNION.  IT APPEARS THAT THE CRACKS ORIG	INATED IN A REPAIRED AREA THAT WAS WELDED.  THE CRACKS WERE DETECTED VISUALLY.					1	L	7	2 	3O	3	O		A20SO   	E14EA
2004122300001	20041223	00001	EA  	2004	12	23	CA041115008      	2	20041111	G	8530	LW16740	EXHAUST VALVE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHEN THE EXHAUST PIPES WERE REMOVED TO INSPECT THE EXHAUST VALVES, IT WAS FOUND THAT ALL SIX VALVES ON THE ENGINE HAD ER	OSION WEAR ON THE STEMS AND THE BACK SIDE OF THE VALVE FACE. THIS IS THE SECOND ENGINE THAT THIS PROBLEM HAS BEEN FOUND 	ON IN OUR FLEET.				1	L	7	2 	3O	3	O		A20SO   	E14EA
2004122300002	20041223	00002	EU  	2004	12	23	CA041116001      	1	20041105	G	2997	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYDRAULIC SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											ON TAKEOFF, PILOT SELECTED MLG UP, A HYD CAUTION & WARNING SYS LAMP, MASTER CAUTION & AURAL GONG ACTIVATED. MLG SELECTED	 DOWN NO CHANGE OBSERVED & MLG SELECTED UP NO CHANGE OBSERVED. HYD C/B PULLED.   INDICATION OF A RED NLG LIGHT & GREEN M	LG LIGHTS. PILOT FLEW ACFT BACK TO MAIN BASE,  WITH MLG DOWN. ON APPROACH, MLG SELECTED DOWN & EMERGENCY GEAR HANDLE WAS	 USED TO APPLY DOWN PRESSURE & TO CONFIRM THAT THERE WAS HYD PRESS. ALL 3 GREEN MLG LIGHTS ILLUMINATED. ACFT DID A LOW F	LY OVER TO CONFIRM DOWN. LANDING UNEVENTFULL. HYD POWER RELAY FOUND FAILED. HYD POWER RELAY REPLACED. MLG RETRACTION & E	XTENTION TEST PERFORMED, NO DEFECTS. ACFT RETURNED TO SERVICE.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004122300003	20041223	00003	SW  	2004	12	23	CA041116002      	1	20041108	G	2910	2781006143	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											HYDRAULIC FLUID WAS OBSERVED LEAKING FROM BELLY OF AIRCRAFT.  FURTHER INSPECTION REVEALED A CRACK IN THE 90 DEGREE BEND 	SECTION OF THE TUBE.  THE LINE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. NOTE:  THIS LINE IS NOT INCLUDED IN THE LI	ST IF LINES REQUIRING A SPECIAL INSPECTION IN ACCORDANCE WITH SB 227-29-005, YET THE LINE DOES PASS THE CRITERIA INCLUDE	D IN THE SB.			2	L	7	2 	4T			RT	A8SW    		6	C	3PNE
2005021400196	20050214	00196	NE  	2005	2	14	CA041116003      	2	20041116	G	8520	261280	CRANKSHAFT      			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								JP201660			(CAN) CRANKSHAFT FAILED AT THE MALE SPLINE NEAR THE NECKED DOWN AREA NEXT TO THE BUTT FACE IN THE FRONT CRANKSHAFT (P/N 	261279). CRANKSHAFT IS BEING HELD FOR POSSIBLE FURTHER INVESTIGATION.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
2005031400071	20050314	00071	EA  	2005	3	14	CA041116004      	1	20040924	G	5510	S203307	HINGE BRACKET   			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	AEIO540L1B5 	41532	NE  	HARTZL	HCC3Y	HCC3YR      	GL  	STABILIZER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPLETION OF SGB 55-02R1 STABILIZER ATTACHMENT HINGE BRACKET BOLTS FOUND LOOSE (TURN BY FINGERS).						1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA
2005031400072	20050314	00072	EU  	2005	3	14	CA041116005      	1	20041104	G	5753	25CF263321A	SHAFT           	BAC         		BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					FLAP VANE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DHB511					(CAN) UPON PERIODIC INSPECTION IT WAS NOTED THAT THERE WAS APPARENT CONTACT BETWEEN THE IB FLAP VANES ON BOTH LT AND RT 	ASSEMBLIES ONTO THE TORQUE SHAFT AND BEVEL HOUSING ASSY. THIS UNUSUAL CONTACT WAS DEDUCED TO OCCUR DURING FLIGHT LOADS A	S THE CLEARANCE BETWEEN THESE ASSEMBLIES AT ITS CLOSEST LOCATION (ABOUT 15 DEGREES OF FLAP DEFLECTION) HAS APPROXIMATELY	 0.600' CLEARANCE. EVEN WITH ANY ABNORMAL PLAY CAUSED BY WORN BUSHINGS ON THE ATTACHING HARDWARE OF THE FLAP MECHANISM C	OULD NOT PRODUCE THIS KIND OF CONTACT. INVESTIGATION IS ONGOING.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
2005031400073	20050314	00073	EA  	2005	3	14	CA041117001      	1	20041116	G	5330		SKIN            			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540L1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BELLY SKIN CRACKING AT VARIOUS (MULTIPLE POINTS) RIVETS LOOSENING ON INSPECTION COVER SKIN LAP RIVETS LOOSENING. S	USPECTED FROM TURBULENCE CREATED BY PROP INSTALLATION. REPAIRED BY PATCH AND REPLACEMENT OF RIVETS.					1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA
2005031400079	20050314	00079	NM  	2005	3	14	CA041117002      	1	20041105	G	7933	FRF6E2821P	CONNECTOR       			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					NR 3 ENGINE	SHORTED         	W				E	J			ENGINE SHUTDOWN         	DUMP FUEL               			M			OVER TEMP                 			CL	CLIMB          	1			CA											(CAN) AT TOP OF CLIMB, THE SECOND OFFICER NOTED AND INFORMED THE CAPTAIN THAT THE NR 3 ENGINE OIL TEMP WAS WELL ABOVE RE	DLINE. CREW CARRIED OUT HIGH ENGINE OIL TEMP SUPPORT CHECKLIST WHICH RESULTS IN SHUTTING DOWN THE ENGINE.  CREW DUMPED A	PPROX. 13,000 LBS OF FUEL AND RETURNED TO DEPARTURE. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. TROUBLESHOOTING CARRIED O	UT BY MAINTENANCE FOUND THE FIREWALL BULKHEAD CONNECTOR SHORTING OUT. AIRCRAFT IS AOG UNTIL REPAIRS AND VERIFICATION ENG	INE RUNS CARRIED OUT.		2	L	7	3 	4F	4	F		A3WE    	E2EA
2005031100102	20050311	00102	NE  	2005	3	11	CA041117003      	2	20041015	G	7200		ENGINE          								PWA   	PT6   	PT6A25      	52043	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE (10,000 FT) THE PILOT REPORTED A LOUD NOISE FOLLOWED BY ENGINE FLAMEOUT.  AN ATTEMPTED RELIGHT WAS U	NSUCCESSFUL AND AN EMERGENCY LANDING WAS PERFORMED.  THE ENGINE IS UNDER INVESTIGATION.   MFG WILL MONITOR THE PROGRESS 	AND FINDINGS OF THE INVESTIGATION AND WILL AMEND THIS REPORT TO REFLECT ROOT CAUSE, ONCE ESTABLISHED.									3	T			E4EA
2004122300010	20041223	00010	NE  	2004	12	23	CA041117004      	2	20041115	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						FIRE            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A	J		FLAME/FIRE                	WARNING INDICATION        		CL	CLIMB          	1			CA								DB0009			(CAN) SHORTLY AFTER TAKEOFF, THE CREW WERE ADVISED OF SMOKE AND FLAMES EMANATING FROM THE ENGINE.  THE ENGINE WAS SECURE	D AND AN UNSCHEDULED LANDING WAS PERFORMED AT POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND WILL REVISE THIS 	REPORT TO REFLECT ROOT CAUSE, ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2004122300011	20041223	00011	NE  	2004	12	23	CA041117005      	2	20041116	G	7200		ENGINE          			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RIGHT	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											DURING DAILY CHECK, OIL WAS FOUND IN TAILPIPE AND LAST TWO STAGES OF TURBINE SECTION COATED WITH OIL.  RT ENGINE SER NR 	667210.  RT ENGINE REPLACED.  ENGINE SER NR ON 667217. TIMES  61700.25 CYCLES 57721.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005020100094	20050201	00094	EU  	2005	2	1	CA041117006      	1	20041116	G	2910	AC67244	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					CHECK VALVE	STIFF           	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE PILOT WAS DOING PRE FLIGHT HYDRAULIC TEST IAW FLIGHT MANUAL REQUIREMENTS IAW AWD CF-2003-15R3 AND NOTICED A ST	IFFNESS IN THE FLIGHT CONTROLS. THE AIRCRAFT WAS SHUT DOWN. AN ENGINEER WAS NOTIFIED AND STARTED TO TROUBLESHOOT THE PRO	BLEM. THIS SERVO WAS REMOVED AND THE DEFECT WAS RESOLVED.  THE AIRCRAFT WAS RETURNED TO SERVICE. THIS IS THE INITIAL REP	ORT SINCE THE AIRCRAFT IS OUT IN THE FIELD AND REPORTING IS DIFFICULT.  THE ENGINEER SUSPECTS THE CHECK VALVE IN THE ACC	UMULATOR BLOCK WAS THE PROBLEM. THE AFFECTED SERVO WILL BE IN CITY LATER.		1	G	7	1 	3U	3	U		H9EU    	E19EU
2005020100189	20050201	00189	EA  	2005	2	1	CA041118001      	2	20041026	G	7414	1068291018	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	LOOSE           	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) A RT BREAKER POINT HOLD DOWN SCREW CAME OUT AND CAUSED THE ENGINE TO RUN ROUGH, INTERMITTENTLY.  THE MAG WAS REPLA	CED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005031400064	20050314	00064	NM  	2005	3	14	CA041118003      	1	20040809	G	5753	MS271113AN3166R	WASHER          			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FLAP TRACK	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) RT IB AFT MID FLAP (TWO) OB TRACK CARRIAGE ROLLER BOLT TAB WASHERS AND NUTS MISSING.  CORRECT HARDWARE INSTALLED, 	INDEPENDENT CHECK CARRIED OUT.  CONTRACTED AMO ADVISED.					2	L	7	3 	4F	4	F		A3WE    	E2EA
2005012100173	20050121	00173	SW  	2005	1	21	CA041118004      	1	20041118	G	5514	3066112	FAIRING         			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	HORIZONTAL STAB	MISLOCATED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE HORIZONTAL STAB FAIRING SCREW HOLES FOUND TO BE DRILLED THROUGH THE RIVETS ATTCHING T	HE SKIN TO THE CLOSING RIBS OF BOTH HORIZONTALSTABS. HOLES WERE LOCATED ON THE LOWER SURFACES ONLY. 7 OF 19 RIVETS WERE 	DRILL ED ON THE PORT STAB AND 5 OF 19 RIVETS WERE DRILLED ON THE STBD STAB. THE HOLES WERE DRILLED AT TIME OF AIRCRAFT M	ANUFACTURE. AIR TRACTOR HAS BEEN NOTIIFIED BY MAINTENANCE PLANNING.			1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL
2004122300019	20041223	00019	CE  	2004	12	23	CA041119001      	1	20041112	G	5711	08113507	SPAR            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12751								WHILE DOING A 100HR INSPECTION ON THE AIRCRAFT, AME'S NOTICED BELLY SKIN ON LOWER RT SIDE WRINKLED.  FURTHER INSPECTION 	REVEALED THAT THE WEB SKIN ON THE REAR OF THE FUSELAGE FRONT SPAR SKIN WAS CRACKED.  THE PROTECTIVE TOP CAP OF CARPET WA	S REMOVED AND IT WAS DISCOVERED THAT THE UPPER SPAR CARRY THRU WAS BROKEN.  AIRCRAFT WAS TAKEN APART AND THE FUSELAGE FR	ONT SPAR ASSEMBLY WAS REMOVED AND WILL BE REPLACED.  INSPECTION OF THE TECHNICAL RECORDS SHOWED THAT THE AIRCRAFT HAD BE	EN DAMAGED AFTER A NOSE GEAR COLLAPSE AND REPAIRED IN 1979.  THE SKIN UNDER THE DOOR HAD BEEN REPLACED RIGHT BESIDE THE 	FUSELAGE FRONT SPAR ASSEMBLY.	1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
2004122300020	20041223	00020	SW  	2004	12	23	CA041119002      	1	20041031	G	7810	LW16620	SEGMENT         			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  					LT ENG EXHAUST	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L543361A			DURING THE INSPECTION OF THE LT ENGINE AFTER IN-FLIGHT STOPPAGE, A HOLE WAS FOUND N AN EXHAUST SEGMENT.  DUE TO RESTRICT	ED SPACE A HEAT SHROUD THAT CONCEALED THE HOLE COULD NOT BE REMOVED WITHOUT REMOVING THE ENTIRE EXHAUST SYSTEM.  THE HOT	 GASES ESCAPING FROM GROUNDING THE MAG IMMEDIATELY SHUT THE ENGINE DOWN.  THE COMPANY INSPECTION PROGRAM HAS BEEN AMENDE	D AND NOW REQUIRES THE EXHAUST SYSTEM TO BE REMOVED AND INSPECTED.  THIS REQUIRES THE IMMEDIATE INSPECTION AND FOLLOW-UP	 REMOVAL, INSPECTION EVERY 200 HRS AND TRACKED ON COMPANY INSPECTION SHEETS.		1	L	7	2 	3O	3	O		A12SW   	E14EA
2005020100096	20050201	00096		2005	2	1	CA041119003      	4	20041119	G	3460	101741111	COMPUTER        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	FMS CONTROLLER	FAULTY          	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			CA											(CAN) CREW REPORTED THAT THERE WAS BURNING SMELL AND FOLLOWED SHORTLY BY WISPS OF SMOKE COMING FROM AREA TO THE CAPTAINS	 SIDE OF CENTER CONSOLE, JUST UNDER HIS INSTRUMENT PANEL. CREW WAS UNABLE TO IDENTIFY SOURCE OF SMOKE, AND CARRIED OUT P	ROCEDURES IAW QRH UNIDENTIFIED SMOKE, AND RETURNED TO BASE. CREW CONFIRMED SMOKE STOPPED FOLLOWING QRH PROCEDURES.  ENGI	NEERING FOUND CIRCUIT BREAKER RNAV 1 ON AVIONICS CB PANEL POPPED LOCATION G4. FMS CONTROLLER/COMPUTER WAS REMOVED,  INSP	ECTED WITH A STRONG SMELL OF BURNING EMANATING FROM UNIT. WIRING IN GENERAL AREA WAS INSPECTED FOR DAMAGE, AND POWER SUP	PLIES AND GROUND VALUES WERE CHECKED FOR PROBLEMS, NONE FOUND. FAULTY FMS UNIT HAS BEEN REMOVED FOR INVESTIGATION.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020400003	20050204	00003	EU  	2005	2	4	CA041119004      	1	20041118	G	3222	5322012038	STRUT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	DIRTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLT CREW REPORTED THE NLG NOISY WHEN RETRACTED & SCRATCHES WERE SEEN IN THE NOSE WHEEL YOKE. ACFT PLACED ON JACKS 	& RETRACTION TEST CARRIED OUT. NO DISREPENCIES NOTED. APPEARED NLG OLEO HAD NOT EXTENDED COMPLETELY AFTER TAKEOFF. PRIOR	 TO RETRACTING MLG, HAD INTERFEERED WITH THE NOSE GEAR DOOR RETRACT MECANISM. STRUT DEFLATED & FOUND TO BE VERY STIFF & 	COULD NOT BE MOVED UP & DOWN WITH NORMAL HAND PRESSURE. AFTER DISASSEMBLY DIRT FOUND ACCUMULATED UNDER LOWER MICARTA GUI	DE BUSHING WITHIN LOWER OLEO RETAINING NUT. ALL PARTS CLEANED & UNIT REASSEMBLED PER MM. UNIT SERVICED & FOUND TO BE FRE	E TO MOVE WITH HAND PRESSURE. UNIT PRESSUREIZED & SERVICED PER MM.  BINDING OF BUSHING INCREASED WITH COLDER TEMPS.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005020400004	20050204	00004	NE  	2005	2	4	CA041119005      	1	20041118	G	6320	S613723054001	BEVEL GEAR      	SKRSKY      		SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					M/R GEARBOX	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						A14K7791120					(CAN) DURING CLIMB OUT THE MAIN GEARBOX CHIP LIGHT ILLUMINATED. AIRCRAFT RETURNED TO SEVICE LANDING.ON INSPECTION, METAL	 PARTICLES WERE DISCOVERED ON THE CHIP PLUG AND IN THE COARSE SCREEN. THE MGB WAS REMOVED FROM SERVICE. AT DISASSEMBLY O	NE TOOTH WAS FOUND MISSING FROM MAIN BEVEL GEAR. OIL/WATER CONTAMINATION WAS ALSO PRESENT.				2	G	7	2 	4U	4	U		1H15    	1E3
2005031400063	20050314	00063	EU  	2005	3	14	CA041119006      	1	20041116	G	7921	RK25198A	OIL COOLER      			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	LT ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE, THE LT OIL PRESSURE WARNING LIGHT ILLUMINATED AND OIL PRESSURE WAS SEEN TO DROP.  LT ENGINE WAS SHUT DOWN	AND A/C LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED LT OIL COOLER WAS LEAKING AND ENGINE OIL CONTENTS WERE LOW.  OI	L COOLER WAS REPLACED, FILTER AND ENGINE CHECKS WERE CARRIED OUT, A/C RELEASED TO SERVICE.  DURING PREVIOUS DAY AC HAD B	EEN EXPOSED TO BLIZZARD CONDITIONS WHILE ON GROUND.  IT IS BELIEVED THAT SNOW ENTERED OIL COOLER BEFORE ENGINE COVERS CO	ULD BE INSTALLED. THIS SNOW MELTED, THEN FROZE INSIDE COOLER MATRIX, CAUSING SOME OF MATRIX TUBES TO CRACK. NEXT DAY, WI	TH ENGINE RUNNING, THE ICE MELTED EXPOSING THE MATIX CRACKS, ALLOWING OIL LOSS AND, ULTIMATELY, LOSS OF OIL PRESSURE.	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005020400005	20050204	00005	EU  	2005	2	4	CA041119007      	1	20041117	G	3246	5006227A	WHEEL           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	NLG	VIBRATION       	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) DEPARTING ON FLT. ON TAKE OFF ROLL NOSEWHEEL SHIMMY AND VIBRATION WAS FELT. THE TAKE OFF WAS ABORTED. MAINTENANCE 	INSPECTION REVEALED FROZEN GRAVEL AND ICE ON THE INNER RIM OF BOTH NOSEWHEELS. THE NOSE U/C AND SHIMMY DAMPER WAS INSPEC	TED, NO DEFECTS WERE FOUND. BOTH NOSEWHEELS WERE CHANGED AND THE A/C RELEASED TO SERVICE. NO SUBSEQUENT VIBRATION WAS RE	PORTED.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE
2004121000016	20041210	00016	WP  	2004	12	10	CA041119008      	2	20041118	G	7310	30751301	FUEL LINE       								GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED OIL PUMP REPLACEMENT SEVERE WEAR WAS FOUND ON THE PRIMARY FUEL MANIFOLD FEED LINE NEAR THE FUEL	 FLOW TRANSMITTER.  THE DAMAGE WAS CAUSED BY CONTACT BETWEEN THE FUEL FLOW TRANSMITTER INLET LINE B-NUT AND THE FEED LIN	E DUE TO LACK OF CLEARANCE. MOST OF THE DAMAGE WAS CAUSED BY THE CUTTING ACTION OF THE  BNUT AS IT WAS TIGHTENED DURING 	INSTALLATION OF THE FUEL FLOW TRANSMITTER WHICH HAD BEEN REMOVED 300 HR. EARLIER FOR ENGINE OVERHAUL. TWO OF THE THREE E	NGINES ON THE AIRCRAFT HAD SIMILAR DAMAGE. THE DAMAGED LINES WERE REPLACED ON BOTH ENGINES.							4	F			E6WE
2004121000068	20041210	00068	EA  	2004	12	10	CA041119009      	2	20041102	G	7414	S6LN1208	MAGNETO         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAGNETO WAS REMOVED AT ENGINE REMOVAL.  MAG WAS SENT IN BECAUSE THE OIL SLINGER RING WAS NOT IN THE GROOVE. TEAR D	OWN RESULTED IN THE FOLLOWING FINDINGS, WIRE ROUTING INCORRECT, LEAD WEARING ON COM SCREW, COIL LEAD NOT POSITIONED CORR	ECTLY, TUBING MISSING FROM COVER SCREW, EXCESSIVE GREASE LEAKING FROM ROLLER BEARING.  IMPROPER GREASE IN BEARING, WRONG	 WASHERS INSTALLED ON DISTRIBUTOR BLOCK STUDS, DISTRIBUTOR GEAR WASHER WAS WORN ON ID, DISTRIBUTOR BLOCK CRACKED AT ONE 	OF THE 6 ELECTRODES, VENT SCREEN W AS PAINTED OVER.		1	L	7	2 	3O	3	O		A20SO   	E14EA
2004121000069	20041210	00069	SO  	2004	12	10	CA041120001      	2	20041102	G	8500		ENGINE          			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 200 HR. INSP. THE OIL FILTER WAS CUT OPEN TO LOOK FOR METAL.  FILTER ELEMENT WAS WASHED IN VAROSOL AND DRAI	NED THROUGH A FILTER TO REVEAL METAL PARTICLES.  THE ENGINE SHOP WAS CALLED TO IDENTIFY THE METAL. WE PULLED NR 2 & 4 CY	LINDERS TO OBSERVE THE NR 3 CRANKSHAFT BEARING AND FOUND THAT IT WAS ABLE TO BE TURNED IN THE JOURNAL BY HAND. THE ENGIN	E WAS IN FINE WORKING ORDER UP TO THIS INSP.  THE ENGINE WAS REMOVED AND SENT TO A REPAIR SHOP.			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P21EA
2005020100165	20050201	00165	EU  	2005	2	1	CA041122002      	2	20041114	G	8500		ENGINE          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  		FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SMOKE ENTERED COCKPIT.  PILOT RETURNED TO BASE.  ENGINE LOST POWER AND BEGAN TO MISSON FINAL AND WAS SHUT DOWN.						1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO
2005020100166	20050201	00166	EA  	2005	2	1	CA041122003      	2	20041119	G	8530	71973	GASKET          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	INTAKE FLANGE	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L4441827A			(CAN) INTAKE FLANGE GASKET SPLIT THROUGH CIRCUMFERENCE RESULTING IN MINOR VACUUM LEAK. THE GASKET MATERIAL IS HARD AND B	RITTLE, AND APPEARS TO BE ERODING ON THE INNER EDGE. THIS IS THE FOURTH GASKET FOUND SPLIT IN THE LAST FEW WEEKS. THREE 	ON THIS ENGINE (1164 HOURS) AND ONE ON ANOTHER AT 700 HOURS. BOTH MGF FACTORY REMANUFACTURES.  SUSPECT DEFICIENCY IN MAT	ERIAL.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005020100170	20050201	00170	CE  	2005	2	1	CA041122004      	1	20041117	G	3244	185F035	TIRE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG	BLISTERED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A PILOT REPORTED THAT THE NR 3 TIRE WAS FLAT, MAINTENANCE REPLACED THE WHEEL ASSY.  DURING THE REMOVAL IT WA	S NOTICED THAT THE IB SIDEWALL HAD A LARGE BLISTER.  IT APPEARS THAT AN AREA (3 INCHES IN DIAMETER) OF THE OUTSIDE LAYER	 OF RUBBER (.0625 IF AN INCH THICK) WAS DISBONDED FROM THE REST OF THE TIRE, THE AIR PRESSURE CAUSED THIS TO INFLATE CRE	ATING A LARGE BLISTER. THIS BLISTER EVENTUALLY RUBBED ON THE BRAKE CALLIPER CAUSING THE BLISTER TO BURST, DEFLATING THE 	TIRE.		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE
2004121000018	20041210	00018	EU  	2004	12	10	CA041122005      	1	20041120	G	2720	065008617	CONTROL UNIT    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	YAW DAMPER	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) YAW DAMPER INDICATION LAMP WOULD NOT ILLUMINATE ON KMC 321 CONTROL HEAD. 'YD' INDICATION OK ON BOTH EFIS SCREENS. 	 REPLACED WITH SERVICEABLE UNIT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004121000071	20041210	00071	GL  	2004	12	10	CA041122006      	2	20041120	G	7230		TURBINE         			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					STAGE 3	FAILED          	W				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL, RT ENGINE PERFORMED AN UNCOMMANDED IN FLIGHT SHUT DOWN AT 80 KNOTS.  PRELIMINARY REPORT REVEAL A 	CRACK TURBINE CASE AND LP STAGE 3 BLADE FAILURE.  THE FAN BLADES WORE A HUGE GROOVE IN THE FAN CASE.  ENGINE EN ROUTE TO	 ROLLS ROYCE CANADA FOR FAILURE INVESTIGATION.				2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH
2004122200171	20041222	00171	EU  	2004	12	22	CA041122007      	1	20041120	G	3080	9754421421	ELEMENT         	ROSEMOUNT   		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	VANE HEATER	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						0425					(CAN) WHILE PERFORMING A CHECK OF THE PROBES HEATING SYSTEM, THE LT VANE HEAT WAS FOUND INOP. AOA ASSY REPLACED, FUNCTIO	N TESTS SATISFACTORY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004122200172	20041222	00172	GL  	2004	12	22	CA041122008      	2	20041106	G	7230		COMPRESSOR      			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				D	Y		INFLIGHT SEPARATION       	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								CAE312392			(CAN) UNCOMMANDED IN-FLIGHT SHUTDOWN.  IN CLIMB MODE AT 10,000 FT, FLIGHT CREW HEARD A LOUD BANG AND THE NR 1 ENGINE SHU	TDOWN.  MINOR FINDINGS ON MCD'S.  LP WILL ROTATE, HP WILL NOT ROTATE.  CMC DOWNLOAD SHOWED HP VIBRATION EXCEEDANCE OF 1.	7 IPS FOR 11SECONDS.  FOUND HPC1 IGV DAMAGE AND HPC1 BLADE DAMAGE ON BORESCOPE.  NO EVIDENCE OF FOD.  ENGINE IN ROUTE FO	R INVESTIGATION AT ROLLS-ROYCE CANADA.			2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH
2005031100103	20050311	00103	NE  	2005	3	11	CA041122009      	2	20041118	G	7200	TAY6501510	ENGINE          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 2	VIBRATION       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			20192								(CAN)  AIRCRAFT ENCOUNTERED HI VIBRATION IN CLIMB ON NR2 ENGINE GAUGE, MFDS MESSAGE ALERT (REF JOURNEY LOG PAGE 031117).	 UNABLE TO MAINTAIN THRUST.   THRUST WAS REDUCED BY .15 TO CLEAR ALERT.  AIRCRAFT RETURNED TO BASE.  MAINTENANCE TROUBLE	SHOT IAW AMM 71-00-00, 811-811A, STEP 101 TO 108. VIBRATION SURVEY WAS C/OUT IAW AMM 71-00-00 AND VIBRATION WAS FELT AT0	.6 IPS.  THE NR2 ENGINE WAS REPLACED (P/N OFF: TAY650-15/10, S/N OFF: 17679,P/N ON: TAY650-15/10,S/N ON: 17653) IAW AMM 	71-00-00 (REF TASK CARD 71-00-00-400-814-C).		2	L	7	2 	4F	4	F	RT	        	E25NE
2005020100176	20050201	00176	EU  	2005	2	1	CA041122010      	1	20041119	G	3260	SK3852	INDICATOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) PILOT DECLARED AN EMERGENCY LANDING BECAUSE HE HAD NO GREEN LIGHT ON HIS LANDING INDICATOR, BUT HAD NO MESSAGE ON 	MFDU, THAT THE GEAR WAS UNSAFE. NOTE: IN REFERENCE TO THE QRH (QUICK REFERENCE HANDBOOK, ABNORMAL PROCEDURES,6.09 PAGE2,	 THE FLIGHT CREW WAS NOT REQUIRED TO DECLARE AN EMERGENCY. AIRCRAFT DID 2 FLY BYES TO CONFIRM WITH TOWER AND LANDED WITH	 NO PROBLEM. MAINTENANCE REPLACED THE LANDING GEAR POSITION INDICATOR  IAW 32-61-02. LANDING GEAR EXTENSION/RETRACTION C	OMPLETED IAW 32-00-00.		2	L	7	2 	4F	4	F	RT	        	E25NE
2005020100151	20050201	00151	EA  	2005	2	1	CA041122011      	2	20041116	G	7322		O-RING          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FCU FUEL BOWL	DISPLACED       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK ON LT ENGINE IN FLIGHT. CAUSE BEING, DISPLACED O-RING ON FCU FUEL BOWL.  VARIFIED BOWL HAD BEEN TORQUED 	TO SPECS IAW MM, CHAPTER 73-10-02 FOR ARGO-TECH PUMPS.					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC
2005020100177	20050201	00177	NM  	2005	2	1	CA041122012      	1	20041122	G	3260	858601	PSEU            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT MLG	INTERMITTENT    	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CL	CLIMB          	1			CA											(CAN) AFTER T/O, RT MLG DOWNLOCK GREEN LIGHT STAYS ON AFTER GEAR UP SELECTION.  FLIGHT CREW EXTENDED THE LANDING GEAR AN	D LANDED BACK AT BASE. LANDING GEAR INSPECTION CHECKED - OK.  PSEU CODES RETRIEVED (53, 55).  R/R PSEU. LANDING GEAR TES	TED OK. AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100137	20050201	00137	NM  	2005	2	1	CA041122013      	1	20041118	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A 4 INCH CRACK WAS FOUND ON THE OUTER FUSELAGE SKIN JUST AFT OF THE WING TO BODY FAIRING RT SIDE.  CRACK LOCATED O	N STR 15R (2) TWO INCHES AFT OF STA.727A.   CRACK REPAIRED IAW SRM 53-30-3 FIG48 DETAIL XI TIMES 53851.20 CYCLES 46695.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005020100138	20050201	00138	NE  	2005	2	1	CA041122014      	2	20041026	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					LEFT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								124496			(CAN) DURING CRUISE, PROPELLER SPEED DECREASED ACCOMPANIED BY MASTER WARNING AND CCAS+LOW ALERTS.  THE CREW SECURED THE 	ENGINE, DECLARED PAN PAN AND COMPLETED A SING LT ENGINE LANDING AT DESTINATION.  MFG WILL MONITOR THE INVESTIGATION AND 	AMEND THIS REPORT TO REFLECT ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	        	E2ONE
2004121000019	20041210	00019	EA  	2004	12	10	CA041122015      	1	20041121	G	2424	51539008C	CONTROL UNIT    			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	GENERATOR	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			34748								(CAN) DURING MAINTENANCE SERVICING, ENGINEER FOUND STARTER GENERATOR WARM.  AIRCRAFT ENGINE WAS COLD AND NO ATTEMPTED ST	ARTS HAD BEEN MADE.  MAINTENANCE INSPECTION FOUND FAULT CAUSED BY GENERATOR CONTROL UNIT.  DC GENERATOR CONTROL UNIT REP	LACED.  AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2004122200176	20041222	00176	NM  	2004	12	22	CA041122016      	1	20041120	G	5210	852202081007	SEAL            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PAX DOOR	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, UNABLE TO PRESSURIZE AIRCRAFT TO HIGH DIFFERENTIAL , 'CABIN PRESS' WARNING LIGHT ILLUMINATED.  FLIGH	T ATTENDANT REPORT LOUD WHISTLING FROM FORWARD EMERG EXIT DOOR.  AIRCRAFT RETURNED TO ORIGINATING AIRPORT.  MAINTENANCE 	INSPECTION FOUND FORWARD EMERGENCY EXIT DOOR INFLATABLE SEAL WORN.  SEAL REPLACED.  AIRCRAFT RETURNED TO SERVICE. (PART 	IS CONSIDERED AN EXPENDABLE AND TIMES ARE NOT TRACKED)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005020100065	20050201	00065	CE  	2005	2	1	CA041123001      	1	20041119	G	2730	NAS427K6	PIN             			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR CONTROL	MISSING         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE PRIMARY CABLE FOR THE ELEVATOR CONTROL HAD JUMPED OUT OF THE PULLEY. THE (SPRING PIN) THAT PREVENTS THIS FROM 	HAPPENING WAS OUT OF POSITION (UNABLE TO STOP THE CABLE FROM LEAVING THE PULLEY). ABRASION OF THE ELEVATOR CABLE AT THE 	PULLEY AND ON SUPPORTING STRUCTURE A SHORT DISTANCE FROM WHERE THE ELEVATOR CABLE, EMERGES FROM THE PRESSURE VESSEL AS I	T TRAVELS AFT TO THE BELLCRANK.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA
2004122200177	20041222	00177	NM  	2004	12	22	CA041123002      	1	20041118	G	3244	DSC428	TIRE            			DHAV  	DHC8  	DHC8301     	1386003	NM  										TIRE	FAILED          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) DURING A TAKEOFF, AS THE SPEED INCREASED A MILD VIBRATION WAS FELT WHICH QUICKLY INCREASED.  THE VIBRATION WAS PRO	BABLY GENERATED BY THE LT OUTBOARD MAIN TIRE FAILING.  THE TAKEOFF WAS REJECTED ABOVE 70 KNOTS WITH THE TIRE FINALLY FAI	LING BETWEEN 90 TO 100 KNOTS.  THE AIRCRAFT WAS ABLE TO ROLL ON THE REMAINING LT INBOARD MAIN TIRE UNTIL IT FAILED AT AB	OUT 20 KNOTS.  THE AIRCRAFT WAS STOPPED ON THE RUNWAY WITHOUT FURTHER INCIDENT.  ENGINEERING ASSESSED THE AIRCRAFT FOR D	AMAGE CONFIRMING THAT THE WHEEL ASSEMBLIES ONLY REQUIRED REPLACEMENT.  AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER 	INCIDENT.  GOODYEAR (31X9.75-14 12PLY)	2	H	7	2 	4T			RT	A13NM
2004122200179	20041222	00179	NM  	2004	12	22	CA041123003      	1	20041123	G	5397	H75C20	WIRE            			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					AFT LAV	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											FOUND WIRE BUNDLE INSIDE TOILET SHROUD BURNING AND SMOKING, C/B SYST 2 WATERLINE HEATER (LAV LIGHTS) POPPED IN AVIONICS 	BAY.  FURTHER T/S ON WIRING BURNED, FOUND WIRES IDENTIFIED AS H75C20,H75A20, AND H75A20N (GRN) ALL BROKEN FROM SPLICES. 	 ALSO, HEATER TAPE RINSE LINE B8 NEEDS TO BE REPLACED DUE WIRE BROKEN.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2005020100098	20050201	00098	NM  	2005	2	1	CA041123004      	1	20041122	G	5240	69222825	HINGE           	BOEING      		BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					DOOR HALF	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC BAY DOOR SEPARATED FROM AIRCRAFT.  AIRCRAFT WAS BEING POSITIONED FROM THE MAIN MAINTENANCE BASE ON THE M	ORNING OF NOVEMBER 22, 2004.  DURING SERVICE CHECK BY MAINTENANCE, IT WAS NOTICED THAT THE HYDRAULIC BAY DOOR WAS MISSIN	G. MAINTENANCE SUSPECT DOOR HINGE FAILURE. THE HYDRAULIC BAY STRUCTURE WAS INSPECTED FOR SECONDARY STRUCTURE DAMAGE. SER	VICEABLE DOOR AND DOOR HINGE ASSY WAS INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005041900012	20050419	00012	EU  	2005	4	19	CA041123005      	1	20041118	G	2910	410100211	PTU             			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					FUEL PRESSURE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER TOW TO GATE, A LEAK WAS NOTICED COMING FROM THE PRESSURE TRANSFER UNIT. UNIT WAS REPLACED BEFORE FLIGHT.						2	L	7	2 	4F	4	F	RT	A28NM   	E37NE
2005041900013	20050419	00013	NE  	2005	4	19	CA041123006      	2	20041123	G	7314	1383M68P12	PUMP            			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					HP FUEL	CONTAMINATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) UNABLE TO START NR 2 ENG. DUE FUEL VALVE LT AT PEDESTAL & EICAS MSG FOR 'R FUEL VALVE'.  CHECKED 28VDC AT FUEL CUT	OFF SW AND PWR AVAILABLE. REPLACED FUEL S/O VALVE SOLENOID, NO FIX.  REPLACED HMU, NO FIX.  REMOVED FUEL PUMP AND FOUND 	CONTAMINATED WITH METAL.  MPN 9355M33P13 IN (STREAMER CAVITY).				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2005041900014	20050419	00014	CE  	2005	4	19	CA041123007      	1	20041118	G	2720	0400107150	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIGHT RUDDER CABLE FOUND SLIGHTLY FRAYED WHERE IT TRAVELS OVER THE REARMOST PULLEY IN THE AFT FUSELAGE.  THERE WER	E APPROXIMATELY 8 TO 10 WIRES BROKEN.  CABLE WAS REPLACED WITH NEW.					1	H	7	1 	3O	3	O	NT	3A19    	E223
2005012400003	20050124	00003	SW  	2005	1	24	CA041123008      	1	20040720	G	7500	3017393	LINE            	PWA         	PT6T3       	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					P3 AIR	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						CPPS61172					(CAN) LINE BROKE.  A/C RETURNED TO BASE.  LINE WAS REPLACED.  A/C WAS RETURNED TO SERVICE.  NO FURTHER DEFECTS.						1	G	7	1 	4U	4	U		H4SW    	E22EA
2005020100171	20050201	00171	SW  	2005	2	1	CA041123009      	1	20041124	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1250 								(CAN) UPON REACHING CRUISING ALTITUDE OF 14, 000 FEET CO-PILOTS HEATED WINDSHIELD SHATTERED.  WINDOW REMAINED INTACT AND	 FLIGHT CREW DEPRESSURIZED AIRPLANE AND FLEW TO A SAFE ALTITUDE.  FLIGHT CREW NOTICED A SPARK OR FLASH INSIDE WINDSHEILD	 PRIOR TO IT SHATTERING, MOST LIKELY RELATED TO WINDSHIELD HEAT SYS.  WINDSHEILD HEAT WAS TURNED ON PRIOR TO TAKEOFF. AC	  WAS CLOSE TO ITS DESTINATION AND CARRIED OUT AN UNEVENTFUL LANDING. MAINT INSPECTED THE WINDOW AND FOUND NOTHING THAT 	MAY HAVE CAUSED THE FAILURE INCLUDING ANY IMPACT DAMAGE. THE WINDOW AND IT'S TEMPERATURE CONTROLLER HAVE BEEN REPLACED A	S A PRECAUTION.  THIS WINDOW WAS INSTALLED ON THE AIRCRAFT ON JANUARY 20, 2004 AND HAD A TOTAL TIME OF 1250.5 HOURS.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2005020100172	20050201	00172	SW  	2005	2	1	CA041123010      	1	20041103	G	2821		BYPASS SWITCH   			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FILTER ASSY HEAD	CORRODED        	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA						3755					(CAN) FILTER LIGHT CAME ON UPON LANDING.  REMOVED FILTER AND INSPECTED.  NO CONTAMINATION FOUND AND TEST LIGHT CIRCUIT. 	 A LIGHT CAME ON AGAIN AND UPON INVESTIGATION, IT WAS FOUND THAT THE SWITCH WAS CORRODED.  A NEW FILTER ASSY. WAS INSTAL	LED AND TESTED.  IT FUNCTIONS CORRECTLY.  INCIDENT HAPPENED 35 HOURS AFTER 300 HR INSP,  WHICH INCLUDED FILTER CHANGE.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2005012400004	20050124	00004	SW  	2005	1	24	CA041123011      	1	20040712	G	6320	212040054005	CASE            	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					M/R GEARBOX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						ABW270					(CAN) PILOT REPORTED HEARING A LOUD BANG AND THOUGHT PIECES OF THE HELICOPTER FELL FROM THE BELLY.  PILOT WAS FLYING VER	TICAL REFERENCE WITH A BAMBI BUCKET.  UPON IMMEDIATE RETURN TO THE PAD, THE HELL HOLE SIDE INSPECTION PANELS WERE REMOVE	D AND THE SUPPORT CASE WAS FOUND BROKEN AT LIFT LINK FITTING.  THE TRANSMISSION ASSEMBLY WAS REPLACED.  A/C RETURNED TO 	SERVICE.			1	G	7	1 	4U	4	U		H4SW    	E22EA
2005012400005	20050124	00005	SW  	2005	1	24	CA041123012      	1	20040707	G	2810	FCE53191	FUEL CELL       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						SPLIT           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			18044								(CAN) LOW FUEL LIGHT COMING ON WITH 250-300 LBS INDICATED IN LT LOWER FUEL CELL. INVESTIGATION FOUND SPLIT IN FUEL CELL 	INTERNALLY ACROSS BAFFLE, WHICH ACTED LIKE A ONE WAY VALVE.  THIS WOULD PUMP FUEL AWAY FROM BOOST PUMP WHEN A/C IS IN UN	USUAL ATTITUDES (HOVER/LONG LINING).				1	G	7	1 	4U	4	U		H4SW    	E22EA
2004121000020	20041210	00020		2004	12	10	CA041124001      	4	20041119	G	3416	C1621AA02	INDICATOR       			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING STRAIGHT AND LEVEL FLIGHT, THE ISI (STANDBY ADI) SHUTDOWN AND CAME BACK ONLINE BY ITSELF.  THE ISI WAS REPL	ACED.					2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN
2004122300029	20041223	00029	NM  	2004	12	23	CA041124002      	1	20040826	G	2742	3993001010	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					RT PITCH FEEL	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											DURING TAKEOFF RUN AT A SPEED BETWEEN 100 AND 120 KIAS, GOT 'ELEVATOR FEEL' FAULT LIGHT ON.  TAKEOFF ABORTED, PASSENGERS	 DEBRIEFED, AND RETURNED TO GATE.  THE CENTRAL DIAGNOSTIC SYSTEM (CDS) WAS INTERROGATED AND FCECU FAULT CODES EA AND E9 	WERE FOUND LOGGED IN THE FAULT HISTORY, THESE FAULTS INDICATE THAT THE RIGHT PITCH FEEL ACTUATOR IS NOT CORRECTLY TRACKI	NG THE COMMAND AND THE MESSAGE WILL SHOW WHEN THE RIGHT PITCH FEEL ACTUATOR OR THE FCECU HAS FAILED.  THE RT PITCH FEEL 	ACTUATOR WAS CONSEQUENTLY REPLACED IN ACC WITH AMM TASK 27-32-11.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2004122300030	20041223	00030	EA  	2004	12	23	CA041124003      	2	20041122	G	7414	M3548	ROTOR SHAFT     	SLICK       	4345        	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00072126					(CAN) ON RUN UP MAGNETO CHECK, FOUND LT MAG INOP.  LT MAG REMOVED AND INSPECTED, ROTOR GEAR WAS FOUND SEPARATED FROM ROT	OR SHAFT.  RT MAGNETO WAS INSPECTED IN THE SAME AREA OF LT MAG FAILURE NO DEFECT FOUND.  A NEW MAGNETO WAS INSTALLED IN 	LT POSITION RT MAGNETO REINSTALLED.  MAGNETOS TIMED TO ENGINE AIRCRAFT GROUND RUN FUNCTION CHECK-SERVICEABLE.				1	G	7	1 	3O	3	O		4H12    	1E10
2005020100105	20050201	00105	EU  	2005	2	1	CA041124004      	1	20041121	G	2740	864401	PROXIMITY SWITCH			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STAB	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AC DIVERTED, AFTER HAVING A HYDR  STAB NR 1 FAULT IN FLIGHT (LOST FAULT ON LANDING).  MAINT C/OUT A HYDR CONTROL S	TABILIZER OPS CHECK IAW AMM 27-42-01, NO FAULT FOUND.  ON FOLLOWING FLIGHT, SAME MESSAGE REAPPEARED ON THE MSDS (MULTI F	UNCTIONAL DISPLAY SYSTEM) AT THE TOP OF THE DESCENT. MAINT TESTED THE STAB SYSTEM IAW AMM 27-42-01.  ALL INDICATIONS FOU	ND NORMAL.  FUNCTIONAL TEST OF  STICKING SWITCH WAS C/OUT IAW AMM 27-42-01-710-054-A03.  NO FAULTS FOUND.  ON NR 1 ENGIN	E START, HYDRAULIC STAB 1 FAULT OCCURRED.  MAINT  TROUBLESHOOTING CONFIRMED THE NR 1 STAB PROXIMITY SWITCH P/N OFF, 8-64	4-01, S/N OFF, 330- P/N ON, 8-644-01, S/N ON, A2231) AT FAULT AND WAS REPLACED AND TESTED IAW AMM 27-42-01.	2	L	7	2 	4F	4	F	RT	        	E25NE
2005020100153	20050201	00153	EU  	2005	2	1	CA041124005      	1	20041123	G	5610	D20543406	WINDSHIELD      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) NOV 23RD 2004, RT FLIGHT OFFICER WINDSHIELD CRACKED IN FLIGHT DURING CLIMB.  AIRCRAFT C/OUT AN AIR TURN BACK.  MAI	NTENANCE REPLACED THE WINDSHIELD (P/NOFF, D20543-406, S/N OFF, 01303H2172 - P/N ON  D20543-406, S/N ON 04198H1107) IAW A	MM 56-11-00.				2	L	7	2 	4F	4	F	RT	        	E25NE
2005020100154	20050201	00154	NM  	2005	2	1	CA041124006      	1	20041123	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	INOPERATIVE     	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, 10 MIN. AFTER TAKE OFF, CLOSE TO 25 000 FT,  PILOT NOTICED NR 2 ENGINE HYD PUMP CAUTION LIGHT FOLLOW	ED BY A LOSS OF NR 2 HYD FLUID QTY ON COCKPIT GAUGE.  PILOT FOLLOWED Q400 QUICK REF HANDBOOK PROCEDURE NR 12.5. PTU HAS 	BEEN MANUALLY SELECTED ON WITH NO PRESSURE INCREASE IN NR 2 SYST DUE NO HYD FLUID, PTU SELECTED OFF,  NR 2 HYD ISOLATION	 VALVE SELECTED ON.  AC RETURNED AND ALTERNATE LANDING GEAR EXTENSION PROCEDURE USED.  NR 2 ENGINE DRIVE HYD PUMP R & R 	IAW AMM.  NR 2 HYD SYS BLEED IAW AMM AND NR 2 HYD SYS SERVICE IAW AMM. AC RETURN TO MAINT BASE.  ENGINE DRIVE HYD PUMP D	ETAIL FINDING REPORT WILL FOLLOW.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005012400006	20050124	00006	NE  	2005	1	24	CA041124007      	1	20041118	G	6210	6117020201	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					MAIN ROTOR	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE ROTOR BLADE INTEGRITY MONITOR SYSTEM INDICATED A LEAK IN ONE OF THE MAIN ROTOR BLADES. THE PILO	T LANDED THE AIRCRAFT SAFELY AND MAINTENANCE REPLACED THE BLADE AND SENT IT IN FOR INSPECTION.  DURING INSPECTION, A LEA	K WAS INDICATED UNDER THE CUFF WHICH WAS THEN REMOVED AND A CRACK WAS FOUND BETWEEN BOLT HOLES.  THE BLADE IS SCRAP AND 	AVAILABLE FOR INSPECTION.			2	G	7	2 	4U	4	U		1H15    	1E3
2005012400007	20050124	00007	CE  	2005	1	24	CA041124008      	1	20041117	G	5610	5042006936	WINDSHIELD      			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	COCKPIT	BROKEN          	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) RT FRONT INNER PANE OF WINDSHIELD SHATTERED IN FLIGHT.						1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA
2005020100155	20050201	00155	SW  	2005	2	1	CA041124009      	1	20041108	G	6510	327211	DISC PACK       			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TAIL ROTOR DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISC PACK, 1 DISC CRACKED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2005020100109	20050201	00109	NM  	2005	2	1	CA041124010      	1	20040830	G	2742	3994001009	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	ELEV PITCH TRIM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING DECENT INBOUND TO BASE, THE PITCH TRIM CAUTION LIGHT CAME ON, QRH PERFORMED AND IT BECAME APPARENT THAT WE 	HAD A FAILURE OF THE PITCH TRIM.  ATC NOTIFIED AND THE APPROACH PLANNED WITH HIGH SPEED FOR AS LONG AS POSSIBLE. DURING 	SPEED REDUCTION STICK FORCES INCREASED SIGNIFICANTLY AS DESCRIBED IN QRH. STICK FORCES LIGHTENED ON SELECTION OF FLAP 5,	 AND INCREASED AGAIN WITH SPEED REDUCTION. ALTHOUGH QUITE HEAVY TO HOLD, THE APPROACH AND LANDING WERE PERFORMED WITHOUT	 PROBLEMS. ELEVATOR PITCH TRIM ACTUATOR WAS REPLACED IAW AMM TASK 27-32-06.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005020100110	20050201	00110	NE  	2005	2	1	CA041124011      	2	20041110	G	7260		DRIVE ASSY      			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					GEARBOX	FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								124598			(CAN) DURING CRUISE, ENGINE OIL PRESSURE DROPPED TO ZERO FOLLOWED BY AN UNCOMMANDED ENGINE SHUTDOWN.  A SINGLE ENGINE LA	NDING WAS CARRIED OUT AT DESTINATION.  SUBSEQUENT INVESTIGATION HAS EVIDENCED A FRACTURED (ACCESSORY GEARBOX DRIVE) TOWE	RSHAFT.  PWA WILL INVESTIGATE THE EVENT AND REVISE THIS REPORT TO REFLECT ROOT CAUSE, ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	        	E2ONE
2004121000021	20041210	00021	SO  	2004	12	10	CA041124012      	2	20041122	G	8520	643045	CAMSHAFT        			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C507   	GL  	ENGINE	SHEARED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								246120R			(CAN) THE ENGINE LOST POWER ON CLIMB-OUT OF CALGARY.  THE PILOT FEATHERED THE PROP AND RETURNED TO CALGARY. THE ENGINE W	AS GROUND RUN AND THE PROP GOVERNOR WAS FOUND TO BE INOPERATIVE.  UPON REMOVAL OF THE GOVERNOR, IT WAS FOUND THAT THE DR	IVE P/N 538076 WAS NOT IN INSTALLED POSITION.  THE BEVEL GEAR P/N 534655 WAS ALSO MISSING.  UPON FURTHER INSPECTION IT W	AS FOUND THAT THE CAM SHAFT P/N 643045 HAD SHEARED ALLOWING THE GOVERNOR DRIVE TO FALL OUT OF ITS POSITION AND DROP INTO	 THE OIL PAN.  THE ENGINE HAS BEEN REMOVED AND SENT TO AN ENGINE SHOP FOR TEARDOWN AND REPAIR.  A COPY OF THE TEARDOWN R	EPORT WILL BE INCLUDED IN THIS SDR WHEN WE RECEIVE IT.	1	L	7	2 	3O	3	O		A34CE   	E8CE	5	C	P57GL
2004121000048	20041210	00048	NM  	2004	12	10	CA041125001      	1	20041122	G	5280	65224787	BRACKET         			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG DOOR	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON ARRIVAL, MAINTENANCE PERSONEL NOTED THE NOSE LANDING GEAR DOORS HANGING OPEN.  FURTHER INSPECTION FOUND THE B	RACKET FOR THE DOOR OPERATION ROD BROKEN.  SEE IPC 32-30-00-06 ITEM 89.  BRACKET AND HARDWARE REPLACED AND GEAR SWINGS C	ARRIED OUT, AND A/C RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA
2005020100106	20050201	00106	NM  	2005	2	1	CA041125002      	1	20041110	G	3260	82410888011	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) DURING DECENT TO BASE WITH LANDING GEAR RETRACTED, NOSE (GREEN), NOSE (RED) AND HANDLE (AMBER) LIGHT ILLUMINATED F	OR ABOUT 3 MINUTES.  EXTENSION, LANDING AND TAXI NORMAL.  PSEU FAULT HISTORY INDICATED NGDN1 UNREASONABLE NEAR FAULT.  R	EPLACED NGDN1 PROXIMITY SENSOR IAW AMM 32-61-06.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005020100173	20050201	00173	NM  	2005	2	1	CA041125003      	1	20040903	G	6120	699018002	ECU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLLER	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) AUTO FEATHER SYSTEM FAILED TO ARMED WHEN TAKE-OFF POWER WAS APPLIED. ABORTED TAKE-OFF.  FAULT CODE 794 WAS LOGGED 	IN THE CENTRAL DIAGNOSTIC SYSTEM (CDS) DURING THE FOLLOWING OVERSPEED GOVERNOR TEST.  A FUNCTIONAL TEST OF THE PEC AND C	ALIBRATION PROCEDURE WAS THEN PERFORMED IAW AMM TASK 61-20-36-720-801.  FAULT CODE 238 REMAINED LOGGED IN THE CDS AS WEL	L AS PEC CAUTION LIGHT AND POWERPLANT MESSAGE ON THE ED AND FINALLY THE LT PROPELLER ELECTRONIC CONTROL UNIT (PEC) WAS R	EPLACED IAW AMM TASK 61-20-36.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO
2005020100107	20050201	00107	CE  	2005	2	1	CA041125004      	1	20041025	G	3213	NAS464P5A42	BOLT            	CESSNA      		CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	NLG STRUT	SHEARED         	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) BOLT SHEARED ON LANDING CAUSING NOSE GEAR TO PIVOT FORWARD. NOTE: THIS BOLT WAS LAST CHANGED SEPTEMBER 9/94 AT 287	5 I.T.T. (AIRCRAFT PRESENT TT IS 6238.7 HOURS) THIS AIRCRAFT HAS OPERATED ON SKIS (SUSPECT THAT BOLT WAS OVERSTRESSED IN	 THIS CONFIGURATION).  THIS BOLT WAS CRACKED PRIOR TO FAILURE AS HALF OF FRACTURE IS BLACK AND TOTAL FAILURE IS WHITE. S	OME DAMAGE TO AIRFRAME WAS ENCOUNTERED.  IT SHOULD BE NOTED THAT INSPECTION OF THIS BOLT IS NOT REPLACED IN INSPECTION S	CHEDULE.		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA
2005020100102	20050201	00102	GL  	2005	2	1	CA041125005      	1	20041123	G	5520	PAF06080P11	BUSHING         	DIAMON      		DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					LT OB ELEVATOR	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION, LT OB ELEVATOR BUSHING FOUND MISSING.						1	L	7	1 	3O	3	O	NT	A47CE   	1E10
2005020100103	20050201	00103	CE  	2005	2	1	CA041126001      	1	20041122	G	2752	656014131	CABLE           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					TE FLAPS	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AC DEPARTED, DURING CLIMB THE PILOTS NOTICED THAT THE FLAP INDICATOR DID NOT MATCH FLAP SELECTOR HANDLE.  FLAP POS	ITION WAS VERIFIED VISUALLY BY CO-PILOT PRIOR TO RETURNING TO BASE.  UPON MAINTENANCE INVESTIGATION IT WAS FOUND THAT TH	E FWD FLAP FOLLOW-UP CABLE WAS BROKEN AT THE PULLEY SWEDGED BALL.  SL560-27-11 (SWEDGED BALL INSPECTION) WAS ACCOMPLISHE	D APRIL26/04 AT 573.1 A/F HOURS 411 LDGS.  THIS SB WAS NEXT DUE AT 873.1 HRS.  AIRCRAFT TT AT FAILURE WAS 846.3 HRS (-26	.8 HRS TO NEXT INSPECTION) THE CABLE WAS REPLACED, RIGGED IAW  MM,  DUAL INSPECTION C/W AND RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005012400008	20050124	00008	CE  	2005	1	24	CA041126003      	1	20041125	G	3244	5004913	TIRE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) ON TAKE OFF SOUND WAS HEARD BY THE FLIGHT CREW.  THEY ABORTED THE TAKE-OFF.						2	L	7	2 	4F	4	F		A10CE   	E6WE
2005020100071	20050201	00071	WP  	2005	2	1	CA041126004      	2	20041125	G	7310	8945681	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE FUEL	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) UPON DECENT INTO AIRPORT POWER LEVER STAGGER WAS ENCOUNTERED BY FLIGHT CREW.  UPON LANDING AND TAXING THE OIL PRES	SURE COULD NOT BE MAINTAINED AND THE FLIGHT CREW SHUT DOWN THE ENGINE.  UPON INVESTIGATION THE FUEL FLOW TRANSMITTER LIN	E WAS FOUND CRACKED WHICH CAUSED THE ENGINE TO NOT BE ABLE TO MAINTAIN FUEL PRESSURE WHICH CAUSED IT TO SHUTDOWN.  THE L	INE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2005020100095	20050201	00095	EU  	2005	2	1	CA041126005      	1	20041123	G	2434	9789601091	BRUSH BLOCK     	PILATS      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	WORN            	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA						100446					(CAN) DURING CRUISE FLIGHT, GEN 2 LIGHT CAME ON. PILOT PULLED GEN 2 CIRCUIT BREAKER AND LANDED AT BASE. INVESTIGATION RE	VEALED A SLIGHT CONDUCTIVE PATH BETWEEN THE TWO BRUSHES WITH THE BRUSH BLOCK ASSY REMOVED BELIEVED TO BE CAUSED BY BRUSH	 BLOCK DUST. THE SLIP RING WAS ALSO FOUND TO BE VERY DIRTY. THE SLIP RING WAS CLEANED, A NEW BRUSH BLOCK ASSY INSTALLED 	AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2004121000049	20041210	00049	EA  	2004	12	10	CA041126008      	1	20041125	G	2421	31708500	ADAPTER         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AC GEN	PULLED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING CRUISE, NR1 ENG OIL PRESSURE FLUCTUATED. ON APPROACH NR 1 LOW OIL PX CAUTION LIGHT ILLUMINATED. CREW ELECTE	D TO FEATHER & SHUTDOWN NR 1 ENGINE. MAINTENANCE INSPECTION FOUND ENGINE WITH LOW OIL QUANTITY DUE TO OIL LOSS THROUGH P	ARTIAL S OPERATION OF NR 1 AC GENERATOR FROM ADAPTOR PLATE. TOP TWO STUDS HAD PULLED OUT OFADAPTOR PLATE, LOWER TWO STUD	S AND NUTS STILL INTACT , BUT NUTS SLIGHTLY LOOSE, ALLOWING AC GENERATOR TO BACK OFF FROM ADAPTOR PLATE BY APPROX. 1/4 I	NCH AT TOP , STILL IN CONTACT WITH ADAPTOR PLATE AT BOTTOM. AC GENERATOR AND ADAPTER PLATE REPLACED . ADAPTOR PLATE IS C	LASSIFIED AS AN EXPENDABLE PART , TIMES NOT TRACKED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005012400010	20050124	00010	SW  	2005	1	24	CA041126009      	1	20041125	G	5510	306611306612	COVER           			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	HORIZONTAL STAB	MISLOCATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION IT WAS NOTED THAT ON THE LT AND RT HORIZONTAL STABILIZERS, THE HOLES THAT WERE DRILLED FO	R THE GAP COVER SCREW HOLES WERE DRILLED THROUGH 2 RIVETS ON THE LT AND RT STABILIZERS ON THE LOWER SURFACES ONLY.  THE 	RIVETS ATTACH THE SKIN TO THE END RIB.  REPAIRS WILL BE ACCOMPLISHED PRIOR TO THE AIRCRAFT BEING RETURNED TO SERVICE.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL
2004121000050	20041210	00050	NM  	2004	12	10	CA041126010      	1	20041126	G	3213	161T11387	AXLE            	BFGOODRICH  	161T110070  	BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					RT MLG	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			73707	49091							(CAN) ACFT 684 ON LANDING, DISCOVERED RT ML GEAR AFT AXLE BROKEN, IT SEEMS THAT HAPPEN DURING TAKEOFF IN XXX, BECAUSE FL	IGHT CREW REPORT ANTI- SKID LIGHT WAS ON DURING WHOLE FLIGHT.  MORE INFO AND PICTURES WILL FOLLOW AS IT BECOME AVAILABLE	.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2005021400219	20050214	00219	EA  	2005	2	14	CA041129001      	1	20041128	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) THE LT SIDE WINDOW CRACKED WHILE IN APPROACH. VSB CSB-NP-139322 WAS PERORMED ON NOV 2003.  WINDOW WAS REPLACED IAW	 AMM.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005031100104	20050311	00104	EA  	2005	3	11	CA041129002      	1	20041123	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) THE RT SIDE WINDOW CRACKED WHILE IN CRUISE.  A NEW WINDOW WAS INSTALLED AS IAW AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005031100106	20050311	00106	CE  	2005	3	11	CA041129004      	1	20041001	G	7921		VALVE           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	OIL COOLER	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 371 HOURS AFTER OVERHAUL.  METAL WAS OBSERVED IN THE OIL FILTER.  ENGINE REMOVED, DISMANTLED, AND INSPECTED.  CORR	OSION FOUND ON RODS AND CRANKSHAFT.  ENGINE APPEARED TO HAVE NEVER RUN WARM ENOUGH TO BURN THE WATER OUT OF THE OIL.  LA	CK OF ANY MARKS ON THE VERNATHERM VALVE CONFIRMS THE VALVE NEVER CLOSED TO ROUTE OIL TO COOLER.  AIRCRAFT TEST FLOWN AFT	ER REPAIR.  OIL TEMP GAUGE READ 160 DEG IN CRUISE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2005031100015	20050311	00015	NE  	2005	3	11	CA041129005      	2	20041129	G	7314	350880	SHAFT           	PWA         		BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					PUMP	SHEARED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			31526								(CAN) IMMEDIATELY AFTER 500FT, R PRIM PUMP EICAS MSG, STATUS QTY/PX NML. CLIMBING OUT, R QTY DECREASED STEADILY TO ZERO 	BUT PX NML W/DEMAND PUMP IN AUTO.  CKD DEMAND PUMP OFF AND SYS PX WRNG LT DEMAND PUMP AUTO AND RETURNED TO DEPARTURE.  F	OUND RT EDP LEAKING INTERNALLY, RT EDP RPLD DUE DRIVE SHEARED.  PX AND CASE DRAIN FILTERS CONTAMINATED SAME, REPLACED PU	RCHASED, PO 19E823411.  RT RESERVOIR DRAINED/REFILLED 9 USG, EGR  C/OUT LEAK CKD SATISFACTORY.			2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2005031100024	20050311	00024		2005	3	11	CA041129006      	4	20041129	G	2330	7002061002	MONITOR         			AIRBUS	330   	A330300     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					ROW 12 A,B	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) APPROX 30 MINUTES AFTER TAKEOFF, PAX IN 12B,C NOTICED A BURNING SMELL IN OVERHEAD BIN.  (THERE WAS A BANGING SOUND	 AT TAKEOFF APPARENTLY) ALSO NOTICED WERE SMALL PUFF OF SMOKE COMING FROM VENT ABOVE THE PAX IN 12 A,C (A COUPLE OF TIME	S) SMOKE SMELL WAS CONFIRMED FROM CREW.  RETURNED.  FOUND VIDEO MONITOR AT SEAT 12 A,C SMELLING OF SMOKE.  MONITOR REMOV	ED AND CONNECTORS CAPPED.  SEE SNAGL1443368, MONITOR REPLACED AND CHECKS OK.			2	L	7	2 	4F	4	F	RT	        	E39NE
2005031100025	20050311	00025	NM  	2005	3	11	CA041129007      	1	20041129	G	7312	702101601425	FUEL HEATER     			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT ENGINE	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) MIDWAY THROUGH THE FLT, THE LT ENG OIL QTY BEGAN TO DECREASE AT THE RATE OF APPROX 1 LITRE EVERY 10 -15 MINUTES.  	LT ENG THRUST REDUCED OIL QTY STILL DECREASED TO ZERO OIL PRESS AND TEMP REMAINED NORMAL ACTION: REPLACED SERVO FUEL HEA	TER IAW MM 73-11-09.				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
2004121000022	20041210	00022	NM  	2004	12	10	CA041129008      	1	20041126	G	3233	651781914	ACTUATOR        			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) NOSE WHEEL DISAGREEMENT LIGHT REMAINED ON AFTER GEAR SELECTED UP.  RETURNED TO FIELD.  NOSE GEAR LOCK ACTUATOR REP	LACED, AND GEAR SWINGS C/O.  CHECKED SERVICEABLE. TIMES- 59932:32  CYCLES- 55882.					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041900015	20050419	00015	NE  	2005	4	19	CA041129009      	2	20041129	G	7200		ENGINE          			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LEFT	SURGES          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) LOUD BANG AND YAW FELT AT CLIMB THRUST 7000 FT , RETURNED.  ADDED MAINTENANCE INFO, LT ENG SURGE DET. MSG91827. LA	NDING SMOOTH.  91827.(SIC)  ACTION: DFDR CHANGED. REPLACED EVBC IAW MM-75-31-01. ENG. BOROSCOPE CARRIED OUT. NO FAULTS. 	ENG. TEST 8, 9 AND 10 CARRIED OUT NO FAULTS. CONS. SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2004121000059	20041210	00059	NM  	2004	12	10	CA041129010      	1	20041128	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) FUSELAGE CRACK FOUND ON OUTER SKIN AT STN. 955.9 - 959.65 BELOW STR. 21L. FUSELAGE CRACK REPAIRED IAW SRM 53-30-3 	FIG 48 DETAIL X. TIMES- 64477:16					2	L	7	2 	4F	4	F		A16WE   	E2EA
2005020100108	20050201	00108	CE  	2005	2	1	CA041129011      	1	20041127	G	2752	C3010020211	COUPLING        	CESSNA      		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ACTUATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STUDENT AND INSTRUCTOR WERE PERFORMING A WALK AROUND OF THE AIRCRAFT BEFORE GOING FOR A LESSON.  STUDENT SELECTED 	FLAPS DOWN THEY STARTED TO GO DOWN THEN THE FLAPS STOPPED MOVING BUT THE MOTOR KEPT RUNNING.  FLAP MOTOR WAS REMOVED AND	 IT WAS FOUND THAT THE COUPLING BETWEEN THE MOTOR AND THE ACTUATOR HAD BROKEN.  NEW COUPLING WAS INSTALLED AND THE FLAPS	 WORKED CORRECTLY.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005031400037	20050314	00037	SO  	2005	3	14	CA041129012      	1	20041109	G	2820	8004804	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AIRCRAFT ON TRAINING FLIGHT.  PILOT REPORTS STRONG FUEL ODOR IN COCKPIT. INVESTIGATION REVEALED LT FUEL PRESSURE F	LEXIBLE HOSE TO GAUGE LEAKING FROM UNDER HOSE FITTING SOCKET WHEN FUEL BOOST PUMP TURNED ON. THIS FUEL LEAK WAS A FINE M	IST SPRAY.  HOSES WERE DRY AND HARDENED DUE TO AGE.  REPLACED ALL FLEXIBLE RUBBER HOSES TO LT AND RT GAUGES.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2004121000060	20041210	00060		2004	12	10	CA041129013      	4	20041125	G	3418	861DL	SENSOR          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ANGLE OF ATTACK	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) NOV 25TH 2004, AIRCRAFT HAD A  STALL COMPUTER FAULT, MFDU MESSAGE ON TAKEOFF ROLL.  REJECTED THE TAKEOFF AT 90 KTS	 INDICATED.  A DMI (DEFERRED MAINTENANCE ITEM) 14809 WAS RAISED IAW MEL 27-35-3, FOR A STALL WARNING COMPUTER TO BE REPL	ACED, IT WAS REPLACED NOV 26TH ALONG WITH AN AOA VANE REPLACED IAW AMM.				2	L	7	2 	4F	4	F	RT	        	E25NE
2005020100111	20050201	00111	EA  	2005	2	1	CA041129014      	1	20041129	G	2913	848847	PUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYDRAULIC SYS	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FAULT: ON CLIMB OUT MSP, CREW RECEIVED PAX DR HANDLE LATCH MSG, FOLLOWED BY HYD SYS 3 LOW PRESS.  MSG FOLLOWED BY 	PAX DR WARNING MSG. ON AIR RETURN, ON APPROACH FLT, RECEIVED GEAR DISAGREE MSG AND CARRIED OUT MNL EXTENSION.  FOUND LIN	E LEAKING ON PUMP 3B.  FOUND CASE CRACKED ON PUMP 3A. REPLACED BOTH 3A AND 3B HYD. PUMP REPLACED PRESS/RETURN AND CASE D	RAIN FILTERS SYS. 3.  REPLACED HYD. LINE ON PULSE DAMPENER PUMP 3B. HYD SYST. SERVICED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2004121000062	20041210	00062	WP  	2004	12	10	CA041129015      	1	20041125	G	2410		CSD             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					GENERATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE LEFT CSD LOW OIL PRESSURE LIGHT CAME ON IN FLIGHT. CSD DISCONNECTED PER QRH . AIRCRAFT DIVERTED. A DMI (DEFERR	ED MAINTENANCE ITEM)  08580 WAS RAISED IAW MEL 24-1-1.  MAINTENANCE LATER REPLACED THE CSD AND THE CSD OIL COOLER.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005012400015	20050124	00015	SW  	2005	1	24	CA041129016      	1	20041129	G	1430	AN45A	BOLT            			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	VERTICAL STAB	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE IB FORWARD AUX FIN ATTACH BOLT WAS FOUND SHEARED AT THE HEAD.  IT APPEARS THAT THE FI	N WAS INSTALLED WITH A PRE LOAD CAUSING THE BOLT TO FAIL.  SUB-CONTRACTOR HAS BEEN NOTIFIED OF THIS OCCURRENCE AND IS CU	RRENTLY INVESTIGATING THE REQUIREMENT FOR A SHIM INSTALLATION.  THE REMAINING ATTACH BOLTS WILL BE REMOVED FOR NDT INSPE	CTION TO ENSURE THE SERVICEABILITY OF THE BOLTS PRIOR TO RE-INSTALLATION.			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL
2004121000063	20041210	00063	GL  	2004	12	10	CA041129017      	2	20041121	G	7240	6870992C	COMBUSTION LINER			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE PILOTS WERE DOING TRAINING, THEY NOTICED AN INCREASE IN TOT.  DID A POWER CHECK AND FOUND THAT THE ENGINE WAS 	BELOW SPEC.  AIRCRAFT RETURNED TO BASE AND IT WAS DISCOVERED THAT THE THERE WAS A 1 INCH CRACK THAT FOLLOWED A WELD IN T	HE E ARM PIT AREA. NOTE: IN THIS REGION THERE IS A MESHED DOUBLER.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2004121000023	20041210	00023	EA  	2004	12	10	CA041129018      	2	20041126	G	7310		MANIFOLD        								PWA   	PT6   	PT6A27      	52043	EA  					FUEL SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFTER REPLACING A SET OF FUEL MANIFOLD ADAPTERS ON A PT6A-27 ENG, A GROUND RUN WAS CARRIED OUT. THE RESULTING GROU	ND RUN SHOWED SIGNS OF FUEL LEAKAGE FROM THE TRANSFER TUBES P/N 3011155.ENGINE PERFORMANCE DATA SHOWED THAT THE T5 TEMPE	RATURE AND FUEL FLOW NUMBERS WERE HIGHER THAN BEFORE REPLACEMENT.  AFTER FURTHER TROUBLESHOOTING AND GROUND RUNS, THE T5	 AND WF REMAINED ABOVE TARGET LIMIT ONDATA PLATE SPEED RUNS. AFTER DOUBLE CHECKING CALIBRATION OF THE T5 TEMPERATURE SYS	TEM AND TORQUE INDICATION SYSTEM, ANOTHER SET OF GROUND RUNS WERE CARRIED OUT.  THE RESULTS SHOWED CONTINUED HIGH T5 AND	 HIGHFUEL FLOW.THE ENGINE WAS THENSPLIT AT THE 'C' FLANGE AND A HOT SECTION INSPECTION CARRIED OUT.						4	T			E4EA
2005020100072	20050201	00072	CE  	2005	2	1	CA041130001      	1	20041128	G	2130	CM357024	COUPLER         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN PRESSURE	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COUPLING DISCONNECTED WHEN AIRCRAFT WAS AT FLIGHT LEVEL AND AIRCRAFT AT A OPERATING CABIN PRESSURE ALTITUDE. AIRCR	AFT CABIN LOST PRESSURIZATION.					1	L	7	2 	4F	4	F		A22CE   	E1NE
2004121000025	20041210	00025	NM  	2004	12	10	CA041130002      	1	20041117	G	5512	653120043	PANEL           			BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					HORIZONTAL STAB	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			71148								(CAN) RT HORIZONTAL STABILIZER-TO-FIN SLIDING SEAL SEPARATED FROM AIRCRAFT DURING FLIGHT.  DAMAGE WAS ALSO FOUND ON AN A	DJACENT COMPOSITE VERTICAL FIN PANEL AND THE LOWER SURFACE OF THE HORIZONTAL STABILIZER, CAUSED BY SEPARATION OF THE SLI	DING SEAL FROM THE AIRCRAFT.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005031100105	20050311	00105	EA  	2005	3	11	CA041130003      	1	20041112	G	3222	162005	BEARING         	MENASCO     		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT ON DEPARTURE RETRACT, THE GEAR WOULD NOT RETRACT. POSITION INDICATION LIGHTS REMAINED GREEN AND THE G	EAR SELECTOR LEVER WAS ILLUMINATED AND REMAINED SO. NO CIRCUIT BREAKERS WERE TRIPPED ON THE FLIGHT DECK. THE AIRCRAFT LA	NDED WITHOUT INCIDENT, THERE WAS NO INJUURY TO PASSENGERS OR FLIGHT CREW. THE AIRCRAFT WAS FERRIED FOR REPAIRS, ALL NOSE	 AND MAIN WEIGHT SWITCHES WERE CHECKED, ALL WIRING FOR THE LANDING GEAR SYSTEM WAS CHECKED INC WITH MFG WIRING MANUAL 32	-00-00, NO FAULT FOUND. LANDING GEAR RETRACTIONS AND EXTENSIONS CARRIED OUT, FIVE TIMES BUT COULD NOT GET FAULT TO REPEA	T ITSELF.  DECIDED TO REPLACE ALL MAIN LANDING GEAR WEIGHT SWITCHES, AS A PRECAUTION, P/N 21HE23RB, QTY 4.	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
2005020100073	20050201	00073	CE  	2005	2	1	CA041130004      	1	20041116	G	7931	040031178	LINE            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	OIL PRESS	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE OIL PRESSURE LINE UNDER THE INSTRUMENT PANEL WAS CHAFED AGAINST THE CABIN HEATER CONTROL CABLE.  WE REPLACED T	HE PRESSURE LINE AND INSTALLED IT CORRECTLY.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
2004121000026	20041210	00026	GL  	2004	12	10	CA041130005      	2	20040930	G	7230	230397911	COUPLING        	RROYCE      		AGUSTA	A109  	A109        	0260109	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	SHEARED         	W				B				EMER. DESCENT           				W	Y	M	INADEQUATE Q C            	ENGINE STOPPAGE           	OVER TEMP                 	CR	CRUISE         	1			CA						CAC39323					(CAN) AFTER FRETTING WEAR OVER PILOT OUTSIDE DIA, THE ADAPTER COUPLING SHEARED IN T (TWO) PARTS. REFERENCES: CEB A-1392 	FROM CEB 250-C20 SERIES.					1	G	7	2 	3U	3	U		H7EU    	E4CE
2005020100122	20050201	00122	GL  	2005	2	1	CA041130006      	1	20041113	G	2752		SEAL            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN)A/C HAD FLAP STUCK FULL DOWN. INSP REVEALED FLAP ACT SEAL HAD COME LOOSE, INTERFERED WITH NR 5 FLAP SWITCH.  WILL T	AKE ACTUATOR FROM OTHER AC TO USE ON THIS A/C.  INSP REVEALED THAT SEAL ON OTHER A/C HAD COME LOOSE TOO, BUT HAD NOT YET	 CONTACTED SWITCHES, PROCEEDED TO RE-GLUE SEAL IAW INSTRUCTIONS  INSTALLED UNIT ON THIS A/C.  UNIT WHICH WAS REMOVED FRO	M MFB WAS FURTHER INSPECTED, SEAL RE-GLUED, TAB OF NR 5 SWITCH WAS STRAIGHTENED, UNIT INSTALLED IN OTHER A/C, GROUND TES	TED SERVICEABLE.		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2005031400044	20050314	00044	GL  	2005	3	14	CA041130007      	1	20041113	G	2752		SEAL            	DIAMON      	222750010   	DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC HAD THE FLAP STUCK FULL DOWN. INSP REVEALED THAT FLAP ACTUATOR SEAL HAD COME LOOSE AND INTERFERED WITH THE NR5 	FLAP SWITCH. A/C WAS IN MAINT FOR A TOTALLY UNRELATED DEFECT, TROUBLESHOOTING DECIDED, THAT WE TAKE THE ACTUATOR FROM IT	 TO USE ON A/C. INSP REVEALED THAT THE SEAL ON A/C HAD COME LOOSE TOO, BUT HAD NOT YET CONTACTED THE SWITCHES AND THEREF	ORE WE RE-GLUED SEAL IAW MFG INSTRUCTIONS AND INSTALLED THIS UNIT ON MFB. THEREAFTER UNIT WHICH WAS REMOVED FROM MFB WAS	 FURTHER INSPECTED, SEAL RE-GLUED AND TAB OF NR5 SWITCH WAS STRAIGHTENED.  UNIT INSTALLED IN OTHER A/C AND GROUND TESTED	 SERVICEABLE.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2005041900016	20050419	00016	GL  	2005	4	19	CA041130008      	1	20041126	G	2752		SEAL            	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FLAP ACTUATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WITH FLAPS STUCK AT LANDING POSITION DURING WALK AROUND. INSPECTION REVEALED ANOTHER FLAP ACTUATOR SEAL SEPARATION.  A/C	 HAD JUST UNDERGONE A 200 HR INSPECTION AT WHICH TIME SEAL INSPECTED & FOUND TO BE IN PLACE. SEAL AREA IS COVED BY A COM	POSITE COVER WHICH IS SOMEWHAT SEE THROUGH BUT DOES NOT ALLOW FOR A PHYSICAL CHECK OF SEAL POSITION ONLY A VISUAL.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH
2005041900017	20050419	00017	NE  	2005	4	19	CA041130009      	2	20041126	G	7250		RIVET           								PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								PS114139			A FIELD SERVICE REPRESENTATIVE WAS SERVICING THE POWER SECTION WHEN HE NOTICED A LOOSE NR 3 BEARING COVER.  THE LOOSE BE	ARING COVER HAD COME INTO CONTACT WITH THE 2ND STAGE PT DISK, RENDERING IT SCRAP.  THE BEARING COVER LOCATES IN THE PT S	HAFT HOUSING USING 6 LOCATING LUGS (P/N 3030491) AND 6 RIVETS (P/N AN123318).  FIVE OF THE 6 RIVETS WERE SHEARED.  THE R	IVETS HAVE BEEN IN SERVICE FOR AT LEAST 5034 HOURS AND POSSIBLE AS HIGH AS 12757 HOURS.								4	T			E26NE
2005020100097	20050201	00097	WP  	2005	2	1	CA041130010      	1	20041128	G	2611		WARNING LIGHT   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CABIN SMOKE	ILLUMINATED     	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) TAXIING FOR DEPARTURE, ANNOUNCEMENT TO DIM CABIN LIGHTS, ROWS 10 TO 11 STARTED TO PUSH CALL BUTTONS TO INDICATE SM	OKE IN THAT AREA. CREW COULD NOT LOCATE SOURCE OF SMOKE. FLIGHT CREW DECLARED EMERGENCY EVACUATION.  MAINT INSPECTED FOL	LOWING; CABIN LIGHTING, CEILING PANEL IN FWD AREA WAS LOWERED IN ORDER TO INSPECT CB AND TRANSFORMERS, AISLE CEILING LIG	HT (IN FWD AREA) SOCKET AND BALLAST, UPPER SIDEWALL LAMP SOCKETS ROWS 1 TO 12 LT AND RT WERE INSPECTED FOR EVIDENCE OF A	RCING. REPLACED 2 BALLASTS AT SEAT ROWS 16L, 18R (AS THEY WERE FOUND INOP, NO SIGNS OF ARCING OR BURNING). INSPECTED CAR	GO COMPARTMENTS.  RECIRCULATION FAN. APU OIL QUANTITY. APU ENGINE RUN C/OUT. NO FAULTS WERE FOUND.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005020100099	20050201	00099	CE  	2005	2	1	CA041130011      	1	20041122	G	2410	AC2101	CONTROL UNIT    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ALTERNATOR	FAILED          	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) ALTERNATOR FIELD C/B TRIPPED WHEN ALTERNATOR TURNED ON.  ZERO VOLTS FOUND AT ALT FIELD TERMINAL.  REPLACED ALTERNA	TOR CONTROL RELAY, NO CHANGE.  REPLACED ALTERNATOR CONTROL UNIT, VOLTAGE AT FIELD TERMINAL OF ALTERNATOR.  ALTERNATOR FU	NCTIONING NORMALLY DURING GROUND RUNUP.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA
2005020100090	20050201	00090	CE  	2005	2	1	CA041130012      	1	20041129	G	2435	23048018	STARTER GEN     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	LEFT	FAILED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT AT 12000 FEET THE PILOTS NOTICED THE LT GENERATOR FAIL LIGHT CAME ON.  ALSO A PASSENGER INDIC	ATED THAT HE NOTICED SPARKS COMING FROM THE ENGINE. THE GENERATOR WAS SELECTED OFF AND AIRCRAFT RETURNED TO BASE FOR INS	PECTION.  MAINTENANCE INSPECTED THE AIRCRAFT AND NOTICED THAT THE REAR BEARING IN THE STARTER GENERATOR HAD FAILED CAUSI	NG IT TO SELF-DESTRUCT.  THE GENERATOR WAS REPLACED, ENGINE WAS INSPECTED FOR DAMAGED AND AIRCRAFT WAS RETURNED TO SERVI	CE.		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA
2005020100144	20050201	00144	NE  	2005	2	1	CA041201002      	1	20041130	G	5314	7620202003101	KEELBEAM        			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11167								(CAN) KEELBEAM LOWER CONDUIT IS A BOX SECTION EXTRUSION WHICH RUNS FROM STA 188 TO STA 255.  IT IS LOCATED ON FUSELAGE T	UBE IN BETWEEN TWO FUEL CELLS. SIX HYDRAULIC TUBES ARE INSTALLED INSIDE CONDUIT AND ARE SECURED IN PLACE BY RUBBER BLOCK	S. MOISTURE IS INTRODUCED POSSIBLY THROUGH BLOCKS AND IS RETAINED IN THE EXTRUSION, CAUSING CORROSION, ALMOST TO POINT O	F PERFORATION.  LT UNCHECKED THIS WOULD RESULT IN FUEL LEAKS FROM INTEGRAL TANKS. THE INTERNAL CORROSION BUILD UP WAS SO	 SEVERE THAT HYDRAULIC TUBES COULD NOT BE REMOVED BY NORMAL MEANS AND WERE DESTROYED IN REMOVAL.  ONCE INITIATED, CORROS	ION GROWTH APPEARS TO BE RAPID. RECOMMEND A PERIODIC INSPECTION OF THIS AREA WITH THE YEARLY CALENDAR INSPECTION.	1	G	7	2 	3U				H1NE
2005020100075	20050201	00075	EU  	2005	2	1	CA041201003      	1	20041128	G	3211	5531012326	ATTACH BRACKET  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION, A CRACK WAS FOUND ON THE BRACKET WHICH ATTACHES THE NOSE GEAR ACTUATOR TO THE AIRFRA	ME.  THE SUPPORT, PN 553.10.12.326 WAS ORDERED AND IS CURRENTLY BEING REPLACED.  OTHER AIRCRAFT IN OUR OWN FLEET WERE IN	SPECTED AS WELL WITH NO DEFECTS FOUND.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE
2005041900018	20050419	00018	WP  	2005	4	19	CA041202001      	2	20041201	G	7250		RIVET           								GARRTT	TPE331	TPE33110UA  	01514	WP  					TURBINE WHEEL	SEPARATED       	W				K				NONE                    				D	C		INFLIGHT SEPARATION       	F.O.D.                    		IN	INSP/MAINT     	1			CA								P54214			UPON A REGULARLY SCHEDULED HOT SECTION INSPECTION THE NR 2 TURBINE WHEEL WAS FOUND TO HAVE A RIVET MISSING AT THE BASE O	F ONE OF THE TURBINE BLADES.  THIS RIVET INSTALLATION IS FOR EXPANSION PURPOSES.  THE 3RD STAGE TURBINE AND STATOR ASSY 	WAS FOUND DAMAGED FROM THIS RIVET AS IT PASSED THROUGH IT AFTER DISLODGING FROM THE NR 2 TURBINE.  OUR COMPANY TURBINE S	HOP MANAGER HAS WITNESSED THIS SAME PROBLEM SEVERAL TIMES IN THE PAST.								4	T			E4WE
2005020100087	20050201	00087	NM  	2005	2	1	CA041202002      	1	20041202	G	3234	114079016	SELECTOR VALVE  			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FAULT: AFTER T/O AND GEAR UP, NR 1 LGCIU ECAM MSG ON.  ALSO DURING A GO-AROUND AFTER GEAR SELECTED UP, MASTER (RED	) WARNING CAME ON WITH MSG. (GEAR DISAGREEMENT) DURING APROX. 10 SEC.ACTION:  MLG DOOR SEL VALVE REPLACED IAW MM 32-31-3	4. FUNCTIONAL CHECK CARRIED OUT OK, LEAK CHECK C/OUT SERVICE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005012400026	20050124	00026	CE  	2005	1	24	CA041202003      	1	20041202	G	2434	66082019	GENERATOR       			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT DC	FAILED          	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) RT DC GENERATOR FAILED.  SMOKE NOTICED IN THE CABIN BY PASSENGER.						2	L	7	2 	4F	4	F		A10CE   	E6WE
2005012400027	20050124	00027	CE  	2005	1	24	CA041202004      	1	20041126	G	2710	666000163	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					LT OB AILERON	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DUE TO THE RISK ASSOCIATED TO BROKEN MAIN CONTROL CABLES, FOLLOWING THE BROKEN RT WING DOWN OB AILERON CABLE P/N 6	660001-62 AT RWS 54  (REF. SDR NR 20031113014), WE DECIDED TO INSPECT THE AILERON WING CABLES MORE FREQUENTLY THAN THE 1	200 HRS REQUIRED BY THE PHASE 61.  LT WING UP OB AILERON CABLE P/N 6660001-63 WAS FOUND WORN AT LWS 54 AND LWS 78 WITH B	ROKEN STRANDS AT LWS 54 ONLY. THE CABLE WAS ORDERED AOG AND INSTALLED THE CABLE WAS REPLACED ON LAST PHASE 51 INSPECTION	 (NOW PHASE 61) HAS BEEN NOTIFIED. UNTIL MFG COMES WITH A NEW FREQUENCY INSPECTION WE ARE LOWERING THE INTERVAL INSPECTI	ON AT 500 FLIGHT HOURS.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2005012400028	20050124	00028	SW  	2005	1	24	CA041202005      	1	20041202	G	1430	AN6C13A	BOLT            			AIRTRC	AT802 	AT802A      	0390308	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 STABILIZER STRUT ATTACH BOLTS WERE REMOVED FOR INSPECTION. THE LOWER RH BO	LT WAS SUSPECTED OF BEING CRACKED.  THE BOLT WAS LPI INSPECTED AND THE CRACK WAS VERIFIED.  ALL AIRCRAFT IN OUR FLEET WI	LL HAVE THE BOLTS INSPECTED USING THE LPI METHOD. WE WILL REPORT ANY FURTHER FINDINGS OF CRACKS.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL
2005020100017	20050201	00017	EU  	2005	2	1	CA041202006      	2	20041202	G	7200		ENGINE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RIGHT	FAILED          	W				A				UNSCHED LANDING         				X	P		ENGINE FLAMEOUT           	NO WARNING INDICATION     		CR	CRUISE         	1			CA											(CAN) AC WAS ENROUTE, WHILE IN CRUISE THE AC YAWED TO THE RT AND THE STBD ENGINE SPOOLED DOWN.  IN-FLIGHT SHUTDOWN PROCE	DURE WAS CARRIED OUT AND THE AC RETURNED, WHERE AN UNEVENTFULL LANDING WAS MADE. UNTIL THE ENGINE SHUT DOWN, OPERATING I	NDICATION WERE NORMAL. MAINTENANCE INSPECTION REVEALED HEAVY STEEL CONTAMINATION OF THE OIL FILTERS, INCLUDING A COMPLET	E CROWN FROM A GEAR WHEEL. INITIAL INVESTIGATION INDICATES THE PROPELLER GEAR BOX FAILED.THIS ENGINE IS DUE FOR OVERHAUL	 AND THE ENSUING STRIP REPORT WILL FURNISH A MORE IN DEPTH REPORT.		2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899
2005012400029	20050124	00029	EA  	2005	1	24	CA041203001      	1	20041203	G	2897		WIRE            			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	LT WING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION ( B CHECK ), FOUND JUST ABOVE THE PRESSURE REFUELLING LINE, LOCATED ON LT WING W/S 196 (ACCES	S PANEL 541-5), AN ELECTRIC WIRE, THAT GOES TO THE FUEL DRAIN SOLENOID VALVE, CHAFED. IT DID CAUSE AN ARCING.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE
2005020100018	20050201	00018	NM  	2005	2	1	CA041203002      	1	20041203	G	3251	C24736001	CONTROL VALVE   			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  					NLG STEERING	INOPERATIVE     	W				O				OTHER                   				L			NO TEST                   			CR	CRUISE         	1			CA			33284	19954							(CAN) IN CRUISE, WHEEL  NOSE WHEEL STEERING FAULT . TRIED RESET ANTI-SKID /NW STEERING SWNO FIX. NO NW STEERING ON LANDI	NG. TOWED TO GATE.  TESTED BSCU 1 AND 2 FAULTED NLG STEERING SERVO FTN 6GC.   IAW TSM AND AMM REPLACED NLG STEERING SERV	O FTN 6GC.  OPERATION TEST PERFORMED BSCU 1 AND 2 TESTED, NO FAULTS.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005041900019	20050419	00019	SW  	2005	4	19	CA041203003      	1	20041202	G	2150	35BD219DUM	BEARING         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TRANSMISSION	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA						21					(CAN) IN FLIGHT NOISE WAS HEARD AND SMALL AIRFRAME VIBRATION. A/C LANDED AS PRECAUTION AT AIRPORT. AIRCRAFT INSPECTED AN	D PROBLEM NOT DETECTED. COULD NOT DUPLICATE NO ISE OR VIBRATION. A/C FLOWN TO BASE AIRPORT. UPON FURTHER INVESTIGATION B	EARING IN SPEED REDUCER FOUND FAILED DAMAGE LIMITED TO BEARING.				1	G	7	2 	4U	4	U		H4SW    	E22EA
2005041900020	20050419	00020	EU  	2005	4	19	CA041203004      	1	20041202	G	2430	U37151	CONTROL UNIT    			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					VOLT PROTECTION	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON 2/12/04, AT 22:30 THE A/C WAS IN CLIMB OUT OF YYQ. SMOKE AND FUMES WERE NOTED IN THE CABIN, AND SUBSEQUENTLY IN	 THE COCKPIT. AN UNEVENTFULL LANDING WAS MADE. THERE WERE NO ABNORMAL INSTRUMENT INDICATIONS DURING THIS OCCURRENCE. MAI	NTENANCE INVESTIGATION REVEALED THE PORT ALTERNATOR VOLTAGE CONTROL PROTECTION UNIT HAD FAILED. THE UNIT WAS REPLACED AN	D SYSTEM CHECKS SHOWED NORMAL OPERATION. WIRING HARNESSES WERE INSPECTED AND NO DETERIORATION WAS FOUND. THE A/C WAS REL	EASED TO SERVICE.		2	L	7	2 	3T	4	T		A24EU   	A196
2006061200431	20060612	00431		2006	6	12	CA041203005      	4	20041019	G	2562	BP1045	BATTERY         	EBC         		LAKEAC	LAKE  	250LAKE     	5110322	NE  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	ELT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						74739GA					UNDER MANUF INSPECTION AND RECERTIFICATION PROCESS, CANADIAN AIR MOTIVE FOUND ILLEGAL AND UNAPPROVED BATTERY PACK INSIDE	 ELT (NOT EXPIRED CONDITION AUG 2006).  AS PER EBC MANDATORY CLASS 1 SERVICE BULLETIN NO.: 8401, ONLY GS21 OR GS51 IS AP	PROVED FOR THIS ELT MODEL.  THIS SB 8401 IS IN CONFLICT WITH BATTERIES APPROVED BY TRANSPORT CANADA AND INDUSTRY CANADA 	(AIRWORTHINESS NOTICE NO.: B014 EDITION 5; 28 MARCH 2002).			1	H	7	1 	3O	3	O	NC	1A13    	1E4	5	C	P33EA
2005041900021	20050419	00021	NM  	2005	4	19	CA041203006      	1	20041128	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) AN OUTER FUSELAGE CRACK WAS FOUND AT STR 16 LT BETWEEN STA 767 & 787 APPROX 2 INCHES LONG. FUSELAGE CRACK REPAIRED	 IAW SRM 53-30-1 FIG.48 PROCEDURES I, IV & VII. THIS REPAIR IS TIME LIMITED UNTIL 25 FEB. 04. TIMES- 61761:52 CYCLES- 57	769.				2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041900022	20050419	00022	EU  	2005	4	19	CA041203007      	1	20041203	G	6730		LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLUID LEAK AT UPPER HOUSING SPLIT LINE.						1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041900023	20050419	00023	NM  	2005	4	19	CA041203008      	1	20041201	G	3897		WIRE            			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					POT WATER TANK	ARCED           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE POTABLE WATER INDICATION BECAME INOPERATIVE AND WAS DEFERRED. TROUBLESHOOTING FOUND WIRES IN THE AREA NEAR THE	 WATER TANK ON A BELLY STRINGER AT STN 960 TO BE BURNED BY ARCING. WIRES AFFECTED WERE POTABLE WATER INDICATION, R2 DOOR	 WARNING LIGHT AND LAV DUMP GASKET HEATER. THE AREA WAS WET FROM CONDENSATION WHICH HELPED TO PROMOTE THE ARCING. THE WI	RES WERE REPAIRED PER AMM.			2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041900024	20050419	00024	NM  	2005	4	19	CA041206001      	1	20041204	G	2612	10109601	FIRE LOOP       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AN AIRCRAFT EXPERIENCED A NR 2 ENGINE FIRE WARNING IN FLT. CREW SHUT ENGINE DOWN AND FIRE WARNING CEASED. FIRE BOT	TLES NOT DISCHARGED. A/C LANDED ON NR 1 ENGINE SATISFACTORILY.  A/C NOT DIVERTED FROM ORIGINAL DESTINATION. FULL EMERGEN	CY DECLARED.INITIAL INSPECTION REVEALS NO FUEL, OIL OR AIR LEAKS AND THERE IS NO PHYSICAL DAMAGE APPARENT.  PEC LOOP REM	OVED. BOTH ITEMS HAVE A P/N 10-1096-01 WHICH IAW IPC 26-11-03-01 ITEM 30, IS POST SB 84-26-03.  A/C HAS COMPLETED ENGINE	 RUNS WITH BLEED AIR BOTH OFF AND ON, AFTER PEC LOOP REPLACEMENT. ALL IS OPERATING CORRECTLY. AIRCRAFT HAS BEEN SIGNED U	P AS SERVICEABLEAND IS BACK INTO SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN
2005041900025	20050419	00025	EU  	2005	4	19	CA041206002      	1	20041206	G	7931	41SG3811	TRANSMITTER     			AIRBUS	A321  	A321211     	3930370	EU  	CFMINT	CFM56 	CFM563B1US  	 	GL  					ENGINE OIL	FLUCTUATES      	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE WE HAD TO SLOW DOWN OIL PRESS NR 2 FLASHED GREEN 14 PSI. HAD SOME POWER THE PRESSURE FLUCTUATED BETWEEN 	18-19 PSI WHEN POWER WAS SELECTED TOWARD IDLE OIL PRESSURE WENT TO 10 PSI (RED). WE KEPT THE POWER UP DURING DECENT AND 	APPROACH. REPLACED OIL PRESS. TRANSMITTER. OPERATIONAL CHECK CARRIED OUT AT IDLE AND HIGH POWER OIL PRESSURE NORMAL. LEA	K CHECK CARRIED OUT, NIL LEAKS.			2	L	7	2 	4F	4	F	RT	A28NM   	E2GL
2005041900026	20050419	00026	NE  	2005	4	19	CA041206003      	2	20041202	G	7200		ENGINE          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BOTH	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								JA03070308			(CAN) AT 15,000 FT IN LEVEL FLIGHT BOTH ENGINES EXPERIENCED A SIMULTANEOUS, UNCOMMAMDED, PARTIAL POWER ROLL-BACK.  THE A	IRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT GROUND RUNS WERE UNABLE TO DUPLICATE THE EVENT.  AIRFRAME CONTROL CA	BLES AND ENGINE BOV ACTUATOR RODS WERE FOUND MISRIGGED AND CORRECTED.  PWC WILL IN VESTIGATE TO ESTABLISH ROOT CAUSE AND	 WILL AMEND THIS REPORT TO REFLECT SAME, ONCE AVAILABLE.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA
2005041900027	20050419	00027	SO  	2005	4	19	CA041206004      	1	20041203	G	2410	ALT8421R	ALTERNATOR      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	SEIZED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) ON A FLIGHT,  PILOT NOTIED RH ALT OUT LIGHT CAME ON. PILOT CONTINUED FLIGHT AIRPORT. MAINTENANCE THE NEXT MORNING 	NOTICED THAT THE RT ALTERNATOR BELT HAD BROKEN AND THAT THE ALTERNATOR WAS SEIZED. ALTERNATOR WAS REMOVED AND DISSASSEMB	LED FRONT AND REAR BEARINGS WERE DESTROYED AND BRUSH HOLDER WAS DAMAGED.				1	L	7	2 	3O	3	O		A20SO   	E14EA
2005041900028	20050419	00028	EA  	2005	4	19	CA041206005      	1	20041206	G	3246	C6FSM225627	PLATE           			DHAV  	DHC6  	DHC6300     	2802606	EA  										FUSELAGE	MISDRILLED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MAIN BOLT AND SPIGOT HOLES ARE DRILLED APPROXIMATELY 0.250 INCHES TOO FAR AFT WHICH DOES NOT ALLOW MINIMUM EDGE DI	STANCE FOR THE AFT ROW OF RIVETS TO BE MAINTAINED.  ONLY PROVIDES 7/32' (0.21875') EDGE DISTANCE FOR A MS20470AD6 RIVET 	WHEREMINIMUM EDGE IS 3/8' (0.375').				1	H	7	2 	3T			RT	A9EA
2005041900029	20050419	00029	NE  	2005	4	19	CA041206006      	2	20041203	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MALFUNCTIONED   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA								114079			(CAN) ON APPRAOCH THE ENGINE EXPERIENCED A POWER LOSS ACCOMPANIED BY LOW OIL AND FUEL PRESSURE WARNINGS. THE AIRCRAFT LA	NDED AT POINT OF DESTINATION. THE EVENT WAS NOT REPRODUCED DURING SUBSEQUENT GROUND AND FLT TESTS.  THE FUEL CONTROL UNI	T HAS BEEN REPLACED.  PWC WILL MONITOR THE INVESTIGATION AND WILL AMEND THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERMIN	ED.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
2005041900030	20050419	00030	WP  	2005	4	19	CA041206007      	2	20041201	G	7321	8978015	FUEL CONTROL    			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA								P44722C			(CAN) UPON DESCENT FORM 25,000 FT THROUGH MODERATE TURBULENCE, THE LT ENGINE POWER WOULD NOT RETARD. THE POWER LEVER WAS	 MOVED FROM FULL POWER TO FLIGHT IDLE AND NO REPSONSE.  UPON REACHING 20,000 FT THE ENGINE BECAME RESPONSIVE AGAIN TO PO	WER LEVER MOVEMENT.  THE AIRCRAFT WAS RUN ON THE GROUND BY MAINTENANCE PERSONNEL AND NO FAULTS COULD BE FOUND.  IN DISCU	SSION WITH THE MANUFACTURER, MAINTENANCE ELECTED TO REPLACE THE THE P2T2 SENSOR.  GROUND RUNS CARRIED OUT ALL WITHIN MAN	UFACTURERS PARAMETERS AND AIRCRAFT RETURNED TO SERVICE.  SNAG AHS NOT DUPLICATED ITSELF AGAIN.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE
2005041200034	20050412	00034	CE  	2005	4	12	CA041206008      	1	20041130	G	5711	5011002611	SPAR            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			24431								(CAN) DURING LANDING PHASE AIRCRAFT ROLLED TO LT WHEN APPROACH FLAPS WERE SELECTED. ROLL RESPONSE WAS CORRECTED WITH AIL	ERON TRIM INPUT. FURTHER FLAP DEPLOYMENT DID NOT CREATE ANY FURTHER CONTROL DIFFICULTY.  MAINTENANCE INSPECTED AIRCRAFT 	AND DISCOVERED THAT THE RT OUTER FLAP WAS NOT SYMETRICAL TO OTHER FLAPS. THE IB FLAP HANGAR HAD CHANGED POSITIONS DUE TO	 A CRACK IN THE REAR SPAR WEB AT THE FLAP HANGAR ATTACH POINT.  SEVERAL OTHER ANGLES AND BRACKETS WERE ALSO BROKEN.  A R	EPAIR SCHEME WAS REQUESTED FROM MFG.		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2005041900031	20050419	00031	NM  	2005	4	19	CA041207001      	1	20041207	G	3397	2067081	CONNECTOR       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LIGHT	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) AN OPERATOR HAS FOUND BURNED PINS ON THE LT SIDEWALL LIGHTING CONNECTOR 3320-P39/J39. DUE TO THE PLUG DAMAGE THEY 	WILL REPLACE THE CONNECTOR AND THE BURNED PIN OR PINS SHOWING SIGNS OF OVERHEATING.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041900032	20050419	00032	SW  	2005	4	19	CA041207004      	1	20041206	G	6320	222040111101	SPLINE          	BELL        		BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					TRANSMISSION	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A54					(CAN) THE TRANSMISSION WAS IN FOR A HARD LANDING SUDDEN STOPPAGE INSPECTION AND EXCESSIVE WEAR WAS FOUND ON THE INTERNAL	 SPLINES OF THE GEARSHAFT AS WELL AS ON THE EXTERNAL SPLINES OF THE SUNGEAR.THE WEAR WAS NOT A RESULT OF THE HARD LANDIN	G.THIS IS THE SECOND TRANSMISSION IN THE LAST THREE MONTHS THAT HAS HAD THIS SAME PROBLEM.				1	G	7	2 	3U	3	U	RT	H9SW    	E1GL
2005041900033	20050419	00033	EU  	2005	4	19	CA041207005      	1	20041202	G	3810		LINE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					POTABLE WATER	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, CANNOT PRESSURIZE ACRFT. ACRFT RETURNED TO DEPARTURE AIRPORT.  MX FOUND CABIN AIR FILTER FOR OUTFLOW	 VALVES FULLY ICE COVERED DUE TO POTABLE WATER TANK LINE LEAKING AND DRIPPING OVER FILTER.  FILL WATER LINE FITTING AT T	HE TANK CONNECTION TIGHTENED & FILTER CLEANED.  SYSTEM TESTED AND ACRFT DISPATCHED SERVICEABLE. SAME PROBLEM OCCURRED 2 	DAYS LATER (UNABLE TO PRESSURIZE THE AIRCRAFT).  THE DRAIN WATER LINE FROM POTABLE WATER TANK FOUND LEAKING & WATER DID 	CONTAMINATE RT OUTFLOW VALVE, LT SECONDARY OUTFLOW VALVE & OUTLET VALVE FOR AVIONICS COOLING. WATER LINE TIGHTENED & WAT	ER TANK PRESSURIZED & CHECKED FOR LEAK.  ALL LISTED VALVES REPLACED & AIRCRAFT DISPATCHED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	        	E25NE
2005041900034	20050419	00034	NM  	2005	4	19	CA041208001      	1	20041201	G	3350	6104781	BATTERY PACK    			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	EMERGENCY LIGHT	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12160								(CAN) EMERGENCY LIGHT BATTERY PACK AT POSITION 3352-P2 WAS REMOVED DUE TO INOPERATIVE E-LIGHTS AT CEILING FIRST THREE PO	SITIONS.  DURING OVERHAUL OF THE BATTERY PACK IT WAS FOUND THAT THE PACK HAD SHORTED OUT.  IT APPEARS THAT DURING THE LA	ST CELL REPLACEMENT THE CONNECTION LEADS WERE CUT TO SHORT WHICH PREVENTED THE CORRECT ROUTING OF THE WIRES.  WHEN THE P	ACK WAS INSTALLED ON THE AIRCRAFT THE WIRES BE CAME PINCHED AND THE PACK SHORTED OUT.  THE PACK WAS INSTALLED ON NOVEMBE	R 08/04  & REMOVED FROM THE AIRCRAFT ON DECEMBER 01/04.  ALTHOUGH THE LAST DEEP CY CLE OCCURRED 140 HOURS PREVIOUS, IT I	S UNKNOWN WHEN THE LAST PACK OVERHAUL WITH CELL REPLACEMENT OCCURRED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041900035	20050419	00035	CE  	2005	4	19	CA041208002      	1	20041201	G	7500	12991003363	TUBE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	BLEED AIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSPECTING ONE OF THE FLEETS 1900D AIRCRAFT BLEED AIR TUBE PN 129-910033-63 FOUND TO BE CRACKED ALONG THE WE	LD. TIME OF THIS ACRFT 21,691.6 HOURS.  A PRECAUTIONARY INSPECTION WAS COMPLETED ON AN OTHER AIRCRAFT TOTAL TIME 6291.9.	 THE SAME PN TUBE WAS FOUND CRACKED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005071200026	20050712	00026	SW  	2005	7	12	CA041208003      	1	20041206	G	2810	412361639101	FUEL CELL       			BELL  	412   	412         	1182202	SW  										LT UPPER	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE TROUBLE SHOOTING A FUEL INDICATION PROBLEM, TWO RED PLASTIC PROTECTIVE CAPS WERE FOUND IN THE LT UPPER AFT T	ANK.					1	G	7	2 	4U				H4SW
2005041900036	20050419	00036	EU  	2005	4	19	CA041209001      	1	20041209	G	5310		STRUCTURE       			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	VIBRATION       	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) VERT SIGNIFICANT RUMBLE/VIBRATION DURING CLIMB AND CRUISE.  A/C ROUTED TO HANGAR FOR INVESTIGATION. NOTE: MORE INF	O. WILL FOLLOW AS BECOME AVAIL.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005041900037	20050419	00037	NE  	2005	4	19	CA041209002      	2	20041209	G	7200		ENGINE          			AIRBUS	A321  	A321211     	3930370	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  					NR 2	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								779274			(CAN)  THE CREW REJECTED TAKE-OFF AT A SPEED GREATER THAN 100 KNOTS. THE DECISION TO REJECT WAS A RESULT OF A NR 2 ENGIN	E ROLL BACK AFTER A N2 OVERSPEED. ACRFT RETURNED TO GATE. A/C OFFLINE FOR INVESTIGATION,  DFDR REMOVED FOR READOUT. NOTE	: MORE INFO WILL FOLLOW AS BECOME AVAIL.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005041900039	20050419	00039	NM  	2005	4	19	CA041209004      	1	20041207	G	5610	8SC0043014	WINDSHIELD      			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) SHORTLY FOLLOWING TAKE-OFF, IN THE CLIMB, AT 9000FT THE CO-PILOT'S WINDSHIELD CRACKED. THE CREW CARRIED OUT APPLIC	ABLE PROCEDURES AND LANDED SHORTLY AFTER. THE CO-PILOT'S WINDSHIELD WAS REPLACED AND THE AIRCRAFT WAS RETURNED BACK INTO	 SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005041900040	20050419	00040	EU  	2005	4	19	CA041209005      	1	20041208	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYDRAULIC SYS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED THAT CYCLIC WAS STIFF WHEN MOVED TO LEFT AND IT WANTED TO MOVE RIGHT WHEN COLLECTIVE LOWERED (NO PR	OBLEMS WHEN COLLECTIVE WAS RAISED).  LEFT MAIN SERVO WAS CHANGED AND DEFECT WAS CURED.					1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041900041	20050419	00041	SW  	2005	4	19	CA041209006      	1	20041124	G	5720	1701971	STRAP           			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE33110T   	 	WP  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REPLACEMENT OF LOWER SPAR CAP, WE WERE ADVISED THAT AN NEW AD IS PENDING AND WILL BE ISSUED IN JANUARY 2005	 TO ADDRESS A CORROSION PROBLEM WITH THE PART NUMBERS. THE STRAPS WERE REMOVED AND EXTENSIVE CORROSION WAS FOUND UNDER T	HE STEEL STRAPS ON THE UPPER WING SKIN. THIS IS BEING REPAIRED AS PER TWIN COMMANDER'SINSTRUCTIONS AT A TWIN COMMANDER S	ERVICE CENTRE.			1	H	7	2 	3T	4	T		2A4     	E4WE
2005041900043	20050419	00043	SW  	2005	4	19	CA041209007      	1	20041125	G	3244	AB3L6	TIRE            			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  					MLG	BLOWN           	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) LT MAIN TIRE WAS REPORTED TO ME AS THE D.M. TO BE FLAT. THE CREW WERE ON TAKEOFF WHEN THERE WAS SHAKING AND AIRCRA	FT VEERING TO THE LT.  THEY CONTINUED THE TAKEOFF AND MADE A LOW PASS BY THE FSS STATION FOR A VISUAL. IT WAS DETERMINED	 TO LAND WITH NO PROBLEMS. THE TIRE WAS INSTALLED ON THE ACRFT OCTOBER 13/04 AND HAS ACCUMULATED 162 HOURS. TIRE PRESSUE	S ARE CHECKED REGULARLY AND ON THAT PARTICULAR DAY. THE TIRES WERE CHECKED BY ME AND NO NICKS OR DAMAGE WAS NOTED. THIS 	TIRE PLY LOOKS AS IFIT WAS PULLED AWAY FROM THE STEEL BEAD.		1	L	7	2 	3O	3	O		A12SW   	E14EA
2005041900044	20050419	00044	GL  	2005	4	19	CA041209008      	2	20041119	G	7310	6875632	LINE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL CONTROL	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) WHILE ON A SLING OPERATION, PILOT NOTICED A FLUID LEAKING FROM THE BELLY IN THE CARGO MIRROR. THE AIRCRAFT WAS LAN	DED IMMEDIATELY AND IT WAS DISCOVERED THAT FUEL WAS LEAKING FROM A FUEL LINE FITTING. THE ENGINE WAS SHUT DOWN AND THE L	INE WAS CHECKED FOR TIGHTNESS AND WITNESS MARK. AS THE LINE WAS FOUND TORQUED SATISFACTORILY, THE LINE WAS REMOVED AND T	HE CRACKWAS DISCOVERED. THE LINE HAD BEEN INSTALLED SERVICEABLE.NO LOSS OF POWER OR OTHER OPERATIONAL DISCREPANCIES WERE	 NOTED WHILE IN FLIGHT.		1	G	7	1 	3U	3	U		H2SW    	E4CE
2005041900045	20050419	00045	EU  	2005	4	19	CA041209009      	1	20040909	G	2497		WIRE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	RT WING ROOT	CHAFED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, POWER LOSS ON RT ENG AT A FREQ OF 1-2 MINS, A TOTAL OF 4 TIMES. DURING FINAL , LANDING & TAXI TO SHU	TDOWN, ENG NORM. CHIP DETECTOR & FILTERS INSPD, NO FAULTS FOUND.  FUEL PRESSURE OK. COMPLETE GROUND RUN PERFORMED WITH N	O FAULTS. TEST FLT PERFORMED WITH NO FAULTS. PROBLEM REOCCURRED 5 WEEKS LATER. COMPLETE WIRING SYS FOR TORQUE IND SYS IN	SPD. CHAFED WIRE FOUND BEHIND TERM BLOCK IN RT WING ROOT. DISASSEMBLED TO EXPOSE WIRE FOR INSP. CHAFED WIRES & CHAFED PA	INT ON STRUCT COULD NOT BE SEEN WITH A MAGNIFIER. VOID IN INSULATION FOUND.  WIRE REINSULATED & REPOSITIONED. TORQUE IND	 SYS WORKS WITH MILLIVOLTS (PREAMPLIFIED). SUSPECT MOISTURE PROVIDING A GROUND PATH & TORQUE SYS SEEING AN OVRTORQUE.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL
2005041900046	20050419	00046	EU  	2005	4	19	CA041209010      	1	20041005	G	2823	39423091	SHUTOFF VALVE   			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	FUEL	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START SEQUENCE THE ENGINE APPEARED TO START NORMALLY UNTIL STARTER DIS-ENGAGED THEN SHUT ITSELF DOWN. TESTI	NG FOUND FUEL SHUTOFF VIBRATING LOUDLY WHEN POWER APPLIED WITH ENGINE STOP BUTTON. SUSPECT THE VALVE WAS TRYING TO BE OP	EN ANDCLOSED AT THE SAME TIME. REPLACED THE VALVE AND THE ENGINE STARTED AND STOPS NO RMALLY.				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL
2005041900047	20050419	00047		2005	4	19	CA041209011      	4	20041208	G	6122	210332210316	PILOT VALVE     	WOODWARD    																CSU	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2243677F					(CAN) CSU WAS INVOLVED IN A PROP STRIKE THEREFORE OH IS MANDATORY. UPON DISASSY OF CSU IT WAS DISCOVERED THAT THE PILOT 	VALVE PN 210332 WAS PITTED AND CORRODED ON THE BALL BEARING RACE SURFACE. THE FLYWEIGHT DRIVER PN 210317 AND THE FLYWEIG	HT HEAD PN 210316 AND THE FLYWEIGHT DRIVE SPRING PN 192662 WERE CORRODED BEYOND REUSE.THE CORROSION WAS OBSERVED ON THE 	EXTERNAL SURFACES. THE OVERHAUL WAS COMPLETED USING SERVICEABLE PARTS WHILE THE U/S COMPONETS WERE RETURNED TO OUR CUSTO	MER.
2005041900048	20050419	00048	NE  	2005	4	19	CA041209012      	2	20041201	G	7200		ENGINE          								PWA   	PWA120	PW125B      	 	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								124246			(CAN) DURING CLIMB THE ENGINE FLAMED OUT.  A RELIGHT ATTEMPT WAS UNSUCCESSFUL AND THE AIRCRAFT DIVERTED TO POINT OF DEPA	RTURE.P&WC WILL MONITOR THE INVESTIGATION OFTHE EVENT AND SUPPLIMENT THIS REPORT TO REFLECT ROOT CAUASE, ONCE ESTABLISHE	D.									4	T			E20NE
2005041900049	20050419	00049	NE  	2005	4	19	CA041209013      	2	20041206	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				W	J		INADEQUATE Q C            	WARNING INDICATION        		TO	TAKEOFF        	1			CA								DA0260			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION IN FLIGHT AND WAS SHUTDOWN BY THE PILOT DUE TO AN ASSOCIATED IT	T INCREASE TOWARDS RED-LINE. AN INFLT RELIGHT CARRIED OUT AND THE INCIDENT REOCCURRED. THE ENGINE WAS AGAIN SHUT DOWN.A 	SECOND RELIGHT WAS CARRIED OUT AND THE ENGINE RESPONDED NORMALLY TO THROTTLEINPUTS.  PWC WILL INVESTIGATE THE EVENT AND 	WILL SUPPLIMENT THIS REPORT TO IDENTIFY ROOT CAUSE ONCE DETERMINED.			1	L	7	2 	4F	4	F		A22CE   	E00053EN
2005041900050	20050419	00050	CE  	2005	4	19	CA041209014      	1	20041209	G	3233	50820208	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE ENDPLAY CHECK, THE ACTUATOR S ENDPLAY WAS AT THE MAX ALLOWABLE 0.018 INCH, THESE ACTUATORS HAVE A	 7500 CYCLE OVERHAUL REQUIREMENT AND THIS ONE ONLY HAD 1636 CSO.					1	L	7	2 	3T	4	T		A14CE   	E4EA
2005041900051	20050419	00051	WP  	2005	4	19	CA041209015      	1	20041206	G	7714	A5696	WARNING SYSTEM  			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					LOW RPM	INOPERATIVE     	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA							083				(CAN) DURING PILOT DAILY INSPECTION, THE LOW RPM WARNING UNIT WAS INOP. TECHNICIAN CONFIRMED THAT SYSTEM WAS DEFECTIVE A	FTER TROUBLESHOOTING AND PART HAS BEEN REPLACED AND FOUND SERVICEABLE.					1	G	7	1 	3O	3	O		H11NM   	E295
2005041900052	20050419	00052	SW  	2005	4	19	CA041210001      	1	20041025	G	6220	407010105101	STUD            	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					HUB ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A177					(CAN) ALL EIGHT STUDS (STATIC STOPS) FOUND CRACKED ON INSPECTION. MAINTENANCE CREWS REPORT LOWER STUDS ARE ALWAYS FOUND 	TO BE CRACKED ANY TIME THEY ARE INSPECTED. PROBLEM IS COMMON THROUGHOUT FLEET OF SEVEN BELL 407 HELICOPTERS.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
2005041900053	20050419	00053	EA  	2005	4	19	CA041210002      	1	20041209	G	2560	6000	LATCH           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					CABIN	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NEW PART, DISCOVERED AT INSTALLATION. DOES NOT LATCH. THE SPRING WHICH POSITIVELY PUSHES THE LATCH TO THE LOCK POS	ITION IS MISSING.					1	H	7	1 	3R	4	T		A815    	E4EA
2005041900054	20050419	00054	SO  	2005	4	19	CA041210003      	2	20041112	G	8530	538304	PUSHROD         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					EXHAUST	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								279878R			(CAN) AIRCRAFT RETURNED TO XXXX AFTER THE PILOT NOTICED A VIBRATION AND LOSS OF POWER.UPON INSPECTION OF THE ENGINE, FOU	ND NR 1 CYCLINDER EXHAUST PUSH ROD WAS BROKEN. PUSH ROD, ROD HOUSING ASSEMBLY & LIFTER WERE REPLACED AND ENGINE RUN & LE	AK CHECKED SERVICEABLE.				1	H	7	1 	3O	3	O		A16CE   	E5CE
2005041900055	20050419	00055	EA  	2005	4	19	CA041210004      	1	20041210	G	3242	MS276125	ADAPTER         			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					BRAKE	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER INSTALLING ALL FOUR BRAKES, WE BLED THE SYSTEM. WHILE DOING THE NR 2 BRAKE BLEEDING, THE NR 1 BRAKE BLEED PO	RT ADAPTER SHEARED AND BECAUSE OF THE HYDRAULIC PRESSURE THE ADAPTER HIT OUTBOARD MLG DOOR. HYDRAULIC SYSTEM PRESSURE WA	S IMMEDIATLY STOPPED.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005041200035	20050412	00035	SW  	2005	4	12	CA041210005      	1	20041210	G	5551	30653222	ATTACH FITTING  			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 RT HORIZONTAL STABILIZER AUX FIN WAS LOOSE. UPON INVESTIGATION BY MAINTENANCE STAFF I	T WAS NOTED THAT THE FORWARD AUX FIN ATTACH PLATE WAS COMPLTELY CRACKED THROUGH AND THE REAR ATTACH PLATE WAS CRACKED ON	 BOTH SIDES OF THE RADIUS. THE CRACK LENGTHS ON THE REAR PLATE WERE APPROXIMATELY 1INCH AND .3125 INCH IN LENGTH. THE TO	TAL WIDTH OF THE PLATE IN THE AREA IS 1.75 INCHES.  THE PARTS WILL BE REPLACED PRIOR TO THE AIRCRAFT RETURNING TO SERVIC	E.		1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL
2005041900057	20050419	00057	CE  	2005	4	19	CA041213002      	1	20041208	G	3230	131378252CL	MASTER LINK     	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG CHAIN	DISCONNECTED    	W				O				OTHER                   				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) WHEN THE FLT CREW EXTENDED LANDING GEAR FOR LANDING , THEY HEARD STRANGE SOUNDS AND THEY ONLY RECIEVED TWO MAIN LA	NDING GEAR LIGHTS. THE NOSE GEAR LIGHT WAS NOT GREEN AND THEY HAD A RED LIGHT ON IN THE HANDLE. THEY LOOKED IN THE NACEL	LE MIRROR AND WERE ABLE TO TELL THAT THE NOSE GEAR WAS ONLY HALF WAY EXTENDED.THE CREW DID AN EMERGENCY EXTENSION PROCED	URE WITH NO CHANGE. THE AIRCRAFT WAS LANDED IN THIS CONFIGURATION.ON LOOKING AT THE AIRCRAFT IN THE HANGER IT WAS FOUND 	THAT THE FORWARD NOSE LANDING GEAR CHAIN HAD COME APART AT THE MASTER LINK. THE LINK WAS HALF IN PLACE BUT THE CLIP WAS 	MISSING.  WE DO NOT KNOW IF THE CLIP BROKE OR CAME OFF. THE NOSE GEAR CHAIN AND MASTER LINK WAS NEW 376.1 HOURS AGO.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
2006091300287	20060913	00287		2006	9	13	CA041213003      	1	20041213	G	1400		TUBE            								PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								63225			(CAN) DURING ENGINE VISUAL INSPECTION AT MFG, HAVE IDENTIFIED THAT 2 ITEMS FROM THE FUEL PRESSURE TUBING WERE NOT GENUIN	E AND WERE MANUFACTURED BY AN UNKNOWN SOURCE. THOSE 2 ITEMS HAVE NO IDENTIFICATION NUMBERS BUT WERE INSTALLED IN REPLACE	MENT OF: FUEL CONNECTOR P/N 3100499-01 CONNECTOR BOLT P/N 3100504-01 BOTH PARTS ARE KEPT IN QUARANTINE FOR 21 DAYS FOR T	CCA REVIEW, AFTER WHICH THEY WILL BE DESTROYED. (TC NR 20041213003)								4	U			E22EA
2005041900058	20050419	00058	EU  	2005	4	19	CA041213005      	1	20041204	G	6400	350A33214501	BUSHING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					T/R PITCH LINK	CRACKED         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						MA1406					(CAN) DURING ROUTINE HYDS OFF TRAINING, TAIL ROTOR INPUTS MADE THROUGH TAIL ROTOR PEDALS WERE NOT BEING TRANSFERRED TO T	AIL ROTOR. PILOTS RESELECTED HYDS ON & TAIL ROTOR RESPONDED NORMALLY TO TAIL ROTOR INPUTS. AIRCRAFT RETURNED TO HANGAR F	OR INSPECTION. WHEN PITCH LINKS BOLTS WERE LOOSENED ON TAIL ROTOR SPIDER, NOTICED DEFLECTION ON ATTACHMENT FLANGES.  WIT	H BOLTS LOOSENED, TAIL ROTOR MOVED FREELY WHEN PEDALS ACTUATED (HYDS OFF & ACRFT NOT RUNNING).  INSPECTION OF 1 TAIL ROT	OR PITCH LINK REVEALED 2 CRACKS THAT WENT COMPLETELY THROUGH BUSHING IN ELASTIMERIC BEARING. WHEN 2 PITCH LINKS REPLACED	 & TEST PERFORMED, CONCLUDED THAT UNBOOSTED TAIL ROTOR INPUTS RESPONDED NORMALLY. ACRFT RETURNED TO SERVICE.	1	G	7	1 	3U	3	U		H9EU    	E19EU
2005041900060	20050419	00060	NE  	2005	4	19	CA041214001      	2	20041212	G	7532		FITTING         			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA								666056			(CAN) AT TRANSITION TO CRUISE FL 350 AFTER DEPARTURE, THE NR 2 ENGINE APPEARED TO SURGE OR COMPRESSOR STALL. AFTER 2 ATT	EMPTS TO REDUCE THROTTLE THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE FOUND A LE	AK AT THE PS4 FITTING AT THE PRESSUE RATIO BLEED CONTROL (PRBC). THE O-RING WAS REPLACED AND THE FITTING RESECURED.  AIR	CRAFT WAS GROUND CHECKED WITH NO FURTHER PROBLEM AND RETURNED TO SERVICE.			2	L	7	2 	4F	4	F		A16WE   	E2EA
2005041900062	20050419	00062	SW  	2005	4	19	CA041214002      	1	20040713	G	6410	206016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BLADE HAS A CHORDWISE CRACK AT BLADE STATION 12.64. THE CRACK IS 2.65 IN. (67.3MM) LONG ON THE DATA PLATE SIDE	 OF THE BLADE AND 0.4 IN. (10MM) LONG ON THE OTHER SIDE.					1	G	7	1 	3U				H2SW
2005041900064	20050419	00064	CE  	2005	4	19	CA041214003      	1	20041118	G	5610	10138402524	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, CREW HEARD A BANG AND NOTICED THE OUTER PANE OF THE RT WINDSHIELD HAD CRACKED.  CABIN PRESSURE WAS 	REDUCED AND THE FLIGHT WASCONTINUED TO DESTINATION.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005041900067	20050419	00067	NE  	2005	4	19	CA041214004      	2	20041211	G	7261	7938314506	LINE            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ENGINE OIL	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, LT ENGINE OIL PRESSURE DROPPED TO 39 PSI.  AIRCRAFT LANDED BACK TO DEPARTURE AIRPORT.  ON APPROACH, 	OIL QTY DROPPED TO 5 QTS AND OIL PRESSURE TO35 PSI.  MAINTENANCE FOUNDTHE PRESSURE LINE LEAKING BETWEEN THE OIL PRESSURE	 TRANSMITTER AND THE REDUCER. OIL PRESSURE LINE REPLACED, TESTED AND AIRCRAFT DISPATCHED SERVICEABLE.THE OIL LINE WAS FO	UND CRACKED AT THE TUBE FLARE AT THE REDUCER CONNECTION.  THE TECHNICIAN FOUND THE FITTING OVER TIGHTENED AND LINE STRES	SED DURING THE REMOVAL.IT IS CONCLUDED THAT THE LINE WAS NOT PROPERLY INSTALLED.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005041900069	20050419	00069	WP  	2005	4	19	CA041214005      	2	20041123	G	7250	8657923	BEARING         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								P63181C			(CAN) OIL WAS FOUND LEAKING FROM THE AFT BEARING COVER, ENOUGH OIL WAS LEAKING WHICH ALLOWED A 4 INCH DIAMETER POOL OF O	IL IN THE STUB PIPE.ENGINE TEAR DOWN STRIP REPORT WILL BE SENT IN.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE
2005041900071	20050419	00071	NE  	2005	4	19	CA041214006      	2	20041214	G	7497	3957985114	INTERFACE UNIT  			AIRBUS	A321  	A321211     	3930370	EU  	CFMINT	CFM56 	CFM565B4    	 	NE  					IGNITION SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ENG 1 IGN 'A' FAULT, ENG 2 IGN 'A' FAULT. 1&2 IGN A C/B POPPED. ENG 1 CTLC/B POPPED. STRONG SMELL OF ELECTRICAL BU	RNING. CONNECTOR 473VC SHORTED, CONNECTOR REPLACED. BMC NR 1 DAMAGED, REPLACED PER MM 36-11-34-400. EIU NR 2 CAUSING INT	FC PROBLEMS WITH AEVC. EIU NR 2 REPLACED PER M M 73-24-34-500. ENGINE RUN CARRIED OUT AND ALL TESTS OK.				2	L	7	2 	4F	4	F	RT	A28NM   	E38NE
2005041900075	20050419	00075	NM  	2005	4	19	CA041214007      	1	20041209	G	7932	10607225	INDICATOR       			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					OIL QTY	UNRELIABLE      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	N		FLUID LOSS                	FALSE WARNING             		CL	CLIMB          	1			CA											(CAN) DURING CLIMB ENGINE NR 2 OIL QUANTITY DECREASED RAPIDLY TO ZERO, FOLLOWED BY A RISE IN OIL TEMP.  CREW SHUTDOWN TH	E ENGINE ANDRETURNED TO AIRPORT. MAINTENANCE CHECKED OIL QTY AND FOUND TANK FULL. MAIN OIL FILTER CHECKED FOR CONTAMINAT	ION, NONE FOUND. BEARING TEMP INDICATORS CHECK ED FOUND NORMAL. HIGH POWER ENGINE RUN CARRIED OUT, NO FAULTS FOUND. AIRC	RAFT RE TURNED TO SERVICE. FAULT REOCCURRED ON NEXT FLIGHT LEG, HOWEVER, QTY RAPIDLY FLUCTUATED BETWEEN FULL, ZERO AND Q	UANTITIES IN BETWEEN. CREW IDENTIFIED THIS AS AN INDICATION PROBLEM AND CONTINUED FLIGHT. MAINTENANCE AT NEXT STATION PL	AC ED NR 2 ENGINE OIL QUANTITY SYSTEM ON MEL PART REPLACEMENT SCHEDULED FOR NEXT DAY.	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005041900078	20050419	00078		2005	4	19	CA041214008      	4	20041214	G	3442	6225136201	ANTENNA         			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					WX RADAR	DAMAGED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) ON ND. SYSTEM RETURNED TO NORMAL BUT GIVEN HISTORY, RETURNED HNL. ANT. COULD BE FELT AND HEARD CLUNKING. REPLACED 	WX RADAR ANT IAW W/C 34-41-11-000-801-862-050. REPLACED BOTH RADAR T/R UNITS IAW W/C 34-41-313-400. RADAR ANTENNA 34-40-	0247 OFF FTN 639J4G ON FTNRJTR38. NR 1 T/R 34-40-0249 OFF S/N 6050 ON S/N 9J1U NR 2 T/R OFF FTN 76W092 ON S/N 90 DC.				2	L	7	4 	4F	4	F	RT	A197    	E37NE
2005041900079	20050419	00079		2005	4	19	CA041214009      	4	20041214	G	3442	6225136201	ANTENNA         			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					WX RADAR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON ND. SYSTEM RETURNED TO NORMAL BUT GIVEN HISTORY, RETURNED HNL. ANTENNA. COULD BE FELT AND HEARD CLUNKING. REPLA	CED WX RADAR ANTENNA AS PER W/C 34-41-11-000-801-862-050. REPLD BOTH RADART/R UNITS AS PER W/C 34-41-313-400. RADAR ANT 	34-40-0247 OFF FTN 639J4G ON FTNRJTR38. NR 1 T/R 34-40-0249 OFF S/N 6050 ON S/N 9J1U NR 2 T/R OFF FTN 76W092 ON S/N 90DC	.			2	L	7	4 	4F	4	F	RT	A197    	E37NE
2005041900081	20050419	00081	SO  	2005	4	19	CA041215001      	1	20041214	G	7810		EXHAUST DUCT    			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10665	10665				57188			(CAN) DURING ROUTINE MAINTENANCE 2 CRACKS WERE FOUND ON THE STARBOARD ENGINE EXHAUSTDUCT. THE CRACKS WERE LOCATED APPROX	IMATELY 1.250 INCHES AFT OF THE REDUCTION GEARBOX MOUNTING FLANGE BETWEEN THE 10 AND 11:30 CLOCK POSITIONS. THE ORIGIN A	PPEARED TO BE FROM THE PORT EXHAUST STUB FORWARD ATTACHMENT AREA. THE CRACK LENGTHS WERE .350 AND .613 INCHES WITH A SEP	ARATION OF 2.250 INCHES. THE EXHAUST DUCT WASREMOVED AND SENT OUT FOR REPAIR.			1	L	7	2 	4T	4	T		A21SO   	E4EA
2005041900082	20050419	00082	CE  	2005	4	19	CA041215002      	1	20041214	G	7602	AN742D3	CONTROL UNIT    			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					MIXTURE	LOOSE           	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								L2107015			(CAN) PILOT WAS IN CRUISE, HE STARTED TO LEAN THE ENGINEWENT PAST LEAN OF PEAK SO HE PUSHED THE MITURE BACK IN BUT THE E	NGINE WAS STILL LOSING POWER. HE LANDED IN A FIELD WITHOUT ANY DAMAGE.ENGINEER WENT OUT AND REMOVED THE COWLING AND DISC	OVERED THAT THE CLAMP THAT HOLDS THE MIXTURE CABLE TO THE MIXTURE SUPPORT ASSEMBLY WAS LOOSE. CLAMP WAS REPLACED. MIXTUR	E WAS MOVED WORKS CORRECTLY. AIRCRAFT WAS FLOWN BACK TO BASE WITHOUT INCIDENT.			1	H	7	1 	3O	3	O	NT	3A19    	E223
2005041900083	20050419	00083	CE  	2005	4	19	CA041215003      	1	20041213	G	3230	6046H39A	RELAY           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					MLG	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) DURING A MISSED APPROACH PILOT INITIATED A TURN TO RETURN FOR A 2ND APPROACH WHEN MLG EXTENDED UNCOMMANDED WITH NO	 DOWN OR UP INDICATION LIGHTS. PILOT SLOWED ACRFT & CONTINUED TO DESTINATION WITH MLG SELECTED DOWN & CONFIRMED MLG DOWN	 WITH EMERGENCY GEAR HANDCRANK. MX INSPECTED ACRFT & FOUND MLG DYNAMIC BRAKING RELAY TO BE MALFUNCTIONING. ON INSPECTION	 OF RELAY, DETERMINED THAT A SPRING OFF OF ONE OF THE CONTACTS HAD BROKEN IN HALF & BROKEN PIECE HAD SHORTED OUT RELAY C	AUSING MLG TO EXTEND. RELAY REPLACED & ACRFT TEST FLOWN WITH NO REOCCURANCE. INSTALLATION DATE OF THE RELAY COULD NOT BE	 FOUND BUT MANUFACTURING DATE 6/77.	1	L	7	2 	3O	3	O	RT	3A16    	3E1
2005041900084	20050419	00084	CE  	2005	4	19	CA041215004      	1	20041116	G	7714	D11125025	TACHOMETER      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TACHOMETER WAS FULL OF OIL. TACH SHAFT SEAL LW14260 AND TACHOMETER REPLACED. TACHOMETER P/N D1-112-5025S/N 17488						1	H	7	1 	3O	3	O	NT	3A12    	E274
2005041900085	20050419	00085	NE  	2005	4	19	CA041215005      	2	20041206	G	7250	312345201	TURBINE BLADES  								PWA   	PW121 	PW121       	52124	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16038	10372							(CAN) LP TURBINE BLADES WERE INSTALLED NEW DURING THE 1999 OVERHAUL OF ENGINE & HAD ACCUMULATED TSN = 10372.6 HOURS AND 	CSN = 11948 CYCLES. 41 BLADES WERE ROUTED FOR CREEP INSPECTION. REMAINING BLADES COULD NOT BE INSPECTED DUE TO DAMAGE AB	LE TO CONCLUDE THAT THE LP TURBINE BLADES FAILED DUE TO CREEP, RESULTING IN SECONDARY IMPACT DAMAGE TO THE LP STATOR AND	 DOWNSTREAM GAS PATH COMPONENTS.								4	T			E20NE
2005041900086	20050419	00086	EU  	2005	4	19	CA041215006      	1	20041215	G	2731	Z4244100011	SHAFT           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ELEVATOR TRIM	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION, THE ELEVATOR TRIM CONTROL CABLE DRUM WAS NOTICED TO BE OFFSET ON AN ANGLE.  FURTHER IN	SPECTION REVEALED THE SHAFT THAT THE DRUM IS ATTACHED TO HAD THE LT END SHEARED OFF.THE LT AND RT ENDS ARE SUPPORTED BY 	THE LT AND RT INBOARD SEAT RAILS.  THE SHAFT IS A HOLLOW STEEL TUBE AND THE SUPPORT IS ALSO STEEL. THE HIGH AMOUNT OFTRI	MMING OF THE AIRCRAFT OVER TIME CAUSED THE LT END OF THE TUBE TO BE CUT THROUGH. THIS COULD LEAD TO A STUCK TRIM CONTROL	WHICH WOULD MAKE THE AIRCRAFT DIFFICULT TO CONTROL.  WE INITIATED AN IMMEDIATE INSPECTION OF ALL OUR Z242L AIRCRAFT TRIM	 CONTROL SHAFTS.  AT THIS TIME WE ARE LUBRICATING THIS AREA OF ROTATION.  DURING INSPECTIONS WE WILL BE PAYING CLOSER AT	1	L	7	1 	3O	3	O	0	A76EU   	1E10
2005041900087	20050419	00087	NE  	2005	4	19	CA041215007      	2	20041214	G	7310		ENGINE          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  						FAILED          	W				A				UNSCHED LANDING         				D	M		INFLIGHT SEPARATION       	OVER TEMP                 		CL	CLIMB          	1			CA								PR0271			(CAN) DURING CLIMB (6000 FT) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK ACCOMPANIED BY ITT INCREASE, A LOUD B	ANG AND FLAMES EVIDENT FROM THE EXHAUST. THE PILOT SHUT THE ENGINE DOWN IN FLT, DECLARED AN EMERGENCY AND SUBSEQUENTLY L	ANDED ON A ROAD.  PWC WILL INVESTIGATE THE INCIDENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERMIN	ED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
2005042000001	20050420	00001	EA  	2005	4	20	CA041216001      	1	20041216	G	3250	C6CF12425	CABLE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					NLG STEERING	MISINSTALLED    	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA											(CAN) NOSE WHEEL STEERING CABLE ROUTED INCORRECTLY RESULTING IN ALMOST SAWING THROUGH THE HYDRAULIC HAND PUMP SUCTION LI	NE P/N C6H1001-294.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
2005042000002	20050420	00002	EU  	2005	4	20	CA041216002      	1	20041213	G	3070		CONNECTOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STATIC VENT HEAT	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FOLLOWING A DISCREPANCY WITH THE LAVATORY DRAINING,  MAINTENANCE FOUND THE HEATER ASSY FOR STATIC VENTILATION (REA	R DRAIN MAST) NOT WORKING.  ONE OF THE 2 CONNECTORS AT THE HEATER WAS FOUND BURNED.  THE INSULATION BLANKET AROUND THE H	EATER WAS FOUND CARBONIZED.  THERE WAS NO SMOKE REPORTED.  THE AREA WAS FOUND DRY. THE CAUSE OF THE BURNED CONNECTOR STI	LL UNKNOWN. THE AIRCRAFT MANUFACTURER IS INFORMED.  THE RESULT OF INSPECTION ON 2 OTHER AIRCRAFT WAS FOUND SATISFACTORY.	  MORE DETAILS WILL FOLLOW.		2	L	7	2 	4F	4	F	RT	        	E25NE
2008013100009	20080131	00009	EA  	2008	1	31	CA041216003      	1	20041216	G	7120	CSP28229	BOLT            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENG MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT ENGINE REMOVAL 3 OF THE 4 TOP ENGINE MOUNT BOLTS PN CSP282-29 BOLT FAILED. THE HEADS SHEARED OFF AFTER APPROXIM	ATELY 3/1 - 1.25 TURN(S) OF THE BOLT. (TC NR 20041216003)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2008013100010	20080131	00010	EA  	2008	1	31	CA041216004      	1	20041216	G	7120	CSP28229	BOLT            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT ENGINE REMOVAL, ONE OF THE TOP ENGINE MOUNT BOLTS P/N CSP282-29 BOLT FAILED. THE HEADS SHEARED OFF AFTER APPROX	IMATELY A .7500 TURN OF THE BOLT.  REVIEWED (TC NR 20041216004)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
2005042000003	20050420	00003	CE  	2005	4	20	CA041216006      	1	20041203	G	2740	051010545	CONTROL CABLE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	HORIZONTAL STAB	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13168	13168							(CAN) CABLE FRAYING AT REAR PULLEY IN HORIZONTAL STABILIZER.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005042000004	20050420	00004	CE  	2005	4	20	CA041216007      	1	20041203	G	5312	05123635	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13168	13168							(CAN) BULKHEAD FOUND CRACKED AROUND RUDDER TUBE HOLD DOWN CLAMP.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005042000005	20050420	00005	NM  	2005	4	20	CA041216008      	1	20041215	G	2751	106131713	TRANSMITTER     	BOEING      		BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LT TE FLAPS	STICKING        	W				J	A			DUMP FUEL               	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING INITIAL CLIMBOUT, FLAPS CYCLED FROM 5 DEG. TO 2 DEG. CREW NOTICED THAT LT OUTBOARD FLAPS WERE INDICATING 5 	DEG. & RT OUTBOARD FLAPS WERE INDICATING 3 DEG. CAUSING AN ASSYMETRY SPLIT. CREW HAD TO DUMP FUEL TO LAND WITHIN LANDING	 WEIGHT. CREW ACCOMPLISHED AN ASSYMETRY FAULT LANDING. LANDING ACCOMPLISHED & ACRFT RETURNED TO RAMP. MX CONFIRMED FLAPS	 WORKING PROPERLY BUT LT OUTBOARD FLAP INDICATING SYS FAULTY. MX INSPECTED LT OUTBOARD FLAP INDICATION SYS (CABLES, CABL	E DRUM, TRANSMITTER) ALL CABLES WERE CLEANED & LUBED. FLAPS CYCLED NUMEROUS TIMES & NO FURTHER FAULTS FOUND. MX SUSPECT 	FLAP INDICATION TRANSMITTER CABLE HUNG-UP AT THE DRUM ASSY. AS A PRECAUTION, LT OUTBOARD FLAP TRANSMITTER REPLACED.	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005042000006	20050420	00006	EA  	2005	4	20	CA041216009      	2	20041214	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RIGHT	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								L11568A			(CAN) ON DEPARTURE, THE CREW HAD A POWER LOSS ON THE RT ENGINE, FEATHERED ENGINE AND RETURNED FOR A LANDING. THE ENGINE 	WAS REPLACED WITH A SERVICEABLE ONE AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE SHALL BE OPENED IN OUR ENGINE SHOP 	IN THE NEAR FUTURE TO DETERMINE THE EXACT CAUSE, SUSPECTED TO BE A PROBLEM IN THE ACCESSORY GEARTRAIN, AT WHICH POINT A 	CLOSED SDR WILL BE FILED.			1	L	7	2 	3O	3	O		A20SO   	E14EA
2005042000007	20050420	00007	CE  	2005	4	20	CA041216010      	1	20041214	G	8120	470954001	WASTEGATE VALVE 			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540AK1A  		EA  					TURBOCHARGER	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WASTEGATE BUTTERFLY VALVE FOUND SEIZED ON INSPECTION.  THIS IS THE SECOND VALVE FOUND SEIZED ON TWO DIFFERENT AIRC	RAFT WITH LOW TTSN.					1	H	7	1 	3O	3	O	NT	3A13
2005042000008	20050420	00008	NE  	2005	4	20	CA041216011      	2	20041215	G	7261		B-NUT           			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					OIL LINE	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								891283			(CAN) APPROX 30 MINS AFTER TAKE OFF, CREW NOTED LOSS OF OIL QTY IN NR 2 ENG & DID AN AIR TURNBACK. SEVERAL MINS LATER CR	EW NOTED FLUCTUATING OIL PRESSURE IN NR 2 ENG & CARRIED OUT A PRECAUTIONARY SHUTDOWN.  MX ISOLATED LEAK TO AN AREA WHICH	 HAD BEEN DISTURBED BY MX THE PREVIOUS DAY DURING A B-CHECK. AT THAT TIME, COKING HAD BEEN NOTED ON OIL LINES INTERFACE 	AT REAR TURBINE FRAME & A GASKET REPLACED IN REAR BEARING HOUSING. INVEST IN THIS AREA FOUND TOP FITTING OF OIL SUPPLY L	INE LOOSE BY 1 FLAT (60 DEGREES).  B-NUT ON THIS TUBE IS RETAINED BY A PIN WHICH TENDS TO ADD DRAG TO TORQUE.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN
2005042000009	20050420	00009	SO  	2005	4	20	CA041216012      	1	20041216	G	7810	8402917	TANK            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					FUEL COLLECTOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) RIGHT FUEL COLLECTOR TANK WAS LEAKING INSIDE THE WHEEL WELL.FOUND TANK WAS CRACKED ON THE UPPER INBOARD WELD FLANG	E.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
2005042000010	20050420	00010	EA  	2005	4	20	CA041217001      	1	20041216	G	3260	864808	PROXIMITY SENSOR			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER GEAR UP SELECTION  PROX SYS FAULT STATUS MESSAGE APPEARED.  THE GEAR WAS RE-CYCLED AND THE MESSAGE PERSISTED	. MAINTENANCE CARRIED OUT PSEU BITE CHECK AND FOUND A06 FAIL AND NVRAM FAIL .THE PSEU WAS REPLACED AND THE SYSTEM TESTED	 SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042000011	20050420	00011	EA  	2005	4	20	CA041217002      	1	20041213	G	3234	555406	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	MALFUNCTIONED   	W				O				OTHER                   				P			NO WARNING INDICATION     			CL	CLIMB          	1			CA											(CAN) DURING LANDING GEAR EXTENSION, NOSE GEAR TOOK 3-4 TIMES LONGER THAN NORMAL TO EXTEND AND LOCK.  MAINTENANCE REPLAC	ED THE NOSE LANDING GEAR SELECTOR VALVE AND THE SYSTEM TESTED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042000012	20050420	00012	GL  	2005	4	20	CA041217003      	1	20041214	G	2752		SEAL            	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					SPINE SHAFT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IT WAS NOTICED DURING SCHEDULED INSPECTION THAT THE FLAP ACTUATOR SEAL HAD COME LOOSE ON THE SHAFT. ASSY WAS REMOV	ED AND SEAL RE-GLUED IN PLACE AS PER DIAMOND INSTRUCTION, RE-INSTALLED.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO
2005042000013	20050420	00013	EU  	2005	4	20	CA041217004      	1	20041116	G	5741	HC536H04230	LINK            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING TO BODY	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37986								(CAN) DURING INSPECTIONS CARRIED OUT ON THE ABOVE NOTED ACRFT FOR THE LEASE RETURN,  ENGINEERS FOUND WING TO FUSELAGE CO	NNECTING LINKS AT REAR SPAR FITTING S, FRAME 29 CORRODED IN THE BORE ON BOTH ENDS OF THE LINKS. BOLTS ASSOCIATED WITH TH	E LINKS WERE ALSO CORRODED UNDER THE HEAD AND AROUNDTHE UNDER CUT AREA OF THE THREADED END OF THEBOLT.  INITIAL THRESHOL	D FOR THESE INSPECTIONS IS AT 24000 FLTS AND THE REPEAT WAS TO BE DONE AT 12000 FLIGHTS THE TWO AIRCRAFT THAT HAVE HAD T	HE INSPECTIONS CARRIED OUT ON WERE ON A SAMPLING PROGRAM AND BEING TRACKED ACCORDINGLY.REPLACEMENT PARTS WERE ORDERED AN	D ARE INSTALLED ON THE ABOVE NOTED AIRCRAFT.	2	H	7	4 	4F	4	F		A49EU   	E6NE
2005042000014	20050420	00014	WP  	2005	4	20	CA041217005      	1	20041215	G	7711	LG80EI	TRANSMITTER     			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LT ENGINE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, LT ENGINE EPR DROPPED TO 1.35 FOLLOWED BY AUTO THROTTLE DISCONNECT AND AIRCRAFT DECELERATION.  EPR 	LINE INSPECTED, NO FAULTS FOUND.  ENGINE RUN-UP CARRIED OUT AS PER AMM AND ENGINE PARAMETERS FOUND WITHIN LIMIT.  THE PR	ESSURE TRANSMITTER WAS REPLACED FOR PRECAUTIONARY.  NO MALFUNCTION WAS REPORTED ON FOLLOWING FLIGHTS.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005042000015	20050420	00015	NE  	2005	4	20	CA041217006      	2	20041217	G	7310		LINE            								PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE FUEL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE VISUAL INSPECTION AT PWC, WE HAVE IDENTIFIED THAT 2 ITEMS FROM THE FUEL PRESSURE TUBING WERE NOT GEN	UINE AND WERE MANUFACTURED BY AN UNKNOWN SOURCE. THOSE 2 ITEMS HAVE NO IDENTIFICATION NUMBERS BUT WERE INSTALLED IN REPL	ACEMENT OF: FUEL CONNECTOR P/N 3100499-01 CONNECTOR BOLT P/N 3100504-01 BOTH PARTS ARE KEPT IN QUARANTINE FOR 21 DAYS FO	R TCCA REVIEW, AFTER WHICH THEY WILL BE DESTROYED.NOTE: THIS IS THE 2ND OCCURENCE RECENTLY								4	U			E22EA
2005042000016	20050420	00016		2005	4	20	CA041217007      	1	20041216	G	1100	3017809	DATA PLATE      								PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								60263			(CAN) ENG RECEIVED WITH FALSE DATA PLATE (ORIGINAL DATA PLATE FOUND IN ENG LOGBOOK). THE FALSE DATA PLATE ENGRAVED WITH 	SN 63235 WHILE THE ENGINE INTERNAL COMPONENTS SHOWED THAT ALL THESE COMPONENTS WERE FITTED INTO ENGINE SN 60263. SIMULTA	NEOULY, REAL ENGINE SN 63235 WAS IN HOUSE FOR REPAIR WITH ITS REAL DATA PLATE AND THE S/N 63235 ENGRAVED ON IT.									4	U			E22EA
2005042000017	20050420	00017	SO  	2005	4	20	CA041220001      	1	20041220	G	5280	5452810	DOOR            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					LANDING GEAR	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA							7820038				(CAN) INFLIGHT, THE CREW NOTICED THAT THE RED GEAR IN TRANSIT LIGHT ILLUMINATED AT SPEEDS ABOVE 210 KNOTS. THE AIRCRAFT 	LANDED SAFELY AT ITS DESTINATION. UPON INSPECTION, THE INNER SKIN OF THE RIGHT OUTBOARD GEAR DOOR WAS FOUND CRACKED AND 	BENT INWARDS BY THE AIRFLOW. THE DOOR WAS REPLACED AND SATISFACTORY GEAR SWINGS WERE CARRIED OUT.				1	L	7	2 	3T	4	T		A8EA    	E4EA
2005042000018	20050420	00018	CE  	2005	4	20	CA041220002      	1	20041216	G	3233		SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ACTUATOR	NOT CLOSED      	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) DURING LANDING PROCESS, THE CREW NOTED THAT THE NOSE GEAR DOWN GREEN INDICATION WAS NOT ILLUMINATING. MAINTENANCE 	FOUND THE INTERNAL SWITCH ON THE ACTUATOR WAS NOT CLOSING PROPERLY AND THE ACTUATOR WAS REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005042000019	20050420	00019	CE  	2005	4	20	CA041220003      	1	20041219	G	3260	MS24171D1	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	SHORTED         	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) DURING LANDING PROCESS, GEAR REQUIRED 2 ATTEMPTS FOR EXTENSION. MAINTENANCE FOUND THE LANDING GEAR RELAY, WAS PITT	ED INTERNALLY PROVIDING INTERMITTENT CONTACTS.THIS OPERATOR HAS EXPERIENCED NUMEROUS FAILURES AT OR ABOVE 8000 HOURS TSN	 ON THESE RELAYS. AS A RESULT, THE RELAY WAS HARDTIMED AT 5000 HOURS WITH (TO DATE) GOOD SUCCESS. THIS RELAY FAILED AT A	PPROX 3700 HOURS TSN. THEREFORE, THE HARDTIME FOR THIS FLEET SHALL BE ESCALATED TO 3000 HOURS.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005042000020	20050420	00020	EU  	2005	4	20	CA041220004      	1	20041214	G	3246	314611	WHEEL           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							1057				(CAN) THE LEFT MAIN TIRE WAS LOOSING AIR. UPON INSPECTION, A CRACK WAS DISCOVERED IN THE LEFT INBOARD WHEEL HALF, AT THE	 TIRE BEAD AREA. NO INDICATIONS OF HARD LANDING WERE FOUND. THE WHEEL WAS REPLACED WITH AN OVERHAULED UNIT AND THE OLD W	HEEL WAS SENT OUT FOR WARRANTY CONSIDERATION.				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE
2005042000021	20050420	00021	SO  	2005	4	20	CA041220005      	2	20041207	G	7322	629390A8	METERING VALVE  			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					FUEL INJECT SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL METERING UNIT ON TCM I0-520 ENGINE HAD FUEL STAINING LINES AND SCREEN INSPECTED ON FAULTS FOUND.  COOLING SHR	OUD REMOVED AND SYSTEM WAS PRESSURIZED. SOURCE OF LEAK WAS DETERMINEDTO BE FROM A FILLESTER HEAD SCREW IN THE CENTER OF 	THE DATA PLATE.  SCREW WAS LOCKWIRED AND SEALED WITH TCM LEAD SEAL ON THE LOCKWIRE.  LOCKWIRE WAS CUT IT WAS FURTHER DET	ERMINED THAT THE SCREW WAS SHEARED OFF.  BROKEN SCREW WAS REMOVED, NEW SCREW INSTALLED WITH EXISTING SEAL WASHERS. SYSTE	M WAS AGAIN PRESSURE TESTED NO FURTHER FAULTS FOUND.		1	H	7	1 	3O	3	O		A4CE    	E5CE
2005042000022	20050420	00022	EA  	2005	4	20	CA041220006      	2	20041212	G	8530		CYLINDER HEAD   			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ENGINE	SEPARATED       	W				O				OTHER                   				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA								E2991136A			(CAN) HEAD SEPARATION WHILE IN FLIGHT.  DISCOVERED WHILE INVESTIGATING A ROUGH RUNNING ENGINE AS REPORTED BY PILOT.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
2005042000023	20050420	00023	EA  	2005	4	20	CA041221002      	2	20041213	G	7240	3029248	COMBUST CHAMBER 			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								057378			(CAN) DURING CLIMB THE ENG EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY AUTO-FEATHER.  THE AIRCRAFT DIVERTE	D TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A FRACTURED COMBUSTOR SMALL EXIT DUCT AND ASSOCIATED CT BLADE AN	D VANE DAMAGE.				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA	6	C	P15EA
2005042000024	20050420	00024	SW  	2005	4	20	CA041221003      	1	20041210	G	7820	099001050	MUFFLER         			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AD CF90-03R2 REQUIRES PRESSURE TESTING OF MUFFLERS USED FOR CABIN HEAT. CRACK NOTED AT RT END PLATE ABOVE INLET PO	RT,  AT OUTER EDGE OF PREVIOUS WELD REPAIR. CRACK WAS NOT INSIDE CABIN HEAT MUFF AREA.					1	H	7	1 	3O	3	O	NC	A759    	E274
2005042000025	20050420	00025	CE  	2005	4	20	CA041221004      	1	20041216	G	5610	PPG1013840257	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) WHILE IN THE CLIMB, PASSING THROUGH 15000 FT THE CAPTAINS WINDSHIELD CRACKED.THE CREW CARRIED OUT THE APPLICABLE F	LIGHT MANUAL PROCEDURES AND RETURNED BACKTO AIRPORT. THE AIRCRAFT WAS LATER FERRIED TO THE MAINTENANCE BASE WHERE THE WI	NDSHIELD WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2005042000026	20050420	00026	SW  	2005	4	20	CA041221005      	1	20041214	G	6510	206040339009	BEARING         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					BLOWER ASSY	ROUGH           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING BLOWER ASSEMBLY DISSASSEMBLY FOR CLEANING TAIL ROTOR DRIVESHAFT BEARING WAS FOUND TO FEEL ROUGH WHEN ROTATE	D.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005042000027	20050420	00027	SW  	2005	4	20	CA041221006      	1	20041206	G	6510	327211	DISC            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R DRIVE SHAFT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION 4 DISC ASSY WHERE FOUND TO BE CORRODED AND HAD TO BE REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
2005042000028	20050420	00028	EA  	2005	4	20	CA041221007      	1	20041210	G	5610		WINDOW POST     			DHAV  	DHC3  	DHC3        	2800202	EA  										COCKPIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN UNSCHEDULED INSPECTION OF WINDSHIELD POST AT BOTH LT AND RT SIDES SEVERE CORROSION WAS FOUND. THE LT POS	T WAS CORRODED THROUGH IN AREAS WITH SEVERE CORROSION ALTHOUGH IT HAD NOT GONE THROUGH.THIS FINDING IS ALSO DESCRIBED IN	 DEHAVILLAND SB 3/29.				1	H	7	1 	3R				A815
2005042000029	20050420	00029	NM  	2005	4	20	CA041221008      	1	20041209	G	2910	DSC252A40272	LINE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	BRAKE ASSY	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) AN OPERATOR EXPERIENCED A HYDRAULIC FLUID LOSS FROM NR 2 SYSTEM ON THEIR A/C DURING TAXI. THE FLUID LOSS WAS DUE T	O A LEAK ON THE FLEXIBLE LINE FOR NR 3 BRAKE UNIT. THE LINE PN DSC252A4-0272 (IPC 32-42-00 FIG 17 ITEM 20) WAS FOUND DAM	AGE CLOSE TO ONE OF THE END FITTINGS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005042000030	20050420	00030	CE  	2005	4	20	CA041222001      	1	20041221	G	3211		LANDING GEAR    			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LEFT	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) LT MLG WOULD NOT INDICATE DOWN AND LOCK, ACCOMPANIED BY TWO RED UNSAFE LIGHTS. ALTERNATE GEAR EXTENSION DID NOT SO	LVE THE PROBLEM. AIRCRAFT PLACE INSIDE HANGAR FOR A 3 HOURS PERIOD. HYDRAULIC SYSTEM BLED AND GEAR RETRACTIONS CARRIED O	UT. UNABLE TO DUPLICATE DEFECT ON GROUND.				2	L	7	2 	4F	4	F		A10CE   	E6WE
2005042000031	20050420	00031	EA  	2005	4	20	CA041222002      	1	20041214	G	5230	C4BM13583	FITTING         	DHAV        		DHAV  	DHC4  	DHC4        	2800302	EA  										HINGE ARM	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CARGO DOOR PN C4B1024-5. CRACKS FOUND ON AFT LT AND RT HINGE ARM FITTING ASSEMBLY PN C4BM1358-3. THESE CRACKS WERE	 ON OUTBOARD FLANGE AROUNG TOP AND BOTTOM ATTACH HOLES.					2	H	7	2 	4R				1A19
2005042000032	20050420	00032		2005	4	20	CA041222003      	4	20041208	G	3497	1835501010001	CONTROL UNIT    	HONEYWELL   		CESSNA	500   	560CESSNA   	2076750	CE  										COCKPIT	DAMAGED         	W				H	B			DEACTIVATE SYST/CIRCUITS	EMER. DESCENT           			D	B	H	INFLIGHT SEPARATION       	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	CL	CLIMB          	1			CA						U1195					(CAN) CLIMBING THROUGH FL300 A LOUD BANG OCCURRED FOLLOWED BY ELECTRICAL SMOKE ORIGINATING FROM THE CENTRE PEDESTAL. PRI	MARY NAVIGATION FAILED IMMEDIATELY AS THE GNC-XL FMS FAILED. THE FMS WAS ISOLATED ELECTRICALLY AND THE CREW PERFORMED A 	RAPID DESCENT AND REQUESTED PRIORITY HANDLING. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENCE. INVESTIGATION ON THE GROUN	D REVEALED DAMAGE CONFINED TO THE FMS BOX AND THE UNIT WILL BE SENT TO HONEYWELL FOR FURTHER ANALYSIS.			2	L	7	2 	4F			RT	A22CE
2005042000033	20050420	00033	SO  	2005	4	20	CA041222004      	2	20041214	G	8500	643207	CRANKCASE       			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA								510659			(CAN) THE NR 4 CYLINDER HAD LOW COMPRESSION AND WAS REMOVED FOR REPAIR. WHILE THE CYLINDER WAS REMOVED, A CRACK WAS FOUN	D AROUND THE 4 O'CLOCK POSITION CYLINDER ATTACH STUD. THE CRACK WAS ABOUT 1.5 INCHES LONG RADIATING INWARD. THE ENGINE W	AS REMOVED FORREPAIR.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA
2005042000034	20050420	00034	SW  	2005	4	20	CA041222005      	1	20041217	G	7120	590000	MOUNT           			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE OIL AND FILTER CHANGE, VISUAL INSPECTION FOUND THE ENGINE MOUNT P/N 590000, STRUT FORK CRACKED. THE 	FORK ATTACHES TO THE ENGINE MOUNT BLOCK P/N 590002, AFFIXED TO THE FIREWALL.					1	L	7	1 	3O	3	O		2A3     	E286
2005042500001	20050425	00001	GL  	2005	4	25	CA041222006      	2	20041209	G	7250	23038160	TURBINE         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAT15353			(CAN) CHIP LIGHT AND ENGINE VIBRATION.  PRECAUTIONARY LANDING. ON SUBSEQUENT INSPECTION,  TURBINE FOUND TO HAVE FAILED. 	 EXHAUST STACKS AND COMBUSTION LINER FOUND CRACKED.  REMOVED TURBINE AND INSTALLED SERVICEABLE TURBINE,  EXHAUST STACKS 	AND COMBUSTION LINER.  AIRCRAFT INSPECTED,  TEST RUN,  TEST FLOWN AND CHECKED SERVICEABLE.  TURBINE TO QUALIFIED OVERHAU	L SHOP.			1	G	7	1 	3U	3	U		H2SW    	E4CE
2005042500002	20050425	00002	EU  	2005	4	25	CA041222007      	1	20041113	G	2612	30011690040012	SENSOR          			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					LT FIRE LOOP	OPEN            	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING PREFLIGHT CHECKS, THE LT ENGINE FIRE WARNING FAILED TO TEST. TROUBLESHOOTING REVEALED A FAILED FIRE LOOP. F	IRE LOOP WAS REPLACED WITH NEW PRIOR TO FURTHER FLIGHT.					2	L	7	2 	4F	4	F		A33EU   	E6WE
2005042500003	20050425	00003	EU  	2005	4	25	CA041222008      	1	20041215	G	2842	360930001	AMPLIFIER       			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					FUEL QTY IND	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE CREW NOTICED THAT THE RT FUEL QUANTITY GAUGE HAD DROPPED TO ZERO. THE LOW LEVEL LIGHT DID NOT I	LLUMINATE, ASSURING THE CREW THAT THIS WAS AN INDICATION PROBLEM ONLY.  THE RT QUANTITY AMPLIFIER WAS REPLACED AND THE S	YSTEM WAS PROPERLY CALIBRATED PRIOR TO THIS FLIGHT. THE RECENTLY REPLACED AMPLIFIER WAS FOUND TO HAVE FAILED INTERNALLY.				2	L	7	2 	4F	4	F		A33EU   	E6WE
2005042500004	20050425	00004	EU  	2005	4	25	CA041222009      	1	20041210	G	7331	7231602	INDICATOR       			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					FUEL FLOW	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE RT FUEL FLOW GAUGE FAILED.  GAUGE WAS REPLACED AND SYSTEM TESTED SERVICEABLE.						2	L	7	2 	4F	4	F		A33EU   	E6WE
2005042500005	20050425	00005	GL  	2005	4	25	CA041222010      	3	20041217	G	6111	C4902	NUT             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RETENTION NUT THREAD CRACKED, 3 INCHES IN LENGTH, . DISCOVERED DURING OVERHAUL L.P.I. INSPECTION.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA
2005042500006	20050425	00006	SO  	2005	4	25	CA041222011      	1	20041201	G	2720	62701154	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  										RUDDER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER REMOVAL OF RUDDER,  FOUND MANY STRANDS BROKEN ON LT AFT RUDDER CABLE. THE CABLE CHAFING AT AFT BULKHEAD.THE 	CABLE WAS REPLACED BY NEW P/N 62701-154.					1	L	7	2 	3O				A19S0
2005042500007	20050425	00007	SO  	2005	4	25	CA041222012      	1	20041215	G	1430	AN511A	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	IO540M1A5   	41532	EA  					STABILIZER	MISMANUFACTURED 	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHEN REINSTALLING THE HORIZONTAL STAB, (AT THE AFT SPAR ATTACH POINT) USING NEW HARDWARE,  IT WAS DISCOVERED THAT 	THE REQUIRED BOLTS WERE LONGER IN TOTAL LENGTH BY 0.1875 AND SHANK LENGTH BY 0.1875, THAN THE ORIGIONAL BOLTS REMOVED. T	HIS CAUSED THE NUTS TO SHANK OUT WHEN TORQUED. IT IS APPARENT THAT THE ENGINEERING SPECIFICATIONS FOR AN AN5-11A BOLT HA	VE CHANGED SINCE 1970. THE PARTS LISTING PAGE WAS LAST REVISED MAY 1981.  THIS SITUATION IS NOT EASILY NOTICED AS THE NU	T END IS ONLY VISIBLE USING A MIRROR SO THE ONLY INDICATION IS BY 'FEEL' OF THE WRENCHES WHEN AT FINAL TORQUE VALUE.  IT	 IS ADVISABLE NOT TO ASSUME THAT A STANDARD PART WILL ALWAYS BE PHYSICALLY THE SAME SIZE AFTER 35 YEARS OF PRODUCT IMPRO	1	L	7	2 	3O	3	O		A20SO   	1E4
2005042500008	20050425	00008	WP  	2005	4	25	CA041222014      	2	20041209	G	7322	307080022	FUEL CONTROL    			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) WHILE ON APPROACH TO DESTINATION AIRPORT,  THE LT ENGINE FLAMED OUT.  POWER LEVER WAS AT FLIGHT IDLE POSITION.  FL	AME OUT OCCURRED AS POWER LEVER WAS ADVANCED FROM FLIGHT IDLE.  LT ENGINE MAIN FUEL CONTROL REPLACED IAW MANUFACTURERS R	ECOMMENDATIONS.				2	L	7	2 	4F	4	F		A10CE   	E6WE
2005042500100	20050425	00100	NM  	2005	4	25	CA041222015      	1	20041221	G	8012	8216003	START VALVE     			AMD   	FALC50	FALCON2000  	2730170	NM  										ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN DURING CLIMB AND THE AIRCRAFT DIVERTED TO NEAREST AIRPORT.  SUBSEQU	ENT INSPECTION REVEALED THE AIRFRAME AIR-START VALVE STUCK IN THE OPEN POSITION AND EVIDENCE OF LOCALIZED OVER HEATING. 	 A (START VALVE FAILED OPEN) EICAS MESSAGE WAS REPORTED.				2	K	7	3 	4F			RT	A50NM
2005042500009	20050425	00009	EA  	2005	4	25	CA041222016      	2	20041222	G	7421	REM38E	SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA								L2751651A			(CAN)  NR 1 TOP SPARK PLUG INSULATOR FOUND BROKEN UNDER ELECTRODES.  REPLACED NR 1 TOP SPARK PLUG,  REMAINING PLUGS FOR 	LT MAGNETO CLEANED AND FUNCTION TESTED.  GROUND RUN CARRIED OUT,  LT MAGNETO OPERATION NORMAL.					1	H	7	1 	3O	3	O	NT	3A12    	1E10
2005042500010	20050425	00010	NM  	2005	4	25	CA041222017      	1	20041220	G	3221	654581945	GUSSET          			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE PHASE 2 CHECK (137.5 HRS.)  A 3.5 INCH (THREE AND A HALF INCH)  CRACK WAS FOUND ON THE NOSE LANDI	NG GEAR GUSSET WHILE CARRYING OUT SERVICE DIFFICULTY ALERT AL-2002-03.  RETRACT ACTUATOR SUPPORT FITTING GUSSET REPLACED	 IAW SRM 51-30-2 FIG II.TIMES.  64641.30  CYCLES. 61588.				2	L	7	2 	4F	4	F		A16WE   	E2EA
2008013100011	20080131	00011		2008	1	31	CA041222018      	4	20041222	G	2565	PDMC6E101729	ACTUATOR        			DHAV  	DHC6  	DHC6        	2802606	EA  										SLIDE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) SLIDE ACTUATOR MANUFACTURED TO INCORRECT LIMITS. SLIDE ACTUATOR WILL NOT FIT ONTO BETA SWITCH BRACKET P/N C6E1060-	3. GROOVE FOR SLIDE ON A  C6E1017-29 IS .1300 +/- .0005. GROOVE ON SLIDE FROM J.A.S. PDM C6E1017-29 IS .1200 +/- .0005. 	TRACK ON BETA SWITCH BRACKET IS .1250. (TC NR 20041222018)				1	H	7	2 	3T			RT	A9EA
2005042500011	20050425	00011	NE  	2005	4	25	CA041222019      	2	20041220	G	7310		SHUTOFF VALVE   								PWA   	305   	PW305B      	52128	NE  					ENGINE FUEL	ACTIVATED       	W				A				UNSCHED LANDING         				X	B	J	ENGINE FLAMEOUT           	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA								305118			(CAN) ON TAXI PRIOR TO TAKEOFF,  THE CREW WERE ALERTED TO SMOKE EMINATING FROM THE ENGINE.  ON TAKEOFF THE ENGINE EXPERI	ENCED AN UNCOMMANDED SHUTDOWN.  THE CREW DECLARED AN EMERGENCY AND RETURNED TO POINT OF DEPARTURE.  INITIAL INSPECTION R	EVEALED THE EMERGENCY FUEL SHUT-OFF VALVE HAD ACTIVATED.  PWC WILL INVESTIGATE THE EVENT AND SUPPLIMENT THIS REPORT TO R	EFLECT ROOT CAUSE, ONCE DETERMINED.								4	F			E35NE
2005042500012	20050425	00012	WP  	2005	4	25	CA041222020      	1	20041218	G	2140		HEATER          			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					CABIN/COCKPIT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				M	H	G	OVER TEMP                 	ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          	CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT,  THE CREW EXPERIENCED MULTIPLE AVIONICS FAILIERS,  INCLUDING BOTH COMMS,  BOTH NAVS,  BOTH TRANSPOND	ERS,  AN ADF,  AND AN RMI. THE A/C RETURNED TO BASE WITHOUT INCIDENT.  THE CREW HAD COMMENTED THAT THE COCKPIT WAS VERY 	WARM PRIOR TO DEPARTURE. MAINTENANCE DISCOVERED THAT SOME ANTENNA CABLES LEADING FROM THE COCKPIT APPEARED TO HAVE BEEN 	DAMAGED DUE TO OVERHEATING.  IT WAS FURTHER FOUND THAT THE HERMAN NELSON USED IN THE PRE-HEATING OF THE A/C HAD A DEFECT	IVE THERMOSTAT THAT RESULTED IN UNCONTROLLED FULL HEAT OUTPUT. THE HEATER WAS SENT FOR REPAIR.  MAINTENANCE REPLACED 5 A	NTENNA COAX CABLES, THE NR 2 COMM TRANSCEIVER, AND THE ADF RECEIVER. THE A/C WAS RETURNED TO SERVICE.	2	L	7	2 	4R	4	T		6A6     	E282
2005042500013	20050425	00013	NE  	2005	4	25	CA041223001      	2	20041221	G	7230		COMPRESSOR      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2 ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								728089			(CAN) A LOUD BANG HEARD ON ROTATION FROM NR 2 ENGINE.  POWER WAS REDUCED TO IDLE AND AIRCRAFT LANDED BACK.  ENGINE FAN B	LADES FOUND DAMAGED.  ENGINE REPLACED.  THE CAUSE HAS NOT BEEN IDENTIFIED.  AWAITING FOR SHOP REPORT.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005042500014	20050425	00014	NE  	2005	4	25	CA041223003      	2	20041223	G	7200		ENGINE          			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					LEFT	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								350131			(CAN) UNCOMMANDDED ACCELERATION ON THE LT ENGINE ON TAKE OFF AROUND + 7 PERCENT ABOVE RETURN TO NORMAL 40 SECONDS LATER.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042500015	20050425	00015	NE  	2005	4	25	CA041223004      	1	20041215	G	6200	7610708001104	SUPPORT         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11010								(CAN) DURING INSPECTION MANDATED BY ASB 76-65-62 SEVERE FRETTING WAS DISCOVERED ON LOWER FAYING SURFACE. SUPPORT ARM HAS	 BEEN REPLACED AND A/C  RETURNED TO SERVICE.					1	G	7	2 	3U	3	U		H1NE    	E1GL
2005021400181	20050214	00181	SW  	2005	2	14	CA041223005      	1	20040821	G	6710	206010355009	PITCH LINK      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED 100-HOUR INSPECTION TWO (2) VERTICAL CRACKS WERE FOUND ON A MAIN ROTOR PITCH LINK.  THE CRACKS 	(APPROX. .180)					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005042500016	20050425	00016	EA  	2005	4	25	CA041223006      	1	20041221	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDSHIELD CRACKED DURING CRUISE AT FL330. A/C DIVERTED WHERE THE WINDSHIELD WAS REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042500017	20050425	00017	EA  	2005	4	25	CA041224001      	1	20041221	G	5610	NP1393226	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN)  RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT. FLIGHTDECK RT SIDE WINDOW CRACKED DURING APPROACH.  WINDOW	 REPLACED IN MUNICH,  AND THEN RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042500018	20050425	00018	EA  	2005	4	25	CA041224002      	1	20041220	G	2820	T99A38603	EJECTOR         			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OVERNIGHT,  APPROX 1200 LBS OF FUEL TRANSFERED INTO THE CENTER TANK.  THE FLT HAD REPORTED AN INCREASE OF 120 LBS 	IN 10 MINUTES,  HOWEVER IT WAS NOT DETERMINED IF THE FUEL TRANSFER WAS NOTED ON GROUND OR IN FLT BY THE CREW.  MAINTENAN	CE FOUND THE LT MAIN EJECTOR CRACKED.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005042500019	20050425	00019	EA  	2005	4	25	CA041224003      	1	20041104	G	5312		BULKHEAD        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26106								(CAN) MAINTENANCE FOUND TWO CRACKS ON THE 'SEMI-PRESSURE BULKHEAD' (FS559) NEAR THE AFT AILERON QUADRANT.  REPAIR WAS PE	RFORMED IN ACCORDANCE WITH REPAIR ENGINEERING ORDER (REO) 601R-53-41-256.  SUBSEQUENTLY CRACKS HAVE BEEN FOUND ON TWO AD	DITIONAL A/C: 06-DEC-04. A/C 7025 (25185FH, 20290FC)  REO 601R-53-41-263 20-DEC-04. A/C 7004 (27332FH, 21860FC)  REO 601	R-53-41-267.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042500020	20050425	00020	EA  	2005	4	25	CA041224004      	1	20041203	G	5280	CC67010520	DOOR            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RT MLG	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING THRU 16,000 FT, THE FLT CREW HEARD A STRANGE NOISE.  ALL COCKPIT INDICATIONS WERE NORMAL.  UPON POS	T FLT INSPECTION, MAINTENANCE FOUND THE RT MAIN GEAR DOOR MISSING.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005042500021	20050425	00021	EA  	2005	4	25	CA041224005      	1	20041120	G	5280	CC67010520	DOOR            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RT MLG	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) FOLLOWING DEPARTURE,  FLIGHT CREW HEARD A BUMP.  POST FLT INSPECTION REVEALED THAT THE RT INBOARD MLG DOOR WAS MIS	SING.  IN ADDITION IT WAS FOUND THAT THE RT IB FLAP SUFFERED SEVERAL DEEP GOUGES, THE RT PROXIMITY HARNESS CONDUIT WAS D	ENTED,  THE RT OB MLG DOOR WAS DAMAGED, AND THERE WAS A SCRATCH IN THE BOTTOM OF THE WING ABOVE THE INBOARD MLG DOOR.  A	 NEW DOOR WAS INSTALLED,  THE AIRCRAFT WAS REPAIRED AND RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005042500022	20050425	00022	SW  	2005	4	25	CA041224006      	1	20041101	G	6410	206016201131	BEARING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R BLADE	MISALIGNED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SUBJECT TAIL ROTOR BLADE ASSY WAS REMOVED FROM A/C DUE TO EXCESSIVE T/R VIBRATIONS AT 1.1 IPS.  OPERATOR'S OVERHAU	L SHOP PERFORMED AN INSPECTION AND AN ALIGNMENT OF SPHERICAL BEARINGS CHECK.  IT HAS BEEN DETERMINED THAT THE BEARINGS A	LIGNMENT WAS OVER LIMITS (.011 INCH VERSUS .008 INCH MAX ALLOWABLE). THE BLADE WAS REPAIRED BY REMOVING BOTH BEARINGS,  	REPLACING ONE WORN BEARING IAW BHY-206L-CR & OVERHAUL MANUAL.  UPON COMPLETION AN ALIGNMENT CHECK WAS PERFORMED WITH A R	ESULT OF .005 INCH.  THE BLADE WAS SUBSEQUENTLY RETURNED TO SERVICE WITH NO FURTHER DISCREPANCIES NOTED.		1	G	7	1 	3U	3	U		H2SW    	E4CE
2005042500023	20050425	00023	EU  	2005	4	25	CA041224009      	1	20041223	G	2820		FUEL SYS        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 1 ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AFTER DEPARTURE DURING CRUISE, A FUEL UNBALANCE WAS NOTICED AND LEAK SUSPECTED FROM NR 1 ENGINE.  ENGINE NR 1 WAS 	SECURED AND AIRCRAFT LANDED BACK TO DEPARTURE AIRPORT.  BOTH ENGINES WERE RAN AND NO LEAK WAS FOUND.  THE AUTO FEED SYST	EM WAS PUT INOPERATIVE AS PRECAUTION AND AIRCRAFT DISPATCHED AS PER MEL.  SAME OCCURRENCE ON THE FOLLOWING FLIGHT.AIRCRA	FT STILL UNDER INVESTIGATION.  DETAILS WILL FOLLOW.			2	L	7	2 	4F	4	F	RT	        	E25NE
2005042500024	20050425	00024	SO  	2005	4	25	CA041224010      	1	20041222	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					LT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L346673			(CAN) DURING AN EVENT NR 3 INSPECTION THE LT ENGINE MOUNT WAS FOUND TO BE CRACKED AT THE UPPER RT SUPPORT TUBE AT THE WE	LDING POINT WHERE IT MEETS THE RUBBER MOUNT ISCOLATOR WEB.  THIS MOUNT HAD PIPER SB 1033 CARRIED OUT AT THE UPPER LT SUP	PORT TUBE.				1	L	7	2 	3O	3	O		A19S0   	E286
2005042500025	20050425	00025	EU  	2005	4	25	CA041226001      	1	20041224	G	6520	770441	MAGNETIC SEAL   	UROCOP      		SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					T/R GEARBOX	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						MA1729					(CAN) UPON LANDING AT DESTINATION AFTER A 40 MINUTE FLIGHT.  PILOT CARRIED OUT A WALKAROUND AND NOTICED AN UNUSUAL AMOUN	T OF OIL ON TAILBOOM FROM BELOW TAIL ROTOR GEARBOX.  OIL LEVEL WAS CHECKED AND WAS FOUND TO BE DOWN A LITTLE BUT STILL I	N ACCEPTABLE RANGE LEVEL.  UPON EXAMINATION BY AME INPUT SEAL TO GEARBOX WAS COVERED IN OIL.  OIL LEVEL WAS DOWN 1/2 OUN	CE FOR 4 HOURS OF FLYING.  MAGNETIC SEAL WAS REMOVED AND EXAMINED AND IT WAS DETERMINED THAT THE CARBON RING OF THE MAGN	ETIC SEAL HAD A DEFECT.  WHEN EXAMINED WITH A MAGNIFYING GLASS A TINY DIAGONAL CRACK WAS FOUND ON THE FACE OF THE RING. 	A NEW MAGNETIC SEAL WAS INSTALLED AND GROUND RUN AND FLIGHT TEST FOLLOWED.  NO OIL LEAK EVIDENT AFTER FLIGHT.	1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005042500026	20050425	00026	EA  	2005	4	25	CA041226002      	1	20041221	G	7830	1EN2893	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THRUST REVERSER	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) RT THRUST REVERSER UNLOCKED MESSAGE IN CLIMB.  PROCEDURE ACCORDING QRH PERFORMED.  RT ENGINE SHUTDOWN DUE TO THRUS	T LEVER/THRUST SPLIT UP TO 9 PERCENT IN LEVEL FLT AT 4000 FT.  RT REVERSER FOUND STOWED.  DEACTIVATED ACCORDING TO MEL P	ROCEDURES. RESISTANCE CHECK OF THE FOLLOWING SWITCHES PERFORMED: S33EZ,  S34EZ,  S32EZ,  PDU FLEX SHAFT LOCK SWITCH AND 	PDU BRAKE SWITCH.  RESISTANCE CHECK PERFORMED.  FOUND AT THROTTLE LOCK OUT SWITCH,  ONE INTERNAL SWITCH STICKS FROM TIME	 TO TIME.  FOUND AT DEPLOYED SWITCH,  WIRING CHAFED AT CARRIER TUBE.  THROTTLE LOCKOUT SWITCH (S33EZ) PN 1EN289-3 AND DE	PLOYED SWITCH (S32EZ) PN 1EN61-6 REPLACED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2005042500027	20050425	00027	WP  	2005	4	25	CA041228001      	1	20041228	G	6710	D2781	CONTROL SYSTEM  			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					GOVERNOR	MALFUNCTIONED   	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			W			INADEQUATE Q C            			CR	CRUISE         	1			CA								L2484140A			(CAN) DURING CRUISE THE GOVERNOR WHICH CONTROLS THE ENGINE FROM AN OVERSPEED,  MALFUNCTIONED WHICH CAUSED THE ENGINE AND	 MAIN ROTOR SYSTEMS TO OVERSPEED.  DURING THE ENGINE TEARDOWN THE CRANKSHAFT GEAR WAS FOUND DAMAGED.  THE CONNECTING ROD	 BEARINGS WERE ALSO FOUND DAMAGED WITH SLIGHT SPALLING OF THE BEARINGS.  THE GOVENOR SYSTEM IS SUSPECTED AND WE ARE IN C	ONTACT WITH ROBINSON HELICOPTERS TO DETERMINE WHY THE GOVERNOR DID NOT CONTROL THE OVERSPEED.  ROBINSON HELICOPTERS HAVE	 RELAYED TO US THEY HAVE HAD FURTHER PROBLEMS WITH THE SYSTEM BUT ARE REQUIRING FURTHER INVESTIGATION.  WE WILL UPDATE W	HEN FURTHER INFORMATION IS AVAILABLE TO US.	1	G	7	1 	3O	3	O		H11NM   	E295
2005042500028	20050425	00028	NE  	2005	4	25	CA041228002      	2	20041205	G	7230	210009021	HOUSING         			BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					COMPRESSOR	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE31939			(CAN) DURING REFUELING BETWEEN HELI-LOGGING CYCLES AME ON SITE ROUTINELY OPENS ENGINE COWLS FOR AN INSPECTION OF ENGINE 	COMPARTMENT AREA.  HE NOTICED AFT ENGINE MOUNT ROD END (BELL PN 214-060-114-001) HAD COMPLETELY PULLED OUT OF ENGINE COM	PRESSOR HALF CASTING PN 2-100-090-21. ROD END HAD JAMMED ON AN ANGLE INTO THREADED HOLE PREVENTING FURTHER ENGINE MOVEME	NT AND POSSIBLE AIRFRAME DAMAGE.  AIRCRAFT IMMEDIATELY SHUTDOWN AND GROUNDED.  ENGINE REMOVED FOR REPAIR.  IT APPEARS JA	M NUT PN 214-060-121-001 WHICH SECURES ROD END INTO ENGINE HAD COME LOOSE SINCE ENGINE INSTALLED 36.6 HOURS PRIOR.  THIS	 ALLOWED MOVEMENT IN THREADS BETWEEN ROD END AND COMPRESSOR HOUSING EVENTUALLY CAUSING THREADS TO FAIL AND THE ROD END T	2	G	7	1 	4U	4	U		H6SW    	E4NE
2005042500029	20050425	00029	NM  	2005	4	25	CA041229001      	1	20041229	G	2752	113T12518	RING GEAR       			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					FLAP ACTUATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RING WAS FOUND CORRODED AND GEAR BEARING SURFACES WERE PITTED.  NR 6 FLAP ACTUATOR HAD CORROSION EMITTING FROM AFT	 SIDE OF MOUNT FLANGE.  REMOVED ACTUATOR AND INVESTIGATED SOURCE. FOUND RING GEAR CORRODED. REACTION RING INSTALLED AND 	ACTUATOR REINSTALLED PER AMM 27-51-11 AND BAC 5009.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
2005042500030	20050425	00030	NM  	2005	4	25	CA041229002      	1	20041229	G	3244	32200022	TIRE            			AIRBUS	A319  	A319114     	3930350	NM  										NLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ON LANDING THERE WAS A NOISE FROM THE NOSE GEAR AND WAS DIFFICULT TO TAXI. ON INSPECTION,BOTH NOSE WHEEL TIRES WER	E FLAT. COMPANY SAFETY REG REQ. FDR C/B PULLED. BOTH NOSE WHEELS REPLACED. CONDUIT BRACKET REPAIRED. BURST TIRE INSPECTI	ON CARRIED OUT PER AMM 05-51-15. DFDR REPLACED.				2	L	7	2 	4F			RT	A28NM
2005042500031	20050425	00031	EU  	2005	4	25	CA041229003      	1	20041229	G	2730		COMPUTER        			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					ELAC NR 2	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) F/CTL ELAC 1 PITCH FAULT,  F/CTL ELAC 2 PITCH FAULT,  F/CTL STAB.  JAM,  APPEARED ON ECAM.  ECAM PROCEDURE COMPLET	ED NORMALLY AND A/C REMAINED IN ALTN LAW.  RESET ELAC 1 & 2 VIA PUSH BUTTONS AND SYSTEM RESET ITSELF. ELAC NR 2 REPLACED	 AND TESTED PER AMM.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
2005042500032	20050425	00032	EU  	2005	4	25	CA041230001      	1	20041214	G	2910		LINE            			CASA  	C212  	C212CC      	2410204	EU  										HYDRAULIC SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DISCOVERED SMALL RUBBER PIECES IN HYDRAULIC FILTER.  PARTICLES APPEARED TO BE FROM MANUFACTURE OF HOSE ASSEMBLIES,	  RESEMBLING INTERIOR LINING OF TYPICAL HOSE.  REPLACED ALL FLEXIBLE HOSES IN HYDRAULIC SYSTEM AS IT WAS IMPOSSIBLE TO D	ETERMINE WHICH HOSE HAD CONTAMINATED THE SYSTEM.  WITH NEW HOSES IN PLACE,  THE SYSTEM WAS FLUSHED OUT TO REMOVE ANY FUR	THER CONTAMINATION AND FILTER WAS REPLACED.  THE HOSES HAD EEN IN SERVICE SINCE 2002.			2	H	7	2 	4T				A43EU
2005042500033	20050425	00033	NM  	2005	4	25	CA041230002      	1	20041230	G	7500	9639	BLEED AIR SYS   			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					RIGHT	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) R' BLEED DUCT LEAK''EICAS MSG',QRH  COMPLETED. LIGHT DUCT LEAK STAYED ON FOR 90 MINUTES, WENT OUT FOR 30 MINUTES, 	THEN CAME ON AGAIN. NOTICED THAT RT BLEED PRESSURE STAYED AT 5 PSI, NOT ZERO.  VISUAL INSPECTION OF PNEUMATIC DUCTS, CLA	MPS AND OVERHEAT DETECTION LOOP CARRIED OUT FROM MLG WW TO NR 2 ENG PYLON- NIL FAULTS FOUND. REPLACED DUCT 1 / MLG WW FI	RE DETECTION CARD M691- ENGS GROUND RUN. ALL INDICATION AND OPS NORMAL.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
2005042500034	20050425	00034	CE  	2005	4	25	CA041230003      	1	20041227	G	2121		MOTOR           	RAYTHN      		BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					BLOWER ASSY	SEIZED          	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						20					(CAN) PILOTS NOTICED SMOKE COMING FROM UNDER THE LT INSTRUMENT PANEL THAT QUICKLY STARTED TO FILL THE COCKPIT.  THEY DES	CENDED, DEPRESSURIZED AND DECLARED AN EMERGENCY.MAINTENANCE DISCOVERED THAT THE BLOWER MOTOR HAD SEIZED CAUSING THE SMOK	E IN THE AIRCRAFT.				1	L	7	2 	3T	4	T		A14CE   	E4EA
2005042500035	20050425	00035	EA  	2005	4	25	CA041231001      	2	20041217	G	8500		ENGINE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						OVERSPEED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA								L2455340A			(CAN) DURING A TRAINING FLIGHT, THE ENGINE HAD A UNCOMMAMDED OVERSPEED AND A FULL THROTTLE TO IDLE SPEED CONDITION. THE 	PILOTS RETURNED TO THE AIRPORT WHERE FURTHER INVESTIGATION COULD NOT DUPLICATE THE PROBLEM. THE PILOTS COULD NOT EXPLAIN	 TO THE REASON WHY THE AIRCRAFT HAD THESE DEFECTS. THEY SAY THEY WERE COMPLETELY UNCOMMANDED. THE AIRCRAFT OVERSPEED WAS	 ABOVE 109 PERCENT.  WE HAVE CONDUCTED AN OVERSPEED INSPECTION IAW LYCOMING SB 369J. NO DAMAGE WAS FOUND AND FURTHER INV	ESTIGATION TO THE GOVERNOR SYSTEM IS STILL ON GOING. WE HAVE INSTALLED A NEW GOVERNOR FOR SAFTEY REASONS. WE WILL UPDATE	 AS SOON AS WE HAVE MORE INFORMATION.	1	G	7	1 	3O	3	O		H11NM   	E295
2005042500036	20050425	00036	EU  	2005	4	25	CA041231002      	1	20041230	G	3810		LINE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					POTABLE WATER SY	BURST           	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF,  COULD NOT GET AIRCRAFT TO PRESSURIZE.  AIRCRAFT LANDED BACK TO DEPARTURE AIRPORT.  MAINTENANCE FO	UND BOTH PRIMARY AND SECONDARY OUTFLOW VALVES AND OUTFLOW VALVE DRAIN LINE CONTAMINATED WITH ICE.  WATER CAME FROM POTAB	LE WATER SYSTEM.  A WATER LINE BUSTED DUE TO COLD WEATHER AND WATER RESIDUAL WAS THE CAUSE OF CONTAMINATION.  BOTH VALVE	S AND DRAIN LINE REPLACED			2	L	7	2 	4F	4	F	RT	        	E25NE
2005042500037	20050425	00037	EU  	2005	4	25	CA050103001      	1	20041231	G	3222		SLEEVE          			AIRBUS	A319  	A319112     	3930323	EU  										AXEL	SEIZED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						L2325					(CAN) THE CREW REPORTED A GRINDING NOISE COMING FROM THE NOSE GEAR. ON INVESTIGATION, MAINTENANCE FOUND THE RIGHT HAND N	LG WHEEL INBOARD BEARING ASSY SEIZED ONTO THE AXEL SLEEVE. ATTEMPTS TO FREE THE SLEEVE HAVE BEEN UNSUCCESSFUL AND THE NO	SE GEAR STRUT HAD TO BE REPLACED.				2	L	7	2 	4F			RT	A28NM
2005042500041	20050425	00041	WP  	2005	4	25	CA050104003      	1	20041230	G	7711		INDICATOR       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2 ENGINE EPR	INOPERATIVE     	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT REJECTED TAKE OFF AT 65 KNOTS, DUE TO NR 2 ENGINE EPR GAUGE BEING INOPERATIVE. MAINTENANCE REMOVED EPR LI	NES AND FOUND WATER INU  PIPE OF PT7. THE WATER WAS BLOWN OUT AND DRIED. ENGINE RUN CARRIED OUT, SYSTEM FOUND SERVICEABL	E.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005042500042	20050425	00042	WP  	2005	4	25	CA050104004      	1	20041230	G	7711		LINE            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2 ENGINE EPR	CONTAMINATED    	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT REJECTED TAKE OFF  AT LESS THEN 40 KNOTS, DUE TO NR 2 ENGINE EPR DID NOT RESPOND TO THROTTLE MOVEMENT. MA	INTENANCE FOUND WATER IN EPR LINE. MAINTENANCE BLEW AIR AND CLEANEDTHE EPR LINES PT7, PT2 IAW AMM 77-1 1-03, 77-11-04. E	NGINE RUN CARRIED OUT, SYSTEM FOUND SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE
2005021400182	20050214	00182	EU  	2005	2	14	CA050104005      	1	20041227	G	2910	SD3730311	LINE            			STBROS	SD3   	SD360       	8100606	EU  										HYD PRESSURE	RUPTURED        	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) UPON SELECTING GEAR DOWN DURING APPROACH THE STATED PRESSURE LINE RUPTURED CAUSING HYDRAULIC SYSTEM TO LOSE ALL FL	UID. LANDING WAS ABORTED AND AN EMERGENCY WAS DECLARED. GEAR WAS EXTENDED USING EMERGENCY GEAR EXTENSION. AIRCRAFT LANDE	D SAFELY AND WAS TAXIED USING DIFFERENTIAL POWER FOR STEERING TO A SAFE LOCATION WHERE PASSENGERS WERE DISEMBARKED. MAIN	TENANCE REPLACED LINE, SERVICED HYDRAULIC SYSTEM AND RETURNED AIRCRAFT TO SERVICE.			2	H	7	2 	4T				A41EU
2005031100027	20050311	00027		2005	3	11	CA050104007      	4	20041209	G	3420	7012100825	RMU             			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  						FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DISPLAY SCREEN LOST YELLOW AND GREEN COLOR LEAVING ONLY RED AND BLUE.  REPLACED RMU WITH EXCHANGE UNIT.  NOTE: THI	S IS THE SECOND UNIT TO FAIL. THE FIRST FAILED WITH 264 HOURS TSN.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005031100028	20050311	00028	CE  	2005	3	11	CA050104008      	1	20041126	G	3242	21656	BRAKE ASSY      			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					MLG	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WEEPING OF HYDRAULIC FLUID PAST PISTON PACKINGS, MFG SB 2-1601-32-2 RECOMMENDS INSTALLATION OF OVERSIZE PACKINGS P	/N 68-1507 TO REDUCE THE PROBLEM.  THESE PACKINGS WERE INSTALLED WHEN THE BRAKES WERE MANUFACTURED.   APPROXIMATELY 325 	LANDINGS IS NOT VERY GOOD LIFE.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005031100029	20050311	00029	CE  	2005	3	11	CA050104009      	1	20041031	G	2435	300SG42982	STARTER GEN     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ENGINE	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) GENERATOR FUNCTION OK IN FLIGHT, AFTER SHUTDOWN.  ON ENGINE START, ENGINE WOULD NOT ROTATE.  FOUND COMMUNTATOR AND	 BRUSHES DAMAGED BY ARCING.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005031400029	20050314	00029	GL  	2005	3	14	CA050104010      	2	20041214	G	7532	23053176	BLEED VALVE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BLEED VALVE WAS INSTALLED AFTER OVERHAUL TO REPLACE A TIME EXPIRED UNIT.  SUBSEQUENT POWER CHECK REVEALED HIGH TOT	.  BLEED VALVE WAS WAS RETURNED TO VENDOR TO CORRECT FAULT.  PART WAS INSTALLED AND FAILED A SECOND TIME.  PART WAS REPL	ACED WITH ANOTHER UNIT, POWER CHECK SATISFACTORY.				1	G	7	1 	3U	3	U		H2SW    	E4CE
2005031400054	20050314	00054	EA  	2005	3	14	CA050104011      	1	20041229	G	5302	S612066120	WEB             	SKRSKY      		CARSON	S61   	S61LSKRSKY  	       	EA  	GE    	CT58  	CT581401    	30011	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A12324					(CAN) DURING A ROUTINE INSPECTION, A CRACK WAS FOUND ON THE LT FORWARD CORNER OF THE LOWER WEB FITTING.						2	G	7	2 	4U	4	U		H8EA    	1E3
2005031400055	20050314	00055	EA  	2005	3	14	CA050105001      	2	20041216	G	7414	4371	MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL699239A			(CAN) AT 500 HOUR INSPECTION, A 1.5 INCH CRACK WAS NOTICED ON THE MAGNETO COIL ADJACENT TO THE OUTPUT CONNECTOR.  MAGNET	O REMOVED FROM SERVICE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2005031400056	20050314	00056	EA  	2005	3	14	CA050105002      	2	20041221	G	7414		DISTRIBUTOR GEAR	LYC         		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						919635					(CAN) UNABLE TO START ENGINE. FOUND TWO PLASTIC TEETH MISSING FROM DISTRIBUTOR GEAR.						1	G	7	1 	3O	3	O		H10WE   	E274
2005031400051	20050314	00051	NM  	2005	3	14	CA050105003      	1	20041220	G	2780		CONTROL SYSTEM  	BOEING      		BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SLAT	FAILED          	W				J	A			DUMP FUEL               	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA			36135								(CAN) DURING CLIMB FLAPS/SLATS SELECTED UP.  FLAPS INDICATED UP, SLAT AMBER REMAINED ON AND AIRCRAFT ROLLED TO THE RT. S	ECOND OFFICERS PANEL INDICATED NR6 SLAT STILL IN TRANSIT. FLAPS AND SLATS CYCLED A NUMBER OF TIMES TO NO AVAIL. DECISION	 TO RETURN WAS MADE, 8000 LBS OF FUEL DUMPED.  AC LANDED WITHOUT FURTHER INCIDENT AND WITHOUT DECLARING AN EMERGENCY. MA	INT INSPECTED AND TESTED SLATS WITH NO FAULT FOUND ON NR6 SLAT. HOWEVER NR3 KREUGER WAS FAULTED AND REPAIRED. THIS WAS I	NCIDENTAL AND WE BELIEVE NOT RELATED TO THE NR6 SLAT PROBLEM.  IT IS SUSPECTED THAT NR6 SLAT BECAME ASKEWED INFLIGHT WHI	CH COULD NOT BE DUPLICATED ON THE GROUND.  AIRCRAFT WAS RELEASED WITH NO FURTHER FAULT ON THE NEXT FLIGHTLEG.	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005031400052	20050314	00052	EA  	2005	3	14	CA050105004      	2	20041215	G	8500		ENGINE          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LEFT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								RL194661			(CAN) AFTER TAKEOFF THE LT ENGINE ENCOUNTERED RPM FLUCTUATIONS, THE AIRCRAFT RETURNED TO THE AIRPORT. AFTER SOME DISCUSS	ION WITH THE MECHANICS, THE PILOTS DRAINED THE AIRCRAFT AGAIN AND CARRIED OUT A GROUND RUN. EVERYTHING RETURNED TO NORMA	L. THE AIRCRAFT DEPARTED RIGHT AFTER THE TANKS WERE FILLED.  WHEN THE AIRCRAFT RETURNED TO BASE, WE VERIFIED AND CLEANED	 ALL THE INJECTORS AND DRAINED THE AIRCRAFT, ALL THE ENGINE FUEL LINES WERE PURGED AS WELL. THERE WAS NO WATER IN THE TA	NKS AND NO INJECTORS WERE CLOGGED.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005031100033	20050311	00033	EA  	2005	3	11	CA050105007      	2	20041130	G	8520		CAMSHAFT        			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2685451A			(CAN) AIRCRAFT IS OPERATED BY BUSY FLIGHT TRAINING UNIT NO COMPLAINTS OF ENGINE MALFUNCTIONS HAD BEEN REPORTED. ENGINE W	AS RUN UP, FOUND NORMAL, PRIOR TO INSPECTION.  OIL SUCTION SCREEN WAS INSPECTED AND FOUND CLEAN.  OIL PRESSURE FILTER WA	S CUT OPEN AND A SMALL AMOUNT OF STEEL FILINGS WERE FOUND ON FURTHER INVESTIGATION BY REMOVING NR 1 AND 3 CYLINDERS.  TH	E AFT INTAKE LOBE ON THE CAMSHAFT WAS FOUND TO BE ALMOST NON-EXISTENT.  THE ENGINE WAS SENT TO AN OVERHAUL SHOP FOR REPA	IRS.		1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA
2005031400060	20050314	00060	NE  	2005	3	14	CA050105010      	2	20041212	G	7261		CASE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								AE0015			(CAN) DURING CRUISE CREW IDENTIFIED LOW OIL PRESSURE.  THE ENGINE WAS SHUTDOWN AND THE FLIGHT DIVERTED.  INSPECTION REVE	ALED LOW ENGINE OIL QUANTITY AND SUBSEQUENT INVESTIGATION FOUND OIL LEAKAGE FROM THE FRONT INLET CASE DRAIN LOCATION.  M	FG WILL INVESTIGATE THE INCIDENT AND SUPPLEMENT THIS REPORT TO IDENTIFY ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
2005031400057	20050314	00057	NE  	2005	3	14	CA050105011      	2	20041224	G	7261		TUBE            			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					OIL TRANSFER	FRACTURED       	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								120089			(CAN) DURING CRUISE ENGINE TEMPERATURES INCREASED ACCOMPANIED BY SMOKE AND EXHAUST ODOR IN THE CABIN.  THE CREW REDUCED 	ENGINE POWER. FIRE WARNING INDICATION ACTIVATED 12 MINUTES LATER AND THE CREW CARRIED OUT FIRE SUPPRESSION PROCEDURE AND	 SHUTDOWN THE ENGINE IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FRACTURED NR 6 AND NR 7 BEARING OIL TRANSFER TUBE, A B	URNED FIRE HARNESS LOOP AND METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR.  MFG WILL INVESTIGATE THE EVENT AND WILL SUPPLE	MENT THIS REPORT TO PROVIDE ROOT CAUSE ONCE DETERMINED.		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE
2005031400058	20050314	00058	NE  	2005	3	14	CA050105012      	2	20041223	G	7532	30B1695	SENSE LINE      			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					P 2.8	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) CREW REPORTED COMPRESSOR STALL DURING TAKE-OFF.  SUBSEQUENT INVESTIGATION REVEALED A BROKEN P2.8  BLEED VALVE (BOV	) SENSE LINE.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
2005031400059	20050314	00059	NM  	2005	3	14	CA050105013      	1	20041229	G	3233	65404676	ACTUATOR        			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					NLG DOWNLOCK	SEPARATED       	W				O				OTHER                   				D	K	J	INFLIGHT SEPARATION       	FLUID LOSS                	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE CREW OBSERVED 'A' (HYDRAULIC) SYSTEM DEPLETION. SYSTEM DESELECTED, NORMAL LANDING CARRIED OUT. TH	E NOSE LANDING GEAR DOWN LOCK ACTUATOR SEPARATED FROM THE AIRFRAME MOUNT AND HAD DAMAGED THE HYDRAULIC LINES.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2005041200044	20050412	00044	SO  	2005	4	12	CA050106003      	1	20041220	G	2913	1213HBG310	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) TOOK OFF, ENROUTE, AIRCRAFT WAS ON A BASE RELOCATION FLIGHT.  PILOT HAD GEAR IN-TRANSIT LIGHT FOR LONGER THAN NORM	AL AFTER GEAR WAS SELECTED UP.  RE-SELECTED GEAR DOWN AND LOCKED 3 GREEN.  RE-SELECTED GEAR UP AND STILL HAD IN-TRANSIT 	LIGHT.  CONTINUED WITH GEAR HANDLE SELECTED UP AND IN-TRANSIT LIGHT ON.  AC LANDED WITHOUT INCIDENT, MAINT DISCOVERED HY	DRAULIC OIL UNDER COWL.  FURTHER INVESTIGATION REVEALED A CRACKED RT HYDRAULIC PUMP HOUSING.  PUMP HAS BEEN CHANGED AND 	HYDRAULIC SYSTEM INSPECTED, SERVICED AND OPERATED ON THE GROUND, NO ABNORMALITIES NOTED. NOTE: HYDRAULIC PUMP REMOVED DI	D NOT HAVE A DATA PLATE ALTHOUGH RECORDS DID INDICATE THAT IT WAS A ZERO TIMED UNIT AT ENGINE CHANGE IN 1998.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005042500044	20050425	00044	NE  	2005	4	25	CA050107001      	2	20041128	G	7320	8237006	HMU             			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					RT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE WOULD NOT START.						2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN
2005042500047	20050425	00047	EA  	2005	4	25	CA050107006      	2	20041229	G	7200		ENGINE          			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			19181					PCE86394			(CAN)  APPOX 20 MINS INTO FLT, & AT FLT LEVEL 120 ENROUTE TO DIKO FROM DIBK WITH 19 PAX, MASTER CAUTION LIGHT ILLUMINATE	D ACCOMPANIED WITH NR 2 ENG LOW OIL PRESSURE LIGHT.  NR 2 OIL PRESSURE GAUGE CONFIRMED ACTIVE WARNING LIGHT WITH PRESSUR	E INDICATION OF BELOW 75 PSI & DECREASING. ENG SHUTDOWN CARRIED OUT IAW QRH CHKLST. ENG SECURED & FLT DIVERTED TO ABIDJA	N.  UNITED NATIONS FLT FOLLOWING CENTRE 'AMIGO BASE' INFORMED ON HF FREQUENCY OF SIT & ASKED TO INFORM ALL FORCE NOUVELL	E MILITARY GROUND TO AIR SECURITY SURVEILLANCE & DEFENSE SITES INCLUDING FRENCH AIR FORCE OF OUR NEW ROUTING & ALTITUDE 	& CANCEL OF PREVIOUSLY SCHEDULED AIR TASKING ORDERS. FLT TERMINATED WITHOUT ANY FURTHER INCIDENTS BACK IN ABIDJAN.	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
2005042500048	20050425	00048	NM  	2005	4	25	CA050107007      	1	20041211	G	2913	570717	SHAFT           	EATON       		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD PUMP	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			37321	16534		MX459159C					(CAN)  NR 1 ENG HYD PUMP CAUTION LIGHT ILLUMINATED WITH FLAP RETRACTION ON TAKEOFF. NR 1 SPU TURNED OFF,  MAIN PRESSURE 	DEPLETED TO 0 PSI.  FLUID QTY REMAINED STEADY. A/C RETURNED TO YYZ.  INPUT SHAFT SHEARED FROM AN INTERNAL FAILURE.  PUMP	 DISMANTLED.  INTERNAL DAMAGE FROM 2 BROKEN PISTONS (PN 404783), CAUSING DAMAGE TO OTHER PARTS.  (PISTON SHOE PLATE PN 3	96386 & RETAINER PN 405892) ALSO HARDWARE DAMAGE NOTED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005021400183	20050214	00183	EA  	2005	2	14	CA050110001      	1	20041229	G	2150	GG67095009	ACM             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					BOTH	SEIZED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT RETURNED TO FIELD AFTER LAV SMOKE DETECTOR WENT OFF AND VISIBLE SMOKE IN CABIN.  AN EMERGENCY WAS DEC	LARED AND AN EMERGENCY EVACUATION WAS PERFORMED AFTER LANDING.  NOTE: IT WAS REPORTED THAT SOMEONE BROKE BOTH ANKLES DUR	ING THE EVACUATION FROM THE OVERWING ESCAPE.  BOTH ACMS WERE REPLACED.  INVESTIGATION REVEALED THAT ONE ACM WAS ON MMEL 	AND THE AIRCRAFT WAS OPERATING ON ONE ACM.  DURING THE TAKEOFF THAT OTHER ACM LOCKED UP.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN
2005042000085	20050420	00085	SO  	2005	4	20	CA050110004      	1	20041208	G	2450	5AMP	CIRCUIT BREAKER 			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELECTRICAL	DAMAGED         	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA							7400992				(CAN) AC WAS RETURNING WHEN RT ALT WENT OFF-LINE, 5 MIN LATER LT ALT SYS WENT OFF-LINE. BATTERY, LT ALT, BOTH VOLT REG, 	 LT OVER-VOLT RELAY, LT VOLT REG CB WERE REPLACED.  NO TEST FOR OVER-VOLT RELAY SPECIFIED IN MM, IN ELEC SYS OF MM A 500	 HOUR OVER-VOLT RELAY OPS CHECK IS RECOMMENDED, HAS BEEN ADDED TO AC`S TBO SHEET.  LT 5 AMP FIELD (VOLTAGE REG) CB.  WHE	N IT WAS MEASURED AFTERWARDS A VOLTAGE DROP/RESISTANCE WAS NOTED ACROSS IT.  WOULD CAUSE VOLT REG TO THINK BUSS VOLTAGE 	WAS LWR THAN IT ACTUALLY WAS.  IN THIS CASE 28.2V WAS MEASURED AT FIELD TERMINAL ON VOLT REG WHILE 30.5V WAS MEASURED AT	  BUSS. THIS WOULD CAUSE RT ALT SYS TO GO OFF-LINE DUE TO IMBALANCE. LT ALT SYS WOULD CONTINUE IN THIS MANNER.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
2005031400032	20050314	00032	EA  	2005	3	14	CA050110006      	2	20041229	G	7200		ENGINE          			DHAV  	DHC7  	DHC7100     	2802404	EA  	PWA   	PT6   	PT6A50      	52043	EA  						INOPERATIVE     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE ENGINE EXPERIENCED AN OIL PRESSURE LOSS IN CRUISE.  THE CREW SHUT THE ENGINE DOWN AND DIVERTED FLIGHT.  SUBSEQ	UENT INSPECTION REVEALED METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR AND IN THE ENGINE OIL FILTER.  MFG WILL MONITOR THE	 INVESTIGATION OF THIS EVENT AND SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE ONCE DETERMINED.				2	H	7	4 	4T	4	T		A20EA   	E4EA
2005031400033	20050314	00033	NE  	2005	3	14	CA050110007      	2	20041226	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						INOPERATIVE     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THE CREW REPORTED A LOW OIL PRESSURE WARNING FOLLOWING TAKE-OFF.  THE CREW SHUT THE ENGINE DOWN IN FLIGHT AND DIVE	RTED TO POINT OF DEPARTURE. MFG WILL INVESTIGATE THE EVENT AND SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERM	INED.				2	H	7	2 	4T	4	T	RT	        	E20NE
2005042500051	20050425	00051	EA  	2005	4	25	CA050110008      	2	20041210	G	7200		ENGINE          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NR 1	FAILED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AFTER TAKE-OFF, THE NR 1 ENGINE REPORTEDLY LOST POWER. THE AIRCRAFT SETTLED TO THE GROUND, DEPARTED THE RUNWAY AND	 WAS CONSUMED BY FIRE. PWC WILL INVESTIGATED THE ENGINE AND WILL SUPPLIMENT THIS REPORT TO PROVIDE ROOT CAUSE, AS AND WH	EN DETERMINED.				1	L	7	2 	4T	4	T		A24CE   	E4EA
2005031100021	20050311	00021	EA  	2005	3	11	CA050117010      	2	20041204	G	7200		ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA								56857			(CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN UNDER UNKNOWN CIRCUMSTANCES.  SUBSEQUENT DISASSEM	BLY REVEALED A SEIZED COMPRESSOR ROTOR AND METAL DEBRIS IN THE ENGINE OIL FILTER AND CHIP DETECTOR.  MFG WILL MONITOR TH	E INVESTIGATION OF THIS EVENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, AS AND WHEN IT IS DETERMINED.				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA	6	C	P15EA
2005042000089	20050420	00089	EU  	2005	4	20	CA050119004      	1	20041213	G	5532	350A1402000901	SKIN            	UROCOP      		SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					VERTICAL FIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						TB3536					(CAN) CRACK WAS FOUND AT VERTICAL FIN.  THIS FIN WAS SENT TO MFG FOR REPAIR.						1	G	7	1 	3U	3	U		H9EU    	E00054EN
2005041200005	20050412	00005	NM  	2005	4	12	CA050120002      	1	20041028	G	5751	65C25920	BALANCE WEIGHT  	BOEING      		BOEING	737   	737248C     	1384415	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT AILERON	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						92					(CAN) DURING HEAVY MAINTENANCE THE RT AILERON WAS DISCOVERED IN AN IMPROPER CONFIGURATION. THE BALANCE WEIGHT ASSOCIATED	 WITH A COMPOSITE UNIT WAS FOUND TO BE INSTALLED WHEN THE AILERON WHICH WAS REMOVED FOR REPAINT COULD NOT BE BALANCED AT	 REINSTALLATION. THE BALANCE WEIGHT IS USED ON 65C25911 COMPOSITE SERIES AILERONS. THE DATE OF INSTALL IS NOT KNOWN.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2005042500070	20050425	00070	NE  	2005	4	25	CA050121005      	1	20041125	G	5510	2220021	FITTING         			CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HC92Z	HC92ZK8     	GL  	HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSP, IT WAS NOTICED THAT AC DID NOT COMPLY WITH REQUIREMENTS OF AD98-10-12 WITH REF TO SB78 HORIZON	TAL STABILIZER INSP AND REWORK. AD98-10-12 WAS SIGNED OUT IN THE TECH RECORDS ON SEPT 1,1998 AT 1683.22 TT. REMOVAL OF F	ITTINGS REVEALED P/N 2-2200-21 LT FITTING TO BE CRACKED.  HAVE HAD SEVERAL INSTANCES WHERE AD98-10-12 HAD BEEN SIGNED OU	T WHILE NOT MEETING THE REQUIREMENTS OF THE AD AND SB.  FAILURE OF THE HORIZONTAL STABILIZER FITTINGS IS IMMINENT IF THE	SE CRACKS ARE LEFT UNDETECTED. RECOMMEND MAINTAINERS OF LAKE AC REEVALUATE THE REQUIREMENTS OF AD98-10-12 AND SB78 AND M	AKE SURE THEIR AC MEETS THESE REQUIREMENTS BY ENSURING THAT SB78 WAS CARRIED OUT CORRECTLY.	1	H	7	1 	3O	3	O		1A13    	E286	5	C	P892
2005042000102	20050420	00102	EU  	2005	4	20	CA050124010      	1	20041222	G	7830		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					NR 1	MALFUNCTIONED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA								124446			(CAN) DURING LANDING ROLL, ONE ENGINE DID NOT RESPOND CORRECTLY TO SELECTION OF REVERSE THRUST. AS A RESULT, THE AIRCRAF	T DEPARTED THE RUNWAY.  VARIOUS ENGINE ACCESSORIES HAVE BEEN REMOVED FOR EVALUATION.   MFG WILL MONITOR THE INVESTIGATIO	N AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E2ONE
2005041200021	20050412	00021	SO  	2005	4	12	CA050125015      	2	20040716	G	8520		PISTON          			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	DISINTEGRATED   	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) ENGINE HAD 450 HOURS SINCE TOTAL O/H, WAS PERFORMING NORMAL. CYL LEAK TEST WERE MIN. 60/80 AND OIL CONSUMPTION WAS	 1 LT-13 HRS.  AC WAS IN BASE LEG WITH POWER REDUCED GRADUALLY BACK TO 20 IN., PROP NEAR FINE,  MIXTURE NEAR RICH.  VIBR	ATION STARTED IN ENGINE, IT WAS LOOSING RPM AND POWER. TANKS WERE SWITCHED AND BOOST PUMP ACTIVATED BUT WITH NO RESULTS.	 GEAR WAS RETRACTED, MORE FLAP ADDED.  A CRASH INTO TREES CARRIED OUT ABOUT A MILE SHORT OF RUNWAY.  DISCOVERED THAT THE	RE WAS A HOLE IN THE CASE NEAR NR 5 CYL.  NTSB FINDINGS CONCLUDED THAT NR 5 PISTON DISINTEGRATED, OTHER 5 PISTONS HAD NO	RMAL WEAR FOR 450 HRS. NO INDICATION OF ANY PROBLEMS FROM VIBRATION START UNTIL STOPPED IN TREES IS 25 SECONDS.	1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL
2005021400189	20050214	00189	EA  	2005	2	14	CA050126012      	1	20041019	G	2435	03600923	BEARING         	LUCAS       		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	STARTER GEN	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			22546			978					(CAN) DEFECT 422403, STARTED NR 2 DID NOT DISENGAGE AFTER START, QRH WAS FOLLOWED, DC GEN CAUTION LIGHTS REMAINED ON, NO	 HIGH DISCHARGE BATTERY STARTER GEN SENT TO SHOP.  UNIT INSPECTED, CONFIRMED BEARING FAILURE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005042000126	20050420	00126	EA  	2005	4	20	CA050128007      	1	20041120	G	5753		HINGE BRACKET   			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOOSE RIVETS ATTACHING CENTER FLAP HINGE BRACKET TO IB AND OB PORTIONS OF FORE FLAP ASSY.  HIDDEN PROBLEM DOES NOT	 REALLY SHOW UP UNTILL YOU TAKE THE FLAP OFF.  FORE FLAP DISASSEMBLED AND RIVETS REPLACED WITH NEW.					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA
2005061700015	20050617	00015	EU  	2005	6	17	CA050207003      	1	20041205	G	6730	M02801H003101	PISTON ROD      	AGUSTA      		AGUSTA	A109  	A109E       	0260119	EU  	PWA   	PW206 	PW206B      	0	NE  					ACTUATOR	CORRODED        	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						0066					APPARENT CORROSION PITS ON SURFACE OF PISTON ROD LEADING TO SMALL HYDRAULIC LEAKS, DESIGN HAS BEEN CHANGED TO REPLACE AR	COR FINISH OF PISTON ROD BY CHROME.  NOTE THAT PART NUMBER OF ACTUATOR IS 109-0900-39-103 AND ORIGINAL MANUFACTURER OF A	CTUATOR IS MECAER S.P.A.				1	G	7	2 	3U	3	U	RT	H7EU    	E42NE
2005042500131	20050425	00131	NM  	2005	4	25	CA050211008      	1	20041219	G	2120	21178041	COMPUTER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CABIN PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			14473	14473							(CAN) ON CLIMB OUT WITH CABIN PRESSURIZATION SET TO AUTO IN BOTH NORMAL AND CAB SET MODE THE RATE OF PRESSURIZATION WAS 	UNCONTROLLABLE UP TO MAX DIFF.A/C RETURNED TO DEPT AIRPORT. SYSTEM OPERATED SERV IN MANUAL MODE. COMPUTER REPLACED AND F	UNCTION CHECKS CARRIED OUT SERV.NO STRIP REPORT FROM REPAIR FACILITY AS OF YET.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005042500157	20050425	00157	SW  	2005	4	25	CA050216010      	1	20040911	G	6322		HANGER ASSY     	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COOLER BLOWER	ROTATED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA						SHL017					(CAN) PILOT REPORTED A HIGH FREQUENCY VIBRATION.  UPON INVESTIGATION, THE BEARING IN THE FORWARD HANGER ASSEMBLY OF THE 	OIL COOLER BLOWER WAS FOUND TO BE ROTATING.  BLOWER ASSEMBLY REPLACED.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005042500162	20050425	00162	EA  	2005	4	25	CA050221002      	1	20040920	G	2820	C38214	SEAL            			DHAV  	DHC6  	DHC6300     	2802606	EA  										FUEL CAP	CRACKED         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			50862								(CAN) DURING FLIGHT FUEL FUMES ENTERED IN THE AIRCRAFT CABIN.  AFTER LANDING 3 PAX WERE TAKEN TO THE HOSPITAL DUE TO FEE	LING SICK FROM THE FUMES.  FUEL CAP WAS SUSPECTED TO BE LEAKING WHICH CAUSED THE FUEL TO ENTER THE CABIN THRU THE PAX DO	OR SEAL.  FUEL CAP WAS REPLACED.  PROBLEM HAS NOT REOCCURED.				1	H	7	2 	3T			RT	A9EA
2005050300115	20050503	00115	SW  	2005	5	3	CA050228012      	1	20040908	G	6710	D2A201030C	BELLCRANK       			KAMOV 	KA32  	KA32A1      	       	SW  	AMTR  	VK1A  	KLIMOVK1A   		GL  					COLLECTIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DISCOVERED DURING POST FLIGHT INSPECTION.   MFG HAS ISSUED A LETTER REGARDING THIS ITEM IN JAN. 2001. MAINTE	NANCE CREWS CHECK THIS AREA AT LEAST TWICE DAILY.					1	G	7	2 	4U	4	J	NC	        	EXPE4J
2005050300038	20050503	00038	SO  	2005	5	3	CA050308015      	2	20041007	G	8520	654101A7R	CRANKCASE       			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								282770R			(CAN) CRANKCASE FAILURE (7TH STUD CRANKCASE) AS RESULT OF A RECENT FAILURE.   DURING CHANGE ON CYL NR1, SPECIAL ATTENTIO	N WAS PAID TO NR2, NR3 INTERMEDIATE BRG SADDLE.  INSP CONCLUDED THAT MOVEMENT OF BRGS HAD OCCURRED, TEARDOWN OF ENG WOUL	D BE REQUIRED FOR INVESTIGATION.  FOUND THAT THERE WAS FRETTING OF CRANKCASE ON NR2, NR3 INTERMEDIATE MN BRG THRU-BOLT P	ADS. PINCH FIT IS LOST ON MN BRGS IN THESE POSITIONS, THEY BECOME LOOSE. NOTE: BRGS ON BOTH SIDES OF CRANKCASE WERE MOVI	NG IN NR2, NR3 INTERMEDIATE BRG POSITIONS.  BRG IS ABLE TO MOVE IN BRG SADDLE (NOT ROTATIONAL). FURTHER OPS WOULD HAVE A	LLOWED INCREASED MOVEMENT OF THE BRG, BLOCKING OR RESTRICTING OIL FEED GALLERY IN SADDLE, CAUSE OIL STARVATION.	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA
2005052300119	20050523	00119	CE  	2005	5	23	CA050315007      	1	20041110	G	5210	99120754	SEAL            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					PAX DOOR	LEAKING         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CABIN AIR LEAK PAST CABIN DOOR SEALS IN FLIGHT WITH CABIN DIFFERENTIAL PRESSURE GREATER THAN APPROXIMATELY 7 PSI. 	 BOTH DOOR SEALS REPLACED AND SHIMMED TO GIVE CORRECT GAP BETWEEN DOOR SEAL AND CABIN DOOR FRAME.  NOTE: THE GAP WAS INC	ORRECTLY SET BY THE AIRCRAFT MANUFACTURER WHEN THE AIRCRAFT WAS BUILT.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN
2005052300088	20050523	00088		2005	5	23	CA050324005      	4	20040929	G	3444	9650676008	INVERTER        			AMD   	FALC90	FALCON900B  	2730171	EU  										GPWS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE GPWS FAILED IN FLIGHT. THE CONNECTOR PLUG ON THE GPWS INVERTER WAS CLEANED OF MOISTURE AND THE SYSTEM WAS TEST	ED SERVICEABLE.					2	L	7	3 	4F			RT
2005052300087	20050523	00087	EU  	2005	5	23	CA050324007      	1	20040929	G	3020	6911B030100	ANTI-ICE VALVE  			AMD   	FALC90	FALCON900B  	2730171	EU  										NR 1 ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE FLIGHT CREW NOTICED THAT THE NR 1 ENGINE ANTI-ICE VALVE WOULD NOT CLOSE UNLESS POWER WAS REDUC	ED TO IDLE. THE VALVE WAS REPLACED AND A SATISFACTORY ENGINE RUN WAS CARRIED OUT.					2	L	7	3 	4F			RT
2005052300086	20050523	00086	CE  	2005	5	23	CA050324009      	1	20040929	G	3260	65430087	UPLOCK SWITCH   			CESSNA	560   	560XL       	2076702	CE  										NLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA							5026				(CAN) AFTER TAKEOFF, THE LANDING GEAR WOULD NOT RETRACT, THE AIRCRAFT RETURNED TO THE AIRPORT. THE NOSE GEAR UPLOCK SWIT	CH WAS FOUND TO BE FAILED. THE SWITCH WAS REPLACED, MULTIPLE SATISFACTORY GEAR SWINGS WERE CARRIED OUT AND THE AIRCRAFT 	WAS RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A22CE
2005052300065	20050523	00065		2005	5	23	CA050331003      	4	20040706	G	3422	7003360941	COMPUTER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AHRS	UNSERVICEABLE   	W				O	H			OTHER                   	DEACTIVATE SYST/CIRCUITS			I			FLT. ATTITUDE INST.       			CR	CRUISE         	1			CA											(CAN) IN FLIGHT, NR2 HSI TOPPLED AND UNABLE TO RESET. LANDED, REPLACED AHRS WITH SERVICEABLE UNIT, FUNCTION CHECK AND FO	UND SERVICABLE.  SINCE THE AHRS WAS SENT OUT ON SPEX EXCHANGE WE DIDN'T RECEIVE A STRIP REPORT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005052300062	20050523	00062	NM  	2005	5	23	CA050331004      	1	20040712	G	5610	8SC0043013	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON ROUTINE INSPECTION FOUND CAPT WINDSHIELD DELAMINATED BEYOND ALLOWABLE LIMIT IAW MML.  WINDSHIELD REPLACED FUN	CTION CHECKS CARRIED OUT AND FOUND TO BE SERVICEABLE.  WINDSHIELD WAS QUARENTINE SINCE IT IS UNREPAIRABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005071200024	20050712	00024	EA  	2005	7	12	CA050406006      	2	20040404	G	7310		FITTING         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FUEL LINE	LEAKING         	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ENGINE LOST POWER, SUBSEQUENT INSPECTION REVEALED A LOOSE FITTING ON THE INLET SIDE OF THE MECHANICAL FUEL PUMP CA	USING PUMP TO DRAW AIR THUS DEPLETING THE FUEL TO THE CARBURETOR. THE FITTING WAS TIGHTENED AND LOCK FLUID WAS USED ON T	HE JAM NUT ONLY, NOT THE FITTING				1	L	7	1 	3O	3	O		2A13    	E274
2005051900225	20050519	00225	NE  	2005	5	19	CA050419002      	2	20041125	G	7200		ENGINE          			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  						INOPERATIVE     	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								12516			(CAN) DURING TAKEOFF, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  MFG WILL MONITOR THE INVESTIGATION OF THIS	 INCIDENT AND WILL ADVISE OF ROOT CAUSE, ONCEESTABLISHED.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA
2005071500136	20050715	00136	NM  	2005	7	15	CA050519002      	1	20040920	G	3240	2661942	HOUSING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	BRAKE ASSEMBLY	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED OVERHAUL OF THE BRAKE ASSEMBLY, THE ASSEMBLY WAS PRESSURE TESTED, IT WAS THEN THAT IT WAS DISCO	VERED THAT ON ONE OF THE PISTON HOUSINGS WAS LEAKING WHEN THE SYSTEM PRESSURE WAS BROUGHT TO THE MAXIMUM RATED PRESSURE.	  THE UNIT WAS DISASSEMBLED AND SENT FOR NDT, WHERE THEY FOUND THAT THE HOUSING HAD A CRACK IN THE SIDEWALL OF A PISTON.	  IT WAS DETERMINED THE CRACK WAS BEYOND LIMITS. THE UNIT WAS SCRAPPED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2005071400092	20050714	00092	NE  	2005	7	14	CA050615010      	1	20041231	G	7920	23001955	HOUSING         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENG OIL BYPASS	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CL	CLIMB          	1			CA											(ENGINE OIL FILTER) BYPASS INDICATOR HOUSING CRACKED.						1	G	7	2 	3U	3	U		H1NE    	E1GL
2005090600010	20050906	00010	SW  	2005	9	6	CA050616006      	1	20040611	G	2842	EA4703587	TRANSMITTER     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL INDICATOR	UNSERVICEABLE   	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) FUEL QUANTITY INDICATION FLUCTUATES AT NEAR FULL FUEL LEVELS. UPPER SENDING UNIT REPLACED. THIS INSTALLATION WAS 2	49.9 HOURS.					1	G	7	1 	3U	3	U		H2SW    	E4CE
2005090700006	20050907	00006	SW  	2005	9	7	CA050616007      	1	20040501	G	6330	204030913005	WASHER          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					XMSN MOUNT	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CONICAL WASHER FOR TRANSMISSION MOUNT BOLT - LT AFT POSITION - FOUND CRACKED. CRACK HAD NOT TRAVELLED COMPETELY TH	ROUGH WASHER, IT HAD STARTED AT OUTBOARD EDGE. WASHER REPLACED.					1	G	7	1 	4U	4	U		H4SW    	E22EA
2005090600011	20050906	00011	SW  	2005	9	6	CA050616008      	1	20040727	G	6310	406340104101	SEAL            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENG TO XMSN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FORWARD PTO SEAL REMOVED DUE TO OIL TRANSFER FROM ENGINE TO TRANSMISSION.  UPON SEAL REMOVAL IT WAS FOUND THE IB S	EAL LIP HAD BEEN FOLDED UNDER THE SEAL AT 2 LOCATIONS, APPROXIMATELY 1 INCH EACH. THE TENSION SPRING FROM THE SEAL HAD S	TAYED ON THE SEAL, A BARELY DETECTABLE WEAR POINT WAS CREATED AT THIS LOCATION.  THIS WEAR POINT IS APPROXIMATELY 0.030 	INCH FROM THE RUNNING SURFACE OF THE SEAL.   ALSO FOUND AT SEAL REMOVAL WAS TWO OTHER TENSION SPRINGS BEHIND THE SEAL, T	HERE WAS NO DETECTABLE DAMAGE NOTED FROM THESE SPRINGS.  NEW SEALS INSTALLED FORWARD AND AFT POSITIONS, A/C GROUND RUN, 	LEAK CHECKED AND RETURNED TO SERVICE.	1	G	7	1 	3U	3	U		H2SW    	E4CE
2005090600022	20050906	00022	CE  	2005	9	6	CA050802004      	1	20040827	G	6120	MS21042L4	NUT             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	LT PROPELLER	LOOSE           	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, THE CREW NOTICED THE LT ENGINE TORQUE WAS OVER RED LINE, POWER WAS REDUCED.  MAINTENANCE LATER DIS	COVERED THAT PART OF THE LOW PITCH ARM WAS BROKEN OFF.   IT WAS DETERMINED THAT THE NUT PN MS21042L4 HOLDING THE PIN PN 	100-960036-1 HAD BECOME LOOSE AND THIS ALLOWED THE LOW PITCH ARM TO CONTACT THE PROP BULKHEAD AND BREAK OFF.  THE POWER 	SECTION WAS REPLACED FOR LIGHT OVERHAUL.			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA
2005090600032	20050906	00032	SW  	2005	9	6	CA050804002      	1	20040629	G	6410	206016201131	BLADE           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAIL ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON PILOT DAILY INSPECTION DAMAGE NOTED TO T/R BLADE ASSY.  BLADE ASSY VISUALLY INSPECTED AND FOUND DAMAGED BEYON	D ACCEPTABLE LIMITS.   BLADE REPLACED.					1	G	7	1 	3U	3	U		H2SW    	E1GL
2005110800063	20051108	00063	GL  	2005	11	8	CA051003016      	1	20041029	G	7810	10351002	EXHAUST HEADER  			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR5 EXHAUST HEADER FOUND CRACKED 75 PERCENT OF THE WAY AROUND JUST BELOW FLANGE WELD.						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA
2005110800029	20051108	00029	WP  	2005	11	8	CA051006001      	1	20041027	G	2910	MS2190512D	FITTING         			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					HYD LINE	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AIRCRAFT RETURN TO BLOCK AFTER LOSS OF HYDRAULIC FLUID.  AFTER INVESTIGATION MAINTENANCE FOUND FROM LT ENGINE DRIV	E HYDRAULIC PUMP PRESSURE LINE AND AC HYDRAULIC PUMP, T-FITTING AT FS 319 CRACKED.  THE FITTING WAS REPLACED, SYSTEM REP	LENISHED AND LEAK CHECK SERVICEABLE. AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4R	4	T		6A6     	E282
2006010500178	20060105	00178	SW  	2006	1	5	CA051108009      	1	20041120	G	5711	2722136006	FITTING         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			43098								(CAN) DURING A ROUTINE PHASE INSPECTION OF THE WING AND CENTER SECTION OF THE AIRCRAFT, SMALL CRACKS WERE FOUND IN THE R	T WING AFT SPAR WING TO FUSELAGE ATTACH FITTINGS (PN 27-22136-006 AND 27-22135-006).   THE CRACKS WERE FOUND VISUALLY AN	D CONFIRMED USING EDDY CURRENT. THE MANUFACTURER WAS CONTACTED FOR A REPAIR AND ANALYSIS AND DETERMINED THE SPAR FITTING	S REQUIRED REPLACING.   NEW FITTINGS WERE PROCURED AND REPLACED.  THE MANUFACTURER DID NOT FEEL IT WAS NECESSARY TO DO A	 FLEET INSPECTION ON THESE SPAR FITTINGS DUE TO THIS ONE INSTANCE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE
2006062200093	20060622	00093	SW  	2006	6	22	CA051115006      	1	20040705	G	5230		STRUCTURE       			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5059 								ON MAINTENANCE SHUTDOWN DURING A NORMAL HELI LOGGING DAY, DURING INSP OF FLIGHT CONTROLS THE APPRENTICE NOTICED SOME SMO	KING COMING FROM THE BOTTOM CORNER OF THE STBD OCTAGONAL CARGO DOOR.  UPON FURTHER INSP IT WAS DETERMINED TO BE A CRACK.					1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA
2006062100078	20060621	00078	SW  	2006	6	21	CA060117004      	1	20041105	G	5511	4300143	SPAR            			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											INSPECTION OF THE AIRCRAFT FOUND THE HORIZONTAL STABILIZER UPPER HORIZONTAL SPAR CRACKED.  CRACKED SPAR REMOVED AND NEW 	PART INSTALLED.					1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU
2006070500247	20060705	00247	EA  	2006	7	5	CA060208010      	1	20040507	G	7120	73512562	MOUNT           			DHAV  	DHC6  	DHC6300     	2802606	EA  										RT ENG	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F	R	J	FLT CONT AFFECTED         	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			CA			38359								(CAN) AFTER LIFT-OFF IT WAS NOTICE A POWER LOSS ON THE RT TORQUE GAUGE. THE WEATHER CONDITIONS WERE VERY BAD THE POWER W	AS REDUCED AND THAN THE A/C LANDED 2 MINUTES AWAY.  WHEN THE A/C WAS SECURE AND ENGINE SHUT OFF IT WAS NOTICED THAT THE 	ENGINE MOUNTS ON THE RT ENGINE WERE BROKEN AND THE COWLING OPENED 2 INCH WITH SOME POPPED LATCHES.  RT FLIGHT CONTROLS W	ERE FOUND DAMAGED. (TC NR 20060208010)			1	H	7	2 	3T			RT	A9EA
2006061900149	20060619	00149	WP  	2006	6	19	CA060303015      	1	20040530	G	7931	269A4107	INDICATOR       			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					OIL PRESSURE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											OIL PRESSURE UNSERVICEABLE.  REPLACED CLUSTER ASSEMBLY.						1	G	7	1 	3O	3	O		4H12    	1E10
2006062300164	20060623	00164	WP  	2006	6	23	CA060306009      	1	20041111	G	6240	B3201	HORN            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  HORN NOT PRODUCING HORN SOUND.  HORN REPLACED.  (TC NR 20060306009)						1	G	7	1 	3O	3	O		H11NM   	E295
2006061400230	20060614	00230	EA  	2006	6	14	CA060418001      	1	20040317	G	2730	NAS558P4048	KEY             			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	RT ELEVATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ELEVATOR TRIM SCREW JACK ASSEMBLY SPROCKET SPINS WITHOUT ANY MOVEMENT OF SCREWDRIVE.  FOUND KEY, P/N NAS558P404-8 TO BE 	MISSING CAUSING NO ELEVATOR TRIM TO BE AVAILABLE ON RIGHT SIDE.  REFERENCE DASH 8/300 IPC 27-38-00; FIGURE 15; ITEM 160.	  SCREW JACK REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
2006061900225	20060619	00225	NE  	2006	6	19	CA060528001      	2	20040924	G	7414	B196689RH	MAGNETO         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				500  							(CAN) MAGNETO NOT FUNCTIONING PLUS  MAGNETO UNSERVICEABLE. (TC NR 20060528001)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206
2004123000064	20041230	00064		2004	12	30	CEVR200400001    	4	20041109	G	2561		BATTERY         	EAAEROMARINE	KSE35L8     															VEST LIGHT	BURST           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					348838					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED AND BURST	 OPEN.  THIS MADE THE LIGHT INOPERABLE.  ACCORDING TO THE EAM SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INS	PECTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS.  REPLACED THIS BATTERY	/LIGHT ASSY WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000034	20050310	00034		2005	3	10	CEVR200400002    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LIFE VEST LIGHT	BURST           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					17767					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000035	20050310	00035		2005	3	10	CEVR200400003    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LIFE VEST	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					111521					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000036	20050310	00036		2005	3	10	CEVR200400004    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LFE VEST	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					69775					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000037	20050310	00037		2005	3	10	CEVR200400005    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LIFE VEST	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					191086					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000038	20050310	00038		2005	3	10	CEVR200400006    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LIFE VEST	BURST           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					191455					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000039	20050310	00039		2005	3	10	CEVR200400007    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LIFE VEST	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					35455					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2005031000040	20050310	00040		2005	3	10	CEVR200400008    	4	20041216	G	2561	WABH12	BATTERY         	EAAEROMARINE	KSE35L8     															LIFE VEST	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					35551					DURING THE YEARLY INSPECTION OF THE LIFE VEST, THE WATER ACTIVATED BATTERY FOR THE LOCATING LIGHT HAD EXPANDED & BURST O	PEN. THIS MADE THE LIGHT INOPERABLE. ACCORDING TO THE E.A.M SERVICE INFORMATION SIL-25-104 ,THIS VEST COULD HAVE A INSPE	CTION INTERVAL OF FIVE YEARS, WHICH MEANT THE LIGHT COULD HAVE BEEN INOPERATIVE FOR FOUR YEARS. I HAVE REPLACED THIS BAT	TERY/LIGHT ASSY. WITH A DIFFERENT MANUFACTURES BATTERY/LIGHT ASSY.
2004030100154	20040301	00154	CE  	2004	3	1	CGLMK1           	1	20040216	G	3097	65280073	CONNECTOR       			CESSNA	500   	550         	2076604	CE  										LE HEAT	MISMANUFACTURED 	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CGLMK					0100				NEW HEATED LEADING EDGE WAS RECEIVED FROM MFG WITH THE CONNECTOR MIS-WIRED AND WITH ONE DRY CRIMP.						1	L	7	2 	4F			 	A22CE
2004083000113	20040830	00113	NE  	2004	8	30	CHI2848          	2	20040619	G	7230	6010T57G08	BLADE           			BOEING	107   	1072        	9420604	EA  	GE    	CT58  	CT581401    	30011	NE  					COMPRESSOR	CRACKED         	B			CHIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09		6963 					280319A			CRACKS AT COMPRESSOR BLADE, LOCK SCREW HOLES, STAGES 3,5,6,7,8,AND 10 SLOTS.  THE SUBJECT PARTS HAVE BEEN SUBMITTED TO T	HE MFG FOR EVALUATION.					2	G	7	2 	4U	4	U	 	1H16    	1E3
2004091400076	20040914	00076	NE  	2004	9	14	CHI2849          	2	20040619	G	7230	6010T57G08	COMPRESSOR      			BOEING	107   	1072        	9420604	EA  	GE    	CT58  	CT581401    	30011	NE  					ENGINE	CRACKED         	B			CHIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09		5880 					280130A			CRACKS AT COMPRESSOR BLADE, LOCK SCREW HOLES, STAGES 3 AND 6.  PARTS HAVE BEEN SUBMITTED TO THE MFG FOR EVALUATION.						2	G	7	2 	4U	4	U	 	1H16    	1E3
2004022300092	20040223	00092	CE  	2004	2	23	CM2R             	1	20040108	G	7160	963800295	SEPARATOR       			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  					ENG AIR INTAKE	OBSTRUCTED      	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	3367					TE146	810839R			OLD ENGINE SEPARATOR WAS CRACKED.  ORDERED NEW PART.  INSPECTED NEW PART AND COULD NOT BLOW THROUGH IT.  THE AIR OUTLET 	TUBE WAS BLOCKED INTERNALLY.  NEW OUT OF BOX FAILURE.  IF THIS UNIT WAS INSTALLED ON THE ENGINE IT WOULD HAVE PRESSURIZE	D THE CASE AND LEAD TO POSSIBLE ENGINE FAILURE DUE TO ENGINE OIL LOSS.				1	L	7	2 	3O	3	O	 	3A16    	E5CE
2005040400102	20050404	00102	WP  	2005	4	4	COOSDR040041     	1	20040924	G	5343	49568801	FITTING         			DOUG  	DC9   	DC914       	3022034	WP  	PWA   	JT8   	JT8D5       	52046	NE  					NLG	CRACKED         	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	700ME					45696				FUSELAGE NOSE LANDING GEAR WHEEL WELL RT SIDE AT Y STA 69.55-X 24 INCH -Z16 INCH FITTING (PN 49568801) WITH CRACK.  (K)						2	L	7	2 	4F	4	F		A6WE    	E2EA
2005030100057	20050301	00057	WP  	2005	3	1	COOSDR040042     	1	20041011	G	5313		LONGERON        			DOUG  	DC8   	DC861F      	3021953	WP  	PWA   	JT3D  	JT3D*       	52039	NE  					FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	41CX					45978				FWD CARGO COMPT AT Y STA 360.0, LONGERON 28R CORRODED.						2	L	7	4 	4F	4	F		4A25    	1E8
2005030800278	20050308	00278	WP  	2005	3	8	COOSDR040044     	1	20041015	G	5330		SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					FUSELAGE	CORRODED        	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				LOWER FUSELAGE SKIN WITH CORROSION AT Y-STA 680.0 AND Y-STA 687.0, BETWEEN LONG 31R AND LONG 34R. (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005040400112	20050404	00112	WP  	2005	4	4	COOSDR040045     	1	20041015	G	5340	37502571	FITTING         			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					FUSELAGE	CRACKED         	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				FWD CARGO COMPARTMENT FROM Y-STA 440 TO Y-STA 460, LONGERON 31R SPLICE FITTING, PN 3750257-1, CRACKED. (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005030800277	20050308	00277	WP  	2005	3	8	COOSDR040047     	1	20041015	G	5330	4643785	SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					FUSELAGE	CRACKED         	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				FWD PASSENGER DOOR HOLD OPEN PAN, PN 4643785, AND FUSELAGE EXTERNAL SKIN CRACKED AT Y-STA 15.000. (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005040400111	20050404	00111	WP  	2005	4	4	COOSDR040048     	1	20041015	G	5320	45976431	FITTING         			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					MAIN CABIN	CORRODED        	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				MAIN CARGO CABIN, SUPPORT FITTING, PN 4597643-1, CORRODED AT Y-STA 60-X65, Z 0 INCH.  (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005042500168	20050425	00168	WP  	2005	4	25	COOSDR040049     	1	20041015	G	5340		FITTING         			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					FUSELAGE	CRACKED         	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BK					45978				MAIN CARGO CABIN, FROM Y STA 650 TO Y-STA 680, LONGERON 1 FITTING WITH CRACK.  (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005031400030	20050314	00030	WP  	2005	3	14	COOSDR040051     	1	20041025	G	5330		SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					FUSELAGE	CORRODED        	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				LOWER FUSELAGE SKIN WITH CORROSION AT Y STA 622.0, BETWEEN LONG 27L AND LONG 30L.  (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005040400053	20050404	00053	WP  	2005	4	4	COOSDR040052     	1	20041026	G	5330	57799293	SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					FUSELAGE	CORRODED        	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				FUSELAGE AFT CENTER SECTION, LOWER PLATING (PN 57799293) CORRODED FROM STA 980 TO STA 1040 BETWEEN LONGERON 35L AND 35R.	  (K)					2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2005042500167	20050425	00167	WP  	2005	4	25	COOSDR040053     	1	20041027	G	5755	56551671	SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  	GE    	CFM56 	CFM562C     	13802	NE  					SPOILER	DELAMINATED     	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	825BX					45978				RT WING, SPOILER PN 56551671, SN 2740 UPPER SKIN DELAMINATED AT STA XRS 218. (K)						2	L	7	4 	4F	4	F	RT	4A25    	E2GL
2004110300118	20041103	00118	CE  	2004	11	3	CQN2004F00000    	1	20040930	G	5312	24120043	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	9654B	12955				172RG0947				CRACKS WERE LOCATED AT LT AND RT RELIEF CUTS OF STATION 124.00 UPPER FUSELAGE BULKHEAD.  PROBABLE CAUSE FOR LT SIDE IS A	UX POWER RECEPTACLE AND RT SIDE COULD BE FROM LANDING STRESSES.					1	H	7	1 	3O	3	O	 	3A17    	E286
2004111900034	20041119	00034	CE  	2004	11	19	E8I2004F00000    	1	20040927	G	3240	388111	CONTROL VALVE   			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ44        	66000	GL  					EMERGENCY BRAKE	INOPERATIVE     	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	488RC	576  				RB23				PILOT REPORTED NO BRAKING ACTION WITH HARD PEDAL PRESSURE, AIRCRAFT STOPPED ON ROLL-OUT WITH EMERGENCY BRAKING SYSTEM.  	TROUBLESHOT POWER BRAKE SYSTEM.  REPLACED PN 3903843000003 (CRANE-HYDRO AIRE PN 388111) POWER BRAKE/ ANTISKID SYSTEM CON	TROL VALVE WITH REPAIRED UNIT IAW MM 32-40-05-401.  SYSTEM TESTS IAW MM 32-40-00-501, SATISFACTORY				1	7		2 	3F	4	F	RT	A00010WI	E3GL
2004111900035	20041119	00035	CE  	2004	11	19	E8I2004F00001    	1	20040920	G	2752	3903814020005	ACTUATOR        			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ44        	66000	GL  					TE FLAP	JAMMED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	488RC					RB23				PILOT REPORTED UNABLE TO RETRACT OR EXTEND FLAPS FROM 10 DEGREES EXTENDED POSITION.  TROUBLESHOT SYSTEM, FOUND RT IB FLA	P IB ACTUATOR JAMMED.  REPLACED ACTUATOR WITH NEW PN 3903814020013 ACTUATOR IAW 390 MM 27-50-03-401 AND RIGGED FLAPS AS 	REQUIRED IAW MM 27-50-00-501.  SYSTEM OPERATIONAL, TESTS SATISFACTORY.  SUSPECT RELATED TO SUBJECT OF MANDATORY SB 27-36	42/ SAFETY COMMUNIQUE NR 236.			1	7		2 	3F	4	F	RT	A00010WI	E3GL
2004083000050	20040830	00050	GL  	2004	8	30	EAHR200400001    	2	20040819	G	7230	23059598	SCROLL          	ALLSN       		ENSTRM	F28   	ENSTROM480  	       	GL  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	723BF	245  	49   		CAC80964	5047	CAE845063			COMPRESSOR DISCHARGE SCROLL CRACKED AT LOWER RT CUSTOMER BLEED AIR FITTING.						1	G	7	1 	3O	3	U	NC	H1CE    	E4CE
2004120700154	20041207	00154	GL  	2004	12	7	EAHR200400002    	1	20040721	G	5400	411004030	TUBE            			ENSTRM	F28   	ENSTROM480  	       	GL  	ALLSN 	250C  	250C20      	03013	GL  					PYLON	BROKEN          	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	01	480EH	369  	74   			5046	CAE845090			PYLON TUBE, P/N 4110040-30, BROKEN AT UPPER CLUSTER.						1	G	7	1 	3O	3	U	NC	H1CE    	E4CE
2004042000015	20040420	00015	CE  	2004	4	20	ESPA             	1	20040225	G	2120		ODOR            			LEAR  	35    	35A         	5170602	CE  										COCKPIT	DETECTED        	H			ESPA	E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	11	568PA					205				SMOKE WAS SUSPECTED IN CABIN.  ENTIRE AREA IN SUSPECTED AREA WAS INSPECTED.  NO DEFECTS WERE FOUND.  PILOT REPORTED LEAD	ING EDGE ANTI-ICE WAS INADVERTENTLY LEFT ON POSSIBLE CAUSING THE SMELL OF SMOKE.  AIRCRAFT WAS RUN, SYSTEMS WERE OPERATI	ONALLY CHECKED AND FOUND TO BE GOOD.				2	L	7	2 	4F			 	A10CE
2005102800064	20051028	00064	GL  	2005	10	28	EY2R00082166     	3	20040819	G	6114	D7292C203	HUB             	MCAULY      		CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03					041321			0413212		FOUND HUB CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA
2005102800051	20051028	00051	GL  	2005	10	28	EY2R0072801      	3	20040908	G	6114	DO4993	HUB             			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03								FY2591		FOUND CORROSION ON HUB.						1	L	7	2 	4T				A24CE   		5	C	STC
2005102800063	20051028	00063	GL  	2005	10	28	EY2R0082166      	3	20040819	G	6114	D7292	HUB             	MCAULY      		CESSNA	172   	172         	2072402	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03					041321			0413212		FOUND HUB WITH CORROSION.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA
2005102800048	20051028	00048	GL  	2005	10	28	EY2R0082166A     	3	20040819	G	6114	D7292C203	HUB             	MCAULY      		CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03					041321			0413212		FOUND CORROSION ON HUB.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA
2004071900028	20040719	00028	NE  	2004	7	19	F20181           	2	20040618	G	7261		COVER           			AMD   	FALC20	FALCON      	2720302	EU  	GE    	CF700 	CF7002D2    	30010	NE  					REAR BEARING	LEAKING         	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	Y	J	FLUID LOSS                	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			SW	11	5225G	11438	22   			181	299G099			ON FLIGHT FROM DEPARTURE AIRPORT TO UNKOWN LOCATION, PILOTS REPORTED THAT ENGINE OIL PRESSURE LIGHT FLICKERD ONCE OR TWI	CE THEN CAME ON STEADY.  WHEN ENGINE POWER WAS REDUCED, ENGINE SHUTDOWN ON ITS OWN. LANDED. ON INSPECTION BEFORE ENGINE 	REMOVAL AND REPLACEMENT FOUND NO OIL VISIBLE ON DIPSTICK AND EVIDENCE OF OIL LEAKAGE ON REAR BEARING COVER.  NO OTHER IN	SPECTIONS PERFORMED . ENGINE SENT TO OVERHAUL FACILITY.			2	L	7	2 	4F	4	F	 	A7EU    	E7EA
2004111900026	20041119	00026	SO  	2004	11	19	F692004F00000    	1	20040609	G	3231	AN2315A	BOLT            			PIPER 	PA34  	PA34220T    	7103420	SO  										DOOR	MISINSTALLED    	B			F69R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	ZKJAS					3448010				DURING GROUND TESTING OF THE AIRCRAFT EMERGENCY EXTENSION SYSTEM THE RT A/C FAILED TO EXTEND INVESTIGATION, FOUND THE BO	LT ATTACHING THE DOOR TO THE ACTUATING ROD INSTALLED AROUND THE WRONG WAY CAUSING IT TO FOUL ON THE WING SPAR.					1	L	7	2 	3O			 	A7SO
2004051200027	20040512	00027	CE  	2004	5	12	FBFQA1           	1	20040507	G	3610	621456120	BELLOWS         			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7313     	01518	WP  					PRECOOLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	534H	8587 				6500196	P87512			UPON INSPECTION AND PRESSURIZATION CHECKS THE WYE PIPE BELLOWS WAS FOUND TO BE CRACKED.						2	L	7	2 	4F	4	F	 	A9NM    	E6WE
2004051200017	20040512	00017	CE  	2004	5	12	FBVXA1           	1	20040506	G	2133		LINE            			CESSNA	500   	550         	2076604	CE  										OUTFLOW VALVE	CHAFED          	B				O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			GL	09	627L	1848 				5500843				THE ELEVATOR CONTROL CABLE CHAFED THROUGH OUTFLOW VALVE VACUUM EJECTOR LINE CAUSING A (BUMP) IN THE PRESSURIZATION.  ALS	O CAUSED ERRATIC PRESSURIZATION IN FLIGHT.  REPLACED THE LINE AND OPS CHECKED GOOD.					1	L	7	2 	4F			 	A22CE
2005012600195	20050126	00195	CE  	2005	1	26	FCPR200400020    	1	20041119	G	2810		RETAINING RING  			BEECH 	90    	E90         	1152914	CE  										FUEL CELL	DISLODGED       	B			FCPR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	09	3818C				763474	LW196				FUEL CELL RETAINING RING AND CLIP  HAD DISLODGED AND MIGRATED TO THE FORWARD SIDE OF THE FUEL CELL, THEN PUNCTURED CELL 	RESULTING IN A FUEL LEAK.					1	L	7	2 	3T				3A20
2005031000058	20050310	00058	CE  	2005	3	10	FCPR200500001    	1	20041223	G	2140	31A408150	SEAL            			CESSNA	500   	560CESSNA   	2076750	CE  										TAILCONE	DISLODGED       	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			NM	09	420DM	2030 	90   			5600464				CUSTOMER REPOARTS UNUSUAL SMELL FROM TAILCONE. INSPECTED BLEAD AIR LINES. FOUND PERI-SEAL CONNECTING L/H FLOW CONTROL VA	LVE TO WINDSHIELD BLEED AIR COUPLING LEAKING AND DISLODGEDALLOWING ENGINE BLEED AIR TO DUMP INTO THE TAIL CONE. 2SAFETY 	LANYARDSP/N 26A429-17 ARE BROKEN AND AFT PRESSURE BULKHEAD SHOWS SIGNS OF HEAT SCORCHING. WIRE BUNDLE FROM LH ENGINE PYL	ON TO AFT PRESSURE BULKHEAD IS DAMAGED CAUSING MULTIBLE SYSTEM TO INDICATE FAILURE.			2	L	7	2 	4F			RT	A22CE
2005031000061	20050310	00061	CE  	2005	3	10	FCPR200500002    	1	20041220	G	3510	80129310	OXYGEN BOTTLE   			BEECH 	200   	B200        	1152922	CE  											RUPTURED        	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7250T	5312 	694  			BB1237				DURING 3 YEAR HYDRO TEST O2 BOTTLE (20 YEARS INSERVICE 3HT 1850) RUPTURED AT OR BELOW 2100 PSI. SIGNIFICANT DAMAGE TO TH	E BOTTLE AND PRESSURE TEST TANK OCCURED. NO INJURIES TO TEST PERSONNEL.					1	L	7	2 	4T				A24CE
2004091400179	20040914	00179	SO  	2004	9	14	FSI072304        	2	20040723	G	8530		CYLINDER HEAD   			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SO	09	97660	631  				18267161	466461			ON CLIMB OUT THE NR 4 CYLINDER HEAD SEPARATED FROM THE BARREL.						1	H	7	1 	3O	3	O	NT	3A13    	E273
2004101500076	20041015	00076	CE  	2004	10	15	FTW04LA214       	1	20040816	G	2822	S116052	SWITCH          			CESSNA	188   	188CESSNA   	2073002	CE  	CONT  	O520  	TSIO520T    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	EMER FUEL PUMP	DEFECTIVE       	G			UTCG	O				OTHER                   				S	R	Y	AFFECT SYSTEMS            	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	AP	APPROACH       	1			SW	11	9317J	4144 	125  			T18803794T				AIRCRAFT LOST POWER ON LANDING. CRASHED SHORT OF FIELD. DETERMINED (HI-SIDE) OF EMERGENCY FUEL PUMP SWITCH STUCK IN THE 	HI POSITION.					1	L	7	1 	3O	3	O	 	A9CE    	E8CE	5	C	P47GL
2004090800074	20040908	00074	CE  	2004	9	8	G5203            	1	20040206	G	3230	99102791	CONTROL VALVE   			CESSNA	441   	441         	2076020	CE  										MLG	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03	988AE		600  			4410175				THIS MLG CONTROL VALVE FOUND TO BE REASON THE MLG FAILED A SCHEDULED EMERGENCY EXTENTION CHECK.  FOUND THE RETURN PORT C	LOSED WHEN VALVE NOT ENERGIZED, PORT SHOULD BE OPEN IN THIS CONDITION & THIS CAUSED MLG TO HYDRO-LOCK IN UP POSITION.  T	EAR DOWN REVEALED ON 2ND VALVE NOT ASSEMBLED CORRECTLY, SPOOL WAS INSERTED BACKWARDS RESULTING IN PORTING NOT FUNCTIONIN	G.  VALVE FAILURE WAS NOT DEFINED DURING TEAR DOWN.  VALVE S/N 1152 RETURNED AND FOUND THAT PIN NR 17 IN THE CORE ASSEMB	LY BROKEN AT THE TIP.  IT IS ASSUMED THAT THIS FAILURE OCCURED DURING THE REQUIRED TEST PROCEEDURE.		1	L	7	2 	3T			RT	A28CE
2004050600036	20040506	00036	SO  	2004	5	6	GILALEX404       	1	20040409	G	5551		SUPPORT ANGLE   			AMRGEN	AA5   	AA5B        	3960105	SO  										FUSELAGE	BUCKLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	28478					AA5B0635				AIRCRAFT WAS INSPECTED IAW CE-04-34.  BUCKLING WAS FOUND ON BOTH OF THE SUPPORT ANGLES (1 AND 2) JUST BELOW THE HORIZONT	AL STAB. MOUNTING BOLTS.  SMALL CRACKS FOUND AT THE TOP OF THESE SUPPORT ANGLES.  MINOR BUCKLE FOUND AT LT SIDE OF LOWER	 STIFFENER AT ARROW NUMBER 7.				1	L	7	1 	3O			 	A16EA
2004050600034	20040506	00034	SO  	2004	5	6	GILALEX404A      	1	20040409	G	5551		SUPPORT ANGLE   			AMRGEN	AA5   	AA5B        	3960105	SO  										FUSELAGE	BUCKLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	28478					AA5B0635				AIRCRAFT WAS INSPECTED IAW SAIB CE-04-34.  BUCKLING WAS FOUND ON BOTH OF THE SUPPORT ANGLES JUST BELOW THE HORIZONTAL ST	AB. MOUNTING BOLTS.  SMALL CRACKS FOUND AT THE TOP OF THESE SUPPORT ANGLES.  MINOR BUCKLE FOUND AT LT SIDE OF LOWER STIF	FENER AT ARROW NUMBER 7 IN SAIB PICTURE.				1	L	7	1 	3O			 	A16EA
2005022200013	20050222	00013		2005	2	22	HE66095154       	4	20040524	G	2210	41800847000	ACTUATOR        			UROCOP	EC135 	EC135T1     	5620026	EU  										YAW	UNRELIABLE      	B			HEEA	O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			SW	03	135CR	1458 				0164				CAUSING A YAW ACTUATOR LIGHT, AND AUTOPILOT TO FLY OUT OF TRIM						1	G	7	2 	3U				H88EU
2005022200015	20050222	00015	EU  	2005	2	22	HE66095158       	1	20040601	G	6330	L633M2010102	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  										M/R GEARBOX	UNSERVICEABLE   	B			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	135CR					0164				MAIN ROTOR GEARBOX MOUNT WORN BEYOND LIMITS						1	G	7	2 	3U				H88EU
2005022200017	20050222	00017	GL  	2005	2	22	HEEA095226       	2	20040508	G	7200	23004545	ENGINE          			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  						STALLED         	B			HEER	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			SW	03	6748D	16334				51106				COMPRESSOR STALL WHILE HOVERING FOR TAKE OFF.						1	G	7	1 	3U	3	U		H2SW    	E1GL
2005031000173	20050310	00173	SW  	2005	3	10	HEEA098914       	1	20041231	G	3110	1300071	TRANSISTOR      			BELL  	412   	412         	1182202	SW  										INSTRUMENT PANEL	BURNED OUT      	B			HEEA	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	03	2149S					36002				IN CRUISE FLIGHT, NOTED ELECTRICAL BURNING SMELL.  RETURNED TO BOOTHVILLE.  MAINTENANCE FOUND TRANSISTOR 8Q2 FOR INSTRUM	ENT LIGHTS HAD SHORTED AND CAUSED RESISTOR 8R12 TO BURN OUT.  REPLACED TRANSISTOR 8Q2, RESISTOR 8R12 AND RHEOSTAT 8R5.					1	G	7	2 	4U				H4SW
2004101800033	20041018	00033	SO  	2004	10	18	HN8R200400001    	2	20041005	G	8520	646778	CONNECTING ROD  			BEECH 	95    	95B55       	1152729	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCA3V	EHCA3VF2    	GL  	RT ENGINE	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2147L	1574 				TC1991	215900R	FJ437B		DURING DIFFERENTIAL COMPRESSION CHECK FOUND NR 6 CYLINDER 20/80.  REMOVED CYLINDER AND DISCOVERED THE CONNECTING ROD BEN	T.  REPLACED THE ENGINE.					1	L	7	2 	3O	3	O	RT	3A16    	E5CE	5	C	P6EA
2005021700125	20050217	00125	EU  	2005	2	17	I05R098769       	1	20040825	G	2910	MA12401	PRESSURE SWITCH 			AEROSP	AS355 	AS355*      	       	EU  										HYD SYSTEM	FAILED          	B			I05R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	970SD	196  				3760				PRESSURE SWITCH FAILED IN 3 HRS OF OPERATION.  REPLACED PART.						1	G	7	2 	3U				H11EU
2004092800071	20040928	00071	EU  	2004	9	28	I7LA0002725      	1	20040805	G	6420	109013105115	TRUNNION        			AGUSTA	A109  	A109K2      	0260502	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TAIL ROTOR	OVERHEATED      	E			I7LA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	109RX	149  				10016				UPON 25 HOUR INSPECTION, TRUNION SHOWS SIGNS OF EXCESSIVE HEAT, DISCOLORED (BROWN) COATING. ENAMEL PAINT.						1	G	7	2 	3U	3	U	RT	H7EU    	E19EU
2004092800055	20040928	00055	EU  	2004	9	28	I7LA0002736      	1	20040820	G	6420	109013105115	TRUNNION        			AGUSTA	A109  	A109K2      	0260502	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TAIL ROTOR	LOOSE           	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	901HC					10033				UPON DAILY INSPECTION, MECHANIC NOTED EXCESSIVE PLAY IN TAIL ROTOR HUB AT TRUNION AREA.  TAIL ROTOR HUB WAS REMOVED FOR 	INSPECTION A SOFT FACE MALLET WAS REQUIRED TO FREE THE TRUNION FROM TAIL ROTOR GEARBOX OUTPUT SHAFT.  REMOVAL OF TRUNION	 NOTED SIGNS OF EXCESSIVE HEAT DISCOLORATION OF ENAMAL PAINT/ COATING.  THE TRUNION BUSHINGS/ RACES WERE LOOSE AND SLIDE	 .5 WAY OFF TRUNION WITH NO MECHANICAL MEANS.			1	G	7	2 	3U	3	U	RT	H7EU    	E19EU
2004122200114	20041222	00114	WP  	2004	12	22	JV2R200400001    	2	20041209	G	7321	21190208000	COMPUTER        			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					E/E BAY	FAILED          	B			JV2R	H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CE	03	69WU	25   	25   			46551				DURING MAINTENANCE ENGINE RUN, THE LT COMPUTER FAIL LIGHT ILLUMINATED AT 92 PERCENT AND THE SYSTEM WENT TO MANUAL.  THE 	ENGINE OPERATOR RESET THE SYSTEM PER MANUAL AND PERFORMED A SECOND ENGINE RUN.  LEFT COMPUTER FAIL LIGHT ILLUMINATED AT 	IDLE ON THE SECOND ENGINE RUN AND WENT TO MANUAL.  ENGINE OPERATION WAS STOPPED.  HONEYWELL WAS CONTACTED.				2	L	7	2 	4J	4	F	 	A2WE    	E6WE
2004123000118	20041230	00118	WP  	2004	12	30	JV2R200400003    	2	20041209	G	7320	21190208000	EEC             			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	DEFECTIVE       	B			JV2R	H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CL	CLIMB          	1			CE	03	976SR					46529				OPERATOR REPORTED LEFT DIGITAL ELECTRONIC ENGINE CONTROL COMPUTER FAIL LIGHT ILLUMINATED DURING CLIMB PUTTING THE SYSTEM	 IN MANUAL.  THE OPERATOR REPORTED ATTEMPTING RESET ONE TIME, SYSTEM FAILED AGAIN AND OPERATOR RETURNED TO BASE.  HONEYW	ELL WAS CONTACTED.				2	L	7	2 	4J	4	F	 	A2WE    	E6WE
2004050300124	20040503	00124	CE  	2004	5	3	JV2R20040001     	1	20040308	G	3244		TIRE            			RKWELL	NA265 	NA26565     	7630107	CE  										MLG	SEPARATED       	B			JV2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	47SE					46534				TIRE TREAD SEPARATION FROM TIRE CASING.  EACH TIRE REPORTED HAS LESS THAN TWENTY LANDINGS ON IT.  THIS PROBLEM REPORTED 	TO TIRE MFG.  SAMPLES OF DISCREPANT UNITS FORWARDED TO MFG FOR EVALUATION.  THIS IS THE FIRST OF NINE KNOWN FAILURES OF 	THESE TIRES.  ONE OTHER IS MODEL -65, FOUR ARE ON MILITARY T-39N AIRCRAFT.  THREE OTHER AIRCRAFT REPORTED TREAD SEPARATI	ONS TO ANOTHER REPAIR STATION WHO FORWARDED THEIR INFORMATION TO MFG.  A COPY OF THE MFG CORRECTIVE ACTION REQUEST, NO 6	6 AND THE LETTER REQUESTING AN EVALUATION WILL BE SENT TO MFG AND FSDO WITH THIS REPORT.		2	L	7	2 	4J			 	A2WE
2005012100183	20050121	00183	NE  	2005	1	21	JYDRMDR04065     	1	20041020	G	6410	6516000047101	SPACER          	SKRSKY      		SKRSKY	S64   	CH54B       	8142610	NE  										T/R BLADE	CRACKED         	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	179AC				65V60735280	64091				PART OF THE OB ROOT END SPACER BLOCK BROKE OFF AND WAS SENT THROUGH THE TIP CAP.  THE OB SPACER BLOCK HAS SPLIT AROUND T	HE L/E THROUGH BOLT.  PRIOR TO DISASSEMBLY THE OB MOST SPACER BLOCK COULD BE SEEN AS MISSING A PORTION THAT IS ABOUT THE	 SAME SIZE AS THE HOLE IN THE TIP CAP.  UPON DISASSEMBLY OF THE ROOT END, IT APPEARS AS IF THE ROOT END SPACER BLOCK WAS	 NOT PROPERLY FITTED TO THE INSIDE OF THE SPAR.  THE L/E OF BLOCK WAS BEARING THE COMPRESSIVE STRESS IMPOSED BY THE TORQ	UE SQUEEZE OF THE THROUGH BOLTS.  IB SPACER BLOCK FOR THE THROUGH BOLTS IS CRACKED IN THE SAME AREAS THAT THE OTHER BLOC	K FAILED.  BLOCK WAS NO PROPERLY SHAPED INSIDE OF THE SPAR AND IS SHOWING CONTACT WITH THE SPAR ONLY IN CTR OF BLOCK.	2	G	7	2 	4U				H6EA
2005012100174	20050121	00174	NE  	2005	1	21	JYDRMDR04066     	1	20041020	G	6320	SB21511	BEARING         			SKRSKY	S64   	S64E        	8142604	NE  										M/R GEARBOX	CRACKED         	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CGJZK	1276 			A6105	64003				THE AIRCRAFT CREW REPORTED, AFTER PULLING MAX POWER, THAT THE AC JUMPED.  AFTER RETURNING TO THE LANDING, THE MECHANICS 	CHECKED THE CHIP DETECTOR IN THE MAIN GEAR BOX AND FOUND FERROUS METAL.  UPON TEARDOWN OF THE GEARBOX IN THE SHOP, DISCO	VERED THAT THE INNER RACE OF THE 2ND STAGE INPUT WAS SPALLING AND HAD AN AXIAL CRACK THROUGH THE ENTIRE INNER RACE.  DUE	 TO THE CRACK, THE BEARING LOST ALL PRESS FIT WHICH RESULTED IN THE INNER RACE ROTATING ON INPUT PINION SHAFT. (NM092005	03792)		2	G	7	2 	4U				H4EA
2005033000124	20050330	00124	NE  	2005	3	30	JYDRMDR04069     	1	20041206	G	6320	643520017019	HOUSING         			SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					M/R GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC		2067 		A6148	64084				MGB WAS REMOVED FOR MAIN SHAFT REPLACEMENT AND OVERHAUL.  AFTER DISASSEMBLY OF GEAR BOX, THE UPPER HOUSING WAS LOCALLY B	LENDED, ETCHED UNDER THE INPUTS AND INSPECTED BY FPI.  THE HOUSING WAS REJECTED FOR CRACKS ON THE LT AND RT SIDE.  POOR 	REWELD QUALITY OF CASTING AT MFG.  (K)				2	G	7	2 	4U	4	U		H6EA    	E15EA
2004121000024	20041210	00024	WP  	2004	12	10	KO0R0323         	1	20040115	G	5340	37560231N	FITTING         			DOUG  	DC8   	DC863       	302198A	WP  	PWA   	JT3D  	JT3D7       	52039	NE  					FUSELAGE	CORRODED        	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	865F					46088				EXTERNAL FUSELAGE SKIN HAS A BULGE AT FS315, LONGERON NR 33R.  FOUND DOOR STRUCTURE FITTING CORRODED (FS 315, LONGERON 3	3R).  REMOVED AND REPLACED FITTING IAW DC8, SRM 53-2-0, FIG 2D.  CORROSION REMOVED IAW DC SRM 51-1-8.					2	L	7	4 	4F	4	F	 	4A25    	1E8
2004090800050	20040908	00050	GL  	2004	9	8	KRCX0101AA       	3	20040827	G	6110		COUNTERWEIGHT   			CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C302  	GL  	PROPELLER	DISPLACED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13	1258M	2191 	72   			337F01458	5193972C	722959		ON ANNUAL INSPECTION SAW FINE ALUMINUM POWDER ON ONE BLADE SHANK ON REAR PROP. FOUND SPINNER HAD A LARGE BLISTER CAUSED 	BY PRESSURE FROM WITHIN. WHEN WE REMOVED THE SPINNER WE SAW THE COUNTERWEIGHT FOR THAT BLADE WAS ADVANCED ABOUT 30 DEGRE	ES IN THE CRUISE DIRECTION BUT BOTH BLADES WERE IN FULL FLAT PITCH. THE ALUMINUM POWDER CAME FROM THE BALANCE WEIGHT ARM	 RUBBING THE INSIDE OF THE SPINNER. SENT ENTIRE ASSEMBLY TO THE CRS UF2R211L THAT OVERHAULED IT 72.9 HOURS AGO JAN 2003.	 THE OWNER OF THAT SHOP CLAIMED THE COUNTER WEIGHT CANNOT REACH THE SPINNER. I HAVE EVIDENCE OTHERWISE. THE CRS CORRECTE	D THE LOOSE COUNTERWEIGHT AND ISSUED A YELLOW TAG WITH THE ORIGINAL SPINNER INSTALLED.	1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA
2004112300005	20041123	00005	NM  	2004	11	23	L0FR200400012    	1	20041118	G	3246	260356116	WHEEL           			BOEING	747   	747200      	1384847	NM  										MLG	CRACKED         	B			Q2SA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										FAILED BOLT HOLES ON OUTER RIM IDENTIFIED PER HONEYWELL COMPONENT MM 32-45-12 EDDY CURRENT PROCEDURES.						2	L	7	4 	4F			RT	A20WE
2005030800180	20050308	00180	NM  	2005	3	8	LCQ20052         	1	20041221	G	5330		SKIN            			BOEING	737   	737         	UTILSYS	NM  										FUSELAGE	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	945UA					26684				DENT AT FUSELAGE STA 391, 3 INCHES ABOVE S-17L AT PERIMETER OF EXISTING REPAIR.  REF NR 23648 S/O 269001.						2	L	7	2 	4F			RT	A16WE
2004050300160	20040503	00160	SO  	2004	5	3	LU4R349M         	1	20040316	G	6120	B24521	CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15								BP9634		CYLINDER (PN B-2452-1) SEPARATED FROM PROPELLER ON GROUND RUN. INSPECTION SHOWED THREAD DAMAGE OF CYLINDER. AFTER DISCUS	SION WITH MFG, THE LIKELY CAUSE IS DIE TO HIGH PRESSURE FROM GOVERNOR, USUALLY CAUSED BY STICKING PRESSURE RELIEF VALVE.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA
2005022200211	20050222	00211	NM  	2005	2	22	M0539            	1	20040827	G	5302	206030446001	BULKHEAD        	BELL        		UNIVAR	108   	1083        	9230408	NM  	FRNKLN	6A4165	6A4165*     	27025	EA  					TAILBOOM	CRACKED         	B			BXOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	909C	5947 			BCJN07208	1083909				DURING ANNUAL INSPECTION, FOUND AFT TAILBOOM BULKHEAD PN 206030446001 CRACKED AT LT BOLT HOLE FOR TAIL ROTOR GEARBOX MOU	NT.					1	H	7	1 	3O	3	O		A767    	E238
2004050300182	20040503	00182	CE  	2004	5	3	MAFPAPUA         	1	20040322	G	2810	S2020	DRAIN           			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	FUEL SUMP	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	PK-MA					U20606231	532210	781860		WHILE INSTALLING THE WING FUEL TANK SUMP DRAIN AT THE MFG RECOMMENDED TORQUE VALUE OF 90 IN-LBS, THE DRAIN ITSELF FAILED	, SEPARATING AT THE DRILLED HOLES JUST ABOVE THE FITTING HEAD.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL
2004100400089	20041004	00089	SO  	2004	10	4	MAGMARTINSEPT    	2	20040908	G	7414	103493504	MAGNETO         			CESSNA	206   	TU206*      	       	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23		120  								UPON INSPECTION OF THE MAGNETO INTERIOR, FOUND THAT THE (STRIP-FISH PAPER)  (P/N 10-349326) HAD COME LOOSE FROM THE SIDE	 OF THE CASE AND BECOME INGESTED IN THE DRIVE AND DISTRIBUTOR BLOCK GEARS.  ADDITIONALLY, THE CARBON BRUSH SHOWED EXCESS	IVE SIDE LOAD WEAR.  WERE LOOKING FOR A PROBLEM RELATED TO RF NOISE IN THIS MAGNETO.  HOLD MFG ACCOUNTABLE FOR ERRORS.  	BELIEVE WE NEED TO EITHER WORK DIRECTLY WITH MFG PERSONNEL OR THE FAA TO MAKE SURE QUALITY CONTROL ISSUES LIKE THIS ARE 	NOTICED AND FIXED.		1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2004100400079	20041004	00079	SO  	2004	10	4	MAGSENTANI       	2	20040908	G	7414	103493504	MAGNETO         			CESSNA	206   	TU206*      	       	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21		120  								UPON INSPECTION OF THE MAGNETO INTERIOR, FOUND THAT THE (STRIP-FISH PAPER) (P/N 10-349326) HAD COME LOOSE FROM THE SIDE 	OF THE CASE AND BECOME INGESTED IN THE DRIVE AND DISTRIBUTOR BLOCK GEARS.  ADDITIONALLY, THE CARBON BRUSH SHOWED EXCESSI	VE SIDE LOAD WEAR.  LOOKING FOR A PROBLEM RELATED TO RF NOISE IN THIS MAGNETO.  HOLD MFG ACCOUNTABLE FOR ERRORS.  SERIOU	SLY BELIEVE WE NEED TO EITHER WORK DIRECTLY WITH MFG PERSONNEL OR THE FAA TO MAKE SURE QUALITY CONTROL ISSUES LIKE THIS 	ARE NOTICED AND FIXED.		1	H	7	1 	3O	3	O	 	A4CE    	E8CE
2005021500077	20050215	00077	NE  	2005	2	15	MDR03032         	2	20041002	G	7532	745114	BLEED VALVE     		JFTD12A5A   	SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					COMPRESSOR	OBSTRUCTED      	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	178AC				677806	64097				NR 1 ENG OIL PRESS WAS INDICATING LOWER THAN NR 2 ENG.  PRESS INDICATED 45 PSI.  ADJUSTED PRESS VALVE TO INCREASE CHECK 	AT NEXT FLT.  NR 1 ENG WAS STARTED, INDICATED NML GROUND IDLE.  ACCELERATING TO 70 PERCENT N2, OIL PRESS DROPPED OFF, CA	UTION LIGHT ILLUM, PRESS DROPPED TO ZERO.  PRESS DID NOT IMPROVE, BOTH ENG WERE SHUT DOWN.  SMALL PIECE OF PLASTIC WAS L	ODGED IN PRESSURE RELIEF VALVE, HOLDING IT OPEN.  PIECE OF PLASTIC WAS BROWN COLORED, ABOUT .1875 X .1250 INCH.  OBSTRUC	TION WAS A PIECE OF RELIEF VALVE SEAT.  VALVE WAS REPLACED, AC RETURNED TO SERVICE.  EROSION OF VALVE SEAT CAUSED INITIA	L PRESS LOSS.  VALVE WAS TIGHTENED TO MATCH PRESS WITH THE NR 2 ENG.  SEAT MAY HAVE BEEN DAMAGED BY THIS ADJUSTMENT.	2	G	7	2 	4U	4	U		H6EA    	E15EA
2005021500074	20050215	00074	NE  	2005	2	15	MDR04060         	2	20040802	G	7230	468247001	SPACER          			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					COMPRESSOR	CRACKED         	B			JYDR	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			NM	09	CCFRN	1312 	1312 			64061				COMPRESSOR, SN 672543, CAME INTO THE SHOP AND DURING THE PRELIMINARY TEST RUN, THE VIBES WERE AT 1.7 MILS.  WITH THE VIB	ES EXCEEDING THE LIMITS, THE COMPRESSOR HAD TO BE DISASSEMBLED FOR BALANCE.  DURING THE VISUAL INSPECTION OF THE 3-4 SPA	CER, THERE APPEARED TO BE A CRACK AT ONE OF THE FORWARD LIGHTENING HOLES.  THE CRACK CONFIRMED VIA EDDY CURRENT AND FPI.	  RESEARCH OF THE PREVIOUS W/O AND THE PN 468247-001 INDICATE THAT THE SPACER HAD BEEN SHOTPEENED AND SB 6414 WAS COMPLI	ED WITH.		2	G	7	2 	4U	4	U		H4EA    	E15EA
2004122100164	20041221	00164	NE  	2004	12	21	MDR04061         	1	20040819	G	6420	6595207526101	BEARING RACE    	SKRSKY      		SKRSKY	S64   	CH54B       	8142610	NE  										TAIL ROTOR HEAD	CRACKED         	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	159AC	298  			A9204	64084				TAIL ROTOR HEAD WAS REMOVED FROM AC DUE TO SUDDEN LEAKAGE FROM TAIL ROTOR GRIP.  DISASSEMBLED TAIL ROTOR HEAD AND FOUND 	THE SHOULDER BOLT INNER RACE CRACKED ON THE BACK SLEEVE AND SPINDLE.  CRACK TRAVELS COMPLETELY ACROSS BEARING CONTACT SU	RFACE AND COMPLETELY THROUGH INNER RACE TOT HE SHOULDER BOLT CONTACT SURFACE.  THE CRACKING OF THE INNER RACE WAS A PROB	ABLE CAUSE FOR THE SUDDEN LEAKAGE.  NOTE: THIS IS FIRST OCCURRENCE OF THIS TYPE.  PART WILL BE SENT OUT FOR ANALYSIS.			2	G	7	2 	4U			 	H6EA
2004022500107	20040225	00107	CE  	2004	2	25	MYNR748K         	1	20040114	G	2710	176703013	CONTROL TUBE    			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320*       	41508	EA  					AILERON	WORN            	B			MYNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	3231T	2675 				17700531				AILERON CONTROL SHAFT, WHERE IT MOUNTS TO FIREWALL BEARING WAS RUSTED AND GROVED BEYOND LIMITS, REPLACED LT AND RT SHAFT	S AND BEARINGS.  BEARING PN 0760633-1 END.					1	H	7	1 	3O	3	O	NT	A13CE   	E274
2005031000026	20050310	00026	SW  	2005	3	10	N114EL           	1	20041215	G	2720	63457003	CONTROL ARM     	PIPER       		TMPSON	NAVION	NAVIOND     	6150114	SW  	CONT  	O470  	O470*       	17026	SO  					ZONE 100	SEPARATED       	D				O				OTHER                   				F	S		FLT CONT AFFECTED         	AFFECT SYSTEMS            		CR	CRUISE         	1			GL	03	114E	2879 				NAV416				ON THE RUDDER PEDAL ASSY, THE RUDDER CONTROL ARM ASSEMBLY, TRIM ARM BROKE OFF AT PARENT METAL SURROUNDING THE WELD POINT	.  PILOT REPORTED LOSS OF RUDDER TRIM INPUT.  NO HISTORY OF PART REPLACEMENT. P/N 63457-003.  2879.3 HOURS TOTAL AIRCRAF	T TIME.  HAND TOW BAR FOR THIS AIRCRAFT WAS FOUND BENT ABOUT 20 DEGREES ABOUT ONE MONTH PRIOR TO LOSS OF RUDDER TRIM INP	UT.  REPLACEMENT PART WAS INSTALLED AND FUNCTIONAL CHECK FLIGHTS WERE FLOWN WITHOUT DIFFICULTY.			1	L	7	1 	3O	3	O		A782    	E273
2005031000025	20050310	00025	SW  	2005	3	10	N114EL1          	1	20041215	G	2720	63457003	CONTROL ARM     	PIPER       		TMPSON	NAVION	NAVIOND     	6150114	SW  	CONT  	O470  	O470*       	17026	SO  					RUDDER PEDALS	SEPARATED       	D				O				OTHER                   				F	S		FLT CONT AFFECTED         	AFFECT SYSTEMS            		CR	CRUISE         	1			GL	03	114E	2879 				NAV416				ON THE RUDDER PEDAL ASSY, THE RUDDER CONTROL ARM ASSEMBLY , TRIM ARM BROKE OFF AT PARENT METAL SUROUNDING THE WELD POINT	.  PILOT REPORTED LOSS OF RUDDER TRIM INPUT.  NO HISTORY OF PART REPLACMENT. P/N 63457-003.  2879.3 HOURS TOTAL AIRCRAFT	 TIME.  HAND TOW BAR FOR THIS AIRCRAFT WAS FOUND BENT ABOUT 20 DEGREES ABOUT ONE MONTH PRIOR TO LOSS OF RUDDER TRIM INPU	T.  REPLACEMENT PART WAS INSTALLED AND FUNTIONAL CHECK FLIGHTS WERE FLOWN WITHOUT DIFFICULTY.			1	L	7	1 	3O	3	O		A782    	E273
2005031000027	20050310	00027	SO  	2005	3	10	N114EL2          	1	20041215	G	2720	63457003	CONTROL ARM     	PIPER       		PIPER 	PA32  	PA32301     	7103207	SO  	CONT  	O470  	O470*       	17026	SO  					ZONE 100	SEPARATED       	D				O				OTHER                   				F	S		FLT CONT AFFECTED         	AFFECT SYSTEMS            		CR	CRUISE         	1			GL	03	114E	2879 				328106096				ON THE RUDDER PEDAL ASSY, THE RUDDER CONTROL ARM ASSY, TRIM ARM BROKE OFF AT PARENT METAL SURROUNDING THE WELD POINT.  P	ILOT REPORTED LOSS OF RUDDER TRIM INPUT.  NO HISTORY OF PART REPLACEMENT. P/N 63457-003.  2879.3 HOURS TOTAL AIRCRAFT TI	ME.  HAND TOW BAR FOR THIS AIRCRAFT WAS FOUND BENT ABOUT 20 DEGREES ABOUT ONE MONTH PRIOR TO LOSS OF RUDDER TRIM INPUT. 	 REPLACEMENT PART WAS INSTALLED AND FUNCTIONAL CHECK FLIGHTS WERE FLOWN WITHOUT DIFFICULTY.			1	L	7	1 	3O	3	O		A3SO    	E273
2004030100039	20040301	00039	SW  	2004	3	1	N207RT012804     	1	20040128	G	5302	206021103105	BRACKET         			BELL  	206   	206L4       	1182110	SW  										TAILBOOM	CRACKED         	E			YTRA	R				AUTOROTATION            				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SW	03	207RT					52207				VERTICAL WINGLET BRACKET CRACKED AND ALLOWED WINGLET TO DETACH IN FLIGHT STRIKING THE TAILROTOR AND CAUSING LOSS OF TAIL	ROTOR EFFECTIVENESS. (SW03200405293)					1	G	7	1 	3U			NC	H2SW
2004050600018	20040506	00018	CE  	2004	5	6	N736ZX           	1	20040311	G	5540	22601145	TORQUE TUBE     	CESSNA      		CESSNA	182   	182R        	2072731	CE  										RUDDER BAR	DETACHED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	736Z	5075 								LT RUDDER BAR TORQUE TUBE ASSEMBLY, PN 2260114-5 FAILURE. FAILURE OCCURRED IN FLIGHT RESULTING IN LT SIDE PILOT'S TOTAL 	LOSS OF LT RUDDER AND STEERING CONTROL. NATURE OF FAILURE; LT OB RUDDER PEDAL SOCKET ON TORQUE TUBE BROKE AWAY FROM THE 	TORQUE TUBE. THERE IS NO OBVIOUS REASON WHY THIS MIGHT HAVE HAPPENED. THERE ARE NO BENT OR DAMAGED COMPONENTS WITHIN THE	 SAME SYSTEM, AND THE STEEL TORQUE TUBE HAS ONLY VERY LIGHT INTERNAL CORROSION.			1	L	7	1 	3O			NT	3A13
2004092300084	20040923	00084	CE  	2004	9	23	N827SP1          	1	20040809	G	7722	S32778	INDICATOR       			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					EGT	INOPERATIVE     	D				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	827SP		25   			172S8740				EGT/FUEL FLOW INDICATOR BECAME INOPERATIVE DURING FLIGHT.						1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004102800030	20041028	00030	GL  	2004	10	28	NF22004FCCC      	1	20040723	G	2497		WIRE            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ALT OUTPUT	CHAFED          	B			NF2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	280L					0154				ALTERNATOR OUTPUT WIRE CHAFED ON THE RT FWD VALVE COVER AND BURNED A .2500 INCH HOLE IN THE VALVE COVER.  WIRE AND BAFFL	E ABOVE VALVE COVER NEED TO BE SECURED BETTER.  SHORTING OF THE WIRE ALSO CAUSED DAMAGE TO COMPONENTS IN THE MCU AND SUB	SEQUENT NR 1 ALTERNATOR FAILURE.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO
2004030100124	20040301	00124	SO  	2004	3	1	NI1R200400001    	1	20040211	G	1430		BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  										NLG	SHEARED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	03	554PC	1179 				4496073				NOSE GEAR DID NOT RETRACT AFTER TAKE OFF.  GEAR HANDLE SELECTED UP INDICATIONS: ALL THREE GREEN LAMPS OUT, GEAR UNSAFE L	AMP STAYS ILLUMINATED, HYDRAULIC PUMP MOTOR CYCLES OFF AFTER A NORMAL PERIOD OF TIME.  GEAR SELECTED DOWN INDICATIONS: L	T AND RT MAIN GEAR DOWN AND LOCKED LAMPS ILLUMINATED, GEAR UNSAFE LAMP ILLUMINATED, THROTTLE AT IDLE, GEAR WARNING HORN 	SOUNDING OFF.  PILOT LANDED THE AIRCRAFT SAFELY.  TECHNICIANS FOUND BOLT SHEARED AT THE NOSE GEAR DOWNLOCK TO DRAG LINK 	ASSY.		1	L	7	2 	3O			 	A19S0
2004101300002	20041013	00002	WP  	2004	10	13	NM09EDR001       	1	20040913	G	6230	369D22014	MAST            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CORRODED        	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	502CH	1572 				0252D				DURING 100 HR INSPECTION, THE MAIN ROTOR DRIVESHAFT WAS REMOVED FOR INSPECTION. THE MECHANIC LOOKED DOWN THE MAST AND FO	UND THE PAINT ON THE INSIDE DIAMETER WAS BLISTERED AND PEELING. THE MECHANIC ALSO NOTICED PAINT ON THE TOP OF THE MAIN T	RANSMISSION SPLINES. THE MAIN ROTOR MAST WAS REMOVED AND IT WAS NOTICED THAT THE PAINT ON THE BOTTOM FLANGE WAS ALSO PEE	LING AND THE INSIDE WAS CORRODING. THE MAIN TRANSMISSION WAS REMOVED FOR CONTAMINATION AND INSPECTED. THE MAIN ROTOR MAS	T WAS REPLACED. THE MANUFACTURE WAS NOTIFIED. THE MAST WAS INSTALLED 11-13-2000.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2004051200018	20040512	00018	EU  	2004	5	12	NP0003           	1	20040111	G	2910	MY20751106	LINE            			AMD   	FALCON	FALCON20    	2730103	EU  										HYD SYSTEM	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	04	384K	8878 				387				FOUND HYD FLUID DRIPPING OUT OF TAIL OF AC.  INSPECTED AFT COMPARTMENT, FOUND HYD FLUID UNDER LT HYD RESERVOIR. FOUND RE	SERVOIR MAIN RETURN LINE CRACKED.  REMOVED AND REPLACE LINE. FOURTH ALUMINUM LINE REPLACED IN LT HYD SYST IN AFT COMPART	MENT.  NOTICED THAT THIS LINE IS NOT CLAMPED ANY WHERE BETWEEN END BUT LOOKED LIKE IT SHOULD. CHECKED FOR EXCESS VIBRATI	ONS WHEN THE HYD SYST IS RUNNING AND HAVE ONLY FOUND WHAT WOULD BE CONSIDERED NORMAL. HOWEVER, LINES DO VIBRATE EXCESSIV	ELY AFTER DISCONNECTING THE HYD CART ON FIRST ENGINE RUN. THERE IS AIR IN SYST THAT HAS TO WORK ITS WAY OUT AND DOES WIT	HIN A FEW SECONDS. SUGGESTED THAT A HARDER LOOK AND COME UP WITH A FIX FOR THE OLD, FAILING HYDRAULIC LINES.	2	L	7	2 	4F			RT	A7EU
2004030100126	20040301	00126	GL  	2004	3	1	O05R021320044    	3	20040213	G	6114		FLANGE          			CESSNA	172   	172         	2072402	CE  						MCAULY	1C160	1C160DTM    	GL  	PROP HUB	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								CC184		EXCESSIVE DAMAGE TO MOUNTING FLANGE OF PROPELLER HUB.						1	H	7	1 	3O			NT	3A12    		5	N	P910
2004030100129	20040301	00129	GL  	2004	3	1	O05R200400010    	3	20040213	G	6111	FJC7666A	BLADE           			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	OUT OF TOLERANCE	B			O05R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05								AU9346B		BLADES WERE FOUND TO BE UNDER MINIMUM DIAMETER AND MINIMUM THICKNESS AT STATION 34.  BLADE SERIAL NUMBERS E19818R AND E1	9873R.					1	L	7	2 	3O			 	A7SO    		5	C	P920
2004050300167	20040503	00167	GL  	2004	5	3	O05R200400100    	3	20040405	G	6111	FJC7666A	BLADE           			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	OUT OF TOLERANCE	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05		9026 								2 BLADES REJECTED FOR DIMENSIONS.						1	L	7	2 	3O			 	A7SO    		5	C	P920
2004050300168	20040503	00168	GL  	2004	5	3	O05R200400101    	3	20040405	G	6111	FJC7666A	BLADE           			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05		9026 								2 BLADES REJECTED FOR DIMENSIONS.						1	L	7	2 	3O			 	A7SO    		5	C	P920
2004050300180	20040503	00180	GL  	2004	5	3	O05R200400104    	3	20040405	G	6111	90DHA16	BLADE           			PIPER 	PA28  	PA28R200    	7102811	SO  						MCAULY	2D34C	B2D34C213   	GL  	PROPELLER	SCRATCHED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 BLADE REJECTED FOR SCRATCH IN SHOT PEEN.						1	L	7	1 	3O			 	2A13    		5	C	P7EA
2004050300181	20040503	00181	GL  	2004	5	3	O05R200400105    	3	20040405	G	6111	T10282DB4R	BLADE           			SWRNGN	SA226 	SA226T      	8780122	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 BLADE REJECTED FOR DIMENSIONS.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA
2004050300172	20040503	00172	GL  	2004	5	3	O05R200400106    	3	20040405	G	6111	T10282DB4R	BLADE           			SWRNGN	SA226 	SA226T      	8780122	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 BLADE REJECTED FOR DIMENSIONS.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA
2004050300198	20040503	00198	GL  	2004	5	3	O05R200400107    	3	20040405	G	6111	T10282DB4R	BLADE           			SWRNGN	SA226 	SA226T      	8780122	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 BLADE REJECTED FOR DIMENSIONS.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA
2004050300199	20040503	00199	EA  	2004	5	3	O05R200400108    	3	20040405	G	6110	72CKS6054	PROPELLER       			CESSNA	150   	152         	2071835	CE  						SNSNCH	72C	72CK        	EA  	NR 1	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 PROPELLER ASSEMBLY REJECTED FOR IMPACT DAMAGE.						1	H	7	1 	3O			NT	3A19    		5	N	P9045
2004050300173	20040503	00173	GL  	2004	5	3	O05R200400109    	3	20040405	G	6110	1A103TCM6958	PROPELLER       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  		CORRODED        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 PROPELLER ASSEMBLY REJECTED FOR CORROSION.						1	H	7	1 	3O			NT	3A19    		5	N	P50GL
2004050300200	20040503	00200	GL  	2004	5	3	O05R200400110    	3	20040405	G	6111	82NEA5	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	NR 1 PROPELLER	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 BLADE REJECTED FOR DAMAGE IN SHOT PEEN AREA.						1	L	7	2 	3O			 	3A16    		5	C	P22EA
2004050700005	20040507	00005	GL  	2004	5	7	O05R200400112    	3	20040405	G	6111	T10178B3R	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										1 BLADE REJECTED FOR DIMENSIONS.						1	L	7	2 	4T			 	A24CE   		6	C	P15EA
2004050300201	20040503	00201	GL  	2004	5	3	O05R200400113    	3	20040405	G	6111	T10178B3R	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05		6034 								1 BLADE REJECTED FOR DIMENSIONS.						1	L	7	2 	4T			 	A24CE   		6	C	P15EA
2004050300170	20040503	00170	GL  	2004	5	3	O05R200400114    	3	20040405	G	6111	T10178B3R	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	OUT OF TOLERANCE	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05		6034 								1 BLADE REJECTED FOR DIMENSIONS.						1	L	7	2 	4T			 	A24CE   		6	C	P15EA
2004100400099	20041004	00099	GL  	2004	10	4	O05R200400115    	3	20040617	G	6114	D22013	HUB             			PIPER 	PA32  	PA32R300    	7103213	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	UNKNOWN         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								CH19828E		ELIMINATED AD 2001-23-08 COMPLIANCE REQUIREMENT.						1	L	7	1 	3O			 	A3SO    		5	C	P920
2004071200201	20040712	00201	GL  	2004	7	12	O05R200400116    	3	20040617	G	6114	C701	HUB             			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								814730		PROPELLER HUB CRACKED.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004092300085	20040923	00085	GL  	2004	9	23	O05R200400117    	3	20040617	G	6111	93KB0	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								814730		PROPELLER BLADE HAS A SCRATCH IN SHOTPEEN ON SHANK.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004092300095	20040923	00095	GL  	2004	9	23	O05R200400118    	3	20040617	G	6111	93KB0	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								814730		SCRATCH IN SHOTPEEN ON SHANK.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004120200205	20041202	00205	GL  	2004	12	2	O05R200400119    	3	20040617	G	6111	93KB0	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								814730		SCRATCH IN SHOT PEEN ON SHANK.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004120200206	20041202	00206	GL  	2004	12	2	O05R200400120    	3	20040617	G	6111	93KB0	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09								814730		SCRATCH IN SHOT PEEN ON SHANK.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004120200207	20041202	00207	GL  	2004	12	2	O05R200400121    	3	20040617	G	6111	93KB0	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09								814730		SCRATCH IN SHOT PEEN ON SHANK.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004120200208	20041202	00208	GL  	2004	12	2	O05R200400122    	3	20040617	G	6111	93KB0	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09								814730		SCRATCH IN SHOT PEEN ON SHANK.						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2004092300089	20040923	00089	GL  	2004	9	23	O05R2004117      	3	20040617	G	6111	93KBO	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	SCRATCHED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05								814730		SCRATCH IN SHOTPEEN ON SHANK.  AMMENDED SERIAL NO IN BOX 5 (D)     BF024						1	L	7	2 	3T			RT	A7CE    		5	C	P60GL
2005042100030	20050421	00030	CE  	2005	4	21	PF212LWAA        	1	20041223	G	5610	10138402518	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  										COCKPIT	CRACKED         	P				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CE	07	212LW					BB1420				IN CRUISE FLIGHT AT FL290 IN VMC ON IFR FLIGHT PLAN WITH OAT OF -45C, INNER PANE OF CO-PILOTS WINDSHIELD SHATTERED WITHO	UT WARNING.					1	L	7	2 	4T				A24CE
2005082200091	20050822	00091		2005	8	22	PG9R97674        	2	20041013	G	7313	6899001	FUEL NOZZLE     																	ENGINE	CRACKED         	B			PG9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19			1627 							CRACKED SHROUD AND SPRAY BODY, REPLACED.  IT IS BEING SUGGESTED THAT THESE NOZZLES BE PRESSURE TESTED (AIR OR LIQUID) PR	IOR TO BEING RELEASED FOR SERVICE.  IT IS FURHER SUGGESTED THAT QC DEPARTMENT BE INCLUDED IN THIS PROCESS.  THESE SUGGES	TIONS ARE OF COURSE TO PREVENT LOSS OF VENENUE AND MOST OF ALL, SAFETY.  (BN-FSDO)
2005082200090	20050822	00090	GL  	2005	8	22	PG9R97676        	2	20041013	G	7310	6899001	FUEL NOZZLE     			CESSNA	STC   	STC206C     	1182107	CE  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	CRACKED         	B			PG9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	22425		1412 			45743	890233			NOZZLE CRACKED/ REPLACED. (K)						1	H	7	1 	3O	3	U	NT	A4CE    	E1GL
2005082200087	20050822	00087	GL  	2005	8	22	PG9R97678        	2	20041013	G	7310	6899001	FUEL NOZZLE     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SHROUD	CRACKED         	B			PG9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	1076T		1537 			45373				CRACKED SHROUD/ REPLACED.  (K)						1	G	7	1 	3U	3	U		H2SW    	E1GL
2005082200088	20050822	00088	GL  	2005	8	22	PG9R97679        	2	20041013	G	7313	6899001	FUEL NOZZLE     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	CRACKED         	B			PG9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	10761	1397 				45381				CRACKED SHROUD AND SPRAY BODY/ REPLACED.  (K)						1	G	7	1 	3U	3	U		H2SW    	E1GL
2005030200076	20050302	00076	NM  	2005	3	2	PG9R97903        	1	20041021	G	1410	900D3409526105	LINE            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					OIL SYSTEM	LEAKING         	B			PG9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	368PA					90000012				FOUND TO BE LEAKING A SMALL QUANTITY OF OIL/ REPLACED OIL HOSE ASSY. (K)						1	G	7	2 	3U	3	U	NC	H19NM   	E42NE
2005021700003	20050217	00003	GL  	2005	2	17	PG9R97953        	2	20041105	G	7313	6899001	FUEL NOZZLE     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					ENGINE	CRACKED         	B			PG9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	3895D		1480 			45590				FUEL NOZZLE SPRAY SHROUD CRACKED.  A NEW MATERIAL SHOULD BE USED FOR THE SPRAY SHROUD.  (K)						1	G	7	1 	3U	3	U		H2SW    	E1GL
2004091400178	20040914	00178		2004	9	14	QH52004F00000    	4	20040514	G	2210	AC66375	HOUSING         			BBAVIA	7     	7AC         	2110102	SW  										SERVO ACTUATOR	CRACKED         	B			QH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	3060					7AC6649				THIS PART WAS TESTED IAW MFG 65-40-03.  CRACKED LOCATED AT THE OIL GALLERY.						1	H	7	1 	3O			 	A759
2007010800136	20070108	00136	GL  	2007	1	8	QKPR06008        	1	20040513	G	4930	38828406	FCU             	HONEYWELL   	GTCT36150RR 	DOUG  	A4D   	A4D         	       	GL  										APU	LEAKING         	B			QKPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05										FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUA	LLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO 	EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD. * REMOVE AIRCRAFT INFORMATIO	N.			2	L	7	1 	4R			RT	A1GL
2004050600027	20040506	00027	CE  	2004	5	6	RAFAR182         	1	20040311	G	5540	22601145	TORQUE TUBE     	CESSNA      		CESSNA	182   	R182        	2072734	CE  										ZONE 100	DETACHED        	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	09	736ZX	5075 				R18200813				LT RUDDER BAR TORQUE TUBE ASSEMBLY, PN 2260114-5 FAILURE. FAILURE OCCURRED IN FLIGHT RESULTING IN LT SIDE PILOT'S TOTAL 	LOSS OF LT RUDDER AND STEERING CONTROL. NATURE OF FAILURE; LT OB RUDDER PEDAL SOCKET ON TORQUE TUBE BROKE AWAY FROM THE 	TORQUE TUBE. THERE IS NO OBVIOUS REASON WHY THIS MIGHT HAVE HAPPENED. THERE ARE NO BENT OR DAMAGED COMPONENTS WITHIN THE	 SAME SYSTEM, AND THE STEEL TORQUE TUBE HAS ONLY VERY LIGHT INTERNAL CORROSION.			1	H	7	1 	3O			RT	3A13
2004102600116	20041026	00116	CE  	2004	10	26	RO12004F00000    	1	20041004	G	2420		BRUSHES         	CESSNA      		CESSNA	172   	172S        	2072439	CE  										ALTERNATOR	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	3555L	640  			A128904	172S8865				THIS IS THE 3RD OCCURRENCE OF ALTERNATOR FAILURE IN NEW MFG ALTERNATORS.  EACH TIME ONE OF THE FIELD BRUSHES WAS FOUND I	NSTALLED WITH THE WIRE TOWARD THE SLIP RING (BACKWARDS).  THIS IS THE 2ND M AND D REPORT SUBMITTED REGARDING THIS SAME I	NCIDENT.  NEED TO INFORM MFG OF SITUATION.				1	H	7	1 	3O			NT	3A12
2004022700083	20040227	00083	SW  	2004	2	27	ROSENBERG        	1	20040123	G	3240	MILH5606	FLUID           			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					BRAKE SYSTEM	SOLIDIFIED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	108MB	947  				290008				DURING ANNUAL INSPECTION IT WAS NOTED THAT THE AIRCRAFT WAS VERY HARD TO TAXI. TOOK HIGH RPM'S TO GET AIRCRAFT TO MOVE A	ND PULLED TO THE RIGHT. CHECKED BRAKES. FOUND BRAKE FLUID IN WHEEL CYLINDER HAD TURNED TO CONSISTENCY OF HONEY.  OWNER H	AD NOT GRIPPED ANY BRAKE PROBLEM ON GRIP LIST, AND WHEN CONTACTED, SAID HE HAD NO PROBLEMS WHEN LAST FLOWN. THE BRAKE PE	DALS TOOK VERY HARD FOOT PRESSURE TO PUSH FLUID THROUGH WHEN BLEEDING OUT BAD FLUID.  THE AIRCRAFT IS 10 YEARS OLD AND I	T IS BELIEVED TO BE ORIGINAL FLUID.		1	L	7	1 	3O	3	O	RT	2A3     	E3SO
2004091400166	20040914	00166	SO  	2004	9	14	RX8R2004001      	1	20040521	G	1430	AN3H7A	BOLT            	PIPER       		PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ZONE 700	SHEARED         	B			RX8R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	15	9142B					425501038	PCE99080	BU16835		WHILE TAXIING AFTER LANDING, THE PILOT DISCOVERED THE AIRCRAFT WOULD NOT TURN TIGHT.  AFTER EXAMINATION, IT WAS FOUND TH	E (3) AN-3 BOLTS THAT SECURE THE NOSE STEERING LINKAGE TO THE TOP OF THE NOSE LANDING GEAR STRUT HAD SHEARED.  FOUR OTHE	R AIRCRAFT WERE EXAMINED AND ONE AIRCRAFT WAS FOUND TO HAVE ONE BOLT STRIPPED OUT. WE RECOMMEND THESE BOLTS BE CHECKED O	NCE A YEAR FOR TORQUE.			1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA
2004120900111	20041209	00111	SO  	2004	12	9	RX8R2004002      	1	20041203	G	3213	5768007	STRUT           			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ZONE 700	CRACKED         	B			RX8R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	9116Q	6423 	65   			425501037	PCE99073	BUA27501		RIGHT MAIN LANDING GEAR STRUT CRACKED AT ATTACH POINT TO ACTUATING BRACE.  CRACK IS 2.5 INCHES LONG ALONG AFT SIDE OF AF	T ATTACH POINT LUG.  CRACK IS AT SAME LOCATION THAT GETS INSPECTED IAW PIPER SERVICE BULLETIN 969.  AREA WAS INSPECTED P	ER SB 65.2 HRS. AGO, USING DYE PENETRANT.  THERE WAS NO CRACK AT THAT TIME.				1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA
2004100100069	20041001	00069	SO  	2004	10	1	SD92004F00000    	1	20040809	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										RT ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	53395	2918 				4496076				ENGINE MOUNT TUBE BROKEN BELOW RT ISOLATOR.  DISCOVERED DURING 100 HOUR INSPECTION.						1	L	7	2 	3O			 	A19S0
2004072100058	20040721	00058	NE  	2004	7	21	SEA04LA125       	2	20040715	G	8530		CYLINDER        			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R134059     	52016	NE  					ENGINE	CRACKED         	G			TZKG	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NM	11	7502Y		696  			821B	19771			CYLINDER SEPARATED BETWEEN 2ND AND 3RD HORIZONTAL FINS THROUGH THE SPARK PLUG BOSS.  ENGINE LOST POWER AND THE AIRCRAFT 	NOSED OVER ON EMERGENCY LANDING CAUSING SUBSTANTIAL DAMAGE.  THIS CYLINDER HAD BEE OVERHAULED THREE PREVIOUS TIMES.					1	Q	7	1 	3R	3	R	 	1A16    	5E2
2004050600035	20040506	00035	CE  	2004	5	6	SO1450           	1	20040322	G	2710	05232182	ROD             			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERONS	BENT            	C				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			SO	05	7275G	1898 	20   			17280788	L2848551A			DURING PREFLIGHT, PILOT FOUND LT AILERON CONTROL ROD BENT AT AILERON SURFACE. AIRCRAFT GROUNDED AND TAKEN TO MAINTENANCE	. REMOVED LT AILERON CONTROL ROD AND FOUND IT TO BE BENT APPROXIMATELY 25 DEGREES JUST AFT OF AFT ROD END BEARING. REPLA	CED WITH NEW ROD.				1	H	7	1 	3O	3	O	NT	3A12    	1E10
2004071200160	20040712	00160	CE  	2004	7	12	SO1550           	1	20040610	G	5531	053100695	RIB             			CESSNA	172   	172N        	2072434	CE  										VERTICAL STAB	CRACKED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			SO	05	1951F	3420 				17273041				DURING HIDDEN DAMAGE INSPECTION AFTER BIRDSTRIKE ON VERTICAL STABILIZER LEADING EDGE, FOUND FORMING RIB ASSY CRACKED. RE	PLACED WITH NEW PART.					1	H	7	1 	3O			NT	3A12
2004030300184	20040303	00184	NM  	2004	3	3	SROM200400001    	1	20040217	G	3397		WIRE            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					EMERGENCY LIGHT	DAMAGED         	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	736BP		6    			23465				AFT LEFT EMERGENCY EXIT LIGHT UNDER FA JUMP SEAT INOPERATIVE.  REPAIRED WIRE TO LIGHT ASSEMBLY.  LIGHT OPS NORMAL WITH E	MERGENCY LIGHTS TURNED ON.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030300185	20040303	00185	NM  	2004	3	3	SROM200400002    	1	20040220	G	5310	655495616	SHEAR TIE       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND ELONGATED HOLE IN SHEAR TIE AT STA 500 BETWEEN STR 16R AND 17R, FORWARD UPPER HOLE.  REM	OVED DAMAGED SHEAR TIE.  FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE IAW B737 SRM 53-10-4.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400028	20040304	00028	NM  	2004	3	4	SROM200400003    	1	20040223	G	5310	654652548	SHEAR TIE       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND SHEAR TIE AT STA 380 BETWEEN STR 20R AND 21R HAS HOLES THAT ARE LARGER THEN SRM LIMITS. 	 REMOVED DAMAGED SHEAR TIE, FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE IAW B737 SRM 51-40-3.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400029	20040304	00029	NM  	2004	3	4	SROM200400004    	1	20040224	G	5340	6935352U14	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND CRACKED STRINGER CLIP AT STA 639, STR 4L.  REMOVED DAMAGED CLIP, ORDERED AND INSTALLED N	EW CLIP IAW B737 SRM 51-30-2					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400030	20040304	00030	NM  	2004	3	4	SROM200400005    	1	20040223	G	5340	6935352U14	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND CRACKED STRINGER CLIP AT STA 639, STR 4R.  REMOVED DAMAGED CLIP, ORDERED AND INSTALLED N	EW STRINGER CLIP IAW B737 SRM 51-30-2.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400031	20040304	00031	NM  	2004	3	4	SROM200400006    	1	20040223	G	5340	6935352U14	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND CRACKED STRINGER CLIP AT STA 616, STA 4L.  REMOVED DAMAGED CLIP, ORDERED AND INSTALLED N	EW STRINGER CLIP IAW B737 SRM 51-30-2					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400104	20040304	00104	NM  	2004	3	4	SROM200400007    	1	20040225	G	5311	6546519540	FRAME           			BOEING	737   	737205      	1384456	NM  										APU BAY	CORRODED        	A			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND NON-CPCP CORROSION ON LOWER T-CHORD IN APU CAVITY RT BULKHEAD AT STA 1120-1130.  REMOVED	 DAMAGED T-CHORD, ORDERED AND INSTALLED NEW T-CHORD IAW SRM 51-30-2.					2	L	7	2 	4F			RT	A16WE
2004030400105	20040304	00105	NM  	2004	3	4	SROM200400008    	1	20040225	G	5310	654654851	SHEAR TIE       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND AT STA 747 SHEAR TIE CRACKED AT FASTNER HOLE BETWEEN STR 20L AND 21L.  REMOVED DAMAGE, F	ABRICATED AND INSTALLED REPAIR SHEAR TIE IAW SRM 53-10-4.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400106	20040304	00106	NM  	2004	3	4	SROM200400009    	1	20040225	G	5513	654577428	STRINGER        			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	ELONGATED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND AFT CARGO PIT STRINGER 20L HAS SEVERAL ELONGATED FASTNER HOLES AND MULTIPLE CRACK INDICA	TIONS AROUND HOLES STA 747 TO 887.  REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR STRINGER AND SPLICES IAW SRM 53-10-3	.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400107	20040304	00107	NM  	2004	3	4	SROM200400010    	1	20040226	G	5340	69353521	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND STRINGER TO FRAME CLIP CRACKED AT STA 495-500, STR 24R.  REMOVED DAMAGED STRINGER CLIP, 	FABRICATED AND INSTALLED REPLACEMENT STRINGER CLIP IAW B737 SRM 51-20-1, 51-30-2.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400108	20040304	00108	NM  	2004	3	4	SROM200400011    	1	20040226	G	5330	65479576	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND AFT PIT STA 807 LOWER FORWARD CARGO CUTOUT HAS NON-CPCP CORROSION.  REMOVED DAMAGE FABRI	CATED AND INSTALLED REPAIR DOUBLER IAW 53-10-1, 51-40-3 AND 51-30-2.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004030400109	20040304	00109	NM  	2004	3	4	SROM200400012    	1	20040226	G	5310	654652510	SHEAR TIE       			BOEING	737   	737205      	1384456	NM  										ZONE 100	OVERSIZED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND SHEAR TIE AT STA 380 BETWEEN STR 19R AND 20R HAS HOLES THAT ARE LARGER THEN SRM LIMITS. 	 REMOVED DAMAGED SHEAR TIE, FABRICATED REPLACEMENT SHEAR TIE IAW SRM 53-10-4.					2	L	7	2 	4F			RT	A16WE
2004030400110	20040304	00110	NM  	2004	3	4	SROM200400014    	1	20040226	G	5310	693741210	SHEAR TIE       			BOEING	737   	737205      	1384456	NM  										ZONE 200	ELONGATED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND ELONGATED HOLE IN SHEAR TIE AT STA 400 BETWEEN STR 14R AND 15R AT UPPER HOLE.  REMOVED D	AMAGE, FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE AND REPAIR DOUBLER IAW SRM 53-10-4.					2	L	7	2 	4F			RT	A16WE
2004030400111	20040304	00111	NM  	2004	3	4	SROM200400015    	1	20040226	G	5313	654577835	STRINGER        			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	ELONGATED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND AFT CARGO PIT STRINGER 21R HAC ELONGATED HOLE STA 927.  REMOVED DAMAGE, FABRICATED AND I	NSTALLED REPAIR FILLER CHANNEL SRM 53-10-3.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004042900029	20040429	00029	NM  	2004	4	29	SROM200400016    	1	20040302	G	5313	6545800124	STRINGER        			BOEING	737   	737205      	1384456	NM  										ZONE 100	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND E AND E COMPARTMENT LOWER LOBE INTERIOR HAS CORROSION IN STR 28L BETWEEN STA 316 AND 328	.  REMOVED DAMAGED STRINGER CHANNEL, ORDERED AND INSTALLED NEW STRINGER SECTION IAW MFG SRM 51-30-12.  CPCP LEVEL 1 FIND	ING.				2	L	7	2 	4F			RT	A16WE
2004042900030	20040429	00030	NM  	2004	4	29	SROM200400017    	1	20040302	G	5342	6549857503	ATTACH FITTING  			BOEING	737   	737205      	1384456	NM  										ZONE 300	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963				23466				DURING D CHECK INSPECTION FOUND LT HORZ. STAB T/E I/B ATTACH FITTING HAS SMALL GOUGES.  BLENDED AREA, REMOVED DAMAGE, FL	AP PEENED, TREATED AND PRIMED IAW ASA EA 5510-01186 AND AAR EA 10289.					2	L	7	2 	4F			RT	A16WE
2004042900031	20040429	00031	NM  	2004	4	29	SROM200400018    	1	20040302	G	5313	654576814	STRINGER        			BOEING	737   	737205      	1384456	NM  										ZONE 100	OVERSIZED       	I			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND STR 20R BETWEEN STA 360 AND 400 HAS HOLES THAT ARE LARGER THAN SRM LIMITS.  REMOVED DAMA	GED STRINGER, FABRICATED AND INSTALLED REPLACEMENT STRINGER IAW B737 SRM 51-30-2.					2	L	7	2 	4F			RT	A16WE
2004050600040	20040506	00040	NM  	2004	5	6	SROM200400019    	1	20040308	G	5330	165457771	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 200	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION REQUESTED REMOVAL OF EXTERNAL DOUBLER FROM SKIN STA 970 TO 1016 LT STR 10L TO 14L.  RE-EVALUTE	D SKIN FOR DAMAGE.  REMOVED AND REPLACED SKIN IAW B737 SRM 51-30-2 STA 970 TO 1016 STR 10L TO 14L.					2	L	7	2 	4F			RT	A16WE
2004050600041	20040506	00041	NM  	2004	5	6	SROM200400020    	1	20040310	G	5313	6935352	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										ZONE 100	ELONGATED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND STINGER CLIP STA 495 STR 22R HAS A DAMAGED HOLE.  REMOVED DAMAGED CLIP, FABRICATED AND I	NSTALLED REPLACEMENT CLIP IAW B737 SRM 51-31-5.					2	L	7	2 	4F			RT	A16WE
2004051300028	20040513	00028	NM  	2004	5	13	SROM200400021    	1	20040312	G	5313	6545768103	STRINGER        			BOEING	737   	737205      	1384456	NM  										ZONE 100	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND STR 19R STA 360 - 440 HAS DAMAGE FROM EXISTING REPAIR (GOUGED).  REMOVED DAMAGE STRINGER	 SECTION, FABRICATED AND INSTALLED REPLACEMENT STRINGER IAW  SRM 51-30-5.					2	L	7	2 	4F			RT	A16WE
2004051300029	20040513	00029	NM  	2004	5	13	SROM200400022    	1	20040314	G	5311	654652353	FRAME           			BOEING	737   	737205      	1384456	NM  										ZONE 200	GOUGED          	A			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND GOUGES ON FORWARD SIDE OF FRAME STA 1104 BETWEEN 2ND AND 3RD STR UP FROM APU COMPARTMENT	 RT WEB.  REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER IAW SRM 51-40-3.					2	L	7	2 	4F			RT	A16WE
2004051300030	20040513	00030	NM  	2004	5	13	SROM200400023    	1	20040314	G	5320	6546585564	WEB             			BOEING	737   	737205      	1384456	NM  										ZONE 100	BENT            	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND HORIZONTAL WEB ABOVE APU BENT AT STA 1138.  REMOVED DAMAGE, FABRICATED AND INSTALLED REP	AIR DOUBLER IAW SRM 51-40-2.					2	L	7	2 	4F			RT	A16WE
2004051300031	20040513	00031	NM  	2004	5	13	SROM200400024    	1	20040314	G	5330	65457789	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 200	OUT OF LIMITS   	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND SKIN DOUBLER AT STA 1006 BETWEEN STR 11R AND 12R DOES NOT MEET SRM REQUIREMENTS.  REMOVE	D SKIN DOUBLER, FABRICATED AND INSTALLED REPLACEMENT SKIN IAW B737 SRM 51-20-1.					2	L	7	2 	4F			RT	A16WE
2004051300032	20040513	00032	NM  	2004	5	13	SROM200400025    	1	20040314	G	5330	6545771	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND DENT STA 400 BETWEEN STR 19L & 20L LESS THEN 3 INCHES FROM LAP RIVET AREA IS BEYOND LIMI	TS IAW SRM 53-30-1 FIG 1 DETAIL 3.  REF SAD LOG 4465763 BEYOND LIMITS DUE TO CHANGE IN SRM WHICH INCLUDED PROXIMITY TO S	EAM AND CUTOUT.  REMOVED DAMAGE FABRICATED AND INSTALLED REPAIR FILLERS, DOUBLER AND TRIPLER IAW SRM 53-30-3.				2	L	7	2 	4F			RT	A16WE
2004050700008	20040507	00008	NM  	2004	5	7	SROM200400027    	1	20040315	G	5313	654576822	STRINGER        			BOEING	737   	737205      	1384456	NM  										ZONE 100	BENT            	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND STR 24R BENT BETWEEN STA 420 AND 440.  REMOVED DAMMAGED SECTION OF STR 24R, FABRICATED A	ND INSTALLED REPAIR ANGLE IAW B737 SRM 53-10-3.					2	L	7	2 	4F			RT	A16WE
2004050700009	20040507	00009	NM  	2004	5	7	SROM200400028    	1	20040315	G	5242	6545830120	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 800	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION EEC DOOR EXTERIOR SKIN HAS LIGHT CORROSION AND BARE METAL.  REMOVED DAMAGED SKIN, FABRICATED A	ND INSTALLED REPLACEMENT SKIN IAW  SRM 51-30-2 AND MFG DRAWING NR 65-45830.					2	L	7	2 	4F			RT	A16WE
2004042900040	20040429	00040	NM  	2004	4	29	SROM200400032    	1	20040325	G	5511	6553746753	RIB             			BOEING	737   	737205      	1384456	NM  										ZONE 300	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND LT HORIZONTAL STABILIZER LOWER SINGLE LEG ATTACH RIB FORWARD OF AFT SPAR, CRACKED.   REM	OVED RIB, FABRICATED AND INSTALLED REPLACEMENT RIB IAW B737 SRM 51-20-1, 51-30-5.  STAB STA 67.54 - 69.					2	L	7	2 	4F			RT	A16WE
2004042900041	20040429	00041	NM  	2004	4	29	SROM200400033    	1	20040325	G	5330	65C80736834	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION C/W 069 LOG 4755642 REPLACE SKIN PANEL BS 908 - 1016 STR 20L TO 25L.  REMOVED SKIN PANEL, RECE	IVED AND INSTALLED NEW SKIN PANEL IAW MFG SRM 51-30-2.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004042900042	20040429	00042	NM  	2004	4	29	SROM200400034    	1	20040328	G	5330		DOUBLER         			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION FOUND DENT AT STA 338 TO 344 JUST BELOW FWD AIRSTAIR DOOR CUTOUT BEYOND LIMITS IAW SRM 53-30-1	 FIG 1 DETAIL 3.  REF. SAD LOG 0176053 BEYOND LIMITS DUE TO CHANGES TO SRM INCLUDING PROXIMITY TO CUTOUTS AND SEAMS.  RE	MOVED DAMAGED DOUBLER, FABRICATED AND INSTALLED REPLACEMENT REPAIR DOUBLER IAW ASA EA 5310-02327 AND AAR 10300.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300188	20040503	00188	NM  	2004	5	3	SROM200400035    	1	20040401	G	5330	OO72040400	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 061 LOG 4755634 REPLACE SKIN PANEL BS 173 - 259 STR 19R - 24R.  REMOVED AND REPLACED SKIN 	PANEL IAW B737 SRM 51-30-2.  SKIN REPLACE TO ELIMINATE PREVIOUS DENT REPAIRS.					2	L	7	2 	4F			RT	A16WE
2004050300189	20040503	00189	NM  	2004	5	3	SROM200400036    	1	20040401	G	5330	0072040410	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 062 LOG 4753635 REPLACE SKIN PANEL BS 360 - 540 STR 14R - 19R.  REMOVED AND REPLACED SKIN 	PANEL IAW B737 SRM 51-30-2.  REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300190	20040503	00190	NM  	2004	5	3	SROM200400037    	1	20040401	G	5330	65C80736824	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 063 LOG 4755636 REPLACE SKIN PANEL BS 360 - 540 STR 19R - 25R. REMOVED AND REPLACED SKIN P	ANEL IAW B737 SRM 51-30-2.  SIN REPLACED TO ELIMINATE PREVIOUS REPAIRS FOR DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300191	20040503	00191	NM  	2004	5	3	SROM200400038    	1	20040401	G	5330	65C3584336	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 064 LOG 4755637 REPLACE SKIN PANEL BS 727 - 968 STR 14R - 20R.  REMOVED AND REPLACED SKIN 	PANEL IAW B737 SRM 51-30-2.  PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS FOR DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300192	20040503	00192	NM  	2004	5	3	SROM200400039    	1	20040401	G	5330	0072040404	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 065 LOG 4755638 REPLACE SKIN PANEL BS 727 - 908 STR 20R - 25R.  REMOVED AND REPLACED SKIN 	PANEL IAW B737 SRM 51-30-2.  PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300193	20040503	00193	NM  	2004	5	3	SROM200400040    	1	20040401	G	5330	65C80736850	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 066 LOG 4755639 REPLACED SKIN PANEL MFG 908 STR 20L TO 25L.  REMOVED AND REPLACED SKIN IAW	 MFG SRM 51-30-2.  PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300194	20040503	00194	NM  	2004	5	3	SROM200400041    	1	20040401	G	5330	65C36745116	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W 067 LOG 4755640 REPLACE SKIN PANEL BS 908 - 1016 STR 20R - 25R.  REMOVED AND REPLACED SKIN	 PANEL IAW B737 SRM 51-30-2.  PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300195	20040503	00195	NM  	2004	5	3	SROM200400042    	1	20040401	G	5330	6545800Y135	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION C/W LOG 4755645 REPLACE SKIN PANEL BS 178-259 STR 24R - BLO.  REMOVED AND REPLACED SKIN PANEL 	IAW B737 SRM 51-30-2.  PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300196	20040503	00196	NM  	2004	5	3	SROM200400043    	1	20040331	G	5743	658276415	SUPPORT BEAM    			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	4514 			23466				DURING D CHECK INSPECTION LT MLG SUPPORT BEAM HAS CORROSION IN OB ATTACH HOLE IN BETWEEN BUSHINGS.  REMOVED BUSHINGS AND	 CORROSION.  INSPECTED AND INSTALLED REPLACEMENT BUSHINGS IAW MFG EA 5750-01939 AND EA 10537.  MINOR REPAIR.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300197	20040503	00197	NM  	2004	5	3	SROM200400044    	1	20040331	G	5330	6545775	BEAR STRAP      			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	BROKEN          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION BEAR STRAP HAS A HOLE BROKE FROM EDGE (NO E/D) STA 767, STR 18R.  TRIMMED DAMAGE, FABRICATED A	ND INSTALLED REPAIR FILLER IAW MFG EA. 5330-01764 AND MFG EA 10311.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300140	20040503	00140	NM  	2004	5	3	SROM200400045    	1	20040404	G	5315	65C3453711	FLOORBEAM       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION STA 651 FLOORBEAM, BL O REPAIR ANGLE HAS A FASTNER GIVING SHORTED ON P/N 65C34537-11 ANGLE.  T	RIMMED P/N 65C34537-11 ANGLE, FLAP PEENED, TREATED, PRIMED AND INSTALLED IAW ASA EA 5310-02318 AND AAR EA 10312.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050600030	20040506	00030	NM  	2004	5	6	SROM200400046    	1	20040405	G	5740	6549488501	FITTING         			BOEING	737   	737205      	1384456	NM  										ZONE 500	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION COMPLIED WITH EA 10324 AND ASA EA 5720-01237 (LT WING MLG SUPPORT BEAM FITTING INSPECTION AND 	REPLACEMENT, SB 737-57-1216 REV. 2)  REMOVED AND REPLACED LT WING SUPPORT BEAM FITTING IAW ASA EA 5720-01237 AND AAR EA 	10324.				2	L	7	2 	4F			RT	A16WE
2004050600031	20040506	00031	NM  	2004	5	6	SROM200400047    	1	20040405	G	5711	654532414	SPAR            			BOEING	737   	737205      	1384456	NM  										ZONE 600	ELONGATED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	33963			23466				DURING D CHECK RT WING UPPER SPAR AND SPAR WEB HAS ELONGATED HOLES.  REAMED HOLES, TRIMMED UPPER FOOTPRINT IAW ASA EA 57	20-01241 AND AAR EA 10336.					2	L	7	2 	4F			RT	A16WE
2004050600032	20040506	00032	NM  	2004	5	6	SROM200400048    	1	20040405	G	5314	6545866U205	KEELBEAM        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION TWO CRACKS FOUND ON KEELBEAM LOWER SKIN BETWEEN STA 660 AND 724 1 EA, 1.G INCH AND 1 EA. 1.25 	INCH.  REMOVED DAMAGE WEB, INSTALLED NEW WEB IAW B737 SRM 51-30-2.					2	L	7	2 	4F			RT	A16WE
2004050600033	20040506	00033	NM  	2004	5	6	SROM200400049    	1	20040405	G	5740	6549488502	FITTING         			BOEING	737   	737205      	1384456	NM  										ZONE 600	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION RT WING REAR SPAR TO MLG SUPPORT BEAM FITTING CRACKED AT IB UPPER CORNER.  REMOVED DAMAGED MLG	 SUPPORT BEAM FITTING AND INSTALLED A NEW MLG SUPPORT BEAM FITTING IAW ASA EA 5720-01238 AND EA 10325.					2	L	7	2 	4F			RT	A16WE
2004050300155	20040503	00155	NM  	2004	5	3	SROM200400050    	1	20040318	G	5330	6545775	BEAR STRAP      			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ZONE 100	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION,  BEAR STRAP HAS A HOLE BROKEN FROM EDGE (NO E/D) AT STA 767 AND STR 18R.  REMOVED DAMAGE, FAB	RICATED AND INSTALLED REPAIR FILLER IAW ASA EA 5330-01764 AND AAR EA 10311.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004050300156	20040503	00156	NM  	2004	5	3	SROM200400051    	1	20040408	G	5330	654688259	SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION DENT IN SKIN STA 1147.5, 8.5 INCHES ABOVE S5.  A=2 INCHES  Y=.056  A/Y=35.7, BUT DUE TO PROXIM	ITY OF CUTOUT FOR HORIZONTAL FITTING IT IS BEYOND LIMITS IAW SRM 53-30-1, FIG 1 NOTE K AND DETAIL 111.  COMPLIED WITH HF	EC.  NO DEFECTS NOTED, COMPLIED WITH IAW ASA EA 5330-01757 AND AAR EA 10285.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004051300027	20040513	00027		2004	5	13	SROM200400052    	4	20040411	G	2211		COMPUTER        			BOEING	737   	737205      	1384456	NM  										AUTOFLIGHT	MALFUNCTIONED   	C			SROM	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AL	03	733PA					23466				DURING POST D-CHECK FERRY FLIGHT, RETURNED TO DEPARTURE DUE TO AUTO PILOT CAPTURE LOC VERY SLUGGISH AND OVERSHOOTS DURIN	G CORRECTION.  WILL NOT CAPTURE GLIDE SLOPE.  ALSO, RADIO ALTIMETER DH LIGHT COMES ON WHEN DH IS SET ABOVE 2500 FT AGL S	TARTS INDICATING WHEN PASSING 600 FT, INDICATOR FLICKERS WILDLY UPON READING DH.  DURING CLIMB BETWEEN 4000 AND 5000 RAD	 ALT FLAGG APPEARED BRIEFLY.			2	L	7	2 	4F			RT	A16WE
2004051200019	20040512	00019	NM  	2004	5	12	SROM200400053    	1	20040410	G	5551	6552857	BUSHING         			BOEING	737   	737205      	1384456	NM  										HORIZONTAL STAB	WORN            	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33965				23466				DURING D CHECK INSPECTION RT HORIZONTAL STAB CENTER SECTION, AFT CENTER LUG FORWARD BUSHING FITTING WORN.  REMOVED DAMAG	E, INSTALLED REPAIR BUSHING IAW EA 5510-01191 AND AAR EA 10351.					2	L	7	2 	4F			RT	A16WE
2004051200054	20040512	00054	NM  	2004	5	12	SROM200400054    	1	20040509	G	3350	20131A	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	DISCHARGED      	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	736BP		6    			23465				DURING PREFLIGHT INSPECTION EMERGENCY LIGHTS AT ROWS 10, 11, 15, 16 AND 18 INOPERATIVE.  REPLACED BATTERY PACKS AT STATI	ONS 753 LT AND 629 RT.  OPS CHECK NORMAL.					2	L	7	2 	4F			RT	A16WE
2005022200181	20050222	00181	NM  	2005	2	22	SROM200400055    	1	20040620	G	3350	20131A	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	736BP		6    			23465				L2 DOOR EMERGENCY LIGHT INOP.  CHANGED OUT BATTERY PACK.  OPS CHECKED GOOD.						2	L	7	2 	4F			RT	A16WE
2005022200182	20050222	00182	NM  	2005	2	22	SROM200400056    	1	20040804	G	3350	30043231	LIGHT           			BOEING	737   	737201      	1384454	NM  										EXTERIOR	CORRODED        	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	245US		3    			22751				L2 DOOR EXTERIOR LIGHT INOP.  REMOVED AND REPLACED L2 EXTERIOR EMERGENCY LIGHT IAW B737 M/M 33-51-61 - OPS CH'D GOOD.						2	L	7	2 	4F				A16WE
2004092000053	20040920	00053	NM  	2004	9	20	SROM200400057    	1	20040905	G	3350	582212	POWER SUPPLY    			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					EMERGENCY LIGHT	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				R1 EMERGENCY EXIT SIGN INOPERATIVE.  REMOVED AND REPLACED R-1 EMERGENCY EXIT SIGN BATTERY PACK.  OPS CK GOOD IAW MM 33-5	1-00.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA
2004111000033	20041110	00033	NM  	2004	11	10	SROM200400058    	1	20041104	G	2821		FUEL FILTER     			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	ICED            	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			AL	03	245US					22751				DURING CRUISE NR 2 ENGINE FILTER ICING LIGHT CAME ON AND WOULD NOT CLEAR WITH FUEL HEAT.  OTHER ENGINE PARAMETERS INDICA	TE FUEL HEAT WAS OPERATIVE WITH ENGINE OPERATION NORMAL.  UNEVENTFUL RETURN TO DEPARTURE AIRPORT.  REMOVED AND REPLACED 	NR 2 ENGINE MAIN FUEL FILTER IAW WITH ,  MM 73-11-01 WITH GOOD ENGINE RUN.  NOTE:  REMOVED FILTER VISUALLY HAD SLIGHT AM	OUNT OF DEBRIS PRESENT.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA
2004122200138	20041222	00138	NM  	2004	12	22	SROM200400059    	1	20041203	G	2821	693733587	MODULE          			BOEING	737   	737201      	1384454	NM  										FUEL SYSTEM	MALFUNCTIONED   	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	245US					22751				"NR 2 ENG FUEL FILTER ICING LIGHT ILLUMINATED INFLIGHT FL 320.  FOLLOWED PROCEDURE LIGHT REMAINED ILLUMINATED.  RETURNED	 TO ANC"  THIS WAS A REPEAT WRITE-UP.  CONTINUITY CHECK AND INSPECTION OF ALL ACCESSIBLE WIRING NORMAL.  REPLACED FUEL M	ODULE , (AFTER TESTING BY VENDOR) REPLACED FUEL PRESSURE SWITCH P/N 42D185 WITH NEW UNIT AND REPLACED FUEL PRESSURE SWIT	CH CANNON PLUG WITH NEW.  OPERATIONAL CHECK FLIGHT CONDUCTED WITH NO FAULTS OBSERVED.  AIRCRAFT RETURNED TO SERVICE 12-1	0-04.		2	L	7	2 	4F			 	A16WE
2005030800187	20050308	00187	NM  	2005	3	8	SROM200400060    	1	20041221	G	5210	6990285	SEAL            			BOEING	737   	737205      	1384456	NM  										PAX DOOR	TORN            	C			SROM	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AL	03	733PA		814  			23466				"AT FL 280 & 6PSID A LOUD HIGH PITCHED NOISE AND VIBRATION AT L1 DOOR.  RETURNED TO ANC AND AS A/C DEPRESSURIZED THE NOI	SE LESSENED BUT DID NOT GO AWAY"  "INSPECTED FWD ENTRY DOOR IAW B737MM 52-11-0.  ADJUSTED DOOR STOP PINS AND UPPER GATE 	DOOR IAW B737 MM 52-11-0, OPERATIONAL CHECK GOOD".  DURING GROUND PRESSURIZATION CHECK ORIGINAL PROBLEM WAS DUPLICATED. 	 FURTHER INSPECTION FOUND TEAR IN RUBBER SEAL OF THE HINGE FLAP ASSY LOCATED UNDER THE UPPER HINGE COVER.  FURTHER GROUN	D PRESSURE CHECK CONFIRMED THIS TO BE THE PROBLEM.  REPLACED HINGE FLAP ASSY.		2	L	7	2 	4F			RT	A16WE
2004050700010	20040507	00010	NM  	2004	5	7	SROM20040029     	1	20040318	G	5330	65457789	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION DENT AT STA 479, 12 INCHES BELOW CARGO DOOR.  EDGE OF DENT LESS THAN 3 INCHES FROM CLOSEST FAS	TNERS IN LAP IAW SRM 53-30-1, FIG. 1 DETAIL 3, DENT IS BEYOND LIMITS.  REF. SAD LOG NR 4600061.  AREA IS NOW BEYOND LIMI	TS DUE TO CHANGES IN SRM WHICH INCLUDE PROXIMITY TO CUTOUT, LAP SEAMS AND BUTT SPLICES.  REMOVED DAMAGE, FABRICATED AND 	INSTALLED REPAIR DOUBLERS IAW ASA EA 5330-01766 AND AAR EA. 10304.			2	L	7	2 	4F			RT	A16WE
2004050700011	20040507	00011	NM  	2004	5	7	SROM20040030     	1	20040318	G	5311	6545800	FRAME           			BOEING	737   	737205      	1384456	NM  										ZONE 100	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	7874 			23466				DURING D CHECK INSPECTION FOUND LOSS OF E.D. AT HOLE ON STA 251 FRAME AND W/W LT HAND EDGE STRAP.  REMOVED DAMAGED AREA,	 FABRICATED AND INSTALLED REPAIR FILLER IAW EA 5330-01765 AND  E.A. 10340.					2	L	7	2 	4F			RT	A16WE
2004051300036	20040513	00036	NM  	2004	5	13	SROM20040031     	1	20040323	G	5330	6552988473	SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 100	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	33963	1703 			23466				DURING D CHECK INSPECTION C/W 068 LOG 4755641, REPLACE SKIN PANEL BS 908 - 1016, STR 14L - 20L.  REMOVED SKIN, INSTALLED	 NEW SKIN PANEL IAW SRM 51-30-2.  REPLACED AT CUSTOMER REQUEST DUE TO DENT.					2	L	7	2 	4F			RT	A16WE
2004101800185	20041018	00185	EU  	2004	10	18	SWISSFAA         	1	20040805	G	5210		CANOPY          			PILATS	P3    	P305        	7090101	EU  						HARTZL	HCA3X	HCA3X*      	GL  	COCKPIT	BLOCKED         	Z				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	99						VARIOUS		VARIOUS		TO OUR KNOWLEDGE, AT LEAST 11 N-REGISTERED P-3 HAVE BEEN MODIFIED UNDER 337 FIRLD APPROVALS WITH A ONE-PIECE COCKPIT CAN	OPY REPLACING THE MULTIPLE SHEET CANOPY INITIALLY INSTALLED.  ON AN AIRCRAFT RETURNED TO SWITZERLAND AN UNSAFE CONDITION	 WAS DISCOVERED. THE EMERGENCY CANOPY JETTISON COULD NOT BE OPERATED SINCE THE MECHANISM WAS BLOCKED BY TWO RIVNUTS INST	ALLED TO RETAIN THE NEW CANOPY.  WE HAD THE FAULTY INSTALLATION MODIFIED TO MAKE IT WORK. WE LET YOU KNOW OF THIS DEFECT	 SINCE THERE ARE SOME MORE P-3S OPERATED UNDER FAA REGISTRY THAT MIGHT HAVE THE SAME UNSAFE CONDITION.		1	L	7	1 	3O			RT	        		5	C	P913
2004051300038	20040513	00038	SO  	2004	5	13	T0438            	1	20040504	G	1100		DATA PLATE      			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	DEPARTED        	B				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			SW	05	424PW	197  	197  			3257186	RL900561A			ENGINE DATA PLATE RIVETS ARE BECOMING LOOSE CAUSING THE DATA PLATE TO SEPARATE FROM ENGINE. WE ARE SEEING THIS ON SEVERA	L ENGINES.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA
2004091500090	20040915	00090	EA  	2004	9	15	TL9R200400001    	1	20040611	G	3246	5010598	WHEEL           			CNDAIR	CL600 	CL600*      	       	EA  										ZONE 700	DAMAGED         	B			TL9R	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	13										REPORTED REMOVAL REASON WAS (BEARING FAILURE).  BOTH WHEEL HALVES REJECTED DUE TO BEARING BORE DAMAGE.  OPERATOR IS INVE	STIGATING THE CAUSE.					2	L	7	2 	4F			RT	A21EA
2004083000089	20040830	00089	EU  	2004	8	30	TL9R200400002    	1	20040724	G	3242	C20225310	BRAKE           			AIRBUS	320   	A320233     	3930329	EU  										NR 1	BINDING         	B			TL9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										THE A320 NR 1 BRAKE WAS REMOVED AS WORN TO LIMITS. THERE WERE NO OPERATIONAL PROBLEMS OR UNUSUAL INDICATIONS LEADING UP 	TO THE REMOVAL.  WHILE ATTEMPTING TO REMOVE THE NR 1 MAIN WHEEL TO FACILITATE REMOVAL OF THE BRAKE, IT WOULD NOT COME OF	F AS THE BRAKE WAS JAMMED INTO THE WHEEL. THE WHEEL AND BRAKE WERE REMOVED AS ONE PIECE.  BRAKE ROTOR DRIVE BLOCKS WERE 	DISCOVERED TO HAVE SEPARATED FROM THE ROTOR CAUSING THE WHEEL AND BRAKE TO BE JAMMED AGAINST EACH OTHER.			2	L	7	2 	4F			RT	A28NM
2005022200040	20050222	00040	EU  	2005	2	22	TXER095702       	1	20040608	G	6320	C632A0201053	GEARBOX         			UROCOP	EC120 	EC120B      	8680987	EU  										MAIN ROTOR	MAKING METAL    	B			TXER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	690WR	1265 				1059				MAKING METAL.						1	G	7	2 	3U			NC	R0001RD
2005022200041	20050222	00041	EU  	2005	2	22	TXER095703       	1	20040608	G	6320	C632A0101052	EPICYCLIC       			UROCOP	EC120 	EC120B      	8680987	EU  										M/R GEARBOX	MAKING METAL    	B			TXER	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	09	690WR					1059				MAIN ROTOR GEARBOX EPICYCLIC MAKING METAL.						1	G	7	2 	3U			NC	R0001RD
2005022200123	20050222	00123	EU  	2005	2	22	TXER096384       	1	20040713	G	6730	SC5072	SERVO           			AEROSP	AS355 	AS355*      	       	EU  										TAIL ROTOR	BINDING         	B			TXER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	151TA	4090 				2601				TAIL ROTOR SERVO IS BINDING.						1	G	7	2 	3U				H11EU
2004112300003	20041123	00003	EU  	2004	11	23	TXER097946       	1	20041017	G	6400	365A33354300	FAIRING         			UROCOP	EC155 	EC155B      	8681000	EU  										TAIL ROTOR	CRACKED         	B			TXER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	155EW	376  				6660				TAIL ROTOR FAIRING CRACKED.						1	G	7	2 	3U				H10EU
2004090800028	20040908	00028	SO  	2004	9	8	UXCR200400002    	1	20040826	G	1410	LW18724	HOSE            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  	HARTZL	HCI3Y	HCI3YR2     	GL  	FUEL SYSTEM	FLAKING         	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			SW	05	4128K	874  	5    			4636178	L1005261A	HK325A		DURING CLIMB TO ALTITUDE, THE ENGINE EXHIBITED A ROUGH RUNNING CONDITION THAT NECESSITATED A REDUCTION IN POWER REQUIRIN	G AN UNSCHEDULED LANDING. INSPECTION OF THE ENGINE FUEL INJECTION SYSTEM REVEALED TWO OBSTRUCTED INJECTOR NOZZLES (NR 2 	AND NR 4 CYLINDERS).  UPON FURTHER INSPECTION, IT WAS DETERMINED THE UPPER DECK AIR MANIFOLD HOSES WERE FLAKING MATERIAL	 FROM THE INTERNAL WALL SURFACE SUFFICIENT IN SIZE TO OBSTRUCT THE INJECTOR ORIFICE.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA	5	C	P33EA
2004052500029	20040525	00029	GL  	2004	5	25	W592004F00000    	3	20040127	G	6110	C4513	SPACER          			CESSNA	150   	A150L       	2071828	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER	CRACKED         	B			W59R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9903G				G13417	A1500456		G13417		PROPELLER SPACER WAS FOUND CRACKED FROM DOWEL PIN HOLES.  ONE CRACK PROGRESSED COMPLETELY THROUGH SPACEER, THE SECOND WA	S 90 PERCENT THROUGH SPACER.  PROPELLER DOWEL PIN HOLES ARE ELONGATED AND OVERSIZE, PROPELLER WAS BENT SEVERELY AT ONE T	IME AND IMPROPERY REPAIRED.  ANGLES WERE WELL OUT OF SPEC, SOME AS MUCH AS 1 DEGREE.  PROPELLER WAS OUT OF BALANCE TRACK	 AND ANGLES.  SUSPECT SEVERE VIBRATION FROM PROPELLER OR PREVIOUS IMPACT DAMAGE CAUSED SPACER TO CRACK.  PROPELLER AND S	PACER ARE SCRAP.		1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918
2004060100012	20040601	00012	CE  	2004	6	1	WK1              	1	20040513	G	2121	50041	MOTOR           			BEECH 	200   	A200        	1152921	CE  										CABIN	FAILED          	G			K7MA	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			WP	11	639B		73   			BC67				SHORTLY AFTER TAKEOFF SMOKE WAS OBSERVED IN THE COCKPIT WITH ELECTRICAL ODOR. FORWARD CABIN VENT BLOWER WAS DISABLED AND	 THE SMOKE CLEARED. VENT BLOWER HAD FAILED INTERNALLY.					1	L	7	2 	4T			 	A24CE
2004022700086	20040227	00086	SW  	2004	2	27	WYNBRANDT        	1	20040202	G	3240	MILH5606	FLUID           			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					BRAKE SYS	SOLIDIFIED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	963PM	2503 				251158				DURING A ROUTINE OIL CHANGE IT WAS NOTED THAT THE AIRCRAFT TOOK VERY HIGH RPM TO TAXI. THE BRAKE FLUID IN THE WHEEL CYLI	NDER HAD TURNED THE CONSISTENCY OF HONEY. THE FLUID WAS PURGED BY BLEEDING USING PEDALS PRESSURE TO MOVE FLUID OUT. THE 	BRAKE BLEEDERS HAD TO BE REMOVED TO GET FLUID TO FLOW. THIS IS THE SECOND AIRCRAFT WITHIN THE PAST 2 WEEKS WE HAVE FOUND	 THIS PROBLEM ON. THE TOTAL TIME ON THIS FLUID IS UNKNOWN, SINCE WE HAVE NOT MAINTAINED IT SINCE NEW AS WE DID THE OTHER	 AIRCRAFT WITH THE SAME PROBLEM. IT IS BELIEVED TO BE ORIGINAL.		1	L	7	1 	3O	3	O	 	2A3     	E9CE
2004030300102	20040303	00102	CE  	2004	3	3	YK1R062001       	1	20040227	G	4920	GTCP36150W	APU             			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					APU BAY	FAILED          	B			YK1R	H	E			DEACTIVATE SYST/CIRCUITS	ENGINE SHUTDOWN         			B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SW	11	653XP	11   	11   			258653				DURING TAXI, SMOKE RAPIDLY FILLED THE COCKPIT AND THE CABIN.  EMERGENCY SHUTDOWN OF ALL SYSTEMS WAS PERFORMED, GROUND EM	ERGENCY DECLARED AND AIRCRAFT EVACUATED.  IT WAS FOUND DUE TO FAILURE IN THE APU, OIL ENTERED THE BLEED AIR DUCT WHICH C	AUSED THE SMOKE.  SYSTEM IS IN TROUBLESHOOTING/TEARDOWN PROCESS.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
2004090100083	20040901	00083	NE  	2004	9	1	Z1RA096970       	1	20040823	G	7601	0177987070	TORQUE BOX      			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	INTERMITTENT    	C			Z1RA	O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			SW	11	760AF	1890 				760523				REPLACED TORQUE TRIM CONFORMATION BOX. NO FURTHER DEFECTS						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
2005030800001	20050308	00001		2005	3	8	ZN3R200503A      	2	20041001	G	7250	384001117	TURBINE WHEEL   																	ENGINE	DAMAGED         	B			ZN3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07										TURBINE BLADES WERE FOUND VISUALLY VERY "THIN" IN THE TIP AREA AFTER OPERATION.