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
2007050700187	20070507	00187	NE  	2007	5	7	0088867          	3	20051208	G	6111	10075681	BLADE           			EMB   	120   	EMB120      	3260201	SO  						HAMSTD	14RF	14RF9       	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										PROPELLER BLADE NICKEL SHEATH CRACKED.						2	L	7	2 	4T			RT	A31SO   		6	C	P11NE	 
2005050400058	20050504	00058	EA  	2005	5	4	041251           	1	20050412	G	4950	38462341	CLAMP           	GARRTT      		CNDAIR	CL600 	CL6002A12   	1900304	EA  										APU DUCT	BROKEN          	B				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		IN	INSP/MAINT     	1			CE	01	601RC	14   				3055				APU HAD BEEN RUNNING ON THE GROUND FOR APPROXIMATELY ONE HOUR AND SHUT ITSELF DOWN DUE TO HIGH OIL TEMP AS INDICATED BY 	(BYTE) LIGHT.  VISUAL INSPECTION SHOWED THAT BLEED AIR ELBOW HAD BROKEN OFF OF EXHAUST STACK CLAMP AT THE WELD.  RECOMME	ND REGULAR VISUAL INSPECTIONS FOR CRACKS ON THE STRAP THAT HOLDS THE TUBE TO THE CLAMP.  IN ADDITION, METHOD OF ATTACHME	NT OF TUBE TO THE CLAMP BE MODIFIED TO REDUCE SHARP CORNERS WHERE CRACKS ORIGINATE.			2	L	7	2 	4F			RT	A21EA   					 
2006012500006	20060125	00006	SO  	2006	1	25	050143850        	1	20051213	G	5100		BOLT            			PIPER 	PA28  	PA28181     	7102807	SO  										PROPELLER	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	30034					2843576				DURING REMOVAL OF PROP TO ACCESS BELTS, FOUND ONE PROP BOLT SEVERELY PITTED.  ONLY THE ONE BOLT SHOWED ANY SIGNS OF CORR	OSION.  BOLT HAD ONLY 350 HOURS FROM ORIGINAL FACTORY INSTALL.  BOLT WAS REPLACED AND DIGITAL PHOTO'S WERE SUPPLIED MFG 	TECH SERVICES.				1	L	7	1 	3O				2A13    					 
2005080200103	20050802	00103		2005	8	2	05085444         	4	20050729	G	2300	7000700665	ADC             			CESSNA	650   	650         	2076802	CE  										AVIONICS BAY	INTERFERENCE    	B				O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			CE	03	47AN	6718 				6500054				NR 2 COM INTERFERENCE ON FREQUENCY 127.975.  INTERFERENCE IS COMING FROM BOTH AZ-810 ADC'S. HONEYWELL TECH SUPPORT INSTR	UCTED ME TO INSTALL FOIL TAPE ON ADC EXTERIOR PANEL SEAMS TO ELIMINATE PROBLEM.  THE ADC'S SHOULD BE REPAIRED OR MODIFIE	D INTERNALLY BY HONEYWELL TO ELIMINATE RF INTERFERENCE.				2	L	7	2 	4F				A9NM    					 
2005092000055	20050920	00055	SW  	2005	9	20	0509137          	1	20050906	G	7810	15070001	EXHAUST RISER   			LKHEED	PV1   	PV1         	5260104	SW  	PWA   	R2800 	R2800*      	52026	NE  					NR 5	SEPARATED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	234P					5336				NR 5 EXHAUST RISER HAD SEPARATED FROM ENGINE JUST BELOW THE FLANGE WELD. THE OWNER STATED THIS WAS THE SECOND TIME THIS 	HAS HAPPENED IN 40 HOURS. REPLACED ALL 3 RISERS AND COLLECTOR.					2	M	7	2 	4R	4	R	RT	EXPA2M2 	5E8				 
2005091500006	20050915	00006	GL  	2005	9	15	0509137A         	1	20050906	G	7810	15070001	EXHAUST RISER   			CIRRUS	SR    	SR22        	2130001	GL  										NR 5	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	234PG					0935				NR 5 EXHAUST RISER HAD SEPARATED FROM ENGINE JUST BELOW THE FLANGE WELD. THE OWNER STATED THIS WAS THE SECOND TIME THIS 	HAS HAPPENED IN 40 HOURS. REPLACED ALL 3 RISERS AND COLLECTOR.					1	L	7	1 	3O			NT	A00009CH					 
2005091900124	20050919	00124	EA  	2005	9	19	05252001         	2	20050909	G	7261	STD2217	SEAL            	LYC         		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ADAPTOR	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03		98   	98   							FIRST 100 HOUR INSPECTION AFTER OVERHAUL BY MFG (ENGINE SMOH 98.5). FOUND OIL LEAKING FROM DRY VACUUM PUMP DRIVE. THE EN	GINE VACUUM PUMP ADAPTOR DRIVE OIL SEAL WAS NOT SEATED FAR ENOUGH IN ADAPTOR HOUSING CAUSING LEAKAGE.  REPLACED ADAPTOR 	DRIVE OIL SEAL AND REINSTALLED ADAPTOR AND PUMP WITH NEW GASKETS.  OPERATIONAL AND LEAK CHECK SATISFACTORY.  THIS IS THE	 SECOND OVERHAULED ENGINE WITH SAME PROBLEM.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005112800175	20051128	00175	CE  	2005	11	28	053006           	1	20051102	G	8011	48037901C1	DRIVE ASSY      	ELECTROSYS  		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	97LP	1356 			B061774	17274398	RL1952439A			ON ENGINE START, STARTER DRIVE DID NOT DISENGAGE AND THE DRIVE GEARS SHEARED OFF, DAMAGING THE ENGINE RING GEAR. THE PIL	OT DID NOT DETECT THE FAILURE UNTIL LANDING AND TRYING TO RESTART THE ENGINE.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005112800173	20051128	00173	EA  	2005	11	28	05308            	2	20051104	G	8540	STD2217	SEAL            	LYC         		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03	9621V	168  				17264401	L4394027A			DURING 100 HOUR INSPECTION, FOUND ENGINE VACUUM PUMP DRIVE LEAKING OIL AND CONTAMINATING VACUUM PUMP.  REMOVED VACUUM PU	MP AND ENGINE VACUUM PUMP ADAPTOR DRIVE ASSEMBLY. FOUND SEAL P/N STD-1774 NOT FULLY INSTALLED IN DRIVE ASSY. REPLACED SE	AL AND VACUUM PUMP, OPERATIONAL AND LEAK CHECK SAT. ENGINE HAS 168.7 HOURS SINCE OVERHAUL BY MFG.  THIS IS THE SECOND OV	ERHAULED ENGINE WITH THIS DISCREPANCY.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005101900001	20051019	00001	CE  	2005	10	19	1005FAA001       	1	20051018	G	3340	202331	STROBE          			BEECH 	58    	58          	1152740	CE  										WING TIP	DAMAGED         	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	3694K					TH1177				WING TIP STROBE UNIT FLASH TUBE.  SOLDER JOINT BETWEEN PIN COMING OUT OF FLASH TUBE AND END CAP IS FAILING DUE TO SOLDER	 BEAD BEING GROUND FLAT AFTER ATTACHMENT DURING MANUFACTURE.  MULTIPLE FAILURES - CONDITION EXISTS ON NEW UNITS.					1	L	7	2 	3O				3A16    					 
2005042700151	20050427	00151	GL  	2005	4	27	1050326          	3	20050330	G	6111	F7666A2	BLADE           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	DEREH		387  					CH24122		BLADE 1, S/NR H20755R WAS FOUND WITH A 1 INCH CRACK, STARTING FROM LEADING EDGE, ABOUT 4 INCHES FROM BLADE TIP. THE BLAD	E WAS ALREADY REWORKED AT THIS AREA BECAUSE OF A EARLIER STONE NICK. PROPELLER WAS OVERHAULED IN MARCH 2003 AND HAS 387 	TSO UNTIL CRACK WAS FOUND.				1	L	7	1 	3O	3	O	RT	A51EU   	1E10	5	C	P920	 
2006010600097	20060106	00097	EA  	2006	1	6	1120057261       	2	20051120	G	7261	W2046	PUMP            			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AIR-SIPHON PUMP	MISMANUFACTURED 	D				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			WP	11	3843T	732  	732  			28R30162	L546051A	CH21499		PILOT NOTED RAPID LOSS OF ENGINE OIL PRESSURE.  INITIATED PRECAUTIONARY LANDING.  VISUAL INSPECTION OF MODIFIED P/N 6876	1 DRAINBACK LINE CUTOFF FOR AIR-SIPHON PUMP ( AIR-OIL SEPARATOR STC NR SA3687WE INSTALLATION FOUND SHARP, UNDRESSED AND 	UNBEADED IAW ORIGINAL INSTALLATION INSTRUCTIONS (CIRCA 1993 BY 337) CAUSED INSIDE OF MIL-6000-5/6 HOSE TO BE CUT CAUSING	 MASSIVE OIL LEAK.  PRESENT STC HOLDER, NOW SUPPLIES ONE-PIECE AIR-SIPHON PUMP P/N W-2046 TO REPLACE THIS ASSEMBLY.  REC	OMMEND REPLACING ORIGINAL CUTOFF DRAIN TUBES WITH NEW PART TO PREVENT OIL LOSS.		1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
2005080900069	20050809	00069	CE  	2005	8	9	123197A          	1	20050804	G	2133	66001983	OUTFLOW VALVE   			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					TAILCONE	FAILED          	B				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CE	07	518JG					219				DURING CRUISE, AIRCRAFT LOST PRESSURIZATION.  COCKPIT INDICATIONS ALERTED CREW AS DESIGNED. AIRCRAFT PRESSURIZATION AUTO	MATICALLY DEFAULTED TO EMERGENCY MODE.					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
2005080900058	20050809	00058	CE  	2005	8	9	123197B          	1	20050804	G	2133	261950010	OUTFLOW VALVE   			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					TAILCONE	FAILED          	B				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CE	07	518JG		59   			219				DURING CRUISE, AIRCRAFT LOSS PRESSURIZATION.  COCKPIT INDICATIONS ALERTED CREW AS DESIGNED.  AIRCRAFT PRESSURIZATION AUT	OMATICALLY DEFAULTED TO EMERGENCY MODE.					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
2005070600081	20050706	00081	NM  	2005	7	6	138              	1	20050701	G	5753		SKIN            			BOEING	737   	737522      	138449F	NM  	GE    	CFM56 	CFM56*      	13802	NE  					RT WING TE FLAP	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA					26739				RT WING OB FORE FLAP GOUGED ON OB END.  S/O 269008, OPS NR 24931.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005060700019	20050607	00019	EU  	2005	6	7	14038052105      	1	20050521	G	3212	6040102	FLOAT           			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					MLG	ACTIVATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	316PD					14038				DURING MAINT, TECH ATTEMPTED TO INSTALL SAFETY PIN IN RESERVOIR ASSY, FLOATS DEPLOYED. IT WAS LATER DISCOVERED THAT ELEC	 ACT USED TO DEPLOY FLOATS HAD BEEN PARTIALLY DEPLOYED.  CHECK OF SYS REVEALED THAT ACT ONLY ENERGIZES WHILE DEPLOYMENT 	BUTTON IS DEPRESSED. THIS ALLOWS FOR PARTIAL DEPLOYMENT OF ELEC ACTUATOR WHICH WILL INTERFERE WITH INSTALL OF SAFETY PIN	, CAUSING A DANGEROUS SITUATION FOR PERSONNEL IN VICINITY OF FLOATS.  SUPPLEMENT DOES NOT STATE THAT PILOT MUST CONTINUE	 TO DEPRESS DEPLOYMENT BUTTON IN ORDER FOR FLOATS TO DEPLOY, WHICH COULD CAUSE FAILURE TO DEPLOY IN AN EMERG.  FMS, ICA'	S, AND INSTALLATION INSTRUCTIONS ALL HAVE NOTES TO REMOVE SAFETY PIN BEFORE FLIGHT, NO REQ FOR RE-INSTALLING SAFETY PIN.	1	G	7	2 	3U	3	T		H7EU    	E2NE				 
2005071200062	20050712	00062	NM  	2005	7	12	142              	1	20050701	G	5230		SKIN            			BOEING	737   	737522      	138449F	NM  										CARGO DOOR	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA					26739				AFT CARGO DOOR REQUIRES RESKIN.						2	L	7	2 	4F			RT	A16WE   					 
2005041400112	20050414	00112	EA  	2005	4	14	1622304          	2	20050128	G	8520	AELSTD2213	BOLT            	LYC         							LYC   	O360  	IO360A3B6   	41514	EA  					CRANKGEAR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23					V53790363		L2754551A			DURING ENGINE OVERHAUL, THE PMA CRANKGEAR BOLT P/N: AELSTD2213 MANUFACTURED BY ENGINE COMPONENTS INC FAILED BEFORE REACH	ING RECOMMENDED TORQUE VALUE.  THE AREA JUST BELOW THE GRIP AREA STRETCHED.										3	O			1E10				 
2005042700135	20050427	00135		2005	4	27	1838110          	1	20050325	G	5312	3541046119	BULKHEAD        																	FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	8696	4823 								FRAME FOUND CRACKED WHEN ASSIST STEP WAS REMOVED FOR REPAIR. THE FLOOR MUST BE REMOVED TO ACCESS THE ATTACHMENT NUTS. TH	E BULKHEAD HAD BEEN PREVIOUSLY REPAIRED (AIRCRAFT HAD BEEN INVOLVED IN A GEAR UP INCIDENT IN THE PAST) AND WAS CRACKED P	AST THE REPAIR DOUBLER. A NEW BULKHEAD WAS INSTALLED. A CLOSE INSPECTION OF THE STRUCTURE SHOULD BE PERFORMED WHEN THE S	TEP IS REPAIRED AS THIS MAY BE THE ONLY TIME THE UNDERLYING MEMBERS CAN BE SEEN.																 
2005042700306	20050427	00306	CE  	2005	4	27	18HP             	1	20050331	G	2840	S35944	CONTROL UNIT    			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUEL SENDING	DEFECTIVE       	B			JRUR	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	07	18HP	1300 	100  			18281071	L2823248A	011464		WHILE RUNNING UP AIRCRAFT AFTER MAINTENANCE, IT WAS NOTICED THAT THE FUEL QTY GAGES WERE JUMPING FROM FULL TO EMPTY AND 	THE LOW FUEL LIGHT WAS FLASHING.  BOTH TANKS WERE FULL AT THE TIME.  INSTALLED NEW SENDING UNITS IN BOTH WINGS AND IT SE	EMED TO REMEDY THE PROBLEM.				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2005021700141	20050217	00141	EA  	2005	2	17	200501306        	1	20050124	G	5340	612826	RACK            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										ADC MOUNT	CRACKED         	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	60TF					572563				DURING THE REMOVAL OF THE AIR DATA COMPUTER FOUND TRAY CRACKED AT EACH CORNER OF THE THUMBSCREW CUTOUT AT THE BEND RADII	.					1	H	7	1 	3R				A806    					 
2005041500073	20050415	00073	EA  	2005	4	15	20050209         	2	20050209	G	8500	70384	SHAFT           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					IDLER GEAR	BROKEN          	B			EVGR	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SO	33		1985 	1985 				L251648			AT ENGINE DISASSEMBLY FOR OVERHAUL AFTER RUNNING FULL LIFE (1985.4 HRS) GOVERNOR IDLER GEAR SHAFT WAS FOUND BROKEN INSID	E THE GEAR.  ENGINE RAN NORMALLY, NO OTHER DAMAGE NOTED.					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005050600085	20050506	00085	CE  	2005	5	6	20050413         	1	20050412	G	2731	12601491	ACTUATOR        			CESSNA	206   	U206G       	2073356	CE  										ZONE 300	MISMANUFACTURED 	B			EVGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33	67JA					U20605781				DURING ANNUAL INSP, ELEV TRIM TAB FREE PLAY FOUND TO EXCEED LIMITS.  EXCESSIVE PLAY LOCATED IN ACT ASSY.  NEW ACT INSTAL	LED.  WHILE PERFORMING RIGGING CHK, TAB MOVED TO ITS LIMITS  & A SECOND AMT OBSERVING CABLE MVMNT IN TAIL CONE.   MOVING	 TAB BACK TO NEUTRAL & JUST PRIOR TO REACHING IT, A BANG HEARD FOLLOWED BY TRIM CABLE GOING SLACK. ON INSP, FOUND PINS T	HAT HOLD SPROCKET TO ACT SHEARED.  INVEST FOUND SLEEVE SPROCKET MUSHROOMED.  HOLES WHERE PINS INSTALL APPEAR TO HAVE BEE	N GROUND OR CHISELED.  ACT RETURNED TO SUPPLIER.  DURING RECEIVING INSP OF 2ND NEW ACT, FOUND SPROCKET NOT MOUNTED SQUAR	ELY IN SLEEVE.    SECOND ACT RETURNED TO SUPPLIER. SERVICEABLE UNIT REMOVED FROM ANOTHER 206 & INSTALLED PLANE.	1	H	7	1 	3O				A4CE    					 
2005050600098	20050506	00098	CE  	2005	5	6	20050415         	1	20050412	G	5714	29503040130	FRAME           			HELIO 	H295  	H295        	4300802	CE  										WING BOX	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	62JA		5338 			1443				CARRY-THRU CRACKS,  REWORKED TO B-401-5 TO MEET REQUIREMENTS OF AD 82-16-08.  TOTAL TIME ON THE CARRY THRU IS UNKNOWN.  	WHILE PERFORMING A 100HR INSPECTION, CRACKS WERE FOUND RADIATING FROM CUT-OUT FOR UPPER WING ATTACH BOLTS ON BOTH SIDES 	OF CARRY-THRU.  2 LONGEST CRACKS APPROXIMATELY .25 INCH IN LENGTH & ARE VISIBLE ON BOTH INSIDE & OUTSIDE OF TUBE.  THERE	 IS A SECOND SMALLER CRACK AT EACH CUT-OUT.  2 LARGEST CRACKS ARE IN SAME PLACE IN EACH CUT OUT.  THEY ALIGN WITH A PART	 OF THE CENTERING TOOL USED TO TIGHTEN THE UPPER WING ATTACH BOLT.  IF IMPROPER TECHNIQUE USED WITH THIS TOOL IT COULD P	OSSIBLY CAUSE THESE 2 CRACKS.  THERE ARE NO TOOL MARKS ON THE CARRY THRU THAT WOULD INDICATE THAT THIS IS THE CAUSE.	1	H	7	1 	3O				1A8     					 
2005051700194	20050517	00194	SO  	2005	5	17	200504262992R    	1	20050426	G	3210	6775300	BRACKET         			PIPER 	PA28  	PA28R200    	7102811	SO  										MLG	BROKEN          	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	2992R					28R35382				DURING PREFLIGHT WALK AROUND, THE PILOT NOTICED THE RT MLG DOWN-LOCK SPRING WAS HANGING DOWN BY ONE END.  FURTHER INVEST	IGATION REVEALED THE SPRING BRACKET HAD BROKEN AND THE MAIN GEAR DOWN-LOCK SPRING WAS NOT ATTACHED TO THE TRUNION.  THE 	BRACKET PLATE FAILED AT THE ATTACH POINT FOR THE DOWN LOCK SPRING.  COINCIDENTIALLY THE PILOT/OWNER HAD TAKEN EXTENSIVE 	PHOTOS OF COMPONENTS WITHIN THE LAST 30 DAYS IN PREPARATION FOR RESTORATION ACTIVITIES AND THE FAILING PART APPEARS TO B	E COMPLETELY INTACT.  PART PROVIDED NO INDICATIONS OF FAILURE.		1	L	7	1 	3O				2A13    					 
2005052400114	20050524	00114	SO  	2005	5	24	20050503         	2	20050503	G	8550		OIL FILTER      			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	B			EVGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33		50   								DURING RECENT INSPECTIONS, SEVERAL OIL FILTER ELEMENTS WERE FOUND PULLED AWAY FROM METAL RETAINING STRIP WHICH CLAMPS TH	E ENDS OF FILTER PAPER.  ONE FILTER ELEMENT ALSO HAD A SMALL HOLE PENETRATING FILTER PAPER EACH SIDE OF METAL STRIP.  SO	METIMES METAL STRIP WAS BENT.  THIS CONDITION ALLOWS A SMALL AMOUNT OF OIL TO BYPASS FILTER ELEMENT.  CONTACTED MFG, THE	Y CONFIRMED THAT SOME FILTERS WITH DATE CODE OF 04-07-2004 AND EARLIER WOULD FAIL IN THIS MANNER DUE TO METAL STRIP BEIN	G TOO LONG, INADEQUATE CLAMPING METHOD.  TOTAL OF FIVE FILTERS WITH EARLY DATE CODES WERE FOUND DEFECTIVE, SEVEN WERE RE	MOVED FROM AC, FIVE FILTERS WERE RETURNED TO MFG UNUSED.  MFG REPLACED ALL OUR EARLY DATE CODE FILTERS WITH NEW ONES.	1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005052400109	20050524	00109	CE  	2005	5	24	20050504         	1	20050504	G	2730	12601491	ACTUATOR        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  					ZONE 300	DEFECTIVE       	B			EVGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33	67JA					U20605781				TRIM TAB ACTUATOR IS DEFECTIVE AS RECEIVED.  THIS IS A NEW PART.  THE CHAIN SPROCKET HAS A BENT TOOTH.  LOT NUMBER: 2Q04	.  THIS IS THE THIRD DEFECTIVE, NEW ACTUATOR WE HAVE RECEIVED IN A ROW.  AN (EXPERIENCED) ACTUATOR FROM A STORED AIRCRAF	T IS BEING USED TEMPORARILY TO KEEP THIS PLANE FLYING.  THE DEFECTIVE ACTUATOR IS BEING RETURNED TO THE SUPPLIER.				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005052400115	20050524	00115	CE  	2005	5	24	20050505         	1	20050504	G	5341		TUBE            			HELIO 	H295  	HT295       	4300803	CE  										FUSELAGE	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	5387G					1257				WHILE PERFORMING THE 1500 HOUR INSPECTION REQUIRED BY AD 82-16-08, A CRACK WAS FOUND ON THE RT VERTICAL TUBE OF THE CARR	Y THRU.  THE CRACK WAS LOCATED AT THE TOP WELD OF THE TUBE.  THE LENGTH OF THE CRACK IS ROUGHLY HALF THE CIRCUMFERENCE O	F THE TUBE ON THE FRONT SIDE.  THIS CARRY THRU HAS BEEN MODIFIED IAW STC SA1728CE AND BEARS SN B-537.  THIS AREA IS NOT 	REQUIRED TO BE INSPECTED BY THE AD NOTE.  HOWEVER, HAVE FOUND THAT IT IS NOT UNUSUAL TO FIND A CRACK AT EITHER END OF EI	THER THE VERTICAL OR DIAGONAL TUBES.		1	H	7	1 	3O				1A8     					 
2005070500006	20050705	00006	SO  	2005	7	5	20050605B        	1	20050701	G	2750	1763400	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ZONE 100	CUT             	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15			1100 			273645				IN PERFORMING AD 2003-09-13, FOUND TORQUE TUBE WORE/CUT BY LEFT RUDDER CABLE. 2 INCH LOG AND THRU TUBE WALL. TUBE HAS BE	EN INSTALLED SINCE 1996 1100 HRS AGO. 					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005070800001	20050708	00001	GL  	2005	7	8	20050615         	3	20050615	G	6110	A3495	LOCK PLATE      			CASA  	C212  	C212CC      	2410204	EU  	GARRTT	TPE331	TPE33110R   	0517	WP  	HARTZL	HCB4M	HCB4M       	GL  	PROPELLER	SEPARATED       	M				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SW	05	00168	3550 	506  			336		EAA1838		INSP MX RUN-UP, VIBRATION NR 2 PROP ASSY, VIBRATED A FEW SEC THEN DIMINISHED.  DISCOVERED 2 SAFETY WIRED BOLTS HEADS ON 	GROUND THAT SNAPPED OFF PROP ASSY.  SPINNER HAD PUNCTURE DAMAGE, MINOR DAMAGE TO 2 PROP BLADES.  SPINNER REMOVED, 2 LOCK	 WIRED BOLTS HAD SHEARED OFF FROM BLADE CLAMP & START LOCK PLATE ASSY.  FOD INSPEC DISCOVERED LOCK PLATE 75 YDS FROM ACF	T.  NR 2 ENG REPLACED DUE TO SOAP RECOMMENDATION.  NR 2 PROPELLER HAD BEEN R&R.  PROPELLER BALANCING TASK COMPLETED PRIO	R TO INCIDENT.  START LOCK PLATE WEAR AT START LOCK CONTACT POINT.  START LOCK PN 830 ROTATED PAST CONTACT SURFACE OF ST	ART LOCK PLATE (PN A-3495).  FORCE APPLIED TO START LOCK PLATE CAUSED 2 ATTACHING BOLTS (A-2016) TO SHEAR.	2	H	7	2 	4T	4	T		A43EU   	E4WE	6	C	P56GL	 
2005062300067	20050623	00067	NM  	2005	6	23	20050622A        	1	20050602	G	5330		SKIN            			BOEING	737   	737300      	1384610	NM  										FUSELAGE	DENTED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	387UA					24662				DENT IN THE LT FUSELAGE SKIN IN AREA OF S20L AT BS 465.						2	L	7	2 	4F			RT	A16WE   					 
2005092000050	20050920	00050	CE  	2005	9	20	20050908         	1	20050909	G	5340	B4015	TUBE            			HELIO 	H295  	H295        	4300802	CE  										ZONE 200	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	9185Z					1228				CARRY-THRU VERTICAL TUBE CRACKED ON CARRY-THRU ASSEMBLY.  THIS CARRY-THRU IS MODIFIED BY STC SA1590CE.  TIME IN SERVICE 	IS UNKNOWN.  ALSO NOTED IS THAT THE VERTICAL TUBE WALL THICKNESS WAS .065 INCH RATHER THAN .120 INCH. THE HEAVIER WALL T	HICKNESS OF .120 IS CALLED OUT ON THE DRAWING AND IT IS SURMISED THAT SOME EARLY SERIAL NUMBER CARRY-THRU'S HAD THE LIGH	TER WALL TUBE INSTALLED.  THIS AIRPLANE WAS TOSSED IN A TORNADO AND SUSTAINED DAMAGE TO THE RT MAIN GEAR ATTACHMENT, PRO	PELLER, AND RT WING.  INSPECTED THE CARRY-THRU FOR HIDDEN DAMAGE.  PLEASE NOTE, HAVE FOUND OTHER CARRY-THRU'S WITH CRACK	ED VERTICAL TUBES RESULTING FROM FATIGUE.	1	H	7	1 	3O				1A8     					 
2006010500010	20060105	00010	CE  	2006	1	5	20051129         	1	20051129	G	5711	295030401	TUBE            			HELIO 	H295  	H295        	4300802	CE  										WING SPAR	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	641LW					1265				WING SPAR CARRY THRU P/N 295-030-401 IS CRACKED ON LT VERTICAL TUBE, TOP, FRONT SIDE.						1	H	7	1 	3O				1A8     					 
2005062400049	20050624	00049	NM  	2005	6	24	20052400A        	1	20050603	G	5315		FLOORBEAM       			DOUG  	MD88  	MD88        	3023688	NM  										CABIN	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				CABIN FLOOR SUPPORT STRUCTURE FS 256.0 LBL 44 TO RBL 44 HAS CORROSION.						2	L	7	2 	4F			RT	A6WE    					 
2006012500005	20060125	00005	CE  	2006	1	25	2005AP012502     	1	20051213	G	2752	99105863RX	ROLL PIN        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					TE FLAPS	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	PK-MP	885  	507  			208B0989	PCEPC1004			BOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS IN-OPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT	 BREAKER TO OPEN.  DISASSEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006020900119	20060209	00119	NM  	2006	2	9	2005AP02001      	1	20051226	G	3220		SUPPORT FITTING 			BOEING	747   	747*        	       	NM  										NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33										NOSE WHEEL WELL AREA, LT AND RT TRUNNION SUPPORT FITTING UPPER PART, AFT OF AFT BOLT HOLE WITH CRACK.						2	L	7	4 	4F			RT	A20WE   					 
2006020900120	20060209	00120	NE  	2006	2	9	2005AP02002      	2	20051226	G	7250		GUIDE VANE      			BOEING	747   	747100      	1384825	NM  	RROYCE	RB211 	RB211*      	54555	NE  					NR 1 ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33										ENGINE NR 3 LP TURBINE STAGE 3, NOZZLE GUIDE VANE APPROX 6:10 O'CLOCK POSITION ROOT AREA WITH CRACK.						2	L	7	4 	4F	4	F	RT	A20WE   	A12EU				 
2006012500004	20060125	00004	CE  	2006	1	25	2005AP052501     	1	20051213	G	2752	99105863RX	ROLL PIN        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					FLAP ACTUATOR	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	PK-MP	885  	507  			208B0989	PCEPC1004			BOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS INOPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT 	BREAKER TO OPEN.  DISASSEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005031500223	20050315	00223	SW  	2005	3	15	2005F00043       	1	20050217	G	8011	23032027	STARTER         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	INOPERATIVE     	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	70Q					3160	CAE840517			SHUT DOWN THE HELICOPTER AT ICY, WHEN ATTEMPTING TO RESTART THE IGNITER WAS FIRING BUT THE COMPRESSOR WAS NOT TURNING.  	WENT BACK THROUGH THE CHECKLIST, ON THE SECOND ATTEMPT THE SAME THING HAPPENED, WITH MAINTENANCE PRESENT ON THE THIRD AT	TEMPT THE COMPERSSOR WAS TURNING AND THE FUEL LIT OFF BUT PRIOR TO REACHING FLIGHT IDEL 30-40 PERCENT THE FLAME WENT OUT	.  MAINTENANCE REMOVED AND REPLACED THE STARTER GENERATOR, INSPECTED THE COMPRESSOR FOR FOD, INSPECTED FUEL NOZZLE, AIR 	LINES AND THE FUEL.  GROUND RUN CHECK COMPLIED WITH AND STARTED THREE TIMES WITH THE PILOT RESTARTING THE LAST START.  N	O OTHER DEFECTS FOUND AND STARTING TIME IS 25-35 SECONDS.  (M)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005031500276	20050315	00276	NE  	2005	3	15	2005F00045       	2	20050211	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					RIGHT	MALFUNCTIONED   	G				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	87550					UE205	114436			FLT - FLL/EYW - DURING FLIGHT, DETECTED SMOKE IN THE COCKPIT AND CABIN.  RIGHT ENGINE LOW PRESSURE ANNUNCIATOR ILLUMINAT	ED.  REMOVED AND REPLACED RIGHT ENGINE.  OPERATIONAL CHECK NORMAL.  (M)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005031500366	20050315	00366	EU  	2005	3	15	2005F00053       	1	20050211	G	3234		BELLCRANK       			BRAERO	DH125 	BAE125800A  	1500285	EU  										MLG HANDLE	OBSTRUCTED      	G				A				UNSCHED LANDING         				C	J		F.O.D.                    	WARNING INDICATION        		LD	LANDING        	1			EA	25	1776H					258091				DURING APPROACH, MLG SELECTOR HANDLE WOULD NOT GO TO DOWN POSITION & ENGAGE DETENT.  MLG HANDLE BINDING APPROX 1 INCH FR	OM BOTTOM DETENT.  CYCLED MLG BUT HANDLE WOULD NOT ENGAGE DOWN DETENT.  3 GREEN DOWN & LOCKED LIGHTS & 3 RED MLG LIGHTS 	ILLUMINATED.  MAIN AUX MLG LIGHTS GREEN & NLG MECH IND PIN INDICATING THE NLG DOWN & LOCKED.  ELECTED TO DIVERT TO PERFO	RM A TOWER FLYBY & VISUALLY CONFIRM MLG DOWN.  LANDED WITHOUT INCIDENT.  DID NOT DECLARE AN EMERGENCY.  UPON INVESTIGATI	ON, FOUND AN OBJECT THAT RESEMBLED A INK PEN CAP LODGED BETWEEN FLOORBOARD & MLG HANDLE BELLCRANK IMPEEDING TRAVEL.  OBS	TRUCTION REMOVED &  MLG SELECTOR CONTROL ADJUST PERFORMED IAW 800A MM.  FOUND TO BE OK.  RETURNED TO SERVICE.  (M)	2	L	7	2 	4F			RT	A3EU    					 
2005062700102	20050627	00102	CE  	2005	6	27	2005F00087       	1	20050527	G	8011	EB75A	DRIVE ASSY      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					STARTER	DESTROYED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	98344	124  			E103656	17276279	L926339A			THE DRIVE GEAR ON THE BENDIX DRIVE SHUTTERED.  THIS ALSO CURVED SEVER DAMAGE TO THE TEETH ON THE RING GEAR RENDERING THE	 RING GEAR UNSEVERICEABLE.  WE HAD 2 PREVIOUS PROBLEMS WITH THE BENDIX ON NEW STARTERS THESE.  RELATED TO THE DRIVE NOT 	ENGAUGING OR DISENGAGING PROPERLY.  THIS IS A MUCH MORE SEVERE PROBLEM AND IS PROBABLY RELATED TO A MATERIAL DEFECT IN T	HE PART.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005092000047	20050920	00047	SO  	2005	9	20	2005F00100       	1	20050914	G	3246	C20211170	WHEEL           			LKHEED	P38   	P38L        	5260206	SO  	ALLSN 	V1710 	V1710*      	 	GL  					MLG	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	718	2602 	82   			8187				WHEEL ASSEMBLY RETURNED FOR LOOSE TIE BOLTS, OF 18 TIE BOLTS INSTALLED 2 ARE MISSING 11 ARE LOOSE.  MFG HAS NOW ISSUED S	L F6137-32-843 IN HOPES THIS WILL RESOLVE.					2	M	7	2 	4V	4	V		LTC10   	EXPE4V				 
2005092000048	20050920	00048	SO  	2005	9	20	2005F00101       	1	20050914	G	3246	C20211170	WHEEL           			LKHEED	P38   	P38L        	5260206	SO  	ALLSN 	V1710 	V1710*      	 	GL  						LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	25	718	2602 	82   			8187				WHEEL ASSEMBLY RETURNED FOR LOOSE TIE BOLTS, OF 18 TIE BOLTS INSTALLED 2 ARE MISSING 11 ARE LOOSE.  MFG HAS NOW ISSUED S	L F6137-32-843 IN HOPES THIS WILL RESOLVE.					2	M	7	2 	4V	4	V		LTC10   	EXPE4V				 
2005102800066	20051028	00066		2005	10	28	2005F00108       	1	20050929	G	6120	A30672	BUSHING         	HARTZL      	HCB5MP3C    											HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER HUB	SEPARATED       	B			CQ4R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	03			7    		FWA2607			EVA2607		REPAIRED DAMAGED BUSHING BY REPLACING WITH NEW PART.																6	C	P44GL	 
2005122000148	20051220	00148	CE  	2005	12	20	2005F00110       	1	20051123	G	3610		PNEUMATIC SYSTEM			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  						CONTAMINATED    	D				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			EA	05	401BC					TH1668				DURING PROLINGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER ENTER INTO THE PNEUMATIC SYST	EM.  INSP OF PNEUMATIC SYS REVEALED LARGE AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY 	INSP REVEALED SEVERAL OUNCES OF WATER REMAINING IN SYS.  SYS WAS PRUGED OF ALL WATER AND DRIED.  AC WAS RETURNED TO SERV	ICE.  FLIGHT CREW REPORTED AC AGAIN WAS OPERATED FOR AN EXTENDED PERIOD OF TIME IN HEAVY PRECIPITATION.  THIS AC HAS HIS	TORY OF PREMATURE FLIGHT COMMAND INDICATOR FAILURES CAUSED BY RUST AND WATER CONTAMINATION.  RELOCATE THE PNEUMATIC SYS 	FILTER TO AN AREA BEHIND THE ENGINE BAFFLE ASSY WHERE IT WILL NOT BE SUBJECT TO IMPACT WATER.  (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005031000172	20050310	00172	NM  	2005	3	10	2005FA0000007    	1	20050114	G	5312	6517662	BULKHEAD        			BOEING	727   	7272M7      	138407S	NM  										FUSELAGE	GOUGED          	A			DHLA	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	750DH					21951				RIGHT STA 950 BULKHEAD GOUGED.						2	L	7	3 	4F				A3WE    					 
2005012000047	20050120	00047	CE  	2005	1	20	2005FA0000009    	1	20050104	G	2435	2307900001	STARTER GEN     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					LEFT ENGINE	FAILED          	E				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			GL	25	88FA		790  			BE74				LEFT ENGINE FAILED ROTATE DURING START SEQUENCE INITIATION.  MAINTENANCE DETERMINED BRUSHES BURNT, APPROXIMATELY 50 PERC	ENT LENGTH/LIFE REMAINING.  STARTER/GENERATOR WAS REPLACE, ALONG WITH DC VOLTAGE REGULATOR.  NR 1 INVERTER HAD FAILED CO	UPLE DAYS PRIOR, NO INDICATION ONE FAILURE CONTRIBUTED TO OTHER.				1	L	7	2 	4T	4	T		A14CE   	E2WE				 
2005020100022	20050201	00022	SW  	2005	2	1	2005FA0000014    	1	20050121	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					WING	CRACKED         	B			N3SS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	2974E					7AC6560				DURING PRE-PURCHASE, COMPLIED WITH INSPECTION.  BOTH SPARS IN BOTH WINGS WERE FOUND TO HAVE LOOSE AND MISSING NAILS THAT	 HOLD RIBS OT THE SPARS.  SEVERAL LONGITUDINAL CRACKS WERE FOUND.  RECOMMENDATION TO OWNER WAS TO REPLACE ALL WOOD SPARS	, WITH STC METAL SPARS.				1	H	7	1 	3O	3	O		A759    	E205				 
2005020100019	20050201	00019	CE  	2005	2	1	2005FA0000024    	1	20050117	G	1430		BOLT            			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					WASTEGATE VALVE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	732YK		287  			21061879	294273R			3 OF THE 4 BOLTS THAT ATTACH THE METAL PLATE THAT THE ACTUATOR IS MOUNTED ON TO THE WASTEGATE BODY WERE MISSING.  FOURTH	 BOLT WAS BACKED OUT ABOUT HALF WAY.  ALL THREE BOLTS FOUND LOOSE IN ENGINE COMPARTMENT.  WASTEGATE ASSEMBLY ONLY 287 FR	OM OVERHAUL BY MAIN TURBO.THESE BOLTS ARE NOT EASILY OBSERVABLE AND REQUIRE A MIRROR TO SEE.  RECOMMEND INSPECTION AT EA	CH OIL CHANGE AND TIGHTEN AS NEEDED.			1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005020100020	20050201	00020	CE  	2005	2	1	2005FA0000025    	1	20050110	G	2121	1013841763	BLOWER          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	ARCED           	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	07	773TP	1613 	1613 			BB1722				PILOT REPORTED AN ELECTRICAL SMELL DURING FLIGHT AND THEN THE FORWARD VENTILATION BLOWER WENT INOPERATIVE.  FOUND THE BR	USHES WORN OUT AND ARCING ON THE ARMATURE. REPLACED WITH OVERHAULED UNIT AND FUNCTIONAL CHECK OK.					1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2005020100023	20050201	00023	CE  	2005	2	1	2005FA0000026    	1	20050113	G	2700		CONTROL PANEL   			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300*       	17022	SO  					PITCH CONTROL	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	8803B	3663 	2    			36503				AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING A LANDING ACCIDENT.  PILOT WAS UNABLE TO FLARE AIRPLANE. DURING A POST ACCIDEN	T INSPECTION BY FAA INSPECTORS, IT WAS DISCOVERED THAT THE AIRPLANE'S CONTROL TEE PULLEYS FOR THE AILERON SYSTEM WOULD G	ET (HUNG UP) ON THE RADIO TRAY ASSEMBLY, WHEN THE CONTROL WHEEL TUBE WOULD REACH HALF TRAVEL. THE CONTROL TEE PIVOT AND 	THE LEFT INSTRUMENT PANEL CONTROL TUBE BALL SOCKET, EXHIBITED WEAR, AND THE CONTROL TEE COULD BE MOVED LATERALLY ALONG A	 PORTION OF THE CONTROL TEE PIVOT BOLT. ADDITIONALLY, THE RADIO-MOUNTING TRAY DID NOT INCLUDE THE INSTALLATION OF A VERT	ICAL SUPPORT TO HELP ASSURE PROPER CLEARANCE BETWEEN THE TRAY AND THE CONTROL TEE ASSEMBLY.	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005031100095	20050311	00095	EU  	2005	3	11	2005FA0000027    	1	20050119	G	6320	704A33652036	CAGE            	SNIAS       		SNIAS 	350   	AS350B2     	8680813	EU  										BEARING	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		2367 	2367 		M1899	1883				BEVEL REDUCTION MODULE P/N 350A32-0300-05 S/N M1899 WAS REMOVED AT TSO: 2367.5 FOR METAL CONTAMINATION.  UPON TEARDOWN A	NALYSIS IT WAS DISCOVERED THAT THE BEARING CAGE FOR BEARING P/N 704A33-652-036 TSN: 2367.5, WAS BROKEN.  SUBSEQUENT DETE	RIORATION OF BEARING WAS CAUSE FOR METAL CONTAMINATION.				1	G	7	1 	3U				H9EU    					 
2005020100062	20050201	00062	GL  	2005	2	1	2005FA0000028    	1	20050121	G	5740	2057000103	BEARING         			DIAMON	DA20  	DA20C1      	2990001	GL  										LT WING	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	932AF	840  				C0198				(A) BEARING IN LT WING FOUND LOOSE WITH .0625 INCH PLAY UP AND DOWN. NO PLAY FORE AND AFT. PASTE FROM BEARING ATTACH FOU	ND LOOSE IN WING BAY. REMOVED BEARING AND FOUND NO DAMAGE TO END RIB. FOUND WITH WING OFF DURING 1000 HOUR INSPECTION.					1	L	7	1 	3O			NT	TA4CH   					 
2005020100130	20050201	00130	GL  	2005	2	1	2005FA0000029    	1	20050107	G	3242		ROD             			AMTR  	COZY  	COZY        	05613R8	GL  	LYC   	O320  	O320*       	41508	EA  					RT BRAKE CYL ACT	BENT            	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	01	154MD		25   			154MD				RT BRAKE CYLINDER ACTUATING ROD, LOCATED BEHIND RT RUDDER PEDAL, WAS SLIGHTLY BENT AFT. THIS CONDITION CAUSED INSUFFICIE	NT BRAKE CYLINDER PISTON TRAVEL AND MAKING THE RT BRAKE INOPERATIVE.					1	M	7	1 	3O	3	O	NT	EXPA1M71	E274				 
2005041400104	20050414	00104	NE  	2005	4	14	2005FA0000030    	2	20050119	G	7210	704A33652036	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					REDUCTION G/B	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	1883H	2367 	2367 			1883				BEVEL REDUCTION MODULE (PN 350A32-0300-05, SN M1899) WAS REMOVED AT TSO: 2367.5 FOR METAL CONTAMINATION.  UPON TEARDOWN 	ANALYSIS IT WAS DISCOVERED THAT THE BEARING CAGE FOR BEARING (P/N 704A33-652-036) TSN: 2367.5, WAS BROKEN.  SUBSEQUENT D	ETERIORATION OF BEARING WAS CAUSE FOR METAL CONTAMINATION.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005031100040	20050311	00040	SW  	2005	3	11	2005FA0000065    	1	20050103	G	5610		WINDSHIELD      			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					COCKPIT	CRACKED         	B			OZ5R	B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	3114G					AC583				MRR-M05-01, NR 1 WINDSHIELD CRACKED IN FLIGHT JUST AS CREW STARTED DESCENT.  CREW DEPRESSURIZED AC, DESCENDED TO AN APPR	OPRIATE ALTITUDE FOR NON-PRESSURIZED FLIGHT, AND DIVERTED TO AN AIRPORT WITH VMC CONDITIONS.  CREW LANDED WITH NO FURTHE	R INCIDENT.  OAT WAS APPROXIMATELY -40 AND WINDSHIELD HEAT WAS ON LOW.  INNER GLASS PANE CRACKED, UNDER INVESTIGATION WI	TH THE OVERHAUL/REPAIR FACILITY.  INNER PANE OF THE HEATED WINDSHIELD CRACKED EXTENSIVELY.  REPLACED WINDSHIELD, OPS CHE	CK AND LEAK CHECK GOOD. (K)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005033000080	20050330	00080	SW  	2005	3	30	2005FA0000066    	1	20050105	G	5270		WARNING SYSTEM  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					PAX DOOR	MALFUNCTIONED   	B			OZ5R	B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	60NE					AC760B				CREW OBSERVED THE CABIN DOOR LIGHT CAME ON DURING CRUISE.  CREW VERIFIED HANDLE WAS IN THE FULL CLOSED POSITION.  THE LI	GHT WENT OUT DURING DESCENT, AND WAS ON FOR APPROXIMATELY 10 MINUTES.  THE LIGHT STAYED OUT FOR THE REMAINDER OF DESCENT	 AND LANDING.  ONE OF THE FOLLOWING:  DOOR CLOSING PROCEDURES, DOOR HARD TO CLOSE, DOOR CLICKCLACK RIGGING/ LUBRICATION,	 OR INDICATORS SWITCH RIGGING.  NO FAULT FOUND, COULD NOT GET SYSTEM TO FAIL.  COULD NOT DUPLICATE MALFUNCTION, CLEANED 	ALL CABIN DOOR SWITCHES AND OPS CHECKED DOOR SYSTEM.  OPS CHECKED GOOD. (K)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005033000081	20050330	00081	SW  	2005	3	30	2005FA0000067    	1	20050106	G	5270		WARNING SYSTEM  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					PAX DOOR	MALFUNCTIONED   	B			OZ5R	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			NM	05	60NE					AC760B				MRR-M05-3, CREW OBSERVED THE CABIN DOOR LIGHT CAME ON DURING CRUISE.  CREW VERIFIED HANDLE WAS IN THE FULL CLOSED POSITI	ON.  THE LIGHT WENT OUT WHEN CABIN DIFFERENTIAL PRESSURE WAS LOWERED.  THE LIGHT STAYED OUT FOR THE REMAINDER OF DESCENT	 AND LANDING.  CREW ALSO NOTED THE DOOR SEAL LEAKS.  ONE OF THE FOLLOWING: DOOR CLOSING PROCEDURES, DOOR HARD TO CLOSE, 	DOOR CLICKCLACK RIGGING/ LUBRICATION, OR INDICATOR SWITCH RIGGING.  NO FAULT FOUND, COULD NOT GET SYSTEM TO FAIL.  COULD	 NOT DUPLICATE MALFUNCTION, INITALLY DEFERRED IAW MEL. (K)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005021500129	20050215	00129	EA  	2005	2	15	2005FA0000071    	2	20050128	G	8500		CRANKCASE       			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540B1C5   	41532	EA  					ENGINE	CRACKED         	B			G6NR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	324RR					1386139				CRANKCASE, LARGE CRACK UNDER NR 2 CYLINDER, RESULTING IN MASIVE OIL LOSS. (K)						1	H	7	2 	3O	3	O		6A1     	1E4				 
2005031100097	20050311	00097	NM  	2005	3	11	2005FA0000074    	1	20050110	G	3240	511531	HOUSING         			BOEING	737   	737*        	       	NM  										VALVE	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4590					HOUSING HAS 4 MOUNTING LUG HOLES.  ONE HOLE WAS FOUND CRACKED DURING NDT INSPECTION.  FATIGUE, STEEL HOUSING. MECHANIC R	P1, JOB NR 192167 (K)					2	L	7	2 	4F			RT	A16WE   					 
2005031100099	20050311	00099	NM  	2005	3	11	2005FA0000075    	1	20050110	G	2710	654484511	MANIFOLD        			BOEING	737   	737*        	       	NM  										AILERON	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										MANIFOLD CRACKED AT FILTER BOWL MOUNTING PORT.  FATIGUE AND OVERPRESSURIZATION.  MECHANIC NH2, JOB NR 191795. (K)						2	L	7	2 	4F			RT	A16WE   					 
2005031100100	20050311	00100	NM  	2005	3	11	2005FA0000076    	1	20050110	G	3230	S6026	CYLINDER        			BOEING	727   	727*        	       	NM  										VALVE	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3085					CRACKED THROUGH THREADS IN CYL 1 PORT.  FATIGUE, STRONGER BODY. MECHANIC JW2, JOB NR 191413. (K)						2	L	7	3 	4F			RT	A3WE    					 
2005031100101	20050311	00101	NM  	2005	3	11	2005FA0000077    	1	20050110	G	3230	S6026	CYLINDER        			BOEING	727   	727*        	       	NM  										VALVE	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2370					CRACKED THROUGH THREADS IN CYL 1 PORT.  FATIGUE, STRONGER BODY.  MECHANIC JW2, JOB NR 191407.  (K)						2	L	7	3 	4F			RT	A3WE    					 
2005033000119	20050330	00119	NM  	2005	3	30	2005FA0000078    	1	20050110	G	3230	S6026	HOUSING         			BOEING	727   	727*        	       	NM  										VALVE	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2497					CRACKED THROUGH THREADS IN CYL 1 PORT.  FATIGUE, STRONGER BODY. MECHANIC JW2, JOB NR 191405. (K)						2	L	7	3 	4F			RT	A3WE    					 
2005030100045	20050301	00045	CE  	2005	3	1	2005FA0000079    	1	20050127	G	5522	12346204	ELEVATOR        			CESSNA	210   	T210F       	2073422	CE  	CONT  	O520  	IO520*      	17032	SO  					RT & LT	MISREPAIRED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	6772R					T2100172				DURING AN ANNUAL INSP, FOUND LT ELEVATOR TORQUE TUBE LOOSE, AFTER REPAIR WHILE CHECKING CONTROL SURFACE BALANCE, SURFACE	 WAS FOUND TO BE BADLY OUT OF BALANCE AT  +21 IN LBS.  REMOVED T/E AND FOUND IT TO HAVE BEEN REPLACED WITH A FIELD FABRI	CATED PART BY PERSONS UNKNOWN.  FOUND THE MATERIALS USED TO BE .040 SHEET ALUMINUM, THE FACTORY T/E WAS MADE OUT OF .016	 AND WAS FOAM FILLED, REPLACED THE T/E WITH FACTORY PARTS, REPLACED T/E AND TRIM TAB ON OTHER ELEVATOR DUE TO SAME CONDI	TION, REBALANCED CONTROL SURFACES AND FOUND TO BE WITHIN RANGE OF 0 TO +5.4 IN LBS.  (WP07200509576) (K)		1	H	7	1 	3O	3	O		3A21    	E5CE				 
2005032800086	20050328	00086	EA  	2005	3	28	2005FA0000093    	2	20050216	G	7314	461740	PUMP            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	FUEL SYSTEM	INCORRECT       	B			OG5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	357ND	1564 				2842185	L1977239A	A59575		NOTICED A STICKY SUBSTANCE (OTHER THAN FUEL) LEAKING OUT OF MACHINED HOLE ON SIDE OF FUEL PUMP.  THIS MACHINED HOLE COME	S WITH THE HOLE SEALED FROM THE MFG. (K)					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2005022400076	20050224	00076	SO  	2005	2	24	2005FA0000108    	2	20050130	G	8520	SA631991	SHAFT           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					ENGINE	OUT OF ROUND    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	123AP					347770015	303972			UPON INSTALLING A SHAFT INTO A ROCKER WITH INADEQUATE TOLERANCE LIMITS, NOTED BINDING IN THREE CLOCK POSITIONS. WITH PRU	SSION BLUE, FOUND THAT THE SHAFT IS FORMED IN AN ELIPTICAL OR, MODIFIED TRI-ANGULAR SHAPE WITH REDUCED WEAR SURFACE AREA	 DUE TO INCONSISTANT DIAMETER OF THE SHAFT.  ALL 24 NEW SHAFTS DISPLAYED THE SAME MACHINING RESULTS.  THE HIGHEST PRESSU	RE POINT WAS AT THE NARROWEST CONTACT POINT.  GALLING OF THESE SHAFTS APPEARS TO BE CONSISTANT WITH REDUCED WEAR SURFACE	 AND CROWNING OF THE SHAFT.  WHILE OTHER FACTORS MAY BE ATTRIBUTED TO THE CAUSE OF THE PREMATURE SHAFT FAILURE, THE REDU	CTION IN SURFACE AREA IS CONSISTANT WITH ACCELERATED DECOMPOSITION OF BEARING SURFACE.  AIRWEST AIRCRAFT ENGINES SUPPLIE	1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005030200054	20050302	00054	NM  	2005	3	2	2005FA0000110    	1	20050124	G	3240	511531	HOUSING         			BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3770					MOUNTING LUG CRACKED ON INNER DIAMETER, FATIGUE, STEEL HOUSING. (K)						2	L	7	2 	4F			RT	A16WE   					 
2005033000144	20050330	00144	EU  	2005	3	30	2005FA0000112    	1	20050118	G	7430	103572101	IGNITION SWITCH 			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					COCKPIT	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	865AF					85005				PILOT REPORTED STARTER WOULD NOT ENGAGE, AFTER FURTHER INVESTIGATION FOUND IGNITION SWITCH WAS BAD.  NO PROBABLE CAUSE O	R RECOMMENDATIONS AT THIS TIME. (K)					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2005033000150	20050330	00150	NM  	2005	3	30	2005FA0000116    	1	20050112	G	5330		SKIN            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	MISDRILLED      	B			FDER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	465FE					21289				DRILL START NOTED AT L-BAND NR 1 ANTENNA FWD RT MOUNT HOLE.  BS410, RBL 1. (IN SKIN) FOUND WHILE PERFORMING INSPECTION O	F ANTENNA IAW WORKCARD NR 34X4505. (K)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005033000151	20050330	00151	SO  	2005	3	30	2005FA0000117    	2	20050111	G	8530	AEC631397ST2	CYLINDER HEAD   			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	SEPARATED       	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	362SB	409  				E1848				ECI CYLINDER HEAD AND BARRLE SEPERATION.  (K)						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005033000152	20050330	00152	WP  	2005	3	30	2005FA0000118    	2	20050121	G	7210	035A470105	LINE            			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					GEARBOX	CRACKED         	B			W6NR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	25	772DA					772SA				NR 8 SCAVENGE OIL LINE FROM ENGINE GEARBOX TO VERNATHERM CRACKED INSIDE THE B-NUT SLEEVE AT GEARBOX.  THIS LED TO SIGNIF	ICANT LOSS OF OIL AND A PRECAUTIONARY SHUTDOWN IN FLIGHT.  AC RETURNED DEPARTURE, UNEVENTFUL LANDING, REPLACED OIL LINE.	 (K)				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
2005033000154	20050330	00154	EA  	2005	3	30	2005FA0000119    	2	20050110	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MAGNETO DRIVE	FAILED          	B			YYBR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			GL	03	22PG	617  				277305203	L1767848A			CUSTOMER COMPLAINED OF A VIBRATION ON RT ENGINE.  INSPECTION REVEALED CAGE FAILURE OF THE RT MAGNETO DRIVE GEAR BEARING 	(PN 67542).  CAUSE OF CAGE FAILURE NOT KNOWN.  CANNOT RECOMMEND ACTION TO PREVENT REOCCURRENCE. (K)					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005033000156	20050330	00156	CE  	2005	3	30	2005FA0000120    	1	20050110	G	3213	05412024	BUSHING         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	MLG STRUT	WORN            	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	9453Z	495  				17280193	L2722351A	RD071		DURING NORMAL ANNUAL INSPECTION RT MAIN GEAR WAS JACKED AND CHECKED FOR ATTACHMENT FREEPLAY.  EXCESSIVE FREEPLAY WAS NOT	ED AND UPON FURTHER VISUAL INSPECTION, IT WAS DETERMINED THAT RUBBER EXTRUDING OUT FROM THE GAP BETWEEN THE RT MAIN GEAR	 LEG AND PN 05912024, GEAR LEG BUSHING WAS RESPONSIBLE FOR THE INCREASED FREEPLAY.  REPLACEMENT OF THE PIN - 05412024 RT	 MAIN GEAR LEG BUSHING WITH NEW ELIMINATED ALL RT GEAR LEG FREEPLAY. (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2005033000162	20050330	00162	GL  	2005	3	30	2005FA0000122    	2	20050131	G	7200		ENGINE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						MAKING METAL    	B			GS1R	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			EA	03	41PH					1544				PILOT REPORTED HEARING A GRINDING NOISE FROM THE ENGINE WHICH WAS FOLLOWED BY AN ENGINE CHIP LIGHT INDICATION.  A POWER 	ON PRECAUTIONARY LANDING WAS MADE.  THE ENGINE WAS REMOVED AND REPLACD WITH A LOANER ENGINE.  THE DISCREPANT ENGINE AS A	N ASSEMBLY WAS SENT TO REPAIR STA. FOR FURTHER EVALUATION. (K)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005033000164	20050330	00164	WP  	2005	3	30	2005FA0000124    	2	20050124	G	7210	3101320	HOUSING         			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					SCAV PUMP	FAILED          	B			W6NR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	25	772DA					772SA				IN FLIGHT, PILOT NOTICED FLUCTUATING OIL PRESSURE AND TORQUE.  PRECAUTIONARY LANDING MADE, FOLLOWING TROUBLESHOOTING ENG	INE WAS DISASSEMBLIED GEARBOX SCAVENGE OIL PUMP WAS CRACKED.  APPROXIMATELY 7 HOURS PRIOR, THE NR 8 STAINLESS OIL SCAV. 	LINE CRACKED.  APPROXIMATELY 7 HOURS PRIOR THE NR 8 STAINLESS OIL SCAV LINE CRACKED.  IT IS BELIEVED OIL PRESSURE CYCLIN	G FROM LINE FAILURE FRACTURED SCAV PUMP HSG REPLACED PUMP.  (K)			1	H	7	2 	3T	4	F	RT	A10SW   	E6WE				 
2005040400104	20050404	00104	CE  	2005	4	4	2005FA0000132    	1	20050128	G	2720	071362856	SUPPORT         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					RUDDER PEDAL	DAMAGED         	B			PHKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	7579T					R18200042				WHILE COMPLETING GROUND RUN, PRIOR TO 100 HOUR INSPECTION, NOTICED RUDDER PEDALS DID NOT FEEL RIGHT.  FURTHER INVESTIGAT	ION REVEALED THAT THE NUT-PLATES HAD RIPPED THROUGH THE RUDDER PEDAL SUPPORT PIECES.   (K)					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2005031100001	20050311	00001	SW  	2005	3	11	2005FA0000134    	1	20050216	G	6230	407010104109	CONE            	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R MAST	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	17SP				53444	53444				REPLACED MAIN ROTOR MAST CONE PN 407-010-104-109 FOR HUB SHIFT/MAST NUT TORQUE STABILIZATION PROBLEM.  ORDERED NEW CONE 	P/N 407-010-104-109 FROM MFG. NEW PART WAS RECEIVED WITH A WEAR GROOVE IN CENTER OF CONE FACE (APPEARED USED).   REORDER	ED ANOTHER NEW CONE AND INSTALLED.  INSTALLED MAST NUT AND STABILIZED TORQUE.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005032800043	20050328	00043	CE  	2005	3	28	2005FA0000141    	1	20050218	G	3610	99144022	PRECOOLER       			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					LT PYLON	BLOWN           	D				K				NONE                    				G	M		MULTIPLE FAILURE          	OVER TEMP                 		IN	INSP/MAINT     	1			SO	25	70KW	2200 				5250050				DURING A PREFLIGHT INSPECTION IT WAS NOTED THE PAINT ON THE LOWER SKIN OF THE LEFT PYLON WAS DISCOLORED AND BUBBLED UP. 	VISUAL INVESTIGATION REVEALED THE  PRECOOLER ASSEMBLY HAD FAILED, ALLOWING BLEED AIR INTO THE 6312209-1, DUCT ASSEMBLY, 	WHICH  CAUSED THE 6312209-1 DUCT ASSEMBLY TO FAIL, ALLOWING BLEED AIR INTO THE PYLON.  A CONDUCTIVITY CHECK OF THE COMPO	NENTS WHICH MAKE UP THE PYLON, PYLON SKINS AND FUSELAGE SKINS IN THE AREA OF THE PYLON SHOWED MANY OF THE COMPONENTS TEM	PERATURE TO HAVE CHANGED. THE FUSELAGE SKIN IN THE PYLON AND THE AREAS SURROUNDING THE PYLON WERE NOT AFFECTED BY THE HE	AT.	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2005032800048	20050328	00048	CE  	2005	3	28	2005FA0000142    	1	20050205	G	3211	20410141	SUPPORT         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					MLG ACTUATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2773V		70   			177RG0694				AFTER GEAR EXTENSION PILOT DID NOT GET DOWN AND LOCKED GREEN LIGHT. EMERGENCY PROCEDURES WERE COMPLETED WITH SAME RESULT	S.  GEAR APPEARED DOWN AND LOCKED BY OBSERVERS ON THE GROUND, DURING LOW APPROACH.  UPON TOUCH DOWN THE PILOT REPORTED A	 SAFE GEAR INDICATION.  MAINTENANCE INSPECTION REVEALED MAIN GEAR ACTUATOR SUPPORT BRACKETS (LT AND RT) WERE CRACKED.  A	LSO FOUND ACTUATOR THROUGH PIN TO BE FRACTURED ON RT SIDE. SPECIFIC CAUSE OF FAILURE UNKNOWN.  GEAR SYSTEM OPERATIONALLY	 CHECKED SATISFACTORY AFTER REPLACEMENT OF DAMAGED PARTS.  AIRCRAFT HAD RECEIVED 100 HOUR INSPECTION 70 HOURS PRIOR WITH	 NO ABNORMALITIES NOTED IN MAIN GEAR ACTUATOR SYSTEM.	1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005032800050	20050328	00050	SO  	2005	3	28	2005FA0000143    	1	20050126	G	3252	400910	BOLT            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					NLG CENTERING	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	249PM	3964 	80   			347770422				DURING RAMP INSPECTION, INSPECTOR NOTICED BOLT ATTACHING NOSE GEAR CENTERING DEVICE WAS INSTALLED INCORRECTLY, HEAD OF B	OLT AT TOP OF HARDWARE STACK.  AD 92-13-05 AND SB 893 REQUIRE BOLT TO BE INSTALLED WITH HEAD DOWN AND A CAUTIONARY PLACA	RD TO BE AFFIXED.  PLACARD WAS ABSENT TOO.  MAINTENANCE RECORD CONTAIN DESCRIPTION OF AD BEING ACCOMPLISHED IN 1993.  SU	BSEQUENT RECORD ENTRY IN 2003 DESCRIBES REPLACEMENT OF CENTERING DEVICE ROD END AND BOLT.  SUSPECT PLACARD WAS ABSENT TH	EN, TECHNICIAN NOT AWARE OF AD REQUIREMENTS AND INSTALLED BOLT IAW STANDARD PRACTICES, RATHER THAN AD.		1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005040400005	20050404	00005		2005	4	4	2005FA0000156    	2	20050228	G	7322	MA451048931	CARBURETOR      																	ENGINE	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										THROTTLE LEVER LOCKED UP AT ABOUT 20 PERCENT OPEN THROTTLE POSITION.  DISASSEMBLED AND INSPECTED.  FOUND AIR METERING JE	T AND PIN HAD SEPARATED.  JET WAS BACKED OUT FAR ENOUGH THAT PIN FELL OUT AND LOCKED-UP.  ALSO FOUND THAT RETENSION BALL	 FOR JET IS MISSING.  THERE IS ALSO AND DRAG ON METERING PIN THREADS WHICH ALLOWED IT TO BACK OUT.  (K)																	 
2005030200044	20050302	00044	SO  	2005	3	2	2005FA0000161    	1	20050301	G	2721	6666100	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					RUDDER TRIM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	7653F	4809 				287790205				RUDDER TRIM CONNECTOR FOUND BROKEN OFF DURING ANNUAL INSPECTION.						1	L	7	1 	3O	3	O		2A13    	E286				 
2005032800111	20050328	00111	CE  	2005	3	28	2005FA0000174    	1	20050214	G	5540	NAS682A3	NUT PLATE       	CESSNA      		CESSNA	150   	150D        	2071810	CE  	CONT  	O200  	O200*       	17020	SO  					RUDDER PIVOT	WORN            	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NM	07	901SW					15060734				UPPER RUDDER PIVOT BOLT BACKED OUT OF SELF-LOCKING NUTPLATE AT UPPER RUDDER PIVOT ATTACH AND PIVOT POINT WHILE IN FLIGHT	, RUDDER WAS RIPPED FROM THE LOWER BELLCRANK CONTROL AND DEPARTED AIRCRAFT.  AIRCRAFT LANDED WITHOUT INCIDENT.  RUDDER W	AS RECOVERED AND THE UPPER PIVOT BOLT WAS RETAINED IN THE UPPER RUDDER CAP.  THE BOLT COULD BE INSERTED IN THE NUTPLATE 	WITH LIGHT FINGER PRESSURE ONLY, AND REMOVED SAME WAY.  NUTPLATE WAS WORN AND LOST ITS LOCKING ABILITY.   AT INSTALLATIO	N OF A NEW FACTORY RUDDER ASSEMBLY, A DRILLED AN BOLT WAS USED TO INCLUDE A COTTER KEY BELOW THE NUTPLATE.  (NM072005036	94)(K)	1	H	7	1 	3O	3	O		3A19    	E252				 
2005040400027	20050404	00027	SW  	2005	4	4	2005FA0000176    	1	20050201	G	7921	654585	OIL COOLER      			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					ENGINE	CRACKED         	B			DY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	2138Z	602  				290158	679237			DURING ROUTINE OIL CHANGE, AN EXAMINATION OF THE OIL COOLER FLANGE AREA WHERE IT BOLTS ONTO THE ENGINE STUDS WAS FOUND T	O BE CRACKED.  THE CRACK WAS LOCATED BETWEEN THE STUDS MOUNTING AREA IN THE OIL COLLER SURFACE WELD.  THIS IS THE FOURTH	 INSTANCE OF AN OIL COOLER CRACK FOUND AT THE OIL COOLER BY THIS STA WITHIN THE LAST YEAR.  ALL PREVIOUS CRACKED COOLER 	HAD AT LEAST 500 HOURS TIME IN SERVICE.  CLOSE EXAMINATION OF THIS AREA IS RECOMMENDED AT EACH OIL CHANGE OR COWLING REM	OVAL.		1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2005040100079	20050401	00079	SO  	2005	4	1	2005FA0000177    	2	20050204	G	7414	4001	MAGNETO         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	704YL	394  				15078978	255492A48	K19171		FLANGE BROKEN ON RT SIDE FOR SUPPORT OF MAG.  FOUND ON ANNUAL INSP. 4001 MAG TT 394.  (K)						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2005040100080	20050401	00080	SO  	2005	4	1	2005FA0000178    	1	20050131	G	2140		COMBUSTION LINER			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					HEATER	CRACKED         	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	13AG				A980311	347770115				WHILE PERFORMING AD 04-21-05, THE HEATER FAILED THE PRESSURE DECAY TEST.  REMOVED UNIT AND FOUND CRACKS IN END OF COMBUS	TION LINER.  UNIT WAS REMOVED AND REPLACED WITH OVERHAULED UNIT.  UNIT INSTALLED MAY 1998, AND CONTAINED NEW STYLE CERAM	IC LINER.				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005040100081	20050401	00081	SO  	2005	4	1	2005FA0000179    	1	20050210	G	2140	EM608	BLOWER          			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					DEFOGGER	SEIZED          	B			K5SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92884	249  				4636107				VENT DEFOG BLOWER TRIPPING VENT DEFOG BLOWER CIRCUIT BREAKER.  BLOWER ASSY SEIZED.  REMOVED AND REPLACED BLOWER ASSY. (K	)					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2005040100085	20050401	00085	EU  	2005	4	1	2005FA0000180    	1	20050210	G	3500	9571222212	VALVE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					OXYGEN OUTLET	LEAKING         	B			K5SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	956PC					323	PCEPR0186			PIOTS OXYGEN OUTLET VALVE LEAKS WHEN MASK PLUGGED IN.  SUSPECT INTERNAL SEAL FAILURE. (K)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2005040100090	20050401	00090	CE  	2005	4	1	2005FA0000181    	1	20050206	G	2435		BEARING         	LUCAS       		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A11      	52043	NE  					STARTER GEN	FAILED          	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	893MC				98141	FL216				SHAFT BEARING AT THE COOLING FAN END OF THE S/G CAME APART.  THIS CAUSE THIS END OF THE COMMUTATOR TO MOVE SIDE TO SIDE 	AND THE COOLING FUN RUBBED INTO THE HOUSING.  (K)					2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2005040400029	20050404	00029	EA  	2005	4	4	2005FA0000182    	1	20050222	G	5210	600380091	TRACK           	BOMBDR      		CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	43R	2750 				5334	872121			TRACK/CHANNELS, 600-380091, ARE U CHANNELS THAT FACE EACH OTHER ALLOWING STRUT, 600-38008-17 AND CAMS, TO MOVE UP AND DO	WN INSIDE OF THESE TRACKS.  THE TRACKS ARE MANUFACTURED WITH SMALLER SIDES AND POOR ENGAGEMENT/ LOOSE FIT OF THE STRUT/C	AMS ALLOW THE CAMS TO LIFT OUT OF THE CHANNELS AND JAMMING THE STRUT.  THE END RESULT IS ROD, 600-38003-3 BREAKING RESUL	TING IN THE PASSENGER DOOR GROUND SUPPORT PAD NOT EXTENDING AND THE DOOR TOUCHING THE GROUND.  HAVE BROUGHT THIS TO THE 	ATTENTION OF MFG 8 YEARS AGO WHEN I HAD THE SAME PROBLEM WITH OUT CL-601, SN 5134.  THEY FAILED TO CORRECT THE PROBLEM A	ND IT IS NOW AN ISSUE ON OUR CL-604.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005040100086	20050401	00086	NM  	2005	4	1	2005FA0000183    	1	20050131	G	3510	417N3011414B	PSU             			BOEING	737   	73783N      	13844HI	NM  										CABIN	CONTAMINATED    	W			LLMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	312TZ					32579				CONTAMINATION ON INSIDE OF PSU.  WHILE CARRING OUT ROUTINE MAINTENANCE ON PAX PSUS, CONTAMINATION WAS FOUND AT ROWS 8,13	, 18, AND 23 LT AND RT.  CONTAMINATION APPEARS AS SOME FORM OF CARBON OR GRAPHITE.  IT IS LOCATED DIRECTLY BELOW WHERE T	HE OVERHEAD BINS JOIN AND HAS SETTLED ON THE OXYGEN MASK COVERS INSIDE THE PSUS, AND AT ROW 8 IT IS LOCATED ON THE GASPE	R COVER.  INSPECTIO ALSO CARRIED OUT ON SISTER AC.  SAME DEFECT FOUND.  CONTAMINATION REMOVED AS DETAILED ON NRC 185261.	 (K)		2	L	7	2 	4F			RT	A16WE   					 
2005040400009	20050404	00009	CE  	2005	4	4	2005FA0000184    	1	20050214	G	2800	10810001259	ADAPTER         			BEECH 	77    	77          	1153007	CE  	LYC   	O235  	O235*       	41505	EA  					FUEL TANK	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	1805V					WA270				DOUBLER INSTALLEN IN FUEL TANK HAS NO ACCESS AND MFG CAN NOT TELL US HOW TO STOP FUEL LEAK.						1	L	7	1 	3O	3	O		A30CE   	E223				 
2005033000025	20050330	00025	CE  	2005	3	30	2005FA0000187    	1	20050215	G	3260	622EN186	SQUAT SWITCH    			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					LT MLG	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	901CJ	1252 				5250278				SQUAT SWITCH FOUND WITH ROLLER MISSING.  DURING TROUBLESHOOTING FOR THRUST REVERSER (T) DEPLOYMENT SHORTLY AFTER TAKEOFF	.  AIRCRAFT RETURNED TO FIELD AND MADE AN UNEVENTFUL LANDING.  REPLACED SQUAT SWITCH WITH NEW OF SAME PN.  NO OTHER DEFE	CTS NOTED ON SWITCH.  RECOMMEND THAT PRE-FLIGHT PROCEDURES INCLUDE CHECK FOR PRESENCE AND CONDITION OF SQUAT SWITCH ROLL	ERS.  (K)			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2005031100005	20050311	00005	NE  	2005	3	11	2005FA0000188    	2	20050203	G	7314	9234A8	PUMP            	GE          		LEAR  	24    	24D         	5170311	CE  	GE    	CJ610 	CJ6108      	30006	NE  					RT ENG FUEL	FLAKING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	101VS				GAT6864	218	211035A			THE INTERNAL COATING IN THE GEAR SECTION OF THE FUEL PUMP STARTED FLAKING OFF AND GOT INTO THE HIGH PRESSURE FUEL LINE T	HAT GOES TO THE JET PUMPS IN  THE RT WING.  THE MATERIAL CLOGGED UP THE ORIFICES IN THE JET PUMPS, NOT ALLOWING FUEL TO 	BE TRANSFERRED FROM THE TIP TANK TO THE WING.  NOTE: THE FUEL PUMP HAD ABOUT 4400 HOURS SINCE O/H.  THE DATE WAS 1994 AT	 O/H IAW SUBMITTER.  (EA23200505548) (K)			2	L	7	2 	4J	4	J		A10CE   	1E16				 
2005031400062	20050314	00062	CE  	2005	3	14	2005FA0000190    	1	20050223	G	6100	D4951	FORK            	HARTZL      		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					HJ1597			HJ1597		NDT SHOWS CRACKED IN 2 PLACES ON FORK.  (K)  (REF: 12235)						2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE	 
2005042500179	20050425	00179		2005	4	25	2005FA0000191    	4	20050223	G	6122	D20880	FLYWEIGHT       			CESSNA	182   	182         	2072702	CE  	LYC   	O540  	IO540V4A5   	41532	EA  					GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	195RB				990056					FLYWEIGHT BASE CRACKED ALSO ASSOCIATED PART, C20886 SPRING HEAD AND B20882-1, SPRING DRIVE ALSO CRACKED.  (K)  (REF: 221	24)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005030800281	20050308	00281	NE  	2005	3	8	2005FA0000192    	2	20050207	G	8520	375202	CRANKSHAFT      			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340*      	52016	NE  					ENGINE	FRACTURED       	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15							ZP102313			THE CRANKSHAFT REAR HALF FRACTURED IN TWO, JUST AFT OF THE MASTER ROD BEARING JOURNAL.  (K)						1	Q	7	1 	3R	3	R		1A16    	5E2				 
2005042500181	20050425	00181	CE  	2005	4	25	2005FA0000193    	1	20050204	G	3020	10191011435	RETAINER        			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6*        	52043	EA  					INERTIAL VANE	MISINSTALLED    	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	5XM					FL115				DURING INSP OF ENG INERTIAL VANE CONTROL SYS, IT WAS FOUND THAT RETAINER PLATE, PN 101-910114-35 THAT LOCKS INTO A GROOV	E ON SHAFT, PN 101910114129, FOR AFT INTERIAL VANE, WAS NOT INSTALLED CORRECTLY.  WHEN RETAINER PLATE IS CORRECTLY INSTA	LLED IN GROOVE ON SHAFT ASSY, IT WOULD SECURELY HOLD SHAFT ASSY IN ITS MOUNTING PLATES.  RETAINER PLATE IS LOCATED ON VA	NE SHAFT END OPPOSITE ACT.  THIS ALLOWS SHAFT ASSY TO MOVE BACK AND FORTH WHEN VANE IS OPERATED THROUGH ITS RANGE.  FOUN	D THAT THIS EXCESS SIDE MOVEMENT WOULD ALSO ALLOW BOLT THAT SECURES SHAFT ASSY TO ACTUATOR COULD CATCH ON  SURROUNDING S	UPPORT.  CONDITION WAS FOUND ON BOTH ENGINES OF THIS AC.  SHAFT ASSYS FOR FWD VANE WERE FOUND CORRECTLY INSTALLED. (K)	2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2005033000048	20050330	00048	CE  	2005	3	30	2005FA0000194    	1	20050211	G	2510	551900922	SEAT BACK       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	1250V					5500439				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  	ALSO, PREVIOUS INAPPROPRIATE REPAIR.  CHAIR WAS REPORTED IAW STC ST01042WI, STRUCTURAL SEAT REPAIR. (CE05200503843)  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005033000044	20050330	00044	SO  	2005	3	30	2005FA0000195    	2	20050207	G	7314	64621238AZR	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL SYSTEM	INOPERATIVE     	B			VJ3R	O				OTHER                   				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	NR	NOT REPORTED   	1			WP	07	1556A	178  				CE1318	830106R			ENGINE KEPT DYING AT IDLE.  MAINTENANCE TECH TROUBLESHOT SYSTEM AND FOUND THAT THE ENGINE DRIVEN FUEL PUMP PRESSURE WILL	 NOT STABILIZE.  VARIES BETWEEN 7.5 TO 10 PSI.  REMOVED AND REPLACED ENGINE DRIVEN FUEL PUMP OPS CHECK NORMAL.  PROBABLE	 CAUSE INTERNAL FAILURE IN FUEL PUMP.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005031400089	20050314	00089	CE  	2005	3	14	2005FA0000196    	1	20050210	G	3211	MS203922C45	CLEVIS PIN      			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RT MAIN GEAR	BROKEN          	B			AIHR	O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	11	6571S					LW171				PILOT REPORTED SOUND (LIKE A TIRE BLOWING OUT) UPON LANDING.  THERE WAS SEVERE VIBRATION ON ROLLOUT.  THERE WAS NO VIBRA	TION ON TAXI BACK TO HANGAR.  UPON EXITING AIRCRAFT, PILOT NOTICED RT MAIN GEAR MISALIGNED.  FURTHER INSP BY MAINTENANCE	, FOUND RETAINING CLEVIS PIN FOR UPPER TORQUE LINK SHEARED, CAUSING PIN TO DRIFT OB, CAUSING THE UPPER TORQUE LINK TO BR	EAK AND SEPARATE FROM THE TRUNNION.  RECOMMEND REPLACING CLEVIS PINS WITH NEW EVERY TIEM AD 2002-01-10 IS PERFORMED. (GL	11200507567) (K)		1	L	7	2 	3T	4	T		3A20    	E4EA				 
2005040400084	20050404	00084	CE  	2005	4	4	2005FA0000197    	1	20050211	G	7603	7184510	THROTTLE CABLE  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RT FWD	DAMAGED         	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	11	858MK	1337 				141				AFTER TAKEOFF, THROTTLE WOULD NOT COME BACK.  THROTTLE HAD TO BE FORCEABLY PULLED BACK OUT OF TAKEOFF SETTING.  CABLE WA	S FOUND BAD. (GL11200507568)  (K)					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005032800109	20050328	00109	CE  	2005	3	28	2005FA0000198    	1	20050131	G	5753	052340051	SPAR            			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					RT WING FLAP TRA	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4992R	12474				17256346	29876D9DR			WHILE REPLACING THE FLAP TRACK ASSY, A CRACK APPROX 2 INCHES IN LENGTH AND RUNNING THROUGH THE LOWER RIVET HOLES WAS FOU	ND UNDER THE IB FLAP TRACK.  PROBABLE CAUSE IS FATIGUE.  RECOMMEND THESE AC WITH MORE THAT 8,000 HOURS TT BE INSPECTED B	Y BORESCOPE OR OTHER ACCEPTABLE MEANS, AT THE REAR WING SPAR AROUND THE FLAP TRACK ATTACH AREA. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005040400039	20050404	00039	SO  	2005	4	4	2005FA0000199    	1	20050118	G	2710	62701099	CONTROL CABLE   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					AILERON	FRAYED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2114J	6218 				287916224				FOUND BOTH FORWARD AILERON CONTROL CABLES FRAYED.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2005040400079	20050404	00079		2005	4	4	2005FA0000200    	1	20050120	G	2622	V651554	FIRE BOTTLE     																	CABIN	DISCHARGED      	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09										PORTABLE FIRE EXT NOZZLE WAS FOUND TO BE LOOSE AND BOTTLE COMPLETELY DISCHARGED.  REMOVED NOZZLE FROM BOTTLE AND FOUND N	OZZLE AND BOTTLE THREADS CORRODED.  ALSO, NOZZLE TO BOTTLE O-RING SEAL DETERIORATED.  POSSIBLE CAUSE OF DEFECT COULD BE 	IMPROPER TORQUE VALUE USED DURING BOTTLE ASSEMBLY.																	 
2005040100112	20050401	00112		2005	4	1	2005FA0000202    	4	20050127	G	6122	54696	SPOOL           	HARTZL      		PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	GOVERNOR	MISINSTALLED    	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	55696				3797	28R7335274				GOVERNOR SENT FOR REPAIR DUE TO RPM CONTROL ISSUES AND A HISTORY OF LEAKING.  DURING DISASSEMBLY, THE PILOT SPOOL SHAFT 	THREADS WERE FOUND DAMAGED.  IT WAS DISCOVERED THAT AT THE PREVIOUS ASSY OF THIS PART, A FINE THREADED B3808-4 NUT WAS U	SED IN PLACE OF THE REQUIRED B3808 (COARSE THREAD) NUT.  THE B3808-4 WAS FORCED ONTO THE PILOT SPOOL DISTORTING AND CROS	STHREADED IT.  UNIT WAS REPORTED TO HAVE BEEN OVERHAULED 3/1/94 AND HAD APPROX 200 HOURS TSO.			1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
2005042500193	20050425	00193	SW  	2005	4	25	2005FA0000203    	1	20050120	G	7820	630112501	MUFFLER         			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	91678					290129				VERY SIMILAR TO THE CRACKS REFERENCED IN AD NR 95-12-16 BUT ITS OUTSIDE OF THE SN RANGE LISTED. (K)						1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2005040400057	20050404	00057		2005	4	4	2005FA0000204    	1	20050104	G	2621	344	EXTINGUISHER    																	CABIN	INOPERATIVE     	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09										FIRE EXTINGUISHER WENT THROUGH A WEIGHT AND PRESSURE CHECK AND PASSED BOTH CHECKS.  UPON REINSTALATION OF THE EXTINGUISH	ER INTO THE AC THE TECH NOTICED THE HALON TO BE DEPLETED, ALL SAFETY SEALS WERE IN TACT AND THE EXTINGUISHER WAS NOT CON	TACTING ANY OTHER OBJECTIVES WHILE SITTING STATIC IN THE CABINET, THIS IS THE 3RD EXTINGUISHER OF THIS MODEL TO DO THIS.	  ALSO NOTICED THE CYLINDER HEAD TO BE LOOSE.  (K)																 
2005040100087	20050401	00087	CE  	2005	4	1	2005FA0000213    	1	20050121	G	5330	97430000604	SKIN            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FUSELAGE	MISMANUFACTURED 	B			P6UR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	905GP	6043 				BB789				UPON REMOVAL OF AC TOP SKIN, FOUND 4 RIVETS ON STRINGER NR 4R JUST FWD OF THE EMERGENCY EXIT HATCH TO HAVE NO EDGE DISTA	NCE.  ABOVE THIS AREA AT FS165.25 AND STRINGER NR 2R THERE WAS FOUND ONE FASTENER HOLE WITH SHORT EDGE DISTANCE.  FWD OF	 THIS AREA AT FS 148.90 AND STRINGER NR 3R, FOUND A DOUBLE DRILLED HOLE WITH NO EDGE DISTANCE BETWEEN THEM.  PROB CAUSE:	 DEFECT IN MANUFACTURING.  RESOLUTION: MFG ISSUED ENGINEERING REPAIR FOR THE AFFECTED DISCREPANCY.  DOCUMENT NR FR-KA-01	494, REV 2 DATED 01-13-05.		1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005032800051	20050328	00051	SO  	2005	3	28	2005FA0000215    	1	20050104	G	5340	51023306	PLATE           			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360A1D     	41514	EA  					SEATBELTS	MISINSTALLED    	B			IG8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	123VU	5944 				10059				WHILE REPLACING REAR PX SEATBELTS, IT WAS DISCOVERED THAT REINFORCEMENT PLATE HAD BEEN INSTALLED ON FWD SIDE OF AFT SEAT	 BLKHD UNDER SEATBELT ATTACH BRACKET.  (-6) PLATE SHOULD HAVE BEEN INSTALLED ON AFT SIDE OF BLKHD IAW AGAG DWG 5102299. 	 MS203641032 (THIN SHEER NUT) WAS USED TO SECURE AN3-5A RETAINING BOLTS.  NUTS SHOULD HAVE BEEN INSTALLED IAW DWG.  RESU	LTS IN REDUCED SEATBELT ATTACHMENT STRENGTH COMPARED WITH DESIGN CONFIGURATION.  AC APPEARED TO HAVE ORIGINAL SEATBELTS 	INSTALLED, THIS IMPROPER INSTALLATION WAS ACCOMPLISHED DURING ASSY.  REAR SEAT SEATBELT OB ATTACH BRACKETS INSP FOR PROP	ER INSTALLATION OF PLATE AND PROPER ATTACH HARDWARE PRIOR TO CARRYING REAR SEAT PASSENGERS. (EA07200502731)(K)	1	L	7	1 	3O	3	O	NT	1L71    	E286				 
2005040100093	20050401	00093	SO  	2005	4	1	2005FA0000216    	2	20050209	G	8520		CONNECTING ROD  			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	5130A					21063280	522211			NR 2 CONNECTING ROD FAILED BREAKING CRANKCASE, KNOCKING LT MAG FROM MOUNT.  ROD SHOWED FRICTION WELDING TO CRANK PRIOR T	O FAIURE.  COUNTERWEIGHT DAMAGED BY IMPACT WITH ROD.  APPEARS ENG CONTINUED TO OPERATE BRIEFLY FOLLOWING ROD SEIZURE.  P	ILOT ACCOMPLISHED SUCCESSFUL LANDING IN FIELD, NO APPARENT DAMAGE TO AIRFRAME.  ENG HAS HISTORY OF CYL BEING REMOVED FOR	 TOP O/H WITH 4 BEING CHANGED TWICE.  HAD BEEN EXPERIENCING PERSISTENT OVERBOOSTING, PROBLEM HAD BEEN ADDRESSED AT DIFFE	RENT TIMES.  TURBO CONTROLLER HAD BEEN REPLACED AND WASTEGATE HAD BEEN REMOVED, SERVICED AND REINSTALLED. AFTER COMPLETI	ON, APPEARED OVERBOOST PROBLEM MITIGATED.  ENGINE FAILED.  (GL11200507447)	1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005040100088	20050401	00088	CE  	2005	4	1	2005FA0000217    	1	20050113	G	2710		CONTROL CABLE   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					AILERONS	FAILED          	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	146XL	1780 				187				PRIMARY FLIGHT CONTROL CABLES ARE FAILING INSP, DUE TO WEAR ON CONTROL CABLE FAIRLEADS IN FUSELAGE AND EMPANNAGE.  DETAI	LED INSP IS PERFORMED AT 4800 HRS.  FOLLOWING CABLES FAILE AT 1780.3 HRS.  FUSELAGE AILERON CABLES, RUDDER CABLES, ELEVA	TOR CABLES.  CAUSE IS DUE TO CABLE FAIRLEADS BEING MADE FROM TOO HARD OF MATERIAL CAUSING CONTROL CABLES TO WEAR INSTEAD	 OF FAIRLEADS.  RECOMM: TO PERFORM SB, (FUSELAGE REPLACEMENT OF THE CABIN FLIGHT CONTROL FAIRLEADS) THIS SB INSTALLS DIF	FERENT PN FAIRLEAD IN THE AC, WHICH IS MADE OF A SOFTER MATERIAL. (CE09200502297) (K)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005040400045	20050404	00045	CE  	2005	4	4	2005FA0000222    	1	20050110	G	2720		CONTROL CABLE   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RUDDER	WORN            	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	886CA	1183 				154				AILERON, ELEVATOR, AND RUDDER SYSTEMS PRIMARY CONTROL CABLES ARE DUE INSPECTION AT 600 HOURS IAW MM, AS A PORTION OF PHA	SE B REQUIREMENTS.  ALIERON, ELEVATOR AND RUDDER SYSTEMS PRIMARY CONTROL CABLES ARE DUE REMOVAL AND DETAILED INSPECTION 	AT 4,800 HOURS IAW MM.  PRIMARY FLIGHT CONTROL CABLES ARE NOT LISTED MM (REPLACEMENT SCHEDULE).  INSTALLED NEW RUDDER CO	NTROL CABLES, (PN7627202004-001, 7627202003-001).  WORK PERFORMED AFTER INSPECTION IAW PHASE B REQUIREMENTS. (K) (CE0920	0502303)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005031400074	20050314	00074	SW  	2005	3	14	2005FA0000224    	1	20050215	G	6700	NAS66039D	BOLT            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					DUAL CONTROL	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	45RX	1064 				53412	CAE847447			FOUND THAT MAX POS OF THROT (POWER LEVER ANGLE) COULD NOT BE OBTAINED USING NML ADJ  PROC.  FOUND COPILOT THROTTLE LINKA	GE WAS FOULING ON COLLECT ELBOW (PN 206-001-203-101).  LINKAGE IS ATTACHED TO COL THROTTLE LEVER WITH (NAS6603-9D) BOLT 	INSTALLED W/HEAD FACING FWD.  DUE TO INSTALL OF AIR COMM BLEED AIR HTR KIT (PN 407H-200M12 STC:SR00221DE) BOLT HAD BEEN 	TURNED AROUND W/HEAD FACING AFT.  INSTR CALLS TO REPLACE FACTORY BOLT (NAS6603-9D) W/SHORTER BOLT (NAS6603-8D), NOT INST	ALLED ON THIS AC.  FOUND THAT BOLT (NAS6603-8D) ALSO FOULS IF WASHER/COTTER PIN ARE INSTALLED INCORRECTLY.  ONLY FLIGHT 	FADEC FAILURE WOULD PILOT MOVE THROT PAST (FLIGHT) DETENT POS, USING MAX THROT RANGE.  AC TO BE CHECKED FOR COMPLIANCE.	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005040400062	20050404	00062	EU  	2005	4	4	2005FA0000226    	1	20050214	G	3320	189411	POWER SUPPLY    			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN LIGHT	FAILED          	B			G46R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			WP	13	253SJ					107				CREW HAD POWER ON AIRCRAFT AND NOTICED AN ELECTRICAL BURNING SMELL COMING FROM THE CABIN.  AFTER INVESTIGATING THEY FOUN	D THE CABIN INDIRECT LIGHTING CIRCUIT BREAKER POPPED.  THE MAINTENANCE FACILITY TROUBLESHOT THE PROBLEM TO A POWER SUPPL	Y THAT HAD BURNED UP.  RECOMMEND INVESTIGATION INTO THIS PN POWER SUPPLIES TO SEE IF THEY SHOULD BE TOTALLY REMOVED FROM	 SERVICE.  MFG RECOMMENDED SB F50-335 FOR REPLACING  POWER SUPPLIES WITH IMPROVED POWER SUPPLY THAT INCORPORATES A PROTE	CTION CIRCUIT.  THESE LIGHTING SYS WERE INSTALLED UNDER MFG MODIFICATION F50 M2065+M2674.  THIS AIRCRAFT WILL HAVE SB -3	35 INSTALLED AS SOON AS PART CAN BE PROCURED.	2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2005031100068	20050311	00068	EA  	2005	3	11	2005FA0000247    	1	20050208	G	6700	269A731613	TRIM SYSTEM     			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360*     	41514	EA  					CYCLIC STICK	FAILED          	B			NKVR	K				NONE                    				O			OTHER                     			DE	DESCENT        	1			NM	09	2096W	152  				S1865				DURING DESCENT TO LANDING THE CYCLIC STICK JAMMED SO AS TO NOT ALLOW ANY LATERAL MOVEMENT TO THE RT BEYOND NEUTRAL POSIT	ION.  THIS WAS CAUSED BY THE SPRING TUBE COMING OUT OF THE TRIM HOUSING AND LOCKING THE TRIM ARM AT A .7500 EXTENDED POS	ITION.  THE SPRING TUBE CAME OUT OF THE TRIM HOUSING DUE TO A FAILURE OF THE EPOXY THAT HOLDS IT IN.  THIS TRIM ACTUATOR	 HAS A DIFFERENT COLOR EPOXY THEN OLDER TRIM ACTUATORS.  (WHITE-NEW/ GREEN-OLD) (K).			1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2005040400055	20050404	00055	NM  	2005	4	4	2005FA0000248    	1	20050219	G	3030		HEATER          			GULSTM	200   	200         	4500308	NM  										LT PITOT HEAD	INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	363GA	689  			207782	063				LT PITOT HEAT INOPERATIVE.  FOUND PITOT PROBE HEATING ELEMENT ARCED.  REMOVED AND REPLACED LT PITOT PROBE. (K)						2	L	7	2 	4F			RT	A53NM   					 
2005042600011	20050426	00011	SW  	2005	4	26	2005FA0000249    	1	20050216	G	7110	430061801101	COWLING         			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					LT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	430LF	848  				49096				LT HAND TRANSMISSION COWLING FRETTING AGAINST ADJACENT COWLING.  DZUS FASTENER DOES NOT HOLD COWLING WITH ENOUGH TENSION	, CAUSING FRETTING.  MOVEMENT CAUSED CRACK AT BOTTOM DZUS RAIL. (K)					1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2005040100034	20050401	00034	CE  	2005	4	1	2005FA0000250    	1	20050224	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  										COCKPIT	CRACKED         	D			ACOR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	05	415RB	1854 				BB1513				PILOT REPORTED WINDSHIELD SHATTERED WHILE CRUISING AT FLIGHT LEVEL 24,000 FT.  INNER PANE SHATTERED. (K)						1	L	7	2 	4T				A24CE   					 
2005040400103	20050404	00103	CE  	2005	4	4	2005FA0000251    	1	20050210	G	5610	9910491	WINDSHIELD      			CESSNA	421   	421C        	2076016	CE  										COCKPIT	FAILED          	B			BNZR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			GL	19	316WC	2004 				421C1047				PITOT HEATED GLASS WINDSHIELD FAILED DURING TAKEOFF ROLL.  CAUSE UNKNOWN.  WINDSHIELD WAS INSTALLED ABOUT 8 YEARS AND 20	04.5 HOURS AGO AND FAILED FOR NO APPARENT REASON. (GL19200502495) (K)					1	L	7	2 	3O				A7CE    					 
2005031100002	20050311	00002	EA  	2005	3	11	2005FA0000252    	2	20050131	G	8550	LW18110	IMPELLER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					OIL PUMP	DESTROYED       	D				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			SO	35	100M	1657 				17265590				FLYING AT 1700 FT WITH PWR SETTING OF 2400 RPM, VIBRATION OCCURED.  SCANNED GAGES, ALL NORMAL.  PULLED CARB HEAT AND VIB	RATION DISAPPEARED.  SCANNED GAGES AGAIN, NOTICED OIL PRESS WAS ZERO.  PWR STARTED TO BLEED OFF, RPM`S DROPPED TO 2200, 	DID NOT RESPOND TO THROTTLE ADVANCE.  DESCENDED TO LAND, ENGINE SEIZED.  LANDED AC IN A FIELD W/O DAMAGE TO AC, PERSONNE	L INJURY.  INSP REVEALED OIL SUPPLY AT 7 QTS.  NO METAL IN OIL AND PROP WAS FREE TO ROTATE.  PILOT INDICATED OIL TEMP WA	S NORMAL DURING INCIDENT.  UPON DISASSEMBLY OF ENG, FOUND A LARGE AMOUNT OF NON-FERROUS PARTICLES. OIL SCREEN FOUND TO B	E CLEAN.  DISSASSEMBLED OIL  PUMP, FOUND IMPELLER PARTIALLY DESTROYED AND CRACK STARTING AT CENTER BORE. (SO35200508187)	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005031500109	20050315	00109	SO  	2005	3	15	2005FA0000255    	2	20050121	G	7310	628437	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					RT ENGINE	SHEARED         	B			FFKR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CR	CRUISE         	1			SO	05	21407	91   	91   			347870435	807968R			AIRCRAFT WAS IN CRUISE FLIGHT WHEN IT EXPERIENCED AN IMMEDIATE ENGINE FAILURE ON THE RIGHT ENGINE, PILOT COULD NOT RESTA	RT ENGINE.  AFTER LANDING MAINTENANCE REPORTED A FITTING ON THE FUEL PUMP FOR THE VAPOR RETURN LINE HAD SHEARED.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005032800066	20050328	00066	CE  	2005	3	28	2005FA0000257    	1	20050217	G	5610	10138402519	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	BROKEN          	B			R1JR	B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			SO	15	345WK	2025 				BB1580				PILOT REPORTS THAT AT CRUISE ALTITUDE 24,000 FT, EVERYTHING NORMAL THE PILOTS WINDSHIELD OUTER GLASS SHATTERED.  TO PREV	ENT RECURRENCE, REPLACED WITH KIT-STRESS FREE WINDOW INSTALLATION IAW INSTRUCTIONS PROVIDED.  (K)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005032800100	20050328	00100	SO  	2005	3	28	2005FA0000258    	1	20050219	G	5514	6358500	TAB             			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					STABILIZER	CRACKED         	C			R5NS	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			EA	05	41343	4853 				28R7435171				PILOT NOTED IN FLIGHT WITH MAX NOSE DOWN TRIM AND AIRCRAFT STILL WANTED TO CLIMB.  INSP REALIZED THAT STABILATOR TAB HOR	N BEGAN TO TEAR AWAY FROM TAB SKINS.  THIS DECREASED OVERALL TAB EFFECTIVENESS.  STAB TRIM TAB SKIN AND RIBS WERE CRACKE	D AT THE IB JACK SCREW CONTROL HORN ATTACH POINT.  TAB SKINS (PN 63586-00, 63586-01, NEW STYLE REPLACEMENT (PN 635866-80	0).  TAB IB RIB (PN 63587-00, 63587-01, NEW STYLE REPLACEMENT (PN 63587-002, 63587-003).  NOTE: KNOTS 2U STAB/TAB GAP SE	AL KIT IS INSTALLED ON THIS AIRCRAFT.  THIS KIT MAY HAVE CAUSED EXCESSIVE PRESSURE ON THE TAB`S AND CAUSED CRACK TO FORM	 AT EACH ATTACH POINT. (K)	1	L	7	1 	3O	3	O		2A13    	1E10				 
2005033000021	20050330	00021	CE  	2005	3	30	2005FA0000259    	1	20050222	G	7820	045033862	MUFFLER         			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3596J					15061296	607525A			CRACKING AROUND FRONT RISER.  PART HAS BEEN INSPECTED IAW AD 67-03-01.   PRESSURE CHECK AS REQUIRED AT 100 DEGREE INTERV	ELS.  AIRCRAFT NOT FLOWN SINCE LAST ANNUAL.  8.9 HOURS SINCE LAST REQUIRED INSPECTION IAW AD.  RECOMMEND INSPECTION ANNU	ALLY IAW AD. (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2005032800079	20050328	00079	CE  	2005	3	28	2005FA0000264    	1	20050309	G	8011	S24432	CONTACTOR       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550*      	 	SO  					STARTER	FAILED          	D			RDDR	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			WP	21	PKMPT					U20606987				STARTER CONTACTOR DID NOT DISENGAGE AFTER ENGINE START.  THIS RESULTED IN FAILURE OF THE STARTER AS WELL.  THE SITUATION	 DID NOT BECOME APPARENT UNTIL AFTER TAKEOFF.  THIS AIRCRAFT HAS A (STARTER ENGAGED) WARNING LIGHT INSTALLED BUT IT DID 	NOT INDICATE CLEARLY 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.  FIRST LIGHTWEIGHT STARTER INSTALLED ON THIS AC, INDICATION THAT LIGHTWEIGHT STARTERS HAVE HIGHE	R CURRENT DRAW THAN LARGER STARTER THAT WAS USED.  SUSPECT MFG CONTACTOR CANNOT HANDLE LOAD.(K)	1	H	7	1 	3O	3	O		A4CE    	E3SO				 
2005031000130	20050310	00130	CE  	2005	3	10	2005FA0000273    	1	20050111	G	2912	99144655	FILTER          			CESSNA	750   	750         	2076810	CE  										HYD SYSTEM	LEAKING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23		4550 				0093				HYDRAULIC LEAK FROM RT PYLON NOTED DURING POST FLIGHT, CAUSE: RUDDER STANDBY FILTER ASSEMBLY DIFFERENTIAL PRESSURE INDIC	ATOR HAD 1 RETAINING SCREW SHEARED AT THE HEAD P/N AA-2100-11D99. 3000 PSI OF SYSTEM PRESSURE CAUSED O-RING DAMAGE AND T	HE SUBSEQUENT LEAK.				2	L	7	2 	4J			RT	T00007WI					 
2005031000096	20050310	00096	CE  	2005	3	10	2005FA0000275    	1	20050105	G	2497	3505501	CONNECTOR       			CESSNA	650   	650         	2076802	CE  											ARCED           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	49SM					6500132				A WIRE CONNECTOR WAS INSTALLED TO REPLACE A BROKEN CONNECTOR. CONNECTOR WAS INSTALLED AND APPROVED FOR RETURN TO SERVICE	 BY A CERTIFIED REPAIR STATION.THE WIRE PROVIDED POWER TO THE OVERHEAD LIGHTS. APPROXIMATELY TWO WEEKS AFTER THE MAINTEN	ANCE WAS PERFORMED, THE OPERATOR WAS PERFORMING AN OXYGEN MASK DROP TEST. HE HEARD A NOISE AND THEN SMELLED SMOKE AND SA	W A SMALL FLAME IN THE HEADLINER AREA NEAR THE CABIN DOOR. THE OPERATOR SHUT OFF POWER AND EXTINGUISHED THE FLAME. INVES	TIGATION REVEALED THE CONNECTOR WAS MELTED AND THE WIRING WAS BURNED. THE OXYGEN SUPPLY LINE ADJACENT THE WIRE HAD SOME 	BURNED STRANDS OF OUTER COVERING. THE OPERATOR REPAIRED THE WIRING AND INSTALLED A NEW OXYGEN LINE.	2	L	7	2 	4F				A9NM    					 
2005031100076	20050311	00076	CE  	2005	3	11	2005FA0000276    	1	20050211	G	3246	378941	HEAT SHIELD     	BFGOODRICH  		CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					WHEEL	CONTAMINATED    	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SO	11	404BT				0708	5605038				AFTER LANDING, SMOKE AND SMALL FLAME OBSERVED FROM LT MAIN GEAR WHEEL. FIRE WAS EXTINGUISHED, NO DAMAGE TO LANDING GEAR 	OR AIRCRAFT. LT MAIN GEAR WHEEL ASSEMBLY WAS REPLACED AS A PRECAUTION. THE LT WHEEL HAD BEEN RECENTLY CLEANED WITH A WAT	ER BASED SOLVENT IAW THE WHEEL CMM.  SUSPECT THAT THE PARTS CLEANER USED TO CLEAN THE WHEEL MAY HAVE BEEN CONTAMINATED W	ITH A PETROLEUM BASED LIQUID. IAW MFG, THERE HAVE BEEN REPORTED CASES OF WHEEL FIRES DUE TO THE HEAT SHIELD ABSORBING A 	PETROLEUM SOLVENT.		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005031100065	20050311	00065	GL  	2005	3	11	2005FA0000277    	2	20050120	G	7323	6871461	TUBE            			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	WORN            	C				R				AUTOROTATION            				J			WARNING INDICATION        			CR	CRUISE         	1			SW	09	8375F	1967 	47   			0031A	CAE845077			THE PILOT WAS FLYING AT APPROX. 600 FEET INDICATED, WHEN HE EXPERIENCED A VIOLENT YAW TO THE RIGHT AND A HIGH PITCH ENG.	 SOUND. AN EMERGENCY LANDING WAS MADE WITH PARTIAL POWER UNTIL THE LAST 50 FT. AND THEN THE PILOT HAD TO ENTER AUTOROTAT	ION WITH NO POWER DUE TO EXCESSIVE SURGING AND YAWING THAT RESULTED.  IT HAD BEEN INSTALLED AND WORKING 47.1 HOURS BEFOR	E THE OCCURANCE. THE PROBLEM WAS A B-NUT ON THE PR LINE (REGULATED AIR PRESSURE) HAD SOMEHOW BACKED OFF FROM THE POWER T	URBINE GOVERNOR. THIS CAUSED GOVERNOR FAILURE, CAUSING EXTREME ERRATIC OPERATION OF THE BENDIX FUEL SYS. COMPONENTS.		1	G	7	1 	3U	3	U	0	4H12    	E4CE				 
2005031400085	20050314	00085	SW  	2005	3	14	2005FA0000278    	1	20050209	G	6230	430310461101	BEARING         	BELL        		BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					SWASHPLATE	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	9SP	992  			49086	49086				SWASHPLATE DUPLEX BEARING P/N 430-310-461-101 S/N ZV10085 FOUND WORN ON LOWER RACE.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2005041900038	20050419	00038	SO  	2005	4	19	2005FA0000291    	1	20050301	G	8011		STARTER         			PIPER 	PA44  	PA44180     	7104402	SO  										RT ENGINE	STICKING        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	931ER	2128 	86   			4496155				THIS STARTER SHOWED NO SIGNS OF FAILURE.  DURING MAINTENANCE, THE STARTER WOULD NOT ENGAGE THE RING GEAR.  THE STARTER D	ID HAVE A LONG SERVICE LIFE, BUT IS SIMILAR IN FAILURE TO MANY, MANY OF THESE STARTERS ON THIS FLEET THAT LASTS ONLY SEV	ERAL HOURS, SOMETIMES UNDER 5 HOURS OR NEVER CRANK THE ENGINE THE FIRST TIME AFTER INSTALLATION.				1	L	7	2 	3O				A19S0   					 
2005032800062	20050328	00062	CE  	2005	3	28	2005FA0000297    	1	20050209	G	2421	DOFF10300B	ALTERNATOR      			CESSNA	185   	A185F       	2072821	CE  										ENGINE	CORRODED        	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			NM	11	61423	541  	541  			18504180				LOW VOLTAGE LIGHT COMES ON OCCASIONALLY-RESET SWITCH AND OPERATES NORMAL. FOUND BRUSHES WORN OUT IN ALTERNATOR. REMOVING	 ALTERNATOR WAS EXTREMELY DIFFICULT. MOUNTING BOLT WAS FROZEN IN ALTERNATOR. USING PENETRANT HELPED TO FREE THE BOLT.  D	ISCOVERED THAT FACILITY HAD INSTALLED A STEEL BUSHING IN MOUNTING BOSS DURING OVERHAUL. THE BOLT AND BUSHING WERE RUSTED	 TOGETHER. THE BUSHING APPEARS TO BE A REPAIR.			1	H	7	1 	3O				3A24    					 
2005032800064	20050328	00064	CE  	2005	3	28	2005FA0000298    	1	20050205	G	3246	D306001	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	MLG	FAILED          	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	01	13263	3920 				17262622	L3598627A	723093		FOUND RT MAIN TIRE WAS LOCKED UP. PUT WHEEL ON DOLLY AND PULLED PLANE TO HANGER. CLOSER LOOK IN HANGER FOUND THAT RIM HA	D BLOWN APART. DEFLATED TIRE AND LOOKED INSIDE RIM. FOUND PIECE BROKEN OUT OF CENTER SECTION OF RIM. CRACKS WERE FOUND A	ROUND BOLT HOLES OF RIM HALVES. EXAMINED BROKEN PIECE, FOUND THAT PORTION OF CRACK WAS OLD, REST BEING NEW.  WITH AIR PR	ESSURE IN TIRE, IT WAS TRYING TO BLOW IT APART. HAVE SEEN THIS PROBLEM ALOT WITH MFG WHEELS HAVING CRACKS AROUND BOLT HO	LES, BUT HAVEN`T SEEN ONE COME APART. YOU CAN ONLY SEE CRACKS WHEN CHANGING TIRE FROM THE INSIDE. I THINK IT IS FROM OVE	R-TIGHTENING BOLTS UPON ASSY WHEN CHANGING TIRES. ALSO, HAVING STEEL BOLTS THREADING INTO ALUMINUM HOUSING.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005032800065	20050328	00065	CE  	2005	3	28	2005FA0000299    	1	20050205	G	3246	D306001	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ZONE 700	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	01	13263	3920 				17262622	L3598627A	723093		FOUND RT MAIN TIRE WAS LOCKED UP. PUT WHEEL ON DOLLY AND PULLED PLANE TO HANGER. CLOSER LOOK IN HANGER FOUND THAT RIM HA	D BLOWN APART. DEFLATED TIRE AND LOOKED INSIDE RIM. FOUND PIECE BROKEN OUT OF CENTER SECTION OF RIM. CRACKS WERE FOUND A	ROUND BOLT HOLES OF RIM HALVES. EXAMINED BROKEN PIECE AND FOUND THAT PORTION OF THE CRACK WAS OLD, REST BEING NEW.  WITH	 AIR PRESSURE IN TIRE, IT WAS TRYING TO BLOW IT APART. HAVE SEEN THIS PROBLEM ALOT WITH MFG OF WHEELS HAVING CRACKS AROU	ND BOLT HOLES. BUT NEVER SEEN ONE COME APART. YOU CAN ONLY SEE THE CRACKS WHEN CHANGING TIRE FROM THE INSIDE. MAYBE FROM	 OVER-TIGHTENING THE BOLTS UPON ASSY WHEN CHANGING TIRES. ALSO, HAVING STEEL BOLTS THREADING INTO ALUMINUM HOUSING.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005032800067	20050328	00067	CE  	2005	3	28	2005FA0000300    	1	20050130	G	2820		LINE            			CESSNA	206   	206CESSNA   	2073302	CE  										FUEL SYSTEM	CHAFED          	D				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			WP	17										WHILE PERFORMING AN ANNUAL INSPECTION IN THE CABIN SUBFLOOR AREAS, NOTED A FUEL LEAK AT THE PORT 90 DEGREE RIDGID FUEL L	INE LINKING THE WING TANK, VIA THE PORT DOOR PILLAR, TO SUBFLOOR LINE THAT CONNECTS TO THE SELECTOR VALVE. IT WAS INSTAL	LED BACKWARD.  THIS PLACED THE LINE TOO CLOSE TO A FLOOR BULKHEAD, CAUSING CHAFING AND WEAR-THROUGH. THIS CREATED A LEAK	 BETWEEN THE FUEL TANK AND THE SHUTOFF VALVE BENEATH THE FLOORBOARD.  DO NOT HAVE A SRM FOR PN.			1	H	7	1 	3O				A4CE    					 
2005032800069	20050328	00069	CE  	2005	3	28	2005FA0000301    	1	20050205	G	3246	D306001	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ZONE 700	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	01	13263	3920 				17262622	L3598627A	723093		FOUND RT MAIN TIRE WAS LOCKED UP. PUT WHEEL ON DOLLY AND PULLED PLANE TO HANGER. CLOSER LOOK IN HANGER FOUND THAT  RIM H	AD BLOWN APART. DEFLATED TIRE AND LOOKED INSIDE RIM. FOUND PIECE BROKEN OUT OF CENTER SECTION OF RIM. CRACKS WERE FOUND 	AROUND BOLT HOLES OF RIM HALVES. EXAMINED BROKEN PIECE AND FOUND THAT PORTION OF CRACK WAS OLD, REST BEING NEW.  WITH AI	R PRESSURE IN THE TIRE, IT WAS TRYING TO BLOW IT APART. HAVE SEEN THIS PROBLEM ALOT WITH MFG WHEELS HAVING CRACKS AROUND	 BOLT HOLES. BUT NEVER SEEN ONE COME APART. YOU CAN ONLY SEE CRACKS WHEN CHANGING TIRE FROM INSIDE. THINK IT IS FROM OVE	R TIGHTENING THE BOLTS UPON ASSEMBLY WHEN CHANGING TIRES. ALSO, HAVING STEEL BOLTS THREADING INTO ALUMINUM HOUSING.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005032800070	20050328	00070	CE  	2005	3	28	2005FA0000302    	1	20050205	G	3246	D306001	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ZONE 700	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	01	13263	3920 				17262622	L3598627A	723093		FOUND RT MAIN TIRE WAS LOCKED UP. PUT WHEEL ON DOLLY AND PULLED PLANE TO HANGER. CLOSER LOOK IN HANGER FOUND THAT RIM HA	D BLOWN APART. DEFLATED TIRE AND LOOKED INSIDE RIM. FOUND PIECE BROKEN OUT OF CENTER SECTION OF RIM. CRACKS WERE FOUND A	ROUND BOLT HOLES OF RIM HALVES. EXAMINED BROKEN PIECE AND FOUND PORTION OF CRACK WAS OLD, REST BEING NEW.  WITH AIR PRES	SURE IN TIRE, IT WAS TRYING TO BLOW IT APART. HAVE SEEN THIS PROBLEM ALOT WITH MFG WHEELS HAVING CRACKS AROUND BOLT HOLE	S, BUT NEVER SEEN ONE COME APART. CAN ONLY SEE CRACKS WHEN CHANGING TIRE FROM INSIDE. THINK IT IS FROM OVER TIGHTENING T	HE BOLTS UPON ASSY WHEN CHANGING TIRES. ALSO, POOR DESIGN HAVING STEEL BOLTS THREADING INTO ALUMINUM HOUSING.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005032800090	20050328	00090		2005	3	28	2005FA0000303    	4	20050307	G	3418		TERMINAL        			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					STALL WARNING	LOOSE           	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	66139					T18208367				STALL WARNING INOP, FOUND STALL WARNING SWITCH TERMINAL SCREW LAYING INSIDE WING, SCREW BACKED OUT IN FLIGHT.						1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2005032800105	20050328	00105	EA  	2005	3	28	2005FA0000304    	2	20050207	G	8530	LW12425	CYLINDER HEAD   			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	CRACKED         	D				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			EA	17	62BA	2588 	738  			274859	L947248			DESCENDING IN FLIGHT NR 3 CYL ON RT ENG FAILED.  ENG WAS SHUTDOWN AND FEATHERED.  AC LANDED WITHOUT FURTHER INCIDENT. TH	ERE WAS NO FIRE. POST INCIDENT INSP OF AREA FOUND, CYLINDER HAD CRACKED AND DISLOCATED AT INTERFACE AREA OF STEEL BARREL	 AND CYLINDER HEAD. INTAKE PUSHROD HAD SEPARATED AND WAS LYING ON THE CYLINDER HEAD, WITH CONSIDERABLE OIL LOSS. FURTHER	 INSP FOUND ENGINE BAFFLING INTACT AND CORRECTLY POSITIONED.  CYLINDER PRESENTED NO OBVIOUS FLAWS AT THE MOST RECENT INS	P, WITH OIL CONSUMPTION AND COMPRESSION WITHIN NORMAL LIMITS. IT IS SUSPECTED THAT A DEFECT IN CYLINDER REPAIR PROCESS (	I.E., GRINDING) ALLOWED AN ABNORMAL STRESS CONCENTRATION TO CAUSE A FAILURE.  CYL WAS REGROUND AND HONED TO P.010. (K)	1	L	7	2 	3O	3	O		1A10    	1E4				 
2005032800117	20050328	00117	GL  	2005	3	28	2005FA0000305    	3	20050203	G	6110	C4451	FERRULE         	MCAULY      		CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	BEARING FLANGE	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3301S				746891	21059101		746891		DURING DISASSEMBLY FOR OVERHAUL, BLADE RETENTION FERRULE C4451 FOUND CRACKED IN BEARING FLANGE ON NR 2 BLADE.  THE CRACK	 APPEARS TO HAVE STARTED AT AN OLD ACTUATING PIN HOLE AND IS OVER THREE INCHES LONG.  S/B 196B HAD NOT BEEN ACCOMPLISHED	 ON THIS PROPELLER.				1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
2005041400111	20050414	00111	CE  	2005	4	14	2005FA0000306    	1	20050117	G	7921	8406E	OIL COOLER      			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4J     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ENGINE	CRACKED         	G				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			SO	05	9JY		442  			M2133				IN-FLIGHT ENGINE FAILURE DUE TO OIL STARVATION RESULTING IN AN EMERGENCY LANDING IN TREES. POST ACCIDENT INVESTIGATION R	EVEALED A CRACKED OIL COOLER, WHICH ALLOWED ENGINE OIL SUPPLY TO BE PUMPED OVERBOARD.  REFERENCE ACCIDENT (NR ATL05CA047	).				1	L	7	1 	3O	3	O		A1CE    	E286	5	N	P4EA	 
2005041500228	20050415	00228	SO  	2005	4	15	2005FA0000308    	1	20050301	G	1497	39570002	RELAY           	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  						SHORTED         	B			NX4T	K				NONE                    				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			SO	15	934ER	13   	13   			4496191				CREW NOTED VARIOUS ROCKER SWITCHES, LOCATED ON INSTR PANEL, FAILED TO ILLUMINATE.  IT WAS DISCOVERED THAT FUEL PUMP SWIT	CHES, LOCATED ON LWR PILOT'S PNL, JUST TO LT OF EMER GEAR EXT, WERE CONTACTING GEAR MUTE RELAY (SMALL METAL BOX) LOCATED	 DIRECTLY BEHIND THEM.  CONTACT WAS MADE THROUGH LWR TRMNLS ON EACH SWITCH, WHICH WAS NOT INSULATED AS WERE SOME OF OTHE	R TRMNLS ON SAME SWITCH.  TERMINALS ARE WHERE LIGHTING WIRES FOR INTERNAL SWITCH LIGHTS ARE CONNECTED TO SWITCH.  THIS C	AUSED ALL OF LIGHTS IN ALL OF PNL MOUNTED ROCKER SWITCHES TO NOT ILLUMINATE. EVIDENCE OF ABNORMAL HEAT BEING GENERATED B	Y LIGHT DIMMER ASSEMBLIES (P/N 39570-002), SO THAT ASSY WAS REPLACED WITH SERVICEABLE ASSY, RELAY WAS ALSO REPOSITIONED.	1	L	7	2 	3O	3	O		A19S0   	E286				 
2005042500213	20050425	00213		2005	4	25	2005FA0000309    	4	20050307	G	3418		SWITCH          			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					STALL WARNING	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	66139					T18208367				STALL WARNING INOP FOUND STALL WARNING SWITCH TERMINAL SCREW LAYING INSIDE WING, SCREW BACKED OUT IN FLIGHT.						1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2005041500085	20050415	00085	EA  	2005	4	15	2005FA0000310    	2	20050204	G	8500		ENGINE          			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	RIGHT	FAILED          	C				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	17	27447					317812022	L125968A			THE PILOT ATTEMPTED TO START THE RT ENGINE, WHILE DOING SO,  HE HEARD A LOUD BANG THE ENGINE STARTED, AFTERWARDS, SHUTDO	WN THE ENGINE AND EXITED THE AIRCRAFT. UPON INVESTIGATION, OBSERVED SKIN DAMAGE BETWEEN THE INSIDE NACELLE AND FUSELAGE,	 THE WING LOCKER SUFFERED SKIN DAMAGE ALONG WITH THE WHEEL WELL WHERE OBSERVED DAMAGE TO THE INSPECTION PANEL. THE FLAP 	ALSO SUSTAINED DAMAGE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2005042500199	20050425	00199	SO  	2005	4	25	2005FA0000313    	1	20050307	G	2140	90D382EL	HEATER          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					CABIN	SMOKE           	B			NX4T	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			WP	07	572ER	401  				4496148				NOTICED HEATER SMOKING FROM THE EXHAUST.  HAD PILOT TURN TEMP CONTROL TO LOW AND SHUT DOWN THE HEATER.  OPENED NOSE CONE	 AND NOTICED SMOKE AND STRONG BURNING SMELL. THE HEATER INLET AIR CONTROL CABLE HAD MELTED ALONG WITH A GROUND WIRE TERM	INAL LOCATED ON THE TOP OF THE HEATER.  ALSO THE HEATER ITSELF HAD A BURNED/DISCOLORED AREA ON THE TOP SIDE.  THERMAL HE	AT BREAKER WAS POPPED. FOUND THE HEATER CABIN BLOWER WAS INOPERATIVE, SO THERE WAS NO AIR CIRCULATION THRU THE HEATER OU	TER CAN.  REPLACED HEATER ASSEMBLY.  THIS IS THE SECOND OCCURRENCE WITHIN THE LAST FOUR DAYS ON THE SAME TYPE OF AIRCRAF	T .  HAVE CONTACTED THE MFG CONCERNING PROBLEM.	1	L	7	2 	3O	3	O		A19S0   	E286				 
2005041500169	20050415	00169	GL  	2005	4	15	2005FA0000314    	3	20050224	G	6114	D4885C61	HUB             	MCAULY      	D2AF34C61   	CESSNA	336   	336         	2075602	CE  	CONT  	O360  	IO360A      	17025	SO  	MCAULY	2AF34C	D2AF34C61   	GL  	BLADE SOCKET	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	3860U				781897	3360160		781897		PROPELLER SENT FOR REPAIR OF RED DYE OIL LEAK. AT DISASSEMBLY HUB WAS FOUND CRACKED IN BLADE RETENTION SOCKET THREADS.						1	H	7	2 	3O	3	O		A2CE    	E1CE	5	C	P5EA	 
2005040100010	20050401	00010	NM  	2005	4	1	2005FA0000337    	1	20050203	G	2760	654494710	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										ACTUATOR	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1902					PIN HOLES AND CRACKS IN SIDEWALL OF HOUSING.  CYCLING FATIGUE.  USE NEW IMPROVED STEEL HOUSING AND REMOVED ALUMINUM HOUS	INGS FROM SERVICE. (MECHANIC, BA2, JOB 192740) (K)					2	L	7	2 	4F			RT	A16WE   					 
2005042700030	20050427	00030	NM  	2005	4	27	2005FA0000338    	1	20050203	G	2913	624022	ADAPTER         	VICKERS     		BOEING	747   	747*        	       	NM  										PUMP	ERODED          	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					MX530942					EROSION AROUND STROKING PISTON PORT.  PROLINGED FLUID FLOW AGAINST SOFT METAL STRONGER MATERIAL FOR HOUSING.  (MECHANIC 	BS1, JOB 192844) (K)					2	L	7	4 	4F			RT	A20WE   					 
2005040400080	20050404	00080	NE  	2005	4	4	2005FA0000339    	1	20050131	G	3213	642550120101	AXLE            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					MLG	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	154AC				EAC14465	64037				(MDR05-073) FOUND CRACKED DURING NDT INSPECTION.  CRACK IS APPROXIMATELY 1 INCH IN LENGTH AND IS IN THE KEY GROOVE.  THI	S IS FIRST KNOW DEFECT OF THIS TYPE FOR THIS PART.  CAUSE IS UNKNOWN AND NO RECOMMENDATIONS TO PREVENT RECURRENCE AT THI	S TIME. (K)				2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005040400071	20050404	00071	NE  	2005	4	4	2005FA0000340    	1	20050110	G	6220	6595211522102	BEARING RACE    	SKRSKY      		SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					M/R HEAD	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	158AC	654  				64081				(MDR05-072) THE MRH SLEEVE AND SPINDLE ASSY DEVELOPED AN OIL LEAK WHILE ON AIRCRAFT AND WAS NOTED DURING ROUTE INSPECTIO	N.  UPON REMOVAL AND REPLACEMENT WITH A SERVICEABLE ASSY, A CRAK WAS FOUND ON THE INNER RACE.  VISUAL INSPECTION SHOWS W	EAR AND CORROSION TYPICAL FOR THIS PART THAT HAS BEEN IN SERVICE.  NO OTHER ABNOMALITIES WITH THE EXCEPTION OF THE CRACK	.  CRACK IS APPROXIMATELY 3 INCHES IN LENGTH AND RUNS IN AXIAL DIRECTION.  THIS IS A FIRST TIME OCCURANCE.  CAUSE IS UNK	NOWN AND NO RECOMMENDATIONS TO PREVENT RECURRENCE AT THIS TIME. (K)		2	G	7	2 	4U	4	U		H6EA    	E15EA				 
2005040100107	20050401	00107	NE  	2005	4	1	2005FA0000341    	1	20050131	G	6210	151520604000	SPAR            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	194AC	5538 			64M54385630	64017				(MDR05-074) THE SPAR IS CRACKED ON THE BOTTOM SIDE OF THE BLADE BETWEEN POCKET LOCATIONS NR 5 AND NR 6.  CRACK IS APPROX	IMATELY .300 INCH IN LENGTH .650 INCH FROM THE BACKWALL RUNNING CHORDWISE TO .950 INCH FROM THE BACKWALL.  BLADE HAD A B	IM INDICATION AND WAS REMOVED FROM AIRCRAFT.  CAUSE IS UNKNOWN AND NO RECOMMENDATIONS TO PREVENT RECURRENCE AT THIS TIME	.(K)			2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005040100017	20050401	00017	SO  	2005	4	1	2005FA0000342    	1	20050209	G	2910	HYC5005	POWERPACK       			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					HYD SYSTEM	FAILED          	B			FFKR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	05	4358X	1826 				347670027				AC DEPARTED, DIVERTED, PILOT THOUGHT THAT HIS LANDING GEAR WAS NOT FULLY IN THE UP AND LOCK POSITION (UNKNOWN IF GEAR UN	SAFE LIGHT WAS ON).  PILOT SELECTED GEAR DOWN, NOTHING HAPPENED, PULLED EMERGENCY GEAR EXTENSION AND LANDED WITH NO FURT	HER INCIDENT.  MAINTENANCE INSPECTED SYSTEM AND FOUND THE HYDRAULIC POWER PACK TO HAVE FAILED.  REPLACED POWER PACK. (SO	05200506731)			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005032800053	20050328	00053	SO  	2005	3	28	2005FA0000343    	1	20050303	G	2140	CD21701	SOLENOID VALVE  			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					HEATER	FAILED          	D			J8SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	220FS					31T7620052				INSTALLED A NEW C&D AIRCRAFT HEATER AS A REPLACEMENT TO THE OLD HEATER UNIT.  THE NEW HEATER WOULD RUN APPROX 5 MINUTES 	AND THEN PRODUCE NO HEAT.  TROUBLESHOOTING SHOWED THAT FUEL WAS REACHING TO THE NOZZLE SOLENOID VALVE, BUT NOT PAST.   V	OLTAGE WAS PRESENT, AS WELL AS A CLICK FROM THE SOLENOID.  REPLACED THE SOLENOID VALVE WITH THE SAME PN, AND HAD THE SAM	E ISSUE.  FURTHER TROUBLESHOOTING, USING SHOP AIR ON THE VALVE AND A BENCH POWER SUPPLY, SHOWED THAT AFTER VALVE WOULD H	EAT UP FROM THE ELECTRICAL CURRENT RUNNING THRU IT (APPROX 5 MINUTES) THE UNIT WOULD NOT ALLOW AIR TO PASS.  THE MFG WAS	 ADVISED OF THESE FINDINGS, AND TESTED  A REPLACEMENT VALVE OF THE SAME PN, BUT OF A DIFFERENT BATCH NR AND FOUND IT TO 	1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2005040100056	20050401	00056	WP  	2005	4	1	2005FA0000344    	1	20050222	G	5610	3403110307	WINDOW          			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	COCKPIT	BLEW OUT        	D				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			GL	23	391FL					278				DURING CRUISE FLIGHT AT FL230, THE FO SIDE WINDOW BLEW OUT; AT WHICH TIME, AN EMERGENCY DESCENT WAS EXECUTED TO AN UNEVE	NT LANDING.  (K)					2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2005040100067	20050401	00067	EU  	2005	4	1	2005FA0000345    	1	20050222	G	2731	Z00N6071017251	ACTUATOR        			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  	HARTZL	HCE4N	HCE4N3      	NE  	ELEVATOR TRIM	FROZEN          	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	23	883CA					294	PCEPM174	HH1868		AFTER THE AIRCRAFT HAD BEEN LEFT OUT IN THE RAIN, THE PREVIOUS DAY, THE AC WAS FLOWN.  UPON HAND FLYING THE AIRCRAFT TO 	ALTITUDE, THE PILOT REPORTED THA THE TRIM WHEEL BECAME INCREASINGLY MORE DIFFICULT TO MOVE AS HE ENTERED FREEZING LEVELS	.  AT OAT -8 THE TRIM WHEEL HAD BECOME COMPLETELY FROZEN.  AFTER THE AC HAD TO BE FORCED NOSE OVER, AT OAT +2, THE TRIM 	WHEEL UNFROZE AND WAS ABLE TO BE TRIMED NORMALLY. (K)			1	L	7	1 	3T	4	T	RT	A60EU   	E4EA	5	C	P10NE	 
2005040100040	20050401	00040		2005	4	1	2005FA0000346    	3	20050221	G	6110	3026652	SEAL            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					PROP SHAFT	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	106SL	1060 				1070	RK0087			PROPELLER SHAFT SEAL WAS LEAKING, CAUSING HIGH OIL CONSUMPTION.  (K)						1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2005040100057	20050401	00057	CE  	2005	4	1	2005FA0000347    	1	20050218	G	3210	35825110	BRACE           			BEECH 	35    	M35         	1151526	CE  										NOSE STRUT	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28										FIND A HIGH PERCENTAGE OF THESE PARTS CORRODED ABOVE THE LOWER BUSHING IN THE GROVE WHERE THE FELT FITS.  THIS PART IS M	ADE OF MAGNESUM SO THE MOISTURE RETAINED BY THE FLET AND GREASE ALLOWS PART TO CORROD.  MFG ALLOWS ONLY 10 PERCENT OF WA	LL THICKNESS TO BE REMOVED FROM THE AREA OF THE CORROSION.  THE PITS IN THIS PART WERE APPROX 50 TO 75 PERCENT OF WALL T	HICKNESS. (K)			1	L	7	1 	3O				3A15    					 
2005032800060	20050328	00060	CE  	2005	3	28	2005FA0000348    	1	20050318	G	5500	0411930	BRACKET         			CESSNA	150   	150C        	2071808	CE  	CONT  	O200  	O200*       	17020	SO  					EMPENAGE	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1918Z					15059718				(1) RIVET SHEARED AND BRACKET ROTATED, PARTIALLY.  THIS WAS CAUSED BY FLAP CABLES BEING RIGGED TOO TIGHT.  THIS CAUSED A	 TWIST IN THE CABLES ALLOWING (1) CABLE TO RIDE UP AND OVER THE OTHER CAUSING IT TO COME OFF AN210-2A PULLEY.  THE PILOT	 REPORTED GREAT DIFFICULTY IN EXTENDING FLAPS.  FOLLOW MFG INSTRUCTIONS.  (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2005032800044	20050328	00044	SO  	2005	3	28	2005FA0000350    	2	20050309	G	8530		EXHAUST VALVE   			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200*       	17020	SO  					NR 3 CYLINDER	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	6627F	174  				15063227	629926A			NR 3 CYLINDER HAS A STUCK  EXHAUST VALVE.  UPON CYLINDER REMOVAL IT WAS FOUND THAT THE VALVE HEAD WAS MUSHROOMED AND THE	 ROCKER ARM WAS ALSO DAMAGED.  THIS CAUSED CONCERN DUE TO THE FACT THAT THE CYLINDER ONLY HAD 174.1 TOTAL HOURS SINCE IT	 WAS PURCHASED NEW.  CYLINDER WAS SENT FOR REPAIRS AND THEN INSTALLED BACK ON THE ENGINE. (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2005032800089	20050328	00089	CE  	2005	3	28	2005FA0000351    	1	20050302	G	5340	24130351	ANGLE           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUSELAGE	CORRODED        	B			DDER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	6543V					172RG0766	L2664936A	806017		THIS ANGLE IS WHAT TIES TOGETHER THE WING STRUT, ATTACHES ON THE LT AND RT SIDES OF THE FUSELAGE.  IF THIS CORROSION WHE	RE TO PROGRESS MUCH FURTHER, IT COULD CAUSE THE STRUTS TO FAIL.  (K)					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2005042700044	20050427	00044	SO  	2005	4	27	2005FA0000352    	1	20050307	G	3210		BOLT            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					RT TORQUE LINK	MISSING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	3542K	5664 				2823617				EXAMINATION OF THE AC REVEALED THAT THE LOWER STRUT, BRAKE AND TIRE ASSY WERE MISSING FROM THE RT MAIN GEAR.  UPPER MAIN	 GEAR TORQUE LINK WAS ATTACHED TO THE UPPER STRUT HOUSING.  BRAKE LINE WAS BROKEN OFF AT THE BRAKE CYLINDER FITTING AND 	LOWER STRUT ASSY WAS MISSING.  IT APPEARS THAT TORQUE LINK BOLT FAILED ALLOWING LOWER STRUT ASSY TO EXTEND OUT OF THE ST	RUT HOUSING AND FALL FREE OF THE AC.  UNABLE TO CONFIRM BASED ON AVAILABLE MAINTENANCE RECORES, BUT AC APPEARS TO HAVE G	REASE BOLT REPLACMENT KIT (PN 760-910) INSTALLED.  REPETITIVE NDT INSPECTION BE PERFORMED ON LANDING GEAR TORQUE LINK BO	LT.  (SO13200503296) (K)	1	L	7	1 	3O	3	O		2A13    	E274				 
2005040100102	20050401	00102	SO  	2005	4	1	2005FA0000353    	2	20050224	G	7414	6320	MAGNETO         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	FAILED          	D			AIHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	468TW	58   				414A0071				RT MAGNETO, PN 6320, SN 02091774 FAILED AFTER 58.0 HOURS TOTAL TIME IN SERVICE.  INVESTIAGATION FOUND BROKEN CONTACT ASS	Y.  VISUAL INSPECTION OF BOTH RT AND LT CONTACT ASSY IF SN IS WITHIN 100 OF FAILED PART.  NOTE: LT MAGNETO SAME ENGINE P	N 6320, SN 02091734 FAILED AT 54.0 HRS TT IN SERVICE.  SAME PROBLEM. (GL11200508228)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005042700045	20050427	00045	SO  	2005	4	27	2005FA0000354    	2	20050224	G	7414	6320	MAGNETO         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LEFT	FAILED          	B			AIHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	468TW					414A0071	516571			LT MAGNETO, PN 6320, SN 02091734 FAILED AFTER 54 HOURS TT IN SERVICE.  INVESTIGARTION FOUND BROKEN CONTACT ASSY.   VISUA	L INSPECTION OF BOTH LT AND RT CONTACT ASSY IF SN IS WITHIN 100 HOUR OF FAILED PART.  NOTE; RT MAGNETO SAME ENGINE, PN 6	320, SN 02091744 FAILED AT 58.0 HOURS TT IN SERVICE.  FROM SAME PROBLEM.  (GL11200508227) (K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005040400040	20050404	00040	SO  	2005	4	4	2005FA0000355    	1	20050304	G	2721	96319802	TORQUE TUBE     			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					RUDDER	ELONGATED       	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	39655	6496 				347870403				DURING INSPECTION, TECH DISCOVERED PLAY IN RUDDER TORQUE TUBE FITTING.  TECH INSTALLED SERVICE KIT 764-100V.  AD AND SB 	ADDRESSES INSP AN REPLACEMENT OF THE STEEL TORQUE TUBE FITTING WITH A STEEL REPLACEMENT PART.  THIS AC HAD THE STEEL TOR	QUE TUBE FITTING INSTALLED PREVIOUSLY.  WITH THE STEEL TORQUE TUBE FITTINGS, SEEING THE HOLES ELONGATED.  IT IS DIFFICUL	T TO NOTICE HOLES ARE ELONGATED DURING INSP SINCE THE RUDDER IS NOT REMOVED FROM THE TORQUE TUBE FITTING DURING TYPICAL 	SCOPE OF INSP.  IF TECH MOVES RUDDER TO THE FULL STOP IN ONE DIRECTION AND THEN SLOWLY MOVES TO OPPOSITE STOP AND GENTLY	 PUSHES ON THE RUDDER YOU CAN NOTICE SLIP OF TORQUE TUBE WITHIN FITTING.	1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005040400051	20050404	00051	CE  	2005	4	4	2005FA0000356    	1	20050215	G	2597	4520133L	WIRE            	ARTEX       		BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					BATTERY	BROKEN          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	75RL	1195 			00831	RK312				REMOVED BATTERY FROM ELT 110-406 FOR VISUAL INSPECTION IAW WITH MFG MM.  UPON INITIAL INSPECTION FOUND ONE WIRING TERMIN	AL BROKEN OFF OF ONE BATTERY CELL.  BATTERY EXPIRATION DATE 6/2006.  (K)					2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2005040100013	20050401	00013	SO  	2005	4	1	2005FA0000357    	1	20050321	G	7120	6843949	SUPPORT         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  					NR 2 ENGINE	INCORRECT       	G			NO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	401LC					4606	8CLMG			DURING NR 2 ENGINE REPLACEMENT AND INSTALLATION OF THERMOCOUPLES THE FOLLOWING OBSERVATIONS WERE MADE: 2 COMBUSTION LINE	R SUPPORTS HAD BEEN GROUND TO FIT INTO LINER.  LOOSE LOCKWIRE ON REAR SCAVANGE PUMP RETAINING NUTS.  INLET/ OUTLET OIL T	RANSFER TUBE RETAINING SCREWS LOOSE NOT SAFETY WIRED. (K)				2	H	7	4 	4T	4	T		A1SO    	E282				 
2005040100021	20050401	00021	EA  	2005	4	1	2005FA0000358    	2	20050307	G	8520	AEL18840	CAMSHAFT        			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320C1A    	41508	EA  					ENGINE	BROKEN          	C				B	A			EMER. DESCENT           	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			SO	13	8833Y		100  			301991	L00587655A			WHILE CLIMBING OUT OF 4,000 FT, RT ENGINE (2-23-05) SHUTTERED AND BEGAN VIBRATING EXCESSIVELY.  RETURNED TO AIRPORT.  IN	SPECTION REVEALED THE CAMSHAFT HAD BROKEN COMPLETELY INTO 2 PIECES, ENGINE REMOVED AND SENT TO REPAIR FACILITY FOR FURTH	ER EVALUATION.  ENGINE TT SINCE O/H 100 HOURS.  AUTHORISED RELEASE FORM SHOWED NEW PART RELEASED ON APRIL 25, 2002. (K)				1	L	7	2 	3O	3	O		A1EA    	1E12				 
2005040400086	20050404	00086	SO  	2005	4	4	2005FA0000359    	1	20050303	G	2140		GASKET          	JANITROL    		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					REGULATOR	LEAKING         	H			LM8S	O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			NM	07	978WC					4496041				PILOT REPORTED SMELLING FUEL WHEN THE COMBUSTION HEATER WAS RUNNING.  MAINTENANCE FOUND FUEL SPRAYING FROM A GASKET JOIN	T ON THE REGULATOR SIDE OF THE HEATER FUEL SHUTOFF AND REGULATOR VALVE.  THIS VALVE WAS REPLACED FOR LEAKING IAW AD.  TH	IS VALVE WAS INSPECTED FOR LEAKS DURING THE OPS CHECK OF THE HEATER AS PART OF THE ANNUAL INSPECTION ON 11-9-2004,  93.7	 AIRCRAFT HOURS PRIOR TO THIS FAILURE. (K)			1	L	7	2 	3O	3	O		A19S0   	E286				 
2005042700063	20050427	00063	SO  	2005	4	27	2005FA0000360    	1	20050224	G	7312		HEATER          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					FUEL/OIL	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	83BA	1    				110351	2080			PILOT OBSERVED FLUCTUATING OIL PSI (100-70PSI) BROUGHT POWER BACK TO 200 LBS. TQ AND OIL PSI DROPPED TO 50 PSI.  PILOT F	EATHERED AND SHUTDOWN EFFECTED ENGINE.  AFTER MECH INVESTIGATED THE PROBLEM, FOUND THAT FUEL HAD MIXED WITH THE OIL SUPP	LY AND DILUTED IT TO A WATER LIKE CONSISTENCY.  BELIEVE THAT THE FUEL OIL HEATER CORE HAS HOLE IN IT WHICH WOULD ALLOW F	UEL TO MIX WITH THE ENGINE OIL SUPPLY.  (K)			1	L	7	2 	4T	4	T		A21SO   	E4EA				 
2005032800063	20050328	00063	CE  	2005	3	28	2005FA0000361    	1	20050205	G	5311	504200285758	FRAME           			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6*        	52043	EA  					FUSELAGE	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	325WR					LA10				DURING 6000 CYCLE AIRFRAME INSPECTION, FOUND LT AND RT CABIN FORMERS FRACTURED INTO 2 PIECES AT STA 177.00 AT WL 90-91 (	APPROXIMATE) CAUSE OF FAILURE UNKNOWN (SUSPECT HARD LANDING).  OBTAINED DER FOR REPAIR- CONSULTED MFG TECH SUPPORT ON FI	NDINGS.  REMOVED AND REPLACED LT AND RT FORMERS. (K)				1	L	7	2 	4T	3	T		A31CE   	E2NE				 
2005042700065	20050427	00065	CE  	2005	4	27	2005FA0000363    	1	20050117	G	1430	AN37A	BOLT            	CESSNA      		CESSNA	150   	150D        	2071810	CE  	CONT  	O200  	O200*       	17020	SO  					RUDDER	WORN            	G				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	07	901SW					15060734				TOP RUDDER HINGE BOLT LOOSENED FROM THE SELF LOCKING NUT PLATE AND CAME OUT CAUSING THE RUDDER ASSEMBLY TO DETACH FROM T	HE AC COMPLETELY DURING FLIGHT AT 2000 AGL.  THIS BOLT SHOULD HAVE SOME TYPE OF RETAINING MECHANISM IN ADDITION TO THE S	ELF LOCKING NUT PLATE. (NM07200502996) (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2005040100061	20050401	00061	CE  	2005	4	1	2005FA0000364    	1	20050121	G	7810	STC8645SW	CLAMP           			CESSNA	170   	170B        	2072306	CE  	CONT  	C145  	C145*       	17012	SO  					TAILPIPE	OVERSIZED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	3167A					25811	7909D32			BOTH TAILPIPE/MUFFLER CONNECTIONS WERE FOUND TO BE OVERSIZED.  THE EXHAUST PIPE CLAMPS WERE NOT OF SUFFICIENT STRENGTH T	O SQUEEZE THE OVERSIZED PIPE DOWN ON THE MUFFLER EXHAUST TUBE.  THE RESULTING LOOSE FIT WAS ALLOWING EXHAUST FUMES TO SH	OOT INTO THE CABIN HEAT AND THE CARBURETOR HEAT SECTIONS OF THE MUFFLERS.  ONE THING THAT AGGRAVATED THE CONDITION WAS T	HE FACT THAT THE TAILPIPES WERE CRAMMED TOO FAR UP ON THE MUFFLER PIPE.  THIS MADE IT INEVITABLE THAT ANY LEAKAGE WOULD 	ENTER THE MUFFLER/HEAT SHROUD SECTION.  SUGGEST GIVING THIS AREA CLOSE SCRUTINY.		1	H	7	1 	3O	3	O		A799    	E253				 
2005042700067	20050427	00067	CE  	2005	4	27	2005FA0000366    	1	20050201	G	5711	052340051	SPAR            			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5134F	13526				17252909				DURING A BORESCOPE INSPECTION, A CRACK WAS FOUND IN THE RT REAR SPAR AT THE IB FLAP TRACK ATTACH POINT.  PROBABLE CAUSE 	IS FATIGUE.  THIS IS A VERY HIGH TIME, AC WITH OVER 13, 000 HOURS TT.  IT HAS ALSO BEEN USED AS A FLIGHT TRAINER FOR ITS	 ENTIRE LIFE.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005040400099	20050404	00099	CE  	2005	4	4	2005FA0000369    	1	20050120	G	5397	DPA13	CABLE           			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					FUSELAGE	BURNED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	13	735WR					18265747				DEFECT WAS FOUND AT ENGINE REMOVAL AND FIREWALL CLEANING.  THE ELECTRICAL CABLE BETWEEN AUX POWER RELAY AND STARTER RELA	Y WAS FOUND TO HAVE BURN MARKS AND OBVIOUS DAMAGE TO INSULATION.  ADJACENT TO THE DAMAGED PORTION OF THE CABLE WAS A SHE	ET METAL SCREW IN THE FIREWALL (INSTALLED WITH THE HEAD OF THE SCREW ON AFT SIDE OF FIREWALL).  THE POINTED END OF THE S	CREW HAD PIERCED THE INSULATION AND CAUSED SOME ARCING.  NEW CABLE INSTALLED ON AIRCRAFT, SCREW REMOVED AND REINSTALLED 	IN REVERSE POSITION (HEAD OF SCREW ON FORWARD SIDE OF FIREWALL).  THE SCREW THAT CAUSED THE DAMAGE IS USED TO ATTACH A P	LASTIC SHIELD THAT PROTECTS THE INTERIOR FROM BEING CAUGHT IN THE ELEVATOR CABLE PULLEY THAT IS LOCATED ON AFT SIDE OF F	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2005040100097	20050401	00097	SW  	2005	4	1	2005FA0000376    	1	20050121	G	3210	ED124061	SHAFT           			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					RT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	909HH					15035				SHAFT SECURING TORQUE LINK TO RT MLG STRUT FOUND BROKEN DURING INSPECTION.  THIS TORQUE LINK IS AT TOP OF STRUT AND ROTA	TES LOWER STRUT 90 DEGREES DURING RETRACT/ EXTEND CYCLE.  INSTALLED NEW SHAFT. (K)					1	H	7	2 	3T	3	T		2A4     	E2WE				 
2005032800035	20050328	00035	SW  	2005	3	28	2005FA0000377    	1	20050106	G	2810	206064633105	FUEL CELL       			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					AFT	DAMAGED         	C			UOHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	206GH	3333 				52112				DURING A SCHEDUALED 12 MONTH FUEL SYSTEM INSPECTION IAW MM, THE DEFECT WAS NOTED ON A CUSTOMERS AIRCRAFT.  THE BOTTOM IN	SIDE OF THE AFT FUEL CELL WAS BLISTERED WITH .2500 INCH BLISTER IN DIAMETER, SPACED FROM .5000 INCH TO .2500 INCH APART.	  THE BLISTERS CONTINUED UP THE SIDE OF THE CELL 6 INCHES WITH THE SPACING BECOMING LARGER BETWEEN BLISTERS.  THE FORWAR	D 2 FUEL CELLS SHOWED NO DEFETS, ALL FILTERS WERE NORMAL, THE 2 INLINE SCREENS AND INJECTOR PUMP WERE CLEAN ALSO.  THE A	IRCRAFT MFG WAS NOTIFIED AND THE CELL WAS DETERMINED TO BE UNAIRWORTHY AND WILL BE RETURNED TO THE AIRCRAFT MFG.  PROBAB	LE CAUSE IS UNKNOWN, RECOMMENDATIONS ARE TO RETURNE THE CELL TO MFG TO EVALUATE DEFECTS.(K)	1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2005040400046	20050404	00046	CE  	2005	4	4	2005FA0000382    	1	20050120	G	3250	204301410	SHIMMY DAMPENER 			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NLG	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	534DW					177RG1004				DURING PRE-INSPECTION RUN UP/ TASK, STEERING WAS RESTRICTED TO RT.  FOUND THAT WHOEVER HAD THE SHIMMY DAMPNER OFF LAST, 	REVERSED THE GIMBAL THAT ATTACHES IT TO THE ENGINE MOUNT.  THERE SHOULD BE A WARNING PLACARD OR MODIFICATION THAT MAKES 	REVERSAL IMPOSSIBLE.  (K)				1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005040400096	20050404	00096	WP  	2005	4	4	2005FA0000383    	1	20050322	G	7100	NSL6051513	NOSE COWL       			DOUG  	DC10  	DC10*       	       	WP  										ENGINE	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	25										NOSE COWL SENT TO US FOR REPAIR.  DURING EVALUATION SEVERE INTERGRANULAR CORROSION WAS DISCOVERED ON THE OUTER SKIN OF T	HE ACOUSTIC BARREL.  SUSPECT IMPROPER HEAT TREATMENT AT MFG.  PART IS CONSIDERED BEYOND ECONOMICAL REPAIR AND WILL BE SC	RAPPED AT THIS LOCATION. (K)				2	L	7	3 	4F				A22WE   					 
2005040400050	20050404	00050	CE  	2005	4	4	2005FA0000384    	1	20050112	G	2140	94E422	PRESSURE SWITCH 			BEECH 	58    	58          	1152740	CE  										HEATER	INTERMITTENT    	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	858W	60   				TH2060				INVESTIGATED COMPLAINT OF COMBUSTION HEATER NOT OPERATING.  DURING TROUBLESHOOTING, FOUND COMBUSTION AIR SWITCH CONTINUI	TY INTERMITTENTLY CYCLING OPEN AND CLOSED DURING NORMAL OPERATING PRESSURES.  SWITCH DATE CODE: 9/02.  REPLACED COMBUSTI	ON AIR SWITCH WITH NEW SWITCH, ALSO THERMOSTATIC SWITCH.  HEATER OPERATIONS, NORMAL. (K)				1	L	7	2 	3O				3A16    					 
2005040100045	20050401	00045	CE  	2005	4	1	2005FA0000385    	1	20050131	G	5753	052323113	FLAP TRACK      			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					LT WING	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	4989R					17256343	28598D4D			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 PARTS AT THE MFG FOR REPAIR.  SINCE MFG DOES NOT HAVE LIMITATIONS ON THEIR FLAPS TRACKS, WOULD SUGGEST THAT THEY BE 	REMOVED AND REPLACED AT 5,000 HOUR INTERVALS. (K)		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005040400047	20050404	00047	CE  	2005	4	4	2005FA0000386    	1	20050131	G	5753	052323113	FLAP TRACK      			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	LT WING	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4992R					17256346	29876D9DR	75113		DURING PREFLIGHT, THE LT OB FLAP TRACK WAS NOTICED TO HAVE DAMAGE.  AIRCRAFT WAS IMMEDIATELY GROUNDED AND THE FLAP TRACK	S AND ROLLERS WERE REPLACED WITH NEW PARTS.  NO FURTHER DAMAGE HAD OCCURRED TO THE FLAP ASSY.  SINCE MFG DOES NOT HAVE L	IMITATIONS ON THEIR FALP TRACKS, WOULD SUGGEST THAT THEY BE REMOVED AND REPLACED AT 5,000 HOUR INTERVALS. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2005033000039	20050330	00039	CE  	2005	3	30	2005FA0000387    	1	20050201	G	5711	052340051	SPAR            			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4974R	13293				17256328	29834	XK44008		DURING A BORESCOPE INSPECTION OF THE REAR WING SPAR, A CRACK WAS FOUND AT THE IB FLAP TRACK ATTACH POINT.  PROBABLE CAUS	E IS FATIGUE.  THIS IS A VERY HIGH TIME AC WITH OVER 13,000 HOURS TT.  IT HAS ALSO BEEN USED AS A FLIGHT TRAINER FOR ITS	 ENTIRE LIFE.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2005040100055	20050401	00055	CE  	2005	4	1	2005FA0000388    	1	20050131	G	5711	052340050	SPAR            			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172*      	GL  	LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4989R	12536				17256343	28598D4D	UF022		WHILE CHANGING THE FLAP TRACKS ON THE LT WING 2 SMALL CRACKS, .2500 INCH LONG, EACH WERE NOTICED ON THE IB AFT WING SPAR	 AT THE IB FLAP TRACK ATTACH POINT.  PROBABLE CAUSE IS FATIGUE.  THIS IS A VERY HIGH TIME AIRCRAFT WITH OVER 12,000 HOUR	S TT.  IT HAS ALSO BEEN USED AS A FLIGHT TRAINER FOR ITS ENTIRE LIFE. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2005042700088	20050427	00088	CE  	2005	4	27	2005FA0000389    	1	20050131	G	5711	052340051	SPAR            			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	RT WING IB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4989R					17256343	28598D4D	YC44006		DURING A BORESCOPE INSPECTION, A CRACK WAS FOUND IN THE RT REAR SPAR AT THE IB FLAP TRACK ATTACH POINT.  PROBABLE CAUSE 	IS FATIGUE.  THIS IS A VERY HIGH TIME AIRCRAFT WITH OVER 12,000 HOURS TT.  IT HAS ALSO BEEN USED AS A FLIGHT TRAINER FOR	 ITS ENTIRE LIFE. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2005040100059	20050401	00059	SO  	2005	4	1	2005FA0000390    	1	20050322	G	4950	1159AC2005563	DUCT            			GULSTM	G1159 	G1159       	3953505	SO  										APU BLEED SYS	DAMAGED         	B			W1JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	400M					132				WITH APU RUNNING AND AIR SELECTED ON APU BLEED AIR OPENED HOLE IN INSULATION BY CUTTING BACK INSULATION.  FOUND HOLE IN 	WELDED SEAM BETWEEN TO DUCTS (Y) DUCT NOMINCLATURE IS; DUCT ASSY, APU AND GROUND START.					2	L	7	2 	4F			RT	A12EA   					 
2005032800041	20050328	00041	GL  	2005	3	28	2005FA0000395    	2	20050316	G	7310	P49389	CHECK VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FUEL SYSTEM	MISINSTALLED    	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	01	18SP	796  				53533				COMPONENT INSTALLED ON THE SIDE OF ENGINE. WHEN IT WAS INSPECTED FOUND NUT DISLODGED FROM STUD COVER OF CHECK VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005033000017	20050330	00017	CE  	2005	3	30	2005FA0000396    	1	20050225	G	5712	502205053	RIB             			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					WINGS	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	421CT	6881 				421B0510				DURING AN ANNUAL INSP, NOTED CRACKS IN LT AND RT WING T/E RIBS AT FORWARD END AFT SPAR ATTACHMENT POINT AREAS.  AFFECTED	 RIBS ARE FIRST RIBS IB OF SPOILER SYSTEM ACTUATOR ATTACH POINTS.  ALSO FOUND CRACKED AREA IN WING OB T/E SKIN PANEL AT 	ATTACHMENT POINT TO WS 118.24 T/E RIB, ALSO ADJACENT TO THE RT SPOILER AREA.  AIRCRAFT HAD A MFG ELECTRIC/HYDRAULIC SPOI	LER SYSTEM INSTALLED PREVIOUSLY IAW STC SA4755NM.  SUSPECT IN-FLIGHT STRESSES FROM NORMAL OR HIGH-SPEED OPERATIONS CAN B	E CAUSING ACCELERATED FATIGUE IN THESE AREAS.  RECOMMEND ROUTINE CLOSE VISUAL INSPECTION OF THESE AREAS.  (K)		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005033000015	20050330	00015	CE  	2005	3	30	2005FA0000397    	1	20050225	G	5712	082340063	BULKHEAD        	CESSNA      		CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					LT TIP TANK	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	421CT	6881 				421B0510				DURING AN ANNUAL INSPECTION, FOUND AFT BULKHEAD OF THE LT WING TIP TANK ASSY.  CRACKED THROUGH FROM APPROXIMATE CENTER O	F THE IB LIGHTENING HOLE HORIZONTALLY TO THE BULKHEAD IB EDGE.  CRACKED AREA IS ADJACENT TO AFT ATTACH POINT FOR THE TIP	 TANK ASSY.  AIRCRAFT HISTORY THIS AREA UNKNOWN; MAY HAVE POSSIBLY BEEN CAUSED BY PREVIOUS GROUND MISHANDLING OR (HANGAR	 RASH) TYPE INCIDENT.  (K)			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005032800032	20050328	00032		2005	3	28	2005FA0000398    	4	20050224	G	3416		ENCODER         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					ALTIMETER	LEAKING         	B			ZV8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	95369					2825901				UNIT HAS INTERNAL LEAK.  LEAK PROBABLE CAUSE DUE TO AGE.  DISCREPENCY FOUND DURING MODE C AND ALTIMETER CORRELATION CHEC	K IAW AC43.6B. (K)					1	L	7	1 	3O	3	O		2A13    	E274				 
2005033000016	20050330	00016	CE  	2005	3	30	2005FA0000399    	1	20050303	G	1430		SCREW           	HONEYWELL   	KS271C      	CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ROLL SERVO	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	434SP				3679	172S8302				ROLL SERVO HAD SCREW COME LOOSE AND MADE CONTACT WITH CIRCUIT BOARD CAUSING SHORT AND BURNING UP COMPONENTS ON BOARD.  R	ECOMMEND TO USE LOCTITE ON SCREWS TO PREVENT SCREWS FROM BACKING OUT OF HOLES. (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005033000008	20050330	00008	WP  	2005	3	30	2005FA0000400    	2	20050303	G	7210	8962321	PLANETARY GEAR  			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	REDUCTION G/B	FAILED          	B			IZ2R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	15	644EM		2905 			1534SA	P36337C	CDA3481MI		ON 2/26-2005 AN UNCOMMANDED, INFLIGHT CONTAINED SHUTDOWN OCCURED ON THE LT ENGINE DUE TO A GEARBOX FAILURE.  THE AIRCRAF	T WAS NOT DAMAGED AND MADE A NORMAL LANDING.  INVESTIGATION IN THE ENGINE GEARBOX REVEALED THAT THE RING GEAR SUPPORT AN	D PLANETARY SPUR GEAR WERE BROKEN. (K)				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2005033000010	20050330	00010	WP  	2005	3	30	2005FA0000401    	2	20050303	G	7210	8967451	RING GEAR       			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	REDUCTION G/B	BROKEN          	B			IZ2R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	15	644EM		2905 		P36337C	1534	P36337C	CDA3481MI		ON 2/26/2005, AN UNCOMMANDED, INFLIGHT CONTAINED SHUTDOWN OCCURED ON THE LT ENGINE DUE TO A GEARBOX FAILURE.  THE AIRCRA	FT WAS NOT DAMAGED AND MADE A NORMAL LANDING.  INVESTIGATION IN THE ENGINE GEARBOX REVEALED THAT THE RING GEAR SUPPORT A	ND PLANETARY SPUR GEAR WERE BROKEN.  (K)				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2005033000018	20050330	00018	CE  	2005	3	30	2005FA0000402    	1	20050209	G	5610	5042006930	WINDSHIELD      			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					COCKPIT	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CE	01	564CA	3905 				BE58				INSIDE LAYER OF CO-PILOT WINDSHIELD CRACKED WHILE IN-FLIGHT AT 25,000 FT.  AIRCRAFT RETURNED.  NO PROBABLE CAUSE OR RECO	MMENDATION CAN BE MADE TO PREVENT REOCCURRENCE.  WINDSHIELD CRACKED FOR NO APPARENT REASON. (K)					1	L	7	2 	4T	3	T		A14CE   	E2WE				 
2005033000009	20050330	00009	EU  	2005	3	30	2005FA0000403    	1	20050311	G	5420	L713M2055102	BRACKET         			UROCOP	EC135 	EC135T1     	5620026	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					NACELLE	CRACKED         	B			A7RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	135TG	262  				0298				EJECTOR COWLING ALIGNMENT BRACKET CRACKED DUE TO VIBRATION. (K)						1	G	7	2 	3U	3	U		H88EU   	E19EU				 
2005033000012	20050330	00012	CE  	2005	3	30	2005FA0000404    	1	20050307	G	7810	1019500223	EXHAUST STACK   			BEECH 	200   	B200        	1152922	CE  										ENGINE	CRACKED         	B			A7RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										CRACK IN BARE METAL DUE TO ENGINE VIBRATION. (K)						1	L	7	2 	4T				A24CE   					 
2005033000013	20050330	00013	SW  	2005	3	30	2005FA0000405    	1	20050311	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L        	1181522	SW  										ENGINE	CRACKED         	B			A7RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										EXHAUST STACK CRACKED IN BASE METAL DUE TO VIBRATION. (K)						1	G	7	1 	3U				H2SW    					 
2005032800033	20050328	00033	EU  	2005	3	28	2005FA0000406    	1	20050311	G	5320	L713M2071105	CHANNEL         			UROCOP	EC135 	EC135P1     	8680990	EU  										FUSELAGE	CRACKED         	B			A7RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		422  								INLET CHANNEL, CRACKED BASE METAL DUE TO VIBRATION. (K)						1	G	7	2 	3U			O	H88EU   					 
2005033000014	20050330	00014	CE  	2005	3	30	2005FA0000407    	1	20050308	G	3213	2342100022	STRUT           			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					NLG	DAMAGED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	247FX					187				DURING 300 HOUR INSPECTION (GEAR SERVICE) THE INNER STRUT CHROME WAS FOUND DAMAGED APPROXIMATELY .001 INCH DEEP.  PROBAB	LE CAUSE: WEAR OF SEALS CAUSING THE UPPER CAM TO CONTACT THE INNER CYLINDER.  INSPECTION REPACK OF THE NOSE LANDING GEAR	 ASSY AT 3,000 LANDING INSPECTION. (EA09200504488) (K)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005033000007	20050330	00007	CE  	2005	3	30	2005FA0000408    	1	20050302	G	3030		RELAY           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	545   	PW545A      	 	NE  					SENSOR HEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	1094L					5605094				DURING POST FLIGHT WALK AROUND, PILOT NOTICED THAT THE ROSEMONT SENSOR HAD ICE ON IT.  UPON OPERATIONAL CHECK, FOUND THA	T THE SENSOR WAS NOT HEATING.  TROUBLESHOOTING THE SYSTEM, FOUND THAT THERE WAS NO POWER TO THE HEATING ELEMENT OF THE P	ROBE.  UPON FURTHER INVESTIGATION, FOUND THAT THE RELAY KC311 PINS- X1 AND X2 WERE PINNED IN REVERSE ORDER.  REPINNED TH	E RELAY AND OPS CHECKED THE SYSTEM, GOOD. (EA09200500318) (K)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005032800034	20050328	00034	CE  	2005	3	28	2005FA0000409    	1	20050211	G	2910		LINE            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					HYDRAULIC SYS	CHAFED          	C				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			SO	05	52668					177RG1241				WHILE INVESTIGATING A GEAR UP LANDING, IT WAS NOTED THAT THE HYDRAULIC LINE FROM THE LANDING GEAR PUMP WAS CHAFING AGAIN	ST THE FLIGHT CONTROL CABLES ROUTED IN THE BATTERY COMPARTMENT AREA.  SUGGEST INSPECTING THIS AREA FOR CHAFING AND RE-RO	UTE HYDRAULIC LINE TO PREVENT CHAFING.  WAS REPLACING INTERIOR PANEL AND MAY HAVE BENT THE LINE INTO THE CABLES. (K)				1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005033000024	20050330	00024	NM  	2005	3	30	2005FA0000410    	1	20050307	G	7603		THROTTLE        			BOEING	757   	757200      	1384950	NM  	RROYCE	RB211 	RB211535*   	 	NE  					NR 1 ENGINE	MISINSTALLED    	B			LLMY	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	35	512TZ					26635	30763			REF: (ATC0515) NR 1 ENGINE THROTTLE TELEFLEX CABLE OUTER SLEEVE RETAINING NUT FOUND TO HAVE COME ADRIFT, ALLOWING THE OU	TER PORTION OF TELEFLEX CABLE TO MOVE.  THE RETAINING NUT, ALTHOUGH DRILLED FOR WIRE LOCKING, THERE IS NO EVIDENCE OF WI	RE LOCKING BEING CARRIED OUT.  AC ENTER THE HANGAR WITH TECH LOG DEFECT OF THROTTLE STAGGER, PLA FAULT AND FLUCTUATING E	PR.  BELIEVE THAT HTIS IS RELATED TO THE ABOVE DEFECT.  IN ADDITION, 4 FAN CASE BOLTS AND NUTS WERE FOUND MISSING FROM T	HE FAN CASE FLANGE BETWEEN 3 OCLOCK AND 10 OCLOCK POSITIONS.  ALL DEFECT RECERTIFICATION HAS BEEN CARRIED OUT AND DOCUME	NTED AT REPAIR STATION UNDER W/O: 5200/2005.  (K)	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005032800118	20050328	00118	SW  	2005	3	28	2005FA0000413    	1	20050111	G	6410	212010750105	BLADE           			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	VIBRATION       	B			VE3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	304FD	936  				36229				ON FIRST GROUND RUN, AFTER APPROX 24 HOURS OF HARD RAIN, THE HELICOPTER DEVELOPED A SEVERE VIBRATION.  THE VIBRATION WAS	 TRACED TO A TAIL ROTOR BLADE.  SUSPECT BLADE COLLECTED THE RAIN WATER.  THE BLADE WAS SCRAPPED IAW THE MM.  (K)					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2005040400019	20050404	00019	CE  	2005	4	4	2005FA0000414    	1	20050308	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DYNAMIC BRAKE	FAILED          	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			WP	07	1570A					CE1333	830089R			PILOT SELECTED GEAR DOWN AND NOTHING HAPPENED.  LANDING GEAR WOULD NOT EXTEND.  FLIGHT CREW EXTENDED LANDING GEAR MANUAL	LY AND LANDED WITHOUT INCIDENT.  MAINTENANCE TECH TROUBLESHOT GEAR SYSTEM AND FOUND THAT THE DYNAMIC BRAKE RELAY WAS INT	ERMITTENT.  PROBABLE CAUSE WAS DUE TO INTERNAL FAILURE WITH RELAY.  TO PREVENT RECURRENCE IS INSTALL A NEWER MFG DATE RE	LAY WHICH IS AN IMPROVED UNIT IAW MFG. (K)			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005033000028	20050330	00028	CE  	2005	3	30	2005FA0000415    	1	20050311	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					BRAKES	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8240T	3    				CE1542	825916R			DURING GEAR RETRACTION, GEAR WAS VERY SLOW TO EXTEND.  TROUBLESHOOTING SYSTEM FOUND DYNAMIC RELAY WAS LOOSING 12 VOLTS A	CROSS DOWN RELAY SIDE.  PROBABLE CAUSE AT THIS TIME IS UNKNOWN RETURNED TO MFG FOR ANALYSIS.  NO RECOMMENDATION AT THIS 	TIME. (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005033000047	20050330	00047	CE  	2005	3	30	2005FA0000416    	1	20050310	G	7430	A5109	IGNITION SWITCH 			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					COCKPIT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	106AF	3488 				17281055				DURNG ENGINE RUNUP MAGNETO CHECK, IGNITION SWITCH WILL NOT CAUSE RPM TO DROP WHEN KEY IS TURNED TO LT POSITION.  WHEN KE	Y IS IN LT POSITION, SLIGHT SIDE TO SIDE MOVEMENT OF KEY WILL CAUSE RPM DROP.  UPON OPENING SWITCH, FOUND WORN AND ARCHI	NG CONTACTS.  THE ABOVE MALFUNCTION SEEMS TO OCCUR DUE TO WORN CONTACTS ON SWITCH INTERIOR.  DURING RUNUP, FOLLOW MFG CH	ECKLIST FOR MAGNETO CHECK.  IF ABOVE DEFECT IS FOUND, RECOMMENDATION WOULD BE TO TROUBLESHOOT SYSTEM, VERYIFYING THAT TH	E SIDE TO SIDE MOVEMENT OF KEY ALLOWS NORMAL SWITCH OPERATION, UPON DETERMINATION REPLACE OR OVERHAUL IGNITION SWITCH. (	K)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005033000038	20050330	00038	NM  	2005	3	30	2005FA0000417    	1	20050309	G	3340	300909201	LIGHT           			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					TAILCONE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	90R	893  				32775				WHILE CLEANING LENS, IT APPEARED TO BE LOOSE IN THE HOUSING.  A VERY GENTLE PULL RELEASED THE LENS FROM ITS HOUSING.  TH	E LENS IS THICK GLASS THAT COULD BE A RUNWAY HAZARD IF IT FELL FROM THE AC AND BROKE.  PROBABLE CAUSE IS SKYDROL WHICH L	EAKED FROM RUDDER PCU AND COMPROMISED THE ADHESIVE FEATURES OF THE SEALANT ATTACHING THE LENS TO THE HOUSING ASSEMBLY.  	RECOMMEND INSPECTION OF AC THAT HAVE HAD RUDDER PCU SKYDROL LEAKAGE PROBLEMS.  SOME TYPE OF MECHANICAL ATTACHMENT OF LEN	S TO THE HOUSING SHOULD BE CONSIDERED.  (K)		2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005033000034	20050330	00034	WP  	2005	3	30	2005FA0000418    	1	20050107	G	6510	269A5498005	SHAFT           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360*     	41514	EA  					DRIVE SPLINES	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	269TJ	414  				S1807				DURING ANNUAL INSPECTION GREASE IN LOWER PULLEY SHAFT HAD A RUSTY (BROWN) COLOR (NOTE: ANDEROL GREASE IS BLACK).  UPON I	NSPECTION PART HAS 414.2 HOURS SINCE NEW, THE SPLINES WERE WORN BEYOND LIMITS.  SPECULATION OF MFG AND OUR FACILITY IS T	HAT THE GREASE WAS CONTAMINATED.  (K)				1	G	7	1 	3O	3	O		4H12    	1E10				 
2005033000022	20050330	00022	SW  	2005	3	30	2005FA0000419    	1	20050107	G	6510	269A5559003	DRIVE SHAFT     			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					TAIL ROTOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	72LP	600  				0152				DURING 600 HOUR INSPECTION GREASE IN DRIVE SHAFT HAD A RUSTY (BROWN) COLOR (NOTE: ANDEROL GREASE IS BLACK).  UPON INSPEC	TION PART HAS 600.0 HOURS SINCE NEW.  LIFE LIMIT OF 6000 HRS, THE SPLINES WERE WORN TO THE THICKNESS OF A PIECE OF PAPER	 (APPROX .090 NEW).  SPECULATION OF MFG AND OUR FACILITY IS THAT THE GREASE WAS CONTAMINATED.  FIRST 600 HOUR INSPECTION	 ON THIS AC, SAME GREASE SINCE DELIVERY. (K)			1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2005032800049	20050328	00049	SW  	2005	3	28	2005FA0000420    	1	20050107	G	6320	269A5498005	SHAFT           			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					DRIVE SPLINES	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	72LP	600  				0152				DURING 600 HOUR INSPECTION GREASE IN LOWER PULLEY SHAFT HAD A RUSTY (BROWN) COLOR (NOTE: ANDEROL GREASE IS BLACK).  UPON	 INSPECTION PART HAS 600.0 HOURS SINCE NEW, THE SPLINES SHOWED IRREGULAR WEAR.  SPECULATION OF MFG AND OUR FACILITY IS T	HAT THE GREASE WAS CONTAMINATED.  FIRST 600 HOUR  INSPECTION ON THIS AC, SAME GREASE SINCE DELIVERY FROM MFG. (K)				1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2005040100106	20050401	00106	WP  	2005	4	1	2005FA0000421    	2	20050125	G	7200	TFE73122B	ENGINE          			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RIGHT	FAILED          	B			BHKR	E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			EA	21	96FN	11671	759  			186	P74780			WHILE AT FL300, EXPERIENCED AN INFLIGHT FAILURE OF THE RT ENGINE AS FOLLOWS, RT ENGINE INSTRUMENTS, ITT, N1, N2 AND FUEL	 FLOW ALL BEGAN INCREASING.  RT FUEL COMPUTER WAS TURNED OFF, POWER WAS REDUCED TO IDLE.  THE ENGINE INSTRUMENTS CONTINU	ED TO INCREASE AND JUST PRIOR TO ENGINE SHUTDOWN, A LOUD BANG WAS HEARD FROM THE RT SIDE, FOLLOWED BY A BRIGHT FLASH AND	 SMELL OF SMOKE IN THE COCKPIT.  AC LANDED SAFELY WITHOUT FURTHER INCIDENT.  ENGINE WAS REMOVED FROM AIRCRAFT AND SENT T	O AN OVERHAUL FACILITY DETAILS OF THE ENGINE DISASSEMBLY FINDINGS ARE CONTAINED IN REPORT NR GR2-703 ATTACHED.  IT WAS R	ECOMMENDED THAT HP TURBINE BE FWD FOR FURTHER INSPECTION TO DETERMINE MODE FAILURE. (K)	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005042700129	20050427	00129	EA  	2005	4	27	2005FA0000425    	2	20050214	G	8520	SL3601SC	PISTON RING     			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	4238F					287715010	L848939A			OUT OF CONCERN FROM HAVING 2 PREVIOUS OIL RING FAILURES THAT COULD HAVE BROUGHT ME DOWN.  PULLED CYLINDER NR 1 AND NR 2 	TO REPLACE RING WITH SAME PRODUCTION DATE AS ONE THAT FAILED.  PULLING AND INSPECTING NR 1, FOUND THE RING GAP TO BE EXC	ESSIVE, MFG CALLS FOR .0015 TO .0030. , SEEMS LIKE A LOT OF WEAR IN TOO SHORT OF PERIOD.  HAD RINGS FROM CYLINDERS NR 1,	 2, 4 SENT TO REPAIR STATION TO CHECK FOR HARDNESS OF RINGS.  RING NR 1 CYLINDER WAS 1.5 ON C SCALE ROCKWELL MACHINE, NR	2 WAS A 2.0 ON SAME SCALE.  CYL NR 4 (RING IN 3 PIECES) LARGE PART OF RING WAS BETWEEN 1.5 AND 2,  2ND PIECE WAS A 5.5, 	3RD PIECE WAS 3.5.  MAN DATE 10-1-2002.  SENT MFG BAD RINGS, SENT NEW RINGS AND OLD RINGS BACK WITH COMMENT. (K)	1	L	7	1 	3O	3	O		2A13    	E274				 
2005032800036	20050328	00036	SO  	2005	3	28	2005FA0000427    	2	20050318	G	8530	AEC631397	CYLINDER HEAD   			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	SEPARATED       	G				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	27	96HC	475  	475  			45285				DURING TAKEOFF PILOT NOTICED A SHUDDER OR VIBRATION. UPON LANDING ENGINE BEGAN TO RUN ROUGH.  MAINTENANCE FOUND LT ENGIN	E NR 6 CYLINDER HEAD HAD SEPARATED.  ENGINE WAS OVERHAULED ON 4-23-2004 AND PUT IN SERVICE ON 5-18-2004. THE ENGINE HAD 	475 HOURS SINCE OVERHAUL.  THE CYLINDER WAS A NEW, INSTALLED AT OVERHAUL.				1	L	7	2 	3O	3	O		3A10    	E8CE				 
2005032800058	20050328	00058	SO  	2005	3	28	2005FA0000428    	1	20050322	G	5712	78475009	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	706ER	2592 				2844060	L715451A			DURING A VISUAL INSPECTION, A SMALL CRACK WAS FOUND IN THE RT NOSE RIB P/N-62021-005 AND -004. A MORE THOROUGH INSPECTIO	N REVEALED THAT AN ADDITIONAL CRACK, MUCH LARGER (ABOUT4 INCHES LONG), WAS FOUND ON THE RIB P/N-78475-009 AND -008. THES	E RIBS ARE INCLUDED IN THE MOUNTING ASSEMBLY FOR THE P/N-95643-007 AND -006 AND BRACKET(MAIN GEAR TRUSS). THE OPERATOR O	F THIS AIRCRAFT OPERATES A FLEET OF 6 OF THESE AIRCRAFT, AND ALL THE OTHER AIRCRAFT HAD SIMILAR CRACKS, ON BOTH LT AND R	T WINGS. THE FLEET IS GROUNDED AND THE AFFECTED PARTS ARE BEING REPLACED.		1	L	7	1 	3O	3	O		2A13    	1E10				 
2005032800071	20050328	00071	CE  	2005	3	28	2005FA0000429    	1	20050318	G	3230	504501024	TORQUE TUBE     			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	414RD	4723 				4140502				RT TORQUE TUBES CRACKED DURING GEAR RETRACTION.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2005032800073	20050328	00073	CE  	2005	3	28	2005FA0000430    	1	20050318	G	3230	504501025	TORQUE TUBE     			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	414RD	4723 				4140502				LANDING GEAR TORQUE TUBES ARE CRACKED.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2005040100048	20050401	00048	GL  	2005	4	1	2005FA0000431    	3	20050325	G	6110	A249910	SLEEVE          	HARTZL      												HARTZL	HCE2Y	HCE2YL2     	GL  	PISTON ROD	INCORRECT       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01		120  			A5639B			A5639B		PROPELLER WAS REPAIRED AND O/H IN MY SHOP.  PROP HAD A2499-10 HIGH PITCH STOP SLEEVE INSTALLED BUT APPARENTLY ASSEMBLER 	DID NOT KNOW IT TAKES A 2499-9.   WHEN ASSEMBLED TO GET BLADE ANGLES CORRECT, ALTERED -10 TO A -9 IAW PRINT A2499.  TT O	N PROP 120 HRS SINCE NEW. (K)														5	C	P9EA	 
2005042700134	20050427	00134	GL  	2005	4	27	2005FA0000432    	3	20050325	G	6114	A24182	PISTON ROD      			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	PROP HUB	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	39775					32R7887166		FM1248B		NEW PROP WAS INSTALLED.  ENGINE DEVELOPED METAL.  PROP WAS BROUGHT TO SHOP TO BE FLUSHED OUT.  AFTER CYL REMOVAL, PITCH 	CHANGE TUBE (PISTON ROD) WAS FOUND TO BE TORQUED AT 75 FT LBS INSTEAD OF 40 FT LBS.  PROP WAS DISASSEMBLED AND REASSEMBL	ED TO MAKE SURE FORK WAS NOT UPSIDE DOWN. (K)				1	L	7	1 	3O	3	O		A3SO    	E14EA	5	C	P33EA	 
2005040100058	20050401	00058	GL  	2005	4	1	2005FA0000433    	3	20050325	G	6110		TUBE            													HARTZL	HCC2Y	HCC2YK1     	GL  	PISTON PILOT	MISREPAIRED     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01								CH37962B		PISTON PILOT TUBE, PAPER TOWEL INSTALLED INSIDE OF TUBE, BLOCKED OIL.   PROP HAD / HOUR TIME ON IT.																5	C	P920	 
2005042700133	20050427	00133		2005	4	27	2005FA0000443    	4	20050325	G	3420	2300626020	MOTOR           	COLLINS     	ADI85A      															INDICATOR	INTERMITTENT    	B			JGVR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CE	09					1536					THE MOTORS HAVE HIGH RESISTANCE BETWEEN THE BRUSHES AND ARMATURE OF THE MOTOR. THIS CAUSES THE MOTOR TO STICK INTERMITTE	NTLY, CAUSING A FALSE ATTITUDE DISPLAY IN THE COCKPIT.  CREW REPORTED ON CLIMB OUT, THE ADI DISPLAYED AN ATTITUDE FLAG. 	 PITCH AXIS DID NOT RESPOND TO THE ATTITUDE CHANGE.																	 
2005040400013	20050404	00013		2005	4	4	2005FA0000445    	4	20050307	G	2562	ELT10	RACK            			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ELT	DISLODGED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8310H	149  				328306009	L2276448A	DY1697		DURING ANNUAL INSPECTION, FOUND ELT LAYING ON THE CONTROL CABLES IN AFT FUSELAGE.  LATCH AHD FAILED ON ELT RACK.  (EA212	00505230) (K)					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P25EA	 
2005040400043	20050404	00043	CE  	2005	4	4	2005FA0000446    	1	20050304	G	5343	460337	BRACKET         			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					ACTUATOR	BROKEN          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	484CW					RK334				FLIGHT CREW REPORTED LANDING GEAR UNSAFE LIGHT REMAINED ILLUMINATED AFTER LANDING GEAR RETRACTION FOLLOWING DEPARTURE.  	CREW ELECTED TO RETURN TO AIRPORT.  OBTAINED DOWN AND LOCKED INDICATION ON ALL 3 LANDING GEAR AND LANDED UNEVENTFULLY.  	UPON JACKING AC FOR INVESTIGATION NOTED LT MAIN GEAR ACTUATOR ATTACH BRACKET BROKEN AND DISTORTED AT LT MAIN GEAR ACTUAT	OR ATTACH POINT.  ACTUATOR ATTACH HARDWARE STILL SECURE AND SAFTIED IN BROKEN PORTION.  THIS SN AC WAS NOTED AS BEING AF	FECTED BY MFG.  CUSTOMER SL BJ-CSL-1004R1 ISSUED 11/01/2002.  BJ-CSL-1004R1 REQUIRED REPLACEMENT OF ALL PN 46033-7, LT M	AIN GEAR ACTUATOR BRACKETS ON AFFECTED AC DUE TO INCORRECT HEAT TREATMENT AND CHAMFERING.	2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2005040400107	20050404	00107	NM  	2005	4	4	2005FA0000447    	1	20050315	G	2760	65695223	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										ACTUATOR	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					229					CRACKED BY EXTEND PORT.  FATIGUE, UTILIZE IMPROVED STEEL HOUSING.   (MECHANIC ECI, JOB NR 193967) (K)						2	L	7	2 	4F			RT	A16WE   					 
2005042700143	20050427	00143	NM  	2005	4	27	2005FA0000448    	1	20050315	G	2913	65447821	HOUSING         			BOEING	737   	737*        	       	NM  										HYD PUMP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		61514			1215					HYD PUMP HOUSING IS CRACKED BEHIND PORT (1), FATIGUE.  REDESIGN COVER. (MECHANIC FXS, JOB NR 193727) (K)						2	L	7	2 	4F			RT	A16WE   					 
2005042700144	20050427	00144	NM  	2005	4	27	2005FA0000450    	1	20050301	G	3233	69B802071	HOUSING         	BOEING      		BOEING	747   	747*        	       	NM  										ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					SHL793					ACTUATOR HOUSING CRACKED AT THE BASE, FATIGUE OR OVERPRESSURE.  REDESIGN HOUSING.  (MECHANIC FXS, JOB NR 192820) (K)						2	L	7	4 	4F			RT	A20WE   					 
2005041900042	20050419	00042	SO  	2005	4	19	2005FA0000451    	1	20050328	G	5712	78475007	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SO	15	931ER	2186 				4496155				SINCE FLEET OF SIX PIPER ARROWS WERE ALL FOUND TO HAVE CRACKED RIBS IN THE SAME LOCATION, FOUND DURING ROUTINE INSPECTIO	N.  SDRS WERE SENT.  DETERMINED TO INSPECT FLEET OF TEN SEMINOLES.  THE BASIC WING STRUCTURE IS DESIGNED THE SAME.  FOUN	D SIMILAR CRACKS IN SEVEN OF THE SEMINOLES.  THE CRACKS ARE FOUND IN THE RIB, ADJACENT TO THE FORWARD TRUNNION PLATE (WH	ICH MUST BE REMOVED TO PROPERLY SEE THE CRACK).  IN THIS PARTICULAR AIRCRAFT THE RIB, P/N 78475-007, LOCATED AT AFT STAT	ION 49.25 ON THE RIGHT SIDE, WAS CRACKED.  THE LEFT RIB, CRACKED IN OTHER SEMINOLES IS P/N 78475-006 AND LOCATED AT AFT 	STATION 49.25.	1	L	7	2 	3O				A19S0   					 
2005040400014	20050404	00014	CE  	2005	4	4	2005FA0000452    	1	20050317	G	2822	A10055B	PUMP            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					FUEL BOOST	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	02	65556	53   				T20608496				BOOST PUMP WAS LEAKING AT SEAM BETWEEN ELECTRIC MOTOR AND VANE PUMP.  FUEL HAD A CHANCE TO LEAK INTO ELECTRIC MOTOR BRUS	HES.  BELIEVE THIS TO A  MAJOR FIRE HAZZARD.  BOTH PUMP AND AIRCRAFT WERE NEW.  THIS COULD HAVE BEEN PREVENTED BY BETTER	 QUALITY CONTROL AT THE FACTORY. (K)				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2005042700289	20050427	00289	NE  	2005	4	27	2005FA0000453    	2	20050314	G	8520	126211	CRANKSHAFT      								PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	CRACKED         	B			CP2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15			1200 				P326980			DURING THE OVERHAUL PROCESS, THE FLYWEIGHT LINERS WERE REMOVED AND THE REAR HALF OF THE CRANKSHAFT WAS MAGNETIC PARTICLE	 INSPECTED.  DURING THIS INSPECTION IT WAS DISCOVERED THAT A CRACK HAD DEVELOPED FROM AN ASSEMBLY RIVET HOLE OUT TO THE 	LINER BORE ON THE COUNTER WEIGHT ARM.  UNKNOWN CAUSE.  LINERS SHOULD BE REMOVED AT EACH OVERHAUL AND INSPECTED FOR CRACK	S IN THIS AREA. (K)								3	R			5E2				 
2005040400023	20050404	00023	CE  	2005	4	4	2005FA0000454    	1	20050215	G	5343	24130023	FITTING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					ACTUATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	6400V					172RG0662	RL1993936A			DURING EMERGENCY LANDING GEAR OPERATIONAL CHECK, THE MECHANIC FOUND THE CRACK ON BOTH SIDE CORNER OF THE FITTING NOSE GE	AR ACTUATOR ATTACHING PART.  IT MAY BE SUSPECTED THAT MATERIAL FATIGUE OR AN UNREPORTED LANDING. (K)					1	H	7	1 	3O	3	O		3A17    	E286				 
2005040100004	20050401	00004	GL  	2005	4	1	2005FA0000455    	3	20050304	G	6114	D22013	HUB             													HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								CH14728		(2 EA) CRACKS WERE FOUND USING FLOURESCENT PENETRANT,  INSIDE ENGINE SIDE HUB HALF.  BOTH CRACKS WERE VERIFIED WITH EDDY	 CURRENT.  CRACKS COUL HAVE BEEN CAUSE FROM A PAST GROUND STRIKE (HARD LANDING). (K)															5	C	P920	 
2005040400024	20050404	00024	NE  	2005	4	4	2005FA0000456    	2	20050310	G	7250	30600501	TURBINE         			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					NR 3 ENGINE	FAILED          	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			NM	01	26WP	1754 				312				ENGINE SHUT DOWN AT FL360, ON DEPARTURE.  FLIGHT CREW AND PASSENGERS HEARD LOUD BANG AND FELT VIBRATION.  FLIGHT CREW OB	SERVED NR 3 ENGINE N1 SPOOLDOWN AND 25 DEGREE HIGHER THAN NORMAL ITT, ENGINE OIL PRESSURE WAS NORMAL.  ENGINE WAS SHUT D	OWN AND FLIGHT RETURNED TO DEPARTURE.  POSTFLIGHT INSP OF NR3 ENGINE REVEALED DEBRIS IN EXHAUST DUCT.  NO VISIBLE DAMAGE	 TO THE LOW PRESSURE TURBINE.  AFT OF FAN OR COMPRESSOR AREA, FWD.  SUSPECT COMPONENT FAILURE FWD OF LOW PRESSURE TURBIN	E. ENGINE REMOVED FOR REPAIR, SHIPPED TO MFG.  PENDING INSP TEARDOWN REPORT FROM MFG.  NOT CERTAIN WHAT COMPOENT IN ENGI	NE FAILED. (K)	2	L	7	3 	4F	4	F		A46EU   	E1NM				 
2005040100037	20050401	00037	EU  	2005	4	1	2005FA0000458    	1	20050318	G	7810	1379049H403	EXHAUST STACK   			BAG   	JETSTM	JETSTM3201  	1500217	EU  										ENGINE	CRACKED         	B			A7RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										CRACK IN FLANGE DUE TO ENGINE VIBRATION. (K)						2	L	7	2 	4T			RT	A56EU   					 
2005040100006	20050401	00006	EA  	2005	4	1	2005FA0000459    	2	20050321	G	7414	BL68256013	MAGNETO         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	INOPERATIVE     	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	03	32SJ					32R8429016				AIRCRAFT ARRIVED AT HANGAR WITH ROUGH RUNNING ENGINE.  FOUND DUEL MAG DEAD AND ON SIDE.  REMOVED MAG FROM ENGINE.  FOUND	 TEETH MISSING ON MAG GEAR.  WAS TOLD BY OWNER THAT MAG WAS NOT THAT OLD.					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2005040100008	20050401	00008	EA  	2005	4	1	2005FA0000461    	2	20050318	G	7322	62F1	STOP PIN        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					THROTTLE BODY	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146T		224  		G508088	2843168	L3625536A			STUDENT PILOT REPORTED THROTTLE WOULD NOT ADVANCE BEYOND IDLE.  FOUND CARBURETOR BINDKING INTERNALLY.  DISASSEMBLED CARB	URETOR AND FOUND AIR METERING PIN STOP PIN WORN WHICH ALLOWED AIR METERING PIN TO EXTEND BEYOND NORMAL RANGE AND JAM BET	WEEN STOP PIN AND ACTUATING ARM ON PUMP LEVER ASSEMBLY.  (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
2005040100065	20050401	00065	EU  	2005	4	1	2005FA0000462    	1	20050316	G	3246	GYS18525	BOLT            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG WHEEL	BROKEN          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	655PE				AR75349	199				A BROKEN BOLT WAS NOTICED DURING A TIRE PRESSURE CHECK.  THE WHEEL COVER WAS REMOVED TO INVESTIGATE.  ALL TEN BOLTS WERE	 NDT`D BY PAG PARTICLE INSP AND 3 OTHER BOLTS WERE FOUND CRACKED.  PART CYCLES (LANDINGS) SINCE O/H IS 176 CSO. (K)					2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005040100089	20050401	00089	CE  	2005	4	1	2005FA0000463    	1	20050211	G	8120			GARRTT      		BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  			B			CGHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	30MM				YH023923	P507	L156259	DA1311		WHILE INVESTIGATING OIL LEAK FROM TURBO, FOUND IMPELLER/TURBINE SHAFT HOLD DOWN NUT LOOSE ALLOWING SHAFT TO MOVE LATERAL	LY.  THIS CAUSED SHAFT TO BECOME UNSEATED AT BEARING SEALS.  DISCREPANCY WAS DISCOVERED EARLY ENOUGH TO KEEP IMPELLER AN	D TURBINE WHEELS FROM BEING DAMAGED.  NOTE: TURBO WAS REPAIRED 1.9 HRS EARLIER.  TURBO WAS REPAIRED AND INSTALLED. (K)				1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
2005040100066	20050401	00066	CE  	2005	4	1	2005FA0000464    	1	20050317	G	8011	643259	ADAPTER         			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					STARTER	DEFECTIVE       	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	722SJ					U20603361	830285R			STARTER ADAPTER WAS REMOVED DUE TO DAMAGE CAUSED DURING A (KICK-BACK).  INSPECTION FOUND BEARING RETAINING HOLES THAT HA	D BEEN KNURLED AT THE FACTORY, MISALIGNED, AND COATED WITH A GREENISH BEARING RETAINING COMPOUND.  THE STARTER ADAPTER W	ORM DRIVE SHAFT SHOWED SIGNS OF A HEAVY SIDE LOAD.  THIS CAUSED THE STARTER ADAPTER TO BIND AND NOT RELEASE.  THIS HOUSI	NG HAS AN INSPECTION STAMP OF (TA33) AND A DATE STAMP OF (SEPT 15 2003). (K)			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005040100064	20050401	00064	CE  	2005	4	1	2005FA0000465    	1	20050225	G	3610	AA3216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DRY AIR	DAMAGED         	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	5544A					CE1343				DURING FLIGHT, FLIGHT CREW NOTICED THAT AIR PRESSURE WAS READING ZERO.  LANDED AIRCRAFT AND MAINTENANCE INSPECTED AND FO	UND THE ENGINE DRIVEN DRY AIR PUMP SHAFT WAS SHEARED.  PROBABLE CAUSE IS UNKNOWN. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005050200076	20050502	00076		2005	5	2	2005FA0000467    	4	20050407	G	3421		FITTING         			CESSNA	172   	172S        	2072439	CE  										ATTITUDE GYRO	LOOSE           	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	286SP					172S8238				AIRCRAFT, RELATIVELY NEW PROBLEM BELOW APPEARS TO BE FROM FACTORY INSTALLATION.   VACUUM FITTING ON ATTITUDE GYRO LOOSE.	  THE (90 DEGREE) VACUUM FITTING IN ORDER TO ACCEPT THE VACUUM HOSE FROM RT DIRECTION, WAS NOT PROPERLY SEATED (PIPE THR	EAD SYSTEM) SO THAT THE VACUUM TO THE INSTRUMENT WAS REDUCED CAUSING LOW GYRO SPEED AND THUS IMPROPER OPERATION.  TURBUL	ENCE/HOSE MOVEMENT CAUSED SOME THREAD SEATING AT TIMES TO PRODUCE A USEABLE GYRO, THUS OPERATION WAS ERRATIC.  (K)			1	H	7	1 	3O			NT	3A12    					 
2005050300230	20050503	00230	CE  	2005	5	3	2005FA0000468    	1	20050322	G	3610	3909740080005	TUNING UNIT     			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ44        	66000	GL  					FLOW CONTROL	BROKEN          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	972PF	582  				RB38				DURING REPLACEMENT OF LT BI-FLOW CONTROL VALVE IN CONJUNCTION WITH A SCHEDULED INSPECTION, FOUND PNEUMATIC TUBE IN LT PY	LON AREA BENT AND CRACKED IN HALF.  SUSPECT MAY BE CAUSED DUE TO PREVIOUS ROUGH HANDLING OR FORCING TUBING DURING BI-FLO	W VALVE REPLACEMENT OR RELATED MAINTENANCE IN AREA.  RECOMMENDED A MAINTENANCE PRECAUTION BE ADDED TO SEC 21-20-06-401 I	N THE 390 MM ADVISING TECH TO HANDLE PNEUMATIC LINES IN THIS AREA WITH CAUTION.  (K)			1	7		2 	3F	4	F	RT	A00010WI	E3GL				 
2005050300244	20050503	00244	SO  	2005	5	3	2005FA0000469    	1	20050222	G	3220	40336000	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG	CRACKED         	D			KU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	38SL	3850 				318152167				NLG LINK HAS A CRACKED IAW SL1088. (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005050300245	20050503	00245	NM  	2005	5	3	2005FA0000472    	1	20050304	G	2597	FGFB641103A3	WIRE HARNESS    			AMD   	FALC50	FALCON2000  	2730170	NM  										COPILOT SEAT	SHORTED         	B			CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	790L	6108 				15				FRACTURED WIRE HARNESS UNDER COPILOT SEAT ARCED AND SHORTED, SPARKS AND COPPER GLOBULES.  POSSIBLE FIRE HAZARD IF PAPERS	, ETC. UNDER SEAT.  CIRCUIT BREAKER WAS SLOW TO RE-ACT.  HARNESS NEEDS TO BE MORE RUGGED WITH ATTENTION TO ROUTING AND C	LAMPING. (K)				2	K	7	3 	4F			RT	A50NM   					 
2005050300247	20050503	00247	CE  	2005	5	3	2005FA0000473    	1	20050308	G	3240	3052N	CALIPER         			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					LT BRAKE	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	51824	385  				T20608390				NOTICED LT BRAKE LEAKING FLUID ON IB SIDE OF CALIPER.  CLEANED, INSPECTED, COULDN`T FIND LEAK.  REMOVED CALIPER BENCH TE	STED WITH HYD POWER SUPPLY, FOUND CALIPER TO BE LEAKING THROUGH PIN HOLES IN HOUSING IN 3 PLACES.  (EA23200505995)					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2005050300248	20050503	00248	SO  	2005	5	3	2005FA0000474    	1	20050316	G	7120	102403053	SHIELD          			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					RT ENG MOUNT	CHAFED          	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	5335R	474  				4697100				DURING NORMAL EVENT INSPECTION, IT WAS FOUND THAT THE AIR SHIELD WAS CHAFFING AGAINST THE UPPER RT ENGINE MOUNT LEG WHER	E IT PASSES THROUGH THE BAFFLE SHIELD FOR THE PLENUM ASSY.  RECOMMENDED THAT CLOSE INSPECTION BE GIVEN TO AREA WHERE BAF	FLING COULD BE CUTTING INTO THE ENGINE MOUNT.  BOTH TIMES THIS WAS FOUND, ENGINE MOUNTS HAD TO BE REPAIRED BY APPROVED W	ELDING METHODS BY AUTHORIZED REPAIRED FACILITIES.  (K)			1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2005050300251	20050503	00251	SW  	2005	5	3	2005FA0000475    	1	20050306	G	6300	269A54301	SPLINE          			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360*      	41514	EA  					MAIN ROTOR BELT	STRIPPED        	D				A	B			UNSCHED LANDING         	EMER. DESCENT           			F			FLT CONT AFFECTED         			CR	CRUISE         	1			SO	15	72LP	1138 				0152				WHILE IN CRUISE FLIGHT, TAIL ROTOR FAILURE AT APPROX 700 FT, PILOT WENT TO FLAT PITCH, PUT HELICOPTER IN A DIVE TO AVOID	 ROTATION FROM TORQUE, PERFORMED FULL AUTOROTATION TO THE GROUND, NO DAMAGE TO HELICOPTER OR INJURIES TO OCCUPANTS.  DRI	VE GEAR ON TAIL ROTOR INPUT SHAFT STRIPPED AS WELL AS FWD GEAR ON TAIL ROTOR DRIVE SHAFT.  SUSPECT POSSIBEL METAL PROBLE	M.  CURRENT INSPECTION IS 600 AND 1200 HOURS OR 24 MONTHS, POSSIBLY LOWERING INSPECTION INTERVALS TO SAY 300 HOURS.  HEL	ICOPTER WAS 30 HOURS FROM 1200 HR.  (K)		1	G	7	1 	3O	3	O	O	4H12    	E286				 
2005050300261	20050503	00261	CE  	2005	5	3	2005FA0000478    	1	20050110	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				INSTALLED NEWLY OVERHAULED NLG ACTUATOR AND FOUND TO HAVE EXCESSIVE IN LINE MOVEMENT OF TNE LOCKING MECHANISM.  MOVEMENT	 IN EXCESS OF .1250, MAX ALLOWED .035.  (K)					1	L	7	2 	4F	4	T		A22CE   	E1NE				 
2005050400093	20050504	00093	NM  	2005	5	4	2005FA0000479    	1	20050325	G	5340	144490	MOUNT           			BOEING	747   	747*        	       	NM  										VALVE	FAILED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										VALVE SEPARATED FROM MODULE UPON 45 PSI PROOF PRESSURE TEST.  MOUNTING LUGS FAILED AND BROKE OFF, BLOWING THE VALVE OFF 	THE UNIT.  FATIGUE AND INSUFFICIENT MATERIAL ON MOUNT LUGS TO HANDLE PROOF PRESSURE.  LOWER PROOF PRESSURE TEST OR REDES	IGN MOUNTING LUGS TO WITHHOLD THE PRESSURE.  (MECHANIC WC, JOB NR 194178) (K)				2	L	7	4 	4F			RT	A20WE   					 
2005050500001	20050505	00001	NM  	2005	5	5	2005FA0000480    	1	20050325	G	2913	65447821	HOUSING         			BOEING	737   	737*        	       	NM  										HYD PUMP	ERODED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING HAS A PIN HOLE LEAK ON THE BACKSIDE OF PORT 2, EROSION.  REDESIGN HOUSING. (K)						2	L	7	2 	4F			RT	A16WE   					 
2005050500002	20050505	00002	NM  	2005	5	5	2005FA0000481    	1	20050329	G	3240	511531	HOUSING         			BOEING	737   	737*        	       	NM  										VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										CRACKED AT PLUG PORT.  FATIGUE.  (MECHANIC NH2, JOB NR 194399) (K)						2	L	7	2 	4F			RT	A16WE   					 
2005050500003	20050505	00003	NM  	2005	5	5	2005FA0000482    	1	20050329	G	2710	654484511	MANIFOLD        			BOEING	737   	737*        	       	NM  										FILTER BOWL	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					5236A					FILTER BOWL MOUNTING PORT IS BROKEN OFF AT THE BASE OF THREADS.  FATIGUE.  (MECHANIC LEB, JOB NR 194521) (K)						2	L	7	2 	4F			RT	A16WE   					 
2005041400103	20050414	00103	NM  	2005	4	14	2005FA0000483    	1	20050119	G	5740		ATTACH BRACKET  			CHRIS 	HUSKY 	A1          	221020X	NM  										LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	6RX					1053				DURING A ROUTINE ANNUAL INSPECTION DISCOVERED THE LEFT LOWER WING REAR SPAR ATTACHMENT AFT FITTING CRACKED.  THIS INSPEC	TION IS REQUIRED EA 50 HOURS BY AD 96-12-03R2 AND MANUFACTURES SERVICE BULLETIN 25.  SERVICE BULLETIN 25 INDICATES THE R	EPAIR PROCEDURE FOR PITTS S2 & S1 SERIES AIRCRAFT.  THIS SERVICE BULLETIN AND THE REPAIR PROCEDURES WILL NOT WORK ON THE	 S1 AIRCRAFT.  THE PARTS INDICATED IN SERVICE BULLETIN 25 WILL NOT WORK ON THE S1 AIRCRAFT.  CONTACTED AVIAT AIRCRAFT, T	HAT HAVE NOT BEEN RESPONSIVE TO THE PROBLEM, NEED APPROVED REPAIR PROCEDURE FOR THIS PROBLEM.PHONE 740.494.2554		1	H	7	1 	3O			NC	A22NM   					 
2005041400113	20050414	00113	SO  	2005	4	14	2005FA0000484    	2	20050130	G	8520	SA631991REVC	SHAFT           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					ENGINE	OUT OF ROUND    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	123AP					347770015	303972			UPON INSTALLING A SHAFT INTO A ROCKER WITH INADEQUATE TOLERANCE LIMITS, NOTED BINDING IN 3 O`CLOCK POSITIONS. WITH PRUSS	ION BLUE FOUND SHAFT IS FORMED IN ELIPTICAL OR, MODIFIED TRIANGULAR SHAPE WITH REDUCED WEAR SURFACE AREA DUE TO INCONSIS	TANT DIA OF SHAFT.  ALL 24 NEW SHAFTS DISPLAYED SAME MACHINING RESULTS.  HIGHEST PRESSURE POINT WAS NARROWEST CONTACT PO	INT.  GALLING OF THESE SHAFTS APPEARS TO BE CONSISTANT WITH REDUCED WEAR SURFACE & CROWNING OF SHAFT.  WHILE OTHER FACTO	RS MAY BE ATTRIBUTED TO CAUSE OF PREMATURE SHAFT FAILURE, REDUCTUION IN SURFACE AREA IS CONSISTANT WITH ACCELERATED DECO	MPOSITION OF BEARING SURFACE.  AIRWEST AIRCRAFT ENGINES SUPPLIED PARTS.  RETURNED PARTS.	1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005041500077	20050415	00077		2005	4	15	2005FA0000485    	2	20050211	G	7414		MAGNETO         																	ENGINE	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09										UPON REINSTALLATION OF A MAGNETO (A 1940'S ERA MAG), INSTALLATION WAS NOT SUCCESSFUL AT FIRST.  AFTER DOING THE REPAIR, 	FOUND THAT THE CONDENSER ON THIS ERA OF MAGNETO CAN BE REMOVED WITH JUST A FLATHEAD SCREWDRIVER AND TAKEN OUT WITHOUT RE	MOVING THE MAGNETO FROM THE ENGINE.  STUDENTS OF MY MAINTENANCE SCHOOL WERE UNAWARE OF THIS, AND AS AN A&P I WOULD LIKE 	TO SPREAD THIS SERVICE DIFFICULTY REMEDY AROUND TO THE GENERAL AVIATION PUBLIC.																 
2005041500166	20050415	00166	CE  	2005	4	15	2005FA0000486    	1	20050224	G	5315	241139526256	FLOORBEAM       			LEAR  	25    	25B         	5170511	CE  										FUSELAGE	CRACKED         	E				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			SW	09	911A	12300				163				RIGHT DIVAN FLOOR ATTACH ANGLE P/N 2411395-26-526 CRACKED IN RADIOUS OF BEND 14 INCHES LONG. DISCOVERED WHILE PERFORMING	 CABIN PRESURE LEAK TEST.					2	L	7	2 	4J				A10CE   					 
2005041400108	20050414	00108	NM  	2005	4	14	2005FA0000487    	1	20050120	G	3010	5E2546	ANTI-ICE SYSTEM 			DORNER	DO32  	DO328100    	2996000	NM  											MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	503CG					3086				DURING REPLACEMENT OF THE 17VE, ELEVATOR HORN DEICE INDICATION PROBLEM DISCOVERED THAT TEMP SENSOR FOR HORN ASSY HAD FAI	LED IN HIGH OHM AREA 288-300 OHM RANGE. PROBLEM WOULD NOT ALLOW FAIL LIGHT ON ASSOCIATED SWITCH ON 17VE PANEL TO ILLUMIN	ATE DURING TEST DESCRIBED IN 31-12-13-550-801-A01 ICE, FUEL, & HYD. PANEL 17VE - RETURN TO SERVICE.  WITH A FAILURE OF T	HIS TYPE THERE IS NO WAY FOR CREW TO EVER NOTICE A FAILURE OF ELEVATOR HORN HEAT OR GET  FAIL ANNUNCIATION IN SWITCH LIG	HT.		2	H	7	2 	4T			RT	A45NM   					 
2005050500082	20050505	00082	EU  	2005	5	5	2005FA0000490    	1	20050302	G	6320	350A32314306	GEAR SET        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAIN ROTOR	CORRODED        	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	972BH					2804				GEAR SET HAS EXCESSIVE FROSTING AND PITTING.  REQUESTING WARRANTY CONSIDERATION. (K)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005050500089	20050505	00089	EU  	2005	5	5	2005FA0000491    	1	20050406	G	7810	4201AN11600	CLAMP           			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					TAILPIPE	CRACKED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	281BT					NA0281	P84262			FLUORESSCENT PENETRANT INSP OF THE TAIL PIPE CLAMP REVEALED ONE NUT TO BE CRACKED.  (K)						2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2005050500090	20050505	00090	EA  	2005	5	5	2005FA0000492    	1	20050321	G	3244	256K433	TIRE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					LT MLG	BULGED          	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	915BD	89   				5091				UPON INSPECTION, TECH FOUND BULGE IN SIDEWALL OF LT MLG OB TIRE; SERIAL NR 22000882, 89 TOTAL LANDINGS.  (CE09200503308)	  (K)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050500091	20050505	00091	WP  	2005	5	5	2005FA0000493    	1	20050329	G	1430	2057D17	SCREW           			BOEING	B17   	B17G        	1380204	WP  	WRIGHT	R1820 	R182097     	67020	EA  					COVER	FRACTURED       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	9563Z					83563	99572			(7) OF THE (10) FRONT COVER RETAINING SCREWS WERE FRACTURED, ALL AT THE SAME LOCATION- (3) THREADS FROM SHANK.  ALL (7) 	HAD WORKED THEIR WAY OUT, (3) HAD STARTED TO CONTACT THE PROPELLER HUB.  NR 4 ENGINE AWAITING TEARDOWN REPORT OF NOSE SE	CTION.  (GL13200506288) (K)				2	L	7	4 	4R	4	R		L13     	5E10				 
2005050500092	20050505	00092	SO  	2005	5	5	2005FA0000494    	2	20050206	G	8520		CRANKSHAFT      			CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512       	17008	SO  					ENGINE	BROKEN          	D				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	11	140SG					11573	21757612			THE ENGINE WAS UNDER POWER WHEN THE CRANKSHAFT BROKE.  THE ENGINE RAN UNTIL AIRCRAFT WAS ON GROUND.  THERE WAS AN EXTREM	E VIBRATION. (K)					1	H	7	1 	3O	3	O	NC	A768    	E233				 
2005050500093	20050505	00093	CE  	2005	5	5	2005FA0000495    	1	20050414	G	7830		SWITCH          			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					THRUST REVERSER	INTERMITTENT    	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	03	400JD	115  				7500235				LT THRUST REVERSER (TR) PERFORMED UNCOMMANDED STOW DURING THRUST REVERSER USE AFTER LANDING.  AFTER ACCESSING THE THROTT	LE QUADRANT, IT WAS NOTICED THAT THE WIRES CONNECTED TO THE LT DEPLOY SWITCH WERE STRETCHED VERY TIGHT WHEN THE T/R (PIG	GYBACK) LEVERS WERE IN THE DEPLOY POSITION.  AFTER RUNNING DIAGNOSTICS USING SOFTWARE PROVIDED BY MFG, IT WAS DETERMINED	 THAT THE DEPLOY SWITCH WAS FAULTY.  DURING THE PROCESS OF ACCESSING THE WIRES TO REPLACE SWITCH, WIRE WAS FOUND TO BE B	ROKEN WHERE IT WAS SPLICED.  THE SHRINK WRAP THAT WAS AROUND THE WIRE BUNDLE CONTRIBUTED TO THE INTERMITTENT NATURE OF T	HE DEFECT.  SPLICE WAS REPAIRED AND AN OPERATIONAL CHECK OF THE T/R SYSTEM CONFIRMED THAT THE SYSTEM HAD BEEN FIXED. (K)	2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005050500094	20050505	00094	CE  	2005	5	5	2005FA0000496    	1	20050325	G	2810	052600058	FUEL TANK       			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  					RIGHT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	9443L					17276558				DURING INSTALLATION OF NEW TANK, IT WAS DISCOVERED THAT THE BUNGS FOR INSTALLING THE FUEL STRAINER ASSEMBLIES HAVE BEEN 	BRAZED TO THE TANK INVERSELY.  THE BUNG THAT SHOULD HAVE BEEN BRAZED AT THE AFT LOCATION WAS BRAZED IN THE FORWARD MOUNT	 WAS BRAZED IN THE AFT MOUNT.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2005050500095	20050505	00095		2005	5	5	2005FA0000497    	4	20050223	G	6122	D20880	FLYWEIGHT       			CESSNA	182   	182         	2072702	CE  	LYC   	O540  	IO540V4A5   	41532	EA  					GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	195RB				990056	26005C				FLYWEIGHT BASE CRACKED ALSO ASSOCIATED PART C20886 SPRING HEAD AND B20882-1.  SPRING DRIVE ALSO CRACKED.  (K)  (22124)						1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005050500096	20050505	00096	NE  	2005	5	5	2005FA0000498    	3	20050223	G	6110	D4951	FORK            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17								HJ1597		NDT SHOWS CRACKED IN (2) PLACES ON FORK.  (K) (12235)						2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE	 
2005050500097	20050505	00097		2005	5	5	2005FA0000499    	4	20050325	G	2562	AK450	ELT             			AMTR  	AEROST	AEROSTARBIRD	0560582	GL  										CABIN	INOPERATIVE     	B			BD6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	32CR	101  				0212401				DURING ANNUAL INSPECTION, THE TECH FOUND, DURING THE FUNCTIONAL TEST THAT THE UNIT INDICATED FUNCTION, THE UNIT TRANSMIT	TED ON FREQUENCY, BUT DID NOT EMIT THE SWEEP TONE. (K)					1	M	7	1 	  				EXPA1M71					 
2005050500099	20050505	00099		2005	5	5	2005FA0000500    	4	20050327	G	2200	NALGENE280	TUBE            			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E225*       	17015	SO  					AUTOPILOT	DISINTEGRATED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4606D	640  				D4771				THIS AUTOPILOT WAS INSTALLED 1/23/95.  IT HAS A TUBE THAT IS TEE`D INTO THE STATIC SYSTEM AND RUNS TO THE ALTITUDE HOLD 	PRESSURE TRANSDUCER.  THIS PLASTIC TUBE LOST IS MECHANICAL PROPERTIES AND FELL APART.  THIS OPEND UP THE STATIC SYSTEM T	O CABIN PRESSURE.  RECOMMENDATION-DO NOT USE THIS PLASTIC TUBING ON ANY AIRCRAFT.  (K)				1	L	7	1 	3O	3	O		A777    	E267				 
2005050500101	20050505	00101	NE  	2005	5	5	2005FA0000501    	3	20050127	G	6111	6607132886	BLADE           	ROTOL       												ROTOL	R389	R389*       	NE  	OUTER SLEEVE	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11		31226	5576 		DR6955988			DR6955988		PROPELLER RECEIVED FOR REPAIR OF BURNED OUT DE-ICER.  PROP REQUIRED COMPLIANCE OF AD.  PROP FAILED AD.  PROP WAS DISASSE	MBLED AND A CRACK WAS FOUND IN ROOT END OUTER SLEEVE OF NR 4 BLADE, SN 258.  BLADE IS REJECTED FROM FURTHER SERVICE.  (K	)														6	C	P30NE	 
2005051000042	20050510	00042	CE  	2005	5	10	2005FA0000502    	1	20050413	G	5210	NAS110321D	BOLT            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					CABIN DOOR	SHEARED         	B			NBFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	48A					BC12				DURING ROUTINE MAINTENANCE TO REPLACE CABIN DOOR HARDWARE, FOUND BOLT SHEARED INSIDE BRACKET.  THERE HAVE BEEN MULTIPLE 	SDR`S OF CABIN DOORS OPENING IN FLIGHT DUE TO FAILURE OF SIMILAR HARDWARE.  RECOMMEND REPLACEMENT OF DOOR LATCH MECHANIS	M PINS AND BOLTS AT 5,000 CYCLES RATHER THAN MFG RECOMMENDED 10,000 CYCLES.  (K)				1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2005051000044	20050510	00044	SW  	2005	5	10	2005FA0000503    	1	20050404	G	2720	2742030021R	BELLCRANK       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					RUDDER	CORRODED        	B			EATR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	327BA	25422				TC249				DURING A DETAILED EMPENNAGE INSPECTION THE RUDDER BELLCRANK WAS REMOVED FOR OTHER MAINTENANCE AND CORROSION WAS FOUND IN	 THE MATING AREA WERE THE GUSTLOCK WELDMENT ATTACHED.  THE PART BEING MAGNESIUM HAD PITTING OF OVER .060 WITH THE NORMAL	 OVERALL THICKNESS BEING .1875 OR .187.  THE PART WAS REMOVED AND REPLACED WITH A NEW ALUMINUM PART.  SB ADDRESSES WATER	 BUILD UP CORROSION PROBLEMS IN THIS AREA NONE WERE DONE ON THIS AIRCRAFT.  NOT SURE IF ANY WOULD CURE THE DISSIMILAR ME	TAL BETWEEN THE CHROMOLY GUST LOCK AND THE MAGNESIUM BELLCRANK.  (K)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005051000045	20050510	00045	EU  	2005	5	10	2005FA0000504    	1	20050402	G	6720		CASE            	DUNLOP      		SNIAS 	350   	AS350B2     	8680813	EU  										SERVO	CRACKED         	B			UVIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					FE204					EDDY CURRENT INSPECTION IAW MFG COMPONENT MM, IDENTIFIED A CRACK FROM A PLUG HOLE.						1	G	7	1 	3U				H9EU    					 
2005051000058	20050510	00058	WP  	2005	5	10	2005FA0000505    	2	20050322	G	7261	30607205	OIL TANK        			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7312B    	 	WP  					NR 3 ENGINE	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	38WP					292	P115203			DURING POST FLT INSP MAINT NOTICED EXCESSIVE OIL COVERING NR 3 ENGINE AND NACELLE.  WITH ENGINE COWL OPENED, OIL WAS PRI	MARILY COLLECTED AROUND OIL TANK AREA.  ENGINE AND COWL CLEANED AND PREPPED FOR ENGINE RUNS.  DURING ENGINE RUN OIL WAS 	OBSERVED COMING FROM A SMALL .5 INCH CRACK IN THE OIL TANK WALL.  CRACK WAS LOCATED APPROXIMATELY 2.25 INCHES BELOW TOP 	OF TANK AND 3.5 INCHES ABOVE AND LT OF THE OIL FILLER CAP.  CRACK APPEARS TO ORIGINATE FROM AN INTERNAL WELD OR WELDED B	AFFLE INTERNAL TO TANK ASSY.  NEW OIL TANK ORDERED FOR REPLACEMENT AND RECEIVED.  SAME PN BUT A DIFFERENT DASH NR.  A DI	RECT REPLACEMENT OIL TANK IAW MFG.  TANK RECEIVED HAD DENT SAME AREA AS CRACKED TANK BEING REPLACED. (K)	2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2005051000059	20050510	00059	CE  	2005	5	10	2005FA0000506    	1	20050328	G	3250	35820045	ROD END         			BEECH 	33    	G33         	1151435	CE  										NLG STEERING	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	217CH	7457 				CD1262				STEERING ROD END, HAS SLID INTO PUSHROD TUBE, AND ATTACHED VIA 2 (.1562) SOLID RIVETS.  RIVETS WERE NOT PROPERLY DRIVEN 	DUE TO COMPRESSING INSIDE HOLLOW PORTION OF TUBE INSTEAD OF AT SHOP HEAD, ALLOWING ROD END TO COME LOOSE.  SEPARATION WO	ULD CAUSE LOSS OF NOSE STEERING CONTROL.  RECOMMEND REPLACEMENT OF SOLID RIVETS WITH  CHERRYMAX RIVETS IN ORIGINAL HOLES	.  (NM07200504925) (K)			1	L	7	1 	3O				3A15    					 
2005051000060	20050510	00060		2005	5	10	2005FA0000507    	4	20050324	G	3414	70257N01D02	ALTIMETER       			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312B    	 	WP  					COPILOT	INOPERATIVE     	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	07	94AA					295				THE COPILOTS ALTIMETER FLAGGED JUST AFTER TAKEOFF,  AIRCRAFT RETURNED TO THE FIELD.  AFTER CYCLING THE BATTERIES THE ALT	IMETER BEGAN WORKING AGAIN.  THE COPILOTS ALTIMETER WAS REPLACED AND TESTED WITH NO FURTHER DEFECTS NOTED.  THERE HAVE B	EEN NO PRIOR PROBLEMS REPORTED ON THIS ALTIMETERY SYSTEM. (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005051000061	20050510	00061		2005	5	10	2005FA0000508    	4	20050324	G	3414	702490031304	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	39DK					480				THE PILOTS ALTIMETER FLAGGED DURING PREFLIGHT.  THERE ARE NO PRIOR REPORTS OF PROBLEMS ON THE ALTIMETRY SYSTEM.  THE ADC	 WAS REPLACED AND TESTED WITH NO FURTHER DEFECTS NOTED.  (K)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005051000064	20050510	00064		2005	5	10	2005FA0000509    	4	20050406	G	3416		TRANSPONDER     			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					NR 2	MALFUNCTIONED   	D				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			GL	07	72JF					088				WHILE ENROUTE, IN CRUISE AT FL 370, THE MODE C ON THE NR 2 TRANSPONDER REPORTED A 500 FOOT ERROR.  THE CREW SWITCHED TO 	THE NR 1 TRANSPONDER AND IT REPORTED AN ERROR ALSO.  BOTH PRIMARY ALTIMETERS CROSS CHECKED, OK.  BOTH PRIMARY ALTIMETRY 	SYSTEMS AND THE STANDBY ALTIMETER WERE TESTED AND NO DEFECTS WERE NOTED.  CONNECTIONS WERE CLEANED AND INSPECTED AT THE 	ADC.  COPILOTS ALTIMETER AND BOTH TRANSPONDERS.  THE SYSTEMS WERE RAN TO ALTITUDE AGAIN, STILL WITH NO DEFECTS NOTED.  T	HE AIRCRAFT IS RVSM COMPLIANT.  (K)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005051000086	20050510	00086	CE  	2005	5	10	2005FA0000510    	1	20050304	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	07	5582X	107  				CE1353				PILOT SELECTED GEAR UP AND NOTHING HAPPENED.  AIRCRAFT RETURNED TO BASE.  UPON FURTHER TROUBLESHOOTING, FOUND RELAY WAS 	INTERMITTENT, PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  FURTHER IMPROVEMENT	 ON RELAY ARE NEEDED.  DATE CODE 0445.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005051000087	20050510	00087	CE  	2005	5	10	2005FA0000511    	1	20050330	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	1563A	199  				CE1320	830057R			WHILE IN FLIGHT, PILOT SWITCHED LANDING GEAR HANDLE TO THE DOWN POSITION AND NO RESPONSE APPROX 2 MIN LATER GEAR CAME DO	WN.  MAINTENANCE TECH TROUBLESHOT GEAR SYSTEM AND FOUND THAT THE DYNAMIC RELAY WAS INTERMITTENT.  NO RECOMMENDATION AT T	HIS TIME.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005051000107	20050510	00107	SO  	2005	5	10	2005FA0000512    	1	20050414	G	5712	00241T004	RIB             			AYRES 	S2T   	STRT34      	0970106	SO  	PWA   	PT6   	PT6*        	52043	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	6124Y	6922 				T34198				WING MID-CORD RIB JUST FORWARD OF THE OB AILERON HINGE, FOUND CRACKED WHERE IT IS RIVETED TO THE REAR SPAR.  BOTH LT AND	 RT SIDES SAME.  THIS IS NOT EASY TO SEE DUE TO THE POSITION OF THE EXISTING INSPECTION HOLES BUT CAN BE SEEN IF YOU ARE	 LOOKING FOR IT.  SB ADDRESSES PROBLEMS WITH AILERON HINGE BRACKETS AND REAR SPAR CRACKING IN THIS SAME LOCATION AND DUE	 TO THE SAME STRESS.  PROBABLE CAUSE IS REAR SPAR TWISTING DUE TO AILERON LOADS.  A VERTICAL STIFFENER AT THIS LOCATION 	WOULD REDUCE THIS LOAD TO THE SPAR AND RIB.  (K)		1	L	7	1 	3T	3	T		A3SW    	E2NE				 
2005051000109	20050510	00109		2005	5	10	2005FA0000514    	4	20050324	G	6113	05522311	SPINNER         			CESSNA	172   	172S        	2072439	CE  						MCAULY	IC235	IC235LFA7570	EA  	PROPELLER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	154ME	96   				172S8534				DURING 100 HR INSPECTION THE FORWARD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AROUND 5 OF THE 6 BOLT HOLES.  CAUSE OF TH	E PROBLEM IS THAT WHEN THE PROP MOUNTING BOLTS ARE TORQUED TO THE LIMITS GIVEN IN THE SRM THAT THE FORWARD BULKHEAD GET 	PULLED DOWN SLIGHTLY INTO THE CHAMFER OF THE PROP BOLT HOLES AND THIS IN TURN STRESSES THE PART LEADING TO CRACKING.  TO	 SOLVE THIS PROBLEM, I THINK THAT THE TORQUE OF THE MOUNTING BOLTS AND THE DESIGN OF THE BULKHEAD NEED TO BE EVALUATED A	ND CHANGES MADE. (K)		1	H	7	1 	3O			NT	3A12    		5	N	P12EA	 
2005051000110	20050510	00110	CE  	2005	5	10	2005FA0000515    	1	20050315	G	8120	S25351	CHECK VALVE     			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					TURBOCHARGER	INOPERATIVE     	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1898X					R18201898	L19988740A			OIL LEAKING OUT OF TURBO CHARGER AFTER ENGINE SHUTDOWN, ENGINE HAD NOT BEEN RUN SINCE CHECK VALVE HAD BEEN INSTALLED.  R	EMOVED OIL PRESSURE CHECK VALVE FOR INSPECTION, AND NOTED LOOSE NUT, TOTALLY SEPARATED INSIDE THE CHECK VALVE.  THIS OBV	IOUSLY WAS THAT WAY WHEN IT WAS INSTALLED AS A NEW PART.  (K)				1	H	7	1 	3O	3	O		3A13    	E295				 
2005051000112	20050510	00112		2005	5	10	2005FA0000516    	4	20050406	G	6113	055032112	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	BROKEN          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	972WW	636  				172S9072		VF23031		PROP SPINNER AFT BULKHEAD BROKE AT ONE CORNER WITH NUTPLATE, FREEING ONE AFT EDGE OF THE SPINNER WHICH BENT OUTWARD UNDE	R CENTRIFUGAL FORCE. (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005051000114	20050510	00114	CE  	2005	5	10	2005FA0000517    	1	20050329	G	5540	5730261	HINGE           			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					RUDDER	MISINSTALLED    	B			OACR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	487DH					421B0362				AIRCRAFT WAS HERE FOR COMPLETE EXTERIOR REPAINT.  AFTER REMOVING RUDDER, COMPLIED WITH MFG MEB004.  IT IS JUST A VISUAL 	INSPECTION, BUT IT DOES REQUIRE REMOVING THE RUDDER.  FOUND THAT RUDDER HINGE ASSY WAS INSTALLED UPSIDE DOWN.  FOUND THA	T ABOUT 75 PERCENT OF THE LOWER RUDDER HINGE ASSY ARE INSTALLED UPSIDE DOWN, AND MANY WITH THE BEARING FALLING OUT AND W	EARING ON THE RUDDER HINGE BRACKETS. (K)			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005051000130	20050510	00130	CE  	2005	5	10	2005FA0000518    	1	20050408	G	2822	A8160D	PUMP            			CESSNA	182   	182T        	2072703	CE  										FUEL BOOST	FAILED          	B			NE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07		166  				81337				RECEIVED BOOST PUMP FOR WARRANTY CREDIT WITH A CUSTOMER COMPLAINT OF (FUEL BOOST PUMP POPS CIRCUIT BREAKER).  PRELIMINAR	Y INSPECTION OF THE PUMP REVEALED FOREIGN MATERIAL IN THE INLET PORT.  FURTHER INSPECTION REVEALED THE FOREIGN MATERIAL 	TRIED TO PASS THROUGH THE PUMP AND HAD LOCKED THE ROTOR IN THE INSERT.  THIS WOULD CAUSE THE PUMP TO DRAW HIGH AMPS.  TH	IS IS THE SECOND TIME THIS PROBLEM HAS BEEN SEEN IN THE LAST 4 MONTHS. (K)			1	H	7	1 	3O			NT	3A13    					 
2005051000131	20050510	00131	EA  	2005	5	10	2005FA0000519    	2	20050405	G	8520	SL15357	PISTON          								LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		1832 								DURING A 100 HR INSPECTION, FOUND A SMALL PIECE OF METAL IN THE SUCTION SCREEN.  NO METAL WAS FOUND IN THE FILTER, INSPE	CTED PIECE AND DETERMINED TO BE FROM A PISTON, REMOVED OIL SUMP AND FOUND SEVERAL MORE PIECES, LOOKED INTO CASE.  FOUND 	THE SKIRT OF NR 3 PISTON TO BE MISSING PIECES.  REMOVED NR 3 CYLINDER AND FOUND NO DAMAGE TO THE CYLINDER, REMOVED REMAI	NING CYLINDERS AND FOUND NO DAMAGE.  CYLINDER REMOVED 661.9 HRS AGO FOR AN ENGINE TEARDOWN AND REINSTALLED, TTSN: 3836.8	, TTSO1832.6.  PART HAD A CRACK THAT EXTENDED .5 INCH BEYOND THE BROKEN SECTION HEADED TOWARD THE OIL SCRAPER DRAIN HOLE	.  (K)						3	O			E274				 
2005042700262	20050427	00262	CE  	2005	4	27	2005FA0000520    	1	20050330	G	7810	NE102668	CLAMP           			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					TAILPIPE	BROKEN          	G				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			WP	23	XBGRN	9507 				6500069				IN FLIGHT, TAILPIPE CLAMP FAILED ALLOWING HOT GASSES TO ENTER NACELLE REGION.  PAINT ON HOT AIR SHIELD/DUCTING WAS BLIST	ERED.  N-1 TACHOMETER BEGAN TO WORK INTERMITTENTLY, ITT IND WENT OUT, FIRE LIGHT CAME ON, HIGH-PRESSURE BLEED AIR DUCT O	VERHEAT WARNING CAME ON.  LANDING, ENG WAS EXAMINED, NO IND OF DAMAGE TO INTERIOR OF NACELLE.  SS SHIELDS, WHICH FORM CO	OL AIR DUCT AROUND REAR OF ENGINE, FOUND TO HAVE BLISTERED AND BURNED AWAY PAINT.  SHROUDS WERE CLOSELY EXAMINED, FOUND 	TO BE INTACT WITHOUT DEFORMATION OR RUPTURES.  CLAMP WAS REPLACED, TEST RUNS SHOWED ALL INDICATIONS RETURNED TO NORMAL O	PERATION, INDICATIONS DURING  TEST RUNS THAT INCLUDED HIGH POWER.  NO MFG REQUIREMENT TO REPLACE THIS PRIOR TO FAILURE.	2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2005042500180	20050425	00180	EA  	2005	4	25	2005FA0000521    	2	20050303	G	8550	ES48110	OIL FILTER      								LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	6394	75   					RL1979548A			BOTH ENGINE OIL FILTERS WERE OPENED AFTER AN OIL CHANGE.  BOTH FILTERS HAD THE PAPER FILTER MATERIAL PULLED AWAY FROM TH	E METAL CRIMP HOLDING THE ENDS TOGETHER.										3	O			1E4				 
2005050300219	20050503	00219	GL  	2005	5	3	2005FA0000523    	1	20050405	G	5210		SKIN            			CIRRUS	SR    	SR22        	2130001	GL  										LT DOOR	DEBONDED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8163Q					0785				LT DOOR HANDLE IS MOUNTED IN A TURNED ALUMINUM RECESS THAT IS SUPPOSED TO BE BONDED TO THE DOOR. THIS RECESS HAS COME LO	OSE FROM THE DOOR AND IS FREE TO ROTATE.  WHEN IT ROTATES, IT JAMS THE HANDLE AND MAKES THE DOOR EXTREMELY DIFFICULT TO 	OPEN. THE PART HAS TO BE CUT FROM THE DOOR AND REBONDED TO SECURE IT.				1	L	7	1 	3O			NT	A00009CH					 
2005050300223	20050503	00223		2005	5	3	2005FA0000524    	4	20050406	G	3417	962830A1S8	ADC             			DHAV  	DHC2  	DHC2*       	2800108	EA  										COCKPIT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	47AK	148  				726				THE ADC INSTALLED AS PART OF THE EFIS SYSTEM IAW STC NR SA02207AK WOULD NOT MAINTAIN A CONSTANT ACCURATE ALTITUDE READIN	GS. EACH TIME THE READING WAS RESET, THE ALTITUDE READING WOULD DEVIATE UP TO 2000 FT.					1	H	7	1 	3R				A806    					 
2005050300224	20050503	00224		2005	5	3	2005FA0000525    	4	20050406	G	3417	962830A1S8	ADC             			DHAV  	DHC2  	DHC2*       	2800108	EA  										COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	60077	983  				1419				AIR DATA COMPUTER (ADC) INSTALLED AS PART OF THE STC NR SA02207AK REPORTING VARING ALTITUDE ERROR UP TO 500 FT.						1	H	7	1 	3R				A806    					 
2005050500055	20050505	00055	SO  	2005	5	5	2005FA0000526    	1	20050208	G	8011	MHB6016	RING GEAR       			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	149LH	221  	221  			2842192				NEW STARTER FAILED AFTER 221.2 HOURS IN SERVICE. FAILED IN THE ENGAGED POSITION, DAMAGING STARTER RING GEAR AND REQUIRIN	G REPLACEMENT.					1	L	7	1 	3O	3	O		2A13    	E274				 
2005050500056	20050505	00056	SO  	2005	5	5	2005FA0000527    	1	20050208	G	8011	MHB6016	RING GEAR       			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	149LH	221  	221  			2842192				NEW STARTER FAILED AFTER 221.2 HOURS IN SERVICE. FAILED IN THE ENGAGED POSITION, DAMAGING STARTER RING GEAR AND REQUIRIN	G REPLACEMENT.					1	L	7	1 	3O	3	O		2A13    	E274				 
2005042700132	20050427	00132		2005	4	27	2005FA0000528    	4	20050325	G	3420	2300626020	MOTOR           	COLLINS     	ADI85A      															INDICATOR	INTERMITTENT    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09					772					MOTORS HAVE HIGH RESISTANCE BETWEEN THE BRUSHES AND ARMATURE OF THE MOTOR. THIS CAUSES THE MOTOR TO STICK INTERMITTENTLY	, CAUSING A FALSE ATTITUDE DISPLAY IN THE COCKPIT. THIS PROBLEM BEGAN WITH MOTORS DATE CODED 04/04.  THIS MOTOR WAS VERY	 NOISY IN OPERATION ALSO.  BEARINGS SOUND ROUGH WHILE MOTOR IS OPERATING.																	 
2005050300222	20050503	00222		2005	5	3	2005FA0000529    	4	20050406	G	3425	AHRS500GA222	AHRS            			PIPER 	PA32  	PA32300     	7103212	SO  										COCKPIT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	6117J					327640095				UPON GROUND CALIBRATIONS, SOFTWARE SAID CALIBRATION COMPLETE. DURING FLIGHT CHECK AHRS WANDERED OFF HEADING COURSE UP TO	 30 DEGREES AFTER TAKE OFF OF RUNWAY AND DURING LEVEL FLIGHT.					1	L	7	1 	3O				A3SO    					 
2005050500049	20050505	00049	SO  	2005	5	5	2005FA0000530    	1	20050128	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28R201    	7102816	SO  										ENGINE	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	147LH	197  	197  			2844103				NEW STARTER FAILED AFTER 197.5 HOURS. BENDIX FAILED TO ENGAGE.						1	L	7	1 	3O				2A13    					 
2005050500050	20050505	00050	SO  	2005	5	5	2005FA0000531    	1	20050128	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28R201    	7102816	SO  										ENGINE	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	147LH	197  	197  			2844103				NEW STARTER FAILED AFTER 197.5 HOURS. BENDIX FAILED TO ENGAGE.						1	L	7	1 	3O				2A13    					 
2005042700276	20050427	00276	SO  	2005	4	27	2005FA0000532    	1	20050331	G	5712	78475007	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WING	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	921ER	5631 				4496008				SINCE OUR FLEET WERE ALL FOUND TO HAVE CRACKED RIBS IN THE SAME LOCATION (FOUND DURING ROUTINE INSPECTION / SDRS WERE SE	NT IN).  THE CRACKS ARE FOUND IN THE RIB, ADJACENT TO THE LANDING GEAR TRUSS BRACKET (WHICH MUST BE REMOVED TO PROPERLY 	SEE THE CRACK).  IN THIS PARTICULAR AIRCRAFT THE RIB, P/N 78475-007, LOCATED AT AFT STATION 49.25 ON THE RT SIDE, WAS CR	ACKED. THE RIB, P/N 78475-006, LOCATED AT AFT STATION 49.25 ON THE LT SIDE WAS ALSO CRACKED.			1	L	7	2 	3O				A19S0   					 
2005042700036	20050427	00036		2005	4	27	2005FA0000533    	4	20050316	G	3416	AK350	ENCODER         																	ALTIMETER	LEAKING         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09										STATIC AIR INPUT LEAKS 200 FEET PER MINUTE AT 1000 FEET AGL.																			 
2005042700072	20050427	00072	CE  	2005	4	27	2005FA0000535    	1	20050321	G	3000		BOOT            			CESSNA	500   	560CESSNA   	2076750	CE  										DEICE SYS	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99										DEICE BOOT MALFUNCTIONED.						2	L	7	2 	4F			RT	A22CE   					 
2005050300201	20050503	00201	SO  	2005	5	3	2005FA0000537    	1	20050328	G	3220	86280003	DRAG LINK       			PIPER 	PA44  	PA44180     	7104402	SO  										NLG	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	295ND	4241 				4496030				DURING SCHEDULED INSPECTION THE NLG DRAG LINK PIVOT BOLT WAS FOUND BROKEN IN HALF AND THE NUT AND COTTER PIN END MISSING	. THE OTHER END HAD BEGAN MIGRATING OUT AND COLLAPSE OF THE NOSE GEAR WAS EMINENT. THE DRAG LINK WAS DAMAGED BY THE ROTA	TION OF THE BOLT HEAD BEING ABLE TO ROTATE. THE ASSY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3O				A19S0   					 
2005050400035	20050504	00035	EA  	2005	5	4	2005FA0000539    	2	20050411	G	7322	30804	FLOAT           		MA3PA       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CARBURETOR	CHAFED          	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			EA	11	25446		64   		DTO200	15280666	L2367415	775596		ENGINE QUIT IN FLIGHT, PERFORMED AN EMERGENCY LANDING IN A PARKING LOT. EXITING AIRCRAFT FUEL WAS FOUND RUNNING OUT OF C	OWL, SHUTOFF FUEL SELECTOR, FUEL STOPPED. MAINTENANCE FOUND FUEL LEAKING FROM CARBURETOR. SENT CARBURETOR TO OVERHAUL SH	OP, FOUND PLASTIC FLOAT CHAFFING ON FUEL BOWL BECAUSE OF INSUFFICIENT CLEARANCE CAUSING THE FLOAT TO HANG UP. REASSEMBLE	D CARBURETOR WITH A METAL FLOAT KIT WHICH PROVIDED SATISFACTORY CLEARANCE BETWEEN THE FLOAT AND FUEL BOWL.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005050400083	20050504	00083	SO  	2005	5	4	2005FA0000542    	1	20050412	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	FAILED          	D				K				NONE                    				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	146LH	143  	76   			2844102	L3109151A			STARTER REPAIRED UNDER W/O 6900 FOR SB A-112. FAILED IN SERVICE 76.4 HOURS LATER.						1	L	7	1 	3O	3	O		2A13    	1E10				 
2005050500087	20050505	00087	SO  	2005	5	5	2005FA0000543    	1	20050401	G	2697		GROUND STUD     			GULSTM	G1159 	GIV         	3980115	SO  										ZONE 310	INCORRECT       	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	941AM	776  				1499				WHILE PERFORMING TASK NR 262070, RT FIRE BOTTLE WEIGHT CHECK DURING AIRCRAFT FIRST 2C CHECK, IT WAS DISCOVERED THAT GROU	ND STUDS E4045 AND E4046 DID NOT HAVE THE WIRE TERMINAL HOLD DOWN NUTS TORQUED. THE WIRE TERMINALS WERE FREE TO MOVE UP 	AND DOWN ALONG THE STUDS, APPROXIMATELY .6250 INCH. NUTS WERE TORQUED AND FIRE EXTINGUISHING CIRCUITRY INTEGRITY TEST WA	S PERFORMED AND FOUND TO BE SATISFACTORY.			2	L	7	2 	4F			RT	A12EA   					 
2005042700074	20050427	00074	EA  	2005	4	27	2005FA0000544    	2	20050322	G	7320	25765362	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	FUEL SYSTEM	OUT OF ADJUST   	B				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SO	15	479ER		1574 			172S8942	L2709951A	UC029		ENG QUIT AT 3000 FT, RESTARTED AT 2100 FEET.  ENG WAS RESTARTED, MIX IN IDLE CUTOFF POSITION.  ENG WOULD NOT GAIN MORE T	HAN 500 RPM, FUEL SMELL IN COCKPIT.  ENG FAILED AGAIN WHEN AC WAS ON RUNWAY, WOULD NOT RESTART.  MECH UNCOWLED, VISUALLY	 INSPECT POWER PLANT INSTALL.  NO DEFECTS WERE NOTED UNTIL FUEL SYS WAS TESTED.  FLOWING FUEL (MIXTURE, THROTTLE CLOSED)	 FUEL FLOW INDICATOR SHOWED 7/HR. (GAUGE ALMOST PEGGED).  ALL FUEL NOZZLES WERE REMOVED FROM CYL HEADS, REATTACHED TO DE	LIVERY TUBES FOR VISUAL SQUIRT TEST.  ALL 4 NOZZLES FLOWED, BUT SQUIRTED APPROX 3 TIMES FARTHER THAN NORMAL (12 FEET).  	FUEL SERVO WAS REPLACED TO SOLVE OVERALL PROBLEM.  POST GROUND RUN UPS WERE NORMAL WITH NO DEFECTS NOTED.	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005042700278	20050427	00278	SO  	2005	4	27	2005FA0000547    	1	20050331	G	5712	78475007	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WINGS	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	928ER	4556 				4496026				SINCE OUR FLEET OF SIX PIPER ARROWS WERE ALL FOUND TO HAVE CRACKED RIBS IN THE SAME LOCATION (FOUND DURING ROUTINE INSPE	CTION / SDRS WERE SENT IN) WE DETERMINED TO INSPECT OUR FLEET OF TEN SEMINOLES.  THE BASIC WING STRUCTURE IS DESIGNED TH	E SAME.  WE FOUND SIMILAR CRACKS IN SEVEN OF THE SEMINOLES.  THE CRACKS ARE FOUND IN THE RIB, ADJACENT TO THE LANDING GE	AR TRUSS BRACKET(WHICH MUST BE REMOVED TO PROPERLY SEE THE CRACK).  IN THIS PARTICULAR AIRCRAFT THE RIB, P/N 78475-007, 	LOCATED AT AFT STATION 49.25 ON THE RIGHT SIDE, WAS CRACKED.		1	L	7	2 	3O				A19S0   					 
2005042700153	20050427	00153	CE  	2005	4	27	2005FA0000548    	1	20050330	G	8011	PM2401	HOUSING         			CESSNA	172   	172S        	2072439	CE  										STARTER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	406ER	1684 	1684 			172S9156				THE FORWARD PART OF THE STARTER HOUSING WAS FOUND TO BE TOTALLY BROKEN OFF FROM THE STARTER HOUSING (THE SECTION HOUSING	 THE BENDIX DRIVE).					1	H	7	1 	3O			NT	3A12    					 
2005042700279	20050427	00279	SO  	2005	4	27	2005FA0000549    	1	20050331	G	5712	78475006	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WINGS	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	925ER	5922 				4496012				SINCE OUR FLEET OF SIX PIPER ARROWS WERE ALL FOUND TO HAVE CRACKED RIBS IN THE SAME LOCATION (FOUND DURING ROUTINE INSPE	CTION / SDRS WERE SENT IN) WE DETERMINED TO INSPECT OUR FLEET OF TEN SEMINOLES.  THE BASIC WING STRUCTURE IS DESIGNED TH	E SAME.  WE FOUND SIMILAR CRACKS IN SEVEN OF THE SEMINOLES.  THE CRACKS ARE FOUND IN THE RIB, ADJACENT TO THE LANDING GE	AR TRUSS BRACKET(WHICH MUST BE REMOVED TO PROPERLY SEE THE CRACK).  IN THIS PARTICULAR AIRCRAFT THE RIB, P/N 78475-006, 	LOCATED AT AFT STATION 49.25 ON THE LEFT SIDE, WAS CRACKED.		1	L	7	2 	3O				A19S0   					 
2005042700125	20050427	00125	CE  	2005	4	27	2005FA0000550    	1	20050325	G	5511	263202125	RIB             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					HORIZONTAL STAB	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	103VE	6323 				208B0620				UPON INSPECTION OF HORIZONTAL STABILIZER, MECHANIC NOTED THAT ALL RIVETS SECURING FORWARD FLANGE OF RIB P/N 2632021-25 T	O FORWARD SPAR WERE MISSING.  HOLES WERE DRILLED THRU WITH BARE METAL SHOWING (NO PRIMER IN HOLES).  ASSUMPTION IS THAT 	RIVETS WERE OMITTED AT FACTORY.  THIS DISCREPANCY CAN ONLY BE VIEWED THRU ACCESS PANEL ON TOP, IB, RT SIDE OF HORIZONTAL	 STAB.			1	H	7	1 	3T	3	T		A37CE   	E2NE				 
2005042700126	20050427	00126		2005	4	27	2005FA0000551    	4	20050325	G	6113	05503675	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360LYC*   	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	360SP	1852 				172S8777	L2958951A	UK23071		1.25 INCH CRACK EMANATING FROM PROPELLER BLADE CUTOUT RUNNING PARALLEL WITH THE FORWARD BULKHEAD.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005042700127	20050427	00127		2005	4	27	2005FA0000552    	4	20050325	G	6113	05503675	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360LYC*   	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3532T	1439 				172S8820	L2968451A	XH23051		1 INCH CRACK EMANATING FROM PROPELLER CUTOUT PARALLEL WITH THE FWD BULKHEAD.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005050400119	20050504	00119	SO  	2005	5	4	2005FA0000553    	1	20050413	G	8011	MZ4222	DRIVE ASSY      			PIPER 	PA44  	PA44180     	7104402	SO  										STARTER	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3090A	696  				4496183				STARTER BENDIX DRIVE SHATTERED.						1	L	7	2 	3O				A19S0   					 
2005042700042	20050427	00042	CE  	2005	4	27	2005FA0000554    	1	20050318	G	3210	504501024	TORQUE TUBE     			CESSNA	421   	421B        	2076014	CE  										MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	41114	1546 				421B0458				LANDING GEAR TORQUE TUBE IS CRACKED						1	L	7	2 	3O				A7CE    					 
2005042700071	20050427	00071	SO  	2005	4	27	2005FA0000555    	1	20050321	G	5712	78475009	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	492B	2859 				2844051	L2408751A			DURING A VISUAL INSP, A SMALL CRACK WAS FOUND IN THE RT NOSE RIB P/N-62021-005 AND -004. A MORE THOROUGH INSPECTION REVE	ALED THAT AN ADDITIONAL CRACK, MUCH LARGER (ABOUT 4 INCH LONG), WAS FOUND ON THE RIB P/N-78475-009 AND -008. THESE RIBS 	ARE INCLUDED IN THE MOUNTING ASSEMBLY FOR THE P/N-95643-007 AND -006 AND BRACKET(MAIN GEAR TRUSS). THE OPERATOR OF THIS 	AIRCRAFT HAD SIMILAR CRACKS, ON BOTH LT AND RT WINGS. THE AC IS GROUNDED AND THE AFFECTED PARTS ARE BEING REPLACED.			1	L	7	1 	3O	3	O		2A13    	1E10				 
2005042700075	20050427	00075	SO  	2005	4	27	2005FA0000556    	1	20050322	G	5712	78475009	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	708ER	2327 				2844067	L3020251A			DURING A VISUAL INSPECTION, A SMALL CRACK WAS FOUND IN THE RT NOSE RIB P/N-62021-005 AND -004.  A MORE THOROUGH INSPECTI	ON REVEALED THAT AN ADDITIONAL CRACK, MUCH LARGER (ABOUT 4 IN LONG), WAS FOUND ON THE RIB P/N-78475-009 AND -008.  THESE	 RIBS ARE INCLUDED IN THE MOUNTING ASSY FOR THE P/N-95643-007 AND -006 AND BRACKET (MAIN GEAR TRUSS). THE OPERATOR OF TH	IS AIRCRAFT HAD SIMILAR CRACKS, ON BOTH LT AND RT WINGS. THE FLEET IS GROUNDED AND THE AFFECTED PARTS ARE BEING REPLACED	.		1	L	7	1 	3O	3	O		2A13    	1E10				 
2005042700066	20050427	00066	SO  	2005	4	27	2005FA0000557    	1	20050321	G	5712	78475009	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	701ER	2571 				2844053	L3013951A			DURING VISUAL INSPECTION, A SMALL CRACK WAS FOUND IN THE RT NOSE RIB P/N-62021-005 AND -004. A MORE THOROUGH INSPECTION 	REVEALED THAT AN ADDITIONAL CRACK, MUCH LARGER (ABOUT 4 INCHES LONG), WAS FOUND ON THE RIB P/N-78475-009 AND -008. THESE	 RIBS ARE INCLUDED IN THE MOUNTING ASSY FOR THE P/N-95643-007 AND -006 AND BRACKET (MAIN GEAR TRUSS).  THE OPERATOR OF T	HIS AIRCRAFT HAD SIMILAR CRACKS, ON BOTH LT AND RT WINGS. AC IS GROUNDED AND THE AFFECTED PARTS ARE BEING REPLACED.			1	L	7	1 	3O	3	O		2A13    	1E10				 
2005042700137	20050427	00137	CE  	2005	4	27	2005FA0000558    	1	20050325	G	3233	128054115	ACTUATOR        			CESSNA	182   	R182        	2072734	CE  										NLG	BINDING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	6370T		481  			R18201999				PISTON NUT P/N 9880506-1, DRAGGING ON BEARING END PINS P/N 129009-2. PINS WERE PREVIOUSLY INSTALLED IAW SEB95-20 AND SK2	10-155. PIN CLEARANCE WAS CHECKED ON INSTALLATION, CLEARANCE WAS .020 AND.024. PINS ARE NOW DRAGGING ON PISTON NUT MAKIN	G IT DIFFICULT TO MOVE GEAR INTO THE LOCK POSITION.				1	H	7	1 	3O			RT	3A13    					 
2005051100150	20050511	00150	EA  	2005	5	11	2005FA0000559    	2	20050421	G	7322	105217	CARBURETOR      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			GL	23			1848 			17275405	RL1929439A	RK007		ENGINE RPM WOULD NOT REDUCE BELOW 1300 RPM.  INSTR ATTEMPTED TO LAND AC, BUT COULD NOT REDUCE AIRSPEED DUE TO HIGH ENG R	PM.  THROTTLE WAS ADVANCED TO FULL PWR SETTING, BUT ENG FAILED TO ACCELERATE. AC HIT FENCE, WAS DAMAGED. POST-ACCIDENT G	ROUND RUN, FOUND ENG WOULD NOT IDLE BELOW 1300 RPM OR ACCELERATE PAST 1800 RPM. COMPRESSION TEST  PERFORMED, NR 3 CYL WA	S FOUND TO BE 44/80 PSI, LEAKING THROUGH PISTON RINGS. ASSUMED NOZZLE WAS INGESTED INTO THE NR3 CYLINDER. WHEN CARBURETO	R WAS REMOVED, IT WAS FOUND THAT ACCELERATOR PUMP DISCHARGE NOZZLE (TUBE) WAS MISSING FROM CARB AIR INLET. TUBE IS PRESS	ED-FIT INTO THE INLET CASTING DURING ASSEMBLY. SECOND CARB WAS INSTALLED, ENG RAN AT PROPER IDLE AND FULL POWER RPM.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005050400073	20050504	00073	WP  	2005	5	4	2005FA0000560    	1	20050408	G	2432	AD430B034LB03	BATTERY         			DOUG  	DC9   	DC983       	3022083	WP  										ZONE 100	OVERTEMP        	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	03	315FV					49707				EXTREME SMOKE REQUIRING EVACUATION OF AIRCRAFT. BATTERIES SHOW EVIDENCE OF EXCESSIVE HEAT.						2	L	7	2 	4F			RT	A6WE    					 
2005042700277	20050427	00277	SO  	2005	4	27	2005FA0000562    	1	20050331	G	5712	78475006	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WING	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	923ER	5735 				4496010				SINCE OUR FLEET OF SIX PIPER ARROWS WERE ALL FOUND TO HAVE CRACKED RIBS IN THE SAME LOCATION (FOUND DURING ROUTINE INSPE	CTION / SDRS WERE SENT IN) WE DETERMINED TO INSPECT OUR FLEET OF TEN SEMINOLES.  THE BASIC WING STRUCTURE IS DESIGNED TH	E SAME.  WE FOUND SIMILAR CRACKS IN SEVEN OF THE SEMINOLES.  THE CRACKS ARE FOUND IN THE RIB, ADJACENT TO THE LANDING GE	AR TRUSS BRACKET(WHICH MUST BE REMOVED TO PROPERLY SEE THE CRACK).  IN THIS PARTICULAR AIRCRAFT THE RIB, PN 78475-006, L	OCATED AT AFT STATION 49.25 ON THE RIGHT SIDE, WAS CRACKED.		1	L	7	2 	3O				A19S0   					 
2005042700043	20050427	00043	CE  	2005	4	27	2005FA0000563    	1	20050318	G	3210	504501025	TORQUE TUBE     			CESSNA	414   	414         	2075908	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	414TM	6674 				4140419				LANDING GEAR TORQUE TUBE IS CRACKED.						1	L	7	2 	3O			RT	A7CE    					 
2005042700121	20050427	00121	CE  	2005	4	27	2005FA0000564    	1	20050324	G	5755		SKIN PANEL      			CESSNA	210   	210L        	2073448	CE  										SPEEDBRAKE	CRACKED         	F				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	10		350  				21059635				LT WING, IB AND AFT OF SPEEDBRAKE, INSTALLATION FORMED A CRACK AT THE WING T/E AND AT THE FORWARD STIFFENER ATTACHMENT P	OINT.  WING SKIN EXPERIENCES BUFFETING IN AND OUT OF PLANE WITH SPEEDBRAKES DEPLOYED AS A RESULT OF TURBULENCE.  THE WIN	G PANEL SKIN IS LARGE AND OILCANS IN AND OUT OF PLANE GENERATING SIGNIFICANT TENSILE FORCE ON THE RIVETS AT THE PERIMETE	R OF THE PANEL.  THE ADDED WING STIFFENER LIMITS THE OILCAN MOVEMENT AND STRESS. CRACK INITIATED AT FORWARD RIVET HOLE F	OR ADDED STIFFENER.		1	H	7	1 	3O				3A21    					 
2005051600109	20050516	00109	CE  	2005	5	16	2005FA0000565    	1	20050326	G	3220	0442504201	FORK            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NOSE STRUT	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	23	33LJ	9830 				15282023	L1776615	R774607		LOWER NOSE FORK FAILED AFTER AIRCRAFT TURNED OFF THE RUNWAY AFTER LANDING.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005051600111	20050516	00111	CE  	2005	5	16	2005FA0000566    	1	20050401	G	2822	476087E	PUMP            			CESSNA	210   	210         	2073402	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG WW	WRONG PART      	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	15	9408T					57208				SUSPECT PUMP IS INCORRECT BY PN 4760876 FOR INSTALLATION AC.  INTERFERED WITH NOSE LANDING GEAR UPLOCK OPERATION. (K)						1	H	7	1 	3O	3	O	RT	3A21    	E1CE				 
2005051600112	20050516	00112	NE  	2005	5	16	2005FA0000567    	2	20050411	G	7250	1847M96P02	SEAL            	GE          		BOEING	777   	777*        	UTILUSE	NM  	GE    	GE90  	GE9090B     	 	NE  					HPT ROTOR	CRACKED         	B			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35		11868	2497 		M900146	PPVRC2	900146			MDR/001/05: DURING ENG O/H, 2 CRACKS WERE NOTED ING THE HPT INTERSTAGE SEAL.  CRACKS ARE ABOUT 45 DEGREES APART AND APPE	AR TO ORIGINATE IN THE FWD ARM, OUTER DIAMETER.  BOTH CRACKS ARE THROUGH FORWARD RETAINER AND CATENARY.   1 PASSES THROU	GH BOTH SEAL TEETH AND THE OTHER HAS STARTED DOWN THE SEAL WEB. (K)				2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
2005051600113	20050516	00113	SO  	2005	5	16	2005FA0000568    	2	20050401	G	8530	712BCA221	CYLINDER HEAD   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 6 CYLINDER	SEPARATED       	B			CTYR	O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			GL	21	901BA					414A0232	521421			THE NR 6 CYLINDER, LT ENGINE.  THE AC WAS RUNNING FINE AND ALL OF THE SUDDEN A VIBRATION WAS FELT.  INVESTIGATION:  THE 	HEAD WAS FOUND SEPARATED FROM CYLINDER.  THE HEAD WAS BEING HELD ON BY THE INTAKE PIPE AND EXHAUST.  THE ENGINE AND THIS	 CYLINDER HAD 72.4 TSMOH, RAM ENGINE; TISN 71-2BCA-221 SN 22537-26.  THIS IS A NEW RAM ENGINE WITH ECI NICKEL CYLINDERS.	  (K)			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005051600116	20050516	00116	SO  	2005	5	16	2005FA0000569    	2	20050315	G	8520	SA634503M010	BEARING         								CONT  	O550  	IO550F      	17042	SO  					CRANKSHAFT	DAMAGED         	B			O3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							284791R			UPON DISASSEMBLY IT WAS NOTED THAT THIS BEARING SHELL IS BROKEN.  IT IS LOCATED IN NR 2 FROM REAR SADDLE.  IT APPEARS TH	AT THE BEARING HAS WORKED AND IS POLISHED AS RESULT:  THE CRANKSHAFT, SN C159618N HAS OVERSIZED BLADE BUSHING BOSSES.  U	PON DISASSEMBLY, (LOOSE BUSHINGS) NOTE: FRETTING ON PARTING SURFACE AS A RESULT OF THE BEARING WORKING, THE BEARING TANG	 IN THE SADDLE HAS BEEN MALFORMED.								3	O			E3SO				 
2005051600117	20050516	00117	SO  	2005	5	16	2005FA0000570    	1	20050307	G	2820	3011849	LINE            			EMB   	110   	EMB110P2    	3260124	SO  										NACELLE	CRACKED         	B			EL6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	24AN					110318				FOUND FUEL BYPASS TUBE ASSY CRACKED WHERE TUBE WELDED TO FLARE END OF B-NUT FITTING.  TUBE APPEARS TO BE MFG WITH SMALLE	R RADIUS TO FIT INSIDE FLARE, CAUSING WEAK POINT.  SUGGEST CLOSER INSPECTION AT THIS AREA DURING ROUTINE INSPECTION AND 	PRESSURE CHECK WITH ELEC PUMPS.  NOTE: LINE ASSY LOCATED FROM FUEL CONTROL WAIT FITTING TO START CONTROL VALVE.  CAN BE 	PRESSURED W/ AC ELEC FUEL PUMPS.  (K)			1	L	7	2 	4T				A21SO   					 
2005051600121	20050516	00121	CE  	2005	5	16	2005FA0000571    	1	20050418	G	3220		STRUT           			CESSNA	195   	195A        	2073110	CE  										TAILWHEEL	STUCK           	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	23	1082D					7694				TAILWHEEL STRUT STUCK FULLY EXTENDED FOR LANDING.  SYSTEM DESIGN DOES NOT PERMIT STEERING WHILE STRUT IS IN THIS CONDITI	ON. (K)					1	H	7	1 	3R				A790    					 
2005051600122	20050516	00122	CE  	2005	5	16	2005FA0000572    	1	20050331	G	3260	1003810061	DOWNLOCK SWITCH 			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					NLG	INTERMITTENT    	B			AKGR	O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			CE	05	911CX					LJ830				DURING NORMAL GEAR EXTENSION, NO NOSE GEAR DOWN LOCK LIGHT INDICATION.  CYCLED GEAR SEVERAL TIMES WITH NO CHANGE.  MANUA	LLY EXTENDED GEAR AND OBTAINED GREEN INDICATION.  MAINTENANCE FOUND SWITCH INTERMITTENT. (K)					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2005051600142	20050516	00142	NE  	2005	5	16	2005FA0000573    	2	20050320	G	8520	304430	BOLT            			DOUG  	DC6   	C118A       	3021710	WP  	PWA   	R2800 	R280052W    	52026	NE  					CRANKSHAFT	BROKEN          	B			DA7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	351CE		1697 			44599				CRANKSHAFT CONNECTING BOLT BROKE CAUSING LOSS OF ENGINE POWER.  DAMAGE TO ENGINE INCLUDED REAR MAIN BEARING AND CRANKSHA	FT ASSY.  PROBABLE CAUSE COULD BE OVER TORQUE AT ASSY OR METAL FATIGUE.  PREVIOUS OVERHAUL AGENCY UNKNOWN AT THIS TIME. 	(K)				2	L	7	4 	4R	4	R		6A3     	5E8				 
2005051600137	20050516	00137		2005	5	16	2005FA0000574    	4	20050329	G	2565		LIGHT           	AIRCRUISERS 		AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					ESCAPE SLIDE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	762US				A9077	1358				THE ESCAPE SLIDE LIGHTS DID NOT WORK DUE TO THE CONNECTOR NOT FULLY HOME.  THE ELECTRICAL LOOM AND THE CONNECTOR WERE NO	T STOWED PROPERLY.  (EA33200501197) (K)					2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2005051600138	20050516	00138	EU  	2005	5	16	2005FA0000575    	1	20050404	G	2810	A319	PLACARD         			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					WING FUEL TANKS	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	762US					1358				DEBRIS (PLASTIC RIB AND MANHOLE DOOR IDENTIFICATION DECALS) FOUND ON THE INLET STRAINER OF THE LT AND RT WING FUEL TANK,	 NR 2 MAIN FUEL PUMP AFT SCREENS DURING C-CHECK.  OIT ISSUED BY AIRBUS AND IS APPLICABLE TO MSN1136. (K)					2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2005051700004	20050517	00004		2005	5	17	2005FA0000576    	4	20050329	G	2565	26C150911	QUICK DISCONNECT	AIRCRUISERS 		AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					ESCAPE SLIDE	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	762US				A9004	1358				WHILE CARRYING OUT A SAMPLE INFLATION ON THE AFT ENTRY DOOR, THE ESCAPE SLIDE FAILE TO RELEASE FROM THE PACK DUE TO THE 	QUICK DISCONNECT, PN 25C150911, WHICH CONNECTS THE SLIDE RELEASE CABLE TO THE RELEASE MECHANISM ON THE PACKBOARD ASSY BE	ING MISSING.(K)				2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2005051700005	20050517	00005		2005	5	17	2005FA0000577    	4	20050329	G	2565	26C150911	QUICK DISCONNECT	AIRCRUISERS 		AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					AFT RT SLIDE	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	762US				A9992	1358				DURING A C-CHECK, THE QUICK DISCONNECT WHICH CONNECTS THE SLIDE RELEASE CABLE TO THE RELEASE MECHANISM ON THE PACKBOARD 	ASSY WAS FOUND LOOSE.  THE ELECTRICAL LOOM WAS CONFIGURED FOR A LT DOOR. (K)					2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2005051700006	20050517	00006	NE  	2005	5	17	2005FA0000578    	2	20050420	G	7230	31042163	SPUR GEAR       			JETAIR	JETSTM	JETSTM4101  	1500501	EU  	GARRTT	TPE331	TPE33114GR  	01514	NE  					COMPRESSOR	WORN            	B			AV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	GMAJA					41032	P75048			FORWARD COUPLING STUB SHAFT NUT WAS FOUND FINGER TIGHT CAUSING VIBRATORY FRETTA ND ACCELLERATED WEAR WITH MATERIAL LOSS 	ON THE SPUR GEAR AND SUBSEUQUENT LOSS OF FUEL CONTROL SPUR GEAR DRIVE.  (K)					2	L	7	2 	4T	4	T	RT	A41NM   	E18NE				 
2005042700058	20050427	00058	SO  	2005	4	27	2005FA0000579    	1	20050320	G	5712	78475009	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C    	41514	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	705ER	2633 				2844058	L2995051A			DURING A 100HR. INSPECTION, A SMALL CRACK WAS FOUND IN THE RT. NOSE RIB PN-62021-005 AND -004. A MORE THOROUGH INSPECTIO	N REVEALED THAT AN ADDITIONAL CRACK, MUCH LARGER (ABOUT 4 INCES LONG), WAS FOUND ON THE RIB PN-78475-009 AND -008. THESE	 RIBS ARE INCLUDED IN THE MOUNTING ASSEMBLY FOR THE PN-95643-007 AND -006 AND BRACKET (MLG TRUSS). THE OPERATOR OF THIS 	AIRCRAFT OPERATES A FLEET OF 6 AIRCRAFT, AND ALL THE OTHER AIRCRAFT HAD SIMILAR CRACKS, ON BOTH LT AND RT WINGS. THE FLE	ET IS GROUNDED AND THE AFFECTED PARTS ARE BEING REPLACED.		1	L	7	1 	3O	3	O		2A13    	1E10				 
2005042700038	20050427	00038		2005	4	27	2005FA0000580    	4	20050311	G	3416	A30	ENCODER         			CESSNA	210   	T210N       	2073456	CE  										ALTIMETER	ERRATIC         	B				H				DEACTIVATE SYST/CIRCUITS				P			NO WARNING INDICATION     			CR	CRUISE         	1			NM	09	5434A					21063436				ALTITUDE OUTPUT BECAME ERRATIC, VARYING SEVERAL HUNDRED FT BOTH ABOVE AND BELOW THE ACTUAL ALTITUDE OVER A PERIOD OF 30 	MINUTES.  PROBABLY CAUSED BY INTERMITTENT HEATER THERMOSTAT.					1	H	7	1 	3O				3A21    					 
2005042700073	20050427	00073	SO  	2005	4	27	2005FA0000581    	1	20050322	G	5712	78475009	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	703ER	2743 				2844057	L2983151A			DURING A VISUAL INSPECTION, A SMALL CRACK WAS FOUND IN THE RT NOSE RIB.  A MORE THOROUGH INSPECTION REVEALED THAT AN ADD	ITIONAL CRACK, MUCH LARGER (ABOUT 4 INCHES LONG), WAS FOUND ON THE RIB. THESE RIBS ARE INCLUDED IN THE MOUNTING ASSEMBLY	 FOR THE BRACKET(MAIN GEAR TRUSS). THE OPERATOR OF THIS AIRCRAFT OPERATES A FLEET OF 6 OF THESE AIRCRAFT, AND ALL THE OT	HER AIRCRAFT HAD SIMILAR CRACKS, ON BOTH LT AND RT WINGS. THE FLEET IS GROUNDED AND THE AFFECTED PARTS ARE BEING REPLACE	D.		1	L	7	1 	3O	3	O		2A13    	1E10				 
2005050500048	20050505	00048	SO  	2005	5	5	2005FA0000582    	1	20050414	G	5101	89630004	CABLE           			PIPER 	PA46  	PA46350P    	7104602	SO  										UNKNOWN	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	DEZPA	360  				4622184				CABLE DISCONNECTED FROM CABLE PULL HANDLE. PROBABLY BAD CRIMP. SAME PROBLEM ENCOUNTERED ON OTHER AIRCRAFT OF THIS TYPE A	ND PA-46-310P AS WELL.					1	L	7	1 	3O			RT	A25SO   					 
2005051600001	20050516	00001	CE  	2005	5	16	2005FA0000583    	1	20050422	G	2822	MS2465823D	SWITCH          			BEECH 	90    	C90A        	1152911	CE  										COCKPIT	OVERHEATED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	6028Y	71   				LJ1728				DISCREPANCY ORIGINALLY AN INOPERATIVE LT BOOST PUMP. DURING THE OPS CHECK OF  REPLACEMENT BOOST PUMP, SWITCH WAS NOTED T	O BE INTERMITTENT. AFTER GAINING ACCESS TO SWITCH TERMINALS BY REMOVING THE LT FUEL BOOST PUMP SWITCH, TERMINALS WERE FO	UND IN AN OVERHEATED CONDITION, CONNECTIONS WERE LOOSE. SWITCH AND TERMINALS WERE REPLACED REMAINING SWITCHES, CB WERE I	NSPECTED, OTHER CONNECTIONS WERE ALSO FOUND LOOSE RT SIDE CB PANEL WAS ALSO REMOVED, ELEC COMPONENTS WERE ALSO INSPECTED	.		1	L	7	2 	3T			RT	3A20    					 
2005050300218	20050503	00218	GL  	2005	5	3	2005FA0000584    	1	20050405	G	7710		CONNECTOR       			CIRRUS	SR    	SR22        	2130001	GL  										TACH INDICATOR	DIRTY           	B				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			EA	07	529HH					1228				AT HIGH POWER SETTINGS THE RPM AND TEMPERATURE INDICATIONS WOULD BECOME INTERMITTENT. INVESTIGATION REVEALED THE EGT/CHT	 HARNESS ON THE RT BANK OF CYLINDERS WAS ROUTED TOO CLOSE TO THE EXHAUST SYSTEM AND WAS BURNING THROUGH THE INSULATION O	F THE WIRES. CONNECTOR FOR THE TACH INDICATION WAS DISASSEMBLED, CLEANED, AND REASSEMBLED. OPS CHECK FOLLOWING THIS WAS 	OK.			1	L	7	1 	3O			NT	A00009CH					 
2005050300216	20050503	00216	SO  	2005	5	3	2005FA0000585    	1	20050404	G	3213	6531904	STRUT           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	MLG	BROKEN          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	09	83364	9047 				288390035	L3013736A	22486K		FAILURE OF THE (CAST) MAIN LANDING GEAR STRUT CYLINDER.  CRACK IN UPPER SCISSOR ATTACHMENT RESULTED IN LOSS OF GEAR AND 	STRUT ASSY DURING TAKE-OFF.					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2005050500038	20050505	00038		2005	5	5	2005FA0000586    	4	20050410	G	6122	C290D4T2	GOVERNOR        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					PROPELLER	PLUGGED         	P				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			GL	17	5130A	1200 	1200 			21063280	512211			DEPARTING SOFT FIELD POWER AND RPM FINE ON INITIAL ROLL.  AFTER WHEELS BECAME LIGHT, POWER BLED OFF, YIELDING NO FURTHER	 ACCELERATION OR LIFT.  ABORTED TAKE-OFF, NOSE WHEEL GOUGED INTO SOFT SAND, BREAKING NOSE FORK, PITCHING NOSE OF AIRCRAF	T INTO DIRT.  PROP BLADES BENT, MINOR DAMAGE TO NOSE FAIRINGS.  KEEL CHANNEL WARPED, NOSE GEAR DOORS BENT.  ENGINE CRANK	 DIALS IN LIMITS.  WILL BE TORN DOWN FOR SUDDEN STOPPAGE.  SUSPECT GOVERNOR RETURN MAY HAVE PLUGGED, CAUSING PROP TO INC	REASE PITCH.		1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005051100224	20050511	00224	SO  	2005	5	11	2005FA0000587    	2	20050402	G	7200	TSIO360B	ENGINE          			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360B    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LEFT	DESTROYED       	P				A				UNSCHED LANDING         				A			FLAME/FIRE                			CR	CRUISE         	1			SW	09	328RG	2310 				347570061	303065	AN1145		AFTER TAKE-OFF THE LT ENGINE SUFFERED A CATASTROPHIC FAILURE. TWO CONNECTING RODS (NR 5, 6) FAILED AND KNOCKED A HOLE IN	 THE CRANKCASE. THE RESULTING HOLE IN THE CRANKCASE WAS THE LOCATION OF A FIRE WHICH BURNED THROUGH THE COWLING AND CONT	INUED BURNING.  THE AIRCRAFT WAS LANDED SAFELY.   AFTER LANDING THE FIRE WAS EXTINGUISHED.				1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
2005051000139	20050510	00139	GL  	2005	5	10	2005FA0000588    	1	20050420	G	5341	2057000103	WING ROOT       			DIAMON	DA20  	DA20C1      	2990001	GL  										LEFT	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	929AF	969  				C0195				(A) BEARING IN LT WING FOUND LOOSE WITH .0625 INCH PLAY UP AND DOWN. NO PLAY FORE AND AFT. PASTE FROM BEARING ATTACH FOU	ND LOOSE IN WING BAY. REMOVED BEARING AND FOUND NO DAMAGE TO END RIB. FOUND WITH WING OFF DURING 1000 HOUR INSPECTION.					1	L	7	1 	3O			NT	TA4CH   					 
2005042700039	20050427	00039		2005	4	27	2005FA0000590    	4	20050314	G	3416	AK350	ENCODER         																	ALTIMETER	DEFECTIVE       	B				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			NM	09										STATIC AIR INPUT LEAKS INTO CASE OF UNIT.  UNIT IS NEW FROM STOCK.																			 
2005042700040	20050427	00040		2005	4	27	2005FA0000591    	4	20050314	G	3416	AK350	ENCODER         																	ALTIMETER	DEFECTIVE       	B				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			NM	09										STATIC AIR INPUT LEAKS INTO CASE OF UNIT.  UNIT IS NEW FROM STOCK.																			 
2005042700131	20050427	00131		2005	4	27	2005FA0000593    	4	20050325	G	3420	2300626020	MOTOR           	COLLINS     	ADI85A      															INDICATOR	INTERMITTENT    	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09					38					THE MOTORS HAVE HIGH RESISTANCE BETWEEN THE BRUSHES AND ARMATURE OF THE MOTOR. THIS CAUSES THE MOTOR TO STICK INTERMITTE	NTLY, CAUSING A FALSE ATTITUDE DISPLAY IN THE COCKPIT. THIS PROBLEM BEGAN WITH MOTORS DATE CODED 04/04 MANUFACTURED BY M	OOG, INC.																	 
2005050400069	20050504	00069	WP  	2005	5	4	2005FA0000594    	1	20050408	G	2432	AD430B034LB03	BATTERY         			DOUG  	DC9   	DC983       	3022083	WP  										MASTER	OVERHEATED      	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			EX	EXTERNAL LOAD  	1			GL	03	315FV					49707				EXTREME SMOKE REQUIRING EVACUATION OF AIRCRAFT.  BATTERIES SHOW EVIDENCE OF EXCESSIVE HEAT.						2	L	7	2 	4F			RT	A6WE    					 
2005050400070	20050504	00070	WP  	2005	5	4	2005FA0000595    	1	20050408	G	2432	AD430B034LB03	BATTERY         			DOUG  	DC9   	DC983       	3022083	WP  										MASTER	OVERHEATED      	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	03	315FV					49707				EXTREME SMOKE REQUIRING EVACUATION OF AIRCRAFT.  BATTERIES SHOW EVIDENCE OF EXCESSIVE HEAT.						2	L	7	2 	4F			RT	A6WE    					 
2005050400071	20050504	00071	WP  	2005	5	4	2005FA0000596    	1	20050408	G	2432	AD430B034LB03	BATTERY         			DOUG  	DC9   	DC983       	3022083	WP  										ZONE 100	OVERTEMP        	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	03	315FV					49707				EXTREME SMOKE REQUIRING EVACUATION OF AIRCRAFT.  BATTERIES SHOW EVIDENCE OF EXCESSIVE HEAT.						2	L	7	2 	4F			RT	A6WE    					 
2005050400072	20050504	00072	WP  	2005	5	4	2005FA0000597    	1	20050408	G	2432	AD430B034LB03	BATTERY         			DOUG  	DC9   	DC983       	3022083	WP  										ZONE 100	OVERTEMP        	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			EX	EXTERNAL LOAD  	1			GL	03	315FV					49707				EXTREME SMOKE REQUIRING EVACUATION OF AIRCRAFT.  BATTERIES SHOW EVIDENCE OF EXCESSIVE HEAT.						2	L	7	2 	4F			RT	A6WE    					 
2005050400114	20050504	00114	SO  	2005	5	4	2005FA0000598    	2	20050413	G	8530	532200	O-RING          								CONT  	O520  	IO520*      	17032	SO  					CYLINDER BASE	IMPROPER PART   	G				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			GL	13										INCORRECT CYLINDER BASE O-RINGS INSTALLED AT TOP-OVERHAUL. THE O-RINGS INSTALLED APPEARED TO BE THE SIZE FOR THE ENGINE.	 THESE LARGER CROSS SECTION SEALS WERE PINCHED BETWEEN THE CYLINDER BASE AND THE CRANKCASE. THIS RESULTED IN A LOW THROU	GH-BOLT TORQUE. NUMBERS 2 AND 3 MAIN BEARINGS SPUN, DISRUPTING OIL FLOW TO THE NUMBER 4 CONNECTING ROD. THE NUMBER 4 CON	NECTING ROD FAILED AND PENETRATED THE CASE.								3	O			E5CE				 
2005050400053	20050504	00053	NE  	2005	5	4	2005FA0000599    	2	20050401	G	7200	30729202	BEARING RACE    			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					ENGINE	FRACTURED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07			1052 				P77111C			ENGINE RETURNED TO SERVICE CENTER FOLLOWING COMMANDED SHUTDOWN IN FLIGHT DUE TO LOW OIL PRESSURE.  DURING INSPECTION A F	RACTURED CAGE AND OUTER RACE WAS FOUND ON A FORWARD PLANETARY ROLLER BEARING.					2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2005050400052	20050504	00052	CE  	2005	5	4	2005FA0000600    	1	20050412	G	5730	67221463	SKIN            			CESSNA	750   	750         	2076810	CE  										RT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	906QS					7500206				DURING SCHEDULED INSPECTION FOUND SEVERAL SMALL SPOTS OF CORROSION ON BOTH LEFT AND RIGHT LOWER WING SKINS. PN OF THESE 	WING SKINS ARE: 67221463, 4 , 67221663,4 AND 67221723. SOME OF THESE AREAS EXCEEDED .007 INCH DEPTH. CONTACTED MFG ENGIN	EERING FOR REPAIR DISPOSITION. CAUSE OF CORROSION UNKNOWN.				2	L	7	2 	4J			RT	T00007WI					 
2005050300215	20050503	00215		2005	5	3	2005FA0000601    	4	20050404	G	3420	2300626020	MOTOR           	COLLINS     	ADI85A      															ADI	INTERMITTENT    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09					793					CREW REPORTED COMMAND FUNCTION STICKING AND ADI DISPLAYS CMD FLAG.  INSPECTION REVEALED MOTOR HAD HIGH START VOLTAGE. MO	TOR DATE CODE IS 04/04. MOTOR WAS INSTALLED NEW 11/2004.																		 
2005051900133	20050519	00133	EU  	2005	5	19	2005FA0000602    	1	20050413	G	2436	R25VON	VOLT REGULATOR  			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  						INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	864AF					85004	L2826348A			AFTER 20 MINUTES INTO ENGINE, START CHARGING SYSTEM STILL SHOWING 7 AMPS OF CHARGING.  MAINT TECH FOUND VLOTAGE REGULATO	R WAS NOT WORKING.  VOLTAGE REGULATOR WAS REPLACED AND OPERATIONAL CHECK OF CHARGING SYSTEM CHECK, GOOD.  NO RECOMMENDAT	IONS AT THIS TIME.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2005051900134	20050519	00134	EA  	2005	5	19	2005FA0000603    	2	20050414	G	7314	RG9570K1M	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					FUEL SYSTEM	MALFUNCTIONED   	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	117  				85001				PILOT REPORTED THAT IDLE RPM WAS TOO HIGH, 850 RPM.  WHILE TECH WAS TRYING TO ADJUST IDLE, FOUND THAT THE FUEL PRESSURE 	WAS LOW - 16 PSI AND UNABLE TO ADJUST.  REPLACEMENT OF ENGINE DRIVEN FUEL PUMP WAS REQUIRED.  RECOM TO ADD A METHOD PLUS	 DATA FOR MAKING ADJUSTMENT IN THE FIELD.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2005051900135	20050519	00135	NE  	2005	5	19	2005FA0000604    	1	20050401	G	7330	3033606	LINE            			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					ENG FUEL	CHAFED          	B			CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	780P					760359	36099			FUEL LINE FROM FUEL CONTROL TO FUEL FLOW TRANSMITTER CHAFED APPROCIMATELY 30 PERCENT THROUGH THE WALL THICKNESS AT THE P	OINT WHERE IT PASSES THROUGH FRONT FIRE SHIELD.  POOR CLAMPING ARRANGEMENT AND PASS THROUGH HOLE DESIGN IN FIRE SHIELD A	RE CAUSE OF CHAF AND POTENTIAL FIRE HAZZARD.  SUGGEST MFG REDESIGN CLAMPING AND PASS THROUGH HOLES.  (K)				1	G	7	2 	4U	4	U		H1NE    	E4EA				 
2005051900136	20050519	00136	CE  	2005	5	19	2005FA0000605    	1	20050408	G	2435	23048016	STARTER GEN     			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					NR 2 ENGINE	INOPERATIVE     	B			XUPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	71EN		608  			LJ632				AFTER START, NR 2 GENERATOR CAME ON LINE AND WAS CARRING A LOAD.  NR 2 GEN LOAD METER SHOWED HIGH AMP SPIKE AND DROP OFF	  LINE, WITH IN-OP LIGHT COMING ON.  REPLACED STARTER GEN, SYSTEM OPS TESTED GOOD.  (K)					1	L	7	2 	3T	3	T		3A20    	E2NE				 
2005051900137	20050519	00137	CE  	2005	5	19	2005FA0000607    	1	20050401	G	5712	9511003119	RIB             			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LT WING	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	128WS	674  				TH1982				DURING SCHEDULED ANNUAL INSPECTION, FOUND LT WING BATT RIB AFT ANGLE AT IB MLG DOOR AFT ATTACH POINT CRACKED.  HAVE NOTE	D SIMILAR CRACKING IN OTHER LOW-TIME RAC MODEL 58 AIRCRAFT.  CRACKING SEEMS TO BE RELATED TO INSTALLATION OF MACHINED AL	UMINUM DOORS THAT REPLACED OLDER STYLE RIVETED CONSTRUCTION DOORS.  SUSPECT STIFFNESS OF NEWER-STYLE CONSTRUCTION DOORS 	TRANSFERRING INCREASED LOADS TO AIRFRAME STRUCTURE.  ADJACENT DOOR ATTACH ANGLES REPLACED FOR CRACKING AT 266.7 HRS TTAF	.  RECOMMEND CLOSE INSP OF WING RIB ANGLES AT IB DOOR ATTACH POINTS EACH ANNUAL/ 100 HR INSP UNTIL ISSUE RESOLVED BY MFG	 EO. (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005051900138	20050519	00138		2005	5	19	2005FA0000608    	1	20050406	G	4920		BLADE           																	COMPRESSOR WHEEL	FATIGUED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05					031365103481					THIS IMPELLER HAS EXPERIENCED WHAT LOOKS LIKE HIGH CYCLE FATIGUE WITH A VERY LOW TT ON THE UNIT.  IT APPEARS TO HAVE FAI	LED DUE TO WHAT STARTED AS A FATIGUE CRACK AND RESULTED IN A LARGE PIECE OF THE IMPELLER COMING OFF.  THIS IMPELLER AND 	ANOTHER WERE PURCHASED WITHIN 30 DAYS OF EACH OTHER AND HAVE S/N THAT ARE 2 DIGETS OFF FROM THE OTHER.																	 
2005052400014	20050524	00014	CE  	2005	5	24	2005FA0000609    	1	20050422	G	7120	04511201	MOUNT           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200*       	17020	SO  					RT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	63581					15077410				100 HOUR INSPECTION, RT LOWER ENGINE MOUNT TUBE CRACKED.  CRACK LOCATED WITHIN 1 INCH OF NOSE WHEEL STRUT SUPPORT CRACK,	 .7500 INCH IN LENGTH AROUND CIRCUMFERENCE OF TUBE.  REPLACED MOUNT. (K)					1	H	7	1 	3O	3	O		3A19    	E252				 
2005052400015	20050524	00015		2005	5	24	2005FA0000610    	4	20050412	G	3197		WIRE            			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					ANNUNCIATOR	BROKEN          	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2116X					18281318				FOUND ORANGE WIRE FOR THE LOW VOLT ANNUNCATOR FOR THE G-1000 BROKEN INSIDE THE J-BOX WOULD NOT CAUSE THE ANNUNCATOR TO L	IGHT UP ON THE PFD (PILOTS FLIGHT DISPLAY).  APPEARS WIRE HAVE CHAFED ON J-BOX TO BREAK WIRE.  ADDRESSED AND CORRECTED A	S REQUIRED.  (CE07200512733)  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400016	20050524	00016	CE  	2005	5	24	2005FA0000611    	1	20050301	G	7797		PIN             			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					TRANSDUCER	LOOSE           	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2116X	75   				18281318				G-1000-3 PIN CONNECTOR FOR MANIFOLD PRESSURE TRANSDUCER, THE PINS WILL GET LOOSE AND CAUSE THE MANIFOLD PRESSURE INDICAT	ION TO JUMP FROM 7.7 TO 55 MP PSI.  TROUBLESHOT, WITH THIS IN THE FUTURE DUE TO VIBRATION OF AIRCRAFT.  NOTE: NEVER HAD 	A RED-X OVER MP INDICATION ON LRU.  (CE07200512739) (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400017	20050524	00017	CE  	2005	5	24	2005FA0000612    	1	20050301	G	7997		PIN             			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					TRANSDUCER	LOOSE           	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2116X	75   				18281318				G-1000-3 PIN CONNECTOR FOR OIL PRESSURE TRANSDUCER, THE PINS WILL GET LOOSE AND CAUSE THE OIL PRESSURE INDICATION TO JUM	P FROM 45 TO 110 PSI.  TROUBLESHOT, RESET PIN TO SHRINK (SHIP SIDE).  SUSPECT WILL HAVE PROBLEMS WITH THIS IN THE FUTURE	 DUE TO VIBRATION OF AIRCRAFT.  NOTE: NEVER HAD A RED-X OVER OIL PRESSURE INDICATION ON LRU.  (CE07200512740) (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400020	20050524	00020		2005	5	24	2005FA0000613    	4	20050429	G	2200	065001802700	SERVO           			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					RT WING AUTOPILO	CHAFED          	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2116X	191  				18281318				DURING MFG 200 HOUR INSPECTION FOUND THE AUTOPILOT SERVO CABLE IN THE RT WING RUBBING ON SERVO CABLE GUARD ALMOST RUBBIN	G THRU ONE LEG OF GUARD.  INSPECTED CABLE FOUND OK.  INSTALLED A NEW GUARD AND CLOCKED TO CORRECT POSITION ON SERVO.  (C	E07200512741) (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400021	20050524	00021	CE  	2005	5	24	2005FA0000614    	1	20050412	G	7797	62803SG513	CONNECTOR       			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					TACH GENERATOR	LOOSE           	B			Z08R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CE	07	21454	576  				18281228				TACHOMETER INDICATION JUMPS AROUND IN FLIGHT.  INSTALLED A NEW TACHOMETER CONNECTOR, IAW MFG SL.  OPS CHECK OK.  (CE0720	0512734) (K)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400023	20050524	00023	CE  	2005	5	24	2005FA0000615    	1	20050412	G	7722	86317	PROBE           			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					EGT	INOPERATIVE     	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	21454	576  				18281228				DURING LEAN FIND FOR G-1000 WOULD NOT INDICATE  NR1 AND NR2 ENGINE CYLINDERS.  TROUBLESHOT, USED EGT/CHT TESTER AND FOUN	D PROBES BAD ALSO SHIP SIDE CONNECTOR WAS ALSO BAD, FOUND SCREWS LOOSE INSIDE CONNECTOR.  REPLACED NR1 AND NR2 ENGINE CY	LINDER PROBES AND CORRECTED CONNECTOR ON SHIP SIDE BY CLEANING AND TIGHTENING SCREWS, OPS CHECK OK.  (CE07200512735) (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400024	20050524	00024	CE  	2005	5	24	2005FA0000617    	1	20050412	G	2842	S38524	PROBE           			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					FUEL QTY	FAILED          	B			Z08R	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CE	07	21454	576  				18281228				DURING FLIGHT, FUEL INDICATIONS WOULD RED-X OUT AND INDICATIONS SHOWING QUANITY JUMPED AROUND LT AND RT SIDE.  TROUBLESH	OT, AND REPLACED PROBES/ SENDERS IAW MFG.  CALIBRATED IAW MFG MM.  OPS CHECK OK.  NOTE: NEED IMPROVEMENT IN TROUBLESHOOT	ING PROCEDURES IN MM AND POSSIBLE BREAKOUT BOXES TO AID IN TROUBLESHOOTING.  G-1000 AIRCRAFT.  (CE07200512737) (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400025	20050524	00025	EA  	2005	5	24	2005FA0000618    	2	20050425	G	8550	LW13792P50	SEAL            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540D4A5   	41532	EA  					CRANKSHAFT	FAILED          	D			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	9241P					244740				UPON TRYING TO INSTALL THE SOLID OIL SEAL OVER THE CRANKSHAFT FLANGE, THE SEAL FAILED AND TOTALLY SEPERATED IN A STRAIGH	T LINE 90 DEGREES TO THE FACE OF THE SEAL.  VERY LITTLE FORCE WAS BEING APPLIED TO THE INSTALLING TOOL WHEN THE SEAL FAI	LED.  THIS WAS SECOND FAILURE OF THE SAME LOT.  PRODUCT SHELF LIFE EXPIRATION DATE 4Q07.  ACCORDING TO MFG THE SHELF LIF	E IS 12 QUARTERS.  (K)			1	L	7	1 	3O	3	O		1A15    	1E4				 
2005052400026	20050524	00026	EA  	2005	5	24	2005FA0000619    	2	20050420	G	7320	RA5AD2	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE FUEL	INOPERATIVE     	B				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	25	494JB					172S9099	L3034351A	JHA7660		IT OCCURRED WHEN PERFORMEING AN OUTGOING ENGINE RUN.  WHEN THE THROTTLE WS PULLED BACK TO IDLE, ON THE S TOP OF THE SERV	O, WHEN WE PULLED A LITTLE HARDER, IT CAUSED THE ENGINE TO STALL AND SHUTDOWN INSTEAD OF JUST DECREASING A FEW MORE RPM.	  RECOMMEND SB TO CHECK ALL MFG AC FOR THIS CONDITION.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005052400027	20050524	00027	SO  	2005	5	24	2005FA0000620    	2	20050413	G	8550	6009	GASKET          			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ENGINE	MISSING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	2430Y					32R8513002	RL2259448A			ON INITIAL GROUND RUN, AFTER INSTALLING FACTORY REMFG, OIL WAS LEAKING FROM ACCY CASE UNDER FUEL PUMP.  WHEN FUEL PUMP W	AS REMOVED TO REPLACE GASKET, IT WAS FOUND THAT THERE WAS NO GASKET INSTALLED.  INSTALLED NEW GASKET, LEAK CHECK GOOD.  	PROBABLE CAUSE: COMPLACENCE, DISTRACTION, OR INDIFFERENCE.  (K)				1	L	7	1 	3O	3	O		A3SO    	1E4				 
2005052400028	20050524	00028	CE  	2005	5	24	2005FA0000621    	1	20050411	G	2730	58151035CR	CONTROL CABLE   			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520F   	17032	SO  					LT ELEVATOR	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5388J					4040666				DURING INSPECTION, FOUND CABLE TO BE BLENDED AT FAIRLEAD APPROX 6 INCHES FROM AFT END OF CABLE.  PROBABLE CAUSE FROM NEW	 STYLE (STAINLESS STEEL) CABLE.  NEW STYLE LASTED ONLY FRACTION OF TIME AS OLD STYLE.  (SW01200504154) (K)					1	L	7	2 	3O	3	O	RT	A25CE   	E7CE				 
2005052400029	20050524	00029	CE  	2005	5	24	2005FA0000622    	1	20050420	G	3520	100801D40218	BUSHING         	BEECH       		BEECH 	90    	F90         	1152909	CE  										CONTROL CABLE	MISSING         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	189JR					LA61				INVESTIGATED PASSENGER OXYGEN SYSTEM MASKS DEPLOYING WHEN SYSTEM ARMED.  FOUND MANUAL CONTROL CABLE BUSHING MISSING AND 	PREVENTING MANUAL CONTROL CABLE FROM OPERATING VALVE THROUGH FULL TRAVEL.  ALSO, FOUND WIRING TO PASSENGER OXYGEN SHUTOF	F VALVE AND BAROMETRIC SWITCH NOT CONNECTED CORRECTLY.  REWIRED BAROMETRIC SWITCH AND OXYGEN SHUTOFF VALVE AND CONTROL I	AW MM.  SYSTEM OPS CHECK OK.  HAVE PREVIOUSLY NOTED SIMILAR PROBLEMS FOLLOWING SCHEDULED MAINT THIS AREA.  (K)			1	L	7	2 	4T				A31CE   					 
2005052400007	20050524	00007	EU  	2005	5	24	2005FA0000624    	1	20050503	G	2780	1075D1003	FCU             			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					SLATS	OUT OF TOLERANCE	Z				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	29	B2001		22   			119				THE SLATS FAILED TO EXTEND WHILE PILOTS WERE PERFORMING THE INSPECTIONS BEFORE TAKEOFF.  THE SLATS LOCKED OUT WHILE MECH	ANIC PLACED THE FLAP/SLAT SELECTOR TO DN POSITION. SLAT UNBALANCE LIGHT CAME ON SIMULTANEOUSLY.  TROUBLESHOOTING FOUND T	HE FSECU OUTPUT VOLTAGE WAS OUT OF TOLERANCE.				2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2005052400128	20050524	00128	CE  	2005	5	24	2005FA0000625    	1	20050415	G	3210	07416321	BUSHING         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					LT MLG	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	812MC	385  				18281208				INNER RUBBER/ PLASTIC MATERIAL NOTED PROTRUDING FROM BOTH SIDES OF BUSHING.  MATERIAL INSIDE BUSHING SPLITTING IN SEVERA	L AREAS.  LT MLG BUSHING ONLY, RT MLG BUSHING APPEARS NORMAL. (K)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052400129	20050524	00129	EA  	2005	5	24	2005FA0000626    	2	20050425	G	7314	ES10382807	CAPACITOR       			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	7694V	70   			C030929	177RG0904	L1552651A			THE MAGNETO WAS OVERHAULED 70 HOURS AGO, THE CAPACITORS WERE SUPPLIED BY OVERHAULER.  THE OVERHAUL WAS DONE AND CAPACITO	RS ARE FAA PMA`D.					1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005052400131	20050524	00131	EU  	2005	5	24	2005FA0000627    	1	20050422	G	7920	30032871	LINE            			AMD   	FALC20	FALCON      	2720302	EU  										ENGINE OIL	CRACKED         	B			AV4R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			WP	07	200GT					137				LOW OIL PRESS IN FLIGHT, PRECAUTIONARY SHUTDOWN PERFORMED.  23 PSI LOWEST READING ON OIL PRESS INDICATOR.  OIL PRESS NEV	ER WENT TO -0- PSI. PRECAUTIONARY SHUTDOWN PERFORMED ON NR2 ENG.  DECLARED EMERGENCY.  ENG ROTATION WAS NORMAL AFTER SHU	TDOWN.  OIL QTY INDICATION AT BOTTOM OF DIPSTICK WHEN CKD ON ARRIVAL.  OIL LEAKING IN FAN BYPASS AREA OF ENG.  FOUND OB 	SURFACE OIL COOLER, DISCOVERED BOTH AFT MNT BRKTS CRACKED.  REPLACED BOTH BRKTS.  REPLACED BOTH IB AND OB OIL TUBES.  FO	UND CRACKS IN UPR, LWR FAIRING, AFT OF FRONT FRM, REPLACED FAIRINGS.  FOUND CRACKS IN BOLT HOLES ON 3 DAGMAR ASSY, REPLA	CED.  FWD SEAL FOR COMP SEC OUTER COWL WORN, REPLACED SEAL.  ENG RUN AND LEAK CHECK PERFORMED, NO LEAKS NOTED.	2	L	7	2 	4F				A7EU    					 
2005052400133	20050524	00133	CE  	2005	5	24	2005FA0000628    	1	20050425	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			WP	07	8268T	536  				CE1547				PILOT SELECTED GEARDOWN AND NOTHING HAPPENED, PILOT THEN CYCLED GEAR SELECTOR TWICE THEN GEAR WENT DOWN, AC RETURNED TO 	BASE.  ON TROUBLESHOOTING, MECHANIC CYCLED GEAR 4 TIMES THEN RELAY FAILED, PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALL	ED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005052400134	20050524	00134	CE  	2005	5	24	2005FA0000629    	1	20050425	G	3200	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	A				UNSCHED LANDING         				O			OTHER                     			AP	APPROACH       	1			WP	07	5521A	799  				CE1338				PILOT SELECTED GEAR UP AND NOTHING HAPPENED, AIRCRAFT RETURNED TO BASE.  ON TROUBLESHOOTING, MECHANIC CYCLED GEAR (8) TI	MES THEN RELAY FAILED, PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005052400136	20050524	00136	CE  	2005	5	24	2005FA0000630    	1	20050127	G	3040	2SC1120A	RELAY           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D1      	52060	NE  					WINDSHIELD HEAT	LOOSE           	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			EA	17	430CW					RK30				CREW SQUAWKED ELEC FUMES AND FOUL ODOR IN COCKPIT.  ODOR SEEMED TO LET UP AFTER BATTERY PLACED IN EMERG AND BOTH GENERAT	ORS PLACED IN EMERG.  MAINT FOUND RT WINDSHIELD HEAT CURRENT SENSE RELAY (L102S) TERMINAL B AND APPROX 2 INCHES OF WIRE 	INSULATION TO OVERHEAT AND MELT WITH RT WINDSHIELD HEAT ON AND WINDSHIELD SUBJECTED TO COLD TEMP.  FOUND WIRE AMP END SE	CURED TO SUBJECT RELAY TERMINAL STUD WITH FLAT NUT AND WASHER.  NO LOCK WASHER WAS INSTALLED.  LACK OF A LOCK WASHER UND	ER NUT ENABLED TERMINAL NUT TO BECOME LOOSE AND ARC UNDER CURRENT LOAD.  REPLACED DEFECTIVE WIRE AND RELAY WITH NEW.  UT	ILIZED NEW LOCK WASHERS UNDER NEW NUTS AT REPLACEMENT RELAY TERM STUDS.  COCKPIT SYS CHECKD NORMAL. (EA172005057764) (K)	2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2005052400137	20050524	00137		2005	5	24	2005FA0000631    	4	20050228	G	3418	602517	RELAY           			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	STALL WARNING	BURNED          	B			ECWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	802MM					4697148	PCERM0158	HH1616		HEAT REMOTE SWITCH MODULE FOR STALL WARNING HEAT (LIFT DETECTOR) HAD SHORTED CAUSING SMOKE IN CABIN/FLIGHT DECK DURING F	LIGHT OPERATION.  SB 1132 WAS ACCOMPLISHED ON 6/25/2003, AC TT 81.2 HOURS.  (K)					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA	5	C	P10NE	 
2005052400139	20050524	00139	CE  	2005	5	24	2005FA0000632    	1	20050407	G	5751	97164	BALANCE WEIGHT  			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AILERON	LOOSE           	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	1VA	6281 				S5500143				WHILE CONDUCTING A PHASE 2 INSP, INSPECTOR NOTICED COCK-EYED BOLT HEADS ON AILERON.  FURTHER INVESTIGATION, INCLUDING RE	MOVAL OF AILERONS, FOUND STATIC BALANCE WEIGHTS VERY LOOSE.  STACK OF WEIGHTS HAD MUCH CORROSION, WHICH CAUSED THE ATTAC	H HOLES TO ENLARGE, THEREFORE CAUSING STACK OF WEIGHTS TO BE VERY LOOSE.  DETAILED INSP OF THIS AREA NOT ON ANY INSPECTI	ON FORM.  NEW PARTS INSTALLED.  SUGGEST OPERATORS OF THIS MODEL AC, REMOVE AILERONS AND COMPLETE DETAILED INSPECTION OF 	THESE WEIGHTS.  (EA21200505634) (K)		1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2005052400142	20050524	00142	CE  	2005	5	24	2005FA0000633    	1	20050419	G	2510	MS27039104	SCREW           			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					CREW SEAT	LOOSE           	B			JZ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	300JD	1389 				7500202				SCREW WAS FOUND LOOSE ON BOTH PILOT AND CO-PILOT SEATS ON 2 SEPARATE OCCASIONS, 6 MONTHS APART.  THE SCREWS WERE RE-TIGH	TENED ON BOTH OCCASIONS THIS PROBLEM IS SIGNIFICANT DUE TO THE FACT THAT THE POSSIBLE FAILURE MODE COULD BE LOSS OF SEAT	 LOCKING CAPABILITY AND THE CREW SEAT BEING FREE TO MOVE FORE AND AFT, THAT A LOCKING FEATURE BE USED FOR THIS SCREW SUC	H AS A LOCK WASHER OR LOCTITE COMPOUND. (K)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005052400143	20050524	00143	NE  	2005	5	24	2005FA0000634    	1	20050225	G	7810		CLAMP           			STOLAC	UC1   	UC1         	9220102	NE  	LYC   	O360  	IO360A1A    	41514	EA  					TAILPIPE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	65NE					023				LT ENGINE IB EXHAUST TAILPIPE CRACKED, EXPELLING HEAT INTO ENGINE COMPARTMENT, BURNING PAINT ON COWLING.  PART FAILURE O	CCURRED BECAUSE OF BROKEN SUPPORT CLAMP, NO PN AVAILABLE DUE TO THE LIMITED PRODUCTION OF THIS AIRCRAFT ON EITHER EXHAUS	T TAILPIPE OR SUPPORT CLAMP.  SUSPECTED CAUSE OF FAILURE IS FROM ENGINE VIBRATION AND SHOCK LOADS IMPOSED BY WATER OPERA	TIONS.  ENTIRE EXHAUST SYSTEM SHOULD BE INSPECTED AT EACH 50, 100 HOUR AND ANNUAL INSPECTION SPECIFICALLY THE REAR SUPPO	RT CLAMPS FOR CRACKS AND DETERIORATION.  (K)		1	H	7	2 	3O	3	O		A6EA    	1E10				 
2005052400144	20050524	00144		2005	5	24	2005FA0000635    	4	20050204	G	3452	KT76C	TRANSPONDER     			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ATC	OUT OF ALIGNMENT	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	463CM	3138 				17280855				TRANSPONDER CAVITY BELOW TRANSMIT POWER TOLERANCE.  ALIGNMENT CORRECTS PROBLEM, BUT THIS CAUTION SHOULD NOT BE NEEDED AT	 THIS TIME.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005052400145	20050524	00145	NE  	2005	5	24	2005FA0000636    	1	20050505	G	3020		WIRE            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					BELLMOUTH HEAT	BURNED          	D			P7ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	22CP					760530				ENGINE ANTI-ICE SYSTEM, ENGINE HEATED INTAKE BELLMOUTH AND SNOW BLANKET.  MAINT FOUND BURNED WIRE AT PLUG J701 AND P701 	(PIN A) 16 GAGE WIRE.  THEY ALSO FOUND THIS WIRE WAS FED BY A 35 AMP COCKPIT DC PRIMARY BUSS CIRCUIT BREAKER THROUGH A 1	0 GAGE WIRE TO PLUG J3004K AND P3004K PINS F AND C.  THE 16 GAGE WIRES (2EA) WAS BUTT CONNECTED TOGETHER TO SINGLE 10 GA	GE WIRE.  ONE OF 16 GAGE WIRES WAS BURNED COMPLETELY THROUGH.  UPON REPAIRING, BURNED WIRE, MECHANIC FOUND THAT 10 GAGE 	AND 16 GAGE WIRE SHOWS SIGNS OF COPPER OXIDATION IN COLOR, BRITTLE TO TOUCH AND SILVER PLATING ON WIRE WAS FLAKING OFF. 	 FURTHER INVESTIGATION SHOWS THIS MAY BE A MFG DEFECT OF WIRE.  FURTHER INVESTIGATION ONGOING WITH MFG OF AC.  (K)	1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2005052400146	20050524	00146	NE  	2005	5	24	2005FA0000637    	1	20050505	G	3020		WIRE            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					BELLMOUTH HEAT	BURNED          	B			P7ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	66CP					760532				ENGINE ANTI-ICE SYSTEM, HEATED INTAKE BELLMOUTH, HEATED SNOW BLANKET.  MAINT FOUND BURNED WIRE AT PLUG J701 AND P701 (PI	N A) 16 GAGE WIRE.  THEY ALSO FOUND THIS WIRE WAS FED BY A 35 AMP COCKPIT DC PRIMARY BUSS CIRCUIT BREAKER THROUGH A 10 G	AGE WIRE TO PLUG J3004K AND P3004K PINS F AND C.   THE 16 GAGE WIRES (2 EA) WAS BUTT CONNECTED TOGETHER TO SINGLE 10 GAG	E WIRE.  ONE OF 16 GAGE WIRES WAS BURNED COMPLETELY THROUGH.  UPON REPAIRING THE BURNED WIRE, MECHANIC FOUND THAT THE 10	 GAGE AND 16 GAGE WIRE SHOWS SIGNS OF COPPER OXIDATION IN COLOR, BRITTLE TO TOUCH AND SILVER PLATING ON WIRE WAS FLAKING	 OFF.  FURTHER INVESTIGATION SHOWS THIS MAY BE A MFG DEFECT OF THE WIRE.  FURTHER INVESTIGATION ONGOING WITH MFG.  (K)	1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2005052400147	20050524	00147	CE  	2005	5	24	2005FA0000638    	1	20050421	G	6100	B5020	SPRING          			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	STRETCHED       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	208JB					20800362		020561		SPRING ASSY STRETCHED TOO LARGE.  (K)						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
2005052400148	20050524	00148	SO  	2005	5	24	2005FA0000639    	1	20050317	G	5312	62444003	BULKHEAD        			PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	5654W	4177 				28815				FOUND DURING INSPECTION, MINER SKIN WRINKLES LT OF FIN.  PREVIOUS DAMAGE TO RUDDER FROM THE REAR FORWARD.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2005052400149	20050524	00149	SO  	2005	5	24	2005FA0000640    	1	20050317	G	5312	62444003	BULKHEAD        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	7360J	5597 				2824712				FOUND DURING INSPECTION.  NO EXTERNAL INDICATIONS.  NO DAMAGE HISTORY.  BULKHEAD AFT FUSELAGE CRACKED AND KINKED.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2005052400150	20050524	00150	CE  	2005	5	24	2005FA0000641    	1	20050412	G	5553	53120252	PAN             			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					VERTICAL STAB	CRACKED         	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	98560	5627 				340A0032				DURING ANNUAL INSPECTION TECHNICIAN WAS INSPECTING TAIL SECTION.  THE PAN (AFT) IS ATTACHED TO BULKHEAD WHICH ARE PRIMAR	Y STRUCTURE (AFT) FOR HORIZONTAL AND VERTICAL STABILIZER.  TAIL FLEX IS TRANSFERRING TO THIS ASSY AND IS CAUSING CRACKS 	IN THE RADIUS.  (K)				1	L	7	2 	3O	3	O		3A25    	E8CE				 
2005052400151	20050524	00151	CE  	2005	5	24	2005FA0000642    	1	20050412	G	5553	53120252	PAN             			CESSNA	340   	340A        	2076405	CE  										VERTICAL STAB	CRACKED         	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	234PS	3703 				340A0368				DURING ANNUAL INSPECTION, TECH WAS INSPECTING TAIL SECTION.  PAN IS ATTACHED TO A BULKHEAD WHICH ARE THE PRIMARY STRUCTU	RE (AFT) FOR THE HORIZONTAL AND VERTICAL STABILIZERS.  TAIL FLEX IS TRANSFERRING TO THIS ASSY AND IS CAUSING CRACKS ON T	HE RADIUS.  (K)				1	L	7	2 	3O				3A25    					 
2005052400153	20050524	00153	CE  	2005	5	24	2005FA0000643    	1	20050427	G	5310	00244002457	SPAR            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					FUSELAGE	CRACKED         	D			MASS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	8117V	11655				TH1628				WHERE HORIZONTAL STAB SPAR ATTACHES.  THE BULKHEAD IS CUT AWAY, TO ALLOW THIS, AND IS FORMED BY JOGGLE BEND.  SIDE TO SI	DE.  AT THIS JOGGLE, IT IS CRACKED, FORE AND AFT, TO INCLUDE BOTH BULKHEAD AND FORMER.  (SW01200504216) (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005052400154	20050524	00154		2005	5	24	2005FA0000644    	4	20050420	G	3418	07133481	STALL WARNING   			CESSNA	172   	172S        	2072439	CE  										RT WING	INOPERATIVE     	D			Q19S	A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CR	CRUISE         	1			EA	07	50605	311  				172S9205				(510901) STUDENT PILOT WAS FLYING W/CFI.  DURING STUDENTS FIRST STALL PRACTICE THE WARNING HORN FAILED TO OPERATE THROUG	H FULL STALL, CFI HALTED MANEUVER.  TROUBLESHOOTING CONFIRMED THAT WARNING HORN WAS DEFECTIVE.  REPLACED WITH NEW, OPS C	HECK AND TEST FLIGHT WERE COMPLETED, OK PROBABLE CAUSE HAS NOT BEEN DETERMINED AT THIS TIME.   (EA07200503884) (K)				1	H	7	1 	3O			NT	3A12    					 
2005052400155	20050524	00155	NE  	2005	5	24	2005FA0000645    	2	20050429	G	7200	117M62G05	SEAL            			BOEING	777   	777*        	UTILUSE	NM  	GE    	GE90  	GE9090B     	 	NE  					ENGINE	DEBONDED        	D			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35							900230			PART WAS PREVIOUSLY REPAIRED.  REP REQUIRES USE OF BRAZE AMS 4777 OR SUITABLE TAPE ALTERNATIVE, USED TAPE SPEZ AMS 4779F	, WITH OVEN TEMP 1050 DEGREES C.  AMS 4779F DOES NOT MELT UNTIL 1068 DEGREES C.  HONEYCOMB BECAME DISBONDED AND LIBERATE	D CAUSLING HPT 1 BLADE OVERHEAT DISTRESS.  BRAZE JOINT FAILED WITHIN 300 CYCLES.				2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
2005052400158	20050524	00158	SW  	2005	5	24	2005FA0000646    	1	20050414	G	2170	18391021	WATER SEPARATOR 			GULSTM	111   	111RKWELL   	0144601	SW  										INLET FLANGE	CORRODED        	C			EW7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11										(WATER SEPARATOR) RECEIVED PAR, INCOMING INSPECTION REVEALS CORROSION AND PITTING AT NUMEROUS POSITIONS AROUND CIRCUMFER	ENCE OF AIR INLET FLANGE.  PART FAILED INCOMING INSPECTION.  8130-3 STATES PART IS AN OVERHAULED UNIT.  W/O CERTIFIES PA	RT AS AIRWORTHY.  PART APPEARS TO HAVE CORROSION FOR CONSIDERABLE TIME.				1	L	7	1 	3O				A11SO   					 
2005052400161	20050524	00161		2005	5	24	2005FA0000647    	1	20050420	G	4920		BLADE           	HONEYWELL   																COMPRESSOR ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05		1824 			031365103479					THIS IMPELLER HAS EXPERIENCED WHAT LOOKS LIKE HIGH  CYCLE FATIGUE WITH A VERY LOW TT ON THE UNIT.  IT APPEARS TO HAVE FA	ILED DUE TO WHAT STARTED AS A FATIGUE CRACK AND RESULTED IN A LARGE PIECE OF THE IMPELLER COMING OFF.  THIS IMPELLER AND	 ANOTHER WERE PURCHASED WITHIN 30 DAYS OF EACH OTHER AND HAVE SN THAT ARE 2 DIGITS OFF FROM THE OTHER.  (K)																	 
2005052400253	20050524	00253	EU  	2005	5	24	2005FA0000648    	1	20050328	G	2710	120A1186	HINGE           			GROB  	120   	G120A       	1660208	EU  										RT AILERON	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	1947 				85003				ON ROUTINE PHASE INSPECTION, MECHANIC FOUND HINGE ON RT AILERON TRIM TAB CRACKED AT ATTACH POINT FOR PUSH PULL ROD.  CAU	SE AT THIS TIME UNKNOWN, NO RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O			RT	A49CE   					 
2005052400254	20050524	00254	EU  	2005	5	24	2005FA0000649    	1	20050328	G	2710	120A1185	HINGE           			GROB  	120   	G120A       	1660208	EU  										LT AILERON	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	867AF	1550 				85007				ON ROUTINE INSPECTION, MECHANIC FOUND HINGE ON LT AILERON TRIM TAB CRACKED AT ATTACH POINT FOR PUSH PULL ROD.  CAUSE AT 	THIS TIME UNKNOWN, NO RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O			RT	A49CE   					 
2005052400255	20050524	00255	EU  	2005	5	24	2005FA0000650    	1	20050328	G	2710	120A1185	HINGE           			GROB  	120   	G120A       	1660208	EU  										LT AILERON	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	1947 				85003				ON ROUTINE PHASE INSPECTION, MECHANIC FOUND HINGE ON LT AILERON TRIM TAB CRACKED AT ATTACH POINT FOR PUSH PULL ROD.  CAU	SE AT THIS TIME UNKNOWN, NO RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O			RT	A49CE   					 
2005052400294	20050524	00294	EU  	2005	5	24	2005FA0000651    	2	20050323	G	8530	21130	VALVE GUIDE     			REIMS 	150   	F150G       	7530120	EU  	RROYCE	O200  	RRO200A     	 	EU  	MCAULY	1A100	1A100MCM    	GL  	ENGINE	LEAKING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	HBCBK					0026	21R274			ENGINE PROCURED WITH -0- TSO AND CYLINDERS INSTALLED.  AFTER 50 HOURS, REMOVED ALL CYLINDERS DUE TO EXCENTRIC VALVE GUID	E BORE AND THEREFORE LEAKING STEM.  AT 151 HOURS TSO, ALL CYLINDERS LOW COMPRESSION (53-67 PSI).  INSPECTION REVEALED DA	MAGED VALVE GUIDES AND CARBON TRACES ON PISTONS.				1	H	7	1 	3O	3	O		A13EU   	E31N	5	N	P918	 
2005052400297	20050524	00297	CE  	2005	5	24	2005FA0000652    	1	20050503	G	3250	3219	PAWL            	CESSNA      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					TAIL WHEEL STEER	WORN            	C				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			GL	15	1767R					18502487				APPEARS THAT THE STEERING LOCK PAWL DID NOT ENGAGE SUFFICIENTLY TO LOCK THE TAIL WHEEL.  UPON LANDING THE TAIL WHEEL CAS	TORED.  SWINGING THE AC TO THE RT AND OFF OF THE RUNWAY.  AC SUSTAINED DAMAGE TO ITS LT WING.  INVESTIGATION DISCLOSED T	HAT THE TAIL WHEEL STEERING PAWL WAS WORN TO A POINT THAT IT WOULD NOT SUFFICIENTLY LOCK THE LOCKING COLLAR.  REPORTERS 	CONCERN IS THAT WEAR OF THIS PIN IS NOT EASILY APPARENT EXCEPT THROUGH WRITE-UP BY A PILOT EXPERIENCED WITH THIS PROBLEM	.  VISUAL INSPECTION OF THE TAIL WHEEL ASSY WOULD NOT DISCLOSE THIS PROBLEM.  (GL15200511027) (K)		1	H	7	1 	3O	3	O		3A24    	E5CE				 
2005052400298	20050524	00298	CE  	2005	5	24	2005FA0000653    	1	20050422	G	1430	AN52510	SCREW           	BEECH       		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FAIRING	WRONG PART      	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	768WT	4974 				FL25				DURING SCHEDULED INSPECTION FOUND SCREWS ATTACHING AFT LOWER EDGES OF FORWARD WING ROOT FAIRINGS TO UNDERSIDE WING ROOT 	FAIRINGS TO BE OF EXCESSIVE LENGTH.  SCREW TIPS HAD GOUGED LT AND RT LOWER FUSELAGE SKINS AT THE APPROXIMATE FS 166.300 	LOCATION TO 0.020 INCH DEEP.  HAVE NOTICED SIMILAR DAMAGE TO OTHER AC SAME LOCATION.  REQUIRED DER APPROVED REPAIRS TO P	RESSURIZED FUSELAGE SKINS.  SUGGEST ANY TECHS INSPECTING THIS AREA PAY CLOSE ATTENTION FOR SCREW TIP DAMAGE, AND TO USE 	ONLY THE CORRECT LENGTH FAIRING ATTACH SCREWS.  RECOMMEND A 1-TIME SB TO INSPECT AND EITHER MODIFY FAIRING ATTACHMENT OR	 PLACARD.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005052400299	20050524	00299	CE  	2005	5	24	2005FA0000654    	1	20050423	G	2720	1015300573	CONTROL CABLE   			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RUDDER	LOOSE           	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	768WT	4974 				FL25				DURING SCHEDULED INSPECTION, FOUND CABLE QUADRANT FOR AUTOPILOT RUDDER SERVO LOOSE ON  RUDDER TORQUE SHAFT ASSY.  REPLAC	ED LOOSE RIVETS W/NEXT SIZE LARGER RIVETS INSTALLED WET W/EA 9309 STRUCTURAL ADHESIVE IAW TECH SUPPORT RECOMMENDATIONS. 	 RECOMMEND THIS AREA BE LOOKED AT CLOSELY ON AC AFTER ACCUMULATION OF 3000 HRS OR MORE.  SUSPECT FATIGUE AND RUDDER SERV	O TORQUE CAUSING RIVETS TO GRADUALLY LOOSEN.  (K)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005052400300	20050524	00300	SO  	2005	5	24	2005FA0000655    	1	20050426	G	5340		FITTING         			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					FUSLEAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	7054	9050 				188915				DURING AN ANNUAL INSPECTION THE LT FRONT CABANE V ATTACH POINT ON THE FUSELAGE WAS FOUND TO BE CRACKED.  THIS IS THE SEC	OND AIRCRAFT IN THE LAST MONTH THAT WAS FOUND ON.  THE LANDING GEAR WAS FOUND TO BE OK ON BOTH AC.  BOTH AIRCRAFT OPERAT	E ON WHEELS, SKIS AND FLOATS.  (K)				1	H	7	1 	3O	3	O		1A2     	E274				 
2005052400301	20050524	00301	CE  	2005	5	24	2005FA0000656    	1	20050423	G	3210	124142312	SADDLE          			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	4934U					21058634				REPLACED BOTH MLG SADDLES AT ANNUAL INSP.  BOTH WERE FOUND TO HAVE HAIR LINE CRACKS IN RADIUS ABOVE IB V-BOLT HOLE USING	 DYE PENETRANT INSPECTION METHOD.  (K)					1	H	7	1 	3O	3	O		3A21    	E5CE				 
2005052400302	20050524	00302	CE  	2005	5	24	2005FA0000657    	1	20050417	G	3220	35825110	BRACE           	BEECH       		BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E225*       	17015	SO  					NOSE GEAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	52WR	3500 				D4841				CORROSION PITS APPROXIMENTLY 30 TO 50 PERCENT OF WALL THICKNESS.  THIS PART ONLY 10 PERCENT OF WALL THICKNESS ALLOWED BY	 MFG.  THIS PART IS MAGNESUM.  THE PITTING IS UNDER THE FLET 35, ABOVE THE LOWER BUSHING,   THE FELT IS SATURATED WITH M	OISTURE AND GREASE WHICH ALLOWS CORROSION TO ATTACH THE PART.  (K)				1	L	7	1 	3O	3	O		A777    	E267				 
2005052500038	20050525	00038	SO  	2005	5	25	2005FA0000658    	1	20050420	G	3230	6775300	SPRING          			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					MLG	BROKEN          	B			RO4R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	994BD	140  				3449310				OPERATOR DID NOT GET RT MAIN GEAR DOWN INDICATION AFTER EXTENDING LANDING GEAR USING EMERGENCY EXTENSION.  AIRCRAFT LAND	ED WITHOUT INCIDENT. RT MAIN GEAR OVER-CENTER SPRING ATTACH PLATE WAS FOUND BROKEN.  WITH THE HYDRAULIC PUMP DISABLED FO	R THE GEAR EXTENSION, THE OVERCENTER BRACE DOWNLOCK HOOK WAS NOT ENGAGED AND THE GEAR WAS NOT LOCKED DOWN AND THE POSITI	ON SWITCH WAS NOT ACTIVATED.  FURTHER INSPECTION FOUND THAT THE SPRING USED PUTS A TORQUE LOAD ON THE MAIN GEAR ATTACH P	LATE CAUSING IT TO TWIST AND SUBSEQUENTLY BREAK.  INSPECTION OF THE SAME PLATE ON THE LT MAIN GEAR REVEALED THAT THE SAM	E CONDITION EXISTS AND THAT THE SPRING ATTACH PLATE HAS BEGUN TO BEND IN THE SAME AREA.  (K)	1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005052500069	20050525	00069	WP  	2005	5	25	2005FA0000662    	2	20050423	G	7310	8975131	FUEL FILTER     			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ENGINE	RESTRICTED      	B			E81R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	725TA					258297				CREW REPORTED, 55 MIN INTO FLIGHT, DURING CRUISE AT FL350, NR1 ENGINE (ENG FUEL) ANNUNCIATOR ILLUMINATED.  LIGHT EXTINGU	ISHED WHEN POWER REDUCED BELOW 90 PERCENT N1.  REQUIRED FURTHER POWER REDUCTIONS TO FLIGHT IDLE TO KEEP LIGHT EXTINGUISH	ED.  DIVERTED FLIGHT, DISCREPANCY VERIFIED AT ARRIVAL.  REPLACED ENG FUEL FILTER AND PERFORMED PRECAUTIONARY DRAINING OF	 WING FUEL TANK SUMPS.  NO REPEAT OF FAULT AFTER 45 MINUTES OF EXTENDED GROUND RUNNING AT VARIOUS POWER SETTINGS.  REMOV	ED FILTER RETURNED TO MAINT FACILITY FOR FURTHER DETAILED INSP.  (K)		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005052500070	20050525	00070	WP  	2005	5	25	2005FA0000663    	2	20050423	G	7310	8975131	FUEL FILTER     			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	RESTRICTED      	B			E81R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			GL	03	725TA					258297	P107152			DURING APPROACH, DIVERT REQUIRED FOR NR1 ENGINE (ENG FUEL) ANNUNCIATOR LIGHT ILLUMINATION, GO-AROUND WAS REQUIRED FOR TR	AFFIC.  DURING GO-AROUND NON FLYING PILOT OBSERVED FICKERING NR2 ENGINE (ENGINE FUEL) ANNUNCIATOR LIGHT INDICATION.  VER	IFIED DISCREPANCY UPON ARRIVAL AT MAINTENANCE.  REPLACED NR2 ENGINE HP FUEL PUMP FILTER AND DRAINED WING FUEL TANK SUMPS	.  NO FAULT RETURN NOTED DURING 45 MINUTE EXTENDED GROUND RUN AT VARIOUS POWER SETTINGS.  REMOVED FILTER RETURNED TO OPE	R MAINT FOR FURTHER DETAILED INSP.  (K)		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005052500072	20050525	00072	CE  	2005	5	25	2005FA0000664    	1	20050422	G	2435	23080050	STARTER GEN     			BEECH 	MU300 	400A        	1155402	CE  										ENGINE	INOPERATIVE     	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	480LX	271  				RK398				INVESTIGATED PILOT REPORT OF LT ENGINE NOT ROTATING WHEN STARTER BUTTON DEPRESSED.  FOUND STARTER GEN NOT ROTATING WITH 	POWER APPLIED.  REPLACED STARTER GEN WITH OVERHAULED UNIT IAW MM.  ENGINE START AND GENERATOR OPERATIONS NORMAL.  TRANSI	ENT AIRCRAFT AT OFF-SITE FACILITY, NO MAINT RECORDS AVAILABLE.  UNIT TO BE INSPECTED AND TORN DOWN FOR INVESTIGATION. (K	)			2	H	7	2 	4F			RT	A16SW   					 
2005052500113	20050525	00113		2005	5	25	2005FA0000665    	1	20050309	G	3350		BATTERY         																	EMERGENCY LIGHT	WRONG PART      	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09										UNIT CONTAINS 24 NICAD CELLS IN PLACE OF THE 12 LEAD ACID CELLS THAT BELONG IN IT.  THE HIGHER VOLTAGE APPEARS TO HAVE B	URNED UP THE CELL SWITCH BLOCK.  NICAD CELLS ARE NOT AN APPROVED REPLACEMENT CELL FOR THIS UNIT.  (K)																		 
2005052500121	20050525	00121	EU  	2005	5	25	2005FA0000668    	1	20050418	G	2910	NAS16124	O-RING          			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					RESERVOIR	DEFECTIVE       	B			AR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	711KE		2182 			288				FOLLOWING MAINT TROUBLESHOOTING OF HYD SYS.  IT WAS FOUND TO HAVE DEFECTIVE O-RING JUST AFT OF THE HYD RESERVOIR AT A T-	FITTING LOCATION.  DEFECTIVE O-RING DEPLEATED HYDRAULIC RESERVOIR RUNNING HYDRAULIC SYS OUT OF FLUID.  THIS CAUSED THE R	T ENGINE DRIVEN HYD PUMP TO CAVITATE AND DAMAGED PUMP INTERNALLY.  O-RING WAS REPLACED WITH A NEW O-RING, AND ENGINE DRI	VEN HYD PUMP WAS REPLACED.  SYS WAS SERVICED AND OP FUNCTION CHECKED AND LEAK CHECKED WITH NO OTHER DISCREPANCIES NOTED.	  MAINTENANCE CARE WHEN WORKING WITH HYD O-RINGS.   SUSPECT O-RING FAILURE DUE TO NORMAL DETERIORATION AND OR IMPROPER I	NSTALLATION AT TIME OF LAST MAINT FUNCTION PERFORMED TO THAT FITTING. (K)	2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2005052500122	20050525	00122	SO  	2005	5	25	2005FA0000670    	2	20050426	G	7261	653814	GEAR            			PIPER 	PA12  	PA12        	7101202	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					OIL PUMP	BROKEN          	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	92732	1547 				12168	L113768A			ENGINE LOST POWER FOR UNKNOWN REASONS.  ENGINE WAS DISASSEMBLED AND INSPECTED.  INVESTIGATION FOUND BROKEN DRIVE DOGS ON	 THE OIL PUMP GEAR, AS WELL AS GEAR TEETH ON THE CRANKSHAFT GEAR AND OUTSIDE DIAMETER OF THE CAM GEAR.  THE REASON FOR T	HE FAILURE OF THE OIL PUMP GEAR IS UNKNOWN.  I DO NOT BELIEVE THE OIL PUMP PROBLEM CAUSED THE TEETH OF THE OTHER GEARS T	O BRAKE.  I WOULD BE REMISS IN RECOMMENDING A COURSE OF PREVENTIVE ACTION DUE TO THE LACK OF CAUSAL FACTOR OF THIS OCCUR	RENCE.  (K)		1	H	7	1 	3O	3	O		A780    	E9CE				 
2005052300288	20050523	00288	CE  	2005	5	23	2005FA0000671    	1	20050502	G	3220	1018200741	FORK            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	678SS	6607 	150  			BB1021				FOUND CRACKED NOSE FORK TUBE AT LOWER WELD AREAS WHILE PERFORMING AD 2004-23-02, DURING ROUTINE PHASE INSPECTION. FORK W	AS REPLACED WITH MFG KIT NR 101-8030-1, SN 2463.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005052500128	20050525	00128	EA  	2005	5	25	2005FA0000672    	2	20050406	G	8520	75038	CRANKSHAFT      			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	FAILED          	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	54231	1400 				277554025				ENGINE WAS DISASSEMBLED AND INSPECTED DUE TO CRANKSHAFT FAILURE.  FOUND NR3 CHEEK BROKEN.  THIS FAILURE CAUSED EXCESSIVE	 DAMAGE TO THE CRANKCASE, CAMSHAFT, NR1 AND NR 2 CONNECTING ROD, AND THE ASSOCIATED TAPPET BODIES.  CAUSE OF THE FAILURE	 COULD POSSIBLY BE A METALLURGIC DEFECT OR A FORM OF FATIGUE.  WITHOUT ACCESS TO A LABORATORY FOR EXTENSIVE TESTING WE C	AN NOT ACCURATELY CONCLUDE WHAT CAUSED THIS FAILURE OR HOW LONG THIS DEFECT HAD BEEN PRESENT AT THE TIME OF FAILURE.  DU	E TO THE LACK OF CONCLUSIVE CAUSE WE WOULD BE REMISS IN SPECULATING THE REMEDY FOR THIS EVENT. (K)		1	L	7	2 	3O	3	O		1A10    	1E4				 
2005052500138	20050525	00138	SO  	2005	5	25	2005FA0000674    	1	20050111	G	3220	40336000	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4093W					318152176				INSPECTED NOSE GEAR DRAG LINKAGE RETRACT ROD ATTACHMENT AREA IAW SL AND FOUND CRACK USING DYE PENETRANT INSP.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005052500139	20050525	00139	EA  	2005	5	25	2005FA0000675    	2	20050103	G	7230		COMPRESSOR      			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A27      	52043	EA  					LT ENGINE	STALLED         	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	13	599CZ					U89				LT ENGINE PRODUCED A SERIES OF SOUNDS INDICATIVE OF COMPRESSOR STALL WHEN LEVELED AT FL190.  TORQUE RAPIDLY DIMINISHED A	ND TEMPERATURE ROSE.  PILOT SHUTDOWN ENGINE AS A PRECAUTION.  ENGINE REMOVED AND SENT FOR ANALYSIS.  (K)					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005052500179	20050525	00179	SW  	2005	5	25	2005FA0000680    	1	20050129	G	2510	140216501	BELLCRANK       			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540*     	41532	EA  					PILOT SEAT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	1085K	2024 				270035				PILOT SEAT HEIGHT ADJUST BELL CRANK CRACKED AND SPLIT OPEN ON RT SIDE.  THIS CAUSED SEAT TO LEAN DOWN TO THE RT.  CRACK 	APPEARS TO START AT A WELD ON THE END OF THE TUBE.  CRACK CONTINUED IN SPIRAL TOWARD ACTUATOR ATTACH POINT.  OPPOSITE EN	D OF TUBE BENT AND BINDING.  ACTUAL ITEM FAILED IS THE WELDED ARM ASSY.  THIS CAUSED THE OTHER 2 PART IN THE ASSEMBLY, T	UBE AND BEARINGS TO BE DAMAGED.  (EA23200505225) (K)			1	L	7	1 	3O	3	O	RT	2A3     	E14EA				 
2005052500181	20050525	00181	GL  	2005	5	25	2005FA0000682    	1	20050103	G	7921	AD36	OIL COOLER      			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235L2A     	41505	EA  					ENGINE	CRACKED         	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	07	215LF	87   				201032				ENROUTE, DIVERTED, AFTER REPORTING AN OIL PRESSURE PROBLEM.  AIRCRAFT OIL COOLER DEVELOPED LEAK, LANDED AS A PRECAUTIONA	RY MEASURE.  REMOVED AND REPAIRED OIL COOLER.  (NM07200502583) (K)					1	L	7	1 	  	3	O		EXPA1L71	E223				 
2005052500197	20050525	00197	NE  	2005	5	25	2005FA0000686    	2	20050110	G	7421		IGNITER         								GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	DAMAGED         	B			I2VR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03							249J048			IGNITER WOULD NOT THREAD INTO ENGINE LOSS DURING O/H ASSEMBLY.  1ST THREAD SHOWS DAMAGE AND FURTHER EXAMINATION SHOWS TH	READ DIAMETER IS .003 INCH-.004 INCH LARGER THAN THE OTHER NEW IGNITER INSTALLED ON THIS ENGINE.  THE UNDAMAGED IGNITER 	WAS CHECK-THREADED INTO BOTH ENGINE BOSSES WITH NO PROBLEMS.  RECOMMMEND CAREFUL CONDITION CHECKS.  (K)									4	F			E7EA				 
2005052500198	20050525	00198		2005	5	25	2005FA0000687    	4	20050104	G	3424	1394T10010RA	INDICATION SYS  			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540*      	41532	EA  					TURN COORDINATOR	INOPERATIVE     	B			S1FR	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			SO	33	962AC					20608057				UNIT WAS INSTALLED IN AIRCRAFT ON 12/20/2004.  AFTER APPROX .5 HOURS, PILOT OBSERVED TURN COORDINATOR OFF FLAG, MOMENTS 	LATER AUTOPILOT DISENGAGED.  THIS UNIT REPLACED AN EARLIER INSTALLED OVERHAULED UNIT INSTALLED 7/04.  (K)					1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2005052500202	20050525	00202	EU  	2005	5	25	2005FA0000691    	1	20050112	G	3260	120A5191	UPLOCK          			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	862AF					85002				DURING FLIGHT, GEAR SELECTED TO DOWN AND LT MAIN GEAR EXTENSION WAS DELAYED.  AFTER ABOUT 25 SECONDS LT MAIN GEAR EXTEND	ED.  MAINTENANCE TECHNICIAN FOUND LT LANDING GEAR UP LOCK ASSY WAS INTERMITTENT.  REPLACED ASSY.  NO RECOMMENDATION AT T	HIS TIME.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2005052500203	20050525	00203	CE  	2005	5	25	2005FA0000692    	1	20050119	G	2701	05117816	CONTROL COLUMN  			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					COCKPIT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2881L					17256081				WHILE ACCOMPLISHING SEB ON CONTROL YOKE, FOUND WATER WHEN INSP HOLE WAS DRILLED AT BASE OF CENTER TUBE.  .2500 CUP OF BL	ACK RESIDUE WAS FOUND WHEN TUBE WAS CUT OPEN.  INSIDE OF CONTROL YOKE TUBE WAS RUSTED MODERATELY THE FULL LENGTH OF CENT	ER TUBE.  NO LEAK IN FIREWALL OR WINDSHIELD WERE FOUND TO ACCOUNT FOR WATER ENTRY.  AC WAS PURCHASED DISASSEMBLED 12 YEA	RS AGO, POSSIBLY WATER WAS INTRODUCED AT THAT TIME.  INSTALLED SERVICEABLE YOKE AND ACCOMPLISHED SEB SUCCESSFULLY. (CE01	200502663) (K)		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005052500204	20050525	00204		2005	5	25	2005FA0000693    	4	20050105	G	6122	O20887	DRIVE GEAR      	MCAULY      		GULSTM	114   	114TC       	0145002	SW  	LYC   	O540  	TIO540*     	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	FLYWEIGHT	SHEARED         	B			W59R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	77HK	1200 			970719	20020				GOVERNOR FAILED TO CYCLE PROP DURING RUN-UP.  AT DISASSEMBLY OF GOVERNOR, GEAR WAS FOUND SHEARED AT THE VALVE SLOTS, JUS	T UNDER FLYWEIGHT ASSY.  IT APPEARS AS THOUGH THE DRIVE GEAR SEIZED IN THE GOVERNOR BODY ABOVE THE SLOTS.  CAUSE UNKNOWN	.  (K)				1	L	7	1 	3O	3	O	RT	A12SO   	E14EA	5	C	P58GL	 
2005052600087	20050526	00087	CE  	2005	5	26	2005FA0000700    	2	20050107	G	7414	01040158	MAGNETO         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					ENGINE	SHORTED         	B			BJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	6300B	602  				1157				ON A 500 HOUR MAGNETO INSPECTION, FOUND MAGNETO SPARKING INTERNALLY.  AC RAN GOOD AND HAD A 100 RPM MAG DROP.  INTERNAL 	SPARKING WAS BETWEEN COIL AND CARBON BRUSH.  BRUSH AND SPRING DESTROYED AND PART OF DISTRIBUTOR BLOCK MISSING.  RECOMMEN	D MANDATORY INTERNAL INSPECTION OF MAGNETOS DURING ANNUAL.  NEED TO ADD FARS.  (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2005052600088	20050526	00088	SO  	2005	5	26	2005FA0000701    	1	20050105	G	3246	1159SCL20343	WHEEL           			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					LT MLG	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	44CE	162  				1125				UPON LANDING, THE LT IB WHEEL FAILED AT THE FLANGE AREA.  APPROX .3333 OF THE FLANGE AREA BROKE AWAY AND ALLOWED THE LOC	K RING.  (STILL INTACT AND SAFETIED), TO SEPARATE.  DEBRIS, (FLANGE OR WHEEL HALF) CROSSED OVER AND HIT THE RT IB WHEEL,	 GLANCED UP AND PUNCTURED THE RT WING TRAILING EDGE BOX, (COMPOSITE MATERIAL) AND THE TIRE MADE CONTACT WITH THE RT WING	 FLAP AND DENTED THE IB END OF IT.  NOTE: THE WING T/E BOX IS NOT PART OF THE FUEL TANK.  IT IS FOR AERODYNAMIC FAIRING 	OF THE WING.  (WP19200504331) (K)		2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2005052600109	20050526	00109	CE  	2005	5	26	2005FA0000705    	1	20050112	G	3200	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DYNAMIC BRAKE	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	5585Y	120  				CE1389	830091R			PILOT SELECTED GEARDOWN AND NOTHING HAPPENED.  LANDING GEAR WOULD NOT EXTEND.  FLIGHT CREW EXTENDED LANDING GEAR MANUALL	Y AND LANDED WITHOUT INCIDENT.  MAINTENANCE TECH TROUBLESHOT GEAR SYSTEM AND FOUND THE DYNAMIC BRAKE RELAY WAS INTERMITT	ENT.  RECOMMENDATION IS FOR MFG TO INVESTIGATE THIS ISSUE WHICH HAS HAPPENED ON SEVERAL OCCASIONS AND COME UP WITH AN IM	PROVED RELAY THAT IS MORE RELIABLE.  (K)			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005052600117	20050526	00117	CE  	2005	5	26	2005FA0000706    	1	20050113	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DYNAMIC BRAKER	INTERMITTENT    	B			VJ3R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	07	5582X	527  				CE1353	825984R			PILOT SELECTED GEAR UP AND NOTHING HAPPENED.  STILL INDICATING (3) GREEN LIGHTS LANDING GEAR WOULD NOT RETRACT.  MAINTEN	ANCE TECH TROUBLESHOT GEAR SYSTEM AND FOUND THAT THE DYNAMIC RELAY WAS INTERMITTENT.  NO RECOMMENDATION AT THIS TIME. (K	)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005052600118	20050526	00118	CE  	2005	5	26	2005FA0000707    	1	20050108	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BRAKER	INTERMITTENT    	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			WP	07	5544A	100  	100  			CE1343				PILOT SELECTED GEAR DOWN AND NOTHING HAPPENED, BEFORE PILOT COULD COMPLETE HIS CHECK LIST TO CRANK GEAR DOWN, THE GEAR W	ENT DOWN ON ITS OWN.  AIRCRAFT RETURNED TO BASE.  UPON FURTHER TROUBLESHOOTING FOUND RELAY WAS INTERMITTENT, PORBABLE CA	USE AT THIS TIME UNKNOWN.  THIS IS SUPPOSE TO BE AN IMPROBED RELAY SO THERE IS NO RECOMMENDATION AT THIS TIME.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005053100010	20050531	00010	CE  	2005	5	31	2005FA0000710    	1	20050430	G	3222	35825110	BRACE           			BEECH 	35    	K35         	1151524	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG	CORRODED        	B			F5GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	826R	5940 				D6153				CORROSION PITS APPROXIMATELY 30 TO 50 PERCENT OF WALL THICKNESS.  THIS PART ONLY 10 PERCENT OF WALL THICKNESS ALLOWED BY	 MFG.  THIS PART IS MAGNESIUM.  THE PIRTING IS UNDER THE FEL 35, ABOVE THE LOWER BUSHING, THE FELT IS SATURATED WITH MOI	STURE AND GREASE WHICH ALLOWS CORROSION TO ATTACK THE PART.  (K)				1	L	7	1 	3O	3	O		3A15    	E1CE				 
2005052600127	20050526	00127	SO  	2005	5	26	2005FA0000711    	1	20050512	G	2820		FITTING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					FUEL PUMP	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	975DC	20   	20   			317812059	RL829961A			FUEL LINE FITTING CRACKED AT THE INLET TO THE FUEL PUMP.  CRACK WAS LOCATED IN THE BEND RADIUS (45 DEGREE FITTING)OF A S	TRATOFLEX HOSE ASSEMBLY.  FUEL WAS SPRAYING FROM THE FITTING AFT TOWARDS THE TURBO AND CAUSED AN ENGINE FIRE IN FLIGHT, 	LT ENGINE.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005053100047	20050531	00047	EA  	2005	5	31	2005FA0000713    	2	20050426	G	8500	R182097	ENGINE          			BOEING	B17   	B17G        	1380204	WP  	WRIGHT	R1820 	R182097     	67020	EA  					NR 4	FAILED          	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TO	TAKEOFF        	1			WP	23	3703G		46   			4483546A	046778			UPON TAKEOFF, NOTICED STEADY DROP IN ENGINE OIL PRESSURE.  SHUT ENGINE DOWN AT MIN OIL PRESSURE.  PRESSURE STILL DECREAS	ING.  CHECKED SCREENS AND OIL PRESSURE VALVE ON GROUND.  COULD NOT GET ENGINE TO MAKE MIN ACCEPTABLE PRESSURE.  REMOVED 	ENGINE.  UPON REMOVAL OF PROP, BRONZE OR BRASS WAS IN PROP SHAFT. (K)				2	L	7	4 	4R	4	R		L13     	5E10				 
2005053100048	20050531	00048	EA  	2005	5	31	2005FA0000714    	2	20050426	G	8500	R182097	ENGINE          			BOEING	B17   	B17G        	1380204	WP  	WRIGHT	R1820 	R182097     	67020	EA  					NR 2	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	23	3703G	42   				4483546A				ON FINAL, ENGINE WAS PRODUCING LOW OIL PRESSURE.  UPON LANDING, CHECKED SCREENS, OK, CLEANED OIL PRESSURE RELIEF VALVE A	ND APU FOR MAX OIL PRESSURE WAS STILL LOW.  COULD NOT GET ENGINE TO PRODUCE ACCEPTABLE OIL PRESSURE.  REMOVED ENGINE.  (	K)				2	L	7	4 	4R	4	R		L13     	5E10				 
2005053100049	20050531	00049		2005	5	31	2005FA0000715    	4	20050421	G	6122	D20880	RETAINER        	MCAULY      							LYC   	O540  	IO540*      	41532	EA  					PROP GOVERNOR	DAMAGED         	B			GCDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		345  			001989					FLYWEIGHT RETAINING DISC, DAMAGED.  (K)											3	O			1E4				 
2005053100057	20050531	00057	CE  	2005	5	31	2005FA0000716    	1	20050420	G	3230		UNKNOWN         			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					NLG	MALFUNCTIONED   	B			WVER	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			EA	09	797PA					098				DURING DEPARTURE, AFTER MAINTENANCE (ENGINE AND THRUST REVERSER) THE NOSE LANDING GEAR DID NOT RETRACT.  THE AC RETURNED	 TO DEPARTURE FOR REPAIR.  PROBABLE CAUSE:  THE AC WAS JACKED, THE LANDING GEAR WAS FUNCTIONALLY TESTED IAW MM.  THE DIS	CREPANCY COULD NOT BE DUPLICATED.  SUSPECTED AN AIR LOCK IN THE NOSE LANDING GEAR RETRACTION SYSTEM.  A CHECK FLIGHT WAS	 PERFORMED WITHOUT FURTHER INCIDENT.  (EA09200504998) (K)			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005053100058	20050531	00058	CE  	2005	5	31	2005FA0000717    	1	20050425	G	5755	24920016	SPOILER PANEL   			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					RT WING	MISMANUFACTURED 	B			WVER	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09	246FX					183				SPOILER PANEL ASSEMBLY WAS FOUND TO BE WARPED DURING TRIM TO FIT AIRCRAFT IAW SB.  PROBABLE CAUSE: MFG ERROR.  MFG WILL 	EVALUATE AND MAKE CHANGE.  (EA09200505066) (K)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005053100059	20050531	00059	NE  	2005	5	31	2005FA0000718    	2	20050420	G	7230	1B6509	BLADE           	PWA         							PWA   	2037  	F117PW100   	 	NE  					ENGINE	FRACTURED       	B			PQBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		7626 			B70312					SUBJECT ENGINE WAS RECEIVED FOR PROACTIVE NIB 10/11TH STATOR REMOVAL.  DURING INSPECTION, ONE 9TH STAGE HPC BLADE WAS FO	UND FRACTURED WITH APPROX 1.140 LENGTH OF THE BLADE MISSING.  THIS IS FIRST SHOP VISIT FOR THE ENGINE.  (K)										4	T			E17NE				 
2005052400068	20050524	00068	SO  	2005	5	24	2005FA0000719    	1	20050502	G	8011	653074A41R	ADAPTER         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ZONE 500	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9267W	1378 	1378 			3447016	811456	011308		STARTER ADAPTER ASSEMBLY BOLT FLANGE CRACKED AT E  THE 10 O'CLOCK POSITION.  HOUSING UNIT DOES NOT MATCH STARTER ADAPTER	 ACCESSORY CASE FOOTPRINT (OVERLAYS), RESULTING IN DIMINISHED LOAD AND VIBRATION DISTRIBUTION.					1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P22EA	 
2005052400061	20050524	00061	SO  	2005	5	24	2005FA0000720    	1	20050502	G	8011	653074A41R	ADAPTER         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	STARTER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9267W	1378 	1378 			3447016	811456	011308		STARTER ADAPTER ASSEMBLY BOLT FLANGE CRACKED AT E  THE 10 O'CLOCK POSITION.  HOUSING UNIT DOES NOT MATCH STARTER ADAPTER	 ACCESSORY CASE FOOTPRINT (OVERLAYS), RESULTING IN DIMINISHED LOAD AND VIBRATION DISTRIBUTION.					1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P22EA	 
2005052400062	20050524	00062	SO  	2005	5	24	2005FA0000721    	1	20050502	G	8011	653074A41R	ADAPTER         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	STARTER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9267W	1378 	1378 			3447016	811456	011308		STARTER ADAPTER ASSEMBLY BOLT FLANGE CRACKED AT E THE 10 O'CLOCK POSITION.  HOUSING UNIT DOES NOT MATCH STARTER ADAPTER 	ACCESSORY CASE FOOTPRINT (OVERLAYS), RESULTING IN DIMINISHED LOAD AND VIBRATION DISTRIBUTION.					1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P22EA	 
2005052400063	20050524	00063	SO  	2005	5	24	2005FA0000722    	1	20050502	G	8011	653074A41R	ADAPTER         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ZONE 500	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9267W	1378 	1378 			3447016	811456	011308		STARTER ADAPTER ASSEMBLY BOLT FLANGE CRACKED AT E  THE 10 O'CLOCK POSITION.  HOUSING UNIT DOES NOT MATCH STARTER ADAPTER	 ACCESSORY CASE FOOTPRINT (OVERLAYS), RESULTING IN DIMINISHED LOAD AND VIBRATION DISTRIBUTION.					1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P22EA	 
2005053100068	20050531	00068	GL  	2005	5	31	2005FA0000723    	1	20050503	G	7810	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	224ST	301  				0882				DURING AN ANNUAL INSPECTION OF THIS AC.  THE NR5 EXHAUST HEADER WAS FOUND TO BE CRACKED .7500 WAY AROUND THE CIRCUMFEREN	CE OF THE PIPE.  NR 5 EXHAUST HEADER WAS REPLACED.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005053100069	20050531	00069	SO  	2005	5	31	2005FA0000724    	1	20050503	G	2140		PRESSURE SWITCH 			PIPER 	PA31  	PA31350     	7103110	SO  										CABIN HEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	130BV					317952216				PERFORMING AD ON THE AFFECTED HEATER IAW SB A-103.  UPON COMPLETION OF THE PRESSURE DECAY TEST, PERFORMED AND OPS TEST O	F AIR PRESSURE SWITCH.  FOUND THE SWITCH FAILED IN A CONTACT CLOSED CONDITION.  UPON REMOVING THE SWITCH, NOTICED IT WAS	 A 94E42-1 SWITCH.  THIS IS THE PN THAT (ACCORDING TO SB A-103) HAS BEEN REDESIGNED TO ELIMINATE THE NOTED FAILURE MODE 	OF OLD SWITCH AND UPGRADE OLDER TECHNOLOGY HEATERS.(K)			1	L	7	2 	3O				A20SO   					 
2005053100070	20050531	00070	CE  	2005	5	31	2005FA0000725    	1	20050501	G	8011	ES6462751	STARTER         			BEECH 	35    	E35         	1151512	CE  	CONT  	E225  	E225*       	17015	SO  					ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	7312B					D3775				STARTER INOPERATIVE. (K)						1	L	7	1 	3O	3	O		A777    	E267				 
2005052400008	20050524	00008	EU  	2005	5	24	2005FA0000726    	1	20050503	G	2780	1075D1003	FCU             			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					ZONE 900	OUT OF TOLERANCE	Z				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	29	B2001		22   			119				THE SLATS FAILED TO EXTEND WHILE PILOTS WERE PERFORMING THE INSPECTIONS BEFORE TAKE-OFF.  THE SLATS LOCKED OUT WHILE MEC	HANIC PLACED THE FLAP/SLAT SELECTOR TO DN POSITION. SLAT UNBALANCE LIGHT CAME ON SIMULTANEOUSLY.  TROUBLE SHOOTING FOUND	 THE FSECU OUTPUT VOLTAGE WAS OUT OF TOLERANCE.				2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2005053100071	20050531	00071	EA  	2005	5	31	2005FA0000727    	2	20050501	G	8520		LIFTER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	SPALLED         	C			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	733ZK					17268677	L297076			LIFTERS SPALLED ON 5/7/2005, BUT NO DAMAGE TO THE CAMSHAFT AT THAT TIME.  2/16/2005 LIFTERS SPALLED AGAIN CAUSING THE CA	MSHAFT TO NEED REPLACEMENT. (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005052400064	20050524	00064	SO  	2005	5	24	2005FA0000728    	1	20050502	G	8011	653074A41R	ADAPTER         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ZONE 500	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9267W	1378 	1378 			3447016	811456	011308		STARTER ADAPTER ASSEMBLY BOLT FLANGE CRACKED AT E  THE 10 O'CLOCK POSITION.  HOUSING UNIT DOES NOT MATCH STARTER ADAPTER	 ACCESSORY CASE FOOTPRINT (OVERLAYS), RESULTING IN DIMINISHED LOAD AND VIBRATION DISTRIBUTION.					1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P22EA	 
2005052400065	20050524	00065	SO  	2005	5	24	2005FA0000729    	1	20050502	G	8011	653074A41R	ADAPTER         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ZONE 500	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9267W	1378 	1378 			3447016	811456	011308		STARTER ADAPTER ASSEMBLY BOLT FLANGE CRACKED AT E THE 10 O'CLOCK POSITION.  HOUSING UNIT DOES NOT MATCH STARTER ADAPTER 	ACCESSORY CASE FOOTPRINT (OVERLAYS), RESULTING IN DIMINISHED LOAD AND VIBRATION DISTRIBUTION.					1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P22EA	 
2005052400037	20050524	00037	CE  	2005	5	24	2005FA0000730    	1	20050503	G	3411	651447411	STATIC LINE     			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	669B	890  				5501060				ALTERNATE STATIC LINE CHAFED THROUGH IN CO-PILOTS SIDEWALL IN COCKPIT.  REPLACED LINE WITH NEW BUT THE LOCATION IS VERY 	DIFFICULT TO PREVENT CONTINUED CHAFING.  RECOMMEND MFG LOOK AT THIS AREA AND POSSIBLE REROUTING.					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005052400038	20050524	00038	CE  	2005	5	24	2005FA0000731    	1	20050503	G	3411	651447411	STATIC LINE     			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	669B	890  				5501060				ALTERNATE STATIC LINE CHAFED THROUGH IN CO-PILOTS SIDEWALL IN COCKPIT.  REPLACED LINE WITH NEW BUT THE LOCATION IS VERY 	DIFFICULT TO PREVENT CONTINUED CHAFING.  RECOMMEND MFG LOOK AT THIS AREA AND POSSIBLE REROUTING.					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005052400039	20050524	00039	CE  	2005	5	24	2005FA0000732    	1	20050503	G	3411	651447411	STATIC LINE     			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						CHAFED          	B			N81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	669B	890  				5501060				ALTERNATE STATIC LINE CHAFED THROUGH IN CO-PILOTS SIDEWALL IN COCKPIT.  REPLACED LINE WITH NEW BUT THE LOCATION IS VERY 	DIFFICULT TO PREVENT CONTINUED CHAFING.  RECCOMEND MFG LOOK AT THIS AREA AND POSSIBLE REROUTING.					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005052400040	20050524	00040	CE  	2005	5	24	2005FA0000733    	1	20050503	G	3411	651447411	STATIC LINE     			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						CHAFED          	B			N81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	669B	890  				5501060				ALTERNATE STATIC LINE CHAFED THROUGH IN CO-PILOTS SIDEWALL IN COCKPIT.  REPLACED LINE WITH NEW BUT THE LOCATION IS VERY 	DIFFICULT TO PREVENT CONTINUED CHAFING.  RECOMMEND MFG LOOK AT THIS AREA AND POSSIBLE REROUTING.					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005053100081	20050531	00081		2005	5	31	2005FA0000734    	4	20050517	G	3452	CI105	ANTENNA         			PIPER 	PA46  	PA46500TP   	7104622	SO  										NR 1 TRANSPONDER	BROKEN          	B				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SO	11	175WB					4697181				NR 1 TRANSPONDER ANTENNA BROKEN OFF DURING FLIGHT.						1	L	7	1 	3O			RT	A25SO   					 
2005060100018	20050601	00018	CE  	2005	6	1	2005FA0000735    	1	20050504	G	2821	33199C	GASKET          	RAYTHN      		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					FUEL STRAINER	OUT OF POSITION 	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	4488Q	100  				TH2088				THE MATERIAL THE UPPER AND LOWER GASKETS ARE NOW MADE OF IS MUCH SOFTER THAN THE ORIGINAL DESIGN.  THEY TEND TO COMPRESS	 AND SLIDE OUT FROM UNDER THE STRAINER WALL INTO THE CENTER OF THE FUEL STRAINER BODY AND BEGAN TO LEAK FUEL.  THE STRAI	NER HOUSING IS NOT MACHINED TO HOLD THE SOFTER GASKET.  (K)				1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005060100020	20050601	00020	EU  	2005	6	1	2005FA0000736    	1	20050513	G	3040		CONNECTOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A60A     	52043	NE  					LT WINDSHIELD	DAMAGED         	B			K5SR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			NM	07	956PC	1536 				323				LT WINDSHIELD HEAT FOUND BURNED/OVERHEATED WIRING CONNECTOR AT CENTER ELEMENT POSITIVE WIRE ATTACH TOP OB CORNER OF WIND	SHIELD.  NO DAMAGE TO WIRING NOTED.  SYSTEM WAS PREVIOUSLY INSPECTED IAW SB.  ALL ITEMS CHECKED SATISFACTORY.  (NO COMPO	NENT FAILED, ONLY THE CONNECTOR WAS DAMAGED) (K)				1	L	7	1 	3T	4	T	RT	A78EU   	E4EA				 
2005060100050	20050601	00050	EA  	2005	6	1	2005FA0000737    	2	20050506	G	8520	5015	STUD            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					NR 4 CYLINDER	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9816C					28R7837222				NR 4 CYLINDER BASE STUD FAILED IN TENSION.  NUT AND 30 PERCENT OF STUD LENGTH FOUND BETWEEN NR2 AND NR4 CYLINDERS ON THE	 INNER CYLINDER BAFFLE.  NR 4 CYLINDER REMOVED AND REMAINING  PARTIAL STUD REMOVED WITH STUD EXTRACTOR.  INSTALLED NEW S	TUD, PN 50-15 AND REPLACED REMOVED CYLINDER.  TORQUED TO RECOMMENDED TORQUE (600 IN LBS) IAW MFG MM.  PROBABLE CAUSE: ME	TAL FATIGUE DUE TO AGE OF ENG CRANKCASE STUDS AND NR OF CYLINDER REMOVAL AND REPLACEMENTS DURING THE ENG LIFETIME.  AC, 	MOST OF LIFE AS TRAINING AC.  THROUGH INSP OF AND OR REPLACEMENT OF CYL BASE STUDS DURING ENG O/H WITH MANDATORY REPLACE	MENT TIME PERIODS OR CYCLES. (GL11200510739) (K)	1	L	7	1 	3O	3	O		2A13    	1E10				 
2005060100051	20050601	00051	SO  	2005	6	1	2005FA0000738    	2	20050328	G	8530	FRST712CCA01	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	2284L					E929				THIS CYLINDER CRACKED ALL THE WAY AROUND THE TOP OF THE BARRELL.  DATE OF OCCURANCE 04/26/2004.  (K)						1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005060100056	20050601	00056	NM  	2005	6	1	2005FA0000739    	1	20050418	G	3213	161N16264	AXLE            			BOEING	757   	757*        	       	NM  										MLG	BROKEN          	G			XC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01		39308				620				(REF: PO0043200R011)AXLE WAS FOUND BROKEN NEAR THE CENTER POINT THAT WAS CONCEALED BY THE TRUCK BEAM DEGES OF THE FRACTU	RE SHOW SEVERE CORROSION AND PEELED CHROME PLATING.  (K)					2	L	7	2 	4F			RT	A2NM    					 
2005060100098	20050601	00098	CE  	2005	6	1	2005FA0000740    	1	20050425	G	2740	07612053	ROLL PIN        			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470*       	17026	SO  					STAB TRIM WHEEL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	15BF	4774 				18052353				FOUND ROLL PIN BROKEN DURING 100 HOUR INSPECTION.  APPEARS TO HAVE FAILED UNDER NORMAL OPERATING CONDITIONS.  RECOMMEND 	INSPECTION OF THIS ASSEMBLY WITHIN 25 HOURS AND AT 100 HOUR INSPECTIONS THEREAFTER.  (K)					1	H	7	1 	3O	3	O		5A6     	E273				 
2005060100101	20050601	00101	CE  	2005	6	1	2005FA0000741    	1	20050202	G	3710	ADV211CC	PUMP            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	OVERHEATED      	D				K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			GL	15	54589	299  				17275007				REMOVED VACUUM PUMP DUE TO TOTAL FAILURE AND OVERHEAT CONDITION, MELTED TACH CABLE THAT RUNS ABOUT 1 INCH AWAY, THIS IS 	THE SECOND FAILURE IN THE FLEET WITH OVERHEAT CONDITION, BOTH PUMPS HAD LESS THAN 300 HOURS SINCE NEW.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005060100102	20050601	00102	CE  	2005	6	1	2005FA0000742    	1	20050202	G	3710	ADV211CC	PUMP            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	OVERHEATED      	D				K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			GL	15	65045	287  				17275674				REMOVED VACUUM PUMP DUE TO OVERHEAT CONDITION, BACK OF PUMP WAS DISCOLORED, THE TACH CABLE THAT RUNS ABOUT 1 INCH AWAY F	ROM THE VACUUM PUMP WAS MELTED ABOUT 4 INCHES.  THIS IS THE SECOND PUMP IN THE FLEET WITH THIS TYPE OF FAILURE, BOTH PUP	S HAD LESS THAN 300 HOURS SINCE NEW.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005060100103	20050601	00103	EA  	2005	6	1	2005FA0000743    	2	20050505	G	8520	LW17226	CRANKSHAFT      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	IO360E1A    	41514	EA  					RT ENGINE	FRACTURED       	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	09	28721	*    	1894 			447995296	RL14972T			RT ENGINE STARTED RUNNING ROUGH, THEN STOPPED AND WENT INTO FEATHER.  AC LANDED WITHOUT INCIDENT.  UPON INVESTIGATION IT	 WAS FOUND THAT WHEN THE PROPELLER WAS ROTATED THE AFT CYLINDERS (NR 3, NR 4) PISTONS WOULD NOT MOVE NOR DID ANY ACCESSO	RIES ON THE BACK OF THE ENGINE MOVE.  SUSPECT A CLEAN CRANKSHAFT FAILURE (FRACTURE).  NO EXTERNAL CRANKCASE DAMAGE NOTED	.  (K)			1	L	7	2 	3O	3	O		A19S0   	1E10				 
2005060100106	20050601	00106		2005	6	1	2005FA0000744    	1	20050421	G	4980		BAFFLE          																	APU EXHAUST	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										INTERNAL LINER MISSING AND BAFFLE PLATES CRACKED.  CAUSED BY APU ENGINE VIBRATION.  (K)																			 
2005060100120	20050601	00120	EU  	2005	6	1	2005FA0000745    	1	20050411	G	7160	350A54108004	INTAKE          			SNIAS 	350   	AS350*      	       	EU  										ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										AIR INTAKE, CRACKED BASE METAL DUE TO VIBRATION. (K)						1	G	7	1 	3U				H9EU    					 
2005060100156	20050601	00156	EA  	2005	6	1	2005FA0000746    	1	20050411	G	3210	C6UM11108	LANDING GEAR    			DHAV  	DHC6  	DHC6*       	2802606	EA  										MLG	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										MAIN GEAR LEG, CRACK IN BASE METAL DUE TO CYCLIC LANDING STRESSES. (K)						1	H	7	2 	3T				A9EA    					 
2005060100157	20050601	00157		2005	6	1	2005FA0000747    	1	20050412	G	7921	S5411267000000	OIL COOLER      																	UPPER	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										UPPER OIL COOLER AND DEICER, BASE METAL CRACKED DUE TO VIBRATION.  (K)																			 
2005060100158	20050601	00158	SO  	2005	6	1	2005FA0000748    	1	20050501	G	8011		DRIVE GEAR      			PIPER 	PA28  	PA28150     	7102804	SO  	LYC   	O360  	IO360A1A    	41514	EA  					STARTER	CORRODED        	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	5906W				E073209	282814	L991436			STARTER BENDIX DRIVE HAS EVIDENCE OF RUST AND CORROSION ON AT LEAST 1 GEAR TOOTH.  THE BENDIX DRIVE GEAR TOOTH BROKE.  S	HEERING THE REMAINING BENDIX TEETH AS THEY MESHED WITH THE MATING RING GEAR.  (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
2005060100159	20050601	00159	EA  	2005	6	1	2005FA0000749    	2	20050501	G	7322	105217	CARBURETOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	LEAKING         	B			WS9R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	07	8405S					288116255	L776239A			CARBURETOR LEAKS FROM THROTTLE SHAFT AND FROM ACCELERATOR PUMP.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2005060100160	20050601	00160	CE  	2005	6	1	2005FA0000750    	1	20050501	G	8011	ES6462751	STARTER         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	421GW		131  			421B0873	608257			STARTER INOPERATIVE.  (K)						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005060100161	20050601	00161	CE  	2005	6	1	2005FA0000751    	1	20050501	G	8011		DRIVE GEAR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					STARTER	CRACKED         	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	4609Q				E053694	17261724	L959339A			STARTER BROKE.  VISUAL INSPECTION FOUND BENDIX DRIVE GEAR CRACKED AND APPEARS BENT.  END BUSHING IS ALSO CRACKED.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005060100167	20050601	00167	CE  	2005	6	1	2005FA0000752    	1	20050104	G	2822	A8160D	PUMP            			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					FUEL SYSTEM	OBSTRUCTED      	B			NE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2182F	142  				18281340				RECEIVED BOOST PUMP FOR WARRANTY CREDIT WITH A CUSTOMER COMPLAINT OF (BREAKER POPS WHEN FUEL PUMP IS TURNED ON).  PRELIM	INARY INSPECTION OF THE PUMP REVEALED FOREIGN MATERIAL IN THE INLET PORT.  FURTHER INSPECTION OF THE PUMP REVEALED THE F	OREIGN MATERIAL TRIED TO PASS THROUGH THE PUMP AND HAD LOCKED THE ROTOR IN THE INSERT.  THIS WOULD CAUSE THE PUMP TO DRA	W HIGH AMPS.  (K)			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005060100175	20050601	00175	SO  	2005	6	1	2005FA0000753    	1	20050503	G	2910	4613800	HYDRAULIC LINE  			PIPER 	PA31T 	PA31T       	7103124	SO  										HYDRAULIC SYS	RUPTURED        	G				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			GL	21	2338V					31T8020049				POST ACCIDENT INSP REVEALED HYD SYSTEM DRAIN/FILL LINE HAD RUPTURED/BURST CAUSING RAPID LOSS OF HYD RESERVOIR CONTENTS. 	 SELECTED GEAR DOWN, GEAR DID NOT EXTEND.  ATTEMPTED EMER MANUAL GEAR EXTEN, (FELT GEAR COMING DOWN) LOST HYD PRESSURE. 	UNABLE TO SECURE GEAR IN DOWN AND LOCKED.  AC SUSTAINED DAMAGE DURING EMER LANDING.  FAILURE OF HYD DRAIN LINE CAUSED RA	PID LOSS OF HYD FLUID RESERVOIR CONTENTS.  FAILURE PREVENTED HYD SYS PRESSURE TO BUILD TO ALLOW NORMAL OR EMERGENCY EXTE	NSION OF THE LANDING GEAR.  LINE FAILED PARALLEL TO GRAIN STRUCTURE RUPTURE APPROX 0.5625 IN LENGTH.  WATER CONTAMINATIO	N IN LINE FROZE, EXPANDED, CAUSING RUPTURE.  SUGGEST REGULAR PURGE/DRAIN OF LINE CONTENTS DURING PLANNED MAINT. (K)	1	L	7	2 	3T				A8EA    					 
2005060100198	20050601	00198	SO  	2005	6	1	2005FA0000754    	1	20050511	G	2821	2230600	GASCOLATOR      			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540*       	41532	EA  					FUEL SYSTEM	CONTAMINATED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	4514Y					254066				DURING AN ACCIDENT INVESTIGATION FUEL GASCOLATOR WAS FOUND WITH LARGE AMOUNTS OF WATER AND SOLID CONTAMINANTS.  IT WAS N	OTED THAT THE PART COULD NOT BE ROTATED TO ENSURE DRAINAGE OF CONTAMINANTS WHEN AC IS ON THE GROUND DUE TO COWL SUPPORT 	STRUTS INTERFERENCE.  GASCOLATOR COULD BE RELOCATED 2 INCHES IB TO ENSURE CLEARANCE OF THE COWL SUPPORT STRUTS.  THE CON	TAMINANTS COULD NOT BE DRAINED OUT EFFECTIVELY. (SW09200512483) (K)			1	L	7	1 	3O	3	O		2A10    	E295				 
2005060100213	20050601	00213		2005	6	1	2005FA0000756    	2	20050314	G	8520	SA629340	ROD BOLT        																	ENGINE	DEFECTIVE       	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										UNABLE TO ACHIEVE PROPER BOLT TORQUE AND ALIGN COTTER PIN HOLES WITH CASTELATED NUT.  HOLES IN DRILLED HEAD MISALIGNED. 	 (K)																		 
2005060100214	20050601	00214		2005	6	1	2005FA0000757    	2	20050314	G	7414		RETAINER        	BENDIX      																MAGNETO	OUT OF POSITION 	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		10   			F0FA246R					MAGNETO COIL RETAINING WEDGE HAS FALLEN OUT AND BECAME LODGED BETWEEN THE GEAR TEETH, CAUSING THEM TO BREAK OFF.  ALSO, 	APPEARS THAT THE DISTRIBUTOR BLOCK WAS CRACKED AND FAILED DUE TO THIS OTHER DEFECT.  (K)																		 
2005060100215	20050601	00215		2005	6	1	2005FA0000758    	1	20050322	G	8011		DRIVE GEAR      	LAMAR       							LYC   	IO360 	IO360L2A    	 	EA  					STARTER	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07					85522811		L1766751A			STARTER BENDIX FAILED, DESTROYING ITSELF AND THE MATING RING GEAR.  (K)											3	O			1E10				 
2005060200056	20050602	00056	EA  	2005	6	2	2005FA0000760    	2	20050426	G	8500	R182097	ENGINE          			BOEING	B17   	B17G        	1380204	WP  	WRIGHT	R1820 	R182097     	67020	EA  					NR 3	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	3703G		11   			4483546A	036743			UPON ANNUAL INSPECTION, ENGINE WAS FOUND TO BE SEIZED, CHECKED FOR OIL IN GIL TANK, 25 GAL REMAINING.  ENGINE REMOVED FR	OM AC.  UPON REMOVAL OF PROPELLER, PROP SHAFT WAS FULL OF METAL.  NOSE CASE FAILURE.  (K)					2	L	7	4 	4R	4	R		L13     	5E10				 
2005060200058	20050602	00058	EA  	2005	6	2	2005FA0000761    	2	20050426	G	8500	R182097	ENGINE          			BOEING	B17   	B17G        	1380204	WP  	WRIGHT	R1820 	R182097     	67020	EA  					NR 3	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	3703G					4483546A	082437			UPON INSTALLATION OF ENGINE AT NR 3 POSITION,  METAL WAS FOUND IN PROPELLER SHAFT.  ENGINE HAD RUN IN TIME ONLY AS -0- T	SMO.  ENGINE REMOVED AND NOT RUN ON AIRCRAFT. (K)					2	L	7	4 	4R	4	R		L13     	5E10				 
2005060200065	20050602	00065	CE  	2005	6	2	2005FA0000762    	1	20050108	G	3340	3538013243	SWITCH          			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					COCKPIT	FAULTY          	D				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			EA	17	3267N					TH1767				INTERNAL UPPER BRAIDED CONDUCTOR ON LINE SIDE FAILED, SEPARATED FROM ITS CONTACT OR WELD.  SPRING MECHANISM FOR SWITCH B	ECOMES CONDUCTOR.  SPRING CAN NOT HANDLE THE CURRENT OF LANDING LIGHT CIRCUIT, AND OVERHEATS.  OVERHEATING OF SPRING CAU	SED NYLON TOGGLE ASSY TO FAIL. TOGGLE ASSY IS RENDERED USELESS, SWITCH LOOSES ALL MECHANICAL FUNCTION.  SWITCH CONTINUES	 TO COMPLETE CIRCUIT, OVERHEAT MELTING THE SWITCH HSG.  AS HSG AND OTHER INTERNAL COMPONENTS FAIL, SWITCH LOOSES ITS CIR	CUIT PROTECTION FEATURE, SMOKE IS EMITTED INTO COCKPIT.  THIS PROCESS WILL ONLY DISCONTINUE WHEN ALL POWER IS REMOVED.  	ONCE POWER IS REMOVED FROM AC, SWITCH WILL COOL ALLOWING UPPER CONTACT TO OPEN, WHICH OPENS THE CIRCUIT. (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005052300131	20050523	00131	CE  	2005	5	23	2005FA0000763    	1	20050502	G	3230		FITTING         			CESSNA	206   	U206F       	2073333	CE  										FLOAT	FAILED          	G				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			GL	21	114GS					U20603077				THIS AIRCRAFT IS EQUIPPED WITH MFG AMPHIBIAN FLOATS.  DURING FLIGHT, HYDRAULIC PUMP TURNED ON AND WOULD NOT SHUT OFF.  P	ILOT PULLED BREAKER AND NOTED BLUE LIGHTS INDICATION GEAR UP WERE NOT LIT.  PILOT RESET BREAKER AND SELECTED GEAR DOWN. 	GEAR WOULD NOT SHOW GREEN ON ANY OF 4 LANDING GEAR.  PILOT MADE LANDING WITH MAIL WHEELS PARTIALLY EXTENDED.  MINOR DAMA	GE TO KEEL STRIPS.  INVESTIGATION REVEALED GEAR PRESSURE HOSE BULKHEAD FITTING IN LT FLOAT FAILED DUE TO CORROSION OF B-	NUT ON FITTING WERE FRONT STRUT ATTACHES TO FLOAT.		1	H	7	1 	3O				A4CE    					 
2005052300132	20050523	00132		2005	5	23	2005FA0000764    	4	20050502	G	3197	89340002	ANNUNCIATOR     			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					COKCPIT	MISWIRED        	B				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			SO	15	939ER	4    				4496201				AC WITH INCONSISTENT ANNUNCIATOR INDICATIONS.  DURING REPAIR, TROUBLESHOT SYS, CONFIRMED DISCREPANCY:  OIL LIGHT AND GEA	R WARNING LIGHT FLICKERS ON THEN OFF ON ANNUN PANEL, REMOVED ANNUN PANEL, FOUND WIRE TO PTT LIGHT TEST INTERFACE PLUG PI	N 3 TO ANNUN PANEL GROUND MISWIRED.  INSTALLED NEW ANNUN PANEL, FOUND LOW BUS LIGHT INOP, HEATER OVER TEMP LIGHT INOP ON	 PTT TEST. REPAIRED WIRE ON ORIGINAL ANNUN PANEL IAW MFG MM.  REINSTALLED ORIGINAL UNIT ONTO PANEL. PLACED AC ON JACKS, 	PERFORMED GEAR SWING TO VERIFY GEAR UNSAFE WARNING ANNUNCIATOR LIGHT, AND THROTTLE HORN/LIGHT COMBINATION.  PERFORMED EN	G RUN UP AND VERIFIED OIL LIGHT ANNUNCIATION, PERFORMED PTT LIGHT TEST ON ANNUN PANEL, NO DEFECTS NOTED.	1	L	7	2 	3O	3	O		A19S0   	E286				 
2005052400010	20050524	00010	SO  	2005	5	24	2005FA0000765    	1	20050503	G	2741	63585003	TRIM TAB        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O360  	O360*       	41514	EA  						CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8461T	9168 				288216057				LT AND RT TRIM TABS CRACKED AT IB LOCATION WHERE THEY ARE CONNECTED TOGETHER.  SKINS AND IB RIBS WERE CRACKED ABOUT 1 IN	CH ON RIBS AND SKINS.					1	L	7	1 	3O	3	O		2A13    	E286				 
2005052400042	20050524	00042	EA  	2005	5	24	2005FA0000766    	2	20050503	G	8530	LW12215	CYLINDER        			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	34KA		625  			P262	L93359			DURING DIFFERENTIAL COMPRESSION TEST, AIR WAS HEARD LEAKING FROM LOWER CYLINDER AREA.  COMPRESSION WAS 40/80.  USING LIQ	UID LEAK DETECTOR, FOUND AIR BLOWING OUT FROM A CRACK IN CYLINDER FIN.  REMOVED CYLINDER FROM ENGINE AND NOTED A CRACK I	N THE COMBUSTION CHAMBER RUNNING FROM LOWER SPARK PLUG HOLE TO INTAKE VALVE.				1	L	7	2 	3O	3	O		A12CE   	E10EA				 
2005052400141	20050524	00141	EA  	2005	5	24	2005FA0000767    	2	20050505	G	8520		CAMSHAFT        			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					LT ENGINE	BROKEN          	B				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			GL	21	325YH		1413 			317812007	L628561A			THE LT ENGINE STOPPED IN CRUISE FLIGHT.  AFTER INVESTIGATION IT WAS FOUND THE CAM HAD FAILED JUST FORWARD OF THE NR 5 AN	D NR 6 CYLINDERS AND CRACKED THE LT CASE HALF.  TBO IS 1800HRS, COMPONENT TIME IS 1413.3 TSMOH.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005052400295	20050524	00295	CE  	2005	5	24	2005FA0000768    	1	20050506	G	7722	86317	PROBE           			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE CHT/EGT	LOOSE           	B				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CE	07	2116X	207  				18281318				"OMEGA" BRAND NAME OF CONNECTORS USED ON THE ALCOR CHT/EGT PROBES. THE SCREWS THAT HOLD THE CONNECTOR AND CONNECTION OF 	THE WIRE FOR THE PROBES WILL WORK LOOSE CAUSING A FALSE OR NO INDICATION ON THE G-1000 SYSTEM. NEEDS TO HAVE SOMEWAY TO 	LOCK THE SCREWS INTO PLACE, SUCH AS LOCTITE OR A STAR WASHER. NOTE, THIS HAS BEEN AN ONGOING PROBLEM.				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005052600206	20050526	00206	SO  	2005	5	26	2005FA0000769    	1	20050513	G	3250	95394	BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG STEERING	BROKEN          	G				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			SO	19	865SC					347970265				PILOT REPORTS TO CONTROL TOWER ON FINAL APPROACH, AN UNSAFE NOSE GEAR INDICATION (NO GREEN).  TOWER OBSERVED NOSE GEAR, 	BUT COULD NOT VERIFY DOWN AND LOCK. PILOT ATTEMPTS EMERGENCY GEAR EXTENSION AND CYCLES GEAR. THE NOSE GEAR STILL WILL NO	T EXTEND AND LOCK. AIRCRAFT LANDS AND NOSE GEAR COLLAPSES ON TOUCHDOWN.  MAINTENANCE PLACES AIRCRAFT ON JACKS AND EXTEND	S NOSE GEAR TO DOWN AND LOCKED POSITION. A BRACKET FALLS FROM NOSE GEAR AREA. STEERING BRACKET HELPS KEEP GEAR ALIGNED W	HEN EXTENDED AND RETRACTED.		1	L	7	2 	3O				A7SO    					 
2005060200074	20050602	00074	SO  	2005	6	2	2005FA0000770    	2	20050519	G	8520	632041F	ROD             			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520B    	17040	SO  					ENGINE	BROKEN          	G				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			GL	21	6131X	3709 	123  			310R1296	183838H			DURING CRUISE FLT, ENG BEGAN TO VIBRATE SEVERELY AND PILOT SHUTDOWN.  TEARDOWN AND INVESTIGATION REVEALED THE NR 2 ROD B	ROKE 1/2 WAY BETWEEN PISTON AND CRANK.  IT IS SUSPECTED THIS ENG ENCOUNTERED LIQUID LOCK AT SOME TIME CAUSING A BENT ROD	 THAT EVENTUALLY FAILED.				1	L	7	2 	3O	3	O		3A10    	E8CE				 
2005060700190	20050607	00190	CE  	2005	6	7	2005FA0000771    	1	20050414	G	2510	MM201088	LOCK            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O320  	O320*       	41508	EA  					SEAT BACK	SLIPPED         	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	17	9795B	5379 				172RG1042	L3001936A			WHEN COPILOT LEANED AGAINST THE SEAT BACK LOCK FAILED AND ALLOWED THE BACK TO FULLY BE IN THE AFT POSITION.  (GL17200503	735) (K)					1	H	7	1 	3O	3	O		3A17    	E274				 
2005060700192	20050607	00192	NM  	2005	6	7	2005FA0000772    	1	20050505	G	5302	500N3422	FITTING         			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47B     	 	GL  					TAILBOOM	CRACKED         	B			IL3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	451DL	638  				RN042				UPPER RT TAILBOOM ATTACH FITTING CRACKED.  THIS IS THE SAME AREA COVERED IN AD AND SB, 25 HOUR INSPECTION. (K)						1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2005060200075	20050602	00075	GL  	2005	6	2	2005FA0000773    	3	20050519	G	6114	3E1951	PLATE           								CONT  	O550  	IO550B      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	SCORED          	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	328M	555  								WHILE PERFORMING HARTZELL PROPELLER SERVICE LETTER HC-SL-61-239, AND RAYTHEON MANDATORY SERVICE BULLETIN 61-3706 PART"B"	, SCORING WAS FOUND ON ALL PROPELLER SPLIT MOUNTING PLATES, DUE TO NO MOUNTING WASHERS INSTALLED. THE PLATES WERE REPLAC	ED WITH NEW ONES, P/N 3E1951, AND THE PROPER WASHERS WERE INSTALLED, P/N A1381. INSPECTION OF THE PROPELLER HUB AND MOUN	T STUDS HAD NEGATIVE DEFECTS.								3	O			E3SO	5	C	P36EA	 
2005060700194	20050607	00194	CE  	2005	6	7	2005FA0000774    	1	20050510	G	8011	65556624	STARTER         			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	LTSIO520AE  	17040	SO  					ENGINE	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	9488C	30   				T30300180	246729R			DURING TAKEOFF THE (STARTER ENGAGED) LAMP ILLUMINATED INDICATING HAD SELF ENGAGED.  AIRCRAFT LANDED.  STARTER NOT BURNED	 UP BUT INTERNAL ACTION SOUNDS UNUSUAL.  NOTE: THIS IS THIRD STARTER FAILURE IN 5 WEEKS. (K)					1	L	7	2 	3O	3	O		A34CE   	E8CE				 
2005060700196	20050607	00196		2005	6	7	2005FA0000775    	1	20050510	G	2435	M2399	ARMATURE        	ELECTROSYS  																STARTER MOTOR	UNSERVICEABLE   	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19					8021149					PILOT REPORTED UNUSUAL NOISE DURING ATTEMPTED START.  REMOVED AND DISASSEMBLED STARTER.  FOUND THE GEAR SPLINES ON ARMAT	URE SHAFT CRACKED AND SHEARED.  SHOWS THESE SPLINES ARE NOT VERY DURABLE, RECOMMEND REGULAR OVERHAUL INSPECTION.  (K)																		 
2005060700197	20050607	00197	SO  	2005	6	7	2005FA0000776    	1	20050503	G	5540		FLANGE          			PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6*        	52043	EA  					RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	85KG	3539 				31T1104017				PILOT REPORTED AIRCRAFT YAW IN FLIGHT.  CABLE TENSION HAD PREVIOUSLY BEEN ADJUSTED BUT WAS LOOSE AGAIN.  FOUND FLANGE CR	ACKED AT AFT BOLT ON PILOT SIDE RUDDER TORQUE TUBE BEARING.  CAUSE UNKNOWN BUT POSSIBLE EXCESS RUDDER PEDAL FORCE WITH A	IRCRAFT ON GROUND AND NOT MOVING.  (K)				1	L	7	2 	3T	3	T		A8EA    	E2NE				 
2005060700198	20050607	00198	GL  	2005	6	7	2005FA0000777    	1	20050413	G	6120	B65091	SPRING          			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROPELLER DOME	FRACTURED       	B			AKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	269SB	1337 				1160		JC130B		PROPELLER PITCH WENT UNCONTROLLABLE IN STRAIGHT AND LEVEL FLIGHT.  SPRING HAD ONE COMPLETE FRACTURE AND AT LEAST 4 INCOM	PLETE FRACTURES.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
2005060800002	20050608	00002	CE  	2005	6	8	2005FA0000778    	1	20050412	G	6120	B24913	ROD             	HARTZL      		BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470*      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	PITCH CHANGE	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	4522S				AN493	TC1889		AN493		(17590) OLD STYLE 2 PIECE PITCH CHANGE ROD CRACKED AND SEPARATED AT MATING JOINT IN FLIGHT CAUSING PROPELLER TO INADVERT	ENTLY FEATHER.  THE PROBABLE CAUSE OF THIS IS DUE TO WEAK CONSTRUCTION.  THE MANUFACTURER SHOULD CONSIDER MANDATORY REPL	ACEMENT OF ALL OLD STYLE 2 PIECE PITCH CHANGE RODS AT THE TIME OF NEXT DISASSEMBLY AND UPGRADING TO A NEW STYLE 1 PIECE 	PITCH CHANGE ROD TO PREVENT ANY POSSIBLE RECURRENCE.  (K)			1	L	7	2 	3O	3	O		3A16    	E1CE	5	C	P920	 
2005060800037	20050608	00037	WP  	2005	6	8	2005FA0000779    	2	20050412	G	7200		ENGINE          			AMD   	FALC20	FALCON      	2720302	EU  	GARRTT	ATF3  	ATF36       	29002	WP  					NR 2	LEAKING         	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	200GT	1373 				137	P21			ENGINE EXPERIENCED LOW OIL PRESSURE IN FLIGHT.  PRECAUTIONARY SHUTDOWN PERFORMED.  23 PSI LOWEST READING ON OIL PRESSURE	 INDICATOR.  OIL PRESSURE NEVER WENT TO -0- PSI.  NO ABNORMAL VIBRATION EXPERIENCED.  PRECAUTIONARY SHUTDOWN PERFORMED O	N NR 2 ENGINE.  EMERGENCY DECLARED.  ENGINE ROTATION NORMAL AFTER SHUTDOWN.  ENGINE DID NOT LOCK UP.  OIL QUANTITY INDIC	ATION AT BOTTOM OF DIPSTICK ON ARRIVAL.  EVIDENCE OF OIL LEAKING IN FAN BYPASS AREA OF ENGINE.  (K)			2	L	7	2 	4F	4	F		A7EU    	E7WE				 
2005060800038	20050608	00038	CE  	2005	6	8	2005FA0000780    	1	20050405	G	3233	66000264001	ACTUATOR        			LEAR  	60    	60LEAR      	5170707	CE  										MLG	FAILED          	B			LK2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07										WHILE PERFORMING A FUNCTIONAL TEST OF THE MAIN LANDING GEAR SIDE BRACE ACTUATOR, THE TEST BENCH IN OVERHAUL SHOP, FROZE 	UP.  FURTHER INVESTIGATION REVEALED THAT AN ORIFICE LOCATED INSIDE THE ACTUATOR HAD DISLODGED FROM ITS ORIGINAL DESIGNED	 LOCATION WITHIN THE ACTUATOR.  THE DISCREPANT ACTUATORS  ARE PART OF A SB FOR IMPROVED BRAKING.  (K)				2	L	7	2 	4F			RT	A10CE   					 
2005060800039	20050608	00039	SO  	2005	6	8	2005FA0000781    	2	20050307	G	7421	RHB32S	SPARK PLUG      			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					ENGINE	INTERMITTENT    	B			BWVR	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	07	998PM	678  				E3251				ENGINE PERFORMANCE ROUGH ABOVE 10,000 FT.  APPEARS TO BE LIKE MISS LT OR RT MAG.  INSPECTED AIR FILTER, CHECKED OK.  INS	PECTED LT AND RT MUFFLERS FOR BLOCKAGE CHECKED OK,  CHECKED ALL IGNITION WIRES WITH HIGH TENSION TEST ON CHECKED OK.  CH	ECKED MAG TIMING CHECKED OK.  FLOWED FUEL INJECTION LINES AND CLEANED FUEL NOZZLES AND CLEANED MAIN FUEL SCREEN AND ENGI	NE FUEL SCREEN.  REPLACED ALL 12 SPARK PLUGS AND GASKETS.  RAN AND OPS CHECKED GOOD.  (K)			1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005060800040	20050608	00040	NE  	2005	6	8	2005FA0000782    	2	20050511	G	8530	399354	CYLINDER HEAD   			WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985AN14B   	52008	NE  					NR 2	SEPARATED       	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			CE	07	9026F	7070 	43   			1639	20590			DURING SPRAYING OPERATION, THE AIRCRAFT WAS CLIMBING INTO A RT TURN.  THE PILOT HEARD A LOUD BANG, AND THE ENGINE BEGAN 	RUNNING EXTREMELY ROUGH.  THE AIRCRAFT MADE A FORCED LANDING.  INSPECTION OF THE ENGINE FOUND THE NR 2 CYLINDER HEAD SEP	ARATED FROM THE SLEEVE AT THE NR 3 LARGER COOLING FIN FROM THE BOTTOM.  AD WAS COMPLIED WITH DURING LAST OVERHAUL, 43 HO	URS EARLIER. (CE07200513320) (K)			1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2005060800041	20050608	00041		2005	6	8	2005FA0000783    	4	20050421	G	6122	D20880	RETAINER        	MCAULY      							LYC   	O540  	IO540*      	41532	EA  					FLYWEIGHT	DAMAGED         	B			GCDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17					001989					(22209)  FLYWEIGHT RETAINING DISC DAMAGED.  (K)											3	O			1E4				 
2005060800042	20050608	00042	CE  	2005	6	8	2005FA0000784    	1	20050510	G	8120		BEARING         			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	TURBOCHARGER	FAILED          	B			J7BR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	01	4243C	407  			CHL00379	4140539	519943	984062		PILOT EXPERIENCED MANIFOLD FLUCTUATIONS DURING FLIGHT.  A PRECAUTIONARY LANDING WAS MADE.  AN INSPECTION REVEALED FAILED	 TURBINE SHAFT BEARINGS.  THE TURBOCHARGER WAS REPLACED WITH A NEW IDENTICAL UNIT.  (K)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2005060800045	20050608	00045	SW  	2005	6	8	2005FA0000785    	1	20050511	G	6310	SKCP2281103	DRIVE SHAFT     			BELL  	204   	UH1H        	1181407	SW  	LYC   	T53   	T53L13B     	41549	NE  					ENG TO TRANSMISS	VIBRATION       	B			LS1R	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			EA	13	53AG					7221588	LE21990R			( 2005-5-1) PILOT NOTICED VIBRATION AND RUMBLE COMING FROM THE MAIN TRANSMISSION AREA ON TAKEOFF.  MECHANIC DID TROUBLE 	TROUBLESHOOTING PROCEDURES AND NOTICED ONE OF THE FLEX PLATES ON THE MAIN DRIVE SHAFT HAD SNAPPED CAUSING THE DRIVE SHAF	T TO BE IN FAIL SAFE MODE.  DRIVE SHAFT WAS REPLACED AND PILOT CONTINUED. (K)				1	G	7	1 	4U	4	U		EXPA1G71	E17EA				 
2005060800051	20050608	00051	CE  	2005	6	8	2005FA0000786    	1	20050517	G	7500	45A40304011	TUBE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					RT ENGINE	UNSERVICEABLE   	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	101CC	2013 				RK277				DURING INSPECTION FOUND FLEXIBLE BELLOWS EXTENDED DUE TO THE WIRE BRAID FAILURE.  INTEGRITY OF THE BLEED AIR SUPPLY TUBE	 WAS INTACT.  INSPECTION OF THE LT ENGINE TUBE FOUND BRAID PARTIALLY FAILED.  BOTH BLEED AIR SUPPLY TUBES WERE REPLACED 	WITH NEW.  (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2005060800052	20050608	00052	CE  	2005	6	8	2005FA0000787    	1	20050518	G	2510	LC6010030C	LOCK            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					SEAT BACK	FAILED          	B			LW5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	9795B					172RG1042				PILOTS SEAT BACK LOCK MECHANISM SLIPPED AS PILOT LEANED BACK TO GET HIS BAG OUT OF THE REAR SEAT.  UPON REMOVAL FRO AC M	ECHANICS WERE ABLE TO CAUSE SEAT BACK LOCK MECHANISM TO FAIL.  THIS IS THE SECOND FAILURE TO OCCUR WITH THIS MECHANISM. 	  PART LAST FAILURE OCCURRED APPROX A MONTH AGO ON THE CO-PILOTS SEAT (MDR WAS FILED).  WE HAVE NOT YET DONE AN INSPECTI	ON ON THE AC AS YET, DUE TO THE FACT IT IS A LEASE.  PROBABLE CAUSE WAS WEAR IN THE SEAT BACK LOCK MECHANISM, CAUSING IT	 TO SLIP OR NOT FULLY ENGAGED IN THE LOCKED POSITION.  (K)		1	H	7	1 	3O	3	O		3A17    	E286				 
2005060800054	20050608	00054	SO  	2005	6	8	2005FA0000788    	2	20050502	G	7414	K3056	DISTRIBUTOR GEAR	SLICK       		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					MAGNETO	BURNED          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	2224D	991  			97011180	TH1824	683550			DURING DISASSEMBLY OF MAGNETO FOR 500 HR INTERNAL INSPECTION, FOUND DISTRIBUTOR FINGER ON DISTRIBUTOR GEAR SEVERELY BURN	ED WITH MATERIAL MISSING.  FOUND MAGNETO INTERNAL TIMING 2 TEETH OFF FROM SPECIFIED.  SUSPECT INCORRECT INTERNAL TIMING 	CAUSED A LARGE GAP BETWEEN FINGER AND DISTRIBUTOR BLOCK TARGET WHEN FIRING; RESULTING IN EXCESSIVE BURNING AND PITTING O	F DISTRIBUTOR FINGER.  OTHER FACILITY ALSO FOUND THIS CONDITION ON SEVERAL SIMILAR MODEL MAGNETOS DUE TO INCORRECT INTER	NAL TIMING WHEN DISASSEMBLED FOR OVERHAUL.  RECORDS INDICATE MAGNETO POINTS AND CAPACITOR REPLACED LAST ANNUAL INSPECTIO	N.  (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005060800055	20050608	00055	CE  	2005	6	8	2005FA0000789    	1	20050505	G	1430		RIVET           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					STRINGER CLIP	MISSING         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	200ZT	2475 				BB1393				DURING VISUAL INSPECTION OF AFT FUSELAGE STRINGERS AT AFT PRESSURE BULKHEAD FOR COMPLIANCE WITH AD, NOTED (1) RIVET MISS	ING FROM NR7L STINGER CLIP AT ZEE SECTION ATTACHMENT.  RIVET MISSING WAS AT FARTHEST FORWARD POSITION, REQUIRED REMOVING	 INSULATION AND SEALANT FOR GOOD VISUAL ACCESS.  NO DAMAGE WAS NOTED AND RIVET WAS INSTALLED IAW SRM.  SUSPECT RIVET NOT	 INSTALLED AT MANUFACTURE DUE TO CLOSE CLEARANCES AND MARGINAL EDGE DISTANCE.  TECHNICIANS SHOULD BE AWARE THAT SOME POR	TIONS OF THIS AREA THAT IS REQUIRED TO BE INSPECTED MAY REQUIRE SOME EFFORT TO REMOVE INSULATION, SEALANT, ETC.  (K)		1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2005060800056	20050608	00056	EU  	2005	6	8	2005FA0000791    	1	20050412	G	5740	D5755000220539	FITTING         			AIRBUS	320   	A320211     	3930320	EU  										RT WING SPAR	CRACKED         	B			T48R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	754US					283				RT WING REAR SPAR TO AILERON SUPPORT FITTING AT APPROX WS 13484 AND RIB 25 (OB OF AILERON OB ACTUATOR), IS CRACKED AT UP	PER LUG RADIUS.  REMOVED AND REPLACED FITTING (DIAPHRAGM) ASSEMBLY IAW SRM.  (K)					2	L	7	2 	4F			RT	A28NM   					 
2005060800190	20050608	00190		2005	6	8	2005FA0000792    	4	20050526	G	2562	AK450	ANTENNA         																	ELT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										THE ANTENNA BROKE IN THE BASE.  (K)																			 
2005061000009	20050610	00009		2005	6	10	2005FA0000793    	4	20050526	G	2562	AK450	ANTENNA         																	ELT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										THE ANTENNA BROKE IN THE BASE.  (K)																			 
2005060700103	20050607	00103	CE  	2005	6	7	2005FA0000794    	1	20050523	G	5280		DOOR            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					MLG	DELAMINATED     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	4455B					TC2203				IB LANDING GEAR DOORS HAD CORROSION DUE TO DELAMINATION OF FORWARD EDGE OF GEAR DOORS.						1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2005061000053	20050610	00053	CE  	2005	6	10	2005FA0000795    	1	20050526	G	2420	E3FF10300AA	ALTERNATOR      			CESSNA	210   	P210N       	2073454	CE  										ENGINE	BURNED OUT      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	732RS	68   	68   			P21000592				OWNER STARTED HEARING RADIO STATIC AND AFTER A FEW MINUTES,  LOST ELECTRICAL POWER.  ON THE GROUND,  MECHANIC CHECKED RE	GULATOR,  CHECKED OK, CHANGED ALTERNATOR OPS CHECKED OK. PART ONLY HAS 68 HOURS ON THE OVERHAUL.					1	H	7	1 	3O				3A21    					 
2005060900053	20050609	00053	CE  	2005	6	9	2005FA0000796    	1	20050525	G	5312	051310929	DOUBLER         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FIREWALL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	98483	17968				17276298	L946839A	BB048		THESE FIREWALL DOULBLERS ARE INSTALLED FROM FACTORY WITH SOME STRUCTURAL STEEL RIVETS PASSING THROUGH THESE ALUMINUM DOU	BLERS, CAUSING CORROSION TO FORM ON BOTH LT AND RT DOUBLERS VERY NEAR ENGINE DYNAFOCAL MOUNT LOCATIONS, REQUIRING REPLAC	EMENT OF BOTH DOUBLERS.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005061300063	20050613	00063	SO  	2005	6	13	2005FA0000797    	1	20050429	G	3243		MASTER CYLINDER 			PIPER 	PA18  	PA18A150    	7101837	SO  	LYC   	O320  	O320A2B     	41508	EA  					BRAKE ASSY	LEAKING         	G				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AL	03	624M4					188739				NORTH RIVER BRAKE BOOSTERS INSTALLED WITH STC SA2318NM.  BRAKE PLUNGER HAS EXCESSIVE PLAY WHICH CAUSED FLUID TO BYPASS I	NTERNALLY. PILOT LOST DIRECTIONAL CONTROL OF THE AIRCRAFT ON LANDING CAUSING SUBSTANTIAL DAMAGE TO THE AIRCRAFT. THREE P	REVIOUS LANDINGS THAT DAY THE BRAKE FUNCTIONED NORMALLY.  SITUATION COULD BE DUPLICATED BY ALLOWING THE PLUNGER TO FALL 	TO THE RT SIDE AND THEN BE DEPRESSED WITH NO BRAKE ACTUATION AND NO EXTERNAL FLUID LOSS.			1	H	7	1 	3O	3	O		1A2     	E274				 
2005060800100	20050608	00100		2005	6	8	2005FA0000798    	1	20050425	G	4920	38007021	IMPELLER        																	APU	BROKEN          	B				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	07		6880 	6880 							DURING APU OPERATION, A PIECE OF THE 3822400-5 IMPELLER SEPARATED AT THE RIM.  THIS RESULTED IN HIGH VIBRATION LEVELS AN	D CATASTROPHIC DAMAGE TO THE LOAD COMPRESSOR AND POWER SECTIONS.  (K)																		 
2005060800150	20050608	00150	EU  	2005	6	8	2005FA0000799    	1	20050513	G	5541		PLATE           	GROB        		GROB  	120   	G120A       	1660208	EU  										RUDDER SPAR	DEBONDED        	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	1997 				85001				DURING ROUTINE INSPECTION OF AIRCRAFT, TECH FOUND EXCESSIVE MOVEMENT BETWEEN RUDDER AND RUDDER LEVER ASSY.  FURTHER INSP	ECTION SHOWED DISBONDING BETWEEN THE RUDDER SPAR AND THE RUDDER LEVER ASSY SPACER PLATE.  PROBABLE CAUSE APPEARS TO BE E	XCESSIVE FLEXING OF THE SPAR OR IMPROPER BONDING.  (SPAR AND SPACER ARE COMPOSITE MATERIAL) THE SPAR MAY NOT BE RIGID EN	OUGH IN THIS AREA.  RECOMMENDATION AT THIS TIME IS TO INCREASE STRENGTH/RIGIDITY OF THE SPAR AND IMPROVED BONDING METHOD	.  (K)		1	L	7	1 	3O			RT	A49CE   					 
2005060800154	20050608	00154	EU  	2005	6	8	2005FA0000800    	1	20050513	G	5541	120A3115	PLATE           	GROB        		GROB  	120   	G120A       	1660208	EU  										RUDDER SPAR	DEBONDED        	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	1997 				85003				DURING FLEET - WIDE INSPECTION OF AIRCRAFT, TECH FOUND EXCESSIVE MOVEMENT BETWEEN RUDDER AND RUDDER LEVER ASSY.  FURTHER	 INSPECTION SHOWED DISBONDING BETWEEN THE RUDDER SPAR AND THE RUDDER LEVER ASSY SPACER PLATE.  PROBABLE CAUSE APPEARS TO	 BE EXCESSIVE FLEXING OF THE SPAR OR IMPROPER BONDING.  (SPAR AND SPACER ARE COMPOSITE MATERIAL) THE SPAR MAY NOT BE RIG	ID ENOUGH IN THIS AREA.  RECOMMENDATION AT THIS TIME IS TO INCREASE STRENGTH/RIGIDITY OF THE SPAR AND IMPROVED BONDING M	ETHOD.		1	L	7	1 	3O			RT	A49CE   					 
2005060800155	20050608	00155	EU  	2005	6	8	2005FA0000801    	1	20050513	G	5541		PLATE           	GROB        		GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					RUDDER SPAR	DEBONDED        	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	867AF	1589 				85007				DURING FLEET-WIDE INSPECTION OF AIRCRAFT, TECH FOUND EXCESSIVE MOVEMENT BETWEEN RUDDER AND RUDDER LEVER ASSY.  FURTHER I	NSPECTION SHOWED DISBONDING BETWEEN THE RUDDER SPAR AND THE RUDDER LEVER ASSY SPACER PLATE.  PROBABLE CAUSE APPEARS TO B	E EXCESSIVE FLEXING OF THE SPAR OR IMPROPER BONDING.  (SPAR AND SPACER ARE COMPOSITE MATERIAL) THE SPAR MAY NOT BE RIGID	 ENOUGH IN THIS AREA.  RECOMMENDATION AT THIS TIME IS TO INCREASE STRENGTH/RIGIDITY OF THE SPAR AND IMPROVED BONDING MET	HOD.  (K)		1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2005060800161	20050608	00161	CE  	2005	6	8	2005FA0000802    	1	20050523	G	5540	5433000020	RUDDER          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					TAIL	DAMAGED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	249FX					193				UPON REMOVAL AND REPLACEMENT OF RUDDER CABLES, FOUND RUDDER SUPPORT STIFFENER ANGLE CRACKED UNDER RUDDER PRIMARY TRAVEL 	STOP AT FRAME STA 48, ALSO FOUND RUDDER LEADING EDGE PANELS 331,332, AND 333 TO BE CRACKED AND RUDDER FORWARD SPAR TO BE	 DAMAGED AT RUDDER CENTER AND UPPER HINGE POINTS WL 92.34 AND WL 122.83.  PROBABLE CAUSE: RUDDER OVER TRAVELING WHEN GUS	T LOCK NOT INSTALLED AND WHEN PARKED OUTSIDE IN WINDY CONDITIONS.  REC: ENSURE FLIGHT CONTROL GUST LOCKS ARE INSTALLED W	HEN PARKED OUTSIDE.(EA09200505203) (K)		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005060800163	20050608	00163	CE  	2005	6	8	2005FA0000803    	1	20050521	G	5544	5412481026	SUPPORT BRACKET 			LEAR  	60    	60LEAR      	5170707	CE  										RUDDER	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	198HB					198				UPON REINSTALLATION OF RUDDER ASSY, FOUND RUDDER SUPPORT BRACKET AND STIFFENER ANGLE CRACKED UNDER RUDDER PRIMARY TRAVEL	 STOP AT FRAME STA 48.  PROBABLE CAUSE: RUDDER OVER TRAVELING AGAINST PRIMARY STOP, WHEN GUST LOCK NOT INSTALLED AND WHE	N PARKED OUTSIDE N WINDY CONDITIONS.  REC: ENSURE FLIGHT CONTROL GUST LOCKS ARE INSTALLED WHEN PARKED OUTSIDE.  (EA09200	505204) (K)			2	L	7	2 	4F			RT	A10CE   					 
2005060800171	20050608	00171	NM  	2005	6	8	2005FA0000804    	1	20050523	G	2621	M80530044	SEAT            	KIDDE       		BOEING	727   	727*        	       	NM  										FIRE BOTTLE	DAMAGED         	B			P94R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					89651EK					RECEIVED APU FIRE EXTINGUISHER FOR OVERHAUL AFTER FIRING.  DURING THE DISASSEMBLY, IT WAS DISCOVERED THAT THE PYROTECHNI	C CARTRIDGE MELTED THE STAINLESS STEEL BOTTLES SEAT RENDERING THE PRESSURE VESSEL SCRAP.  THIS TYPE OF DAMAGE IS CONSIS	TENT WITH PREVIOUSLY REPORTED DAMAGE CAUSED BY THIS MFG CARTRIDGES.  REPAIR STATION IS VERY CONCERNED SINCE AT LEAST (2)	 OTHER UNRELATED REPAIR STATIONS HAVE REPORTED SIMILAR PROBLEMS WITH THE PYROTECHNIC CARTRIDGES FROM THIS MFG. (K)			2	L	7	3 	4F			RT	A3WE    					 
2005061300121	20050613	00121	EU  	2005	6	13	2005FA0000805    	1	20050503	G	2780	1075D1003	CONTROL UNIT    			ISRAEL	1125  	ASTRASPX    	4500205	EU  										ZONE 900	OUT OF TOLERANCE	Z				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			WP	03	B2001		22   			119				THE FSECU HAS A RELIABILITY PROBLEM.  HERE IS THE FAULT HISTORY BELOW; SERVICE TIME ON S/N 131 IS 6.1 HOURS.  SERVICE TI	ME ON S/N 149 IS 0.8 HOURS.  SERVICE TIME ON S/N 140 IS 328.2 HOURS.  SERVICE TIME ON S/N 107 IS 605.4 HOURS.  SERVICE T	IME ON S/N 317 IS 38.9 HOURS.  VERY LOW TIME ON THESE UNITS THAT FAILED.  THE FLIGHT CONTROL SYSTEM IMPROVEMENTS HISTORY	 AS NOTED HEREIN AFTER; CHANGE THE P/N OF SLAT FLEXIBLE SHAFT NR 1 FROM V25W513320-001 OR V25W513330-001 TO V25W513330-2	01.  CHANGE THE P/N OF SLAT PDU FROM V25W513310-001 OR V25W513310-003 TO V25W513310-003 MOD AB.		2	L	7	2 	4F			RT	A16NM   					 
2005061300122	20050613	00122	EU  	2005	6	13	2005FA0000806    	1	20050503	G	2780	1075D1003	CONTROL UNIT    			ISRAEL	1125  	ASTRASPX    	4500205	EU  										ZONE 900	OUT OF TOLERANCE	Z				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	03	B2001		22   			119				THE FSECU HAS A RELIABILITY PROBLEM.  HERE IS THE FAULT HISTORY BELOW; SERVICE TIME ON S/N 131 IS 6.1 HOURS.  SERVICE TI	ME ON S/N 149 IS 0.8 HOURS.  SERVICE TIME ON S/N 140 IS 328.2 HOURS.  SERVICE TIME ON S/N 107 IS 605.4 HOURS.  SERVICE T	IME ON S/N 317 IS 38.9 HOURS.  VERY LOW TIME ON THESE UNITS THAT FAILED.  THE FLIGHT CONTROL SYSTEM IMPROVEMENTS HISTORY	 AS NOTED HEREIN AFTER; CHANGE THE P/N OF SLAT FLEXIBLE SHAFT NR 1 FROM V25W513320-001 OR V25W513330-001 TO V25W513330-2	01.  CHANGE THE P/N OF SLAT PDU FROM V25W513310-001 OR V25W513310-003 TO V25W513310-003 MOD AB.		2	L	7	2 	4F			RT	A16NM   					 
2005061400058	20050614	00058	SO  	2005	6	14	2005FA0000807    	1	20050522	G	2433	WH120	CONVERTER       			GULSTM	G1159 	GIV         	3980115	SO  										LAV TOILET	FAILED          	C				H				DEACTIVATE SYST/CIRCUITS				S	B		AFFECT SYSTEMS            	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			NM	09	941AM	843  				1499				PILOTS DISCOVERED AUX DC CONV CIRCUIT BREAKER POPPED AFTER LAV WOULD NOT FLUSH.  BREAKER WAS RESET, IT IMMEDIATELY POPPE	D AGAIN WITH SMALL AMOUNT OF SMOKE EMANATING FROM CABIN CONVERTER, ID 106A1.  BREAKER SECURED.  FLIGHT COMPLETED SANS FL	USH TOILETS AND CABIN READING LIGHTS.  NEW UNIT INSTALLED.  OPERATIONAL CHECK SATISFACTORY.  NOTE: THE FAILED UNIT SERIA	L NUMBER WAS WELL ABOVE THE RANGE AFFECTED TO UPDATE TO MOD 5 STATUS PER GAC AND KGS.			2	L	7	2 	4F			RT	A12EA   					 
2005062900004	20050629	00004	CE  	2005	6	29	2005FA0000808    	1	20050430	G	2740	04321383	CHAIN           			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470*       	17026	SO  					AFT STABILIZER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	15BF					18052353				CHAIN LINK CRACKS IN AFT STABILIZER CHAIN.  POSSIBLE OVER STRESS OR MFG DEFECT.  (K)						1	H	7	1 	3O	3	O		5A6     	E273				 
2005062900062	20050629	00062	SO  	2005	6	29	2005FA0000810    	1	20050118	G	3230	402427	DRAG LINK       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					LT MLG	BROKEN          	B			ML2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	63764					277754097				AC WAS ON ROLL OUT AFTER LANDING, WHEN LT MAIN LANDING GEAR DRAG LINK ASSY SEPARATED BETWEEN UPPER LINK ASSY AND LOWER L	INK ASSY.  THIS ALLOWED LT MLG STRUT ASSY TO FOLD AFT ALLOWING AC TO COLLAPSE ON RUNWAY.  WHEN AC WAS RECOVERED, THE LT 	MLG CENTER DRAG LINK ATTACH BOLT WAS FOUND SHEARED IN CENTER OF BOLT SHANK.  BOTH HALVES OF BOLT WERE STILL IN THE LT LO	WER DRAG LEG AND WERE ABLE TO BE REMOVED FOR INSP.  VISUAL INSP OF BOLT FRACTURE INDICATED AN EXITING CRACK ACROSS APPRO	X .7500 PERCENT OF THE BOLT SHANK WITH A NEW CRACK THROUGH REMAINING .2500 PERCENT OF BOLT SHANK.  A REPLACEMENT BOLT WA	S INSTALLED TO FACILITATE RECOVERY OF AC AND AC WAS TURNED OVER TO OWNER FOR REPAIRS TO BE COMPLETED.  (K)	1	L	7	2 	3O	3	O		1A10    	E14EA				 
2005062900023	20050629	00023	SO  	2005	6	29	2005FA0000811    	1	20050509	G	5797		WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  										RT WING	SHORTED         	B			OF1R	C				ABORTED TAKEOFF         				A			FLAME/FIRE                			TO	TAKEOFF        	1			EA	17	151LL					317852025				RT WING EXPLODED ON TAKEOFF ROLL DUE TO IGNITED FUEL VAPORS TRAPPED IN EMPTY WING CAVITY OR OF FUEL CELLS.  INSP REVEALE	D; RT MAIN FUEL CELL VENT NIPPLE WAS BROKEN OFF, VERY BRITTLE AND DETERIORATED, ALLOWING FUEL VAPORS TO ACCUMULATE IN TH	IS CAVITY.  PREVIOUSLY INSTALLED COLEMILL WINGTIP AND LANDING LIGHT MODIFICATION WAS PERFORMED, ROUTING ITS 28 VOLT POWE	R WIRE FROM ROOT TIP FOLLOWING AFT STRINGER, PASSING THRU RIBS VIA STRINGER CUTOUTS WITH NO PROTECTION.  THIS WIRE WAS F	OUND TO BE SHORTED AND BURNED OFF WITH EVIDENCE OF EXCESS ARCHING AT WING STA 148, BREAKER WAS POPPED CAUSING IGNITION O	F ABOVE FUEL VAPORS.  INCIDENT COULD HAVE BEEN AVOIDED, PROPER FUEL CELL INSP AND ROUTING WIRES PROPERLY IAW ADV CIR.	1	L	7	2 	3O				A20SO   					 
2005062100001	20050621	00001	GL  	2005	6	21	2005FA0000812    	1	20050607	G	3220		LANDING GEAR    			AMTR  	LANCAR	LANCAIRES   	       	GL  	CONT  	O360  	TSIO360CB   	17025	SO  					NOSE	VIBRATES        	G				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			WP	19	1169G					ES063FB				SEVERE NOSE GEAR SHIMMY DURING LANDING.  NOSE GEAR STRUT SERVICED WITH MIL-H-5606, REQUIRED 30-WT FORK OIL.  NEXT FLT A 	SEVERE SHIMMY AGAIN.  INSP REVEALED ENG MOUNT BROKEN 6 PLACES AS A RESULT.  ENG MOUNT & NOSE GEAR STRUT REPLACED, ON NEX	T FLT, A SEVERE NOSE GEAR SHIMMY ENCOUNTERED.  INSP DISCLOSED NOSE GEAR STRUT HOT TO TOUCH & COLOR OF OIL CHANGED.  COWL	ING BURNED NEAR TURBO CHARGER.  STANDARD LANCAIR ES COWLING WAS NOT DESIGNED FOR A TURBOCHARGED ENG INSTALLATION.  HEAT 	WITHIN COWL TRANSFERS INTO NOSE GEAR STRUT & HEATS STRUT & OIL TO A TEMP THAT RENDERS INTERNAL SHIMMY DAMPENING SYS INEF	FECTIVE & DAMAGES OLEO STRUT.  TELEDYNE TSIO-360 SERIES ENGINE IS NOT AN ENGINE INSTALLATION RECOMMENDED BY LANCAIR. 	1	L	7	1 	  	3	O		EXPA1L71	E9CE				 
2005062900007	20050629	00007	SO  	2005	6	29	2005FA0000813    	2	20050127	G	8520	653547	MAIN BEARING    			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C402   	GL  	NR 2	DISINTEGRATED   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	756XE					U20604432	28484012	980169		METAL WAS FOUND IN OIL FILTER.  CLEANED WENT FOR TEST FLIGHT, LOST OIL PRESSURE.  ENGINE REMOVED, WITNESSED TEARDOWN.  F	OUND NR 2 MAIN BEARING SPUN AND DISINTEGRATED.  CRANKSHAFT CHECKED OUT OK.  ENGINE CASE WAS BADLY DAMAGED AT THE NR 2 BE	ARING BOSS ENGINE HAD 790 HOURS SFRM.  ENGINE OPERATIONS WAS MOSTLY ON A FLOATPLANE.  (K)				1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P47GL	 
2005062900054	20050629	00054	SO  	2005	6	29	2005FA0000814    	2	20050502	G	8520	A73851	PISTON          			CESSNA	185   	A185F       	2072821	CE  	CONT  	O200  	O200*       	17020	SO  					ENGINE	CRACKED         	D			YEBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	26DL					18502287	L859615			REMOVED CYLINDERS ON A FRESHLY OVERHAULED ENGINE PRIOR TO RUNNING AND FOUND A 3 INCH CRACK AROUND THE OIL RING LANDING. 	 (K)					1	H	7	1 	3O	3	O		3A24    	E252				 
2005062100159	20050621	00159	EU  	2005	6	21	2005FA0000815    	1	20050609	G	7910	029907004	PROBE           			AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					OIL TANK	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	166FB					18	P112161			DISCOVERED OIL LEVEL PROBE IN ENGINE OIL TANK TO HAVE ONE RIVET MISSING FROM THE DATA TAG AND THE PLASTIC END CAP CRACKE	D AT ONE RIVET HOLE.  THE DATA TAG WAS VERY LOOSE BUT STILL ATTACHED BY THE ONE REMAINING RIVET.  IF THE DATA TAG OR END	 CAP WERE TO COME LOOSE, THEY COULD RESTRICT OR PLUG THE ENGINE OIL SUPPLY STANDPIPE.  THE DEFECT WAS FOUND DURING AN EN	GINE INSTALLATION.  THIS IS AN AIRFRAME SYSTEM COMPONENT.			2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2005061600216	20050616	00216	NM  	2005	6	16	2005FA0000816    	1	20050608	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	127  	127  		0099990080	90000085				DURING ACCOMPLISHMENT OF AD 2002-10-05- MAIN ROTOR UPPER HUB INSP FOUND (2) BOLT HOLES CRACKED AS DEPICTED IN MD HELICOP	TERS SERVICE BULLETIN 900-072.  CRACKS WERE FOUND USING MAGNIFIED VISUAL METHOD.  HUB WAS SUBSEQUENTLY INSPECTED BY EDDY	 CURRENT METHOD TO VERIFY CRACKS.  EDDY CURRENT INSPECTION USING A BOLT HOLE SCAN FOUND A THIRD HOLE CRACKED.  THIS CRAC	K WAS NOT VISIBLE AT THE FLANGE SURFACE USING THE MAGNIFIED VISUAL METHOD.  TO DATE HUB IS ON ORDER PENDING REPLACEMENT.			1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2005062100109	20050621	00109	NE  	2005	6	21	2005FA0000817    	1	20050214	G	6320		THRUST WASHER   			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					M/R GEARBOX	WORN            	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	173AC	926  				64015				MAIN GEAR BOX, SN A6051 REMOVED FOR BRASS CONTAMINATION.  UPON DISASSEMBLY DISCOVERED BRASS MATERIAL WAS FROM SECOND STA	GE PLANETARY THRUST WASHERS. 34 OUT OF 36 THRUST WASHERS WORN ON ID BEYOND MAX SERVICEABLE LIMITS.  18 EA BEARINGS HAD S	HARP EDGES INNER RACE EDGES.  CURRENTLY BE EVALUATED BY BEARING SUPPLIER.  NEED TO BREAK SHARP EDGES.  (K)				2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005062100111	20050621	00111	NE  	2005	6	21	2005FA0000818    	2	20050302	G	7250		DUCT            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					TURBINE SECTION	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	189AC					641001				NR 1 ENGINE REMOVED FROM ACFT,  DUE TO 5 INCH AXIAL BULGE AT OUTER TURBINE CASE,  2-3 OCLOCK POSITION WITH APPROX  .5625	 INCH HORIZONTAL CRACK RUNNING THROUGH CENTER MOST PORTION OF THE BULGED AREA.  UPON REMOVAL OF ENGINE HOT SECTION, TURB	INE OUTLET DUCT FOUND TO HAVE APPROX A 8.5 INCH SECTION OF MATERIAL BROKEN OFF AND PEELED BACK FROM OUTER DUCT AREA AT N	R 2 AND NR 3 COMBUSTION CAN POSITIONS.  THE P AND D VALVE AND FUEL MANIFOLD ASSEMBLIES WERE INSP AND FOUND TO HAVE NO EV	IDENCE OF FAILURE.  PROBABLE CAUSE IS UNKNOWN AND NO RECOMMENDATIONS TO PREVENT RECURRENCE AT THIS TIME. (K)		2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005062100110	20050621	00110	NE  	2005	6	21	2005FA0000819    	1	20050414	G	6520	6435664071	GEAR            			SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					T/R GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC		284  			64084				TGB AND SERVO ASSY REMOVED FROM ACRFT FOR MAKING METAL.  GEARBOX DISASSEMBLED AND DURING VISUAL INSP OF OUTPUT GEAR, ONE	 TOOTH FOUND CRACKED.  FRIVE SIDE OF TOOTH SHOWS THE MAJORITY OF CRACKING, STARTING FROM IB TO ALMOST MIDWAY ON TOOTH EX	TENDING ACROSS TIP LAND TO OPPOSITE SIDE, THEN OB.  APPEARS TO BE 3 CRACKS EXTENDING THE LENGTH OF GEAR TOOTH AND ENDING	 UP AT APPROX .2500 INCH AND .3750 INCH FROM THE ROOT. MPI INSP CONFIRMED TOOTH WAS CRACKED. NO OTHER CRACKS FOUND.  (K)			2	G	7	2 	4U	4	U		H6EA    	E15EA				 
2005062300074	20050623	00074	NE  	2005	6	23	2005FA0000820    	2	20050413	G	7250	597602	TURBINE BLADES  			SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					ENGINE	BROKEN          	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	159AC					64084				COMPRESSOR ASSY WAS REMOVED FROM AC FOR FAILING VIBRATION ANALYSIS.  DURING THE PRELIMINARY INSPECTION IT WAS NOTED THAT	 A PIECE OF 2ND STAGE TURBINE BLADE OUTER SHROUD KNIFE EDGE WAS MISSING.  THE MISSING PIECE WAS APPROXIMATELY .500 INCH 	LONG AND FROM THE AFT KNIFE EDGE.  FURTHER INSPECTION REVEALED NO OTHER DAMAGE.  THE BLADE WAS IN OVERHAULED CONDITION W	HEN INSTALLED.  (K)			2	G	7	2 	4U	4	U		H6EA    	E15EA				 
2005061600270	20050616	00270	GL  	2005	6	16	2005FA0000821    	1	20050531	G	3240	MS24775222	O-RING          			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O470  	TSIO470*    	17026	SO  					BRAKE ASSY	FLAT            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	8156E					0726				AC LANDED AND DISCOVERED THEY HAD NO RT BRAKE.  AC LOST DIRECTIONAL CONTROL AND IMPACTED A PARKED AIRCRAFT CAUSING SUBST	ANTIAL DAMAGE TO THE PARKED AIRCRAFT.  INVESTIGATION REVEALED THE RT BRAKE O-RING WAS FLAT AND THE HOUSING AND DATA PLAT	E SHOWED EXTREME HEAT.  REVIEW OF THIS SITUATION FOUND THAT THERE HAVE BEEN MANY OWNER REPORTS IN THE OWNERS NEWSLETTER 	OF RT BRAKE FAILURES DUE TO THE NEED TO STEER THE AC WHICH HAS A CASTERING NOSE WHEEL.			1	L	7	1 	3O	3	O	NT	A00009CH	3E3				 
2005061600275	20050616	00275	CE  	2005	6	16	2005FA0000822    	1	20050605	G	2910	S217840150A	HOSE            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					HYD SYSTEM	LEAKING         	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	23	7972V					177RG0915				PILOT SELECTED GEAR DOWN ON FINAL APPROACH AND THE GEAR FAILED TO EXTEND.  THE INVESTIGATION FOUND THAT THE NOSE GEAR DO	WN LINE WAS LEAKING AT THE BULKHEAD END CAUSING TOTAL LOSS OF HYDRAULIC FLUID.  THE AIRCRAFT LANDED GEAR UP WITH NO INJU	RIES AND MINOR DAMAGE TO THE EXTERIOR OF THE AIRCRAFT.  (WP23200509350) (K)				1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005061600235	20050616	00235	CE  	2005	6	16	2005FA0000823    	1	20050526	G	2435	03600918	BEARING         			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					STARTER GEN	SEIZED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	350TT	301  			P1047	FL413				PILOT REPORTED RT ENGINE SURGING, SMOKE FROM EXHAUST SIMULTANEOUSLY WITH  RT GENERATOR GOING OFF LINE IN CRUISE FLIGHT. 	 FOUND RT STARTER/ GENERATOR ANTI-DRIVE (BRUSH END) BEARING SEIZED, INPUT SHAFT INTACT.  REPLACED STARTER/GENERATOR AND 	EXAMINED OIL FILTER IAW MM FAILED GENERATOR SPECIAL INSPECTION PROCEDURES.  NO APPRECIABLE METALLIC PARTICLES NOTED IN O	IL FILTER SENT IN FOR ANALYSIS.  GENERATOR OPERATINS NORMAL AND ENGINE PERFORMANCE WITHIN MM, SERVICE LIMITS AFTER START	ER/GENERATOR REPLACEMENT.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005062700103	20050627	00103	WP  	2005	6	27	2005FA0000824    	1	20050606	G	6230	23600	MAST            			HILLER	UH12  	UH12E       	4360122	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	D			JYBG	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			NM	09	76431		229  			992				HELICOPTER EXPERIENCED A PROGRESSIVE LATRIAL VIBRATION.  SUBSEQUENT INSPECTION FOUND 2 CRACKS FROM THE PITCH PIN SLOT AR	EA OF THE MAST.  ONE CRACK FROM THE TOP OF ONE SLOT AND ANOTHER CRACK FROM THE BOTTOM OF THE SAME SLOT PROGRESSING THE O	PPOSITE DIRECTION.  THE TOP CRACK IS APPROX 1.6 INCHES AROUND THE DIAMETER OF THE MAST AND THE BOTTOM CRACK IS APPROX 1.	3 INCHES.			1	G	7	1 	3O	3	U		4H11    	E4CE				 
2005062700104	20050627	00104	SO  	2005	6	27	2005FA0000825    	1	20050603	G	2421	4111810R	ALTERNATOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FROZEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	36116		214  			287816614				ALTERNATOR FROZE UP UPON ENGINE SHUTDOWN.  OVERHAULED.						1	L	7	1 	3O	3	O		2A13    	E274				 
2005062700105	20050627	00105	SO  	2005	6	27	2005FA0000826    	1	20050603	G	2421	4111810R	ALTERNATOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	9284A		342  			288616041				ALTERNATOR CREATES WHINE OVER RADIOS AND HAS NO OUTPUT AT IDLE RPM, (VOLTAGE IS BATTERY VOLTAGE) OVERHAULED.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2005062700106	20050627	00106	NE  	2005	6	27	2005FA0000827    	1	20050601	G	6420	SB25011	BEARING         			SKRSKY	S61   	S61A        	814210C	NE  	GE    	CT58  	CT581401    	30011	NE  					TAIL ROTOR	BRINELLED       	D			JYER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	1043T	1743 				61083				AT OVERHAUL, REMOVED HUB BEARING INNER RACES AND FOUND (1 EACH) CRACKED ABOUT 1.5 INCHES DUE TO SEVERE BRINNELING.  PROB	ABLE CAUSE COULD BE DUE TO GREASE (MINIMAL AMOUTS).  RECOMMEND DAILY PURGING OF HUB BEARING TO PREVENT ANOTHER OCCURENCE	.   (K)				2	G	7	2 	4U	4	U		H2EA    	1E3				 
2005062700107	20050627	00107	CE  	2005	6	27	2005FA0000828    	1	20050623	G	3710	B906	HOSE            			CESSNA	172   	172P        	2072436	CE  										VACUUM SYS	CRACKED         	B			DINR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	13	51178	5000 				17274274				VACUUM SYSTEM HOSES (ORIGINAL EQUIPMENT), RED PLASTIC INNER LINER CRACKING WITH PIECES AND FLAKES BREAKING OFF.  COULD C	AUSE GYRO OR VACUUM PUMP FAILURE.  (K)					1	H	7	1 	3O			NT	3A12    					 
2005062700109	20050627	00109	EU  	2005	6	27	2005FA0000829    	1	20050422	G	1100		PLACARD         	AIRBUS      		AIRBUS	A319  	A319112     	3930323	EU  	GE    	CFM56 	CFM56*      	13802	NE  					WING FUEL TANK	SEPARATED       	D				O				OTHER                   				D	C		INFLIGHT SEPARATION       	F.O.D.                    		NR	NOT REPORTED   	1			NE	03	727UW				1147	1147				DEBRIS (PLASTIC IDENTIFICATION DECALS) FOUND IN LT AND RT FUEL TANK WING ROOT AREAS DURING C-CHECK.  QIT ISSUED BY MFG A	ND IS APPLICABLE TO MSN1147.  (K)					2	L	7	2 	4F	4	F	RT	A28NM   	E2GL				 
2005062700110	20050627	00110		2005	6	27	2005FA0000830    	4	20050525	G	3417	702490030303	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					E/E BAY	DEFECTIVE       	B			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	27BL					163				THE PILOTS ALTIMETER AND ALTITUDE ALERTER WERE FLAGGED.  THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS	 TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91.411 PART 43 AND TO REMAIN RVSM COMPLIANT.  THERE HAVE BEEN NO PRIO	R REPORTS OF PROBLEMS WITH THIS SYSTEM.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005062700111	20050627	00111		2005	6	27	2005FA0000831    	4	20050427	G	3417	702490030303	ADC             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					E/E BAY	INOPERATIVE     	B			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	4358N					35065				CAPTAIN (LT SIDE) ALTIMETER, VERTICAL SPEED AND ALTITUDE ALERTER INOPERATIVE.  FOUND THE PRIMARY ADC INOPERATIVE.  REPLA	CED THE ADC, TESTED THE PRIMARY ALTIMETERY SYSTEMS, FOUND TO COMPLY WITH FAR AND TOBE RVSM COMPLIANT.  THERE HAVE BEEN N	O PREVIOUS PROBLEMS WITH THIS SYSTEM.  (GL07200508784)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005062700112	20050627	00112		2005	6	27	2005FA0000832    	4	20050527	G	3417	702490030303	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT E/E BAY	DEFECTIVE       	B			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	56EM					144				PILOTS ALTIMETER AND ALTITUDE ALERTER WERE FLAGGED.  THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS TES	TED AND INSPECTED AND FOUND TO COMPLY AND TO REMAIN RVSM COMPLIANT.  THERE HAVE BEEN NO PRIOR REPORTS OF PROBLEMS WITH T	HIS SYSTEM.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005062700113	20050627	00113		2005	6	27	2005FA0000833    	4	20050506	G	3417	702490030303	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT E/E BAY	DEFECTIVE       	B			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	813AS					167				ON TAKEOFF ROLL OUT, THE PILOTS ALTIMETER, IVSI AND ALTITUDE ALERTER FLAGGED.  THE TAKEOFF WAS ABORTED.  THE ADC WAS FOU	ND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR AND REMAIN RVSM COMPL	IANT.  THERE HAVE BEEN NO PRIOR REPORTS OF PROBLEMS WITH THIS SYSTEM.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005062700114	20050627	00114	SO  	2005	6	27	2005FA0000834    	2	20050430	G	7322	30804	FLOAT           	PRECISION   		TCRAFT	F19   	F19         	9302703	EA  	CONT  	O200  	O200*       	17020	SO  					CARBURETOR	BENT            	G				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AL	01	3691T	70   				F098				ENG QUIT DURING TAKEOFF AT APPROX 300-500 AGL.  DURING EXAM OF ENG COMPONENTS, IT WAS NOTED ADVANCE POLYMAR FLOAT WAS BE	NT AWAY FROM THE FLOAT AT APPROX 45 DEGREE ANGLE.  THIS CONDITION WOULD LEAD TO THE FLOW INTO THE CARBURETOR.  PRECISION	 SIL MS-4 REV 1 ADDRESSES NEW ADVANCED POLYMER FLOATS.  REF INSTALLATION INSTRUCT E-955.  THERE IS NO WARNING OR CAUTION	 TO ALERT OVERHAULERS TO BE AWARE OF BENT FORK CONDITION IN EITHER OF THESE DOCUMENTS.  SPECIFIC CLEAR BETWN FORKED RETR	ACTOR AND FLOATBODY.  SPECIFIC FLOAT DROP REQUIRED TO ALLOW FUEL TO INFLOW TO CARB BOWL.  ILLUSTRATIONS CORRECT RETRACTO	R FORK/CLIP POSITIONS.  REINSTATE SPRING CLIP ON FLOAT VALVE TO ENSURE POSITIVE PULL ON FLOAT VALVE.	1	H	7	1 	3O	3	O	NC	1A9     	E252				 
2005062700116	20050627	00116	CE  	2005	6	27	2005FA0000835    	1	20050602	G	1430	NAS620518D	BOLT            			RAYTHN	390   	390         	7150030	CE  										NR 3 FLAP ROLLER	CHAFED          	B			YK1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	128JL	385  				RB28				UPON REMOVAL OF FLAP ACTUTORS FOUND NR 3 LT AND RT FLAP ACTUATORS WERE DEEPLY GOUGED, DUE TO FLAP TRACK BOLTS INSTALLED 	BACKWARDS.  PN OF BOLT NAS6205-18D.  REMOVED BOLT AND INSPECTED AND REINSTALLED IN THE CORRECT DIRECTION.  (K)					1	7		2 	3F			RT	A00010WI					 
2005062800139	20050628	00139	CE  	2005	6	28	2005FA0000836    	1	20050601	G	2797		CIRCUIT BOARD   			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					PITCH TRIM	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	6033N					21062901				ELECTRIC PITCH TRIM SYSTEM RAN AWAY ON APPROACH.  AUTOPILOT/ TRIM DISCONNECT HAD NO EFFECT.  PILOT DISENGAGED PITCH TRIM	 CIRCUIT BREAKER TO STOP THE RUNAWAY.  AFTER THE CIRCUIT BREAKER WAS DISENGAGED, THE CONTROL WHEEL VIBRATED ON THE APPRO	ACH AT APPROXIMATELY 120 TO 130 KNOTS.  FOUND CONTROL WHEEL ELECTRICAL RIBBON CIRCUIT BOARD LOOSE BEHIND INSTRUMENT PANE	L CAUSING GROUND.  REATTACHED BOARD WITH NEW SCREWS AND SPACERS.  OPS CHECK OK.  INSPECTED STABILIZERS, RUDDER, ELEVATOR	S AND TAB.  NO DEFECTS FOUND AT THIS TIME.  (K)		1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005062800137	20050628	00137	EA  	2005	6	28	2005FA0000837    	1	20050601	G	5500	C3FS465502	PLATE           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6*        	52043	EA  					TAIL SECTION	CRACKED         	B			GJRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	606KA	9702 				37				PART FOUND TO BE CRACKED FROM BOTH REAR CORNER EXTENDING 2 INCHES IN LENGTH.  PART HAS 9702 HOURS.  STA 398-414.  (K)						1	H	7	1 	3R	3	T		A815    	E2NE				 
2005062800001	20050628	00001	SO  	2005	6	28	2005FA0000838    	1	20050603	G	2433	LS0305002	CONVERTER       			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					DC SYSTEM	FAILED          	D			YJ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	4990P	1    				188564				CONVERTER WAS INSTALLED IAW MFG INSTRUCTIONS, DIAGRAMS AND INSTALLATION WAS APPROVED WITH A 337.  CONVERTER FAILED IN LE	SS THAN 10 SECONDS.  OUT OF FIVE CONVERTERS, FOUR IN AC AND ONE ON THE TEST BENCH, ALL HAVE FAILED.  (K)					1	H	7	1 	3O	3	O		1A2     	E274				 
2005062800003	20050628	00003	CE  	2005	6	28	2005FA0000839    	1	20050517	G	5311	00244002465	FRAME           			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	TSIO550A    	41516	SO  					BULKHEAD	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	8131H					E2755				BULKHEAD FRAME ASSY AT STA 272.  CRACKED AT TOP PORTION LT AND RT IN BEND RADIUS, APPROX CRACK TO BE ABOUT .5 INCH ON LT	 AND 1 INCH ON RT.  (K)					1	L	7	1 	3O	3	O		3A15    	E5SO				 
2005062800004	20050628	00004	CE  	2005	6	28	2005FA0000840    	1	20050510	G	5312	00244002465	BULKHEAD        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	8183E					E2612				BULKHEAD AT STA 272, REAR AFT FUSELAGE FOUND CRACKS AT TOP PORTION OF BULKHEAD AT RADIUS OVER CRACK APPROX .5 ON LT AND 	ABOUT 1.5 ON RT ALSO CAUSING DOUBLER TO CRACK OUT THAT HOLDS THE 2 SKINS TOGETHER.  (K)					1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005062800138	20050628	00138	CE  	2005	6	28	2005FA0000841    	1	20050510	G	5312	00244002465	BULKHEAD        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					FUSLEAGE	CRACKED         	D			MASS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	8026T					E2701				WEB BULKHEAD AT STA 272 REAR AFT FUSELAGE, FOUND CRACKS AT TOP PORTION ON RADIUS OF POST.  CRACK TO BE APPROX 1 INCH ON 	LT AND ABOUT .2400 INCH ON RT, ALSO CAUSING DOUBLER TO CRACK OUT THAT HOLDS THE 2 SKINS TOGETHER.  PROBABLE CAUSE, JUST 	HIGH TIME IN AIRFRAME, ALSO MFG TO MAKE A MODIFICATION, SUCH AS A BIGGER DOUBLER TO PREVENT FUTURE CRACKS.  (K)				1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005062800005	20050628	00005	CE  	2005	6	28	2005FA0000842    	1	20050517	G	5312	00244002465	BULKHEAD        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	1830V					E3087				TAIL BULKHEAD AT STA 272.0, FOUND CRACKS ON TOP PORTION IN BEND RADIUS AREA, APPROX .5 INCH TO .2500 INCH LONG ON TOP, L	T AND RT AREA.  PROBABLE CAUSE SEEMS TO BE FATIGUE DUE TO HIGH TOTAL TIME ON AIRFRAME.  (K)					1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005062800127	20050628	00127		2005	6	28	2005FA0000843    	4	20050504	G	2562	MN1300	BATTERY         	ACK         		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					ELT	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	19866				037866	17260817				DURING ANNUAL INSPECTION THE ELT WAS INSPECTED IAW FAR.  THE 24 MONTH OLD MN 1300 BATTERIES WERE FOUND LEAKING WITH FLUI	D VIVIBLE IN THE BOTTOM OF THE UNITS EACH 12 MONTHS OR REQUIRING A SEALED BATTERY INSTALLATION.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005062800135	20050628	00135	CE  	2005	6	28	2005FA0000844    	1	20050517	G	5312	00244002457	BULKHEAD        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					FUSELAGE	CRACKED         	D			MASS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	8245H					TH1635				BULKHEAD CRACKED AT TOP PORTION AT JOGGLED AREA BELOW AFT HORIZONTAL ATTACH BRACKET/SPAR CRACK TO BE ABOUT .2500 INCH ON	 RT, ABOUT 1 INCH ON LT, CAUSE PROBABLY DUE TO HIGH AIRFRAME TT AND FATIGUE.  (SW01200504562) (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005062900027	20050629	00027	EA  	2005	6	29	2005FA0000845    	1	20050524	G	5320	600310687	FLOOR SUPPORT   			CNDAIR	CL600 	CL6001A11   	1900302	EA  	LYC   	ALF502	ALF502L2C   	 	NE  					FUSELAGE	CRACKED         	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	40HJ	15110				1058				FLOOR SUPPORT LOCATED AT RBL 9.0 FS 460 CRACKED AT FLANGE.  DURING FLOORBEAM REPLACEMENT A VISUAL INSPECTION REVEALED CR	ACK AT FLANGE.  INSPECTED 3 OTHER FLOOR SUPPORTS IN AIRCRAFT, NO OTHER CRACKS FOUND.  THE FLOOR SUPPORT IS CURRENTLY INC	LUDED IN THE 60 MONTH BELOW FLOOR INSPECTION TASK.  (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2005062200200	20050622	00200	CE  	2005	6	22	2005FA0000846    	1	20050614	G	2622	99103494	FIRE BOTTLE     			CESSNA	441   	441         	2076020	CE  										CABIN	DISCHARGED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	441CT		490  			4410048				THIS FIRE BOTTLE HAS 1 YEAR ON IT AND THE PRESSURE HAS DROPED TO 20 PSI.  THIS IS THE SECOND FIRE BOTTLE THAT DID NOT MA	KE IT TO 5 YEARS.  OVERHAULED BY KELLY AEROSPACE.  (QUALITY OF WORKMANSHIP AND OR PARTS)?  THIS NEVER HAS BEEN A PROBLEM	.				1	L	7	2 	3T			RT	A28CE   					 
2005062200219	20050622	00219	SO  	2005	6	22	2005FA0000847    	2	20050614	G	7421	RHB32S	SPARK PLUG      			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	2664M	106  	28   			E2317	675239			SPARK PLUG MAIN INSULATOR BROKE-OFF INTO ENGINE DURING OPERATIONS BETWEEN 88 AND 106 HOURS OF USE.  A MAJOR PIECE OF CER	AMIC MATERIAL WAS INJESTED INTO THE ENGINE.					1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005062300132	20050623	00132	CE  	2005	6	23	2005FA0000848    	1	20050607	G	3520	10142187	CONTROL CABLE   			BEECH 	B300  	B300        	1159232	CE  										PAX OXYGEN SYS	BROKEN          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	21	6117C	199  				FL417				PERFORMING A PHASE 1 INSPECTION, IT IS REQUIRED TO PERFORM A FUNCTIONAL CHECK OF THE PASSENGER OXYGEN SYSTEM.  THE TEE H	ANDLE CONTROL WAS PULLED TO MANUALLY DEPLOY AND FLOW THE PASSENGER OXYGEN MASKS.  THE MASKS DID NOT DEPLOY AND THERE WAS	 NO OXYGEN FLOW.  FURTHER INVESTIGATION REVEALED THAT THE CONTROL CABLE WAS CONNECTED TO THE PASSENGER OXYGEN SHUT OFF V	ALVE AND THE CONTROL CABLE WAS BROKEN SOMEWHERE IN THE MIDDLE.  THE CONTROL CABLE WAS REPLACED WITH NEW AND PASSEGER OXY	GEN SYSTEM OPERATIONAL CHECKED NORMAL.		2	L	7	2 	4T			RT	A24CE   					 
2005062300047	20050623	00047	CE  	2005	6	23	2005FA0000849    	1	20050606	G	5711	082260041	SPAR CAP        			CESSNA	310   	310D        	2074212	CE  										LT WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	3031R	5772 				39115				LT WING REAR UPPER SPAR CAP IN NACHELL/EXHAUST AREA AND OUTBOARD WS 80.0-100.0 APPROX. 20 INCHES, WAS FOUND DURING VISUA	L INSPECTION, TO HAVE SEVERE EXFOLIATED INTERGRANULAR CORROSION RINDERING THIS SECTION OF SPAR TO BE UNSERVICABLE.  ALSO	 JUST I/B OF BATTERY BOX ON THE FORWARD SPAR IS AN AREA OF HEAVY SURFACE CORROSION CAUSED BY BATTERY ACID/FUMES ON THE L	OWER CAP AND WEB.  WS 85.0-89.5			1	L	7	2 	3O				3A10    					 
2005062400073	20050624	00073	CE  	2005	6	24	2005FA0000850    	1	20050621	G	2720	A402092N	CONTROL CABLE   			BEECH 	35    	35BEECH     	1151502	CE  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	421B	434  				D1428				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLEY POSITIONS.						1	L	7	1 	3O				A777    					 
2005062400074	20050624	00074	EU  	2005	6	24	2005FA0000851    	1	20050621	G	2720	A402092N	CONTROL CABLE   			LET   	L13   	L13ACBLANIK 	1360312	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	421BA	434  				028902				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLLEY POSITIONS.						1	K	0	0 	  				G24EU   					 
2005062300053	20050623	00053	SO  	2005	6	23	2005FA0000852    	1	20050606	G	3250		CLAMP           			PIPER 	PA46  	PA46350P    	7104602	SO  										NLG	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	364ST					4636364				DURING A 100 HOUR INSPECTION IT WAS NOTICED THAT THE CLAMPS THAT SECURE THE PRESSURIZATION BELLOWS TO THE NOSE GEAR STEE	RING TUBES WERE NOT INSTALLED.					1	L	7	1 	3O			RT	A25SO   					 
2005062300064	20050623	00064	EA  	2005	6	23	2005FA0000853    	2	20050610	G	7414	K3822	DISTRIBUTOR BLK 	SLICK       		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT MAGNETO	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	442ES	2052 			97021204	17280350	L2740351A			DURING PRELIMINARY RUNUP AT ANNUAL INSP, TECH NOTED ENGINE DIFFICULT TO START, & ROUGH ON LT MAG WHEN COLD. ATTEMPTS TO 	CHECK TIMING ON LT MAG WITH A MAG SYNCHRONIZER UNSUCCESSFUL. POINTS WERE ERRATIC DURING CLOSING & OPENING. REMOVAL OF CA	P DISCLOSED SIGNIFICANT DEBRIS. DISASSEMBLY OF MAG DISCLOSED ROTOR GEAR HAD CONTACTED THE DISTRIBUTOR BLOCK, GRINDING RO	TOR GEAR & DISTRIBUTOR GEAR / BLOCK. ROTOR GEAR HAD ALSO WORN A .0625 DEEP GROOVE IN THE CONDENSER. IT APPEARED THE CONT	ACT BETWEEN THE ROTOR GEAR & CONDENSER WAS ONLY THING PREVENTING ROTOR GEAR FROM DISENGAGING ROTOR SHAFT, & TOTALLY FAIL	ING MAG. THERE WAS EVIDENCE THE ROTOR GEAR HAD NEVER BEEN FULLY SEATED ON THE ROTOR SHAFT.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005062400078	20050624	00078	EU  	2005	6	24	2005FA0000854    	1	20050621	G	2720	A402092AN	CONTROL CABLE   			LET   	L13   	L13ACBLANIK 	1360312	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	422BA	442  				028903				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLEY POSITIONS.						1	K	0	0 	  				G24EU   					 
2005062400079	20050624	00079	EU  	2005	6	24	2005FA0000855    	1	20050621	G	2720	A402092AN	CONTROL CABLE   			LET   	L13   	L13ACBLANIK 	1360312	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	435BA	156  				029101				LEFT AND RIGHT RUDDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLEYS.						1	K	0	0 	  				G24EU   					 
2005062900036	20050629	00036	SO  	2005	6	29	2005FA0000856    	1	20050607	G	3246	16147	WHEEL           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	68SD					327940126				AIRCRAFT LANDING SAFELY, WHILE TAXIING, LT TIRE WENT FLAT.  ONCE WHEEL FAIRING REMOVED, NOTED IB WHEEL HALF WAS RUBBING 	BRAKES.  PILOT THEN SAID BEEN SMELLING RUBBER AFTER LANDING BRIEFLY.  ONCE DISASSEMBLED, WITH BRAKE DISC REMOVED, IB WHE	EL HALF CRACKED ALONG BEAD AREA, 3 INCHES AND RIM BOWED OUT.  PILOT REPORTED TIRE REPLACED 6 MONTHS EARLIER.  BETTER INS	PECTION OF WHEELS AT TIME OF TIRE CHANGE COULD HAVE PREVENTED THIS SITUATION.  (K)			1	L	7	1 	3O	3	O		A3SO    	1E4				 
2005062400083	20050624	00083	EU  	2005	6	24	2005FA0000857    	1	20050621	G	2720	A740255N	CONTROL CABLE   			LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	427BA	579  				029009				RIGHT RUDDER CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062400085	20050624	00085	EU  	2005	6	24	2005FA0000858    	1	20050621	G	2720	A740255N	CONTROL CABLE   			LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	434BA	1137 				029011				RIGHT RUDDER CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062800146	20050628	00146		2005	6	28	2005FA0000859    	1	20050531	G	8011	MZ2399S	ARMATURE        	ELECTROSYS  																STARTER	BROKEN          	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19		120  			A082960					PILOT REPORTED GRINDING NOISE WHEN STARTER WAS ENGAGED WITH NO MOVEMENT OF PROPELLER.  REMOVED STARTER AND DISASSEMBLED.	  FOUND DRIVE SPLINES ON ARMATURE SHAFT BROKEN OFF.  THIS IS SECOND SUCH DEFECT FOUND IN A MONTH.  NO APPARENT CAUSE WAS	 FOUND.  NO TOLERANCE COULD BE FOUND IN MM FOR SPLINE WEAR.  (K)																	 
2005062800091	20050628	00091	CE  	2005	6	28	2005FA0000860    	1	20050601	G	3240	09102200	CYLINDER        	CLEVELAND   		CESSNA	170   	170B        	2072306	CE  	CONT  	C145  	C145*       	17012	SO  					BRAKE ASSY	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	3167A					25811				STC SA13GL INSTALLATION.  IN BOTH BRAKE ASSEMBLIES, 30-63A, THE 091-02200 CYLINDER ASSEMBLIES WERE FOUND TO BE CRACKED A	CROSS AND PARALLEL TO THE 069-00400 ANCHOR BOLT HOLE.  THIS IS THE SECOND AIRCRAFT, FOUND WITH CRACKS IN THE 091-02200 C	YLINDER ASSEMBLIES.  THIS AREA IS READILY ACCESSIBLE AND SHOULD BE PART OF THE PREFLIGHT INSPECTION.  THE CRACKS ARE EAS	ILY SEEN, WHEN LOOKING FOR THEM.  (K)			1	H	7	1 	3O	3	O		A799    	E253				 
2005062800117	20050628	00117	SO  	2005	6	28	2005FA0000861    	1	20050610	G	8011		DRIVE GEAR      			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	4583T					28R7235099				BENDIX DRIVE GEAR COMES APART DAMAGING RING GEAR SUPPLIER. (NOT MFG)  STATED THIS WAS A COMMON PROBLEM.  SECOND INSTANCE	 FOR THIS AIRCRAFT.  (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
2005062800100	20050628	00100	SO  	2005	6	28	2005FA0000862    	1	20050610	G	8011		DRIVE GEAR      			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					STARTER	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	55003	140  				28R7335166				BENDIX DRIVE GEAR COMES APART DAMAGING RING GEAR SUPPLIER (NOT MFG) STATED THIS WAS A COMMON PROBLEM.  (K)						1	L	7	1 	3O	3	O		2A13    	1E10				 
2005062800116	20050628	00116	CE  	2005	6	28	2005FA0000863    	1	20050527	G	3250	1693800821	BOLT            			BEECH 	23    	B24R        	1151253	CE  	LYC   	O360  	IO360A1A    	41514	EA  					NLG STEERING	SPLIT           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	23PD	9    				MC408				WHEN RETRACTING AND EXTENDING GEAR THE FORWARD EYE BOLT ON THE NOSE GEAR STEERING BARREL (TUBE) STRUCK THE UPPER BOLT HE	AD A NUMBER OF TIMES AND THE HELM BEARING HOUSING SPLIT RENDERING THE NOSE GEAR STEERING INOPERATIVE.  AIRCRAFT LANDED W	ITHOUT INCIDENT.  (SW19200512298) (K)				1	L	7	1 	3O	3	O		A1CE    	1E10				 
2005062900018	20050629	00018	CE  	2005	6	29	2005FA0000864    	1	20050521	G	3600	W901B20CE	CLAMP           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D1      	52060	NE  					BLEED AIR	DEFECTIVE       	D			XEFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	234DK					RK182				DURING FLIGHT, THE CREW HEARD A POP AFTER WING DEICE HAD BEEN TURNED ON.  THEY PERFORMED THE NESSARY PROCEDURES ACCORDIN	G TO THE CHECKLIST.  DETAILED INSPECTION REVEALED THAT THE SUSPECT CLAMP HAD SEPARATED AND CAUSED ENGINE BLEED AIR TO DU	MP INTO THE AFT EQUIPMENT AREA.  (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2005062400084	20050624	00084	EU  	2005	6	24	2005FA0000865    	1	20050621	G	2720	A740254N	CONTROL CABLE   			LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	428BA	837  				029010				LEFT CABLE FOUND FRAYED AT AFT PULLEY.  RIGHT CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900019	20050629	00019	SW  	2005	6	29	2005FA0000866    	1	20050610	G	2510	140215501	SEAT            			MOONEY	M20   	M20J        	5870219	SW  										PILOTS SIDE	CRACKED         	B			FGQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	5262F					241667				OPTIONAL VERTICALLY ADJUSTING PILOTS SEAT MOVED AFT DURING TAKEOFF, FOUND LT REAR BELLCRANK ASSY CRACKED WHICH DISTORTED	 SEAT ALLOWING SEAT PINS NOT TO FULLY ENGAGE SEAT TRACKS.  INSTALLED A NEW BELLCRANK AND TUBE.  NEW BELLCRANK HAD REINFO	RCEMENT STRAPS WELDED AT FAILURE POINT.  SEAT OPERATED NORMALLY AFTER REPLACEMENT.  (K)				1	L	7	1 	3O				2A3     					 
2005062800159	20050628	00159		2005	6	28	2005FA0000867    	1	20050602	G	3244	196K089	TIRE            																	MLG	DAMAGED         	B			AKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05										IT APPEARS THAT THE TIRE WAS DAMAGED IN THE MOLDING PROCESS.  THERE ARE 2 INJURIES IN THE SIDEWALLS OF THE TIRE ALMOST D	IRECTLY ACROSS FROM EACH OTHER.  AIR ESCAPES FROM THE TIRE VERY SLOWLY UNTIL THE WEIGHT OF THE AC IS PLACED ON IT, EVEN 	THEN YOU HAVE TO LISTEN CLOSELY TO HEAR THE AIR ESCAPING.  (K)																	 
2005062900068	20050629	00068	EU  	2005	6	29	2005FA0000868    	1	20050519	G	2701	BE4510057	CONTROL COLUMN  			BEAGLE	121   	B1211       	1120424	EU  	CONT  	O200  	O200A       	17020	SO  					COCKPIT	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	556MA	1505 				013				DURING ANNUAL INSPECTION CRACK WAS OBSERVED ON CONTROL COLUMN 1.0 INCHES LENGTH (49 MM).  CRACK WAS CONFIRMED BY MAGNETI	C PARTICLE INSPECTION.  THE COMPONENT FORMS PART OF THE AC FLIGHT CONTROL SYSTEM AND IS CRITICAL TO FLIGHT.  BOTH THE LT	 AND RT FITTING ARE THE SAME PN.  PROBABLE CAUSE IS STRESS CORROSION CRACKING.  (EA35200501663)				1	L	7	1 	3O	3	O		A22EU   	E252				 
2005062800092	20050628	00092	SO  	2005	6	28	2005FA0000869    	2	20050322	G	7414		IMPULSE COUPLING			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					MAGNETO	LOOSE           	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	815P					TH1949				DURING ANNUAL INSPECTION, COMPLY WITH 500 HR MAGNETO INTERNAL INSPECTION, WHICH INCLUDES THE IMPULSE COUPLING IAW MFG SB	.  ONE IMPULSE COUPLING WAS FOUND TO BE VERY LOOSE, DUE TO LOOSE RIVETS, WOULD HAVE FAILED SOON.  FAILURE OF THIS TYPE C	AN CAUSE EXTENSIVE DAMAGE TO MAGNETO AND ENGINE.  MFG INSPECTION CHECKLIST DOES NOT CALL FOR DETAILED INSPECTION OF MAGN	ETO IMPULSE COUPLING OR OTHER MAGNETO INTERNAL PARTS OTHER THAN POINTS.  REPLACED COUPLING WITH NEW PART.  OLD PART ONLY	 HAD 529 HRS.  LOOSE RIVETS AND WORN PAWLS.  (K)		1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005062800118	20050628	00118	CE  	2005	6	28	2005FA0000870    	1	20050602	G	2510	551900921	ATTACH BRACKET  	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT SEAT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	157DW					5500253				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  ALSO, PREVIOUS INAPPROPRIATE REPAIR.  CHAIR WAS REPAIRED	 IAW STC ST01042WI STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005062900024	20050629	00024	NE  	2005	6	29	2005FA0000871    	2	20050608	G	7200	414D32101	ADAPTER         			BOEING	234   	234         	1385049	EA  	LYC   	AL5512	AL5512      	41581	NE  					ENGINE	CRACKED         	B			CHIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	242CH	4955 				MJ023				DURING OVERHAUL OF ENGINE AWN ADAPTER, NDT FOUND .450 INCH TOTAL LENGTH CRACK IN THE BOLT HOLE OF LUG NR 1.  IN THE BORE	 OF LUG, CRACK LENGTH IS .300 OF INCH AND ACROSS FACE OF LUG, THE CRACK LENGTH IS .150 OF INCH.  ILLUSTRATION DEPICTS LO	CATION AND SCHEMATIC OF CRACK FOUND.  FIRST TIME CRACK OF THIS NATURE NOTED ON THIS ADAPTER.  CHECKED OTHER ADAPTERS MFG	 UNDER THIS LOT NR.  THIS REVIEW CONCLUDED THAT THE CRACKED ADAPTER IS AN ISOLATED INCIDENT AND NOT RELATED TO MATERIAL 	DEFICIENCIES.  (K)		2	G	7	2 	4U	4	U		H9EA    	E4NE				 
2005062900025	20050629	00025	CE  	2005	6	29	2005FA0000872    	1	20050607	G	8120	AN62946	VALVE           			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	3AF34C	3AF34C*     	GL  	TURBOCHARGER	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4946K				TH08A69KFO22	P21000378	278771R	786058		RECEIVED TURBO CHARGER CHECK VALVE AND INSTALLED IN CORRECT ORIENTATION.  RAN ENGINE AND THE TURBO CHARGER CAVITATED DUE	 TO LOSS OF OIL SUPPLY.  FURTHER INVESTIGATION REVEALED THE NEW CHECK VALVE WAS BACKWARDS INTERNALLY IE: THE CHECK VALVE	 WAS AT THE OPPOSITE END OF THE FITTING AND FLOW ARROW COMPARED TO THE ORIGINAL CHECK VALVE.  RECOMMEND THAT ALL CHECK V	ALVES BE EXAMINED TO VERIFY PROPER PHYSICAL FLOW DIRECTION AND PROPERTIES.  (K)			1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P22EA	 
2005062800167	20050628	00167	SO  	2005	6	28	2005FA0000873    	2	20050602	G	8500		ENGINE          								CONT  	O520  	IO520D      	17032	SO  						MAKING METAL    	D				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AL	05										FACTORY REBUILT ENGINE WAS INSTALLED ON THE AIRFRAME.  DURING THE GROUND RUNS, LEAK CHECKS AND FINAL ADJUSTMENTS, THE ME	CHANIC NOTED THE PROP GOVERNOR WAS NOT CONTROLLING THE PROP AS IT SHOULD.  AFTER PERFORMING CHECKS RECOMMENDED BY THE MF	G, PROP WAS REMOVED AND METAL FLAKES WERE NOTED IN THE END OF THE CRANKSHAFT.  THE OIL FILTER WAS REMOVED AND INSPECTED 	AND WHAT APPEARED TO BE BRONZE, AND STEEL PARTICLES WERE FOUND.  THE FILTER ALONG WITH AN OIL SAMPLE WERE SUBMITTED TO T	HE ENGINE MFG.  REQUESTED THE ENGINE BE RETURNED TO THEM FOR FURTHER ANALYSIS.							3	O			E5CE				 
2005062800136	20050628	00136	SO  	2005	6	28	2005FA0000874    	1	20050607	G	5743	1159SB206233	RIB             			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					LT MLG	GOUGED          	B			BTVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	117MS	8617 	4198 			335				UPON REMOVAL OF THE BEARING ASSEMBLY FROM THE FORWARD LUG ON THE LT SPONSON RIB FOR THE MAIN LANDING GEAR ASSY, THE BORE	 OF THE LUG REVEALED A DEEP GROOVE CUT BETWEEN THE 10 O`CLOCK AND 2 O`CLOCK POSITION.  FOUND TO BE BEYOND MFG LIMITS.  R	EPLACED SPONSON RIB.  (K)				2	L	7	2 	4F	4	F		A12EA   	E2EU				 
2005062900092	20050629	00092	EU  	2005	6	29	2005FA0000875    	1	20050621	G	2720	A402092AN	CONTROL CABLE   	LET         		LET   	L13   	L13ACBLANIK 	1360312	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	423BA	375  				028904				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLEYS.						1	K	0	0 	  				G24EU   					 
2005062900093	20050629	00093	EU  	2005	6	29	2005FA0000876    	1	20050621	G	2720	A740254N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA	1030 				029007				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900096	20050629	00096	EU  	2005	6	29	2005FA0000877    	1	20050621	G	2720	A740255N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	430BA	1183 				029012				LEFT RUDDER CABLE FOUND FRAYED AT AFT PULLEY.  RIGHT RUDDER CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900097	20050629	00097	EU  	2005	6	29	2005FA0000878    	1	20050621	G	2720	A740255N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	431BA	826  				029013				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900098	20050629	00098	EU  	2005	6	29	2005FA0000879    	1	20050621	G	2720	A740255N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	437BA	970  				029015				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900099	20050629	00099	EU  	2005	6	29	2005FA0000880    	1	20050621	G	2720	A740255N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	419BA	1032 				029006				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900100	20050629	00100	EU  	2005	6	29	2005FA0000881    	1	20050621	G	2720	A740254N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	410BA	805  				029005				LEFT RUDDER CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900101	20050629	00101	CE  	2005	6	29	2005FA0000882    	1	20050621	G	2720	A402092N	CONTROL CABLE   			BEECH 	35    	35BEECH     	1151502	CE  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	421B	434  				D1428				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLEY POSITIONS.						1	L	7	1 	3O				A777    					 
2005062900102	20050629	00102	CE  	2005	6	29	2005FA0000883    	1	20050621	G	2720	A402092N	CONTROL CABLE   			BEECH 	35    	35BEECH     	1151502	CE  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	421B	434  				D1428				LEFT AND RIGHT RUDDER CABLES FOUND FRAYED AT FRONT AND REAR PULLEY POSITIONS.						1	L	7	1 	3O				A777    					 
2005062900117	20050629	00117	EU  	2005	6	29	2005FA0000884    	1	20050621	G	2720	A740255N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	438BA	415  				029016				RIGHT RUDDER CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062900119	20050629	00119	EU  	2005	6	29	2005FA0000885    	1	20050621	G	2720	A740255N	CONTROL CABLE   	LET         		LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	433BA	673  				029014				RIGHT RUDDER CABLE FOUND FRAYED AT FORWARD AND AFT PULLEYS.						1	K	0	0 	  			RC	G24EU   					 
2005062800121	20050628	00121	SO  	2005	6	28	2005FA0000886    	1	20050607	G	5530		SHEAR WEB       			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					VERTICAL STAB	DAMAGED         	B			BTVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	117MS	8617 				335				REPAIRED FORWARD VERTICAL SHEAR WEB ASSY OF THE VERTICAL STABILIZER DUE TO HOLE ELONGATION.  (K)						2	L	7	2 	4F	4	F		A12EA   	E2EU				 
2005062900028	20050629	00028	SO  	2005	6	29	2005FA0000887    	1	20050607	G	5542		SKIN            			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					RUDDER LE	CRACKED         	B			BTVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	117MS	8617 			GAC334	335				REPAIRED SKIN ON RUDDER LEADING EDGE AT THE NR 2 RUDDER HINGE POINT.  (K)						2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2005070700035	20050707	00035	EA  	2005	7	7	2005FA0000888    	2	20050620	G	8530	SL36006WA20P	CYLINDER        			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	2024Z	1106 	1106 			0098	L3678936A			DURING 100HR COMPRESSION CHECK, AIR WAS FOUND TO BE LEAKING AROUND TOP SPARK PLUG AREA.  FURTHER INSPECTION NOTED CRACK 	ALONG TOP COOLING FIN AREA.  UPON REMOVING CYLINDER, CRACK WAS FOUND TO RUN FROM AREA AROUND TOP SPARKPLUG HOLE THROUGH 	EXHAUST SEAT AND THROUGH TO EXHAUST FLANGE MOUNTING STUD.				1	G	7	1 	3O	3	O	O	4H12    	E286				 
2005070700036	20050707	00036	EA  	2005	7	7	2005FA0000889    	2	20050620	G	8530	SL36006WA20P	CYLINDER        			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	2024Z	1106 	1106 			0098	L3678936A			DURING 100HR COMPRESSION CHECK, AIR WAS FOUND TO BE LEAKING AROUND TOP SPARK PLUG AREA.  FURTHER INSPECTION NOTED CRACK 	ALONG TOP COOLING FIN AREA.  UPON REMOVING CYLINDER, CRACK WAS FOUND TO RUN FROM AREA AROUND TOP SPARKPLUG HOLE THROUGH 	EXHAUST SEAT AND THROUGH TO EXHAUST FLANGE MOUNTING STUD.				1	G	7	1 	3O	3	O	O	4H12    	E286				 
2005062800151	20050628	00151	SO  	2005	6	28	2005FA0000890    	2	20050601	G	8530		CYLINDER        			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NR 1	CRACKED         	D			EAVV	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	1249G					310Q1100	1482908V	727202		FOUND CASE CRACKED BEYOND REPAIR AT NR 1 CYLINDER, FOUND 2 THRU BOLTS SHEARED AND 5 CYLINDER STUDS BROKEN ON NR 1 CYLIND	ER.  THRU BOLTS DEFECTIVE CAUSING A CHAIN REACTION IN SHEARING CYLINDER STUDS.  SINCE CYLINDER WAS NO LONGER SEATED SQUA	RELY TO THE CASE, THIS CAUSED THE CASE TO CRACK WHILE ENGINE WAS IN OPERATION.  (K)				1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
2005062700207	20050627	00207	GL  	2005	6	27	2005FA0000891    	1	20050622	G	5514	5221007	BRACKET         			NAMER 	T6    	SNJ4        	6400414	GL  										HORIZONTAL STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	7070C					8813164				WHILE PERFORMING REPAIRS TO RT AND LT HORIZONTAL STABILIZERS, IT WAS DISCOVERED THAT THE OUTBOARD AND CENTER HINGE TEE R	EINFORCEMENT BRACKETS, P/N 52-21007 AND 52-21008, OF BOTH STABILIZERS WERE SEVERLY CORRODED.  THESE BRACKETS REINFORCE T	HE REAR SPAR WHERE THE ELEVATOR HINGE BRACKET ASSEMBLIES BOLT ON.  BOTH TEE REINFORCEMENT BRACKETS OF BOTH STABILIZERS W	ERE REPLACED WITH NEW PARTS.  FAILURE OF THESE REINFORCEMENTS COULD CAUSE THE BOLTS FOR THE ELEVATOR HINGE BRACKET ASSEM	BLIES TO PULL THROUGH THE SPAR.		1	L	7	1 	3R				A2575   					 
2005062700211	20050627	00211	GL  	2005	6	27	2005FA0000892    	1	20050622	G	5514	5221008	BRACKET         			NAMER 	T6    	SNJ4        	6400414	GL  										HORIZONTAL STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	7070C					8813164				WHILE PERFORMING REPAIRS TO RT AND LT HORIZONTAL STABILIZERS, IT WAS DISCOVERED THAT THE OUTBOARD AND CENTER HINGE TEE R	EINFORCEMENT BRACKETS, P/N'S 52-21007 AND 52-21008, OF BOTH STABILIZERS WERE SEVERLY CORRODED.  THESE BRACKETS REINFORCE	 THE REAR SPAR WHERE THE ELEVATOR HINGE BRACKET ASSEMBLIES BOLT ON.  BOTH TEE REINFORCEMENT BRACKETS OF BOTH STABILIZERS	 WERE REPLACED WITH NEW PARTS.  FAILURE OF THESE REINFORCEMENTS COULD CAUSE THE BOLTS FOR THE ELEVATOR HINGE BRACKET ASS	EMBLIES TO PULL THROUGH THE SPAR.		1	L	7	1 	3R				A2575   					 
2005062900073	20050629	00073	CE  	2005	6	29	2005FA0000893    	1	20050623	G	1100	07050429	PLACARD         			CESSNA	182   	182S        	2072701	CE  										CABIN	REVERSED        	Z				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	2465N	194  	5    			18280658				DURING INITIAL AUSTRALIAN CERTIFICATE OF AIRWORTHINESS INSPECTION, LT & RT CABIN DOOR HANDLE ESCUTCHEON/PLACARDS FOUND T	O BE TRANSPOSED.  THIS MEANS THAT INTERIOR DOOR HANDLE OPERATION INSTRUCTION IS IN REVERSE SENSE & EXIT HANDLE CANNOT BE	 OPERATED PER THE INSTRUCTIONS.  ESCUTCHEONS SWAPPED TO CORRECT SIDES.				1	H	7	1 	3O			NT	3A13    					 
2005062900074	20050629	00074	CE  	2005	6	29	2005FA0000894    	1	20050623	G	1100	0705042910	PLACARD         			CESSNA	182   	182S        	2072701	CE  										ZONE 800	REVERSED        	Z				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	2465N	194  	5    			18280658				DURING INITIAL AUSTRALIAN CERTIFICATE OF AIRWORTHINESS INSPECTION, LT & RT CABIN DOOR HANDLE ESCUTCHEON/PLACARDS FOUND T	O BE TRANSPOSED.  THIS MEANS THAT INTERIOR DOOR HANDLE OPERATION INSTRUCTION IS IN REVERSE SENSE & EXIT HANDLE CANNOT BE	 OPERATED PER THE INSTRUCTIONS. ESCUTCHEONS SWAPPED TO CORRECT SIDES.				1	H	7	1 	3O			NT	3A13    					 
2005063000113	20050630	00113	SO  	2005	6	30	2005FA0000895    	2	20050617	G	7322		ARM             			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					CARBURETOR	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	145RC	6566 				120				FOUND THAT THE FLOAT VALVE ARM WAS HITTING THE RETAINER HUB WHEN THE VALVE WAS FULLY ENGAGED.  IT WOULD APPEAR THAT THE 	ARM COULD SUFFER ENOUGH DAMAGE TO SEVER THE ARM FROM THE FLOAT BASE AND THAT WOULD ALLOW THE FLOAT VALVE CLOSE AND SHUT 	THE FLOW OF FUEL OFF FROM THE ENGINE.  PHOTOS OF THE VALVE. (K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005070100008	20050701	00008	CE  	2005	7	1	2005FA0000896    	1	20050512	G	5730	17220044	SKIN            			CESSNA	177   	177A        	2073706	CE  	LYC   	O360  	O360*       	41514	EA  					RT WING	CORRODED        	B			PVCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	30297	2369 				17701178				DURING AN ANNUAL INSP, RT WING IB L/E SKIN WAS FOUND CORRODED THROUGH BENEATH STRINGER.  A POSSIBLE CAUSE FOR THE EXCESS	IVE CORROSION MAY BE WATER SEEPING THROUGH THE AIR INLET HOSE INSTALLED ABOVE THE AFFECTED AREA.  THIS WATER ENTERS THRO	UGH THE L/E AIR INLET AND CREATES RUST IN THE STEEL WIRE WOUND HOSE AND DRIPS RUST CONTAMINATED WATER ON THE WING SURFAC	E BELOW WHICH MAY ACCELERATE THE CORROSION PROCESS.  IT IS RECOMMENDED THAT CLOSE ATTENTION BE PAID TO THAT PART OF THE 	WING AND TO THE CONDITION OF THE VENT HOSE DIRECTLY ABOVE IT ESPECIALLY IN AIRCRAFT THAT ARE STORED OUTDOORS.  APPLYING 	CORROSION RESISTANT CHEMICAL TO INSIDE OF WING WOULD ALSO HELP SITUATION. (K)	1	H	7	1 	3O	3	O		A13CE   	E286				 
2005070100009	20050701	00009	SO  	2005	7	1	2005FA0000897    	1	20050506	G	5711	82200696	SPAR            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					RT WING	CRACKED         	B			PVCR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	27PG	5238 				4622104				DURING ANNUAL INSPECTION, NOTE THAT SEVERAL RIVETS ATTACHING THE RT WING SKIN TO THE LOWER WING SPAR WERE BECOMING LOOSE	 (SMOKING) JUST OB OF THE MAIN GEAR DOOR AND INBOARD OF THE RIB AT WS79.5.  DURING INSP OF INSIDE OF WING IN SAME AREA, 	A CRACK WAS FOUND ON BOTTOM OF AFT SIDE OF SPAR ANGLE WHICH STARTS AT AFT END OF THE ANGLE AND PROPAGATES FORWARD THROUG	H AND BEYOND THE FIRST 2 ADJACENT BOTTOM RIVETS IB OF THE RIB AT WS 79.5.  IT APPEARS THAT THE WING FLEXES CONSIDERABLY 	IN THAT AREA AS EVIDENCED BY THE LOOSE RIVETS.  LOOSE RIVETS IN THAT AREA MAY HAVE CREATED LESS THAN DESIRABLE STRUCTURA	L INTEGRITY IN AFFECTED AREA.  THIS AREA SHOULD BE GIVEN SPECIAL ATTENTION ESPECIALLY IF LOOSE RIVETS ARE FOUND.  (K)	1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2005070100010	20050701	00010	EA  	2005	7	1	2005FA0000898    	2	20050601	G	7414	21C2153902	HOUSING         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540A1A5   	41532	EA  					LT MAG ADAPTER	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	3532K					18280974	RL2019148A			AFTER ENGINE INSTALLATION, 2 HOURS INTO BREAK IN PERIOD, OIL LEAK DISCOVERED IN BOSS OF CAMSHAFT IDLER GEAR.  LT MAY ADA	PTER BASE, CUT TOO WIDE; HOLE THROUGH TO SHAFT SUPPORT OF IDLER GEAR.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005070100011	20050701	00011	SO  	2005	7	1	2005FA0000899    	1	20050619	G	3213	6549000	CYLINDER        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					RT MAIN GEAR	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	1835T					287105112				UPON LANDING, RT MAIN GEAR SCISSORS ATTACHMENT LUGS BROKE FREE FROM THE CYLINDER.  CODE C, WHEEL WITH SCISSORS DAMAGED R	T FLAP.  (K)					1	L	7	1 	3O	3	O		2A13    	E286				 
2005070100012	20050701	00012	CE  	2005	7	1	2005FA0000900    	1	20050614	G	2810	21219	BLADDER         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	FUEL CELL	CONTAMINATED    	B			RG4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	428BD	10   				E950	822861R	EE4506B		CUSTOMER NOTED WHITE PARTICLES FROM QUICK DRAINS, INSPECTED, FOUND WHAT OWNER FOUND, WHITE PARTICLES.  REMOVED FUEL BLAD	DERS.  INSPECTED FOUND WHITE POWDER/ASH ON VARIOUS PLACES OF BOTH FUEL BLADDERS.  FUEL BLADDERS  MFG 7/04 AND 8/04.  WHI	TE POWDER IS COMING FROM THE INSIDE OF FUEL BLADDERS.  REPLACED BLADDERS WITH NEW FROM MFG UNDER WARRANTY.  MFG IS AWARE	 OF THIS PROBLEM.  CLEANED COMPLETE SYSTEM.  (K)			1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P25EA	 
2005070100014	20050701	00014	CE  	2005	7	1	2005FA0000901    	1	20050614	G	2810	212110	BLADDER         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	FUEL CELL	CONTAMINATED    	B			RG4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	428BD	10   				E950	822861R	EE4506B		CUSTOMER NOTED WHITE PARTICLES FROM QUICK DRAINS.  INSPECTED, FOUND WHAT OWNER FOUND WHITE PARTICLES.  REMOVED FUEL BLAD	DERS.  INSPECTED, FOUND WHITE POWDER/ASH ON VARIOUS PLACES OF BOTH FUEL BLADDERS.  FUEL BLADDERS  MFG 7/04 AND 8/04.  WH	ITE POWDER IS COMING FROM THE INSIDE OF FUEL BLADDERS.  REPLACED BLADDERS WITH NEW FROM MFG, UNDER WARRANTY.  CLEANED CO	MPLETE SYSTEM.  (K)			1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P25EA	 
2005070100024	20050701	00024	CE  	2005	7	1	2005FA0000902    	1	20050614	G	2810		BLADDER         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520*      	17032	SO  					LT FUEL CELL	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	09	101G					310R0017				THE LT OB BLADDER HAD A SMALL SEEPING LEAK AND WAS IGNITED CAUSING AN EXPLOSION.  THE SOURCE OF IGNITION  IS UNKNOWN, BU	T THE SECOND SENDING UNIT IS SUSPECTED.					1	L	7	2 	3O	3	O		3A10    	E5CE				 
2005070100026	20050701	00026	CE  	2005	7	1	2005FA0000903    	1	20050527	G	7330	10238901211	TRANSMITTER     			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL FLOW	FALSE INDICATION	B			VJ3R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			WP	07	1570A	3    				CE1333	830089R			PILOT REPORTED THAT FUEL FLOW WENT TO ZERO INDICATION DURING CLIMB OUT.  ALL OTHER ENGINE INDICATIONS NORMAL.  UPON TROU	BLESHOOTING OF THE FUEL FLOW SYSTEM FOUND FUEL FLOW TRANSMITTER WAS SENGIND ZERO FUEL FLOW READINGS TO FUEL FLOW INSTRUM	ENT.  NO RECOMMENDATIONS AT THIS TIME.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070100072	20050701	00072	SO  	2005	7	1	2005FA0000904    	1	20050624	G	3210	653193	LANDING GEAR    			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	RIGHT	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	11	1835T	5695 	38   			287105112	RL3980836A	76EMS5060		RT MAIN LANDING GEAR BROKE DURING LANDING AT PBF.						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2005070100073	20050701	00073	SO  	2005	7	1	2005FA0000905    	1	20050624	G	3210	653193	LANDING GEAR    			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ZONE 700	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	11	1835T	5695 	38   			287105112	RL3980836A	76EMS5060		RT MAIN LANDING GEAR BROKE DURING LANDING AT PBF.						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2005070100074	20050701	00074	SO  	2005	7	1	2005FA0000906    	1	20050624	G	3210	653193	LANDING GEAR    			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ZONE 700	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	11	1835T	5695 	38   			287105112	RL3980836A	76EMS5060		RT MAIN LANDING GEAR BROKE DURING LANDING AT PBF.						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2005070100050	20050701	00050	NM  	2005	7	1	2005FA0000908    	1	20050426	G	3230	45035	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										VALVE	GOUGED          	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					20509M					BORE IS GOUGED CAUSING LEAKAGE.  TOO MUCH PLAY BETWEEN POPPET AND BORE.  IMPROVE POPPET DESIGN TO HAVE TEFLON GUIDES TO 	PREVENT GOUGING.  (K)					2	L	7	2 	4F			RT	A16WE   					 
2005070100051	20050701	00051	NM  	2005	7	1	2005FA0000909    	1	20050426	G	2913	65447821	HOUSING         			BOEING	737   	737*        	       	NM  										HYD PUMP	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		62917								HOUSING CRACKED.  HOUSING IS TOO WEAK.  MAKE HOUSING STRONGER.  (K)  						2	L	7	2 	4F			RT	A16WE   					 
2005070100052	20050701	00052	NM  	2005	7	1	2005FA0000910    	1	20050420	G	2782	71001297	HOUSING         	SMITHSIND   		BOEING	727   	727*        	       	NM  										ACTUATOR	BROKEN          	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					CAI836					AIRCRAFT RETURNED FROM A FLIGHT WITH HYDRAULIC FLUID LEAKING FROM ACTUATOR.  FLIGHT ENGINEER WALK AROUND, FOUND BODY END	 BROKE OFF AT RETAINER END.  UNKNOWN, THIS IS A NEW AND IMPROVED POST SB BODY.  (K)  (REF: 194950/LEB)					2	L	7	3 	4F			RT	A3WE    					 
2005070100053	20050701	00053	NM  	2005	7	1	2005FA0000911    	1	20050525	G	3232	63141	CAP             	SARGENT     		BOEING	727   	727*        	       	NM  										ACTUATOR	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					3007					CAP IS CRACKED IN BOTTOM OF PORT C.  CAP IS TOO WEAK.  MAKE CAP STRONGER.  (K) (REF: 195902/FXS)						2	L	7	3 	4F			RT	A3WE    					 
2005070100054	20050701	00054	NM  	2005	7	1	2005FA0000912    	1	20050525	G	3252	39346901	CYLINDER        			DOUG  	MD900 	MD900       	3027375	NM  										SHIMMY DAMPER	DELAMINATED     	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01										CHROME HAS DELAMINATED IN CYLINDER BORE.  IMPROPER PLATING.  IMPROVE CHROME PLATING METHOD TO IMPROVE ADHESION TO CYLIND	ER. (K) (REF: 195920/JMG)					1	G	7	2 	3U			NC	H19NM   					 
2005070100055	20050701	00055	NM  	2005	7	1	2005FA0000913    	1	20050525	G	3252	39143567	CAP             			DOUG  	MD900 	MD900       	3027375	NM  										SHIMMY DAMPER	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01										CAP IS CRACKED ON PORT SIDE.  CATASTROPHIC FAILURE.  MANFACTURE CAP FROM SOLID BLOCK OF MATERIAL INSTAD OF CASTING PART.	  (K) (REF: 195920/JMG)					1	G	7	2 	3U			NC	H19NM   					 
2005070100056	20050701	00056	NM  	2005	7	1	2005FA0000917    	1	20050613	G	3230	45035	HOUSING         			BOEING	737   	737*        	       	NM  										MLG VALVE	CORRODED        	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01										BORE IS PITTED CAUSING LEAKAGE.  MOISTURE ALLOWED THROUGH VENT CORRODEING THE UPPER BORE AND WEAKENING THE MATERIAL.  IM	PROVE DESIGN TO PREVENT MOISTURE FROM REACHING BORE.  (K) (REF: 196593/ FXS)					2	L	7	2 	4F			RT	A16WE   					 
2005070100057	20050701	00057	CE  	2005	7	1	2005FA0000920    	1	20050607	G	2752	503801534	DRIVE ASSY      	RAYTHN      		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  					FLAP ACTUATOR	SHEARED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	81SK	17610	1543 		335L94	UE81				RT IB FLAP ACTUATOR WOULD NOT ACTUATE.  UPON TEARDOWN INSPECTION DISCOVERED THE 90 DEGREE DRIVE ASSEMBLY, FLAP CABLE CON	NECTOR COUPLING HAD SHEARED THE ROLL PIN THAT CONNECTS THE COUPLING TO A DRIVE GEAR.  THIS 90 DEGREE DRIVE ASSEMBLY HAS 	NO FIELD MAINTENANCE REQUIREMENTS BEYOND LUBING AND CHECKING GEAR FREEPLAY.  THIS PART IS NOT ALLOWED TO BE REPAIRED IN 	THE FIELD AND NO INSTRUCTIONS TO INSPECT THE SHEAR PINS.  THE FLAP ACTUATOR WAS LAST EACH 10,000 CYCLE INSPECTED 9/04.  	(K)		2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2005070100059	20050701	00059	NM  	2005	7	1	2005FA0000921    	1	20050612	G	5330		SKIN PANEL      			BOEING	737   	737291      	138448W	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					FUSELAGE	CORRODED        	B			KQ7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	583CC					21069				REMOVED CORROSION UNDER SKIN LAP JOINT, BS 787 TO BS 847, S-18R FWD OF AFT CARGO DOOR.  CUT OUT CORRODED SECTION, FABRIC	ATED FILLER, DOUBLER AND TRIPLER.  INSTALLED IAW B737 SRM.  FOUND DURING INSPECTION OF AD.  EXTERNAL VISUAL INSPECTION O	F SKIN FOR CORROSION AND DELAMINATION AT ALL LAP JOINTS IAW SB.  (K)				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005070100060	20050701	00060	NM  	2005	7	1	2005FA0000922    	1	20050613	G	5314		KEELBEAM        			BOEING	737   	737291      	138448W	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					FUSELAGE	CRACKED         	B			KQ7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	583CC	61161				21069				FOUND 8 INCH CRACK AND CORROSION IN LOWER RT KEELBEAM LOWER CHORD DURING C-CHECK.  REMOVED CORRODED RT KEELBEAM LOWER CH	ORD SECTION BS 540.  CUT OUT APPROX 8 INCHES LOWER CHORD.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005070100063	20050701	00063		2005	7	1	2005FA0000923    	4	20050614	G	3100	RMU1OH	MONITOR         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  						BROKEN          	B			FKFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	139PD					53631				3 MONITORS WERE INSTALLED DURING THE COMPLETION OF THE HELICOPTER ON AN FORM THAT WAS FIELD APPROVED.  DURNG LEVEL FLIGH	T, AT 6500 FEET, THE OUTER PANE OF GLASS SHATTERED FROM THE FRONT OF THE MONITOR WITH VARIOUS SIZE PIECES HITTING THE CR	EW.  MFG SENT 2 ENGINEERS WHO REVIEWED THE PROJECT.  THE UNITS ARE PRESSURE TESTED FROM THE FACTORY AND APPROVED TO 30,0	00 FEET.  (K)			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005070600060	20050706	00060	CE  	2005	7	6	2005FA0000924    	1	20050615	G	3234	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			WP	07	8112T	225  				CE1539	830118R			AFTER TAKEOFF AND GEAR HANDLE SELECTED FOR GEAR UP.  THE LANDING GEAR WOULDNT CYCLE UP.  STILL SHOWING 3 GREEN LIGHTS A	ND ON INTRASIT LIGHT.  MAIN TECH TROUBLESHOOT SYSTEM AND FOUND THAT THE DYNAMIC RELAY WAS INTERMITTENT.  NO RECOMMENDATI	ONS AT THIS TIME.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070600080	20050706	00080	EA  	2005	7	6	2005FA0000925    	2	20050614	G	7320	RSA5AD1	SERVO           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					FUEL INJECTOR	MALFUNCTIONED   	B			VJ3R	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	865AF	230  				85005	RL2631948A			PILOT REPORTED ENGINE QUIT AFTER LANDING WITH BOOST PUMP ON.  ON GROUND RUN PERFORMING MIXTURE IDLE CHECK, WE FOUND WITH	 BOOST PUMP OFF, WE HAD .5 INCH MANIFOLD PRESSURE DROP AND WITH BOOST PUMP ON.  WE HAD 1.5 INCH MANIFOLD PRESURE DROP.  	ON FURTHER INVESTIGATION, WE FOUND ICO LEVER STICKY AND ROUGH WHEN YOU MOVE IT.  AT THIS TIME NO PROBABLE CAUSE OR RECOM	MENDATION.  (K)			1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2005070600061	20050706	00061	CE  	2005	7	6	2005FA0000926    	1	20050614	G	3610	AA3216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					INSTRUMENT AIR	WEAK            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8240T	126  				CE1542	825916R			PILOT REPORTED LOW INSTRUMENT AIR PRESSURE AT 1000 RPM.  TROUBLESHOOTING SYSTEM FOUND TO BE OK, DETERMINED AIR PUMP WAS 	NOT PUTTING OUT SUFFICIENT PRESSURE.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070600077	20050706	00077	CE  	2005	7	6	2005FA0000927    	1	20050611	G	3234	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	8240T	172  				CE1542	825916R			LANDING GEAR WOULD NOT RETRACT AFTER THE 5TH CYCLE OF THE LANDING GEAR.  MAINTENANCE TECHNICIAN TROUBLESHOOT GEAR SYSTEM	 AND FOUND THAT THE DYNAMIC RELAY WAS INTERMITTENT.  NO RECOMMENDATION AT THIS TIME.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070600073	20050706	00073	CE  	2005	7	6	2005FA0000928    	1	20050616	G	3234	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	8240T	8    				CE1542	825916R			GEAR HANDLE HAS TO BE RECYCLED BEFORE GEAR COMES UP.  MAINTENANCE TECHNICIAN TROUBLESHOOT GEAR SYSTEM AND FOUND THAT THE	 DYNAMIC RELAY WAS INTERMITTENT.  NO RECOMMENDATION AT THIS TIME.  DYNAMIC RELAY MFG 0504. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070600066	20050706	00066	CE  	2005	7	6	2005FA0000929    	1	20050507	G	2840	10238901211	TRANSMITTER     			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL FLOW	READS HIGH      	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1570A	534  				CE1333	830089R			DURING POST PHASE INSPECTION RUN-UP.  TECHNICIAN FOUND FUEL FLOW READING 25.5 PSI AT HIGH RPM.  INSTALLED FUEL PRESSURE 	METERING GAGES AND FOUND FUEL TRANSMITTER READING HIGH ON ENGINE INSTRUMENT.  NO RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070600074	20050706	00074	SW  	2005	7	6	2005FA0000930    	1	20050323	G	3233	2751016003	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					RT MLG WW	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	782C					AC525				EMERG LAND MADE WITH RT GEAR UNSAFE LIGHT.  AFTER SHUT-DOWN, RT LANDING GEAR, IB ACTUATOR WAS FOUND BROKEN AT FWD MOUNT,	 HANGING DWN BELOW GEAR DOORS FROM AFT MOUNT.  (NOTE: EACH LANDING GEAR HAS 2 ACTUATORS, OB ACTUATOR HAD NO DAMAGE).  BR	OKEN ACTUATOR APPEARS TO BE ORIG ACTUATOR, NO RECORDS CAN BE FOUND INDICATING REPLACEMENT SINCE AC WAS NEW.  ACTUATOR RE	PLACEMENT SINCE IS (ON CONDITION) WITH NO REQUIRED OH TIME.  BROKEN ACTUATOR WAS REMOVED, REPLACED, SENT FOR ANALYSIS.  	MFG DETERMINED THAT CRACK AT FWD MTNG HOLE, WHICH LEAD TO FAILURE, ORIGINATED IN SMALL FLAW IN METAL.  GRADUALLY GREW TO	 POINT OF FAILURE.  STATED THAT THIS IS ISOLATED INCIDENT, AND FEEL THAT NO FURTHER ACTION IS REQUIRED.  (K)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005070600075	20050706	00075	SO  	2005	7	6	2005FA0000931    	2	20050624	G	7414	4309	MAGNETO         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	169PA	134  				C0270	650053			AFTER REMOVAL OF THE RT MAGNETO, INSPECTED THE MAGNETO AND FOUND THAT ONE END OF THE FORKEND OF THE ROTOR SHAFT HAD BROK	EN OFF CAUSING THE POINT TO FAIL TO OPEN.  THE MAGNETO WAS STILL UNDER WARRANTY, WAS UNABLE TO INSPECT MAGNETO FOR FURTH	ER DAMAGE.  (K)				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2005070600070	20050706	00070	EA  	2005	7	6	2005FA0000932    	1	20050616	G	5330	60135003	SKIN            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					FUSELAGE	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	604FJ	5478 				5001				AT LT AND RT FS 755, STRINGER 3,4,5 EXTENSIVE CORROSION WAS FOUND WHERE ACU DUCT IS ATTACHED TO SKIN PANEL.  NUMEROUS RI	VETS WERE MISSING FROM THE STRINGERS DUE TO CORROSION DAMAGE.  AIRCRAFT WAS MFG IN SEPT OF 1986.  (K)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005070600071	20050706	00071	CE  	2005	7	6	2005FA0000933    	1	20050616	G	6100	NAS1149C0332R	WASHER          	HARTZL      		BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	HUB ASSY	IMPROPER PART   	B			EHHR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	21YM				ED4437B	TH2005		ED4437B		WHILE PERFORMING SB WHICH INCLUDES PROPELLER, REMOVING THE MOUNTING PLATE FROM THE SLIP RING, FOUND THAT THE WASHERS USE	D TO HOLD THESE ITEMS TOGETHER ARE TOO WIDE AND SCORED, THE PROP HUB.  WERE ABLE TO POLISH OUT THE SCOPE MARKS ON THE HU	B AND MODIFY THE WASHERS TO HAVE A SLIGHT FLATEN AREA ON ONE SIDE AS NOT TO CONTACT THE HUB.  (K)				1	L	7	2 	3O				3A16    		5	C	P36EA	 
2005070600072	20050706	00072	NE  	2005	7	6	2005FA0000934    	2	20050621	G	8520	12611	CRANKSHAFT      								PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	CRACKED         	B			CP2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15							24877			THE CRANK PIN OF THE REAR HALF CRACKED FROM THE CRANK PIN RADIUS THRU TO THE REAR MAIN BEARING RADIUS.  AFTER CLEANING A	ND CLOSE EXAMINATION, IT IS OUR OPINION THAT THE CRACK ORIGINATED AT THE CRANK PIN RADIUS.  MACHINE MARKS ON THE REMAINI	NG PORTION OF THE RADIUS INDICATE A PREVIOUS REWORK OF THIS AREA.  (K)									3	R			5E2				 
2005070600068	20050706	00068	SO  	2005	7	6	2005FA0000935    	1	20050621	G	5102	FFAX7B	ENVELOPE        			BALWKS	FIREFY	FIREFLY7B   	10501A9	SO  										BALLOON	FAILED          	C				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			WP	05	1539G	263  				10249				BALLOON ENVELOPE FAILED FUEL CONSUMTION FLIGHT TEST.  (K)						1	B	0	0 	  				A14SO   					 
2005070600064	20050706	00064		2005	7	6	2005FA0000936    	4	20050616	G	2297	4020570901	CONTROL PANEL   	HONEYWELL   																AUTOPILOT	MISWIRED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27										MODE CNTRL PNL WAS SENT FROM MFG AS REPLACEMENT FOR FAILED UNIT.  NAV/HSI FUNCTION WHICH ALLOWS SELECTION SOURCE SIDE TH	AT AUTOPILOT IS GOING TO USE IS REVERSED.  WHEN SELECT SIDE ONE AND (1) ON PANEL IS ILLUMINATED AUTOPILOT IS ACTUALLY US	ING SIDE (2) HSI OR SOURCE.  WHEN SELECT SIDE (2) AND (2) IS ILLUMINATED ON PNL, USING SIDE (1) HSI OR SOURCE.  PROBLEM 	WAS DISCOVERED DURING FUNCTIONAL TEST OF PNL AFTER INSTALLATION.  SWITCH WAS WIRED IMPROPERLY DURING OH, MALFUNCTION WAS	 NOT CAUGHT DURING FINAL TESTING.  DURING FINAL CKOUT, THIS FUNCTION SHOULD BE VERIFIED, IF BUGS, POINTERS AND ETC. ARE 	NOT SET IDENTICAL ON BOTH SIDES, AUTOPILOT IS GOING TO BE USING OFFSIDE DATA, AC WILL NOT RESPOND AS COMMANDED. (K)														 
2005070700033	20050707	00033	CE  	2005	7	7	2005FA0000937    	1	20050502	G	2750	0512128	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					CONTROL CABLE	BROKEN          	B			YEBR	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CE	05	26DL	2230 				18502287				PILOT REPORTED THAT THE FLAPS FELT FUNNY AND THAT THEY MADE A GRINDING NOISE.  INSPECTION OF FLAP SYSTEM FOUND PULLEY BR	ACKET FOR LT FLAP EXTEND CABLE HAD BROKEN AT 2 OF THE 4 MOUNTING SCREW TABS.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
2005070700016	20050707	00016	CE  	2005	7	7	2005FA0000938    	1	20050127	G	3220	AHML6	ROD END         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG	BROKEN          	G				L				ABORTED APPROACH        				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			GL	05	25625					E393				DURING APPROACH TO LAND, IT WAS DISCOVERED BY THE PILOT THAT THE NOSE GEAR WOULD NOT EXTEND.  NORMAL AND EMERGENCY GEAR 	EXTENSION WAS PERFORMED WITHOUT SUCCESS.  THE AIRCRAFT MADE A SUCCESSFUL NOSE GEAR RETRACTED EMERGENCY LANDING.  EXAMINA	TION BY MAINTENANCE TECHNICIANS REVEALED THAT THE AFT ROD END ON THE NOSE GEAR RETRACT ROD ASSEMBLY HAD FAILED.  THE ROD	 END WAS INSPECTED BY A METALLURGICAL LAB AND FOUND TO BE A FRESH BREAK WITH NO INDICATION OF PRIOR CRACKING.  A NEW ROD	 END WAS INSTALLED, GEAR RIGGED AND AIRCRAFT WAS RETURNED TO SERVICE.		1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005070700017	20050707	00017	SO  	2005	7	7	2005FA0000939    	1	20050701	G	3211		SUPPORT TUBE    	AYRES       		AYRES 	S2T   	STRT34      	0970106	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					LANDING GEAR	FRACTURED       	G				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			WP	09	4009J	16326				6015				THE RT LANDING GEAR COLLAPSED DURING TAKEOFF FROM A ROUGH DIRT STRIP.  A LANDING GEAR SUPPORT TUBE BROKE NEAR ONE ATTACH	 POINT.  CORROSION WAS PRESENT.					1	L	7	1 	3T	4	T		A3SW    	E4EA				 
2005070700032	20050707	00032	SO  	2005	7	7	2005FA0000940    	1	20050621	G	2731	1561805	ARM             	PIPER       		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					ELEVATOR TAB	CORRODED        	G				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SW	17	2521M					277954072				WHILE INVESTIGATION AIRCRAFT ACCIDENT NR DFW05LA167 THE STABILATOR TRIM TAB ROD WAS DISCOVERED SEPARATED AT APPROX 3 INC	HES FROM TAB.  VISUAL INSPECTION REVEALED CORROSION ON THE INTERIOR OF THE PART.  FUTHER DETAILED INSPECTION SHOWED MINI	MAL SHEAR LIP, LEADING FAILURE TO BE CORROSION FATIGUE DUE TO REPEATED LOADING.  THE OPERATOR REPORTED LOSS OF STABILATO	R TRIM AT 8,000 FT AND VIOLENT SHAKING OF AIRCRAFT.			1	L	7	2 	3O	3	O		1A10    	E14EA				 
2005071200124	20050712	00124	SO  	2005	7	12	2005FA0000941    	1	20050620	G	7603	554528	THROTTLE CABLE  			PIPER 	PA44  	PA44180     	7104402	SO  										RT ENGINE	BROKEN          	B				A				UNSCHED LANDING         				O			OTHER                     			AP	APPROACH       	1			WP	05	570ER	2457 	20   			4496146				DURING CROSS COUNTRY TO KINGMAN, DURING A TOUCH AND GO PROCEDURE THE STUDENT DECREASED THE THROTTLES BUT THE RIGHT ENGIN	E POWER DID NOT REDUCE.  DECLARED AN EMERGENCY AND DURING THE LANDING FLARE THE MIXTURE WAS CUT OFF KILLING THE ENGINE. 	 MAINTENANCE PERSONNEL FOUND THE THROTTLE CABLE HAD BROKEN APPROXIMATELY .5 INCH INSIDE THE INSIDE THE CABLE SHEATH AT T	HE CABIN END OF THE CABLE.  IT APPEARS TO HAVE BEEN CAUSED BY FLEXING AT THIS POINT DURING THROTTLE CHANGES.			1	L	7	2 	3O				A19S0   					 
2005071100148	20050711	00148	SO  	2005	7	11	2005FA0000942    	1	20050708	G	3260		LANDING GEAR    			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NOSE	NO INDICATION   	D				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			EA	17										PILOT DID NOT HAVE A GREEN LIGHT FOR THE NOSE GEAR ON HIS FINAL APPROACH. ATC WAS NOTIFIED AND A VISUAL WAS CONFIRMED TH	AT HIS NOSE GEAR WAS IN A DOWN ATTITUDE. NO INFORMATION WAS GIVEN UPON HOW MANY TIMES THE GEAR WAS CYCLED IF AT ALL. PIL	OT LANDED UNEVENTFUL. THE AIRCRAFT WAS INSPECTED ON THE RUNWAY AND THE NOSE GEAR INDICATOR WAS ILLUMINATED. THE AIRCRAFT	 WAS PUT ON JACKS , GEAR WAS CYCLED , AND AN ADJUSTMENT WAS MADE TO COMPENSATE FOR NORMAL WEAR.			1	L	7	2 	3O	3	O		1A10    	1E10	5	C	P920	 
2005071200067	20050712	00067	SO  	2005	7	12	2005FA0000943    	1	20050701	G	2750	1763400	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ZONE 100	CUT             	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15			1100 			273645				PERFORMING AD 2003-09-13, FOUND TORQUE TUBE WORE/CUT BY LEFT RUDDER CABLE, 2 INCHES LONG AND THRU TUBE WALL.  TUBE HAS B	EEN INSTALLED SINCE 1996 1100 HRS AGO. 					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005071200068	20050712	00068	SO  	2005	7	12	2005FA0000944    	1	20050701	G	2750	1763400	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ZONE 100	CUT             	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15			1100 			273645				PERFORMING AD 2003-09-13, FOUND TORQUE TUBE WORE/CUT BY LEFT RUDDER CABLE, 2 INCHES LONG AND THRU TUBE WALL.  TUBE HAS B	EEN INSTALLED SINCE 1996 1100 HRS AGO. 					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005071200085	20050712	00085	CE  	2005	7	12	2005FA0000945    	1	20050623	G	2710	12339	CONTROL CABLE   			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320E2A    	41508	EA  	SNSNCH	74D	74DM        	EA  	AILERONS	SLIPPED         	P				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NM	05	41690	97   				39973				AILERON CABLE SLIPPED OUT OF THE INBOARD NICOPRESS SLEEVE ON THE FORWARD AILERON CABLE IN THE LEFT WING.  ALL 4 (LEFT AN	D RIGHT WING) CABLES WERE PURCHASED NEW FROM AMERICAN CHAMPION AIRCRAFT IN AUG, 2002 AND INSTALLED DURING THE REBUILD OF	 THE AIRCRAFT.  ALL NICOPESS SLEEVES ON ALL 4 CABLES WERE CHECKED AND FOUND TO BE OUTSIDE OF THE GO/NO-GO GAUGE LIMIT.				1	H	7	1 	3O	3	O		A759    	1E12	5	N	P88614	 
2005071200144	20050712	00144	CE  	2005	7	12	2005FA0000947    	1	20050630	G	3220		COLLAR          			CESSNA	185   	A185E       	2072818	CE  										TAIL WHEEL	MISSING         	H				O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			WP	05	4530F					1851015				THE AIRPLANE GROUNDLOOPED.  DISASSEMBLY REVEALED THAT THE TAIL WHEEL-LOCKING COLLAR WAS NOT INSTALLED ON THE TAILWHEEL A	SSEMBLY.  ALSO, THE STEERING NOTCH ON THE TAILWHEEL STEERING ARM WAS WORN SO THAT A LIGHT AMOUNT OF PRESSURE BY HAND WOU	LD ALLOW THE TAILWHEEL TO BE TURNED ABOUT ITS STEERING AXIS.  THE MISSING LOCKING COLLAR WAS NOT APPARENT UNTIL THE TAIL	WHEEL WAS DISASSEMBLED.			1	H	7	1 	3O				3A24    					 
2005072100171	20050721	00171	SO  	2005	7	21	2005FA0000950    	2	20050115	G	7314	6559211A2	PUMP            			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					FUEL SYSTEM	FAILED          	P				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	11	10368	87   				290286	684961			THIRD FUEL PUMP FAILURE ON AIRCRAFT/ENGINE IN APPROX 90 HRS. FUEL PUMP RETURNED TO CONT FOR ANALYSIS BUT THEY WERE NOT A	BLE TO LOCATE FOR TESTING/ANALYSIS.  NEITHER MOONEY OR CONTINENTAL HAVE BEEN ABLE TO DETERMINE CAUSE OF PUMP FAILURES.					1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2005071300066	20050713	00066	SO  	2005	7	13	2005FA0000951    	2	20050524	G	8520		CONNECTING ROD  			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	FAILED          	P				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			SW	15	4950Z	601  				U20606055	284866R	992752		IN SLOW DESCENT FOR LANDING AT 3,000 FT AGL, SEVERE VIBRATION OCCURRED AND THEN WITHIN 30 SECONDS A LOUD BANG AND OIL CO	VERING WINDSHIELD AND SIDE WINDOWS. DIVERTED FLT ABOUT 5-6 MILES AWAY AND MADE SAFE LANDING AT AIRPORT. UPON INSPECTION,	 NR 2 ROD PENETRATED TOP OF ENGINE CASE AND SUBSEQUENTLY SHEARED MAGNETO OFF OF CASE. SOME INDICATION OF CRANKSHAFT FAIL	URE, BUT UNKNOWN AT THIS TIME AS MFG HAS REQUESTED TO TEAR DOWN ENGINE AT FACTORY.			1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P47GL	 
2005071300085	20050713	00085	CE  	2005	7	13	2005FA0000953    	1	20050627	G	5740	5414030	ANGLE           			NAMER 	T6    	AT6G        	6400434	CE  	PWA   	R1340 	R1340*      	52016	NE  					LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	92778					5114799				UPON COMPLYING WITH EMERGENCY AD 2005-12-51 IT WAS DISCOVERED THE LT OUTER WING LOWER BOLTING ANGLE P/N 54-14030 WAS HEA	VILY DAMAGED BY PITTING, FILIFORM & ESPECIALLY EXFOLIATION TYPE CORROSIONS.  THIS DAMAGE WAS ONLY FOUND AFTER STRIPPING 	PAINT & PRIMER AWAY TO PERFORM THE REQUIRED ZYGLO INSPECTION BY AD 2005-12-51.  DAMAGE WAS NOT APPARENT WITH PRIMER PAIN	T IN PLACE.  THIS TYPE DAMAGE WAS ALSO FOUND ON THE LH FWD LOWER WING CENTER SECTION BOLTING ANGLE.  THIS DAMAGE WAS ALS	O MIRRORED ON THE RT WING & CENTER SECTION BOLTING ANGLES.  RECOMMEND CLOSE VISUAL, ZYGLO OR EDDY CURRENT INSPECTION OF 	ALL WING ATTACH ANGLES AT REGULAR INTERVALS.	1	L	7	1 	3R	3	R		A2575   	5E2				 
2005071500030	20050715	00030	CE  	2005	7	15	2005FA0000954    	1	20050714	G	3246	19949	WHEEL           			BEECH 	35    	V35A        	1151544	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	22PK	21   				D8647				THIS KIT WAS PURCHASED NEW AND OF THE 4 WHEEL HALVES THAT ARE PART OF THE KIT, AFTER ONLY ONE YEAR OF USE, 3 SHOWED SUCH	 SIGNS OF CORROSION THAT IT IS QUESTIONABLE IF THE LIFE OF THE 3 WHEEL HALVES WOULD BE OVER 2 YEARS.  AFTER ITS OWN INSP	ECTION, THE MANUFACTURE DENYS ANY RESPONSIBILITY NOR INTEREST IN THE MATTER.  I FIND IT WORTHY OF INVESTIAGATION AS TO W	HY THE ONE WHEEL HALF CONTINUES TO BE IN VERY GOOD SHAPE WHILE THE OTHER 3 ARE IN SUCH A STATE OF DETERIORATION.			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005071500031	20050715	00031	CE  	2005	7	15	2005FA0000955    	1	20050714	G	3246	19949	WHEEL           			BEECH 	35    	V35A        	1151544	CE  	CONT  	O520  	IO520*      	17032	SO  					ZONE 700	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	22PK	21   				D8647				THIS KIT WAS PURCHASED NEW AND OF THE 4 WHEEL HALVES THAT ARE PART OF THE KIT, AFTER ONLY ONE YEAR OF USE, 3 SHOWED SUCH	 SIGNS OF CORROSION THAT IT IS QUESTIONABLE IF THE LIFE OF THE 3 WHEEL HALVES WOULD BE OVER 2 YEARS.  AFTER ITS OWN INSP	ECTION, THE MANUFACTURE DENYS ANY RESPONSIBILITY NOR INTEREST IN THE MATTER.  I FIND IT WORTHY OF INVESTIAGATION AS TO W	HY THE ONE WHEEL HALF CONTINUES TO BE IN VERY GOOD SHAPE WHILE THE OTHER 3 ARE IN SUCH A STATE OF DETERIORATION.			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072000028	20050720	00028	CE  	2005	7	20	2005FA0000959    	1	20050621	G	8011		DRIVE ASSY      			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					STARTER	FAILED          	B			YEBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	6317T				E111092	R18201975	L2322740A			INSTALLED FACTORY OVERHAULED ENGINE ONTO AIRCRAFT.  THE STARTER BENDIX WAS ENGAGED WHEN ENGINE WAS INSTALLED.  AFTER FIR	ST START THE STARTER WOULD SPIN BUT BENDIX WOULD NOT RE-ENGAGE STARTER RING GEAR ON ENGINE.  REPLAED WITH OVERHAULED SPA	CE STARTER (SN E123085). (K)				1	H	7	1 	3O	3	O		3A13    	E295				 
2005072000114	20050720	00114	CE  	2005	7	20	2005FA0000960    	1	20050715	G	2750	45A6103511	CABLE           			BEECH 	MU300 	400A        	1155402	CE  										TE FLAPS	BROKEN          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	11	746TA	6580 				RK146				FLAP FOLLOW-UP CABLE WAS DISCOVERED CORRODED AND BROKEN IN HALF DURING AN INSPECTION.						2	H	7	2 	4F			RT	A16SW   					 
2005072000163	20050720	00163	NM  	2005	7	20	2005FA0000961    	1	20050704	G	5712	SA3A	RIB             			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  	SNSNCH	76AK	M76AK       	EA  	WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	2172H	2687 				2795	NA	NA		WHILE COMPLYING WITH SB 31 METHOD 1 (INSTALLING INSPECTION PANELS) AND AD 02-26-02, FOUND LEFT INBOARD WALK BOX RIB AFT 	ANGLE SUPPORT COMPROMISED WITH SEVERE EXFOLIATION DAMAGE.  THE ORIGINAL PIECE WAS IN A BAY COATED WITH DIRT.  THE AIRCRA	FT HAD BEEN STORED WITH WINGS OFF FOR 7 YEARS AND NO DEFECTS WERE NOTED WHILE LOOKING IN THE WING CENTER SECTION PRIOR T	O ASSEMBLY.  SINCE A BOROSCOPE HAS LIMITED ABILITY, I RECOMEND INSTALLING THE PANELS TO ALLOW REMOVAL OF DIRT AND OTHER 	DEBRIS THAT ACCUMULATES OVER TIME.  MANUFACTURED AN ANGLE ALUMINUM BRACE FROM STANDARD ANGLE ALUMINUM TO REPLACE ORIGINA	L PART.	1	L	7	1 	3O	3	O		A718    	E233	5	N	1P210	 
2005072000169	20050720	00169	SO  	2005	7	20	2005FA0000966    	1	20050706	G	2710	86396002	RIB             	PIPER       		PIPER 	PA32  	PA32R301    	7103218	SO  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	755BE	3872 				32R8213009				LEFT AILERON OUTBOARD HINGE HALF WAS CORRODED.  AILERON WAS DISASSEMBLED TO REPLACE HINGE HALF.  UPON REMOVING AN3 BOLTS	 AND HINGE HALF FROM NOSE RIB, THE LOWER BOLT HOLE IN THE NOSE RIB WAS FOUND TO HAVE A HALF INCH CRACK ADJACENT TO THE H	OLE.IT IS NOT POSSIBLE TO INSPECT THIS AREA WITHOUT DISASSEMBLY OF THE AILERON.				1	L	7	1 	3O				A3SO    					 
2005072100003	20050721	00003	SO  	2005	7	21	2005FA0000967    	1	20050609	G	5741		ATTACH FITTING  			GULSTM	G1159 	G1159B      	3953535	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					RT WING	CORRODED        	B			N38R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	510SR					070				IAW MM TO COMPLY WITH THE 24 MONTH NDT REQUIREMENTS UNDER THE ULTRASONIC PART OF THE INSPECTION CORROSION WAS FOUND ON B	OTH THE LT AND RT WING ATTACHMENT FITTINGS AT FS 452, BL33, LT AND RT.  TECH OPS REQUIRES COMPLIANCE WITH ASC FOR A 3 PI	ECE FITTING PLATE.  (K)				2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2005072100001	20050721	00001	NM  	2005	7	21	2005FA0000968    	1	20050621	G	8011		DRIVE GEAR      			UNIVAR	108   	108         	9230402	NM  	LYC   	O540  	O540L3C5    	41532	EA  					STARTER	MALFUNCTIONED   	B			YEBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	6317M				E123085	1084317				REMOVED DEFECTIVE STARTER (SN E111092 FROM ENGINE.  INSTALLED OVERHAULED STARTER ONTO ENGINE WITH BENDIX ENGAGED.  AFTER	 FIRST START, THE STARTER WOULD SPIN BUT NOT RE-ENGAGE STARTER BENDIX INTO  RING GEAR ON ENGINE.  INSTALLED PRESTOLITE S	TARTER.  OPERATION AND GROUND RUN CHECKED GOOD.  (K)				1	H	7	1 	3O	3	O		A767    	E295				 
2005072100005	20050721	00005	SO  	2005	7	21	2005FA0000969    	2	20050628	G	7414	IO400309	IMPULSE COUPLING			CESSNA	210   	210M        	2073450	CE  	CONT  	O550  	IO550*      	 	SO  					MAGNETO	WORN            	B			YEBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	6175N	959  	114  		FOICA070R	21062946	289173R			MAGS REMOVED FOR TROUBLESHOOTING OF ENGINE HIGH ALTITUDE OPERATION PROBLEM.  DURING PREINSTALLATION INSPECTION OF COUPLI	NGS.  ONE WAS FOUND WORN BEYOND LIMITS.  (K)					1	H	7	1 	3O	3	O		3A21    	E3SO				 
2005072100016	20050721	00016	SO  	2005	7	21	2005FA0000970    	2	20050701	G	8530	SA55000A1	CYLINDER HEAD   								CONT  	O550  	IO550F      	17042	SO  					ENGINE	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	99							679521			HEAD SEPARATED FROM CYLINDER IN FLIGHT.  NO INJURIES.  NO INCIDENT.  (K)											3	O			E3SO				 
2005072100006	20050721	00006	CE  	2005	7	21	2005FA0000971    	1	20050627	G	5543		SKIN            			CESSNA	210   	T210*       	       	CE  										TRIM TAB	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13										NEW TRIM TAB RECEIVED IN PRIMER.  UPON PAINTING, NOW SHOWS CREASE IN UPPER SKIN FROM IB END APPROX 18 INC IN CENTER OF S	KIN.  CREASE PASSES THROUGH RIVETS IN FRONT OF BLOCK STIFFENER FOR TRIM ACTUATOR FITTING.  FONT RIVETS IN BLOCK OVER DRI	VEN CAUSING BUCKLE IN SKIN AT RIVETS.  SUSPECT INTERNAL BLOCK DAMAGED.  POOR WORKMANSHIP AND INSPECTION AT FACTORY.  (K)				1	H	7	1 	3O				3A21    					 
2005072100180	20050721	00180	CE  	2005	7	21	2005FA0000972    	1	20050718	G	5342	AN45A	BOLT            			CESSNA	150   	152         	2071835	CE  										HORIZONTAL STAB	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	4898B					15283697				AFTER USING AN ORBITAL WAXING BUFFER ON THE HORIZONTAL STABILIZER, THE OWNER NOTICED LOOSENESS AT THE HORIZONTAL STABILI	ZER LEADING EDGE AND THE OUTBOARD EDGE. INVESTIGATION REVEALED THAT BOTH FOWARD ATTACH BOLTS, P/N AN44-5A (IPC FIG 18A I	TEM 1) WERE LOOSE. BOLTS WERE RETORQUED PER MAINTENANCE MANUAL.  THE VIBRATION ACTION OF THE BUFFER APPEARENTLY CAUSED T	HE LOOSENESS.			1	H	7	1 	3O			NT	3A19    					 
2005072200090	20050722	00090	SO  	2005	7	22	2005FA0000974    	2	20050721	G	7414	6310	MAGNETO         			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	113SG	721  				18264758				FOUND AN OIL LEAK COMING FROM THE BASE OF THE LEFT MAGNETO. REMOVED MAG TO REPLACE GASKET. FELT SOMETHING ON THE MOUNTIN	G FLANGE OF THE MAG. FOUND A SECTION OF THE FLANGE ABOUT 1 1/4 INCH CRACKED WHERE THE HOLD DOWN CLIP CLAMPS THE MAG TO T	HE ENGINE CASE. A LITTLE HAND PRESSURE AND THE CRACKED SECTION CAME OFF.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2005072200091	20050722	00091	SO  	2005	7	22	2005FA0000975    	2	20050721	G	7414	6310	MAGNETO         			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	113SG	721  				18264758				FOUND AN OIL LEAK COMING FROM THE BASE OF THE LEFT MAGNETO. REMOVED MAG TO REPLACE GASKET. FELT SOMETHING ON THE MOUNTIN	G FLANGE OF THE MAG. FOUND A SECTION OF THE FLANGE ABOUT 1 1/4 INCH CRACKED WHERE THE HOLD DOWN CLIP CLAMPS THE MAG TO T	HE ENGINE CASE. A LITTLE HAND PRESSURE AND THE CRACKED SECTION CAME OFF.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2005072200092	20050722	00092	SO  	2005	7	22	2005FA0000976    	2	20050721	G	7414	6310	MAGNETO         			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	113SG	721  				18264758				FOUND AN OIL LEAK COMING FROM THE BASE OF THE LEFT MAGNETO. REMOVED MAG TO REPLACE GASKET. FELT SOMETHING ON THE MOUNTIN	G FLANGE OF THE MAG. FOUND A SECTION OF THE FLANGE ABOUT 1 1/4 INCH CRACKED WHERE THE HOLD DOWN CLIP CLAMPS THE MAG TO T	HE ENGINE CASE. A LITTLE HAND PRESSURE AND THE CRACKED SECTION CAME OFF.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2005072200196	20050722	00196	EA  	2005	7	22	2005FA0000977    	1	20050628	G	3234	7455025	CONTROL HANDLE  			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	22SF	72   				5589				WHEN LANDING GEAR HANDLE MOVED TO EXTEND.  NO MOVEMENT OF GEAR OR INDICATION OF MOVEMENT NOTED.  (K)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005072200210	20050722	00210	WP  	2005	7	22	2005FA0000978    	1	20050625	G	7160	5930645509	NOSE COWL       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D        	 	NE  					ENGINE	DEBONDED        	B			UMXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	190AN					53190				SKIN PANELS HAVE DELAMINATED AT FWD EDGE, COMMON TO LIP SKIN.  EVIDENCE OF HIGH TEMPERATURE AS FIBERGLASS APPEARS DARKEN	ED AND IS BRITTLE.  OUTER SKINS OF BARREL ARE DEBONDED AND DISCOLORED BY HIGH TEMPERATURE.  PROBABLE CAUSE:  ANTI-ICE LE	FT OPERATING FOR LONG PERIOD OF TIME ON GROUND.  (K)				2	L	7	2 	4F	4	F	RT	A6WE    	E2EA				 
2005072200207	20050722	00207	CE  	2005	7	22	2005FA0000979    	1	20050502	G	3212	MC2711B	ACTUATOR        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470*       	17026	SO  					FLOAT	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	3126D				257	31924				LT MAIN LANDING GEAR FAILED DOWN AND LOCKED POSITION, UPON INSPECTION, O-RING IN ACTUATOR PLUNGER ASSY, MS28775-214 WAS 	FOUND DEFECTIVE, REPLACED WITH SAME PN RE INSTALLED ACTUATO TO FLOAT ASSY.  OPS CHECKED OK, NO DEFECTS NOTED.  (AL052005	02475) (K)				1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2005072200208	20050722	00208	CE  	2005	7	22	2005FA0000980    	1	20050614	G	5320	53120252	PAN             			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					TAIL	CRACKED         	B			CTUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	340AX	5627 				340A0020				AFT PAN ASSY IN TAIL CRACKED.  THIS IS A RECURRING ISSUE WITH OUT FLEET.  PROBABLE CAUSE IS EXCESS FLEX IN TAIL.  RECOMM	END CLOSER INSPECTION DURING 100 HR/ANNUAL INSPECTIONS.  (GL21200502750) (K)					1	L	7	2 	3O	3	O		3A25    	E8CE				 
2005072200211	20050722	00211	CE  	2005	7	22	2005FA0000981    	1	20050531	G	5312	00244002465	BULKHEAD        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	8248K	19200				E2678				BULKHEAD CRACKED APPROX .3750 INCH ON UPPER LT AREA ON BEND RADIUS, BULKHEAD TIES IN VERTICAL AND HORIZONTAL STABILIZERS	 TOGETHER.  FATIGUE DUE TO HIGH TT ON AIRFRAME, PROBABLE CAUSE?  (SW01200504869) (K)					1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005072200213	20050722	00213	CE  	2005	7	22	2005FA0000982    	1	20050322	G	5610	10138402518	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	905GP	4636 				BB789				PILOTS WERE INCRUISE WITH WINDSHIELD HEAT ON AND WINDSHIELD (INNER) SHATTERED.  TALKED TO TECH AND WAS STATED IT WAS USU	ALLY THE INNER THAT SHATTERS.  ALTITUDE 22,000 FT CLEAR, -35 DEGREES C.  NO TURBLANCE, NO ICING.  (EA17200508780) (K)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005072200212	20050722	00212	CE  	2005	7	22	2005FA0000983    	1	20050505	G	3230	HMX5FG	ROD END         			BEECH 	35    	M35         	1151526	CE  	CONT  	O470  	IO470C      	17026	SO  					NLG	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	374Z	5320 				D6554	722830C			THE BEARING END PARTED FROM THE THREAD PORTION OF THE ROD END, CAUSING COLAPSE OF THE NOSE LANDING GEAR.  THE DEFECT APP	EARED ON ROLL OUT AFTER LANDING, WHEN THE NOSE GEAR COLLAPSED.  STRUCTURAL FAILURE OF THE ROD END.  (SW15200512716) (K)					1	L	7	1 	3O	3	O		3A15    	E273				 
2005072200214	20050722	00214	CE  	2005	7	22	2005FA0000984    	1	20050706	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					CABIN	INTERFERENCE    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1564A	333  				CE1321				GEAR REMAINS DOWN WHEN GEAR HANDLE IS SELECTED FOR GEAR UP.  MAINTENANCE TECH TROUBLESHOOT GEAR SYS AND FOUND THAT THE D	YNAMIC RELAY WAS INTERMITTENT.  NO RECOMMENDATION AT THIS TIME.  DYNAMIC RELAY MFD 0445. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072200215	20050722	00215	GL  	2005	7	22	2005FA0000985    	1	20050701	G	8011		STARTER         			STNSON	10    	10STNSON    	8632004	GL  	FRNKLN	6A4165	6A4165*     	27025	EA  					ENGIEN	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	944C					1083944				THIS STARTER MOTOR REPORTED TO BE INOPERATIVE.  PLACED IN SERVICE 3/1/2005.  REMOVED FROM SERVICE 6/16/2005.						1	H	7	1 	3O	3	O		A709    	E238				 
2005072200220	20050722	00220	EA  	2005	7	22	2005FA0000986    	2	20050628	G	7322	272	CARBURETOR      			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	MALFUNCTIONED   	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	29530					17700944				CUSTOMER REPORTS THAT ENGINE QUIT ON FINAL.  ON THE GROUND PILOT WITNESSED GAS POURING OUT FROM BOTTOM OF COWL.  (K)						1	H	7	1 	3O	3	O	NT	A13CE   	E274				 
2005072200216	20050722	00216	NE  	2005	7	22	2005FA0000988    	2	20050722	G	7210	70BM055420	MODULE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	MAKING METAL    	B			HXSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	802TH	2211 				9023				PILOT REPORTED ENGINE CHIP LIGHT ON HIS WAY TO HANGAR.  MECHANIC DID THE INSPECTIONS IAW MFG MM AND FOUND A SMALL SINGLE	 FLAKE ON THE ELECTRIC MAG PLUG WHICH MONITORS THE REAR BEARING OIL RETURN LINE.  MECHANIC ALSO THEN FOUND MULTIPLE FLAK	ES OF PLATEING ON THIS CHIP PLUG.  REMOVED THE (ENGINE SN9695) AND INSTALLED (ENGINE SN 9120).  SENT ENGINE FOR EVALUATI	ON AND REPAIR.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005072200221	20050722	00221	EU  	2005	7	22	2005FA0000989    	1	20050606	G	7931	APTE176S150G	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL PRESSURE	FAILED          	B			HXSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	6080R					2685				AIRCRAFT WAS LIFTING OFF FOR A STANDARD TOUR AND THEN REPORTED A LOSS OF OIL PRESSURE.  THE PILOT THEN RETURNED TO BASE 	WITH NO TROUBLE AND REPORTED TO MAINTENANCE.  MECHANIC FOUND THAT THE OIL PRESSURE SENSOR HAD FAILED AND REPLACED PART. 	 AIRCRAFT HAS BEEN RETURNED TO SERVICE. (K)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005072200222	20050722	00222	GL  	2005	7	22	2005FA0000991    	1	20050630	G	5740		ATTACH ANGLE    			NAMER 	T6    	AT6C        	6400412	GL  	PWA   	R1340 	R1340*      	52016	NE  					WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	7678Z					889156				WING ATTACH ANGLE, CRACKING BETWEEN ROWS OF FASTENERS.  (K)						1	L	7	1 	3R	3	R		A2575   	5E2				 
2005072200226	20050722	00226	GL  	2005	7	22	2005FA0000992    	1	20050722	G	5740		ATTACH ANGLE    			NAMER 	T6    	AT6D        	6400416	GL  	PWA   	R1340 	R1340*      	52016	NE  					LT WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	7621Z					8815945				WING ATTACH ANGLE, CORROSION WITH LINEAR INDICATIONS.  (K)						1	L	7	1 	3R	3	R		A2575   	5E2				 
2005072500001	20050725	00001	GL  	2005	7	25	2005FA0000993    	1	20050630	G	5740		ATTACH ANGLE    			NAMER 	T6    	SNJ2        	6400404	GL  	PWA   	R1340 	S1H1        	52016	NE  					LT WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	40HS					2027				WING ATTACH ANGLE, CORROSION WITH LINEAR INDICATIONS.  (K)						1	L	7	1 	3R	3	R		A2575   	E129				 
2005072500003	20050725	00003	CE  	2005	7	25	2005FA0000994    	1	20050609	G	2820	530010841	LINE            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					FUEL CROSSFEED	CORRODED        	B			CTUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	98560	5593 				340A0032				DURING ANNUAL INSPECTION FOUND FUEL STAINS ON CROSSFEED LINE UNDER CABIN FLOOR PANEL.  FOUND CROSSFEED LINE CORRODED THR	OUGH.  LINE WAS LEAKING AT A CORRODED AREA.  THERE WAS NOTHING TOUCHING FUEL LINE.  (GL21200502745) (K)					1	L	7	2 	3O	3	O		3A25    	E8CE				 
2005072500006	20050725	00006	SO  	2005	7	25	2005FA0000995    	1	20050624	G	5514	1159CS2000013	ANGLE           			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					HORIZONTAL STAB	CORRODED        	B			LS3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	723MM					357				DURING REPLACEMENT OF AFT TAIL COMPT BULKHEAD CAP-ANGLE, HORIZ AND VERT STABILIZERS REQUIRED REMOVAL.  AFTER REMOVAL, TE	CH FOUND RECENT REPAIR ACCOMPLISHED BY 3RD PARTY REPAIR STATION HAD NUMEROUS ISSUES.  REPAIR WAS ACCOMPLISHED, DUE TO FI	NDING CORROSION DURING 24 MONTH INSPECTION.  STEEL STRAPS WERE REPLACED.  FOUND FOLLOWING DISCREPANCIES:  BETWEEN STA 0 	TO 80.81 ON LT, RT LEADING EDGES.  FOUND 200+ FASTENERS.  MUCH SOFTER FASTENER AND IS NOT APPROVED FOR THIS INSTALLATION	.  CORROSION/RUST ON STEEL STRAPS, LT AND RT TOP SKIN-114 INCORRECT FASTENERS EACH SIDE.  AFT SPAR-60 INCORRECT FASTENER	S.  CTR SECTION UNDER FAIRING WHERE STRAPS OVERLAP-110 INCORRECT FASTENERS.  CORROSION FOUND ON STEEL STRAP IN PANEL.	2	L	7	2 	4F	4	F		A12EA   	E2EU				 
2005072500004	20050725	00004	CE  	2005	7	25	2005FA0000996    	1	20050627	G	8011		PINION GEAR     	LAMAR       		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					STARTER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	510LP				85041608	172S9510				THIS STARTER PINION GEAR FAILED.  PIECES OF THE GEAR JAMMED THE STARTER MOTOR AND DAMAGED THE RING GEAR.  THIS IS THE SE	COND OCCURRENCE OF THIS INCIDENT ON THIS AIRCRAFT.  MFG MENTIONED THAT THERE HAS BEEN PROBLEM IN PAST.  IN ALL CASES BUT	 THIS LAST ONE, TEETH HAVE BEEN BROKEN OFF OF THE RING GEAR.  THE CURRENT INCIDENT HAS ONLY DAMAGED THE RING GEAR TEETH.	  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005072500007	20050725	00007	CE  	2005	7	25	2005FA0000997    	1	20050624	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DYNAMIC BRAKE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5540P	414  				CE1335				DURING GEAR EXTENSION, GEAR DID NOT EXTEND.  TROUBLESHOOTING SYSTEM FOUND DYNAMIC RELAY, DOWN SIDE OF RELAY TO RELEASE A	ND ALLOW GEAR TO EXTEND DOWN.  PROBABLE CAUSE IS STICKING DOWN RELAY MODULE RETURNED TO MFG FOR ANALYSIS.  RECOMMENDATIO	N IS FOR MFG TO DEVELOP AN IMPROVED PRODUCT.  MFD 0425. (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072500023	20050725	00023	CE  	2005	7	25	2005FA0000998    	1	20050623	G	5553	3364000039	FITTING         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					VERTICAL STAB	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5544A	18044				CE1343				WHILE PERFORMING UNSCHEDULED MAINTENANCE, VERTICAL STABILIZER WAS REMOVED, WHILE THE MECHANIC WAS INSPECTING THE FITTING	S FOR REINSTALLATION OF THE VERTICAL STABILIZER NOTICED A CRACK COMING FROM BOTTOM RT LOWER MOUNTING HOLE ON FORWARD FIT	TING.  AT THIS TIME NO PROBABLE CAUSE OR RECOMMENDATION.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072500024	20050725	00024	SO  	2005	7	25	2005FA0000999    	2	20050601	G	8530	CCST712BCA	CYLINDER HEAD   			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	7235F	1156 				21063038	236433R			NR 2 CYLINDER HEAD SEPARATED FROM BARREL.  OCURRENCE OCCURRED DURING DEPARTURE FROM AIRPORT, ENROUTE.  PROBABLE CAUSE IS	 WORN CYLINDER OR POSSIBLE OVERBOOST.  RECOMMEND WHEN PERFORMING COMPRESSION TEST THAT YOU PRESSURIZE AND SOAP CYLINDER 	AT BARREL AND HEAD ASSEMBLY.  (CE03200509143)				1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005072500009	20050725	00009	CE  	2005	7	25	2005FA0001000    	1	20050606	G	5754	10112012341	SKIN            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LT WING LE	DELAMINATED     	B			LX5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	991LL	4190 				FL142				DURING A POST FLIGHT CHECK, A MECHANIC NOTICED A BULGE ON THE UNDERSIDE OF THE IB LEADING EDGE OF THE LT WING.  UPON FUR	THER INVESTIGATION, A DELAMINATION AREA OF APPROXIMATELY 22 INCHES X 10 INCHES WAS FOUND.  AFTER REMOVAL OF THE LEADING 	EDGE AND CLOSER  EXAMINATION THE DELAMINATION WAS CONTAINED WITHIN THE EXHAUST GAS FLOW PATH FROM THE LT ENGINE IB EXHAU	ST STACK.  AFTER CONTACTING MFG, IT WAS DETERMINED THAT THE PART WAS NOT REPAIRABLE AND THE PART MUST BE REPLACED.  (GL1	9200504135)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005072500032	20050725	00032	SO  	2005	7	25	2005FA0001001    	1	20050621	G	2720	62701100	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					RUDDER	WORN            	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	4149G					2843191				LT FORWARD RUDDER CABLE WORN AT FAIRLEAD PASSING THROUGH CENTER WING SPAR AT FS 108.17.  THE CABLE BECAME WORN DUE TO CO	NTINUOUS CHAFING ON THE PHENOLIC FAIRLEAD.  THE CABLE IS NOT CENTER IN THE FAIRLEAD OPENING EITHER THROUGH IMPROPER POSI	TIONING OF THE FAIRLEAD OR FROM IMPROPER POSITIONING OF THE PULLEY QUADRANTS DURING AIRCRAFT ASSEMBLY.  THE REMEDY FOR T	HIS DEFECT WOULD BE TO INCREASE THE OPENING BY WHICH THE CABLE PASSES THROUGH THEREBY ALLOWING SUFFICIENT CLEARANCE FOR 	THE CABLE AND ELIMINATE CHAFING.  (K)		1	L	7	1 	3O	3	O		2A13    	E286				 
2005072500028	20050725	00028	SO  	2005	7	25	2005FA0001002    	1	20050621	G	2710	62701099	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					AILERONS	WORN            	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	4149G					2843191				LT AND RT PRIMARY AILERON CABLES SEVERELY WORN AT WING PULLEYS LOCATED AT WS 49.25.  CABLES HAVE APPROXIMATELY 4725.4 TT	.  THIS DEFECT IS NOT A RESULT OF BINDING PULLEYS BUT MOST PROBABLY DUE TO SUB-STANDARD CABLE USED DURING MFG, SPECIFICA	LLY STAINLESS STEEL CABLE.  ALTHOUGH SB 1048 IS ACCOMPLISHED AT EACH 100 HOUR AND ANNUAL INSPECTION, IT BY NO MEANS SOLV	ES THIS PROBLEM.  IT WOULD BE RECOMMENDED THAT ALL STAINLESS STEEL CABLES BE ELIMINATED AND GALVANIZED STEEL CABLES BE I	NSTALLED.  (K)		1	L	7	1 	3O	3	O		2A13    	E286				 
2005072500029	20050725	00029	EA  	2005	7	25	2005FA0001003    	1	20050706	G	2121	2651601	FAN             			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					TRU COOLING	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	25	779AZ				5141	5176				DURING OPS CHECK OF TRANSFORMER RECTIFIER SYSTEM, IT WAS NOTICED THAT THERE WAS NO AIRFLOW FROM THE INTERNAL COOLING FAN	.  REMOVED AND REPLACED COOLING FAN ASSEMBLY WITH NEW AND IMPROVED UNIT.  THERE WAS NO NOTIFICATION TO THE FLIGHT CREW T	HAT THIS FAN HAD FAILED.  (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005072500010	20050725	00010	CE  	2005	7	25	2005FA0001004    	1	20050705	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BREAKER	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1556A	222  				CE1318				ON ROUTINE PHASE INSPECTION, THE MECHANIC PUT THE GEAR DOWN AND NOTHING HAPPENED.  ON TROUBLESHOOTING, THE MECHANIC FOUN	D THE RELAY WAS INTERMITTENT, PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072500034	20050725	00034		2005	7	25	2005FA0001005    	4	20050629	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	796WW	296  				172S8635				DURING ANNUAL INSPECTION THE FORWARD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AROUND 5 OF THE SIX BOLT HOLES.  THINK THA	T THE CAUSE OF THE PROBLEM IS THAT WHEN THE PROP MOUNTING BOLTS ARE TORQUED TO THE LIMITS GIVEN IN THE SRM THAT THE FORW	ARD BULKHEAD GET PULLED DOWN SLIGHTLY INTO THE CHAMFER OF THE PROP BOLT HOLES AND THIS IN TURN STRESS THE PART LEADING T	O CRACKING.  TO SOLVE THIS PROBLEM, THINK THAT THE POSSIBILITY OF DIMPLING OF THE BOLT HOLES MIGHT CORRECT THE CRACKING.	  (K)		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005072500030	20050725	00030		2005	7	25	2005FA0001006    	4	20050630	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	154ME	187  				172S8534				DURING 100 HR INSPECTION THE FORWARD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AROUND ALL SIX (6) BOLT HOLES.  THINK THAT	 THE CAUSE OF THE PROBLEM IS THAT WHEN THE PROP MOUNTING BOLTS ARE TORQUED TO THE LIMITS GIVEN IN THE SRM AND THAT THE F	ORWARD BULKHEAD GETS PULLED DOWN SLIGHTLY INTO THE CHAMFER OF THE PROP BOLT HOLES AND THIS IN TURN STRESSES THE PART LEA	DING TO CRACKING.  TO SOLVE THIS PROBLEM, THINK THAT THE TORQUE OF THE MOUNTING BOLTS AND THE DESIGN OF THE BULKHEAD NEE	D TO BE EVALUATED AND CHANGES MADE.  ANOTHER SOLUTION MIGHT BE TO ADD A PLATE OVER THE MOUNTING AREA MUCH LIKE THE ONE R	EQUIRED FOR SOME 152 PROP INSTALLATIONS TO ALLOW THE STRESS FROM THE MOUNTING BOLTS TO BE MORE EVENLY DISTRIBUTED.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005072500031	20050725	00031	EA  	2005	7	25	2005FA0001007    	1	20050712	G	5711		SPAR CAP        			DHAV  	DHC6  	DHC6300     	2802606	EA  										LT WING	DAMAGED         	B			JRPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	8PMLK	12456				477				SMOKING MS20470DD8 RIVETS OBSERVED AT WS122  - 140 PROX DURING SCHEDULED INSPECTION.  THESE RIVETS ARE CRITICAL TO WING 	INTEGRITY.  IT APPEARS THAT THE RIVETS DID NOT PROPERLY ENGAGE THE HOLE DURING OEM INSTALLATION.  SUGGEST ALL WING BOXES	 WITHIN 10 SERIAL NUMBER RANGE BE CLOSELY INSPECTED FOR SAME.  NOTE: MFG DATES FOR THE IDENTIFIED WING BOXES ARE MAY 199	5 IN ALL CASES. (K)			1	H	7	2 	3T			RT	A9EA    					 
2005072500027	20050725	00027	CE  	2005	7	25	2005FA0001008    	1	20050722	G	3233	12802412	PISTON ROD      	CESSNA      		CESSNA	182   	R182        	2072734	CE  										NLG ACTUATOR	WORN            	B				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			WP	07	2253T	3958 				R18200008				NOSE GEAR ACTUATOR FOUND LEAKING DURING PREFLIGHT.  MAINTENANCE DISASSEMBLED AND FOUND A GROOVE AROUND THE PISTON ROD (P	/N 1280241-2) WHERE THE 'O'RING AND BACKUP RINGS RIDE.  REPLACED PISTON ROD ASSEMBLY, INSTALLED NEW SEALS.  RE-RIGGED GE	AR AND RELEASED A/C.				1	H	7	1 	3O			RT	3A13    					 
2005072500057	20050725	00057	CE  	2005	7	25	2005FA0001009    	1	20050701	G	2750		BELLCRANK       			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540*      	41532	EA  					TE FLAPS	BINDING         	B			YEBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	239LF	5    				20608239	L30392			BINDING IN FLAP DR SYS AT BELLCRANKS WHERE ROD ENDS ATTACH.  FLAP DR RODENDS WERE FOUND DIGGING INTO BELLCRANK ARMS AS T	HEY OPERATED, NML TRAVEL AS SHOWN BY RUB MARKS ON RODENDS.  BELLCRANK ARMS, EXCESS CLAMPED BY RODEND ATTACH BOLTS, SOME 	BOLTS NOT TIGHTENED SECURELY LEAVING ROD END TO MOVE UP AND DOWN ON BOLT SHANK.  WASHERS WERE INSTALLED BETWEEN RODEND B	RG, BELLCRANK TO RELIEVE CLAMPING STRAIN ON ARMS, PROVIDE CLEARANCE FOR RODENDS TO OPERATE W/O BINDING ON ARMS.  INTERCO	NNECT RODENDS WERE FOUND BINDING AT END OF TRAVEL IN DWN POSITION. BELLCRANK ANGLE DURING RIGGING, ADJUSTING RIGGING TO 	CLOCK BELLCRANK TRAVEL INTO USEABLE ARC THAT PREVENTS BINDING AT ENDS OF ITS RANGE WILL HELP PREVENT FURTHER DAMAGE. (K)	1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2005072500061	20050725	00061	SO  	2005	7	25	2005FA0001010    	2	20050610	G	7414	M3081	POINTS          	SLICK       		PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					MAGNETO	BROKEN          	B			GB7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	818JP	300  			01120433	468408047	528395			CONTACT SPRING BROKEN IN 300.7 HRS OF OPERATION.  (K)						1	L	7	1 	3O	3	O	RT	A25SO   	E8CE				 
2005072500054	20050725	00054	SO  	2005	7	25	2005FA0001011    	2	20050610	G	7414	M3081	POINTS          	SLICK       		PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					MAGNETO	BROKEN          	B			GB7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	818JP	311  			01120434	468408047	528395			CONTACT SPRING BROKNE IN 311.1 HOURS OF OPERATION.  (K)						1	L	7	1 	3O	3	O	RT	A25SO   	E8CE				 
2005072500062	20050725	00062	SO  	2005	7	25	2005FA0001012    	2	20050617	G	8530		CYLINDER HEAD   			CESSNA	210   	210D        	2073414	CE  	CONT  	O520  	IO520A      	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	210AW	71   				21058492	1105724A			ENGINE WITH 450.0 TIS AND CYLINDER NR 2 WITH THE SAME TIS, BUT 31.0 HOURS SINCE REMOVAL/REPAIR/REINSTALLATION.  DURING C	RUISE FLIGHT, ENG BECAME VERY ROUGH WITH LOSS OF POWER.  NORMAL LANDING WAS MADE.  UPON INSP OF ENG, FOUND NR 2 CYL (COL	D).  PERFORMED COMPRESSION CHECK, NR 2 CYL HAD NO COMPRESSION.  BOROSCOPED CYL AND FOUND CRACK PRESENT IN THE ALUMINUM C	YL HEAD APPROX CENTERED ON EXHAUST VALVE SEAT AND EXTENDING IN CIRCULAR PATTERN, 2 PLUS INCHES IN EITHER DIRECTION.  AFT	 END SEEMED TO RELIEVE ITSELF ON EDGE OF LWR SPARK PLUG BOSS (LWR SPARK PLUG HAD NO TORQUE WHAT SO EVER).  THERE WAS A H	OLE (.25 INCH WIDE X .375 INCH LONG) ON FWD END OF CRACK WITH EXHAUST GASES/DEPOSITS PRESENT ON CYL COOLING FINS.  (K)	1	H	7	1 	3O	3	O		3A21    	E5CE				 
2005072500063	20050725	00063	EU  	2005	7	25	2005FA0001013    	1	20050701	G	5751	10425002	PLATE           			AVIAT 	S1S   	PITTSS1S    	72206BW	EU  										AILERON	BROKEN          	B			LQJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	04	CGZRO	800  				1024				AT APPROX 200 MPH, LT AILERON SPADE PLATE FRONT ATTACH POINT BROKE, ALLOWING SPADE PLATE TO PIVOT DOWNWARD TO A FULL VER	TICAL POSITION WHERE IT STAYED UNTIL LANDING.  PHOTO EVIDENCE ATTACHED SHOWS SIGNS OF PREVIOUS CRACKING AS SHOWN BY RUST	.  QUESTIONS ARISE AT AN ADEQUATE PREFLIGHT CHECK BEFORE FAILURE.  INDICATIONS OF AEROBATIC MANEUVERS (SNAP ROLLS) IN EX	CESS OF RECOMMENDED LIMITS.  A DAILY AND ANNUAL INSPECTION OF THE SPADE ASSEMBLIES WILL BE ADDED TO THE MM. (K)			1	Q	7	1 	3O			NC	A8SO    					 
2005072500070	20050725	00070		2005	7	25	2005FA0001015    	4	20050517	G	3100	31004562801	LOGIC CARD      			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					IDU TRAY	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	7333L					347670099				SCC CARD INSTALLED AS PART OF THE EFIS-SV SYSTEM IAW STC NR SA02203AK WOULD NOT ALLOW THE MOVING MAP PAGE TO APPEAR ON T	HE IDU DURING START UP.  (ALO5200502600) (K)					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005072500064	20050725	00064		2005	7	25	2005FA0001016    	4	20050611	G	3160	4300270502	DISPLAY         			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470*      	17026	SO  					COCKPIT	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	3715Y					21058215				DURING GROUND FUNCTIONAL CHECKS FOLLOWING INITIAL INSTALLATION FOUND THE MX20 MULTIFUNCTION DISPLAY WOULD NOT ACCEPT DAT	A FROM THE GNS480.  ADDITIONALLY, THE MX20 HAD NO MAP DISPLAY UPON GPS ACQUISITION.  (AL05200502601) (K)					1	H	7	1 	3O	3	O		3A21    	E1CE				 
2005072500071	20050725	00071		2005	7	25	2005FA0001017    	4	20050507	G	3160	4306081100000	TRANSCEIVER     			CASA  	C212  	C212200     	2410304	EU  	GARRTT	TPE331	TPE331*     	01514	WP  					COCKPIT	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	287MA					287				DURING INITIAL INSTALLATION FOUND THE LOCKING HOLE ON THE RADIO WAS DAMAGED, NOT ALLOWING THE UNIT TO SEAT IN THE TRAY P	ROPERLY.  UNIT WAS REPLACED. (AL200502602) (K)					2	H	7	2 	4T	3	T	RT	A43EU   	E2WE				 
2005072500065	20050725	00065		2005	7	25	2005FA0001018    	4	20050405	G	3100	4306081100000	TRANSCEIVER     			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	7394U					20700437				DURING INITIAL PROGRAMMING FOLLOWING INITIAL INSTALLATION, FOUND THE APM WOULD NOT PROGRAM.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072500069	20050725	00069		2005	7	25	2005FA0001019    	4	20050407	G	3160	4306081100000	TRANSCEIVER     			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	MALFUNCTIONED   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	5277J					20700772				DURING GROUND FUNCTIONAL CHECKS FOLLOWING INITIAL INSTALLATION, MX20 DISPLAYS THE ERROR MESSAGE (GDL90 REQUIRES MAINTENA	NCE).  UPON INSTALLATION OF ANOTHER UNIT, ERROR MESSAGE CLEARED, SYSTEM OPERATION SATISFACTORY.  (AL05200502604) (K)					1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072500074	20050725	00074		2005	7	25	2005FA0001020    	4	20050404	G	3160	5900051	ANTENNA         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520*      	17032	SO  					UAT	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	1673U					20700273				DURING UPGRADE OF UAT, FOUND LOWER UAT ANTENNA UNSERVICEABLE.  (ALO5200502605) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600085	20050726	00085		2005	7	26	2005FA0001021    	4	20050423	G	3160	5900051	ANTENNA         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	1453V					17263590				DURING UPGRADE OF UAT, FOUND UPPER UAT ANTENNA UNSERVICEABLE.  (ALO5200502606) (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005072600095	20050726	00095		2005	7	26	2005FA0001022    	4	20050421	G	3160	5900051	ANTENNA         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	91099					20700073				DURING UPGRADE OF UAT, FOUND LOWER UAT ANTENNA UNSERVICEABLE.  (AL05200502607) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600096	20050726	00096		2005	7	26	2005FA0001023    	4	20050421	G	3160	5900051	ANTENNA         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	91002					20700003				DURING UPGRADE OF UAT, FOUND UPPER UAT ANTENNA UNSERVICEABLE.  (AL05200502608) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600099	20050726	00099		2005	7	26	2005FA0001024    	4	20050429	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	73067					20700558				FOUND UAT ANTENNA BAD DURING UAT UPGRADE.  (ALO5200502609) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072500076	20050725	00076		2005	7	25	2005FA0001025    	4	20050426	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					UAT	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9869M					20700744				FOUND LOWER UAT ANTENNA BAD DURING UAT UPGRADE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600070	20050726	00070		2005	7	26	2005FA0001026    	4	20050423	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	7384U					20700431				FOUND LOWER UAT ANTENNA BAD DURING UAT UPGRADE.  (AL05200502611) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600086	20050726	00086		2005	7	26	2005FA0001028    	4	20050424	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					FUSELAGE	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9399M					20700652				FOUND LOWER UAT ANTENNA BAD DURING UAT UPGRADE.  (AL05200502613) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600087	20050726	00087		2005	7	26	2005FA0001029    	4	20050329	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	UNSERVICEABLE   	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	7320U					20700397				FOUND LOWER UAT ANTENNA BAD DURING UAT UPGRADE.  (AL05200502614) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600082	20050726	00082		2005	7	26	2005FA0001032    	4	20050419	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9728M					20700721				DURING UPGRADE OF UAT FOUND BOTH UAT ANTENNAS UNSERVIEABLE.  (AL05200502617) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600101	20050726	00101		2005	7	26	2005FA0001033    	4	20050412	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9728M					20700721				DURING UPGRADE OF UAT FOUND BOTH UAT ANTENNAS UNSERVICEABLE.  (AL05200502618) (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072600017	20050726	00017	SO  	2005	7	26	2005FA0001034    	1	20050611	G	3260	920070	PROXIMITY SWITCH			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					MLG	LOOSE           	B			ZLWR	A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			SW	05	900DH					111				AC DEPARTED FOR 3 DAY TRIP.  AC MADE A STOP TO PICK UP 1 PASSENGER, THEN TOOK OFF AND HEADED TO PICK UP ANOTHER PASSENGE	R.  ON EXTENDING THE GEAR, LT GEAR DOWN AND LOCKED LIGHT FAILED TO LITE.  CREW TRIED 6 TIMES BY RETRACTING AND EXTENDING	 GEAR TO NO AVIAL.  CREW THEN BLEW GEAR DOWN WITH EMERGENCY EXTENSION SYS., STILL NO LIGHT.  PERFORMED A LOW AND SLOW PA	ST TOWER TO CONFIRM GEAR WAS DOWN, PROCEEDED TO LAND WITHOUT INCIDENT.  PIC CALLED AND SAID THAT THERE WAS A CONNECTOR P	LUG LOOSE IN THE LT WHEEL WELL.  THE PLUG WAS REATTACHED, GEAR PINNED IN THE DOWN AND LOCKED POSITION, DEPLOY HANDLE AND	 D-RING STOWED.  AC WAS FLOWN BACK ON FERRY PERMIT WITH THE GEAR DOWN AND LOCKED.  GEAR WAS SWUNG IAW MM.  (K)	2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2005072600025	20050726	00025	CE  	2005	7	26	2005FA0001035    	1	20050602	G	5340	6805101A	MOUNT BRACKET   			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8419Q	280  				U20603279				DURING A 100 HOUR INSPECTION, FOUND THE MOUNT FOR THE FUEL FLOW TRANSDUCER CRACKED AT THE BEND RADIUS OF ALL 4 MOUNTING 	FLANGES.  (K)					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005072600023	20050726	00023	CE  	2005	7	26	2005FA0001036    	1	20050331	G	5340		BRACKET         			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					WING TO FUSELAGE	WORN            	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	6NR					258701				WHILE FLYING THROUGH TURBULENCE SITTING IN THE VIP CHAIR (CABIN RT FWD FACING) A SLIGHT VIBRATION CAN BE FELT COMING THR	OUGH THE FLOOR AND WILL DIMINISH AFTER LEAVING TURBULENCE.  AFTER TALKING WITH MFG TECH SUPPORT, THIS PROBLEM IS COME TO	 BE KNOWN AS (WING CLUNK).  IT IS CAUSED BY THE PLAY IN THE BRACKET VERTICAL LINK SPHERICAL BEARING AND ATTACH BOLT, IE 	ONE OR ALL.  THERE IS NO SB, IL, COMMUNIQU OUT ON THIS PROBLEM BUT MFG IS AWARE AND HAS A REPAIR KIT OUT THAT ONLY CAN 	BE DONE AT MFG SERVICE CENTER.  (GL13200508700) (K)		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005072600044	20050726	00044	EU  	2005	7	26	2005FA0001037    	1	20050323	G	7720	704A37642043	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101*     		NE  					ENGINE	FAILED          	D			C33R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	209CH	32   				2494				TRANS-PRESS FAILED AFTER A FEW HOURS OF OPERATION.  (K)						1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2005072600045	20050726	00045	EU  	2005	7	26	2005FA0001038    	1	20050725	G	5210		SLIDE           	KAWSKI      		BOLKMS	117   	BK117B2     	5626013	EU  										CABIN DOOR	WORN            	E				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			LD	LANDING        	1			SW	09	440HH	7923 	313  			7238				ON FINAL APPROACH TO LANDING, AT 55 KTS AIRSPEED, THE PILOT GAVE PERMISSION FOR THE MEDICAL CREW TO OPEN DOORS.  THE PAR	AMEDIC (IN THE RT SEAT) OPENED HIS DOOR.  THE NURSE (IN THE LT SEAT) OPERATED THE DOOR LATCH AND BEGAN TO SLIDE THE DOOR	 OPEN.  THE DOOR DEPARTED THE HELICOPTER AND FLEW THROUGH THE MAIN ROTOR SYSTEM AND WAS DESTROYED.INVESTIGATION REVEALED	 WORN FORWARD SLIDER, P/N T6408-103, WORN UPPER DOOR RAIL, P/N 117-24271-01, AND WORN LOWER RAIL, P/N 117-24283-03, COMB	INED TO LET LOWER DOOR GUIDES POP OFF THE RAIL.  THE WIND THEN CAUGHT THE DOOR ABD BLEW IT OFF OF THE TOP RAIL, DEFORMIN	G THE RAIL SUBSTANTIALLY.	1	G	7	2 	3U			NC	H13EU   					 
2005072600158	20050726	00158	NM  	2005	7	26	2005FA0001040    	1	20050623	G	2782	111015	PISTON          	SMITHSIND   		BOEING	727   	727*        	       	NM  										ACTUATOR	BROKEN          	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					4251ADE					PISTON BROKE AT THE KEY GROVE, FATIGUE.  (196962/FXS) (K)						2	L	7	3 	4F			RT	A3WE    					 
2005072600161	20050726	00161	EA  	2005	7	26	2005FA0001041    	2	20050701	G	8530	3813	STUD            			AMTR  	SKYBLT	SKYBOLT     	       	GL  	LYC   	O540  	IO540C4B5   	41532	EA  					NR 3 CYLINDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	25KC					2	L90040			AC WAS ENROUTE WHEN PILOT HEAR (PUFF) NOISE AND SAW OIL BEGINNING TO COME FROM ENGINE COMPARTMENT.  HE THROTTLED BACK AN	D DID A PRECAUTIONARY LANDING AT THE NEAREST AIRPORT.  THROTTLED BACK AND DID A PRECAUTIONARY LANDING.  UPON INSPECTION 	IT WAS FOUND THAT 4 OF 8, NR 3 CYL BASE NUT STUDS (2 EA PN 3813, 2 EA PN 5015) HAD BROKEN OFF ABOUT EVEN WITH HEIGHT OF 	CYLINDER BASE FLANGE.  APPROX 90 PERCENT OF REMAINING CYL BASE NUTS ON ENTIRE ENG WERE FINGER LOOSE.  CASE AND CYLINDER 	WERE NDT AND NO CRACKS WERE FOUND.  NEW STUDS AND NUTS WERE INSTALLED AT FAILED LOCATION, ALL CYL BASE NUTS WERE TORQUED	 IAW MM.  SUSPECT CYL BASE NUTS WERE NOT PROPERLY TORQUED OR PROPER TORQUING SEQUENCE WAS NOT UTILIZED AT OVERHAUL. (K)	1	Q	7	1 	3O	3	O		EXPA1Q71	1E4				 
2005072600167	20050726	00167	SO  	2005	7	26	2005FA0001042    	1	20050708	G	7110	631996	RETAINER        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360KB  	17025	SO  					COWLING	CRACKED         	B			FMOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	6085A		230  			3448021	319073			PILOT REPORTED, AFTER LANDING, HE DISCOVERED OIL ALL OVER THE RT COWLING AND UNDER THE WING BEHIND THE RT ENGINE.  COWLI	NG WAS REMOVED AND A HOLE WAS FOUND IN THE NR 5 CYL INTAKE VALVE COVER.  VALVE COVER WAS REMOVED AND FOUND THAT ROCKER R	ETAINER HAD BROKEN IN HALF.  HALF OF RETAINER WAS STILL CAPTURED BY NUT AND REMAINED IN PLACE.  OTHER HALF HAD FALLEN AW	AY AND BECAME WEDGED BETWEEN ROCKER ARM AND VALVE COVER CAUSING THE HOLE IN THE COVER.  CLY NR 1 INTAKE VALVE RETAINER W	AS FOUND TO BE CRACKED.  REMAINTING ARMS AND RETAINERS WERE INSPECTED ON BOTH ENGINES.  TWO BROKEN RETAINERS, NEW ROCKER	 ARM AND PIN FOR CYL NR 5 WERE REPLACED.  AC THEN RETURNED TO SERVICE.  PROBABLE CAUSE, OVER TORQUED AT O/H. (K)	1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005072600212	20050726	00212	CE  	2005	7	26	2005FA0001043    	1	20050718	G	3233	EA1614	ACTUATOR        			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470*      	17026	SO  					RT MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	3695Y	4276 				21058195				GEAR ACTUATOR WAS FOUND TO BE SPLIT DOWN THE SIDE AND THE TOP HAD BROKEN INTO TWO PIECES.  THE PILOT REPORTED HEARING A 	LOUD POP DURING THE GEAR CYCLE.  THE EMERGENCY HAND PUMP WAS USELESS DUE TO THIS PROBLEM.  THE AIRCRAFT MADE A SAFE LAND	ING AFTER A GROUND CREW PULLED THE GEAR DOWN WHILE THE PILOT FLEW DOWN THE RUNWAY.  (K)				1	H	7	1 	3O	3	O		3A21    	E1CE				 
2005072600219	20050726	00219	SW  	2005	7	26	2005FA0001044    	1	20050714	G	2800	512509	GASCOLATOR      			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					FUEL SYSTEM	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	10368	265  				290286	684961			DURING TROUBLESHOOTING, IT WAS DISCOVERED THAT THE GASCOLATOR WAS ALLOWING AIR TO BE INTRODUED INTO THE SHIPS FUEL SYSTE	M PRIOR TO THE FUEL REACHING THE ENGINE DRIVEN FUEL PUMP.  INSTALLING A NEW GASCOLATOR RESOLVED THE PROBLEM.  (K)					1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2005072600224	20050726	00224	SO  	2005	7	26	2005FA0001045    	1	20050708	G	7810	654326E	COLLECTOR RING  			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					ENGINE	DEFECTIVE       	B			ZKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	802SL					468508087	273841R			THIS IS THE COLLECTOR THAT MOUNTS TO THE TOP OF THE LT TURBO.  FOUND HOLES ON BOTH SIDES OF WELDS ON THE AFT END NEAR TH	E SMALL BALANCE TUBE.  (K)					1	L	7	1 	3O	3	O	RT	A25SO   	E8CE				 
2005072600241	20050726	00241	SO  	2005	7	26	2005FA0001046    	2	20050705	G	7414	4301	MAGNETO         			CESSNA	140   	140A        	2071604	CE  	CONT  	C90   	C9014F      	17009	SO  					ENGINE	DEFECTIVE       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	5380C	475  				15513				BOTH MAGS REMOVED FOR SB, 500 HOUR INSPECTION.  MFG DEFECT NOTED.  ROTATING MAGNET AND BEARING ASSY NOT PRESSED (FAR ENO	UGH) INTO FRONT MAG HOUSING .  MAGS PURCHASED NEW 1/9/98.  UNEVEN WAR NOTED THROUGHOUT WITH FINE BRONZE POWDER COATING I	NTERNAL PARTS.  OD (GREEN) IN COLOR.  MORE CAREFUL ASSEMBLY OF MAG COMPONENTS AT FACTORY.  (NOTE) MAG SN 14 UNITS APART.	  (K)			1	H	7	1 	3O	3	O		5A2     	E252				 
2005072600242	20050726	00242	GL  	2005	7	26	2005FA0001047    	1	20050707	G	3243		SHUTTLE VALVE   			AMTR  	KITFOX	KITFOX      	05613LZ	GL  	ROTAX 	      	ROTAX*      		EU  					MASTER CYLINDER	LOCKED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	316R					1561				FULL STOP LANDING, BRAKES LOCKED UP AND AIRCRAFT NOSED OVER, DAMAGING THE PROPELLER AND LOWER ENGINE COWLING.  MFG HAS I	SSUED SL NR 23 RE: SIMILAR OR SAME PROBLEM.  SOLUTION: RESTRICT BRAKE USE TO PILOT OR CO-PILOT ONLY OR REMOVE THE CO-PIL	OT PORTION OF THE SYSTEM URL.  (NM07200506922) (K)				1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
2005072600284	20050726	00284		2005	7	26	2005FA0001048    	1	20050715	G	3340	NLI707924	SOCKET          																	BEACON	MISMANUFACTURED 	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03					2173					DEFECT IS CAUSED BY IMPROPER CLOCKING OF BASE ON BULB GLASS DURING MANFACTURE.  IMPROPERLY MOUNTED BASE CAUSES INABILITY	 TO ACQUIRE THE CORRET FLASH RATE IN SIDE VIEW OF LAMP ASSY.  (K)																		 
2005072700053	20050727	00053	CE  	2005	7	27	2005FA0001049    	1	20050720	G	3220	NAS464P542	BOLT            			CESSNA	210   	T210H       	2073438	CE  										NLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	01	2234R					T2100384				AIRCRAFT EXPERIENCED A NOSE GEAR FAILURE/COLLAPSE DURING TAXI IMMEDIATELY FOLLOWING LANDING. EXAMINATION OF THE AIRCRAFT	 AT THE SCENE REVEALED  THAT  THE  NOSE GEAR ACTUATOR ASSEMBLY AFT  ATTACHMENT  BOLT  HAD FAILED.  THE HEAD OF THE BOLT 	HAD BROKEN OFF AND THE BOLT HAD SUBSEQUENTLY WORKED IT'S WAY OUT OF THE ATTACH FITTING ALLOWING THE ACTUATOR TO COME LOO	SE DURING TAXI AFTER LANDING. PHYSICAL INSPECTION OF THE BOLT FOUND EVIDENCE THAT  THE HEAD OF THE BOLT HAD MOST LIKELY 	BEEN SEPARATED FOR SOME TIME PRIOR TO THE INCIDENT.		1	H	7	1 	3O				3A21    					 
2005072700090	20050727	00090	CE  	2005	7	27	2005FA0001050    	1	20050707	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	6384V	8800 				172RG0647	L2896336A	010011		MLG ACTUATOR CRACKED. (K)						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2005072700122	20050727	00122	GL  	2005	7	27	2005FA0001051    	1	20050719	G	7120	RV6ADINA1KIT	MOUNT           			AMTR  	VANS  	VANSRV6A    	05610ZG	GL  	LYC   	O320  	O320D1A     	41508	EA  	SNSNCH	70C	70CM7       	EA  	ENGINE	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	6YE					3315	L1902039A	314881L		LOWER RT DIAGONAL ENGINE MOUNT TUBE FOUND CHAFED DO TO EXHAUST PIPE COMING INTO CONTACT WITH THE TUBE, THIS HAPPENED DO 	TO THE CLOSE PROXIMITY OF THE EXHAUST SYSTEM TO THE MOUNT.  CORRECTED BY REPOSITIONING EXHAUST SUPPORT CLAMPS.  WHILE RE	PAIRING THE CHAFED TUBE IT WAS NOTED THAT A SMALL CRACK WAS DEVELOPING IN A TUBE OFF THE END OF A GUSSET ADJACENT TO THE	 RT LOWER SHOCK MOUNT ATTACH POINT, THIS ALSO NEEDED REPAIR BY A WELDED SLEEVE ON THE TUBE, CAUSE UNKNOWN.  (GL132005089	90) (K)		1	L	7	1 	3O	3	O	RT	EXPA1L71	E274	5	N	P28NE	 
2005072700154	20050727	00154	WP  	2005	7	27	2005FA0001052    	1	20050710	G	6320	369D21500505	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	UNSERVICEABLE   	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGBUY	10061	774  			6110958D				DURING ROTATION OF THE M/R HUB WHILE PERFORMING ROUTINE MAINTENANCE A NOTICEABLE (SQUEAK) WAS HEARD COMING FROM THE M/R 	TRANSMISSION.  SUBSEQUENT INVESTIGATION ALLOWED FOR THE DISCOVERY OF THE INPUT PINION HAVING SIDE SLOPE AND THE SQUEAK W	AS HEARD WITH A LISTENING DEVICE INSIDE THE TRANS AND LEAD TO THE DISCOVERY OF THE LOWER CHIP PLUG HAVING A LOT OF METAL	 YET NONE HAD MADE CONTACT.  REMOVED TRANS, PULLED INPUT PINION AND IT AND THE BEVEL GEAR SPALLED.			1	G	7	1 	3U				H3WE    					 
2005072700156	20050727	00156	SO  	2005	7	27	2005FA0001053    	1	20050715	G	5343	9564309	ATTACH BRACKET  			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MLG	CRACKED         	B			OF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	3046U	11486				447995261				DURING INSP BOTH LT AND RT MAIN GEAR DRAG LINK ATTACH BRACKETS WERE REMOVED FOR BRG REPLACEMENT DUE TO EXCESSIVE FREEPLA	Y AT DRAGLINK IB ATTACH END.  UPON FURTHER CLEANING, PAINT RMVL AND INSP OF EACH, BOTH CASTINGS WERE FOUND CRACKED AROUN	D MACHINED FLAT SPOT AREA IN RADIUS OF ONE WEB OF CASTING FOR THE UPPER ATTACH BOLT HOLE.  ORDERED, INSPECTED AND REJECT	ED 4 PAIR OF SERVICEABLE REPLACEMENT PARTS FROM MULTIPLE VENDORS AFTER CLEANING AND INSP OF EACH DUE TO SIMILAR CRACKS I	N SAME AREA.  PROBABLE CAUSE: FROM CYCLES AND LOADING OF COMPONENT AND INACCESSABLILITY FOR ADEQUATE INSP WHILE INSTALLE	D.  SUSPECT ALL THESE CASTINGS SHOULD BE REQUIRED TO BE REMOVED, CLEANED, INSPECTED AT SOME REQUIRED INTERVAL.  (K)	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P25EA	 
2005072700187	20050727	00187		2005	7	27	2005FA0001054    	4	20050414	G	3160	5900051	ANTENNA         			CESSNA	207   	T207        	2073612	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					UAT	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	90193					20700007				FOUND UPPER UAT ANTENNA UNSERVICEABLE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E7CE				 
2005072700186	20050727	00186		2005	7	27	2005FA0001055    	4	20050423	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					UAT	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	6207H					20700551				FOUND LOWER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072700185	20050727	00185		2005	7	27	2005FA0001056    	4	20050429	G	3160	5900051	ANTENNA         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					UAT	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	1232Y					208B0566				FOUND LOWER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	H	7	1 	3T	4	T		A37CE   	E4EA				 
2005072700189	20050727	00189		2005	7	27	2005FA0001057    	4	20050429	G	3160	5900051	ANTENNA         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520*      	17032	SO  					UAT	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	23CF					20700276				FOUND LOWER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072800015	20050728	00015		2005	7	28	2005FA0001058    	4	20050429	G	3160	5900051	ANTENNA         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	23CF					20700276				FOUND UPPER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072800001	20050728	00001		2005	7	28	2005FA0001059    	4	20050429	G	3160	5900051	ANTENNA         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A45      	52043	EA  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	302EH					576				FOUND UPPER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005072800004	20050728	00004		2005	7	28	2005FA0001060    	4	20050427	G	3160	5900051	ANTENNA         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	3516A					317952106				FOUND UPPER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005072800005	20050728	00005		2005	7	28	2005FA0001061    	4	20050428	G	3160	5900051	ANTENNA         			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540*      	41532	EA  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8374T					328106058				FOUND LOWER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE. (K)						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2005072800006	20050728	00006		2005	7	28	2005FA0001062    	4	20050427	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9736M					20700722				FOUND UPPER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072800016	20050728	00016		2005	7	28	2005FA0001063    	4	20050421	G	3160	5900051	ANTENNA         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	7605U					20700443				FOUND UPPER UAT ANTENNA UNSERVICEABLE DURIN UAT UPGRADE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2005072800002	20050728	00002		2005	7	28	2005FA0001064    	4	20050505	G	3160	5900051	ANTENNA         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	20109					17261017				FOUND UPPER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE.   (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005072800007	20050728	00007		2005	7	28	2005FA0001065    	4	20050414	G	3160	5900051	ANTENNA         			CESSNA	207   	T207        	2073612	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					FUSELAGE	INOPERATIVE     	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	90193					20700007				FOUND UPPER UAT ANTENNA UNSERVICEABLE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E7CE				 
2005072800024	20050728	00024		2005	7	28	2005FA0001066    	1	20050728	G	2140	94E42	PRESSURE SWITCH 																	HEATER	FAILED          	B				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	99										DURING COMBUSTION HEATER PRESSURE DECAY TEST IAW AD2004-21-05, WE STILL TEST THE COMBUSTION AIR PRESSURE SWITCH WITH P/N	 94E42, AND FOUND THAT MOST OF THE TIMES THE SWITCH FAILED OR NEEDED ADJUSTMENT																		 
2005072800028	20050728	00028		2005	7	28	2005FA0001067    	1	20050728	G	2140	94E42	PRESSURE SWITCH 																	HEATER	FAILED          	B				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	99										DURING COMBUSTION HEATER PRESSURE DECAY TEST IAW AD2004-21-05, WE STILL TEST THE COMBUSTION AIR PRESSURE SWITCH WITH P/N	 94E42, AND FOUND THAT MOST OF THE TIMES THE SWITCH FAILED OR NEEDED ADJUSTMENT.																		 
2005072800029	20050728	00029		2005	7	28	2005FA0001068    	1	20050728	G	2140	94E42	PRESSURE SWITCH 																	HEATER	FAILED          	B				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	99										DURING COMBUSTION HEATER PRESSURE DECAY TEST I.A.W. AD2004-21-05, WE STILL TEST THE COMBUSTION AIR PRESSURE SWITCH WITH 	P/N 94E42, AND FOUND THAT MOST OF THE TIMES THE SWITCH FAILED OR NEEDED ADJUSTMENT.																		 
2005072900073	20050729	00073	CE  	2005	7	29	2005FA0001070    	1	20050623	G	7160	1250839	DOOR            			CESSNA	210   	T210F       	2073422	CE  	CONT  	O520  	TSIO520C    	17040	SO  					INDUCTION AIRBOX	FAILED          	B			KO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	6129R	121  				T2100029	178109R			INVESTIGATION OF LOW MANIFOLD PRESSURE BY TECH RVEALED THE STEEL TAB RIVETED TO ALTERNATE AIR DOOR FOR MAGNETIC CLOSURE 	HAD FALLEN OFF AND ENTERED TURBOCHARGER.  THE RIVETS USED TO FASTEN TAB TO DOOR WERE MISSING ALONG WITH THE TAB.  THE RI	VET HOLES LOOKED ELONGATED AND WERE POSSIBLY TOO LARGE AT TIME OF MFG.  THE TURBOCHARGER COMPRESSOR WHEEL WAS DESTROYED 	AND METAL FROM TURBO ENTRED INDUCTION SYSTEM OF ENGINE.  OIL FILTER REMOVED AND WAS FOUND TO BE HIGHLY CONTAMINATED WITH	 METAL.  ENGINE WAS REMOVED FOR REPAIR ALONG WITH TURBO.  SUGGEST ALTERNATE AIRDOOR SYSTEM BE INSPECTED EVERY 25 HOURS. 	(K)	1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005072900119	20050729	00119	EA  	2005	7	29	2005FA0001071    	1	20050619	G	3244	256K433	TIRE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30015	NE  					NR 4 MAIN WHEEL	SEPARATED       	B			BTVR	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			GL	23	241FB	1284 	108  		MAY910366	5102				(REF: PA05002) VIBRATION NOTED AT ROTATION SPEED.  FLIGHT CREW RETURNED TO POINT OF ORIGIN AND LANDED UNEVENTFULLY.  NR 	4 TIRE TREAD SEPARATED.  THE NR 4 MAIN WHEEL AND TIRE ASSY WERE CHANGED IAW MM.  THE AC WAS THEN FERRIED TO A MAINTENANC	E BASE TO REPAIR THE DAMAGE FROM THE TIRE FAILURE. (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005072900114	20050729	00114		2005	7	29	2005FA0001072    	4	20050608	G	2565	101630305	SLIDE           																	LT OVERWING	LEAKING         	D			USAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	19		28011	357  							(SHOP) IN THE SHOP, UPON RECEIPT FROM THE VENDOR, A LT OVERWING SLIDE FOR A 767 AIRCRAFT WAS GIVEN A RETENTION TEST.  TH	E TEST FAILED.  THE SLIDE WAS REPACKED AND RETURNED TO SERVICE.  (K)																		 
2005072900130	20050729	00130	CE  	2005	7	29	2005FA0001073    	1	20050720	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BREAKER	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1570A					CE1333				PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION THE GEAR WOULDN`T RETRACT, AFTER A FEW SECONDS THE GEA	R CAME UP ON ITS OWN.  ON TROUBLESHOOTING THE MECHANIC FOUND THE RELAY WAS INTERMITTENT, PROBABLE CAUSE AT THIS TIME UNK	NOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072900136	20050729	00136	CE  	2005	7	29	2005FA0001074    	1	20050720	G	3240	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BREAKER	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1563A	263  				CE1320				PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION THE GEAR WOULD NOT RETRACT.  ON TROUBLESHOOTING THE ME	CHANIC FOUND THE RELAY WAS INTERMITTENT, PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE	 CODE.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005072900135	20050729	00135	EA  	2005	7	29	2005FA0001075    	2	20050729	G	8520	76333	BUSHING         			BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					ENGINE	WORN            	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	27	715BH	230  				25105				MAGNETO IDLER GEAR SHAFT BROKE, THE BREAK WAS CAUSED BY A WORN BUSHING ON THE GEAR/SHAFT P/N'S 76091 & 76283 THAT DRIVES	 IT. THIS IS THE SECOND TIME THIS SHAFT BROKE.  TOTAL TIME SINCE OVERHAUL 230 HOURS.					1	G	7	1 	3O	3	O		2H3     	1E13				 
2005080100026	20050801	00026	GL  	2005	8	1	2005FA0001076    	1	20050729	G	5544	2055450000	SUPPORT         			DIAMON	DA20  	DA20C1      	2990001	GL  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		1166 				C0181				RUDDER SUPPORT BRACKET ON RUDDER TOWER FACING PART AS INSTALLED ON AIRCRAFT, BOTTOM RIGHT LEG CRACKED, OUTSIDE AND INSID	E, AT BASE ABOVE THE WELD. CRACK WAS VISIBLE WITH SMALL MIRROR AND FLASHLIGHT WITH THE RUDDER OFF.					1	L	7	1 	3O			NT	TA4CH   					 
2005080200004	20050802	00004	NE  	2005	8	2	2005FA0001077    	2	20050724	G	8500		ENGINE          			BOEING	75    	PT13D       	1380122	CE  	PWA   	R985  	R985*       	52008	NE  						SEIZED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	808RB					755055	JP207375			ENGINE SEIZED, UNKNOWN CAUSE. (GL11200513505)  (K)						1	Q	7	1 	3R	3	R		A743    	5E1				 
2005080200012	20050802	00012	CE  	2005	8	2	2005FA0001078    	1	20050702	G	3222	1243400202	PISTON          			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG FORK ASSY	SHEARED         	C				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	23	3717Y					21058217				ON LANDING, THE PILOT FELT A NOSE WHEEL VIBRATION.  TOWARD THE END OF THE ROLL OUT THE NOSE DROPPED DOWN, STRIKING THE R	UNWAY.  INSPECTION FOUND THE NOSE WHEEL FORK ASSY SHEARED OFF THE SHOCK STRUT ASSY.  (K)					1	H	7	1 	3O	3	O		3A21    	E1CE				 
2005080200134	20050802	00134	SO  	2005	8	2	2005FA0001079    	2	20050801	G	7414	6310	MAGNETO         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					LEFT	DAMAGED         	D				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			NM	07	61423	1537 				18504180	821801R			PERFORMED MAGNETO CHECK AND FOUND LT MAGNETO DROPPED 500 RPM. REMOVED MAG AND FOUND IMPULSE COUPLING RIVETS SHEARED, DRI	VE GEAR BUMPER RETAINER BROKEN AND BUMPERS DAMAGED. REMOVED OIL FILTER AND FOUND METAL SHAVINGS.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
2005080300001	20050803	00001	CE  	2005	8	3	2005FA0001080    	1	20050715	G	2434	649306	ALTERNATOR      			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	FAILED          	D			GMZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	3042V	709  				EA622				AIRCRAFT ENGINE RUNNING AND ALTERNATOR SWITCH SELECTED TO (ON) POSITION, ALTERNATOR RED ANNUCIATOR LIGHT (ON) AND LOAD M	ETER SHOWING ZERO LOAD BEING CARRIED BY ALTERANTOR.  AC OIL TEMP AND OIL PRESSURE INDICATIONS DROPPED TO ZERO IN FLIGHT 	AS BATTERY VOLTAGE DROPPED WELL BELOW 24.  AC LANDING GEAR AND FLAPS SELECTED TO DOWN POSITION PRIOR TO LANDING, DID NOT	 OPERATE DUE TO LOW BATTERY VOLTAGE AND ALTERNATOR INOPERATIVE.  AC LANDED GEAR UP.  FOLLOWED POH PROCEDURES.  (SW012005	05015) (K)		1	L	7	1 	3O	3	O		3A15    	E8CE				 
2005080300008	20050803	00008	CE  	2005	8	3	2005FA0001082    	1	20050628	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					RT MLG	CRACKED         	B			BNZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	5319V	2893 				172RG0505				PILOT REPORTED SIDE LOAD ON LANDING.  ON SUBSEQUENT TAKEOFF RT MAIN LANDING GEAR WOULD NOT FULLY RETRACT.  FOUND RT ACTU	ATOR CRACKED AT FORWARD BOLT HOLE.  (K)					1	H	7	1 	3O	3	O		3A17    	E286				 
2005080300005	20050803	00005	CE  	2005	8	3	2005FA0001083    	1	20050610	G	3233	98820152	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	9543B					172RG0868				FOUND UPPER FORWARD BOLT SHEARED AND ACTUATOR CACKED AT 100 HOUR INSPECTION.  (GL19200504416) (K)						1	H	7	1 	3O	3	O		3A17    	E286				 
2005080300011	20050803	00011	CE  	2005	8	3	2005FA0001084    	1	20050410	G	2730	0510105391	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ELEVATOR	BROKEN          	B			BNZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	5327V	694  				17281151				ELEVATOR CABLE, BROKEN STRANDS, 2 FT FROM AFT END.  FOUND DURING 100 HOUR INSPECTION.  (GL19200504415) (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005080300009	20050803	00009	CE  	2005	8	3	2005FA0001085    	1	20050525	G	2730	0510105391	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ELEVATOR	BROKEN          	B			BNZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	5353R	886  				17281157				ELEVATOR CABLE, BROKEN STRANDS, 2 FT FROM AFT END.  FOUND DURING 100 HOUR INSPECTION.  (GL19200504414) (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005080300002	20050803	00002	CE  	2005	8	3	2005FA0001086    	1	20050710	G	2730	0510105391	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ELEVATOR	BROKEN          	B			BNZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	5335G	886  				17281158				ELEVATOR CABLE, BROKEN STRANDS, 2 FT FROM AFT END.  FOUND DURING 100 HOUR INSPECTION.  (GL19200504419) (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005080300010	20050803	00010	EA  	2005	8	3	2005FA0001087    	2	20050730	G	7200	PT6A41	ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RIGHT	DAMAGED         	B			MZ2R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			GL	13	432FA	6768 				BB592	PCE81340	FY1144		AIRCRAFT PROCEEDED WITH A NORMAL TAKEOFF IN VFR CONDITIONS.  FOLLOWING ROTATION, AND  AT APPROXIMATELY 50 TO 100 FT AGL,	 THE RT ENGINE LOST POWER, THE PILOT LEVELED OFF.  THE AC WOULD NOT MAINTAIN ALTITUDE, PILOT CHOSE TO LAND IMMEDIATELY, 	WITH ADEQUATE RUNWAY AHEAD.  THE AC LANDED HARD AND WITH LANDING GEAR RETRACTED, CAUSING SUBSTANTIAL DAMAGE TO THE AC.  	NO INJURIES WERE INVOLVED.  UPON INSPECTION OF AIRCRAFT, RIGHT PROPELLER WAS FOUND UNFEATHERED, WHEN THE AIRCRAFT WAS HO	ISTED FOR SECURING, LANDING GEAR WAS SUCCESSFULLY EXTENDED BY USE OF THE EMERGENCY EXTENSION SYSTEM, AND LOCKED IN THE D	OWN POSITION.  CAUSE OF THE ENGINE POWER LOSS IS UNKNOWN AT THIS TIME.  (K)	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005080300007	20050803	00007		2005	8	3	2005FA0001088    	4	20050513	G	2562	MN1300	BATTERY         	ACK         		CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ELT	CORRODED        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	825CD				041121	0189				SECOND ELT FOUND WITH BATTERIES IN THIS CORRODED CONDITION.  (K)						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005080300137	20050803	00137	SO  	2005	8	3	2005FA0001089    	1	20050802	G	1430	MS210426	NUT             			PIPER 	PA34  	PA34200T    	7103406	SO  										COVER	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	36049	4800 				347870287				REPAIR STATION WAS REPAIRING AIRCRAFT HYD LEAK.  WHEN REMOVING LOWER FORWARD WING ATTACH BOLT COVERS FOUND 10 OF THE 16 	MS21042-6 NUTS CRACKED.  PIPER P/N 404-532.					1	L	7	2 	3O				A7SO    					 
2005080300152	20050803	00152	CE  	2005	8	3	2005FA0001090    	1	20050721	G	3610	AA3216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	VIBRATES        	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1569P	320  				CE1300				PILOT REPORTED WHINING NOISE COMING FROM ENGINE AND FELT A VIBRATION COMING THROUGH THE MIXTURE CONTROL CABLE.  TROUBLES	HOOTING, THE MECHANIC FOUND THE AIR PUMP WAS VIBRATING.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005080300154	20050803	00154	SO  	2005	8	3	2005FA0001091    	1	20050726	G	5313		LONGERON        			AYRES 	S2T   	STRT34      	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4020Q	4368 				T34265				BOTH UPPER LONGERON WAS CRACKED APPROXIMATELY 54 INCHES AFT OF DATUM.  THE AREA IS DIFFICULT TO INSPECT AS IT IS 75 PERC	ENT COVERED BY THE HOPPER.   THIS IS A VERY UNUSUAL AREA TO FIND SUCH A DEFECT.  THE AC HAS NO DAMAGE HISTORY AND HAS NO	T BEEN ABUSED.  (K)				1	L	7	1 	3T	4	T		A3SW    	E4EA				 
2005080300151	20050803	00151		2005	8	3	2005FA0001092    	1	20050729	G	8011	MHB6016	STARTER         																		CRACKED         	B			F8ZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07										DRIVE HOUSING ASSY CRACKED ON MOUNTING PLATE.  THIS IS THE 5TH CRACKED HOUSING IN A 2 MONTH PERIOD.  THERE IS A MAJOR PR	OBLEM. (K)																		 
2005080900054	20050809	00054	SO  	2005	8	9	2005FA0001093    	1	20050725	G	2420	4111810R	ALTERNATOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ROTOR,INTERNAL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9284A					288616041				AFTER 46.9 HOURS OF OPERATION OF A NEWLY OVERHAULED ALTERNATOR, OUTPUT CEASED.  HAD UNIT TESTED AND FOUND THE ROTOR OPEN	, NO CURRENT FLOW THROUGH ROTOR.  BRUSHES WERE GOOD.  (K)					1	L	7	1 	3O	3	O		2A13    	E274				 
2005080900048	20050809	00048	CE  	2005	8	9	2005FA0001094    	1	20050808	G	2910	6317003136	LINE            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					HYDRAULIC SYS	SCORED          	B				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			GL	09	247CW	2999 				5250247				DURING FLIGHT, THE LT AND RT HYDRAULIC LOW LEVEL LIGHTS ILLUMINATED ALONG WITH A MASTER CAUTION LIGHT.  AFTER A SAFE LAN	DING, THE ENTIRE TAIL OF THE AIRCRAFT WAS FOUND TO BE SOAKED WITH HYDRAULIC FLUID.  FURTHER INVESTIGATION FOUND THAT HYD	RAULIC LINE HAD RUPTURED AT ONE OF THE BENDS.  IT APPEARS THAT THE RUPTURE POINT WAS AT A SCORE MARK THAT WAS LEFT WHEN 	THE LINE WAS FABRICATED.  EACH END OF THIS LINE IS BENT AT NEARLY A 90 DEGREE ANGLE.  EACH END DISPLAYED THE SAME TYPE O	F SCORE MARKS.  LINE WAS REPLACED WITH NEW.  SUGGEST A ONE TIME INSPECTION OF THIS LINE.  IF IT IS DETERMINED THAT ANY S	CORE MARKS SEEM EXCESSIVE, RECOMMEND REPLACEMENT OF THE LINE.  PROCUREMENT OF NEW LINES SHOULD BE INSPECTED FOR THE SAME	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2005080900049	20050809	00049	CE  	2005	8	9	2005FA0001095    	1	20050808	G	2910	6317003136	LINE            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					HYDRAULIC SYS	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	247CW	2999 				5250247				DURING FLIGHT, THE LT AND RT HYDRAULIC LOW LEVEL LIGHTS ILLUMINATED ALONG WITH A MASTER CAUTION LIGHT. AFTER A SAFE LAND	ING, THE ENTIRE TAIL OF THE AIRCRAFT WAS FOUND TO BE SOAKED WITH HYDRAULIC FLUID.  FURTHER INVESTIGATION FOUND THAT HYDR	AULIC LINE HAD RUPTURED AT ONE OF THE BENDS.  IT APPEARS THAT THE RUPTURE POINT WAS AT A SCORE MARK THAT WAS LEFT WHEN T	HE LINE WAS FABRICATED.  EACH END OF THIS LINE IS BENT AT NEARLY A 90 DEGREE ANGLE.  EACH END DISPLAYED THE SAME TYPE OF	 SCORE MARKS.  LINE WAS REPLACED WITH NEW.  SUGGEST A ONE TIME INSPECTION OF THIS LINE.  IF IT IS DETERMINED THAT ANY SC	ORE MARKS SEEM EXCESSIVE, RECOMMEND REPLACEMENT OF THE LINE.  PROCUREMENT OF NEW LINES SHOULD BE INSPECTED FOR THE SAME.	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2005080900062	20050809	00062	CE  	2005	8	9	2005FA0001096    	1	20050804	G	3220	MS203922C17	PIN             	CESSNA      		CESSNA	210   	210         	2073402	CE  	CONT  	O470  	IO470E      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	NLG	MISSING         	C				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	09	6521X		38   			57521	CS931732E	786931		NOSE GEAR UPLOCK PIN FELL OUT AFTER RETAINING COTTER PIN FAILED, NOT ALLOWING UPLOCK ACTUATOR TO RELEASE GEAR RESLULTING	 IN NOSE GEAR UP LANDING, ALSO FOUND NOSE GEAR UPLOCK SPRING ATTACH BRACKETT SEVERLY WORN. (SW09200511362)					1	H	7	1 	3O	3	O	RT	3A21    	3E1	5	C	P3EA	 
2005080900091	20050809	00091	CE  	2005	8	9	2005FA0001097    	1	20050721	G	2910	MS21902J4	UNION           			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					HYD SYS	LOOSE           	B			CNQ3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	970SK					7500186				HYD UNION WAS FOUND TO BE LOOSE ALLOWING O-RING TO FAIL OVER TIME.  O-RING WAS REPLACED AND FITTING TORQUED.  (K)						2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005080900092	20050809	00092	SW  	2005	8	9	2005FA0001098    	1	20050714	G	6320	407040035101	BEVEL GEAR      	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEAR TOOTH	BROKEN          	B			ULXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	701WP	1425 			A575	53542				HELICOPTER RECEIVED 2 TRANSMISSION CHIP CAUTION LIGHTS IN 2.9 HOURS.  MAIN INPUT GUILL WAS REMOVED FOR INSPECTION OF THE	 BEVEL GEAR.  THE BEVEL GEAR INSPECTION REVEALED 1 MISSING GEAR TOOTH AND AN ADJACENT TOOTH CRACKED.  TRANSMISSION SENT 	TO MFG FOR EVALUATION AND OVERHAUL.  NO RECOMMENDATION TO PREVENT RECURRENCE.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005080900093	20050809	00093	GL  	2005	8	9	2005FA0001099    	1	20050727	G	2420	BC4101	MOUNT           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					MOUNT, FLANGE	BROKEN          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	841CD					0336	686398			ALTERNATOR MOUNT BROKEN AND OIL LEAK.  (THE ALTERNATOR CASE MOUNT FLANGE BROKEN)  DRIVESHAFT IN ALTERNATOR SHEARED.  THE	 ENGINE DRIVE SHAFT HUB HAS NO DAMAGE.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005080900137	20050809	00137	EA  	2005	8	9	2005FA0001100    	2	20050808	G	7322	30800	FLOAT           	PREAIR      	HA6         	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					CARBURATOR	SATURATED       	G				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	19		576  	576  		DG111046					ENGINE RUNNING EXCESSIVELY RICH AT LOW POWER SETTINGS / TAXI.RAW FUEL RUNNING OUT OF INTAKE BOX AND EXHAUST STACKS.EXAMI	NATION OF CARBURATOR DISCLOSED FLOAT HAD FLOODED AND SANK.					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2005081500199	20050815	00199		2005	8	15	2005FA0001101    	4	20050809	G	6122		SNAP RING       	HARTZL      	F624L       	PIPER 	PA31  	PA31350     	7103110	SO  										GOVERNOR	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	3534Y				D2545TJ	317952195				PROP GOVERNOR DRIVE GEAR FOUND BROKEN.  FOUND BROKEN SNAP RING.  DAMAGED COUPLING.  NO METAL IN GOVERNOR.  GEAR AND FLY 	WEIGHTS ROTATED FREELY.					1	L	7	2 	3O				A20SO   					 
2005081000318	20050810	00318	CE  	2005	8	10	2005FA0001107    	1	20050720	G	5210	530323	SOLENOID        			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ44        	66000	GL  					DOOR SEAL	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	112CM	116  				RB123				REF: (PT1838110)  DOOR SOLENOID FAILED IN OPEN POSITION.  WITH EITHER ENGINE RUNNING, THE DOOR COULD NOT BE OPENED/CLOSE	D DUE TO INFLATED SEAL.  SOLENOID REPLACED, OPERATIONAL CHECK GOOD.  (K)					1	7		2 	3F	4	F	RT	A00010WI	E3GL				 
2005081000350	20050810	00350	CE  	2005	8	10	2005FA0001108    	1	20050708	G	2700	0510105365	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RBL102	WORN            	B			CTUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	53289	1198 				172S9331				CABLES WORN BEYOND LIMITS AT A CABLE RUB STRIP IN RT WING BY AUTOPILOT SERVO AT STATION RBL 102.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005081100089	20050811	00089	CE  	2005	8	11	2005FA0001109    	1	20050708	G	2710	0510105362	CONTROL CABLE   	CESSNA      		CESSNA	182   	182P        	2075816	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RT WING, RBL 102	WORN            	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	52389	1198 				18262572				CABLES WORN BEYOND LIMITS AT A CABLE RUB STRIP IN RT WING BY AUTOPILOT SERVO AT STA RBL 102. (K)						1	H	7	1 	3O	3	O	NT	TA13    	1E10				 
2005081100097	20050811	00097	CE  	2005	8	11	2005FA0001110    	1	20050401	G	5343		ATTACH ANGLE    			CESSNA	310   	310G        	2074218	CE  	CONT  	O470  	IO470*      	17026	SO  					MLG	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	414X					310G0091				AT ANNUAL INSPECTION, FOUND 3 RIVETS AND 1 BOLT SHEARED AT RT FWD MLG TRUNNION ATTACH ANGLE.  RIVETS WERE UPPER 2 ROWS O	F 4 ROWS.  REMAINING RIVETS SHOWED SIGNS OF (SMILE) FROM INSTALLATION.  SHEARED BOLT WAS IN UPPER FWD POSITION OF FWD AN	GLE.  SHEARED FASTENERS WERE VISIBLE THROUGH INSPECTION PANEL AT OB CENTER OF GEAR.  NO VISIBLE STRUCTURAL DAMAGE WAS NO	TED.  OWNER WAS NOTIFIED AND AC WAS DEEMED UN-AIRWORTHY.  (K)			1	L	7	2 	3O	3	O		3A10    	E1CE				 
2005081100092	20050811	00092	CE  	2005	8	11	2005FA0001111    	1	20050723	G	2810	55000105	FUEL TANK       			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					WING TIO	PLUGGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	8140G					E2635				RT AUXILIARY FUEL TIP TANK IMPLODED.  DETERMINED PROBABLE CAUSE WAS A PLUGGED VENT.  GUIDANCE SUGGEST: WHEN PARKED, KEEP	 VENT CAPPED LIKE A PITOT COVER.  DURING PREFLIGHT, TO OPEN GAS CAP AND BLOW OR AFFIX A TUBE TO THE .2500 INCH VENT AND 	BLOW TO VERIFY VENT NOT TO BE PLUGGED.  IF VENT IS FOUND PLUGGED, REMOVE RESTRICTION BEFORE FLIGHT.  (GL03200513894) (K)				1	L	7	1 	3O	3	O		3A15    	E3SO				 
2005081100090	20050811	00090	CE  	2005	8	11	2005FA0001112    	1	20050721	G	5330		SKIN            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  					FUSELAGE	CORRODED        	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	5VA	5757 				U20603223				AC WAS UNDERGOING AN EXTENSIVE AVIONICS UPGRADE INSTALLATION AND DURING ANTENNA INSTALLATIONS, TECH NOTICED CORROSION UN	DER FACTORY INSTALED DAMPENING/INSULATION MATERIAL.  CORROSION WAS TO LOWER FUSELAGE SKINS UNDER THIS MATERIAL.  THE COR	ROSION WAS FOUND UNDER THE PIECES FOUND COMING LOOSE.  INTACT PIECES DID NOT SEEM CORRODED UNDERNEATH.  CLEANED CORROSIO	N AND MINOR PITTING, TREATED AND PRIMERED AREAS AFTER REMOVING MATERIAL.  SUGGEST CLOSE INSPECTION THIS AREA, ALL AIRCRA	FT.  PROBLEM MORE THAN LIKELY CAUSED BY AGE AND MOISTURE ACCUMULATION.  FSDO THINKS IT MAY BE GLUE USED.  (K)		1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005081100096	20050811	00096	CE  	2005	8	11	2005FA0001113    	1	20050726	G	2510	551900922	SEAT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	123VP					5500111				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  	CHAIR WAS REPAIRED IAW STC ST01042WI STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005081100069	20050811	00069	SO  	2005	8	11	2005FA0001114    	1	20050804	G	5541		SPAR            			AYRES 	S2    	S2RT660     	0970112	SO  	PWA   	PT6   	PT6A65AG    	52043	NE  					RUDDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	4121G	289  				T660105				THE UPPER RUDDER SPAR WAS BROKEN 12.5 INCHES ABOVE THE UPPER HINGE.  IN ADDITION, THE SPAR CRACKED UNDER THE UPPER HINGE	 FITTINGS.  THIS CAUSED THE RUDDER COUNTER BALANCE TO BE LOOSE RESULTING IN RUDDER FLUTTER.  FURTHER FLIGHT COULD HAVE R	ESULTED IN LOSS OF RUDDER CONTROL.  THE SPAR WEB IS MADE OF .040 INCH ALUMINUM CHANNEL WITH VERY LITTLE IN THE WAY OF ST	IFFNERS.  THE SPAR NEEDS TO BE BEEFED UP.  (K)			1	L	7	1 	  	4	T		        	E4EA				 
2005081100054	20050811	00054	CE  	2005	8	11	2005FA0001115    	1	20050727	G	2916	511700712	TUBE            	CESSNA      		CESSNA	402   	402C        	207590R	CE  										HYD SYSTEM	SPLIT           	E				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SO	17	78FC					402C0496				EIGHT MILES NORTH EAST OF KFLL, PILOT NOTICED A HYDRAULIC SMELL IN THE COCKPIT DURING CLIMB-OUT.  THERE WERE NO ABNORMAL	ITIES NOTED.  PILOT DECLARED AN EMERGENCY AT KPMP.  PILOT LANDED AIRCRAFT AT KPMP WITHOUT INCIDENT.  POST FLIGHT REVEALE	D HYDRAULIC SITE TUBE ON HYDRAULIC RESERVOIR HAD FAILED CAUSING AN ATOMIZED LEAK FROM THE HYDRAULIC SITE TUBE.				1	L	7	2 	3O				A7CE    					 
2005081700006	20050817	00006		2005	8	17	2005FA0001116    	1	20050810	G	3610		REGULATOR VALVE 								CONT  	O360  	LTSIO360EB  	17025	SO  					RT NACELLE	RUPTURED        	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	803G	2390 	2390 							UPON RUN UP, PILOT CYCLED BOOTS. BOOT CYCLE STATUS LIGHT CAME ON BUT EXTINGUISHED BEFORE 6 SECOND INFLATION CYCLE TIMED 	OUT. (PRESS TO TEST SHOWED LAMP OK).  BOOTS REMAINED PARTIALLY INFLATED AND WOULD NOT DE-FLATE. PILOT SPOOLED ENGINES DO	WN AND BOOTS DE-FLATED.  INSPECTION DISCLOSED THAT DIAPHRAGM ON LOW PRESSURE REGULATOR OF THE ASSEMBLY HAD FAILED AROUND	 ENTIRE CIRCUMFERENCE. FAILED DISK SPALLED THE BELL SHAPED PORTION OF REGULATOR RUINING THE REGULATOR AND RENDERING 2H22	-16 PART UNFIT FOR OVERHAUL.							3	O			E9CE				 
2005081700007	20050817	00007		2005	8	17	2005FA0001117    	1	20050810	G	3610		REGULATOR VALVE 								CONT  	O360  	LTSIO360EB  	17025	SO  					DE ICE SYS	RUPTURED        	P				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	01	803G	2390 	2390 							UPON RUN UP, PILOT CYCLED BOOTS. BOOT CYCLE STATUS LIGHT CAME ON BUT EXTINGUISHED BEFORE 6 SECOND INFLATION CYCLE TIMED 	OUT. (PRESS TO TEST SHOWED LAMP OK)  BOOTS REMAINED PARTIALLY INFLATED AND WOULD NOT DE-FLATE. PILOT SPOOLED ENGINES DOW	N AND BOOTS DE-INFLATED.  INSPECTION DISCLOSED THAT DIAPHRAGM ON LOW PRESSURE REGULATOR OF THE AIRBORNE 2H22-16 ASSEMBLY	 HAD FAILED AROUND ENTIRE CIRCUMFERENCE. FAILED DISK SPALLED THE BELL SHAPED PORTION OF REGULATOR RUINING THE REGULATOR 	AND RENDERING 2H22-16 PART UNFIT FOR OVERHAUL.							3	O			E9CE				 
2005081700172	20050817	00172	GL  	2005	8	17	2005FA0001128    	1	20050808	G	5210		DOOR            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					CABIN	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	369SE					0846				BOTH DOORS WILL (POP) OPEN IN FLIGHT, CAUSING A SAFETY DISTRACTION TO THE PILOT AND WIND NOISE THAT KEEPS THE PILOT FROM	 HEARING AT INSTRUCTIONS.  THIS STILL HAPPENS AFTER SEVER TRIPS TO MFG REPAIR STATION AND BACK TO FACTORY FOR REPAIRS.  	MFG RESPONSE IS THAT THE DOORS ARE WITHIN SPECS AND SHOULD NOT COME OPEN.  HAVE HEARD FROM OTHER OWNERS THAT THEY HAVE S	AME PROBLEM WITH THE NEW DOOR DESIGN.  (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005081600212	20050816	00212		2005	8	16	2005FA0001129    	4	20050726	G	2200	4006719906	DRIVE ASSY      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AUTOPILOT SERVO	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	5408G					5500666				THE PILOT REPORTED THAT THE CONTROLS WHERE STIFF IN THE ROLL AXIS.  THE AUTOPILOT WAS TURNED OFF AND THE C/B WAS CYCLED 	WITH NO CHANGE IN THE CONDITION.  AFTER LANDING WITHOUT INCIDENT, TECHS ARRIVED AND TROUBLESHOT THE A/P SYSTEM.  THEY DI	SCOVERED THE AILERON AUTOPILOT SERVO DRIVE CLUTCH WAS NOT FULLY DISENGAGING, CAUSING THE EXCESSIVE FORCE REQUIRED TO ROL	L THE AIRCRAFT.  AILERON AUTOPILOT SERVO DRIVE WAS REMOVED AND REPLACED.  BOTH GROUND AND IN-FLIGHT OPERATIONAL CHECKS W	ERE PERFORMED WITH NO DEFECTS NOTED. (NM13200503639) (K)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005081700059	20050817	00059	SO  	2005	8	17	2005FA0001131    	1	20050809	G	5210	553876	CAM             			PIPER 	PA34  	PA34200T    	7103406	SO  										PAX DOOR	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07		75   								CAM IS THE UPPER LATCH ON THE REAR DOOR IN THE AIRCRAFT.  THE INNER AND OUTER STEMS HOLD THE INNER AND OUTER DOOR LATCH 	HANDLES.  PILOTS AND/OR PASSENGERS APPLY TOO MUCH PRESSURE OR TWIST THE HANDLES TOO FAR, SHEARING THE PART.  THE PART IS	 MADE OF A PLASTIC OR NYLON FORMED IN ONE PART WITH THE LOCKING CAM BETWEEN THE SQUARE ENDS.  HANDLES ARE ATTACHED TOT H	E ENDS BY SCREWS.  (K)			1	L	7	2 	3O				A7SO    					 
2005081700064	20050817	00064	SW  	2005	8	17	2005FA0001132    	1	20050804	G	6710	222310465001	BEARING         			BELL  	230   	230         	1182149	SW  	ALLSN 	250C  	250C30      	03013	GL  					COLLECTIVE LEVER	VIBRATION       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	870SF	2324 				23018				LT COLLECTIVE LEVER SUPPORT BEARING FAILED CAUSING MAIN ROTOR VERT VIBRATION AND LOWER COLLECTIVE LEVER IDLER ELASTROMER	IC BEARINGS TO FAIL AND SOME WERE IN MAIN TRANSMISSION UPPER LUGS/ATTACHMENT POINT TO WEAR.  DISCUSSED WITH MFG PAODUCT 	SUPPORT.				1	G	7	2 	3U	3	U	NC	H9SW    	E1GL				 
2005081700065	20050817	00065	SO  	2005	8	17	2005FA0001133    	2	20050719	G	8530	EC649358CN	CYLINDER HEAD   			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	50QH		212  			21064150	293513R			DURING CRUISE FLIGHT, A LOUD BANG FROM THE ENGINE COMPARTMENT WAS FOLLOWED BY LOSS OF POWER AND SIGNIFICANT ENGINE VIBRA	TION.  THE PILOT MADE AN EMERGENCY LANDING ON A DIRT ROAD WITH NO DAMAGE TO THE AIRCRAFT.  THE NR 1 CYLINDER HEAD HAD FR	ACTURED COMPLETELY THROUGH, JUST ABOVE THE CYLINDER BARREL THREADS, LEAVING A .5 INCH GAP BETWEEN HEAD FINS 6 AND 7.  TH	E CYLINDER HAD BEEN REPAIRED 212 HOURS PRIOR TO FAILURE AND HAD BEEN BORED TO .010 OVERSIZE.  A SERVICEABLE TAG HAD BEEN	 PROVIDED BY THE REPAIR STATION THAT PERFORMED THE WORK.  (K)		1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005081700095	20050817	00095	CE  	2005	8	17	2005FA0001134    	1	20050728	G	5342	12320132F	FITTING         			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520M    	17040	SO  					HORIZONTAL STAB	BROKEN          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9482M	14703				20700698				PILOT FOUND VERTICAL STABILIZER LOOSE ON PREFLIGHT.  MAINTENANCE INSPECTED AND FOUND RT FWD ATTACHMENT FITTING BROKEN.  	REPLACED BOTH FWD FITTINGS WITH NEW PARTS.  (K)					1	H	7	1 	3O	3	O		A16CE   	E8CE				 
2005081700181	20050817	00181	CE  	2005	8	17	2005FA0001135    	1	20050807	G	3230	S13771	SWITCH          			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	MLG	BROKEN          	C				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			NE	05	152BT	3440 				210000486				NO CONFIRMATION OF LANDING GEAR DOWN AND LOCKED.   NO GREEN LIGHTS.  GEAR APPEARED DOWN VISUALLY.  ON INSPECTION ONCE ON	 THE GROUND IT WAS DOWN AND PROPERLY LOCK.  MALFUNCTION WAS THE GEAR INDICATOR POSITION MICRO SWITCH ON THE LT MAIN BROK	EN WIRE AT THE SWITCH.  NEW SWITCH PN: S1377-1 FIXED THE PROBLEM.  NO SIGN OF STRAIN ON WIRE, JUST AGE AND NORMAL FLEXIN	G.			1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL	 
2005081700171	20050817	00171	SO  	2005	8	17	2005FA0001136    	1	20050816	G	4920	36150861	CAP             			GULSTM	G1159 	GIV         	3980115	SO  										APU COMBUSTOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	569CW	820  	820  			1145				APU COMBUSTOR CAP HAD A CRACKED WELD.  THE CRACKED WELD WAS ADJACENT TO THE HEAT DEFLECTOR. UNIT HAD 820 TT SINCE NEW.						2	L	7	2 	4F			RT	A12EA   					 
2005081800091	20050818	00091	SW  	2005	8	18	2005FA0001137    	1	20050811	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	C85   	C85*        	17008	SO  					RT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	84286					7AC2980				AFT RT SPAR HAS LONGITUDINAL CRACK ON LOWER END.  CRACK OCATED AT STRUT ATTACH POINT.  SPAR ALSO SHOWS SIGNS OF ROTTING 	IB OF CRACK AREA.  (K)					1	H	7	1 	3O	3	O		A759    	E233				 
2005081800095	20050818	00095	CE  	2005	8	18	2005FA0001138    	1	20050801	G	2841	45AS48008003	PRESSURE SWITCH 			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FUEL SYSTEM	FAILED          	B			E81R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	432CW					RK32				RT WING OVERPRESSURE ANNUNCIATOR LIGHT ILLUMINATED IN FLIGHT.  FOUND S128 PRESSURE SWITCH TO HAVE CONTINUITY WITH NO PRE	SSURE SWITCH TO HAVE CONTINUITY WITH NO PRESSURE APPLIED.  REPLACED SWITCH ASSY WITH NEW UNIT IAW MM, OPERATIONS NORMAL.	 (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2005081800096	20050818	00096	NE  	2005	8	18	2005FA0001139    	2	20050808	G	7261	209062028001	FITTING         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					VALVE	DETACHED        	B			IGAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	212AH					30959				DURING FLIGHT FITTING BECAME DETACHED CAUSING LOSS OF OIL.  FOUND FITTING MADE OF ALUMINUM.  NEW FITTING MADE OF STEEL. 	 (K)					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005081800107	20050818	00107	CE  	2005	8	18	2005FA0001140    	1	20050729	G	3310	11693	MOUNT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A6       	52043	EA  					INDIRECT LIGHT	FAULTY          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	842E	5802 				UE336				TRANSISTOR MOUNT, INSTRUMENT PANEL INDIRECT LISHTS OPERATE AT FULL BRIGHT REGARDLESS OF POTENTIATOR POSITION.  TROUBLESH	OOTING FOUND THAT TRANSISTOR MOUNT WAS INSTALLED BEHIND LOCATION CALLED OUT AS COPILOTS FLIGHT INSTRUMENTS.  IDENTIFYING	 FAULTY TRANSISTOR COULD NOT BE ACCOMPLISHED UNTIL MIS-ROUTED TRANSISTOR SOCKET WAS FOUND.  NO MAINTENANCE WAS LOGGED IN	 THIS AREA SINCE NEW.  (K)			2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2005082200058	20050822	00058		2005	8	22	2005FA0001190    	1	20050819	G	6120	C299506B0104	CONTROL CABLE   																	PROPELLER	DEFECTIVE       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01										PROPELLER CONTROL CABLE CAME DEFECTIVE FROM MANUFACTURER.  ORDERED A TOTAL OF THREE (3)ALL THREE DEFECTIVE.  APPEARS CAB	LES ARE MANUFACTURED BY NEW VENDOR AS ONE OF THEM WAS IDENTIFIED AS "FIRST ARTICLE SAMPLE.  CONTROLS JAM AND PRODUCE BRA	SS FILINGS DURING ROTATION OF VERNIER CONTROL.  VERNIER CONTROL MACHINES GROVES INTO SURFACE OF SHAFT.  DIGITAL PICTURES	 TAKEN AND CESSNA ENGINEERING CONTACTED																 
2005082200060	20050822	00060	SO  	2005	8	22	2005FA0001192    	2	20050819	G	7260	640756A6	ADAPTER         	CONT        	360KB32     	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	321AK	190  	190  		811403R	3447021	811403R	961314		STARTER ASSEMBLY BOLT HOLE FLANGE CRACKED AT THE 10 O'CLOCK BOLT POSITION.  MANUFACTURER DESIGN FLAW.  ONGOING NUMEROUS 	REOCCURENCES WITH THESE ADAPTER ASSEMBLY ACCESSORY DRIVE HOUSINGS, LEFT SIDE ONLY, IN FLEET  AIRCRAFT.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2005082200061	20050822	00061	SO  	2005	8	22	2005FA0001193    	2	20050819	G	7260	640756A6	ADAPTER         	CONT        	360KB32     	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	321AK	190  	190  		811403R	3447021	811403R	961314		STARTER ASSEMBLY BOLT HOLE FLANGE CRACKED AT THE 10 O'CLOCK BOLT POSITION.  MANUFACTURER DESIGN FLAW.  ONGOING NUMEROUS 	REOCCURENCES WITH THESE ADAPTER ASSEMBLY ACCESSORY DRIVE HOUSINGS, LEFT SIDE ONLY, IN FLEET  AIRCRAFT.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2005082200062	20050822	00062	SW  	2005	8	22	2005FA0001194    	1	20050821	G	5711		SPAR            			BBAVIA	7     	7GCAA       	21101N8	SW  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	8305V	2778 				98				TWO COMPRESSION CRACKS ON RIGHT WING REAR SPAR, ONE ON EITHER SIDE OF PLYWOOD DOUBLER AT STRUT ATTACH POINT. OUT BOARD C	RACK EXTENDS APPROX ONE THIRD DEPTH OF SPAR, EXTENT OF INBOARD CRACK AS YET UNKNOWN, MAY GO BEHIND DOUBLER, CRACKS FOUND	 DURING INSPECTION REQUIRED BY AD 2000-25-02.				1	H	7	1 	3O				A759    					 
2005082200063	20050822	00063	SO  	2005	8	22	2005FA0001195    	2	20050817	G	7314	TF1900	PUMP            			BEECH 	35    	C35BEECH    	1151508	CE  	CONT  	E225  	E225*       	17015	SO  					ENGINE FUEL	WORN            	G				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			WP	09	709D	148  	148  			D2981	40009D			THE ENGINE FUEL PUMP DRIVE WAS FOUND WORN TO THE POINT WHERE IT WOULD NO LONGER DRIVE THE PUMP, CAUSING AND ENGINE FAILU	RE.  THE PUMP HAD 148 HOURS ON IT SINCE OVERHAUL.  IT HAS NOT BEEN DETERMINED IF THE LOCATOR PIN WAS INSTALLED IN THE DR	IVE.				1	L	7	1 	3O	3	O		A777    	E267				 
2005082500125	20050825	00125	SO  	2005	8	25	2005FA0001196    	1	20050806	G	3222	8628003	DRAG BRACE      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	3104C	251  				4496190				UPON LANDING AND NOSE GEAR TOUCHING DOWN PILOTS HEARD LOUD BANG FROM THE NOSE AREA.  NOSE GEAR HALF COLLAPSED (DRAG LINK	 JAMMED AGAINST THE NOSE STRUT TRUNION) AND AC WENT TO THE RT INTO GRASS AREA THEN SPUN TO RT  TURNED 180 DEGREES IN A L	ARGE ARC, CROSSED BACK ACROSS TO LT SIDE OF THE RUNWAY COMING TO REST ON LT SIDE OF RUNWAY.  RECOVERED ONE CRESCENT SHAP	ED FRAGMENT.  APPEARS TO BE ANOTHER PIECE UNACCOUNTED FOR.  PROBABLE CAUSE; DEFECTIVE DRAG LINK, BUSHING OR BOLT AT CONN	ECTION POINT.  (K)		1	L	7	2 	3O	3	O		A19S0   	E286				 
2005082400100	20050824	00100	NM  	2005	8	24	2005FA0001197    	1	20050805	G	2710	3170121	ROD END         			BOEING	747   	747SP21     	1384802	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LT IB PCU	BROKEN          	B			LWXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	145UA					21441				ON AUGUST 5TH, DURING THE FLIGHT CONTROL RIGGING OPERATION, THE LT AILERON IB PCU ROD END WAS FOUND BROKEN.  THIS ROD EN	D IS PART OF THE BENDIX PCU PN 317012-1 ASSEMBLY.  EVIDENCE OF CORROSION IS APPARENT AT CRACKED LOCATION.  UNKNOWN TIME.					2	L	7	4 	4F	4	F		A20WE   	E2EA				 
2005082500126	20050825	00126	CE  	2005	8	25	2005FA0001198    	1	20050709	G	7603		WEDGE           			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  					THROTTLE CABLE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4933U					21058633				CABLE BROKE AT THE S3 WEDGE WHERE THE BARREL END CONNECTS TO THE INTERNAL CABLE.  THIS AREA IS NOT VISIBLE AS THERE IS A	N INTERNAL SLEEVE THAT COVERS THE CABLE IN THIS AREA.  ( CE07200516270) (K)					1	H	7	1 	3O	3	O		3A21    	E5CE				 
2005090100023	20050901	00023		2005	9	1	2005FA0001199    	4	20050806	G	6113		BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROP SPINNER	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	121CW	194  				172S8975				DURING ANNUAL/ 100 HOUR INSPECTION, FOUND SPINNER FWD BULKHEAD CRACKED AROUND 2 HOLES OF THE MOUNTING BOLTS.  BOLTS PULL	ING EDGES OF BULKHEAD HOLES INTO CHAMFER OF THE PROP HOLES, CREATING STRESS AROUND THESE BULKHEAD HOLES LEADING TO CRACK	S.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005082400097	20050824	00097	EU  	2005	8	24	2005FA0001200    	1	20050628	G	6520	4639310062	BEVEL GEAR      			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101*     		NE  					T/R GEARBOX	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117BK	3544 			469	7229				CASE CRUSHING OR SPALLING WITH CRACKS.  COMPONENT COMING DUE 3600 HR TBO.  SUBMITTED FOR ROUTINE OVERHAUL.  DEFECTS FOUN	D DURING NORMAL DETAIL BENCH INSPECTION.  COMPONENT HAS A 10,800 HOUR SERVICE LIFE LIMIT.  (K)					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE				 
2005090100019	20050901	00019	CE  	2005	9	1	2005FA0001201    	1	20050813	G	2421	DOFF10300F	ROTOR SHAFT     	FORD        		CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200*       	17020	SO  					ALTERNATOR	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	18583		900  		C041218	15073961				ALTERNATOR SHAFT SHEARED AT BEARING LOCATION.  DRIVE GEAR, BUSHINGS, RETAINER AND COUPLING ASSEMBLY ROLLED BETWEEN ENGIN	E ACCESSORY CASE AND DRIVE GEAR.  THE SHAFT HAD BEEN PREVIOUSLY CRACKED OVER 50 PERCENT PRIOR TO FAILURE.  (K)					1	H	7	1 	3O	3	O		3A19    	E252				 
2005090100024	20050901	00024	SW  	2005	9	1	2005FA0001202    	1	20050817	G	8011	75622CG	STARTER         			GULSTM	680   	680E        	0141604	SW  										ENGINE	FAILED          	B			MV1R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	17	50		13   			680E81862				ON START UP FOR SECOND FLIGHT OF THE DAY, AC STARTER WOULD NOT ENGAGE AND TURN ENGINE.  SEVERAL ATTEMPS WERE MADE TO STA	RT THE ENGINE.  STARTER WOULD TURN BUT WOULD NOT ENGAGE AND TURN OVER ENGINE.  THIS STARTER WAS INSTALLED ON THIS AIRCRA	FT ON THE SAME ENGINE AND REMOVED FOR THE SAME REASON IN 10/17/01.  (K)				1	H	7	2 	3O				2A4     					 
2005090100022	20050901	00022	EU  	2005	9	1	2005FA0001203    	1	20050705	G	2810		ATTACH BRACKET  			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL CELL	LEAKING         	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	610SM					101				FUEL LEAKING INTO CABIN.  CUSTOMER SQKD FUEL SMELL INSIDE CABIN.  REMOVED INTERIOR AND FLOOR PANELS AND FOUND ATTACHMENT	 BRACKETS MOUNTED INTO WING TANK (INCLUDING COLLECTOR BOX) FASTENERS LEAKING BADLY.  DURING BOOST PUMP OPERATION, FUEL L	EAK INCREASED TO COVER CENTER ISLE WITH FUEL.  RESEALED FASTENERS IN CABIN AND INNER TANK.  (K)				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2005082400095	20050824	00095	CE  	2005	8	24	2005FA0001204    	1	20050823	G	2434	F424R	ALTERNATOR      			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	SEIZED          	D				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SW	15	5416U		77   			21064890	289136R	972424		AIRCRAFT WAS RUN UP PRIOR TO 50 HOUR INSPECTION AND NO DEFECTS WERE FOUND DURING RUN UP. AFTER INSPECTION, PERFORMED POS	T INSPECTION RUN AND NOTICED A LOUD SQUEALING NOISE AND SMOKE COMING FROM ENGINE COMPARTMENT. ENGINE WAS SHUTDOWN AND IN	SPECTION REVEALED THAT ALTERNATOR BELT WAS SLIPPING AROUND PULLEYS. ALTERNATOR WAS FOUND TO BE SEIZED UP.  INSPECTED ALT	ERNATOR WITH BORESCOPE INSIDE OF BLAST TUBE BUT DID NOT FIND REASON FOR SEIZURE. ALTERNATOR WAS SENT BACK FOR WARRANTY C	ONSIDERATION. CAUSE OF SEIZURE AT THIS TIME IS UNKNOWN.		1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P47GL	 
2005082400098	20050824	00098	NM  	2005	8	24	2005FA0001206    	1	20050823	G	3250	2880000000	VALVE           			GULSTM	200   	200         	4500308	NM  										NLG STEERING	BYPASSING       	C				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	07	402LM					082				WHEN THE THRUST REVERSERS WERE DEPLOYED ON THE AIRCRAFT, A VERY LOUD SQUEALING NOISE CAME FROM THE NOSE LANDING GEAR STE	ERING CONTROL VALVE.					2	L	7	2 	4F			RT	A53NM   					 
2005082400099	20050824	00099	NM  	2005	8	24	2005FA0001207    	1	20050823	G	3250	2880000000	VALVE           			GULSTM	200   	200         	4500308	NM  										NLG STEERING	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	402LM	1148 				082				THE NOSE WHEEL STEERING VALVE WAS LEAKING BEYOND LIMITS.						2	L	7	2 	4F			RT	A53NM   					 
2005082400109	20050824	00109	CE  	2005	8	24	2005FA0001208    	1	20050822	G	5230	1014301403	STRUCTURE       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CARGO DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	677BC	8000 				BB86				THE AIRSTAIR DOOR OF THIS AIRCRAFT CLOSES INTO THE CARGO DOOR.  CRACKS WERE FOUND IN THE CARGO DOOR IN THE JAMB AGAINST 	WHICH THE AIRSTAIR CLOSES AND SEALS.  THE CARGO DOOR IS A BONDED ASSEMBLY AND THE JAMB IS A PART OF THIS BOND ASSEMBLY. 	 THREE CRACKS WERE FOUND IN THE JAMB, ONE IN EACH UPPER CORNER AND ONE IN THE LOWER AFTER CORNER.  THIS DOOR, WHILE IT I	S A STANDARD MFG PART WAS INSTALLED IN THIS AIRCRAFT BY STC AT ABOUT 5130 HOURS AIRCRAFT TOTAL TIME.  TOTAL TIME ON THE 	DOOR TODAY IS APPROX. 8000 HOURS.		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005082400110	20050824	00110	CE  	2005	8	24	2005FA0001209    	1	20050822	G	5230	1014301403	STRUCTURE       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CARGO DOOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	677BC	8000 				BB86				THE AIRSTAIR DOOR OF THIS AIRCRAFT CLOSES INTO THE CARGO DOOR.  CRACKS WERE FOUND IN THE CARGO DOOR IN THE JAMB AGAINST 	WHICH THE AIRSTAIR CLOSES AND SEALS.  THE CARGO DOOR IS A BONDED ASSEMBLY P/N 101-430140-3 AND THE JAMB IS A PART OF THI	S BOND ASSEMBLY.  THREE CRACKS WERE FOUND IN THE JAMB, ONE IN EACH UPPER CORNER AND ONE IN THE LOWER AFTER CORNER.  THIS	 DOOR, WHILE IT IS A STANDARD MFG PART WAS INSTALLED IN THIS AIRCRAFT BY STC AT ABOUT 5130 HOURS AIRCRAFT TOTAL TIME.  T	OTAL TIME ON THE DOOR TODAY IS APPROX. 8000 HOURS		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005082500124	20050825	00124	CE  	2005	8	25	2005FA0001210    	1	20050811	G	2750	C1452501S	MOTOR           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					TE FLAP	FAILED          	D			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	80LM	253  				TJ216				FLAP CIRCUIT BREAKER POPS WHEN RETRACTING FLAPS.  FOUND FLAPS GOING OVER TRAVEL IN DOWN DIRECTION, PROBABLY OVERLOADING 	CAUSING OVERLOADING OF FLAP MOTOR.  FOUND MOTOR COILS SHOW SIGNS OF OVERHEATING.  MFG HAS SUPERSEDED MOTOR TO NEW MOTOR.	  (K)				1	L	7	2 	3O	3	O		A23CE   	E8CE				 
2005090100036	20050901	00036	GL  	2005	9	1	2005FA0001211    	3	20050808	G	6110	7503503AF	O-RING          			PIPER 	PA42  	PA421000    	7104225	SO  	GARRTT	TPE331	TPE33114    	01514	NE  	ROTOL	R339	R3394123F8  	GL  	PROP DOME	CUT             	B			GW1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			EA	03	901MT					425527011	P52012			AT THE OUTER MARKER ON APPROACH, THE PILOT NOTICED AN OIL ODOR IN THE ENVIRONMENTAL SYSTEM.  THE AIRCRAFT LANDED WITHOUT	 INCIDENT.  POST FLIGHT WALK AROUND REVEALED OIL LEAK AT THE RT PROPELLER.  MAINTENANCE WAS DISPATCHED AND INVESTIGATION	 REVEALED THE RT PROPELLER DOME PISTON O-RING WAS CUT/ROLLED.  THE O-RING WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO 	SERVICE.  (K)			1	L	7	2 	4T	4	T	RT	A23SO   	E18NE	6	C	P8NE	 
2005082500123	20050825	00123	CE  	2005	8	25	2005FA0001212    	1	20050816	G	2510	551900922	ATTACH BRACKET  			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	120Q					5500332				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  ALSO, PREVIOUS INAPPROPRIATE REPAIR.  CHAIR WAS REPAIRED	 IAW STC SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005090100018	20050901	00018	SO  	2005	9	1	2005FA0001214    	1	20050808	G	5552		HINGE BRACKET   			PIPER 	PA28  	PA28140     	7102802	SO  	ROTAX 	582   	ROTAX582    	55555	EU  					ELEVATOR	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	4243J					2822598				DURING INSPECTION, IT WAS NOTED THAT THE ELEVTOR FORWARD HINGE ATTACH BRACKET WAS CRACKED AT THE AFT BEND IN THE RADIUS 	NEAR THE AFT ATTACH RIVET.  THE OWNER STATED THAT THIS WAS A COMMON OCCURANCE ON THESE MODEL AC AND THAT 2 OTHERS WERE K	NOWN.  (K)				1	L	7	1 	3O	3	I		2A13    	EXPE3I				 
2005082500122	20050825	00122	SO  	2005	8	25	2005FA0001215    	1	20050808	G	5540		HINGE BRACKET   			PIPER 	PA28  	PA28140     	7102802	SO  	ROTAX 	582   	ROTAX582    	55555	EU  					RUDDER	UNSERVICEABLE   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	4243J					2822598				DURING INSPECTION IT WAS NOTED THAT THE RUDDER LOWER HINGE ATTACH FITTING HAD THE AFT 2 ATTACH RIVETS PULLIN OUT OF THE 	REINFORCING CHANNELS.  IT SHOULD BE NOTED THAT THE RUDDER IS ALSO THE VERTICAL FIN ON THIS AIRCRAFT.  RECOMMEND THAT THE	 REST OF THESE (POP-RIVET) FASTENERS BE REMOVED AND AC HARDWARE BE INSTALLED EITHER BOLTS OR STRUCTURAL MS SCREWS.  AC O	WNERS SHOULD ALSO CONSIDER INSTALLING DOUBLER CHANNEL ON THE BOTTOM SIDE OF THIS ATTACH POINT.  (K)			1	L	7	1 	3O	3	I		2A13    	EXPE3I				 
2005090200053	20050902	00053	SO  	2005	9	2	2005FA0001216    	1	20050805	G	3230	2572000	TRANSMISSION    			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	180ML					242609				LANDING GEAR RETRACT SYS WOULD NOT EXTEND GEAR TO A DOWN AND LOCKED POSITION.  SEVERAL ATTEMPTS TO CYCLE GEAR POPPED GEA	R MOTOR CIRCUIT BREAKER.  TRANSMISSION DECOUPLER RELEASED WHEN EMERGENCY GEAR EXTENSION WAS ATTEMPTED, GEAR WOULD NOT GO	 TO DOWN AND LOCKED POSITION.  PILOTS ATTEMPT TO RECYCLE GEAR TO THE RETRACTED POSITION AND THEN TO EXTENDED POSITION AF	TER EMERGENCY GEAR EXTENSION WAS ACTUATED, ADDED TO PROBLEM,  TRANSMSN DECOUPLER WAS IN DIRECT CONTACT WITH GEAR THROUGH	 BOLT, MAKING EXTENSION IMPROBABLE.  SITUATION MAKES POSSIBILITY OF GEAR EXTENSION NEARLY IMPOSSIBLE BECAUSE THE THROUGH	 BOLT CANNOT TRAVEL FAR ENOUGH BACK TO GET DOWN AND LOCKED CONDITION.	1	L	7	1 	3O	3	O		1A15    	E286				 
2005082500116	20050825	00116	NM  	2005	8	25	2005FA0001217    	1	20050824	G	3250	2880000000	CONTROL VALVE   			GULSTM	200   	200         	4500308	NM  										NLG STEERING	BYPASSING       	D				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	402LM					082				WHEN THE THRUST REVERSERS WERE DEPLOYED ON THE AIRCRAFT. A VERY LOUD SQUEALING NOISE CAME FROM THE NOSE LANDING GEAR STE	ERING CONTROL VALVE. THIS IS THE 4TH REPLACEMENT UNIT INSTALLED ON THE AIRCRAFT. THE 5TH UNIT SERIAL NO. IL0138 RESOLVED	 THE PROBLEM. AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A53NM   					 
2005082500117	20050825	00117	NM  	2005	8	25	2005FA0001218    	1	20050823	G	3250	2880000000	CONTROL VALVE   			GULSTM	200   	200         	4500308	NM  										NLG STEERING	BYPASSING       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	402LM					082				WHEN THE THRUST REVERSERS WERE DEPLOYED ON THE AIRCRAFT, A VERY LOUD SQUEALING NOISE CAME FROM THE NOSE LANDING GEAR STE	ERING CONTROL VALVE.					2	L	7	2 	4F			RT	A53NM   					 
2005082500118	20050825	00118	NM  	2005	8	25	2005FA0001219    	1	20050824	G	3250	2880000000	CONTROL VALVE   			GULSTM	200   	200         	4500308	NM  										NLG STEERING	BYPASSING       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	402LM					082				WHEN THRUST REVERSERS WERE DEPLOYED ON THE AIRCRAFT, A VERY LOUD SQUEALING NOISE CAME FROM THE NOSE LANDING GEAR STEERIN	G CONTROL VALVE.					2	L	7	2 	4F			RT	A53NM   					 
2005082500120	20050825	00120	SO  	2005	8	25	2005FA0001220    	1	20050728	G	2810		FUEL TANK       			PIPER 	PA18  	PA18180     	7101880	SO  	LYC   	O360  	O360*       	41514	EA  					LT WING	MISMANUFACTURED 	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	44TC	157  				9941CC				LT WING TANK AT 157 HRS SEAM WELD BROKE OPEN WHILE SITTING ON GROUND CAUSING FUEL LEAK INTO WING.  WELDS EVALUATED FOUND	 TO BE THIN AND OF POOR QUALITY.					1	H	7	1 	3O	3	O		1A2     	E286				 
2005082500121	20050825	00121	SO  	2005	8	25	2005FA0001221    	1	20050728	G	2810		FUEL TANK       			PIPER 	PA18  	PA18180     	7101880	SO  	LYC   	O360  	O360*       	41514	EA  					LT WING	MISMANUFACTURED 	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	44TC	157  				9941CC				LT WING TANK AT 157 HRS SEAM WELD BROKE OPEN WHILE SITTING ON GROUND CAUSING FUEL LEAK INTO WING.  WELDS EVALUATED FOUND	 TO BE THIN AND OF POOR QUALITY.					1	H	7	1 	3O	3	O		1A2     	E286				 
2005082500048	20050825	00048	SO  	2005	8	25	2005FA0001222    	1	20050825	G	2497	7814039	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					BATTERY	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	284HP	1795 				2843372				DURING ROUTINE MAINTENANCE FOUND BATTERY POSITIVE CABLE BEING CHAFED ON CONTROL CABLE TURNBUCKLE IT CAME IN CONTACT WITH	. THE SAWING MOTION OF THE TURNBUCKLE ALMOST WORE THROUGH THE BATTERY CABLE INSULATION JACKET. THE CABLE WAS REROUTED (R	EPOSITIONED) AT LAST 100 HOUR FOR THE SAME REASON. APPARENTLY THE CABLE HAS TAKEN A SET AND KEEPS RETURNING TO ITS ORIGI	NAL BEND CONFIGURATION. RECOMMEND SHORTENING THE CABLE AND CRIMPING THE TERMINAL ENDS 90 DEGREES TO THE LAY OF THE CABLE	.		1	L	7	1 	3O	3	O		2A13    	E286				 
2005090100112	20050901	00112	SO  	2005	9	1	2005FA0001223    	1	20050805	G	1100		PLACARD         			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					SWITCH	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8955P					244412				WHEN DOING OPERATIONAL CHECK AFTER INSTALLATION OF SVS VI UPGRADE KIT ON SVA IA SYSTEM, (AD 2005-11-05).  THE ON/OFF PLA	CARD ON ON/OFF LEVER WAS CONFUSING.  WHEN LEVER VALVE WAS ON OR OPEN, IT LOOKED AS IF IT WERE (OFF) OR CLOSED ON THE PLA	CARD.  (K)				1	L	7	1 	3O	3	O		1A15    	E14EA				 
2005090100105	20050901	00105	EU  	2005	9	1	2005FA0001224    	1	20050811	G	2530	200146901	COVER           			AMD   	FALC90	FALCON900EX 	2730009	EU  										MICROWAVE OVEN	MELTED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21										MICROWAVE OVEN, PN 400-1338-02-L, INSTALLED, EXPERIENCED A (SMOKE EVENT) WHILE FLYING OVER TURKEY.  REP EXAMINED THE UNI	T ON 8/12/2005.  THE MOISTURE COVER HAD OVERHEATED DURING OPERATION WITH A LIGHT LOAD.  SB-MW-02, DATED 4/25/01 TO REPLA	CED MOISTURE COVER WAS NOT INSTALLED.  RECURRENCE COULD BE PREVENTED BY INSTALLING SB-MW-02.  (K)				2	L	7	3 	4F			RT	A46EU   					 
2005083000101	20050830	00101	EU  	2005	8	30	2005FA0001225    	1	20050329	G	3610	FGFB721535200B1	DUCT            			AMD   	FALC90	FALCON900B  	2730171	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					LT BLEED AIR	CRACKED         	B			BG5Y	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	33	103DT	3844 				142				DURING INVESTIGATION OF OIL PRESSURE TRANSMITTER ENGINE NR 1 FOUND HOT AIR LEAK FROM PYLON.  AFTER REMOVAL OF PYLON DOOR	 FOUND BLEED AIR DUCT PROBE TEMPERATURE SUPPORT CRACKED.  NO SIGNIFICANT DAMMAGE FOUND AROUND THE DUCT.  REPLACED BLEED 	AIR DUCT. (K)				2	L	7	3 	4F	4	F	RT	        	E6WE				 
2005083000142	20050830	00142	SO  	2005	8	30	2005FA0001226    	1	20050824	G	5220	86676212	ROD             	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					EMERGENCY EXIT	DEPARTED        	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SO	05	2079N	9493 				447995214				FORWARD EMERGENCY LATCH DID NOT FULLY ENGAGE ALLOWING EMERGENCY EXIT TO DEPART IN FLIGHT.   PROBLEM IS CAUSED BY THE CON	TROLLING ROD BEING TOO SMALL OF DIAMETER TO ENGAGE FORWARD LATCH. ROD BENDS EASILY FEELING LIKE IT FORCED THE FORWARD LA	TCH TO THE ENGAGED POSITION. THERE IS NO WITNESS HOLE TO VIEW ENGAGEMENT OF THE FORWARD LATCH.  IN THIS CASE, A WITNESS 	HOLE WAS MADE IN THE INTERIOR PLASTIC TRIM ON THE LT SIDE OF THE AIRCRAFT AND PAINTED THE LATCH RED SO THAT IT COULD BE 	VIEWED WITHOUT DISMANTLING THE INTERIOR. THE MM DOES NOT MENTION A METHOD TO ENSURE ENGAGEMENT OF THE FORWARD LATCH.		1	L	7	2 	3O	3	O		A19S0   	E286				 
2005083000143	20050830	00143	SO  	2005	8	30	2005FA0001227    	1	20050826	G	3213	40247000	BEARING         	PIPER       		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A11      	52043	NE  					MLG STRUT	DETACHED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	195AA	180  	180  			31T7904001				FOUND UPPER BRGS SEPARATED FROM PISTON TUBES DUE TO PINS MIGRATING INTO PISTON TUBE, TURNING UPPER BRG LOOSE, PINS THEN 	BACKED OUT AND FELL OUTSIDE PISTON TUBE, LOCKED UP MAIN GEAR SHOCK STRUT TRAVEL. CAUSE OF PINS MIGRATING, TURNING UPPER 	BRGS LOOSE WAS THAT PISTON TUBE WAS DRILLED FOR OVERSIZED MAIN GEAR UPPER BRG RETAINER PINS, WHEN UPPER BRGS WERE REPLAC	ED AT O/H THEY WERE NOT REFITTED FOR OVERSIZE PINS, STANDARD PINS WERE USED WHICH ARE SMALLER IN DIAMETER THAN OVERSIZED	 HOLES IN PISTON TUBES ALLOWING THEM TO FALL INTO TUBE AND TURN BRG LOOSE.  SUGGEST THAT PISTON TUBES BE PERMANENTLY MAR	KED TO INDICATE IF OVERSIZED PINS ARE NECESSARY, A WARNING BANNER BE ADDED TO SB779B.	1	L	7	2 	3T	3	T		A8EA    	E4EA				 
2005083000103	20050830	00103	CE  	2005	8	30	2005FA0001228    	1	20050829	G	7602		CONTROL CABLE   			BEECH 	23    	23          	1151202	CE  	LYC   	O320  	O320*       	41508	EA  					MIXTURE	FRACTURED       	H				B				EMER. DESCENT           				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			WP	23	2388Q					M469				THE PILOT LOST ENGINE POWER DURING TAKEOFF.  EXAM FOUND MIXTURE CONTROL CABLE FRACTURED AT 90-DEGREE ANGLE NEAR SET SCRE	W TO CARBURETOR.  FATIGUE ON CABLE INDICATES INSTALLATION ERROR.  FRACTURE COULD NOT BE SEEN DUE TO OUTER SHEATH ON MIXT	URE CONTROL CABLE.				1	L	7	1 	3O	3	O	RT	A1CE    	E274				 
2005090600103	20050906	00103	SW  	2005	9	6	2005FA0001229    	1	20050803	G	1420	MS251822	CONNECTOR       			GULSTM	690TP 	690C        	7630517	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	BATTERIES	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	835CC	1000 	93   			11730				PILOT REPORTED INABILITY OF "SERIES" START WITH A/C.  UPON INSPECTION FOUND + PIN OF RH BATTERY BROKEN OFF IN BATTERY CO	NNECTOR. INSPECTED LH BATTERY FOUND + PIN WITH PARTIAL BURN INDICATION.  REMOVED TOPS OF BOTH BATTERIES AND NOTED INDICA	TION OF HIGH HEAT ABOVE CONNECTOR TERMINAL AREA.  CONTACTED FSI MAINT TRAINING INSTRUCTOR, INDICATED SIMILAR CONDITION F	OUND RECENTLY ON SAME TYPE PLANE AT EAGLE AVIATION.  BATTERY CONNECTOR FOUND TO HAVE LOST TENSION ON CONNECTOR PINS.  PR	EVIOUSLY DISCUSSED SIMILAR PROBLEM WITH GILL MANUFACTURING.  TECHNICIAN SAID WITH LOOSE PINS IN CONNECTOR, CREATES HIGH 	RESISTANCE, WITH HIGH TEMP ON CONNECTOR AREA AND WILL CAUSE AREA TO CRACK DUE TO HEAT.   REPLACED BOTH G-6381E BATTERI	1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2005090100089	20050901	00089	EA  	2005	9	1	2005FA0001230    	2	20050818	G	7322	75107922	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	714VV	509  				15279475	L1507315	K7833		WHILE IN THE PATTERN DOING LANDINGS.  THE ENGINE QUIT WHEN THE POWER WAS REDUCED ON BASE LEG TO LAND.  AN UNEVENTFUL LAN	DING WAS MADE, AND AFTER CLIMBING OUT OF AIRCRAFT, FUEL WAS COMING OUT OF THE COWLING.  UPON FURTHER INVESTIGATION FOUND	 1 OF THE FUEL BOWL FLOATS TO BE .7500 FULL OF FUEL AND THE OTHER WAS .2500 FULL.  CAUSING THE FLOAT TO SINK AND CAUSING	 THE FUEL AIR MIXTURE TO BE TOO RICH AT REDUCED POWER SETTINGS.  CAUSING THE ENGINE TO FLOOD OUT AND QUIT ON THE APPROAC	H TO LAND.  (K)		1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2005090100127	20050901	00127	SO  	2005	9	1	2005FA0001231    	1	20050808	G	2497	7814039	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					BATTERY	CHAFED          	B			C85R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	284HP	1794 				2843372				DURING ROUTINE MAINTENANCE, FOUND BATTERY POS CABLE BEING CHAFED ON CONTROL CABLE TURNBUCKLE IT CAME IN CONTACT WITH.  T	HE SAWING MOTION OF THE TURNBUCKLE ALMOST WORE THRU THE BATTERY CABLE INSULATION JACKET.  THE CABLE WAS REROUTED (REPOSI	TIONED) AT LAST 100 HR FOR THE SAME  REASON.  THE CABLE HAS TAKEN A SET AND KEEPS RETURNING TO ITS ORIGINAL BEND CONFIGU	RATION.  RECOMMEND SHORTENING THE CABLE AND CRIMPING THE TERMINAL ENDS 90 DEGREES TO THE LAY OF THE CABLE.  (K)			1	L	7	1 	3O	3	O		2A13    	E286				 
2005090100131	20050901	00131	GL  	2005	9	1	2005FA0001232    	1	20050819	G	2820	11443004	LINE            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					FUEL SYS	CHAFED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	2354B	750  				0077				MAIN FUEL SUPPLY LINE FROM FUEL SELECTOR TO FIREWALL HAD HOLE CHAFED IN IT.  THE WIRE BUNDLE TO THE CB PANEL WAS CHAFING	 LINE.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005090200002	20050902	00002	SO  	2005	9	2	2005FA0001237    	2	20050830	G	8520		CONNECTING ROD  			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					ENGINE	BROKEN          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NM	04	7600M		848  			55900	62099A			NR 3 CONNECTING ROD PENETRATED CASE. ENGINE TSO 848 HRS.  LAST ENGINE O/H 06/10/1964 OR 41 YEARS AGO. MANUFACTURER RECOM	MENDS 12 YEARS IAW SIL 98-9.					1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2005090200025	20050902	00025	CE  	2005	9	2	2005FA0001238    	1	20050829	G	2731	S26376Z11	PIN             	CESSNA      		CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ACTUATOR	BACKED OUT      	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	07	6239Y	92   	92   		21063131	21064304				THE PIN THAT HOLDS THE DRIVE GEAR ONTO THE ACTUATOR DRUM HAD FALLEN OUT WHEN THE AIRCRAFT WAS TRIMMED NOSE UP. THE PILOT	 HAD TO PUSH ON THE YOKE WITH GREAT FORCE TO PITCH THE AIRCRAFT DOWN.  AFTER EXAMINING THE ACTUATOR, NOTICED THAT THE HO	LE FOR THE PIN WAS ELONGATED AND WOULD NOT HOLD A NEW PIN.  RECOMMEND SOME SORT OF CLAMP BE INSTALLED TO INSURE THE PIN 	COULD NOT BACK OUT.			1	H	7	1 	3O	3	O		3A21    	E8CE				 
2005090600108	20050906	00108	CE  	2005	9	6	2005FA0001242    	1	20050829	G	2731	S26376Z11	PIN             	CESSNA      		CESSNA	210   	T210N       	2073456	CE  										ZONE 300	BACKED OUT      	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			SW	99	6239Y	92   	92   		21063131	21064304				THE PIN THAT HOLDS THE DRIVE GEAR ONTO THE ACTUATOR DRUM HAD FALLEN OUT WHEN THE AIRCRAFT WAS TRIMMED NOSE UP. THE PILOT	 HAD TO PUSH ON THE YOKE WITH GREAT FORCE TO PITCH THE AIRCRAFT DOWN. AFTER EXAMINING THE ACTUATOR I NOTICED THAT THE HO	LE FOR THE PIN WAS ELONGATED AND WOULD NOT HOLD A NEW PIN. I WOULD RECOMMEND SOME SORT OF CLAMP BE INSTALLED TO INSURE T	HE PIN COULD NOT BACK OUT.			1	H	7	1 	3O				3A21    					 
2005090200054	20050902	00054	CE  	2005	9	2	2005FA0001244    	1	20050516	G	5341	08112763	ATTACH FITTING  			CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	WING TO BODY	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	700MA					310J0181	115658511	681031		DURING THE ANNUAL INSPECTION, THE WING FITTING WAS FOUND TO BE CORRODED SO SEVERE THAT IT WAS ALMOST .2500 OF THE WAY TH	RU THE FITTING. PICTURES ENCLOSED THAT SHOW DAMAGE.  FITTING WAS LOCATED ON THE LT SIDE, AFT TOP FITTING. (K)					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
2005090200102	20050902	00102		2005	9	2	2005FA0001245    	1	20050818	G	2140	94E423	SWITCH          																	HEATER ASSY	SHORTED         	B			IS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										FOUND COMBUSTION AIR PRESSURE SWITCH (PN 94E42-3) CLOSED AT ALL TIMES (HAS CONTINUITY).  THIS IS A NORMALLY OPEN (N.O.) 	SWITCH AND CLOSES WHEN IT SENSES AIR PRESSURE AT THE HIGH PRESSURE PORT.  WITH IT CLOSED AT ALL TIMES, THIS SAFETY DEVIC	E WILL TELL THE HEATER THAT IT HAS COMBUSTION AIR, WHETHER ITS THERE OR NOT.  NOT GOOD IF THE COMBUSTION AIR BLOWER FAIL	S.  THIS 94E42 SERIES SWITCH DOES NOT REQUIRE INSPECTION IAW AD AT THIS TIME.  TO PREVENT REOCCURRENCE, RECOMMEND TESTIN	G THESE COMBUSTION AIR PRESSURE SWITCHES IN CONJUNCTION WITH THE PRESSURE DECAY TEST MANDATED BY AD.															 
2005090200104	20050902	00104		2005	9	2	2005FA0001246    	4	20050815	G	3497	3446J1B	CONNECTOR       			BEECH 	MU300 	400A        	1155402	CE  										WIRE BUNDLE	LOOSE           	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	36997	514  				RK397				INVESTIGATED IN-FLIGHT (GPWS), (TERR), AND (WINDSHEAR) FAILE INDICATIONS.  SYSTEM FAILURES CONFIRMED ON GROUND.  FOUND A	IRFRAME WIRING CONNECTOR (3446J1B UNSEATED FROM EGPWS UNIT CONNECTOR DUE TO TENSION ON WIRING BUNDLE.  RESEATED CONNECTO	R PINS AND RESECURED WIRING BUNDLE AS REQUIRED TO RELIEVE TENSION.  REINSTALLED CONNECTOR TO EGPWS UNIT, OPS CHECK OK.  	(K)			2	H	7	2 	4F			RT	A16SW   					 
2005090200103	20050902	00103	SO  	2005	9	2	2005FA0001247    	1	20050729	G	2821		FILTER          			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	CONTAMINATED    	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	8788P					244240				THIS STATION RECEIVED REQUEST FROM REGULAR CUSTOMER, THAT WAS FERRYING AIRCRAFT.  AIRCRAFT ENGINE FAILED TO MAKE FULL PO	WER THEN QUIT ON GROUND.  CREW WAS SENT TO REMOTE AIRFIELD TO TROUBLESHOOT.  AFTER EXTENSIVE TROUBLESHOOTING, FOUND FUEL	 INJECTORS CLOGGED BY DIRT.  FUEL FILTER SCREEN AND FILTER REMOVED AND FOUND BADLY CONTAMINATED.  (PHOTO) AIRCRAFT HAD J	UST RECEIVED A FRESH ANNUAL INSP.  FILTRS AND NOZZLES WERE CLEANED, FUEL LINES PURGED AND ENGINE RUN MADE FULL POWER.  F	ILTERS THEN CHECKED AGAIN AND WERE CLEAN AT THIS TIME.  POOR MAINT AND INSP DETERMINED TO MAJOR FACTOR CONTRIBUTING TO M	ALFUNCTION.  EXPERIENCED PILOT RECONIZED PROBLEM ENGINE COULD HAVE FAILED WHILE AIRBORNE. (K)	1	L	7	1 	3O	3	O		1A15    	E14EA				 
2005090200106	20050902	00106	SO  	2005	9	2	2005FA0001249    	2	20050117	G	8500	GTSIO520L	ENGINE          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	HARTZL	HCC3Y	HCC3YN      	GL  	RIGHT	SEIZED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	112AL	30   				421C0697	610449	DG675B		OIL PRESSURE NEVER CAME UP AFTER PILOT STARTED ENGINE AND ENGINE SEIZED.  TIME ON ENGINE: 03.3.  ENGINE WAS REMOVED AND 	ANOTHER ENGINE WAS PROVIDED, UNDER WARRANTY TO TAKE ITS PLACE.  PN: GTSIO520L/ SN: 292065R					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P25EA	 
2005090200105	20050902	00105	SO  	2005	9	2	2005FA0001250    	2	20050805	G	8500	GTSIO520L	ENGINE          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	HARTZL	HCC3Y	HCC3YN      	GL  	RIGHT	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	112AL	31   				421C0697	292065R	DG675B		DURING MAINTENANCE CHECK, RUNNING THE RT ENGINE AT 1200 RPM, ENGINE LOST OIL PRESSURE AND SHUT DOWN.  THIS IS THE 2ND EN	GINE THAT HAS FAILED WITHIN 30 HOURS OF INSTALLATION.  BOTH ENGINE HAVE BEEN FROM SAME FACILITY.					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P25EA	 
2005090200107	20050902	00107	CE  	2005	9	2	2005FA0001251    	1	20050314	G	8120	S19211	CLAMP           	CESSNA      		CESSNA	337   	T337G       	2075726	CE  	CONT  	IO360 	IO360*      	17025	CE  					TURBOCHARGER	SEPARATED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	289					P3370233				EXHAUST PIPE TO TURBOCHARGER CLAMP FOR FRONT ENGINE CRACKED AT SPOT-WELD AND SEPARATED ON TAKEOFF.  WHEN THIS HAPPENED, 	THE EXHAUST PIPE DEPARTED THE AIRCRAFT AND THE EXHAUST SCORCHED THE ENGINE COWLING AND FIREWALL.  (K)					1	H	7	2 	3O	3	O		A6CE    	E1CE				 
2005090600124	20050906	00124	CE  	2005	9	6	2005FA0001252    	1	20050621	G	7160	AM106735	AIR FILTER      	AIRESRCH    		CESSNA	320   	320E        	2074514	CE  	CONT  	O520  	TSIO520E    	17040	SO  					TURBO CHARGER	FAILED          	G				E				ENGINE SHUTDOWN         				C	Y		F.O.D.                    	ENGINE STOPPAGE           		TO	TAKEOFF        	1			NM	05	3438Q				YE024103	320E0038	1828000R			ACCIDENT INVESTIGATION FOUND RIGHT TURBO CHARGER COMPRESSOR INGESTED PAPER AND JAMMED.  IT WAS DETERMINED THAT THE PAPER	 WAS THE INSTRUCTIONS AND APPLICATION CHART FOR THE FILTER.  A CHECK OF A NEW REPLACEMENT DONALDSON (FAA/PMA FOR CESSNA 	FILTERS) FILTER REVEALED THAT THE INSTRUCTIONS AND A STICKER WERE INSERTED INSIDE THE CANISTER TYPE FILTER.  THE INSTRUC	TIONS (FOLDED INTO A QUARTER SHEET) WERE LAYING (MOLDED) ON THE COURSE INSIDE SCREEN OF THE FILTER. IN-STOCK FILTERS SHO	ULD BE INSPECTED AND INSTRUCTIONS PLACE ON THE OUTSIDE OF THE FILTER.		1	L	7	2 	3O	3	O		3A25    	E8CE				 
2005090600126	20050906	00126	SO  	2005	9	6	2005FA0001253    	1	20050829	G	8010	MX6220	STARTER         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					RT ENGINE	BROKEN          	B				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	21	191ND	60   	60   			4495003	L71871A			PILOT ATTEMPTED START BUT STARTER WOULD NOT CRANK. UPON VISUAL INSP OF STARTER FOUND BENDIX HAD STUCK IN THE EXTENDED PO	SITION ON THE PREVIOS START CAUSINING THE GEAR TO BREAK AND BREAKING 2 MOUNTING PADS OF THE BENDIX HOUSING. DAMAGE WAS A	LSO NOTED ON THE ENGINE RING GEAR. STARTER AND RING GEAR REPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3O	3	O		A19S0   	E286				 
2005091200185	20050912	00185	EU  	2005	9	12	2005FA0001255    	1	20050714	G	2913	41222	SHAFT           			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					DRIVE	SHEARED         	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	401JW				AH49775	46				WHILE PERFORMING AN ENGINE GROUND OPERATION THE HYDRAULIC PUMP OUTPUT CEASED.  A SHEARED PUMP EXTERNAL DRIVE SHAFT WAS D	ISCOVERED.  SYSTEM REGULATION AND RETURN FILTERS AND PUMP HOSES SHOW NO INDICATIONS OF METAL CONTAMINATES.  THE PUP STUB	 SHAFT STILL TURNS BY HAND.  REMOVED PUMP ASSEMBLY FROM SERVICE AND INSTALLED AN OVERHAULED PUMP.  (K)				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005092000074	20050920	00074	SO  	2005	9	20	2005FA0001256    	1	20050812	G	3000	1H2418	VALVE           			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					DE-ICE SYSTEM	DEFECTIVE       	B			BNGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	772DS	534  				4636338				DE-ICE PRESSURE MANIFOLD VALVE DEFECTIVE IAW SL.  (K)						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2005103100113	20051031	00113	CE  	2005	10	31	2005FA0001257    	1	20050718	G	2910	NAS16126	O-RING          			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					A-HYD MANIFOLD	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	19	15RL	1003 			0255	7500165				NAS1612-6, O-RING LOCATED ON AN814-6K, PLUG INSTALLED IN (A) HYDRAULIC SYSTEM MANIFOLD, PN 6717277-3 FAILED, CAUSING LOS	S OF SYSTEM (A) HYDRAULIC FLUID AND SUBSEQUENT PILOT SHUTDOWN OF (A) HYDRAULIC SYSTEM.  FOUND TORQUE ON PLUG TO BE LESS 	THAN 30 INCH POUNDS ALLOWING HYDRAULIC FLUID UNDER PRESSURE TO DAMAGE O-RING.  NO PROVISIONS FOR SAFTEYING THE PLUG ARE 	PROVIDED.  RECOMMEND A DRILLED HEAD PLUG BE INSTALLED AND PROPERLY SAFETIED TO PREVENT LOSS OF TORQUE ON PLUG.  (K)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005103100109	20051031	00109	NE  	2005	10	31	2005FA0001258    	2	20050806	G	8530	399359	CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R134053     	52016	NE  					NR 8	FAILED          	G			HFTG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	9041M		1026 			1703	2P100353			FOUND NR 8 CYLINDER TO HAVE RUPTURED OUTWARD DURING CRASH INVESTIGATION.  ENGINE WAS BEING INSPECTED IAW AD.  PERHAPS TH	IS AD NEEDS TO BE RE-VISITED AS THIS PROBLEM IS TOO COMMON.  (GL19299504540) (K)					1	Q	7	1 	3R	3	R		1A16    	5E2				 
2005091500123	20050915	00123	CE  	2005	9	15	2005FA0001259    	1	20050901	G	8011	643259	ADAPTER         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					STARTER	DAMAGED         	B			VA1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	617CC	800  				421C0897	808298R			METAL IN ENGINE.  STARTER ADAPTER, CRANK GEAR HAD TEETH MISSING.  SB WAS NEVER C/W.  (K)						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005092000220	20050920	00220	EA  	2005	9	20	2005FA0001260    	2	20050822	G	8550		B-NUT           			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					CRANKCASE	LOOSE           	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	13	7546F					28770	L453055A			ENGINE OIL PRESSURE LINE B-NUT AT GEAR CASE LOST TORQUE AND THE ENGINE LOST ALL OIL.  LACK OF LUBRICATION CAUSED FAILURE	 OF THE NR2 CONNECTING ROD BEARING.  (K)					1	H	7	1 	3O	3	O		A759    	1E12				 
2005092600183	20050926	00183	CE  	2005	9	26	2005FA0001261    	1	20050810	G	3231		LINE            			CESSNA	210   	210         	2073402	CE  	CONT  	O470  	IO470E      	17026	SO  					NLG DOOR	MISMANUFACTURED 	D			LX2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	9408T					57208	8867871ER			FERRULE ON NLG DOOR OPEN LINE CRACKED ALONG STRESS RISER CREATED BY FLARING TOOL VISE.  RESULTED IN LOSS OF HYDRAULIC FL	UID TO OPERATE LANDING GEAR.  AIRCRAFT LANDED WITH MAIN LANDING GEAR UP.  (K)					1	H	7	1 	3O	3	O	RT	3A21    	3E1				 
2005103100064	20051031	00064	SO  	2005	10	31	2005FA0001262    	1	20050727	G	3233	8360004	BOLT            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					ACTUATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	527TB					4636166				ON PERFORMING A ROUTINE TIRE CHANGE, I NOTICED THE RT MAIN ACTUATOR BOLT HAD BROKEN THE SAFETY WIRE TO THE TRUNION AND H	AD BACKED OUT UNTIL THERE WERE NO  THREAD ENGAGEMENT TO TRUNION.  ROD END SEIZED ON ACUTATOR OR FAILED TORQUE ON MAINTEN	ANCE.  RECOMMEND PREFLIGHT CHECKLIST.  (K)				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2005092000043	20050920	00043	CE  	2005	9	20	2005FA0001263    	1	20050805	G	5610	66004047	WINDSHIELD      			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE7313A    	01518	WP  					COCKPIT	DELAMINATED     	B			DELR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	32KJ					93				WINDSHIELD HAS CONSIDERABLE DELAMINATIONS AT AREA BELOW DEFOG NOZZLE.  DIMENSIONS OF AREA 3.5 INCH X 2 INCH.  DEPTH OF D	ELAMINATIONS UP TO .125.  THIS IS NOT THE FIRST WINDSHIELD FOUND IN THIS CONDITION.  PROBABLE CAUSE IS ALCOHOL GETTING B	ETWEEN THE WINDSHIELD AND DEFOG ASSEMBLY. (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005103100103	20051031	00103	CE  	2005	10	31	2005FA0001264    	1	20050822	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BREAKER	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8240T	121  				CE1542				ON ROUTINE GEAR INSPECTION, THE MECHANIC NOTICED THE GEAR WAS VERY SLOW ON RETRACTION.  ON TROUBLESHOOTING THE MECHANIC 	FOUND THE RELAY WAS INTERMITTENT, PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE. 	 (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005091500017	20050915	00017	SO  	2005	9	15	2005FA0001265    	2	20050823	G	7313	627335D13A	NOZZLE          			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE FUEL	BROKEN          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T	1433 				CE1547	825913R			ON ROUTINE PHASE INSPECTION THE FUEL INJECTOR NOZZLES WERE REMOVED FOR CLEANING, AT THIS TIME THE MECHANIC DIDNT NOTICE	 ANY DEFECTS.  THE NOZZLES WERE THEN PLACED IN A CLEANING TANK AND AFTER REMOVING THEM FROM THE TANK THE MECHANIC NOTICE	D THE RING THAT THE FUEL INJECTOR LINE SEATS TO WAS BROKEN AWAY FROM THE NOZZLE, RECOMMENDATION AT THIS TIME IS TO DO A 	THROUGH INSPECTION OF THE NOZZLES WHEN THEY ARE REMOVED FOR CLEANING.			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005090800130	20050908	00130	EU  	2005	9	8	2005FA0001266    	1	20050825	G	2510	5110023000	SEAT            			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					BACKREST FRAME	BROKEN          	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	882GA	2360 				082				DURING REUPHOLSTERY OF PILOT SEAT, FOUND BACKREST FRAME BROKEN.  CONTACTED MFG AND WAS GIVEN REPAIR TO ADD WELDED DOUBLE	RS.  (CE09200505050)  (K)					2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2005090800025	20050908	00025	CE  	2005	9	8	2005FA0001267    	1	20050825	G	7120	71	MOUNT           			BEECH 	77    	77          	1153007	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	38026					WA202	L2127315	K3278		THE UPGRADED ENGINE MOUNT WAS FOUND CRACKED.  A PLUG USED TO RELIEVE WELDING PRESSURE AND ADD ADD LINSEED OIL APPEARS TO	 THE THE PROBLEM (STRESS RISER? ETC) THE LINSEED OIL ESCAPED AND MADE A PERFECT CRACK INDICATION WITHOUT USE OF DYE PENE	TRANT.  THE OLDER STYLE, -1 MOTOR MOUNT DOES NOT HAVE PLUGS IN THIS AREA.  (K)				1	L	7	1 	3O	3	O		A30CE   	E223	5	N	P9045	 
2005091500014	20050915	00014	SO  	2005	9	15	2005FA0001272    	2	20050825	G	8520	639468	CRANKCASE       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					ENGINE	CRACKED         	G				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			EA	21	711TX	3459 	514  			421C0165	241213R			OPERATOR COMPLAINT OF SMALL OIL LEAKS IN CRUISE FLIGHT.  CLEANED ENGINE AND RAN, TO INSPECT FOR OIL LEAKS.  AFTER EXTENS	IVE VISUAL INSPECTION AND DYE PENETRANT INSPECTIONS (3) CRACKS IN THE CRANKCASE WERE DISCOVERED.  (2) CRACKS WERE NOTED 	EXTENDING FROM TOP FORWARD CASE HALF BOLT HOLES.  (1) CRACK WAS NOTED ON THE TOP LEFT CASE UNDER THE MAGNETO AREA.  (K)				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005103100148	20051031	00148	EU  	2005	10	31	2005FA0001274    	1	20050907	G	6720	704A3413023	CONTROL CABLE   			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	FAILED          	D				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	353FB	303  				3926				IN FORWARD FLIGHT, TAIL ROTOR CONTROL DEVELOPED SEVERE BINDING.  FOUND CONTROL CABLE TO HAVE INTERNAL FAILURE.  ALIGNMEN	T OF CABLE THROUGH THE REAR BULKHEAD TO THE BELLCRANK CAUSING SIDE PRESSURE ON THE INTERNAL SHAFT IN THE CABLE POSSIBLY 	CAUSING THE BINDING.  (K)				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005092600091	20050926	00091		2005	9	26	2005FA0001276    	1	20050831	G	8011	ES6462751	STARTER         																	ENGINE	DAMAGED         	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										STARTER NEW OUT OF BOX, TOO TIGHT.  8130-3 STATES ONLY APPLICABLE FOR MFG SRS, BUT IS APPLICABLE TO MANY OTHER MFG ENGIN	ES.																		 
2005091500008	20050915	00008	NM  	2005	9	15	2005FA0001279    	1	20050824	G	3820	ES71183206400DK	WATER HEATER    			BOEING	767   	7672AX      	1387000	NM  	GE    	CF6   	CF680       	30025	NE  					GALLEY	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	767A					33685				FA COMPLAINED ABOUT NO HOT WATER AT GALLEY SINK SHORTLY BEFORE LANDING.  ONCE ON GROUND, MAINTENANCE EXPOSED WATER HEATE	R, GOT HEAVY BURNED SMELL.  REMOVED FALSE PANEL COVERING WATER HEATER, NOTED THAT NO CB EITHER ON UNIT OR ON GALLEY CB P	ANEL HAD TRIPPED.  DECIDED TO LOOK AT INSIDE OF INSTALLED UNIT TO SEE IF THERE WAS SOMETHING THAT COULD BE REPAIRED.  LO	OKED AS THOUGH THERE WAS A FIRE INSIDE OF UNIT.  IT BURNED ITSELF OUT, NO EXTERNAL DAMAGE WAS DONE.  PRIOR TO OPENING AR	EA WHERE HEATER IS INSTALLED, THERE WAS NO SMELL ANYWHERE IN GALLEY FROM THE FIRE, NO CB TRIPPED.  UNIT WAS REMOVED FROM	 AC AND SENT TO THE MFG. NO REASON OR CAUSE HAS BEEN FOUND AT THIS TIME.  (SW05200511531) (K)	2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005092000073	20050920	00073	EU  	2005	9	20	2005FA0001280    	1	20050829	G	2120	14632112	SHUTOFF VALVE   			AMD   	FALC20	FALCONF     	2720306	EU  	GE    	CF700 	CF700*      	30010	NE  					P3	INTERMITTENT    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	312K					324				INSTALLED O/H VALVE.  PERFORMED LEAK CHECKS OF VALVE WITH NO DEFECTS NOTED.  AC NOTED LOW AIRFLOW ON GROUND.  OPS CHECKE	D PRESSURIZATION ON GROUND AND FOUND THAT AC WOULD NOT PRESSURIZE.  TROUBLESHOT VALVE AND DETERMINED THAT THE VALVE INST	ALLED WAS MALFUNCTIONING.  VALVE WOULD ONLY MOVE INTERMITTENTLY.  FURTHER REVIEW FOUND THAT THE VALVE WAS PREVIOUSLY O/H	 DUE TO SAME REASON.  NO RECOMMENDATIONS FOR PREVENTING RECURRANCE EXCEPT FOR METHODS AND STANDARDS REVIEW OF THE REPAIR	 STATION THAT OVERHAULED THE PART.  (K)		2	L	7	2 	4F	4	F		A7EU    	E7EA				 
2005091500005	20050915	00005	SO  	2005	9	15	2005FA0001281    	1	20050823	G	5270	587817	SWITCH          			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541*    	41539	EA  					CABIN DOOR	OPEN            	B			E81R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	03	527CB					31P7730001				CONFIRMED REPORT OF CABIN DOOR UNSAFE ANNUNCIATOR REMAINING ILLUMINATED W/DOOR CLOSED.  FOUND UPPER CENTER BAYONET RECEP	TACLE SWITCH TO HAVE OPEN CONTINUITY IN ANY POSITION.  FOUND WIRE L11T PREVIOUSLY JUMPERED TO DOOR SEAL PRESSURE SWITCH 	GROUND AND DOOR WARNING RELAY JUMPERED AROUND FROM L11T CONNECTION TO GROUND CONNECTION BY PERSONS OR FACILITY UNKNOWN. 	 NO RECORDS IN US AC LOGBOOKS OF REPAIRS IN THIS AREA.  REPLACED BAYONET SWITCH W/NEW SWITCH AND REPAIRED/CORRECTED SYST	EM WIRING TO AS SHOWN IN SRM WIRING DIAGRAMS.  DOOR WARNING ANNUNCIATOR OPERATIONAL CHECKS NOW NORMAL.  (K)		1	L	7	2 	3O	3	O		A8EA    	E19EA				 
2005091500010	20050915	00010	CE  	2005	9	15	2005FA0001282    	1	20050817	G	3260	5EN16	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG	FAILED          	B			E81R	O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			GL	03	430CW					RK30				LANDING GEAR SYS RED (GEAR UNSAFE) WARNING LIGHT REMAINED ILLUMINATED FOLLOWING GEAR EXTENSION WHILE LANDING.  ALL (3) G	REEN LANDING GEAR DOWN AND LOCKED POSITION INDICATING LIGHTS ILLUMINATED.  AC FERRIED FOR REPAIRS.  FOUND LT MLG DOOR PO	SITION SWITCH S097 FAILED INTERNALLY.  REPLACED S097 SWITCH ASSY WITH SERVICEABLE UNIT, LANDING GEAR RETRACT/EXTENSION S	YSTEM TESTS NORMAL.  TRANSIENT AIRCRAFT, UNABLE TO DETERMINE TT ON FAILED SWITCH.  SUGGEST THAT LG POSITION INDICATING S	WITCHES BE SCHEDULED REPLACEMENT ITEMS.  PROBABLY IN CONJUNCTION WITH LANDING GEAR 7400 HR/5000 CYCLE INSPECTIONS.  SUGG	EST REPLACING POSITION SWITCHES WITH IMPROVED HERMETICALLY SEALED TYPE SWITCHES AS THEY REQUIRE REPLACEMENT.  (K)	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2005092600084	20050926	00084	SO  	2005	9	26	2005FA0001283    	2	20050907	G	7322	MA3SPA	CARBURETOR      			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99							1996739A			ENGINE HAD BAD HESITATION ON TAKEOFF ACCELERATION.  SURGING OCCURRED DURING CLIMB WITH RPM FLUCTUATIONS OF +/- 50-75 RPM	.  AIRCRAFT AND ENGINE FUEL SCREENS WERE REMOVED AND INSPECTED 3 TIMES IN THE LAST 50 HOURS WITH NO EVIDENCE OF CONTAMIN	ATION.  FUEL LINE TO CARBURETOR WAS REPLACED.  NONE OF THESE ACTIONS WERE OF HELP.  CARBURETOR WAS REMOVED AND SENT BACK	 TO FACTORY SERVICE CENTER.  THEY REPORTED ORANGE PARTICLES IN THE BOWL AND AN ORANGE BUILDUP IN THE VENTURI AREA.  SINC	E NO CONTAMINATION WAS FOUND IN EITHER THE CARB OR AIRCRAFT SCREENS OR THE FUEL SAMPLES; THE SUBMITTER SUSPECTS CONTAMIN	ATION DURING ASSEMBLY BY EITHER PRESERVATIVE OR SOME OTHER SUBSTANCE.  CARB HAD 101 HOURS SINCE RECONDITIONING.  (K)	1	H	7	1 	3O	3	O		3A19    	E252				 
2005091900029	20050919	00029	SO  	2005	9	19	2005FA0001284    	1	20050908	G	2497	PF1416	WIRE            	PRESTOLITE  		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					ALTERNATOR	CHAFED          	G				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			NE	01	2548Z				VARIOUS	278054047				LT ALT NR1 FAILED. REPAIRED WIRING CONNECTIONS, REPLACED ALT AND REG. LT ALT NR 2 FAILED ON T/O.  FOUND FIELD WIRE SEG I	NNER INSULATION CRACKED, BARE UNDER SHIELDING. HEATSHRINK TUBING ADDED TO MAKE INSTALLATION NEATER, FORCED SHIELDING INT	O CONTACT WITH PRIMARY CONDUCTOR BRINGING FIELD TO GROUND. SPLICED IN NEW WIRE SEG. LT ALT NR3 FAILED AFTER 2 FLIGHTS. F	OUND FIELD WIRE SEG PF-14-16 AT WING CNTR LAYING ON BELLY SKIN AND CHAFED THROUGH.   WING CNTR DID NOT HAVE STRAIN RELIE	F BACKSHELL INSTALLED,WAS NOT SECURED AWAY FROM SKIN. CHAFED AREA WAS 2 INCHES OF CONNECTOR.  SPLICED NEW WIRE SEG, SECU	RED WIRE BUNDLE CLEAR OF SKIN.  REPLACED ALT (INSTALLED NR 4) AND REG.  FIELD WIRE IS NOT PROTECTED BY A FUSE OR CB.	1	L	7	2 	3O	3	O		1A10    	E14EA				 
2005092600064	20050926	00064	SW  	2005	9	26	2005FA0001285    	1	20050827	G	5210	269A475511	HINGE           			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					PAX DOOR	FAILED          	B			HA4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	1542D	367  				0198				THE DOOR PIN PORTION OF THE HINGE, WHICH IS RESPONSIBLE RETAINING THE DOOR, FAILED.  THIS LEAVES THE DOOR CONNECTED AT O	NLY ONE POINT AND AN IN-FLIGHT FAILURE COULD POTENTIALLY ALLOW THE DOOR SEPARATE FROM THE AIRCRAFT.  (K)					1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2005092600065	20050926	00065	SW  	2005	9	26	2005FA0001286    	1	20050830	G	5343	269A475511	HINGE           			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					PAX DOOR	BROKEN          	B			HA4R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	1567C	304  				0203				THE DOOR PIN PORTION OF THE HINGE, WHICH IS RESPONSIBLE RETAINING THE DOOR, BROKE IN FLIGHT AND THE DOOR WAS UNSECURED A	T THE LOWER CONNECTING POINT.  THE FLIGHT CREW LANDED, THE DOOR WAS SECURED TEMPORARILY AND THE AIRCRAFT RETURNED TO THE	 MAINTENANCE FACILITY.  (K)				1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2005103100105	20051031	00105	SW  	2005	10	31	2005FA0001287    	1	20050829	G	2497		WIRE HARNESS    			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					CONTROL PANEL	BURNED          	B			MPYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	366GJ	170  				290366				WHEN TROUBLESHOOTING, THE SQUAWK (RECOGNITION LIGHTS ON ALL THE TIME) WE FOUND CARRED WIRE INSULATION IN THE WIRE HARNES	S FEEDING THE OVERHEAD BANK OF SWITCHES THAT CONTROL THE SHIPS EXTERIOR LIGHTING.  WE TRACED THE CHARRED INSULATION TO A	N OVERHEATED CONDITION IN THE RECOGNITION LIGHT CIRCUIT.  A SUBSTANDARD CRIMP ON A WIRE TERMINAL WAS REPAIRED AND THE OV	ERHEATED CONDITION WAS NOT NOTED AFTER THAT.  THE (LIGHTS ON ALL THE TIME) SQUAWK WAS DUE TO THE CHARRED INSULATION ALLO	WING POWER DIRECTLY TO THE RECOG LIGHTS, CIRCUMVENTING THE SWITCH.  (K)		1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2005092000075	20050920	00075	SW  	2005	9	20	2005FA0001288    	1	20050829	G	2497		WIRE HARNESS    			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					COCKPIT	BURNED          	B			MPYR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	17	366GJ	170  				290366				WHEN TROUBLESHOOTING THE SQUAWK (RECOGNITION LIGHTS ON ALL THE TIME), FOUND CHARED WIRE INSULATION IN THE WIRE HARNESS F	EEDING THE OVERHEAD BANK OF SWITCHES THAT CONTROL THE SHIPS EXTERIOR LIGHTING.  TRACED THE CHARRED INSULATION TO AN OVER	HEATED CONDITION IN THE RECOGNITION LIGHT CIRCUIT.  A SUBSTANDARD CRIMP ON A WIRE TERMINAL WAS REPAIRED AND THE OVERHEAT	ED CONDITION WAS NOT NOTED AFTER THAT.  THE (LIGHTS ON ALL THE TIME) SQUAWK WAS DUE TO THE CHARRED INSULATION ALLOWING P	OWER DIRECTLY TO THE RECOG LIGHTS, CIRCUMVENTING THE SWITCH.  (K)		1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2005103100116	20051031	00116	NE  	2005	10	31	2005FA0001289    	2	20050621	G	7261	1710M83P05	SEAL            			BOEING	777   	777*        	UTILUSE	NM  	GE    	GE90  	GE9090B     	 	NE  					HPT ROTOR	FAILED          	B			QEMY	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	35		11468			M900188	HZAKA1				DURING ENGINE O/H UPON EXPOSURE OF THE HPT ROTOR, EVIDENCE OF HEAT DISTRESS WAS NOTED AT THE AFT SEAL LOCATION.  THE HPT	R AFT SEAL SUMP SEAL TEETH AND OIL SLING PRESENTED PLASTIC DEFORMATION AND HEAT DISTRESS.  THE COMPONENT WAS RETURNED TO	 OEM FOR INVESTIGATION.  (K)				2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
2005091900049	20050919	00049	EA  	2005	9	19	2005FA0001290    	2	20050915	G	7261	AA48111	OIL FILTER      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	LEAKING         	D				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			SO	15	431ER	21   				172S9165	L3042351A			INSPECTION OF AIRCRAFT FOLLOWING PILOTS COMPLAINT OF BURNING SMELL IN COCKPIT, AND OIL ON LOWER PART OF AIRCRAFT, REVEAL	ED OIL LEAKING FROM THE BASE SEAM OF THE OIL FILTER.  THE OIL LEVEL HAD GONE DOWN ONE HALF QUART IN THE ONE HOUR FLIGHT.	  THE LEAK WAS NOT FROM THE FILTERS BASE SEAL AND HAD BEEN PROPERLY TORQUED AND SAFETY WIRED IN PLACE. NO DAMAGE WAS VIS	IBLE ON THE FILTER.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005091900050	20050919	00050	CE  	2005	9	19	2005FA0001291    	1	20050902	G	2750		CONTROL TUBE    			CESSNA	140   	140         	2071602	CE  	CONT  	O240  	IO240A      	 	SO  					FLAP SYSTEM	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	89671					8719				THE IB RT FLAP AND SECTION OF THE FLAP CONTROL TUBE WERE EXAMINED.  THE CONTROL TORQUE TUBE WELD CONTAINED SURFACE CORRO	SION AND A FATIGUE CRACK WAS NOTED.					1	H	7	1 	3O	3	O	NC	A768    	E7SO				 
2005091900074	20050919	00074	EA  	2005	9	19	2005FA0001292    	2	20050909	G	8530	LW12988	CYLINDER        			BEECH 	18    	E18S        	1151006	CE  	LYC   	O540  	IO540*      	41532	EA  					NR 1	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	700W					BA54	RL283761A			DURING ANNUAL INSPECTION, IT WAS DISCOVERED DURING A DIFFERENTIAL COMPRESSION CHECK THAT THE NR 1 CYLINDER ON THIS ENGIN	E HAD ALMOST NO COMPRESSION. IT WAS DISCOVERED THAT THE EXHAUST VALVE GUIDE WAS BAD. ALSO, THE EXHAUST VALVE AND INTAKE 	VALVE HAD TO BE REPLACED. THIS CYLINDER WAS ON AN ENGINE THAT HAD BEEN RECALLED FOR THE CRANKSHAFT REPLACEMENT AD AND HA	D ALL CYLINDERS REPLACED AT THAT TIME. THE CYLINDER HAD 149 HOURS IN SERVICE SINCE NEW. MFG WAS NOTIFIED OF THIS PROBLEM	 BUT WAS NOT INTERESTED. THE CYLINDER WAS REPAIRED.		1	L	7	2 	3R	3	O		A765    	1E4				 
2005091900119	20050919	00119	CE  	2005	9	19	2005FA0001294    	1	20050915	G	5520		BOLT            			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					ELEVATOR	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	28	912MA					9482004				DURING PREFLIGHT THE PILOT FOUND EXCESSIVE MOVEMENT IN THE LT OB ELEVATOR HINGE PIN.  MAINTENANCE REMOVED BOTH ELEVATORS	 AND THE RUDDER AND FOUND LONGITUDINAL SCORING ON ALL THE HINGE BOLTS (AN23-40) APPARENTLY CAUSED DURING MFG OF THE AIRC	RAFT.  THE LONGITUDINAL SCORING WAS CAUSED BY THE CENTER NEEDLE BEARING (PN B34PS) ON THE ELEVATOR AND RUDDER.  CIRCUMFE	RENTIAL SCORING WAS ALSO PRESENT ON ALL BOLTS APPARENTLY CAUSED BY IMPROPERLY ALIGNED AND REAMED BUSHINGS (PN 1-3737-1) 	ON THE HORIZONTAL AND VERTICAL STABILIZER HINGES.  THE MFG WAS CONTACTED CONCERNING THE PROBLEM.  THE SAME CONDITION IS 	PRESENT IN SN 943-2004.	1	H	7	1 	3O	3	O		A21CE   	1E10				 
2005102600205	20051026	00205	EA  	2005	10	26	2005FA0001295    	2	20050909	G	8530		VALVE GUIDE     	LYC         		PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	TIO540U2A   	41532	EA  					CYLINDER	BURNED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08		149  				62P088681650	RL283761A			DURING ANNUAL INSPECTION, IT WAS DISCOVERED DURING A DIFFERENTIAL COMPRESSION CHECK THAT NR 1CYLINDER ON THIS ENGINE HAD	 ALMOST NO COMPRESSION. THE CYLINDER WAS REMOVED AND SENT, IT WAS DISCOVERED THAT THE EXHAUST VALVE GUIDE WAS BAD. THE G	UIDE WAS REPLACED ALONG WITH THE INTAKE AND EXHAUST VALVES UNDER WORK ORDER NR 21110.  THIS CYLINDER WAS ON AN ENGINE TH	AT HAD BEEN RECALLED BY THE AD FOR THE CRANKSHAFT AND ALL CYLINDERS WERE REPLACED AT THAT TIME. THE CYLINDER HAD 149 HOU	RS IN SERVICE SINCE NEW. MFG WAS CONTACTED REGARDING THIS PROBLEM AND WAS NOT EVEN INTERESTED IN DISCUSSING IT.		1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2005102600209	20051026	00209	EA  	2005	10	26	2005FA0001296    	2	20050909	G	8530		VALVE GUIDE     	LYC         		PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	TIO540U2A   	41532	EA  					CYLINDER	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	700WG	149  				62P088681650	RL283761A			DURING ANNUAL INSPECTION, IT WAS DISCOVERED DURING A DIFFERENTIAL COMPRESSION CHECK THAT THE NR 1 CYLINDER ON THIS ENGIN	E HAD ALMOST NO COMPRESSION. THE CYLINDER WAS REMOVED AND SENT AND WAS DISCOVERED THAT THE EXHAUST VALVE GUIDE WAS BAD. 	THE GUIDE WAS REPLACED ALONG WITH THE INTAKE AND EXHAUST VALVES UNDER WORK ORDER NR 21110.  THIS CYLINDER WAS ON AN ENGI	NE THAT HAD BEEN RECALLED BY THE AD FOR THE CRANKSHAFT AND ALL CYLINDERS WERE REPLACED AT THAT TIME. THE CYLINDER HAD 14	9 HOURS IN SERVICE SINCE NEW. MFG WAS CONTACTED REGARDING THIS PROBLEM AND WAS NOT EVEN INTERESTED IN DISCUSSING IT.		1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2005092600202	20050926	00202	SO  	2005	9	26	2005FA0001297    	1	20050809	G	3210		LANDING GEAR    			AMRGEN	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320*       	41508	EA  					MLG	NOISY           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	31	9920U					AA5A0320				FOUND THAT WHEN MOVING THE PILOT SEAT THERE WAS A SCRATCHING NOISE AS PLASTIC SLIPPING OVER EACH OTHER.  FOUND CRACK IN 	PART OF THE LANDING GEAR.					1	L	7	1 	3O	3	O		A16EA   	E274				 
2005092000080	20050920	00080	SO  	2005	9	20	2005FA0001299    	2	20050915	G	7414		ROTOR SHAFT     								CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	MAGNETO	SHEARED         	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	25	293D	768  	250  		03090897		824561R	AF3178		UNSCHEDULED FAILURE OF THE LT ENGINE MAGNETO DURING ENGINE START. FOUND MAGNETO ROTOR SHAFT SHEARED AT POINTS CAM DRIVE 	END.										3	O			E7SO	5	N	TA4CH	 
2005092600062	20050926	00062	EA  	2005	9	26	2005FA0001300    	2	20050909	G	8530	72897	VALVE GUIDE     			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					EXHAUST VALVE	STUCK           	B			IGAR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	01	300LF	842  				295				DURING LANDING, RT POSITION ENGINE EXPERIENCED ROUGHNESS.  FOUND CYLINDER NR 2 EXHAUST VALVE STUCK.  VALVE GUIDE INSPECT	IONS ARE DUE AT 1000 HOURS.  ENGINE ONLY HAD 842.6 HRS.  (K)					1	H	7	2 	3O	3	O		A31EU   	1E10				 
2005092600060	20050926	00060	EA  	2005	9	26	2005FA0001301    	2	20050909	G	8520	72877	LIFTER          			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	BROKEN          	B			IGAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	300LF	842  				295	RL2071451A			UPON COMPLYING WITH SB, VALVE GUIDE INSPECTION, FOUND LIFTER BODY PN 72877 BROKEN.  VALVE GUIDE REVEALED NO SIGNS OF STI	CKING.  (K)					1	H	7	2 	3O	3	O		A31EU   	1E10				 
2005092600058	20050926	00058	CE  	2005	9	26	2005FA0001302    	1	20050913	G	5410	J744442	MOUNT           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					COWLING	TORN            	B			DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5027X	100  				172S8966				DURING THE COURSE OF A ROUTINE 100 HOUR INSPECTION, 3 OF THE RUBBER (LORD) COWLING MOUNTS WERE FOUND TORN.  THIS HAS BEE	N A COMMON OCCURRENCE SEEN WHILE MAINTAINING A FLEET OF THIS MODEL AC OPERATED BY A FLIGHT SCHOOL.  IF NOT ADDRESSED THI	S COULD LEAD TO A LOSS OF THE ENGINE COWLING IN FLIGHT.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005092600063	20050926	00063	SW  	2005	9	26	2005FA0001303    	1	20050907	G	2497	430076506109	WIRE            			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					BATTERY	FAILED          	B			NYXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	430SP	1137 				49083				A LOOSE CONNECTION AT THE RING TERMINAL ON THE AIRCRAFT BATTERY CONNECTOR CAUSED SUFFICIENT HEAT BUILDUP TO MELT THE SEC	URING NUT AND WASHER AND CHAR THE WIRING.  THE PROBLEM WAS COMPOUNDED BY THE AIRCRAFT MFG USE OF IMPROPERLY SIZED RING T	ERMINALS AT THIS CONNECTION.  THE MS25036-127 TERMINAL ENDS SPECIFIED BY THE MFG, UTILIZE A (.4375 INCH) HOLE IN CONJUNC	TION WITH (.2500 INCH) STUDS ON THE BATTERY CONNECTOR PN MS25182-2.  THIS IS CONTRADICTORY TO STANDARD PRACTICE AS SPECI	FIED IN AC.  (K)		1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2005103100055	20051031	00055	CE  	2005	10	31	2005FA0001304    	1	20050912	G	5410	J744442	MOUNT           			CESSNA	172   	172R        	2072401	CE  										COWLING	TORN            	B			DYTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	78JA	100  				17280622				THE RUBBER (LORD) MOUNTS USED TO ATTACH THE ENGINE COWLING TO THE AIRFRAME ARE FAILING AT A RATE OF ABOUT 3 MOUNTS EVERY	 100 HOURS.  MAINTAIN A FLEET OF THESE MODEL AIRCRAFT USED IN A FLIGHT SCHOOL ENVIRONMENT AND SEE THIS REGULARLY ON THES	E AIRCRAFT.  IF NOT CORRECTED THIS COULD CAUSE A LOSS OF THE ENGINE COWLING IN FLIGHT.  (K)				1	H	7	1 	3O			NT	3A12    					 
2005103100097	20051031	00097	CE  	2005	10	31	2005FA0001305    	1	20050830	G	2797		WIRE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					CONTROL WHEEL	DAMAGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	494CW					RK4				INVESTIGATED REPORT OF HORIZONTAL STABILIZER TRIM INOPERATIVE AND SYSTEM CIRCUIT BREAKER TRIPPING WHEN TRIM ACTUATED ON 	LANDING.  CREW REPORTED NORMAL TRIM OPERATIONS SLOW JUST PRIOR TO FAILURE.  FOUND BARE WIRING IN COPILOTS CONTROL WHEEL 	AT PITCH TRIM SWITCH.  REPAIRED WIRING AS REQUIRED.  HORIZONTAL STABILIZER TRIM OPERATIONS NORMAL AFTER REPAIRS.  SUGGES	T WIRING IN THIS AREA HAVE BEETER STRAIN RELIEF/CHAFE PROTECTION.  (K)			2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2005092600079	20050926	00079	CE  	2005	9	26	2005FA0001306    	1	20050908	G	2460	4TP110	SWITCH          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CONTROL PANEL	FAILED          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	934RD					258296				INVESTIGATED BATTERY POWER NOT CONNECTING TO AIRCRAFT BUSSES.  FOUND OVERHEAD PANEL BATTERY POWER SELECT SWITCH (IDENTIF	IER (EN)) FAILED.  REPLACED SWITCH ASSY, BATTERY POWER, ENGINE START OPERATIONS NORMAL.  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005103100104	20051031	00104	CE  	2005	10	31	2005FA0001307    	1	20050908	G	8097		CONNECTOR       			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ENGINE STARTER	LOOSE           	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	934RD					258296				INVESTIGATED ENGINE NR 1 AND ENGINE NR 2 STARTERS NOT ROTATING WHEN START SEQUENCE INITIATED.  FOUND WIRING CONNECTORS L	OOSE ON PANEL ZL INTERNAL START CONTACTOR (U) TERMINALS (CONTACTOR, PN A84MAS).  RETORQUED WIRING TERMINALS, ENGINE STAR	T OPERATIONS, NORMAL.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005103100112	20051031	00112	CE  	2005	10	31	2005FA0001308    	1	20050902	G	5510		FASTENER        	BEECH       		BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					VERTICAL STAB	LOOSE           	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	907JE				RK107	RK107				DURING SCHEDULED 1ST (D) INSPECTION FOUND HI-LOK PIN COLLAR LOOSE (UPPER HEX SECTION STILL INTACT) FOR (1) FASTENER (OF 	3) ATTACHING PN 454A23202-3 LT VERTICAL STABILIZER PIVOT PLATE TO VERTICAL STABILIZER AFT SPAR, UPPER LT SIDE.  AREA IS 	JUST BELOW WHERE PN 45A61505-11 ELEVATOR CONTROL ATTACH BRACKET IS INSTALLED.  HI-LOK PIN FOUND STILL SECURE, COLLAR TOR	QUED DOWN AND SNAPPED OFF NORMALLY WHEN TIGHTENED.  SUSPECT COLLAR STARTED BUT NOT TORQUED DOWN AT MFG OR DURING SUBSEQU	ENT POSSIBLE UNDOCUMENTED REPAIRS THIS AREA.  AREA SHOULD BE VISIBLE DURING NORMAL (C) CHECKS OR WHEN AFT VERTICAL STABI	LIZER/ HORIZONTAL STABILIZER FAIRING IS REMOVED.  (K)	2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2005103100106	20051031	00106	SW  	2005	10	31	2005FA0001309    	1	20050903	G	6200	047120252011	GRIP            			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435*     	41516	EA  					MAIN ROTOR	CRACKED         	B			QH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	8554F					6508				MAIN ROTOR GRIP, CRACK IN THREADS.  (K)						1	G	7	1 	3O	3	O		2H3     	1E13				 
2005103100022	20051031	00022	CE  	2005	10	31	2005FA0001310    	1	20050909	G	2497	CV7313	DIODE           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LOOSE	FAILED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	934RD					258296				INVESTIGATED LOSS OF BATTERY POWER AFTER AIRCRAFT DC BUSSES POWERED-UP FOR 4 TO 5 MINUTES.  FOUND COLD-SOLDIER JOINT ON 	EQUIPMENT PANEL ZL DIODE (P) WIRING CONNECTIONS.  REPAIRED SOLDIER CONNECTIONS AS REQUIRED, OPS CHECK NORMAL.  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005103100110	20051031	00110	CE  	2005	10	31	2005FA0001311    	2	20050909	G	8500		ENGINE          			CESSNA	337   	P337H       	2075731	CE  	CONT  	IO360 	IO360*      	17025	CE  					LT AND RT	STOPPED         	D				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			GL	03	37E					P3370127				DURING CRUISE CLIMB, PILOT REPORTED BOTH ENGINES QUIT RUNNING AND DEVERTED.  DURING DECENT ENGINES CAME BACK TO LIFE.  S	UMPED 1 PINT EACH FROM FRONT, BACK FUEL STRAINERS, LT AND RT WING DRAINS.  FUEL APPEARED NORMAL COLOR BLUE AND NO CONTAM	INATES FOUND.  (K)				1	H	7	2 	3O	3	O		A6CE    	E1CE				 
2005092600175	20050926	00175	EU  	2005	9	26	2005FA0001312    	1	20050809	G	2150	451400003	DRIVE BELT      			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					AIR CONDITIONER	FAILED          	B			CDBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	311SJ					3583	9818			AIR CONDITIONER DRIVE BELT FOUND SHREDDED ON ENGINE DECK, FAILED SEVERAL TIME IN HISTORY OF AC.  REPLACED AC COMPRESSOR 	AND DRYER ASSY THINKING COMPRESSOR SEIZURE WHEN HOT. BELT REQUIRED, MM SHOWS 30 LBS TENSION REQUIRED.  BELT INSTALLED TO	 SPECS WAS OPERATED FOR A LENGTH OF TIME ON GROUND, THEN AS THE MM SPECIFIES, TURNED OFF FOR TAKEOFF.  WHEN THE AC WAS R	E-ACTIVATED IN FLIGHT, PILOT REPORTS A BURNING SMELL AND THE AIR TEMP CAME OUT WARM.  AC WAS RETURNED TO HELIPORT WHERE 	THE BELT WAS AGAIN FOUND SHREDDED.  MFG STATES THAT DRIVE BELT AND TENSIONING LISTED IN MM IS NOT CORRECT BELT OR TENSIO	N.  REQUIREMENT TO DEACTIVATE AC FOR TAKE-OFF REMOVED.  MFG PARTS MANUAL, TO REQUIRE NOTICE OF STC`D PARTS. (K)	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005092300093	20050923	00093	CE  	2005	9	23	2005FA0001313    	1	20050919	G	3251	59420011	BELLCRANK       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NLG STEERING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2740B					421C1249				PILOT SAID PRESSURE REQUIRED TO MOVE RUDDER PEDALS WAS NOT NORMAL ON PREFLIGHT INSPECTION.  NOSE GEAR STEERING BELLCRANK	 WAS CRACKED THROUGH AND BROKEN APART ON THE LT SIDE OF THE CENTER MOUNTING RADIUS.  THE RT SIDE OF THIS RADIUS ALSO IS 	CRACKED.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005092300094	20050923	00094	CE  	2005	9	23	2005FA0001314    	1	20050919	G	3251	59420011	BELLCRANK       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NLG STEERING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2740B					421C1249				PILOT SAID PRESSURE REQUIRED TO MOVE RUDDER PEDALS WAS NOT NORMAL ON PREFLIGHT INSPECTION.  NOSE GEAR STEERING BELLCRANK	 WAS CRACKED THROUGH AND BROKEN APART ON THE LT SIDE OF THE CENTER MOUNTING RADIUS.  THE RT SIDE OF THIS RADIUS ALSO IS 	CRACKED.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005092300149	20050923	00149	CE  	2005	9	23	2005FA0001315    	1	20050923	G	3260		DOWNLOCK SWITCH 			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RT MLG	OUT OF ADJUST   	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			GL	21	502SE					LJ740				ON APPROACH THERE WAS NO RT MAIN GEAR INDICATION.  CHECKED GEAR RIGGING AND ADJUSTED RT DOWNLOCK SWITCH IAW M/M.						1	L	7	2 	3T	4	T		3A20    	E4EA				 
2005092300153	20050923	00153	SO  	2005	9	23	2005FA0001316    	2	20050921	G	8530	SA10200	CYLINDER        								CONT  	O300  	O300D       	17022	SO  					ENGINE	BROKEN          	C				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	03		1388 					34897D6D			ENGINE CYLINDER NR 6, CRACKED CIRCUMFERENTIALLY AND FULLY SEPARATED BETWEEN THE 12TH AND 13TH COOLING FINS AS COUNTED FR	OM THE BASE OF THE CYLINDER CAUSING A COMPLETE LOSS OF ENGINE POWER.										3	O			E253				 
2005102700088	20051027	00088	SO  	2005	10	27	2005FA0001317    	1	20050920	G	2810		BLADDER         			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540*       	41532	EA  					FUEL TANK	COLLAPSED       	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	21	4827Y					254618				FOUND AC TO HAVE DAMAGE TO L G BUNGEE, LT BOOM OB ATTACH POINT AT AFT WING CLOSEOUT. NO FUEL IN TANK, VERIFIED BY REMOVA	L OF FUEL LINE AT FUEL VALVE ON BOTTOM OF TANK.  FILLED TANK TO OVERFLOW CONDITION.  WAS ONLY ABLE TO GET 23.2 OF 38 GAL	LONS INTO TANK.   FUEL BLAD PARTIALLY COLLAPSED, UNABLE TO BLOW AIR THROUGH FUEL VENT.  LINE WAS PARTIALLY BLOCKED WHICH	 COULD HAVE CAUSED FUEL CONSUMPTION TO COLLAPSE BLAD UNHOOKING UPPER SNAPS.  SB INSTALLS BOLT, WIDE AREA WASHER IN BOTTO	M OF TANK DIRECTLY BELOW FUEL GAGE/FLOAT TO HOLD BLADDER IN PLACE.  TANK/BLADDER TO BE INSP DURING AC REPAIR TO DETERMIN	E IF BLOCKED VENT CAUSED UPPER BLADDER SNAPS TO UNHOOK COLLAPSING TANK, PREVENTING FULL USABLE FUEL CAPACITY.	1	L	7	1 	3O	3	O		2A10    	E295				 
2005103100131	20051031	00131	EU  	2005	10	31	2005FA0001318    	1	20050730	G	2612	9583820090	PROBE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FIRE DETECTION	FAULTY          	B			HXSR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	05	6094E					2750	4035			PILOT REPORTED THAT HIS FIRE INDICATION LIGHT HAD FLICKERED A COUPLE OF TIMES BUT THEN WENT AWAY.  LIGHT WOULD NOT FLICK	ER ON THE GROUND WHILE NOT RUNNING.  MECHANIC COULD NOT FIND THE FAULT.  CLEANED THE CONNECTIONS AND FIRE DETECTION PROB	ES AND TRIED A RUN UP.  FIRE LIGHT AGAIN FLICKERED A COUPLE OF TIMES THEN WENT OUT.  TROUBLESHOOTING AGAIN FOUND A FIRE 	DETECTION PROBE TO BE PROBABLE.  CHANGED THE PROBE AND AGAIN RAN UP THE AC.  THIS TIME THE FIRE SYSTEM WORKED IAW THE MM	.  TOOK THE AC FOR A FLIGHT TO DETERMINE PROPER FUNCTION UNDER FLIGHT LOADS AND AGAIN THE SYSTEM WORKS IAW MM.  RETURNED	 THE AC TO SERVICE.  (K)	1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005092600193	20050926	00193	EU  	2005	9	26	2005FA0001319    	1	20050723	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYDRAULIC SYS	FAILED          	E			HXSA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	6080R					2685				PILOT WAS ON HIS INTENDED ROUTE AND NOTIFIED OPERATIONS BASE THAT HE WAS TURNING AROUND AND THAT HAD LOST HYDRAULIC ASSI	ST TO FLIGHT CONTROLS.  RETURNED TO BASE AND LANDED WITH NO INCIDENT.  MAINT FOUND THAT THE HYDRAULIC PUMP SPLINES HAD F	AILED AND REMOVED AND REPLACED WITH A SERVICEABLE PUMP.  AC HAS BEEN RETURNED TO SERVICE.  (K)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005092600176	20050926	00176	GL  	2005	9	26	2005FA0001320    	2	20050825	G	7200	23034787	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			HXSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	8357F		1265 			170069D	832729			ENGINE CHIP LIGHTS FOLLOWED BY ENGINE NOISE.  (K)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005103100092	20051031	00092	CE  	2005	10	31	2005FA0001321    	1	20050912	G	3240		LINE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D1      	52060	NE  					HYD SYSTEM	DAMAGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	907JE					RK107				DURING COMPLIANCE WITH INSPECTION PORTION OF SB NOTED CHAFE DAMAGE TO PN 128580101-1 NOTED CHAFE DAMAGE TO PN 128-580101	-1 HYDRAULIC BRAKE LINE FROM ADJACENT FLOORBOARD ATTACH SCREW.  DAMAGE FOUND LESS THAN 10 PERCENT OF  TUBING WALL THICKN	ESS.  RECOMMEND THAT THIS  SB BE MADE AT LEAST A MANDATORY COMPLIANCE ITEM.  SEVERAL OF THE AFFECTED AC INSPECTED AT THI	S FACILITY HAVE SHOWN  EVIDENCE OF DAMAGE IN THIS AREA. (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2005103100026	20051031	00026	EA  	2005	10	31	2005FA0001322    	2	20050901	G	7414	M3548	ROTOR           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					MAGNETO	CRACKED         	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	4145A		482  		99121536	2843150	L3620536A			DURING A ROUTINE 500 HR INSPECTION, THE ROTOR SHAFT WAS FOUND CRACKED AT THE BOTTOM OF THE CAM SLOT.  THE CAUSE IS UNKNO	WN.  THIS IS THE THIRD SUCH DEFECT FOUND IN THIS SERIES OF MAGNETOS IN A YEAR.  (K)					1	L	7	1 	3O	3	O		2A13    	E286				 
2005103100027	20051031	00027	EA  	2005	10	31	2005FA0001323    	2	20050901	G	8520		CRANKSHAFT      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360A1G6   	41514	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	239AT					4496038	L62571A			APPARENT CRANKSHAFT FAILURE:  JUST AFTER TAKEOFF ENGINE STARTED VIBRATING VIOLENTLY.  SHUTDOWN AND LANDED SAFETLY.  ENGI	NE WAS SPLIT IN HALF.  PROP WAS ANGLED DOWN AS FRONT HALF OF ENGINE WAS ANGLED DOWN.  (K)					1	L	7	2 	3O	3	O		A19S0   	1E10				 
2005103100100	20051031	00100	CE  	2005	10	31	2005FA0001325    	1	20050916	G	2750	C3010020110	MOTOR           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					TE FLAP	MALFUNCTIONED   	B			MYNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	915MA	1500 				172S8260				FOUND FLAP MOTOR LOOSE ON TRANSMISSION, CAUSING STATIC IN RADIOS WHEN FLAPS IN TRANSIT TIGHTENED MOTOR ALL OPS GOOD.  (K	)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005103100197	20051031	00197	CE  	2005	10	31	2005FA0001326    	1	20050914	G	2710	05232333	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT WING AILERON	WORN            	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5275S					172S9203				DURING 100 HOUR INSPECTION, WHILE INSPECTING AILERON CABLES, FOUND FLAT SPOT ON THE LT AILERON CROSSOVER CABLE AT THE AI	LERON CABLE ABRASION STRIP ATTACHED TO A RIB ASSEMBLY LOCATED AT WING STATION 71.19.  FURTHER INVESTIGATION FOUND THE CA	BLE BEGINNING TO FRAY.  THE CAUSE IS THE CABLE WEARING ON THE ABRASION STRIP.  TO SOLVE THIS PROBLEM , THE ABRASION STRI	P BE LOWERED OR A PULLEY BE INSTALLED.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005102800132	20051028	00132	CE  	2005	10	28	2005FA0001327    	1	20050914	G	5720	05232333	STRIP           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT  WING	UNSERVICEABLE   	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	141CW					172S9389				DURING 100 HOUR INSPECTION, WHILE INSPECTING THE AILERON CABLES, FOUND A FLAT SPOT ON THE LT AILERON CROSSOVER CABLE AT 	THE AILERON CABLE ABRASION STRIP ATTACHED TO A RIB ASSEMBLY LOCATED AT WING STATION  71.19.  FURTHER INVESTIGATION FOUND	 THE CABLE BEGINNING TO FRAY.  THE CAUSE IS THE CABLE WEARING ON THE ABRASION STRIP.  TO SOLVE THIS PROBLEM, THE ABRASIO	N STRIP BE LOWERED OR A PULLEY BE INSTALLED.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005103100229	20051031	00229	CE  	2005	10	31	2005FA0001328    	1	20050914	G	5720	05232333	STRIP           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT WING	UNSERVICEABLE   	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	2134M					172S9552				WHILE INSPECTING FOR STORM DAMAGE, DURING THE INSPECTION OF THE AILERON CABLES, FOUND A FLAT SPOT ON THE LT AILERON CROS	SOVER CABLE AT THE AILERON CABLE ABRASION STRIP ATTACHED TO A RIB ASSEMBLY LOCATED AT WING STATION 71.19.  FURTHER INVES	TIGATION FOUND THE CABLE BEGINNING TO FRAY.  THE CAUSE IS THE CABLE WEARING ON THE ABRASION STRIP.  TO SOLVE THIS PROBLE	M, THE ABRASION STRIP BE LOWERED OR A PULLEY BE INSTALLED.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005092900016	20050929	00016	CE  	2005	9	29	2005FA0001329    	1	20050821	G	7931	83278	PRESSURE SWITCH 			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					OIL SYSTEM	BLOWN           	H				B				EMER. DESCENT           				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	07	93AF	5321 				17280073	RL211751A			ORIGINAL OIL PRESSURE SWITCH HAD BEEN REPLACED PER SB SB00-79-01.  THE REPLACEMENT SWITCH P/N 83278 FAILED ALLOWING ENGI	NE OIL TO PASS THROUGH SWITCH AND VENT OVERBOARD.  NTSB ACCIDENT NUMBER IS DFW05CA219.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005092900017	20050929	00017	CE  	2005	9	29	2005FA0001331    	1	20050821	G	7931	83278	PRESSURE SWITCH 			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					OIL SYSTEM	BLOWN           	H				B				EMER. DESCENT           				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	07	93AF	5321 				17280073	RL211751A			ORIGINAL OIL PRESSURE SWITCH HAD BEEN REPLACED PER SB SB00-79-01.  THE REPLACEMENT SWITCH P/N 83278 FAILED ALLOWING ENGI	NE OIL TO PASS THROUGH SWITCH AND VENT OVERBOARD.  NTSB ACCIDENT NUMBER IS DFW05CA219.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005101300033	20051013	00033	SO  	2005	10	13	2005FA0001332    	2	20050724	G	7261	CH481091	OIL FILTER      			AMTR  	LANCAR	LANCAIR     	05616TS	GL  	CONT  	O550  	TSIO550E    	17043	SO  					ENGINE	FAILED          	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CE	03	619SJ	1    				357				CHANGED OIL AND OIL FILTER PRIOR TO FLIGHT. WHILE IN CRUISE FLIGHT, OIL PRESSURE BEGAN DECLINING TO < 10PSI. NO RISE IN 	OIL TEMPERATURE. DECLARED EMERGENCY, LANDED UNEVENTFULLY. EXTENSIVE TROUBLESHOOTING REVEALED NEW OIL FILTER TO BE CAUSE 	OF DECLINING PRESSURE PROBLEM (<10 PSI). PILOT EXPERIENCED SAME PROBLEM (LOSS OF OIL PRESSURE (0 PSI) ABOUT ONE HOUR INT	O FLIGHT) ON SIMILAR AIRCRAFT/ENGINE TWO MONTHS LATER FOLLOWING REPLACEMENT OF CH48109 OIL FILTER. REPLACEMENT OF THAT O	IL FILTER FIXED LOW OIL PRESSURE PROBLEM. WILL SUBMIT REPORT SEPARATELY ON THAT INCIDENT. HOLDING OIL FILTERS FOR INSPEC	TION.	1	L	7	1 	3O	3	O	RT	EXPA1L71	E5SO				 
2005101700212	20051017	00212	EU  	2005	10	17	2005FA0001334    	1	20050927	G	3240	AHO89881	BRAKE ASSY      			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					LT MLG	OVERHEATED      	C				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			GL	07	466AE	54   	54   			NA0466				PILOT NOTICED LT OB TIRE WAS FLAT.  MAINT FLEW TO AIRPORT AND CHANGED BOTH LT MAIN GEAR WHEEL AND TIRE ASSYS. AC WAS THE	N FLOWN BACK. UPON INSPECTION OF FLAT TIRE IT WAS FOUND THAT ALL 3 FUSIBLE PLUGS HAD MELTED.  INSPECTED THE LT OB BRAKE 	AND FOUND IT HAD OVERHEATED. DURING DISASSEMBLY OF BRAKE HEAT PACK IT WAS NOTED THAT BACKING PLATE WAS BADLY WARPED AND 	WEAR PADS WERE FLAKING AWAY. RIVETS HOLDING WEAR PADS IN PLACE HAD TURNED BLUE FROM HEAT. IB WHEEL ON THIS AXLE WAS UNAF	FECTED BY HEAT, TIRES HAD NOT BEEN FLAT SPOTTED OR SKIDDED WHICH WOULD INDICATE EXCESSIVE BRAKING WAS NOT USED.  APPEARS	 BRAKE MATERIAL WAS DEFECTIVE. NORMALLY WE SEE SERVICE AND LANDING OF ABOUT 400 HOURS ON EACH HEAT PACK.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005101800178	20051018	00178	CE  	2005	10	18	2005FA0001335    	1	20050921	G	2435	80603201	STARTER GEN     			BEECH 	50    	B50         	1152506	CE  	GARRTT	TFE731	TFE73131C   	01518	NE  					NR 1 ENGINE	FAILED          	E			XORA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NE	03	100E		790  			CH14				UNIT SUSTAINED A MAIN BEARING ARMATURE DRIVE SHAFT FAILURE DURING FLIGHT. THE NR1 MAIN GENERATOR WARNING LIGHT ENUNCIATO	R ILLUMINATED THE ARMATURE, DRIVE BALL DRIVESHAFT, AND BEARING FLANGE ARE NON-SERVICEABLE.  THE ORIGINAL OVERHAUL PERIOD	 (TBO), FOR THIS UNIT IS 900 FLIGHT HOURS.  THE AIR OPERATOR HAS NOW ELECTED TO REDUCE THE TBO OF THE UNIT TO 600 HRS.				1	L	7	2 	3O	4	F		5A4     	E6WE				 
2005110800324	20051108	00324	GL  	2005	11	8	2005FA0001336    	2	20050815	G	7323	252476914	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	STIFF           	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGPHC	2746 	1158 			180257D	CAE832057			ON INSPECTION THE GOV LOOKED TO BE OUT OF RIG.  WHEN THE ARM WAS REMOVED IT WAS DISCOVERED THAT THE SHAFT WAS EXTREMELY 	STIFF.  REPLACED GOVERNOR. (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005110800317	20051108	00317	WP  	2005	11	8	2005FA0001337    	1	20050813	G	6700	369A717111	MOTOR           			HUGHES	369   	369A        	4470503	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FLIGHT CONTROLS	INOPERATIVE     	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	C6BU4					610958D	CAE833793			ON APPROACH TO LANDING THE LONG TRIM MOTOR QUIT WORKING.  REPLACED UNIT. (K)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005110800309	20051108	00309	GL  	2005	11	8	2005FA0001338    	2	20050809	G	7323	369A20023	MOTOR           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR TRIM	INOPERATIVE     	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	C6PNC					1800257D				PILOT BEEPED THE N2 UP AND WAS UNABLE TO BEAP DOWN, THEN LATER GOT IT DOWN WITH NUMEROUS ATTEMPTS AND FLEW IT BACK.  UNI	T WAS CHANGED.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005110800308	20051108	00308	WP  	2005	11	8	2005FA0001339    	1	20050807	G	6220	369D21200501	HUB             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	DAMAGED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	5074R	7035 	2620 			1151D				FOUND THE UPPER M/R P/C LINK BEARING HAD WORN INTO THE ATTACH HUB OF THE PITCH HOUSING ABOUT .130 INCH UNTIL THE SPHERIC	AL PART OF THE BEARING CONTACTED, PREVENTING FURTHER PROGRESSION.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005103100194	20051031	00194	SO  	2005	10	31	2005FA0001340    	1	20050922	G	5500	28321RL	TIP CAP         			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR TIPS	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	9467J	1    				283581				OWNER REMOVED ORIGINAL HORIZONTAL STABILATOR TIPS AND INSTALLED AMR, D, STC SA520CH.  OWNER COMPLAINED THAT THE CONTROL 	FORCES HAD CHANGED CONSIDERABLY.  THE CONTROL FORCES WERE HEAVY ON TAKEOFF CAUSING THE OWNER TO OVER ROTATE.  OWNER REVE	RTED BACK TO ORIGINAL STYLE STABILATOR TIPS.  (NO MORE PROBLEMS) THE OWNER THINKS THAT THE HOLDER OF THE STC SHOULD INFO	RM PEOPLE INTERESTED IN THESE TIPS THAT THERE WILL BE CHANGES IN THE CONTROL FORCES WHEN THE TIPS ARE INSTALLED.  THE OW	NER TALKED TO THE STC HOLDER WHO SAID THAT THERE WOULD BE CHANGES.  THE OWNER THINKS HE SHOULD HAVE BEEN INFORMED BEFORE	 HE BOUGHT THEM AND NOT BE SURPRISED WHEN HE FLEW THE AIRCRAFT.  (K)	1	L	7	1 	3O	3	O		2A13    	E286				 
2005103100192	20051031	00192	EA  	2005	10	31	2005FA0001341    	2	20050920	G	7322	HA6106019	THROTTLE        	PRECISION   		AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360A4K     	41514	EA  					CARBURETOR	STIFF           	B			IG8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	938TE	223  				10217	L3842436A			ANNUAL INSP, IT WAS DISCOVERED THA THE THROTTLE WOULD NOT REACH THE FULL THROTTLE STOP.  THE THROTTLE CABLE WAS DISCONNE	CTED AND THE THROTTLE ARM WAS MOVED BY HAND.  THE THROTTLE WOULD BECOME STIFF AT HALF TRAVEL AND VIRTUALLY IMPOSSIBLE TO	 MOVE BEFORE REACHING THE WIDE OPEN THROTTLE STOP.  THE CARBUETOR WAS REMOVED AND SENT FOR REPAIR.  THIS CARB WAS PREVIO	USLY RETURNED TO MFG FOR REPAIR OF THE SAME CONDITION AT 199.1 HOURS TIME IN SERVICE. ENCOUNTERED CONDITION WAS CAUSED B	Y A FAULY ACCELERATOR PUMP DISCHARGE CHECK VALVE, WHICH CREATED A HYDRAULIC LOCK IN THE ACCELERATOR PUMP, RESTRICTING FW	D THROTTLE TRAVEL.  (K)	1	L	7	1 	3O	3	O	NT	1L71    	E286				 
2005103100174	20051031	00174	CE  	2005	10	31	2005FA0001342    	1	20050923	G	5410	J744442	MOUNT           			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					COWLING	TORN            	B			DYTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	7265B	100  				17280749				DURING A ROUTINE 100 HOUR INSPECTION, 2 OF THE (LORD) COWLING MOUNTS THAT SECURING THE LOWER ENGINE COWLING TO THE AIRFR	AME WERE FOUND TORN IN HALF.  THIS IS A RECURRING PROBLEM ON ALL C AND S MODEL AC OPERATED BY A LOCAL FLIGHT SCHOOL.  IF	 NOT CORRECTED THIS COULD LEAD TO A LOSS OF THE ENGINE COWLING IN FLIGHT.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005103100175	20051031	00175		2005	10	31	2005FA0001343    	4	20050830	G	3417	702490031304	ADC             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	INOPERATIVE     	B			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	701AS					047				ON 5/28/2005, THE PILOTS ALTIMETER INDICATOR AGAIN WAS REPORTED TO SHOW ONLY DASHES INTERMITTENTLY IN FLIGHT, IAW PILOT.	  THE ADC WAS REPLACED AND THE SYSTEM WAS TESTED AND INSPECTED, AND FOUND TO COMPLY WITH FAR, AND TO REMAIN RVSM COMPLAI	NT.  THERE HAD BEEN ONE PRIOR REPORT OF PROBLEMS WITH THIS SYSTEM ON 5/25/2005.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005103100179	20051031	00179		2005	10	31	2005FA0001344    	4	20050829	G	3416	70310N01D01	INDICATOR       			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PILOT ALTIMETER	INTERMITTENT    	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	701AS					047				ON 5/25/2005, THE PILOTS ALTIMETER INDICATOR SHOWED ALL DASHES INTERMITTENTLY IN FLIGHT, IAW PILOT REPORT.  THE PILOTS A	LTIMETER INDICATOR WAS REPLACED AND THE SYSTEM WAS TESTED AND INSPECTED IAW ICA AND FOUND TO REMAIN RVSM COMPLAINT.  THE	RE HAVE BEEN NO PRIOR REPOARTS OF PROBLEMS WITH THIS SYSTEM.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005103100177	20051031	00177	NE  	2005	10	31	2005FA0001345    	2	20050920	G	7240	1968M63G11	LINER           								CFMINT	CFM56 	CFM565A3    	 	NE  					FUEL NOZZLE	DESTROYED       	B			QEMY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35		19566	3031 		42X31412		731433			THE CORE MAJOR MODULE 02 X 31733 WAS REMOVED FROM ESN 731433 FOR COMBUSTOR DISTRESS.  THIS WAS CONFIRMED ON EXPOSURE AT 	REPAIR STATION, WHERE SIGNIFICANT BURNING AND BURN THROUGH ON THE OUTER LINER WAS SEEN IN LINE WITH FUEL NOZZLE N-DEGREE	 15.  THE COMBUSTION CHAMBER WAS PERVIOUSLY REPAIRED AND IS WITH MFG FOR INVESTIGATION.  (K)									4	F			E29NE				 
2005101300032	20051013	00032	EU  	2005	10	13	2005FA0001346    	1	20051004	G	3213	350A41107620	LEAF SPRING     			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					RT SKID	BROKEN          	B				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SW	15	186AE					3872	22484			WHEN HELICOPTER TOOK OFF, PILOT NOTICED AN OBJECT ON THE GROUND WHERE HELICOPTER WAS SITTING. HE SET THE AIRCRAFT BACK D	OWN AND RETRIEVED THE OBJECT. HE THEN NOTICED THAT A 3 INCH AFT SECTION OF THE RT SKID LEAF SPRING HAD SNAPPED OFF. THE 	LEAF SPRING WAS JUST INSTALLED ON THE HELICOPTER PRIOR TO THE FLIGHT. THE LEAF SPRING HAD BEEN REPAIRED AND CAME WITH AN	 8130-3. INSPECTION OF THE PART REVEALED RUST IN THE AREA OF THE BREAK WHICH WOULD INDICATE THAT THE PART HAD BEEN CRACK	ED FOR SOME TIME. PART WAS SENT BACK TO REPAIRER FOR WARRANTY.		1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005101300077	20051013	00077	CE  	2005	10	13	2005FA0001347    	1	20050928	G	2510	MM201057	CYLINDER        			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					SEAT BACK LOCK	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	826KS	2823 	41   			17280792				CREW SEAT BACK LOCK CYLINDER FAILED AND MOUNTING BOLT SHEARED DURING FLIGHT TRAINING, SPIN RECOVERY.  PIC SEAT BACK WENT	 TO HORIZONTAL POSITION. FLIGHT INSTRUCTOR GAINED CONTROL OF AIRCRAFT.  UNEVENTFUL LANDING.  THIS FACILITY HAS REPLACED 	12 OF THESE ASSEMBLIES IN PAST 6 MONTHS AFTER INSPECTION IAW MF SB04-25-02.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005101300198	20051013	00198		2005	10	13	2005FA0001348    	2	20051004	G	7414	ES10357426	DISTRIBUTOR BLK 	CONT        																MAGNETO	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17		300  								THREE MAGNETOS IN SHOP FOR 500HR INSPECTION.  FOUND ALL THREE BLOCKS CRACKED AT FELT WASHER BORE,  EXTENDING IN 2 CASES 	UP INTO TOWER.  THESE THREE BLOCKS ARE AFTERMARKET MANUFACTURE																		 
2005101700215	20051017	00215	CE  	2005	10	17	2005FA0001349    	1	20051004	G	5711		SPAR CAP        			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	300MT					LW143				DURING COMPLIANCE WITH AD 89-25-10, 1,000 HOUR INTERVAL EDDY CURRENT INSPECTION, THE SPAR CAP WAS FOUND TO BE CRACKED 3 	INCHES OB OF BATHTUB AT RT WING LOWER FORWARD SPAR ATTACH POINT.					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2005120200087	20051202	00087		2005	12	2	2005FA0001350    	1	20051004	G	5610		CANOPY          																	COCKPIT	SEPARATED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										CANOPY GLASS SEPARATING FROM FRAME. THIS A TEST.																			 
2005101800190	20051018	00190	EA  	2005	10	18	2005FA0001351    	2	20050927	G	7322		BOWL            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CARBURETOR	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	447ND	139  			75877713	2842247	L2000739A			ENGINE WAS REPORTED TO NOT SHUTDOWN USING MIXTURE CONTROL.  INSPECTED AND FOUND CARBURETOR BOWL LOOSE ON CARBURETOR.  AL	L SAFETY CLIPS ON ATTACHING HARDWARE WERE INSTALLED AND INTACT.					1	L	7	1 	3O	3	O		2A13    	E274				 
2005101800191	20051018	00191	EA  	2005	10	18	2005FA0001352    	2	20050927	G	7322		BOWL            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CARBURETOR	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	447ND	139  			75877713	2842247	L2000739A			ENGINE WAS REPORTED TO NOT SHUTDOWN USING MIXTURE CONTROL.  INSPECTED AND FOUND CARBURETOR BOWL LOOSE ON CARBURETOR.  AL	L SAFETY CLIPS ON ATTACHING HARDWARE WERE INSTALLED AND INTACT.					1	L	7	1 	3O	3	O		2A13    	E274				 
2005102500150	20051025	00150		2005	10	25	2005FA0001353    	2	20051004	G	7414	ES10357426	DISTRIBUTOR BLK 	CONT        																MAGNETO	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		300  								THREE MAGNETOS IN SHOP FOR 500HR INSPECTION.  FOUND ALL THREE BLOCKS CRACKED AT FELT WASHER BORE, EXTENDING IN 2 CASES U	P INTO TOWER.  THESE THREE BLOCKS ARE AFTERMARKET MANUFACTURE.																		 
2005103100193	20051031	00193		2005	10	31	2005FA0001354    	4	20050726	G	2210	4006719906	DRIVE ASSY      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AUTOPILOT	STIFF           	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	5408G					5500666				THE PILOT REPORTED THAT THE CONTROLS WERE STIFF IN THE ROLL AXIS.  THE AUTOPILOT WAS TURNED OFF AND THE CB WAS CYCLED WI	TH NO CHANGE IN THE CONDITION.  AFTER LANDING, WITHOUT INCIDENT, TECHNICIANS ARRIVED AND TROUBLESHOOT THE A/P SYSTEM.  T	HEY DISCOVERED THE AILERON AUTOPILOT SERVO DRIVE CLUTCH WAS NOT FULLY DISENGAGING, CAUSING THE EXCESSIVE FORCE REQUIRED 	TO ROLL THE AIRCRAFT.  THE AILERON AUTOPILOT SERVO DRIVE WAS REMOVED AND REPLACED.  BOTH GROUND AND INFLIGHT OPERATIONAL	 CHECKS WERE PERFORMED WITH NO DEFECTS NOTED.  (K)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005101300059	20051013	00059	EU  	2005	10	13	2005FA0001355    	1	20050816	G	3320	61213	BALLAST         			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					VALANCE LIGHT	UNSERVICEABLE   	B			RO3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	727TA					NA0202				AC WAS DISASSEMBLED FOR INSP.  GROUNDING STRAPS ON VALENCE LIGHTS BROKEN.  REPAIRED GROUNDING STRAPS.  AC WAS REASSEMBLE	D, PWR WAS APPLIED TO AC FOR CHECKOUT.  PWR WAS ON AC FOR HOURS.  INSPECTING OVERHEAD LIGHTING, NOTICED A SPARK.  DROPPE	D VALENCE TO INVESTIGATE, WHILE VALENCE WAS DROPPED, PWR SUPPLY BLEW UP.  NOTICED BECAUSE OF OVERLAPPING OF VALENCE LIGH	T, THAT SILICONE WAS USED TO KEEP GROUNDING STRAPS FROM RUBBING ON LAMP HOLDERS.  LAMP HOLDER WAS RUBBED DOWN, GROUNDING	 STRAP WAS TOUCHING, CAUSING A SHORT AND PWR SUPPLY TO OVERHEAT AND BLOW UP.  RE-ADJUSTED GROUNDING STRAPS TO KEEP THEM 	AWAY FROM LAMP HOLDERS.  PWR SUPPLY WAS SUPPOSED TO SHUT LIGHTS OFF IN CASE OF A SHORT BUT THIS ONE DID NOT.	2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2005101300069	20051013	00069	SW  	2005	10	13	2005FA0001356    	1	20050922	G	5711		SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	5033V					107079				CRACKED SPAR PLATE AT WING STRUT ATTACHMENT LT WING.  APPEARS THAT SOME ONE HAS ATTEMPTED TO ADD GLUE TO PLATE FROM A HO	LE CUT INTO FABRIC ON TOP WING.  IN OTHER WORDS, THIS CRACK HAS BEEN THERE FOR SOME TIME.  COULD NOT DETERMINE IF MAIN S	PAR CRACKED OR SPLIT.  TALKED WITH LAST INSPECTOR AND SAID WING WAS INSPECTED BY PROBE WITH CAMERA ATTACHMENT AND WAS DE	TERMINED AIRWORTHY AT THAT TIME. (K)			1	H	7	1 	3O	3	O	NC	A759    	E274				 
2005110800301	20051108	00301	CE  	2005	11	8	2005FA0001357    	1	20050923	G	2150	HE812933	MOTOR           			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					BLOWER	MALFUNCTIONED   	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	09	414AK					414A0321				RT AIR CONDITIONER BLOWER MOTOR LOCATED UNDER CO-PILOTS SEAT MALFUNCTIONED AND PRODUCED SMOKE WHICH WAS DRAWN THROUGH TH	E RT SIDE VENTILATION DUCTS.  PILOT FOLLOWED EMERGENCY PROCEDURES AND LANDED SAFELY.  (EA09200505819) (K)					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005103100056	20051031	00056	CE  	2005	10	31	2005FA0001358    	1	20050919	G	2450	CV7313	DIODE           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					INTERNAL	OPEN            	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	934RD					258296				INVESTIGATED BATTERY NOT CONNECTING TO AIRCRAFT DC BUSSES.  REPLACED OPEN DIODE (DA) ON GG EQUIPMENT PANEL.  DC POWER OP	ERATIONS NORMAL.  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005103100057	20051031	00057	SO  	2005	10	31	2005FA0001359    	1	20050910	G	5330	62061002	SKIN            			PIPER 	PA28  	PA28R201    	7102816	SO  										FUSELAGE	CRACKED         	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	2221M	4753 				28R7837071				AT CABIN ENTRANCE WING WALK, FOUND SUPPORT PANEL UNDER WING WALK CRACKED.  FAILURE DUE TO REPEATED WALKING.  FACTORY USE	 OF THICKER SHEET METAL MAY HELP.  (K)					1	L	7	1 	3O				2A13    					 
2005110800305	20051108	00305	SO  	2005	11	8	2005FA0001360    	1	20050914	G	5330	62061002	SKIN            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	CRACKED         	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	75340	9286 				28R7635292				AT CABIN ENTRANCE, WING WALK, FOUND SUPPORT PANEL UNDER WING WALK CRACKED.  FAILURE DUE TO REPEATED WALKING ON.  IF FACT	ORY STAMPED SUPPORT OUT OF HEAVIER, THICKER PANEL, MAY HELP PROLONG FAILURE.  (EA21200507814) (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
2005110800306	20051108	00306	SW  	2005	11	8	2005FA0001361    	1	20050528	G	3233		COUPLING        			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	9362V					700011				SUFFERED A GEAR UP LANDING DUE TO A FAILURE OF THE COUPLING BETWEEN THE ACTUATOR AND GEARBOX.  (K)						1	L	7	1 	3O	3	O		2A3     	1E10				 
2005103100028	20051031	00028	EU  	2005	10	31	2005FA0001362    	1	20050926	G	6100	B15892	SPRING          			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	FAILED          	B			LT4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	296TA				AU10273B	384	L2450040A	AU10273B		PROPELLER WAS INSTALLED ON RT SIDE OF AC, THE PROP WENT FEATHER, UNCOMMANDED ON ENGINE SHUTDOWN.  PROPELLER WAS REMOVED 	FROM AC FOR INSPECTION AND WAS RECEIVED WITH THE BLADES IN FEATHER, LOGBOOK WAS NOT SUPPLIED. ALL INFO VIA PHONE.  PROP 	CYLINDER WAS REMOVED AND THE SPRING KIT ASSY WAS CONTAINED.  AFTER DISASSEMBLY, SPRING KIT INSP.  PROP WAS VISUALLY INSP	ECTED, SPRING KIT REBUILT WITH REPLACEMENT PARTS, CYLINDER REINSTALLED AND BLADE ANGLES ADJUSTED.  PROP ASSY RETURNED TO	 SERVICE. ALL WORK/ INSP ACCOMPLISHED IAW MFG MM.  SCREWS, SPRING RETAINER, START WEIGHT LOCK(2 HALVES) AND START LOCK H	SG SENT TO MFG SERVICE CENTER. (K)	1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
2005103100050	20051031	00050	NE  	2005	10	31	2005FA0001363    	2	20050901	G	7210	350A32314306	GEAR            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					RGB	FAILED          	B			FF6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11										GEAR SET, REQUEST WARRENTY ON GEAR SET TOOTH FAILURE OR PINION. (K)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005101700213	20051017	00213	CE  	2005	10	17	2005FA0001364    	1	20050928	G	5711	00011001316	SPAR CAP        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	WINGS	CORRODED        	B			L3CR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	1071T					TC2002	232180H	AN2647R		DURING AN ANNUAL INSPECTION, SOME CORROSION WAS FOUND IN THE AREA OF THE RT WING TIE DOWN ASSY, UPON FURTHER INVESTIGATI	ON AN AREA OF APPROXIMATELY 8 INCHES IN LENGTH WITH SEVERE INTERGRANULAR CORROSION WAS DISCOVERED ON THE LOWER SPAR CAP 	POSSIBLY CAUSED BY DISSIMILAR METAL OF THE TIE DOWN ASSY AND THE LOWER SPAR CAP.  THIS AC HAD SUFFERED THE SAME TYPE OF 	CORROSION ON THE LT WING AT EXACTLY THE SAME LOCATION.  (K)			1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920	 
2005103100155	20051031	00155	CE  	2005	10	31	2005FA0001365    	1	20050927	G	2701	05131663	YOKE            			CESSNA	172   	172B        	2072406	CE  	CONT  	O360  	IO360D      	17025	SO  					LT COCKPIT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	6950X					17247850	551105D			UPON THE FLAIR ON LANDING AT NORMAL WEIGHTS THE CONTROL YOLK BROKE AT THE OUTSIDE LT RADIUS.  THIS CAUSED THE NOSE WHEEL	 OF THE AC TO DROP AT A GREATER SPEED THAN NORMAL AND SHIMMY WAS EXPERIENCED THE MAIN GEAR HAD JUST TOUCHED DOWN WHEN TH	E FAILURE OCCURRED.  PART OF THE YOLK WAS STILL ATTACHED TO THE ASSEMBLY SO AILERON CONTROL WAS MAINTAINED.  (NM13200504	343) (K)			1	H	7	1 	3O	3	O	NT	3A12    	E1CE				 
2005103100181	20051031	00181	GL  	2005	10	31	2005FA0001366    	1	20050930	G	7820	14836001	MUFFLER         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					EXHAUST	MISSING         	B			QRQR	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	05	7171X					0838	917100			REPLACED MUFFLERS ON AC DUE TO THE DETERIORATED CONDITION OF THE SPARK ARRESTERS INSIDE OF THE MUFFLERS.  THE SPARK ARRE	STER IN THE LT MUFFLER WAS GONE.  IT HAD COME LOOSE AND FALLEN OUT OF THE MUFFLER SOMEWHERE.  THE SPARK ARRESTER IN THE 	RT MUFFLER HAD MELTED AND BOWED TO THE LT (IB).  RECOMMEND MANDATORY REPLACEMENT AT A SPECIFIED TIME OR REDESIGN OF ARRE	STERS.			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005103100199	20051031	00199	EA  	2005	10	31	2005FA0001368    	2	20050908	G	8520	SL18840	CAMSHAFT        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	8946C	800  				287690171	L2201436A	15374K		AT ANNUAL INSPECTION METAL WAS FOUND IN OIL FILTER.  ENGINE WAS TORNDOWN, CAMSHAFT AND LIFTER BODIES WERE DAMAGED.  CAMS	HAFT AND LIGTER BODIES WERE PURCHASED FROM VENDOR, 1/4/93 AND INSTALLED IN ENGINE 4/8/93 IAW 2000 HOUR TBO.  FAILURE OCC	URED, TSO 800 HR.  IT APPEAR FAILURE WAS CAUSED BY MFG DEFECT.  (K)				1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2005103100065	20051031	00065	CE  	2005	10	31	2005FA0001369    	1	20050923	G	3220	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D1      	52060	NE  					NLG	CRACKED         	B			PAZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	561JS					5600413				NOSE LANDING GEAR DOORS WERE OBSERVED TO BE DROOPING SLIGHTLY.  NOSE GEAR RETRACT LINKAGE WAS INSPECTED AND TORQUE TUBE 	WAS OBSERVED TO HAVE A BROKEN WELD AT ONE END CAP.  RECOMMEND INSPECTING WELDS CAREFULLY DURING PERIODIC INSPECTIONS.  (	K)				2	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2005103100213	20051031	00213	NE  	2005	10	31	2005FA0001370    	2	20051003	G	7230	797706	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2997 					P673117NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2997.3 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THE CAUSE OF EXCESSIVE CORROSION IS THE	 WINDAGE TABS NOT BEING ADEQUATELY COATED.  ENGINE SN: P673117NB (TSO: 2997.3 HOURS).  (K)									4	J			1E9				 
2005103100223	20051031	00223	NE  	2005	10	31	2005FA0001371    	2	20051003	G	7230	725008	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		4132 	2997 				P673117NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2997.3 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100225	20051031	00225	NE  	2005	10	31	2005FA0001372    	2	20051003	G	7230	797309	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2997 	2997 				P673117NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2997.3 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100226	20051031	00226	NE  	2005	10	31	2005FA0001373    	2	20051003	G	7230	701106	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03										THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2998.9 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100220	20051031	00220	NE  	2005	10	31	2005FA0001374    	2	20051003	G	7230	797309	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03							P673346NB			THES PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2998.9 HOURS.  THE FOLLOWING PART (COMPRESSOR DISKS) WERE DEEMED S	CRAP DUE TO NOT BE ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION IS THE	 WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100221	20051031	00221	NE  	2005	10	31	2005FA0001375    	2	20051003	G	7230	701505F	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5358 	2407 				P673094NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2407.9 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT	 THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED. (K)									4	J			1E9				 
2005103100209	20051031	00209	NE  	2005	10	31	2005FA0001376    	2	20051003	G	7230	701106C	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2407 					P673094NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2407.9 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPSRSSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT	 THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100210	20051031	00210	NE  	2005	10	31	2005FA0001377    	2	20051003	G	7230	725008F	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5845 	2407 				P673094NB			THESE PART WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2407.9 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOWI	NG PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT 	THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED. (K)									4	J			1E9				 
2005103100227	20051031	00227	NE  	2005	10	31	2005FA0001378    	2	20051003	G	7230	797309	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2407 					P673094NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2407.9 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSP	ECT THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100224	20051031	00224	NE  	2005	10	31	2005FA0001379    	2	20051003	G	7230	701106	COMPRESSOR      								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5823 	2824 				P673173NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100215	20051031	00215	NE  	2005	10	31	2005FA0001380    	2	20051003	G	7230	803108	COMPRESSOR      								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2824 					P6733173NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100228	20051031	00228	NE  	2005	10	31	2005FA0001381    	2	20051003	G	7230	797309	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2824 					P673173NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (K)									4	J			1E9				 
2005103100138	20051031	00138	NE  	2005	10	31	2005FA0001382    	2	20051003	G	7230	496705L	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2954 	1493 				P672774NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 1493.7 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT	 THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PART	S BEING NOT LEGIBLE, THE PN AND SN WERE OBTAINED FROM PREVIOUS RECORDS/ DISK SHEETS).  (K)								4	J			1E9				 
2005110900055	20051109	00055	NE  	2005	11	9	2005FA0001383    	2	20051003	G	7230	701106E	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		4275 	1493 				P672774NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 1493.7 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSP	ECT THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF P	ARTS BEING NOT LEGIBLE, THE PN AND SN WERE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005110900024	20051109	00024	NE  	2005	11	9	2005FA0001384    	2	20051003	G	7230	725008F	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		4502 	1493 				P672774NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 1493.7 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPRESSOR DISK) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSPE	CT THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PA	RTS BEING NOT LEGIBLE, THE PN AND SN WERE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005102800135	20051028	00135	NE  	2005	10	28	2005FA0001385    	2	20051003	G	7230	797309B	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		1493 					P672774NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 1493.7 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOW	ING PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSP	ECT THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF P	ARTS BEING NOT LEGIBLE, THE PN AND SN WERE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS). (K)								4	J			1E9				 
2005103100127	20051031	00127	CE  	2005	10	31	2005FA0001386    	1	20050914	G	5610	PAS660011510	WINDOW          			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	CORRODED        	B			N38R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	630SJ					344				ABOUR 1 INCH IN FROM THE OUTER EDGE OF THE WINDOW IT LOOKS LIKE THERE HAS BEEN A CHEMICAL REACTION WERE THE OUTER AND IN	NER WINDOW WAS PUT TOGETHER.  THIS WAS FOUND ON FOUR OTHER WINDOWS ON THE SAME AIRCRAFT.  (K)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005103100020	20051031	00020	NE  	2005	10	31	2005FA0001387    	2	20051003	G	7230	701505	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5891 	2998 				P637881NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION I	S THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PARTS BEING NOT LEGIBLE, THE PN AND SN WERE 	OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005110900054	20051109	00054	NE  	2005	11	9	2005FA0001388    	2	20051003	G	7230	496706	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5129 	2998 							THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISK) WERE DEEMED 	SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION IS	 THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PARTS BE NOT LEGIBLE, THE PN AND SN WERE OBTA	INED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005110800289	20051108	00289	NE  	2005	11	8	2005FA0001389    	2	20051003	G	7230	725008	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5859 	2998 				P637881NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISKS) WERE DEEMED	 SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSIO	N IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PARTS BEING NOT LEGIBLE, THE PN AND SN WE	RE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005110800290	20051108	00290	NE  	2005	11	8	2005FA0001390    	2	20051003	G	7230	701409	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		5545 	2998 				P637881NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 2824.2 HOURS.  THE FOLLOWING PARTS (COMPRESSOR DISK) WERE DEEMED 	SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSPECT THAT THE CAUSE OF EXCESSIVE CORROSION	 IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE:  DUE TO PN AND SN OF PARTS BEING NOT LEGIBLE, THE PN AND SN WE	RE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005110800291	20051108	00291	NE  	2005	11	8	2005FA0001391    	2	20051003	G	7230	725008	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		2898 	160  				P673349NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 160.5 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOWI	NG PARTS (COMPRESSOR DISK) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  SUSPECT T	HAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PARTS 	BEING NOT LEGIBLE, THE PN AND SN WERE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005103100091	20051031	00091	NE  	2005	10	31	2005FA0001392    	2	20051003	G	7230	701409	COMPRESSOR WHEEL								PWA   	JT12  	JT12*       	52042	NE  					ENGINE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		160  					P673349NB			THESE PARTS WERE REMOVED FROM SERVICE AT ENGINE TSO OF 160.5 HOURS (PRIOR TO THE ENGINE TBO OF 3000 HOURS).  THE FOLLOWI	NG PARTS (COMPRESSOR DISKS) WERE DEEMED SCRAP DUE TO NOT BEING ABLE TO READ PN AND/OR SN BECAUSE OF CORROSION.  WE SUSPE	CT THAT THE CAUSE OF EXCESSIVE CORROSION IS THE WINDAGE TABS NOT BEING ADEQUATELY COATED.  (NOTE: DUE TO PN AND SN OF PA	RT BEING NOT LEGIBLE, THE PN AND SN WERE OBTAINED FROM PREVIOUS RECORDS/DISK SHEETS).  (K)								4	J			1E9				 
2005102800137	20051028	00137	SO  	2005	10	28	2005FA0001393    	1	20050919	G	3213	40081	STRUT           			MAULE 	M6    	M6235       	5460160	SO  	LYC   	O540  	IO540*      	41532	EA  					LT MLG	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	5648P	1698 				7426C				UPON LANDING, LT MLG OLEO STRUT FOLDED UPWARDS ALLOWING PROP TO CONTACT GROUND.  INVESTIGATION REVEALED MODERATE CORROSI	ON THROUGHOUT STRUT LOWER MOUNT AND BOLT HOLE.  SUGGEST INSPECTING AND CLEANING LOWER ATTACH POINTS EVERY 100 HOURS.  AP	PLY CORROSION INHIBITOR AND CONSIDER SEALING LOWER STRUT OPENING.  (SO11200516668) (K)				1	H	7	1 	3O	3	O		3A23    	1E4				 
2005102800138	20051028	00138		2005	10	28	2005FA0001394    	4	20050718	G	2562	AK450	ELT             			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O360  	IO360A1A    	41514	EA  					CABIN	WEAK            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7689H	190  				12579				ELT TRANSMISSION WAS VERY WEAK.  INSTALLED IN AC FOR LESS THAN 3 YEARS.  INSTALLED 10/18/01.  REMOVED 09/10/04.  (K)						1	H	7	1 	3O	3	O		A780    	1E10				 
2005110800292	20051108	00292	SO  	2005	11	8	2005FA0001395    	2	20050822	G	8530	654004	CYLINDER        			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300A      	17022	SO  					EXHAUST VALVE	FAILED          	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7218M					55518	53018A			CYLINDER WAS REBUILT 5/12/05 USING CURRENT PRODUCTION MFG EXHAUST VALVE AND GUIDE.  THE EXHAUST VALVE STRUCK (17 HOURS I	N SERVICE) RESULTING IN A BROKEN EXHAUST ROCKER ARM, AS A RESULT AN EMERGENCY LANDING WAS SUCCESSFULLY MADE.  (K)					1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2005110800318	20051108	00318	SO  	2005	11	8	2005FA0001396    	2	20050705	G	8530	1691111	CYLINDER HEAD   								CONT  	O520  	IO520BA     	17032	SO  					ENGINE	CRACKED         	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		865  								CYLINDER 16911-11 BLEW A HOLE IN THE SIDE.  CYLINDER 16757-25 CRACKED.  TSN 71.2 ACA CYLINDERS.  (K)											3	O			E5CE				 
2005110800335	20051108	00335	CE  	2005	11	8	2005FA0001398    	1	20050416	G	5524	12346251	ATTACH BRACKET  			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  					LT ELEVATOR	CRACKED         	B			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7367C					U20603905				DURING AN ANNUAL INSPECTION, THE LT ELEVATOR OB ATTACH HINGE WAS FOUND TO BE CRACKED AT WELD.  UPON FURTHER INSPECTION, 	IT WAS NOTED THAT WELD WAS IN FACT ONLY A SPOT WELD.  THIS PART IS SUPPOSED TO BE WELDED THE FULL LENGTH OF THE HINGE.  	PART APPEARS TO BE THE ORIGINAL FACTORY INSTALLED PART.  (K)				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005103100159	20051031	00159	SO  	2005	10	31	2005FA0001399    	2	20050706	G	8530	AEC631397ST712A	CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		991  								ENGINE CYLINDER HEAD CRACKED. (K)											3	O			E5CE				 
2005110800321	20051108	00321	CE  	2005	11	8	2005FA0001400    	1	20050913	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					WINGS	CRACKED         	B			EATR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	385GH					4410066				WHILE ACCOMPLISHING MFG CQB 03-1 EDDY CURRENT INSPECTION THE CANTED RIB CAPS WERE FOUND CRACKED ON THE LT AND RT WINGS. 	 THE AIRCRAFT WILL REQUIRE SERVICE KIT SK441-110-1 REPAIR KIT IAW CQB 03-1 BEFORE FURTHER FLIGHT.  (K)					1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2005103100212	20051031	00212	CE  	2005	10	31	2005FA0001401    	1	20050124	G	2910	6556600020	LINE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					HYDRAULIC SYS	DAMAGED         	B			MNGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	511TH	900  				5600561				HYDRAULIC LINE, PN 6556000-20, ON LT ENGINE IS MAKING CONTACT WITH FUEL LINE PN 3042937-01.  THIS CAUSED CHAFFING IN EXC	ESS OF 20 PERCENT OF THE WALL THICKNESS ON THE HYDRAULIC LINE AND 10 PERCENT TO 15 PERCENT WALL THICKNESS ON THE FUEL LI	NE.  BOTH LINES WERE REPLACED WITH FACTORY NEW PARTS.  AFTER PART REPLACEMENT CONTACT WAS STILL BEING MADE AND REQUIRED 	THAT SLIGHT ADJUSTMENTS TO THE BENDS ON THE LINES WERE REQUIRED TO MAINTAIN ADEQUATE CLEARANCE.  (K)			2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005110900018	20051109	00018	CE  	2005	11	9	2005FA0001402    	1	20050124	G	2910	OA553191	CONTROL VALVE   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					HYD SYSTEM	SHORTED         	B			MNGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	511TH	900  				5600561				FLAP CONTROL VALVE PN 2710970 TO BE MAKING CONTACT WITH DUMP VALVE PN OA55319-1 CAUSING WAS SUBSTIALLY DAMAGE.  BY SHORT	ING THE STAND OFF ON THE BOTTOM SIDE OF THE DUMP VALVE BY APROX .1250 OF AN INCH A CLEARANCE OF APROX .0625 OF AN INCH W	AS OBTAINED.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005110900010	20051109	00010	EA  	2005	11	9	2005FA0001403    	2	20050920	G	8530		CYLINDER HEAD   			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	6494J					284925	L1938736A			NR 3 CYLINDER PRODUCED CRACK FROM LOWER SPARK PLUG TO EXHAUST PORT, ENGINE LOST POWER DURING CLIMB OUT AT APPROX 700 FT 	ATTEMPT TO RETURN FOR LANDING WAS UNSUCESSFUL, FAILED.  CYCLINDER INSTALLED 1/12/00 RECONDITION CYLINDER TIME UNKNOWN - 	TIME IN SERVICE, APPROX 1300. (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
2005110800337	20051108	00337	SO  	2005	11	8	2005FA0001405    	1	20050922	G	5730	62061002	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  	GE    	CFM56 	CFM567B24   	 	NE  					WING	CRACKED         	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	9089N	9942 				2816003				WING WALK STIFFENER PANEL CRACKED UNDER UPPER WING SKIN, YEARS OF WALKING ON PANEL.  STIFFENER PANEL SHOULD BE HEAVER GA	UGE METAL.  (K)					1	L	7	1 	3O	4	F		2A13    	E00055EN				 
2005103100198	20051031	00198	SO  	2005	10	31	2005FA0001406    	1	20050716	G	5540	6339500	DOUBLER         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER HINGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	9304K					327640076				CRACKS WERE FOUND AT THE TOP OF THE RUDDER SPAR HINGE DOUBLER.  CRACKING WAS ON BOTH SIDES OF THE DOUBLER IN THE BEND RA	DIUS`S.  ACCESS FOR INSPECTION NECCESSITATES REMOVING THE RUDDERS TIP/COUNTERWEIGHT.  RECURRENCE MAY BE PREVENTED BY FAB	RICATING AND INSTALLING AN ADDITIONAL SIMILAR DOUBLER ON THE AFT SIDE OF THE SPAR OPPOSITE THE EXISTING DOUBLER.  HOWEVE	R, THAT MAY EFFECT FLEXIBILITY AND CAUSE THE RUDDER SPAR TO RECEIVE EXTRA STRESS.  (AL03200519295) (K)			1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2005103100069	20051031	00069	CE  	2005	10	31	2005FA0001407    	1	20051010	G	3233	908200151	NUT             			BEECH 	200   	200T        	1152928	CE  										NLG ACTUATOR	FAILED          	C			NBFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	44U		89   			BT14				THE LANDING GEAR WAS BEING OPS CHECKED DURING A SHEDULED COMPLETE INSPECTION.  WITH THE AC ON JACKS, THE LANDING GEAR WA	S BEING RETRACTED WHEN THE ACTUATOR FAILED BEFORE THE GEAR WAS COMPLETELY RETRACTED.  THE NUT ASSY FAILED JUST BELOW THE	 THREADED SECTION WHICH CAUSES THE NLG TO FALL DOWN BUT UNLOCKED WITH NO MEANS TO RETRACT OR LOCK THE GEAR DOWN.  THIS F	AILURE IS VERY SIMILAR TO THE MLG ACTUATOR FAILURE ADDRESSED IN SB 32-3433.  (K)			1	L	7	2 	4T				A24CE   					 
2005103100070	20051031	00070	SW  	2005	10	31	2005FA0001408    	1	20051002	G	2197		CONNECTOR       			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					AUTOPILOT SYS	DISCONNECTED    	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	4171H					240653				CONNECTOR CAME LOOSE FROM SLAVE CONTROLLER WHILE ON THE GROUND.  HSI WAS NOW IN FREE GYRO (UNSLAVED) MODEL BUT THERE WAS	 NO (HDG) FLAG, HENCE GYRO SLOWLY DRIFTED WITHOUT WARNING TO PILOT.  (K)					1	L	7	1 	3O	3	O		2A3     	1E10				 
2005110800310	20051108	00310	CE  	2005	11	8	2005FA0001409    	1	20051005	G	5520	1016100195	TORQUE TUBE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					LT ELEVATOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	6182A	3808 				BB1484				FOUND LT ELEVATOR TORQUE TUBE MOUNTING FLANGE FROM TUBE ASSY TO ELEVATOR RIVETS WORKING LOOSE, ALLOWING THE LT ELEVATOR 	TO HAVE 1.5 INCHES OF PLAY.  THIS WAS FOUND DURING A 400 HOUR LUBRICATION AND INSPECTION.  RECOMMENDATION TO PREVENT REC	URRENCE, USE SOLID RIVET NOT BLIND RIVET.  (K)				1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2005103100083	20051031	00083		2005	10	31	2005FA0001410    	1	20050927	G	8011	ES6462382	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										NEW STARTER DOES NOT TURN FREELY BY HAND.  (K)																			 
2005103100071	20051031	00071		2005	10	31	2005FA0001411    	2	20050927	G	7322	104404	CARBURETOR      																	ENGINE	OUT OF ADJUST   	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										CARBURETOR RUNS LEAN IN THE MID RANGE.  (K)																			 
2005103100084	20051031	00084		2005	10	31	2005FA0001412    	2	20050927	G	7322	105009	CARBURETOR      																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										CARBURETOR, MIXTURE SHUT OFF IS BAD.  (K)																			 
2005102500168	20051025	00168		2005	10	25	2005FA0001413    	1	20050912	G	8011	6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER, CUSTOMER REPORTS AFTER 7.7 HOURS OF OPERATION STARTER SEEPING WAX FROM REAR OF STARTER.  (K)																			 
2005103100042	20051031	00042		2005	10	31	2005FA0001414    	1	20050919	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER, UNABLE TO TURN FREELY BY HAND.  (K)																			 
2005103100043	20051031	00043		2005	10	31	2005FA0001416    	1	20050919	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER, UNABLE TO TURN FREELY BY HAND.  (K)																			 
2005103100080	20051031	00080		2005	10	31	2005FA0001417    	1	20050919	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER, UNABLE TO TURN FREELY BY HAND.  (K)																			 
2005103100081	20051031	00081		2005	10	31	2005FA0001421    	1	20050927	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										NEW STARTER DOES NOT TURN FREELY BY HAND.  (K)																			 
2005103100188	20051031	00188		2005	10	31	2005FA0001422    	1	20050927	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										NEW STARTER DOES NOT TURN FREELY BY HAND.  (K)																			 
2005103100094	20051031	00094		2005	10	31	2005FA0001423    	1	20051007	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER DOES NOT TURN FREELY BY HAND.  (K)																			 
2005103100095	20051031	00095		2005	10	31	2005FA0001424    	1	20050928	G	8011	ES6462751	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER, WAX SEEPING OUT OF END PLATES.  (K)																			 
2005103100189	20051031	00189		2005	10	31	2005FA0001425    	2	20050928	G	7322	1048931	CARBURETOR      																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										CARBURETOR, THIS CARBURETOR WOULD NOT RUN, NEEDLE AND SEAT OVERFLOWS.  (K)																			 
2005103100165	20051031	00165	CE  	2005	10	31	2005FA0001426    	1	20051012	G	5544	10164001423	HINGE           			BEECH 	200   	B200        	1152922	CE  										RUDDER	CORRODED        	B			MGOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	585CE	6720 				BB1194				DURING SCHEDULED PHASE 2 INSPECTION OF AIRCRAFT, FOUND THE CENTER RUDDER HINGE ASSY HAVING INTERGRANULAR CORROSION AROUN	D THE HARDWARE ATTACHING TEE TO THE HINGE ASSY.  THIS TYPE OF CORROSION IS PROBABLY DUE TO THE LOCATION OF THE PART AND 	THE AGE OF THE AIRCRAFT.  (CE09200601298) (K)				1	L	7	2 	4T				A24CE   					 
2005103100167	20051031	00167	NE  	2005	10	31	2005FA0001427    	2	20051010	G	7230	26580471	PLENUM          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	DAMAGED         	B			L3CR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	701SE					208B0701	PCEPC0425	960408		WHILE REMOVING THE ENGINE FOR A SCHEDULED OVERHAUL, WE NOTICED 5 RIVETS SHEARED OFF THE TOP HALF OF THE INDUCTION AIR PL	ENUM BAND ASSEMBLY.  A SHEARED RIVET HEAD CAN EASILY FIT THRU THE ENGINE INLET SCREEN AND COULD BE INGESTED BY THE ENGIN	E CAUSING GREAT DAMAGE OR TOTAL ENGINE FAILURE. (K)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005102800134	20051028	00134	NE  	2005	10	28	2005FA0001428    	2	20051010	G	7230	36580472	PLENUM          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	CORRODED        	B			L3CR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	701SE					208B0701	PCEPC0425	960408		WHILE REMOVING THE ENGINE FOR A SCHEDULED OVERHAUL, WE NOTICED 5 RIVETS SHEARED OF THE TOP HALF OF THE INDUCTION AIR PLE	NUM BAND ASSY.  A SHEARED RIVET HEAD CAN EASILY FIT THRU THE ENGINE INLET SCREEN AND COULD BE INGESTED BY THE ENGINE CAU	SING GREAT DAMAGE OR TOTAL ENGINE FAILURE.  (K)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005110800302	20051108	00302		2005	11	8	2005FA0001429    	4	20050706	G	3497		WIRE            			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					TRANSPONDER	CHAFED          	D			F7HS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	861SF					18281438	L2971748			TRANSPONDER CIRCUIT BREAKER POPPED AND PILOTS NOTED SMOKE IN CABIN.  FLIGHT WAS DISCONTINUED AND DISCREPENCY WAS NOTED. 	 AFTER INSPECTION, CHAFFED WIRE WAS FOUND NEAR THE AVIONICS RACK THAT HAD SHORTED ON THE AIRFRAME.  THE WIRES WERE REPAI	RED IAW MFG RECOMMENDATION.  MFG ALSO RECOMMENDED ANTI-CHAFE BE INSTALLED ON AIRFRAME AT THE LOCATION OF CHAFFING.  (WP1	3200510948) (K)			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2005110800323	20051108	00323	WP  	2005	11	8	2005FA0001430    	2	20050915	G	7200	31018303	DUCT            			MTSBSI	MU2   	MU2B40      	5780440	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	FAILED          	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	361MA	4055 				429SA	P36200			ENGINE EGT SUDDENLY ROSE IN FLIGHT AND POWER HAD TO BE REDUCED.  SAFE LANDING ACCOMPLISHED AT HOME BASE.  TROUBLESHOOTIN	G REVEALED THE COMPRESSOR CROSSOVER DUCT (DIFFUSER) HAD FAILED, CAUSING LOW COMPRESSOR PERFORMANCE.  A VANE HAD BROKEN O	FF AND LODGED, PREVENTING CATASTROPHIC FAILURE OF COMPONENTS DOWNSTREAM.  INVESTIGATION REVEALED THIS PART WAS REQUIRED 	TO BE REPLACED WITH AN UPGRADED DUCT LESS PRONE TO FAILURE AT THE ENTINE TBO EXTENSION, WHICHC WAS RECORDED IN MAINTENAN	CE RECORDS AS HAVING BEEN ACCOMPLISHED AT AN EARLIER TIME, AND THE ENGINE CERTIFIED TO MEET THE 5400 HOUR TBO. (K)		1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
2005110900007	20051109	00007	WP  	2005	11	9	2005FA0001431    	2	20050915	G	7220	31018303	DUCT            			MTSBSI	MU2   	MU2B40      	5780440	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					ENGINE	LOOSE           	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	361MA	4055 				429SA	P36199			ENGINE WAS TORN DOWN, BY AN APPROVED ENGINE SERVICE CENTER, FOR AN AUDIT OF ITS SB AND TBO CONFIGURATION, DUE TO CROSSOV	ER DUCT/DIFFUSER FAILURE OF ITS SISTER ENGINE ON THE SAME AIRCRAFT.  IT WAS FOUND THE MAINTENANCE RECORDS CONCERNING SB 	STATUS AND TBO STATUS WERE IN ERROR ON THIS ENGINE ALSO AND INSPECTION OF THE CROSSOVER DUCT ASSY IN THIS ENGINE WAS FOU	ND VERY LOOSE, BUT NOT YET FAILED.  FAILURE OF THIS PART WAS IMINENTNENT AND SEALS IN THIS DUCT WERE MOSTLY FAILED, AFFE	CTING COMPRESSOR AND ENGINE POWER. COMPRESSOR CROSSOVER DUCT/ DIFFUSER POOR CONDITION FOR ENGINE.  (K)		1	H	7	2 	3T	3	T	RT	A10SW   	E2WE				 
2005102000109	20051020	00109	NE  	2005	10	20	2005FA0001432    	2	20050920	G	7240	1968M63G11	LINER           								CFMINT	CFM56 	CFM565A3    	 	NE  					COMBUSTION CHAM	BURNED          	B			CT5Y	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	33		19566	3031 		42X31412		731433			THE CORE MAJOR MODULE 02X31733 FOR COMBUSTOR DISTRESS.  THIS WAS CONFIRMED ON EXPOSURE, WHERE SIDNIFICANT BURNING AND BU	RN-THROUGH ON THE OUTER LINER WAS SEEN IN LINE WITH FUEL NOZZLE NR 15.  THE COMBUSTION CHAMBER WAS PREVIOUSLY REPAIRED A	ND IS WITH MFG FOR INVESTIGATION.  (K)									4	F			E29NE				 
2005102000114	20051020	00114	NE  	2005	10	20	2005FA0001433    	2	20051009	G	7200	0292005310	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					NR 2	FLAMED OUT      	C				B	A			EMER. DESCENT           	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			EA	17	88CP	2393 	79   			760500				WHILE IN CRUISE, WE WERE VMC ON TOP OF A CLOUD DECK, EXPERIENCED A NR 2 ENGINE CHIP LIGHT.  IMMEDIATELY, NR 2 ENGINE SHU	TDOWN.  NR 1 AUTOPILOT ALSO DROPPED OFF LINE.  EMERGENCY WAS DECLARED AND SINGLE ENGINE INSTRUMENT ILS APPROACH WAS ACCO	MPLISHED. WEATHER AT THE TIME WAS ABOUT 700 FT OVC WITH 5 MILES VISUAL.  INSPECTION REVEALED CONTAINED ENGINE FAILURE WI	TH A SIGNIFICANT AMOUNT OF METAL DEBRIS ON ACCY GB MECHANICAL CHIP PLUG.  THIS ENGINE HAD ONLY 79 HOURS ON IT SINCE RETU	RN FROM MFG FOR REPAIR DUE TO METAL CHIPS.  NR 1 ENGINE EXPERIENCED A 30 SEC POWER EXCURSION DURING ENGINE FAILURE, REQU	IRING IT'S REMOVAL AS WELL. SPECULATION WOULD INDICATE A FAULTY REPAIR.	1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2005102400097	20051024	00097	SW  	2005	10	24	2005FA0001434    	1	20051014	G	5320	407010105101	STOP            			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		2500 								DROOP STOP STUDS HAD CRACK INDICATIONS IN RADIUS DURING FLUORESCENT PENETRATE CHECK. NEW STYLE STOPS INSTALLED.						1	G	7	1 	3U			O	H2SW    					 
2005102000163	20051020	00163	CE  	2005	10	20	2005FA0001435    	1	20051014	G	3250	0024100397	BELLCRANK       			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					STEERING	FRACTURED       	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	21	555ND					TH1750				THE CO-PILOTS RUDDER/STEERING BELLCRANK FRACTURED AT THE CENTER CONNECTING POINT CAUSING A LACK OF NOSE WHEEL STEERING O	N THE CO-PILOTS SIDE.					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005102000169	20051020	00169	NE  	2005	10	20	2005FA0001436    	2	20051015	G	8530		EXHAUST VALVE   			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	R2800CB16   	52026	NE  					ENGINE	STICKING        	I			Z5QB	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	29	996DM		180  			45563				ENGINE EXHAUST VALVE STICKING (5 TIMES) MOST LIKELY CAUSED BY OIL. THE MFG ADDITIVE IN CONTACT WITH LEAD ON THE VALVE ST	EM CAUSES EXCESSIVE PHOSPHOR BUILDUP AND THE VALVE TO STICK. MFG IS AWARE OF THIS PROBLEM.					2	L	7	4 	4R	4	R		6A4     	5E8				 
2005102400158	20051024	00158	CE  	2005	10	24	2005FA0001437    	1	20051017	G	5410	11420247	STUD            			CESSNA	172   	172R        	2072401	CE  	LYC   	O320  	IO320*      	41508	EA  					ENGINE COWLING	COLLAPSED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										THE STUD SPRINGS ARE COLLAPSING UPON INSTALLATION. SUSPECT POOR HEAT-TREATING OF THE SPRINGS.  NOTICED EXCESSIVE CHAFFIN	G (SMOKING) FROM THE ENGINE COWLING SINCE AIRCRAFTS WERE NEW.  AT ABOUT 300TT THE RECEPTACLES FOR THE STUDS STARTED TO F	AIL. WHEN NEW STUDS AND RECEPTACLES WERE INSTALLED, NOTICED THE SPRINGS COLLAPSED AND DID NOT RETURN TO THEIR BEFORE HEI	GHT. THIS CONDITION ALLOWS THE ENGINE COWLING TO FIT LOOSELY AND VIBRATE ENOUGH TO CAUSE THE (SMOKING) AND TO WEAR OUT T	HE RECEPTACLES.		1	H	7	1 	3O	3	O	NT	3A12    	1E12				 
2005110800297	20051108	00297	SO  	2005	11	8	2005FA0001438    	1	20050622	G	8011		GEAR            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					STARTER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	63954				85022809	277854085				ON RESTART IN THE AIR THE STARTER DRIVE GEAR BROKE.  THE PILOT WAS UNABLE TO START THE ENGINE.  THE GEAR ALSO DAMAGED TH	E RING GEAR ON THE ENGINE.  (K)					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005103100214	20051031	00214	CE  	2005	10	31	2005FA0001439    	1	20051004	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					CABIN	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T	134  				CE1350	825982R			GEAR WOULD NOT RETRACT MADE NO NOISE AT ALL.  MAINTENANCE TECH TROUBLESHOOT GEAR SYSTEM AND FOUND THAT THE DYNAMIC RELAY	 WAS INTERMITTENT.  NO RECOMMENDATION AT THIS TIME. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005110800298	20051108	00298	CE  	2005	11	8	2005FA0001440    	1	20051006	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					DYNAMIC BREAKER	INTERFERENCE    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1556A	26   				CE1318				PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE DOWN POSITION, THE GEAR WOULD NOT EXTEND, AFTER CYCLING GEAR SELEC	TOR GEAR WENT DOWN, AC RETURNED TO BASE.  ON TROUBLESHOOTING, THE MECHANIC SELECTED DOWN AND IT FAILED TO EXTEND, AFTER 	TAPPING ON TOP OF RELAY THE GEAR WENT DOWN.  PROBABLE CAUSE AT THIS TIME IS UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY I	AW DATE CODE.  (K)			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005102500072	20051025	00072	EU  	2005	10	25	2005FA0001441    	1	20051021	G	2720	A740255N	CONTROL CABLE   			LET   	L23   	L23         	1360308	EU  										RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	410BA	160  				029005				RT RUDDER CABLE FOUND FRAYED AT FORWARD NR 1 PULLEY.						1	K	0	0 	  			RC	G24EU   					 
2005103100205	20051031	00205	SW  	2005	10	31	2005FA0001442    	1	20050930	G	2720	12364	CONTROL CABLE   			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					RUDDER	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	113AW	5888 				88876				LT RUDDER CABLE BROKE NEAR REAR SEAT BACK HINGE PIVOT BOLT.  NO EVIDENCE OF CABLE CHAFFING ON REAR SEAT FRAME, PULLEY AR	EA, CABLE GUIDE OR SIDE PANEL UPHOLSTERY.  OPTIONAL WIDE REAR SEAT.  NTSB SENT CABLE TO LAB FOR ANALYSIS.  RESULTS PENDI	NG.  AC HAD MADE 3 LANDINGS ON THIS FLIGHT.  ON 4TH LANDING, AIRCRAFT STARTED TO DRIFT RT, PILOT APPLIED CORRECTIVE LT P	EDAL AND CABLE BROKE RESULTING IN A GROUND LOOP AND SUBSTANTIAL DAMAGE TO AIRCRAFT.  (NM03200513237) (K)			1	H	7	1 	3O	3	O	NC	A759    	E274				 
2005103100204	20051031	00204	CE  	2005	10	31	2005FA0001443    	1	20050805	G	3230		GEARBOX         			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MLG	WORN            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	414RJ	7468 				4140632				NOSE LANDING GEAR COLLAPSED ON LANDING ROLL-OUT.  UNABLE TO FIND A BROKEN PART, HOWEVER, LINKAGE WAS WORN INCLUDING PART	S IN GEARBOX.  CONDITION COULD LEAK TO INSUFFICENT OVER-CENTER TENSION ON DOWN LOCK LINKAGE. (SW17200508357)  (K)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2005110800346	20051108	00346	GL  	2005	11	8	2005FA0001444    	1	20051005	G	5610	2056000101	CANOPY          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					COCKPIT	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	644DC	754  				C0144				GLASS SEPARATING FROM FRAME.  (EA07200505548) (K)						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2005103100141	20051031	00141	GL  	2005	10	31	2005FA0001445    	1	20051005	G	5610	2056000101	CANOPY          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					COCKPIT	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	542DC	1164 				C0142				CANOPY GLASS SEPARATING FROM FRAME.  (EA07200505547) (K)						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2005103100142	20051031	00142	SO  	2005	10	31	2005FA0001446    	1	20051010	G	2910	50157001	LINE            			PIPER 	PA31T 	PA31T       	7103124	SO  										HYDRAULIC SYS	CHAFED          	B			GW1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	78CA	5144 				31T7920062				CUSTOMER REPORTED RED FLUID SEEP AT TOP IB OF RT WING.  RT IB LEADING EDGES WERE REMOVED.  IT WAS DETERMINED THAT A LEAD	ING EDGE RETAINING SCREW HAD CHAFED THE RT HYDRAULIC PRESSURE LINE AND SUBSEQUENTLY CAUSED A HYDRAULIC LEAK.  THE LINE W	AS REPLACED AND THE AC WAS RETURNED TO SERVICE.  THIS AREA IS NOT NORMALLY ACCESSED DURING PERIODIC INSPECTIONS.  IT IS 	SUGGESTED THA THE AREA BE INSPECTED AT 800 HOUR INTERVALS.  (EA03200602866) (K)			1	L	7	2 	3T				A8EA    					 
2005103100047	20051031	00047	SO  	2005	10	31	2005FA0001447    	1	20050930	G	5730	89640826	SKIN            			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					WING ROOT	WRINKLED        	B			ECWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	53516	619  				4697132	PCERM0140			DURING ANNUAL INSPECTION NOTED WING ROOTS, BOTH LT AND RT WRINKLED.  AREA OF DEFECT IS FORWARD OF MAIN CARRY THRU SPAR. 	 A SERIES OF 3 WAVES EXTENDING APPROXIMATELY 6-8 INCHES LONG.  PROBABLE CAUSE: SEVERE TURBULENCE OR OVER CONTROL OF AIRC	RAFT EXCEEDING (G) LIMITATIONS.  WING REMOVED AND REPLACED.  (K)				1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2005103100016	20051031	00016		2005	10	31	2005FA0001448    	1	20051012	G	8011	MCL6501	STARTER         																	ENGINE	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER DOES NOT TURN FREELY BY HAND. (K)																			 
2005103100130	20051031	00130	SO  	2005	10	31	2005FA0001449    	1	20051017	G	8011		BUSHING         			PIPER 	PA28  	PA28161     	7102803	SO  										STARTER	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	5336S	302  			E123293	2842133				STARTER BENDIX, FRONT BUSHING FAILURE. (K)						1	L	7	1 	3O				2A13    					 
2005110900036	20051109	00036	NE  	2005	11	9	2005FA0001450    	2	20051012	G	7313		SEAL            								PWA   	JT8   	JT8D15      	52051	NE  					FUEL NOZZLE	WRONG PART      	B			Z3EY	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	03							709210			INCORRECT SEAL INSTALLED ON PRE-ASB6169 FUEL NOZZLES, PT NR 809137-01,  SEAL NR 814352 INSTALLED, CORRECT SEAL FOR PRE A	SB6169 IS NR 775723.  (K)										4	F			E2EA				 
2005102800136	20051028	00136	SO  	2005	10	28	2005FA0001451    	2	20051021	G	8500		ENGINE          			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520D   	17032	SO  						MAKING METAL    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	6675Q					421B0442	219277R			AT INITIAL 10 HR OIL CHANGE, A LARGE AMOUNT OF WHAT APPEARS TO BE BEARING MATERIAL WAS FOUND IN THE DRAIN OIL, DRAIN PLU	G, AND ON FURTHER EXAMINATION, THE OIL FILTER.  ENGINE WAS REMOVED FROM SERVICE AT THIS TIME AND SENT BACK TO OVERHAUL F	ACILITY FOR FURTHER EXAMINATION.  (K)				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005103100201	20051031	00201	WP  	2005	10	31	2005FA0001452    	2	20050729	G	7230	18114PMA	BEARING         								GARRTT	TPE331	TPE33110    	01514	WP  					COMPRESSOR	FLAKING         	B			DSCR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25		112  					P31201			PN 18114 IS PMA REPLACEMENT FOR PN 31014051.  THIS BEARING WAS REMOVED WITH SEVERE FLAKING/ PEELING OF THE SILVER PLATIN	G THAT RESULTED IN CONTAMINATION OF THE ENGINE OIL.  (K)										4	T			E4WE				 
2005103100049	20051031	00049	EU  	2005	10	31	2005FA0001453    	1	20050502	G	7160	350A108004	INTAKE          			SNIAS 	350   	AS350*      	       	EU  										ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										CRACKS IN BASE METAL AND PITTING.  ENGINE VIBRATION EXPOSURE TO ENVIRONMENT.  (K)						1	G	7	1 	3U				H9EU    					 
2005103100086	20051031	00086	EU  	2005	10	31	2005FA0001454    	1	20051014	G	7160	350A54108004	INTAKE          			SNIAS 	350   	AS350*      	       	EU  										NACELLE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										CRACK IN BASE METAL FROM ENGINE VIBRATION.  (K)						1	G	7	1 	3U				H9EU    					 
2005103100087	20051031	00087	EU  	2005	10	31	2005FA0001455    	1	20051014	G	7810	117651121	EXHAUST PIPE    			BOLKMS	117   	BK117A1     	5626010	EU  										ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										EXHAUST PIPE, CRACKED IN BASE METAL FROM ENGINE VIBRATION.  (K)						1	G	7	2 	3U				H13EU   					 
2005103100099	20051031	00099	WP  	2005	10	31	2005FA0001456    	2	20050909	G	7250		TURBINE         			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7314R    	01518	WP  					ENGINE	FAILED          	B			CNQ3	A				UNSCHED LANDING         				E	X	J	VIBRATION/BUFFET          	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			GL	13	175DP	1302 				6507116	102348			AIRCRAFT WAS LEVEL AT 38,000 FT AND THE CREW REPORTED THEY HEARD AN AUDIBLE THUD.  UPON SCANNING THE COCKPIT INSTRUMENTS	 THE LT ENGINE WAS OBSERVED TO BE SHUTTING DOWN NON-COMMANDED.  AIRCRAFT LANDED WITHOUT INCIDENT.  INITIAL INSPECTION RE	VEALED THE LT ENGINE EXPERIENCED A NON-CONTAINED FAILURE IN THE AREA OF THE TURBINE SECTION.  FAILED ENGINE WAS REMOVED 	FROM AIRCRAFT AND SHIPPED TO MFG FOR INVESTIGATIVE TEARDOWN.  (K)			2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2005110800288	20051108	00288	CE  	2005	11	8	2005FA0001457    	1	20051010	G	2750		TRANSMITTER     			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D1      	52060	NE  					TE FLAPS	OUT OF ADJUST   	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	419CW					RK19				FLAP ASYMMETRY ANNUNCIATOR ILLUMINATED DURING APPROACH.  FOUND MIDBOARD ASYMMETRY DETECTOR READING 5.7 VOLTS.  FOUND IB 	ASYMMETRY DETECTOR READING 7.8 VOLTS.  ADJUSTED LT AND RT FLAP POSITION TRANSMITTERS AS REQUIRED IAW MM TO BRING VOLTAGE	S TO 5.8 VOLTS +/- 0.2 VOLTS.  FLAP SYSTEM FUNCTIONAL CHECKS SATISFACTORY, NO ASYMMETRY FAULTS INDICATED AFTER 20 CYCLES	.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2005102700018	20051027	00018	EU  	2005	10	27	2005FA0001458    	1	20050428	G	7810	M10DE0104	EXHAUST STACK   			AEROSP	ATR42 	ATR42*      	8680900	EU  										ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										CRACKING IN EXHAUST DUCT BASE METAL, ENGINE VIBRATION.  (K)						2	H	7	2 	4T			RT	A53EU   					 
2005102700020	20051027	00020	EU  	2005	10	27	2005FA0001459    	1	20050430	G	7810	7811200000200	EXHAUST PIPE    			AEROSP	ATR42 	ATR42*      	8680900	EU  										ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										CRACKS IN BASE METAL NEAR FLANGE.  ENGINE VIBRATION.  (K)						2	H	7	2 	4T			RT	A53EU   					 
2005102700021	20051027	00021	EA  	2005	10	27	2005FA0001460    	1	20050421	G	3210	C6UM11107	LANDING GEAR    			DHAV  	DHC6  	DHC6        	2802606	EA  										MAIN	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										LANDING GEAR, CRACK IN WELD, CAUSED BY CYCLIC STRESS DUE TO LANDING LOADS. (K)						1	H	7	2 	3T			RT	A9EA    					 
2005110800303	20051108	00303	EU  	2005	11	8	2005FA0001461    	1	20051005	G	5412	L713M2072104	FIREWALL        			UROCOP	EC135 	EC135P1     	8680990	EU  										FUSELAGE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										FIREWALL, CRACK IN BASE METAL DUE TO ENGINE VIBRATION.  (K)						1	G	7	2 	3U			O	H88EU   					 
2005110800287	20051108	00287	EU  	2005	11	8	2005FA0001462    	1	20051011	G	7810	S7811200000200	PIPE            			AEROSP	ATR72 	ATR72       	       	EU  										ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										JET PIPE, CRACK IN BASE METAL PARALLEL TO ATTACH FLANGE, FROM VIBRATION.  (K)						2	H	7	2 	4T			RT	        					 
2005103100018	20051031	00018	CE  	2005	10	31	2005FA0001463    	1	20051004	G	2721	6226717104	SERVO           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					RUDDER BOOST	INTERMITTENT    	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	480LX					RK398				INVESTIGATED PILOT REPORT OF INTERMITTENT (RUDDER BOOST FAIL) ANNUNCIATOR LIGHT DURING TAKEOFF, CRUISE, AND CLIMB SEGMEN	TS.  FOUND RUDDER SERVO WOULD SPIKE HIGH VOLTAGE BUT YAW DAMPER WOULD STAY ENGAGED.  REPLACED RUDDER BOOST SERVO W/OVERH	AULED REPLACEMENT UNIT, SYSTEM FUNCTIONAL TESTS SATISFACTORY.  (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2005110800342	20051108	00342	SO  	2005	11	8	2005FA0001464    	1	20051012	G	3244	304K632	TIRE            			EMB   	135   	EMB135BJ    	3260306	SO  										MLG	LEAKING         	B			WC7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25										DURING LEAK CHECK OF A NEW TIRE, IT WAS DISCOVERED THAT THE SIDEWALL WEEP HOLES WERE LEAKING, THIS CONDITION WAS NOTICED	 AFTER THE TIRE HAD COMPLETED A 12 HOUR LEAK CHECK.  (K)					2	L	7	2 	4F			RT	        					 
2005103100051	20051031	00051		2005	10	31	2005FA0001465    	4	20051003	G	3418	07133481	STALL WARNING   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RT WING	INOPERATIVE     	D				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			EA	07	5352A	587  				172S9382				DURING STUDENTS STALL PRACTICE THE WARNING HORN FAILED TO OPERATE THROUGH FULL STALL, CFI HALTED MANEUVER.  TROUBLESHOOT	ING CONFIRMED THAT WARNING HORN ASSY, PN 07133481 WAS DEFECTIVE.  UNIT WAS REPLACED WITH NEW.  THIS IS THE 7TH HORN REPL	ACED IN THIS FLIGHT SCHOOL IN CAUSE IS THE CHEAP GRADE OF PLASTIC USED TO MFG THE REED IN THIS ITEM.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005102800065	20051028	00065	CE  	2005	10	28	2005FA0001466    	1	20051021	G	7603	1065240159	LINKAGE         			BEECH 	58    	58          	1152740	CE  										THROTTLE	JAMMED          	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			WP	27	879JN	849  				TH2066				DURING POWER APPLICATION FOR TOUCH AND GO, UNABLE TO ADVANCE THROTTLE ON RT ENGINE.  FOUND THE LOWER NUT WHICH SECURES T	HE PHENOLIC BLOCK FOR THE ANTI-RETRACT CAM TO THE THROTTLE LINKAGE ROD HAD COME OFF, ALLOWING THE BLOCK TO SEPARATE FROM	 THE LINKAGE ROD. DURING ATTEMPTED POWER-UP, THE NOW UNATTACHED LINKAGE ROD JAMMED AGAINST THE AIRCRAFT STRUCTURE.  THE 	PHENOLIC BLOCK IS ATTACHED TO THE ROD WITH AN315 NUTS AND SECURED WITH A SPLIT LOCK-WASHER. RECOMMEND THAT THE LOWER NUT	 ESPECIALLY BE REPLACED WITH A MS21044N3 NUT, OR BETTER YET A NAS1291-3 NUT, WHICH IS EASIER TO INSTALL.		1	L	7	2 	3O				3A16    					 
2005103100107	20051031	00107		2005	10	31	2005FA0001467    	1	20051012	G	8011	MCL6501	STARTER         																	ENGINE	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER DOES NOT TURN FREELY BY HAND.  (K)																			 
2005103100118	20051031	00118	CE  	2005	10	31	2005FA0001468    	1	20051002	G	2810	20344	FUEL CELL       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					RT WING IB	FAILED          	B			EA4R	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	09	92DD	504  				TH1167				WHILE ENROUTE, PILOT EXPERIENCED TOTAL LOSS OF REMAINING FUEL IN RT WING.  DURING FLIGHT WITHOUT WARNING.  SUBSEQUENTLY 	RT ENGINE EXPERIENCED UNCOMMANDED SHUTDOWN DUE TO FUEL STARVATION.  LARGE QUANTITY OF FUEL LOST IN SHORT TIME.  PILOT LA	NDED, TROUBLESHOT AC AND FOUND RT IB FUEL CELL LEAKING.  FUEL CELL REMOVED AND INSPECTED.  INSPECTION REVEALED INTERCONN	ECT PORTION OF FUEL CELL HAD DEBONDED FROM CELL.  RECOMMEND FAA INSPECT SUBJECT CELL AND DETERMINE REASON FOR PREMATURE 	FAILURE.  DUE TO LOCATION OF FAILURE, REGULAR INSPECT OF FAILURE POINT IS NOT OPTION.		1	L	7	2 	3O	3	O		3A16    	E5CE				 
2005110100001	20051101	00001	EU  	2005	11	1	2005FA0001469    	1	20051027	G	3210	A751305N	DAMPER          			LET   	L23   	L23         	1360308	EU  										MLG	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	437BA	1135 				029015				UPPER HINGE ARM OF GEAR STRUT CRACKED AT WELDS.						1	K	0	0 	  			RC	G24EU   					 
2005110700175	20051107	00175	EA  	2005	11	7	2005FA0001470    	2	20051028	G	7497		P-LEAD          			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					LT MAGNETO	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	7721D	2309 	2309 			225395				DURING RUNUP AFTER ANNUAL INSPECTION, LT MAG WAS NOT WORKING.  FOUND INSULATION ON P-LEAD WIRE WAS DETERIORATING AND SHO	RTING TO SHIELDING CAUSING MAG TO BE CONTINUOUSLY GROUNDED NO MATTER WHAT SWITCH POSITION WAS.  REPLACED SECTION OF P-LE	AD AS REQUIRED.  THIS WIRING IS DIRECTLY ABOVE EXHAUST AND DETERIORATION WAS PROBABLY CAUSED BY HEAT OF EXHAUST SYSTEM O	VER TIME.			1	H	7	1 	3O	3	O		1A6     	E274				 
2005110700176	20051107	00176	EA  	2005	11	7	2005FA0001471    	2	20051028	G	7497		P-LEAD          			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					MAGNETO	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	7721D	2309 	2309 			225395				DURING RUNUP AFTER ANNUAL INSPECTION, LT MAG WAS NOT WORKING.  FOUND INSULATION ON P-LEAD WIRE WAS DETERIORATING AND  SH	ORTING TO SHIELDING CAUSING MAG TO BE CONTINUOUSLY GROUNDED NO MATTER WHAT SWITCH POSITION WAS.  REPLACED SECTION OF P-L	EAD AS REQUIRED.  THIS WIRING IS DIRECTLY ABOVE EXHAUST AND DETERIORATION WAS PROBABLY CAUSED BY HEAT OF EXHAUST SYSTEM 	OVER TIME.			1	H	7	1 	3O	3	O		1A6     	E274				 
2005110700177	20051107	00177	EA  	2005	11	7	2005FA0001472    	2	20051028	G	7497		P-LEAD          			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					MAGNETO	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	7721D	2309 	2309 			225395				DURING RUNUP AFTER ANNUAL INSPECTION, LEFT MAG WAS NOT WORKING.  FOUND INSULATION ON P-LEAD WIRE WAS DETERIORATING AND  	SHORTING TO SHIELDING CAUSING MAG TO BE CONTINUOUSLY GROUNDED NO MATTER WHAT SWITCH POSITION WAS. REPLACED SECTION OF P-	LEAD AS REQUIRED.  THIS WIRING IS DIRECTLY ABOVE EXHAUST AND DETERIORATION WAS PROBABLY CAUSED BY HEAT OF EXHAUST SYSTEM	 OVER TIME.			1	H	7	1 	3O	3	O		1A6     	E274				 
2005110700178	20051107	00178	EA  	2005	11	7	2005FA0001473    	2	20051028	G	7497		P-LEAD          			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					MAGNETO	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	7721D	2309 	2309 			225395				DURING RUNUP AFTER ANNUAL INSPECTION, LEFT MAG WAS NOT WORKING.  FOUND INSULATION ON P-LEAD WIRE WAS DETERIORATING AND  	SHORTING TO SHIELDING CAUSING MAG TO BE CONTINUOUSLY GROUNDED NO MATTER WHAT SWITCH POSITION WAS. REPLACED SECTION OF P-	LEAD AS REQUIRED.  THIS WIRING IS DIRECTLY ABOVE EXHAUST AND DETERIORATION WAS PROBABLY CAUSED BY HEAT OF EXHAUST SYSTEM	 OVER TIME.			1	H	7	1 	3O	3	O		1A6     	E274				 
2005110900058	20051109	00058	EU  	2005	11	9	2005FA0001474    	1	20051012	G	3320	6335110	BULB            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN LIGHTING	IMPROPER PART   	B			JGVR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	09	803JL					258160				A SELA FLORESCENT BULB WAS FOUND IN THE CABIN LIGHTING SYSTEM.  THIS SYSTEM IS AN ALC SYSTEM.  THE SELA BULB HAD IMPROPE	R CONNECTORS ON IT AS WELL.  WE CHANGED OUT THE SELA BULB WITH AN ALC BULB AND USED THE PROPER CONNECTORS WHEN INSTALLIN	G IAW AD 95-22-01 AND IB 90-001.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005110800281	20051108	00281	EA  	2005	11	8	2005FA0001475    	2	20051025	G	7200		ENGINE          			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  						SEIZED          	B			K08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	34HG					34	86183			ENGINE INSTALLED ON AIRCRAFT AFTER RETURN FROM REPAIR FACILITY.  DURING INITIAL GROUND RUN OF ENGINE THE POWER LEVER SEI	ZED AND VERY HARD TO MOVE.  ENGINE TEMPERATURE AND PRESSURE WERE NORMAL.  FEATHERED THE PROPELLER AND SHUTDOWN ENGINE.  	POST INSPECTION SHOWED NO LEAKS WITH THE PROPELLER VERY HARD TO TURN AND BETA REVERSING LEVER SEIZED.  (K)				2	H	7	4 	4T	4	T		A20EA   	E4EA				 
2005110900090	20051109	00090	SO  	2005	11	9	2005FA0001476    	1	20050911	G	2910	NAS161210A	O-RING          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					HYD SHUTOFF VLVE	LEAKING         	B			EBVR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	09	165ST	3    				1053				HYD LINE WAS REPLACED DUE TO CRACK IN FLARE AT TEE FITTING.  REPLACEMENT OF LINE REQUIRED INSTALL OF NEW O-RING, WHERE T	EE FITTING ATTACHES TO FLIGHT CTRL HYD SHUT OFF VALVE.  AFTER INSTALL OF HYD LINE AND O-RING, A LEAK CHECK WAS PERFORMED	.  NO LEAKS WERE NOTED.  AC WAS APPROVED FOR RETURN TO SERVICE.  AFTER 2.6 HOURS, O-RING FAILED CAUSING LEAKAGE OF HYD F	LUID FROM COMBINED HYD SYS.  AC MADE PRECAUTIONARY LANDING.  MAINT REPLACED DEFECTIVE O-RING AND SERVICED HYDR SYS.  LEA	K CHECK WAS PERFORMED AND NO DEFECTS WERE NOTED.  DEFECTIVE O-RING WAS INSPECTED AND FOUND TO BE CUT. DETERMINATION ALSO	 COULD NOT BE MADE AS TO WHY O-RING FAILED 2.6 HOURS AFTER INSTALLATION, INITIAL LEAK CHECK SHOWED NO DEFECTS.	2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2005110700171	20051107	00171	CE  	2005	11	7	2005FA0001477    	1	20051010	G	5740		SUPPORT BRACKET 			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					BEND RADIUS	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	888SR	8872 				18261455				WING T/E SKIN SUPPT BRKT CRACKED CAUSED FLAP INTERFERENCE AND FAILURE.  BRKT IS ATTACHED TO EACH FLAP TRACK RIB INSIDE T	/E OF WING, SUPPT T/E WING SKIN IN FLAP BAY.  PART CRACKED, ALLOWED FLAP SUPPT TO GET CAUGHT DURING FLAP RETRACTION, BIN	DING FLAP.  FLAP STRUCTURE FAILED BEFORE FLAP MOTOR CAUSED CB TO TRIP.  RESULTING CONFIGURATION OF FLAP CAUSED YAW IN FL	T.  VERY LITTLE CLEARANCE BTWN THESE BRKTS AND/OR CRACKED WING SKINS AT BRKT ATTACH POINT, FLAP SUPPT RAILS BY DESIGN.  	BRKTS REST FIRMLY AGAINST UPPER PORTION OF FLAP SUPPT RAILS WHEN FLAPS ARE FULLY RETRACTED, PROPERLY RIGGED.  BRKT APPEA	RS TO BE A SUB-PART OF WHOLE RIB ASSY.  IRREGULARITY OF RIVET HOLES IN BRKTS, FLAP TRACK RIB, HAND DRILLED AT FACTORY.	1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2005110700169	20051107	00169	SO  	2005	11	7	2005FA0001478    	1	20051010	G	3210	67040012	FITTING         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	UNSERVICEABLE   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	2871T	5966 				347250178				MLG PIVOT CASTING (FWD TRUNNION FITTING ASSY) ATTACH HARDWARE CONTINUALLY COMES LOOSE ALLOWING CHAFFING BETWEEN CASTING,	 WING SPAR, ENLARGING ATTACH BOLT HOLES IN CASTING AND SPAR.  AFFECTED LT CASTING HAD BEEN PREVIOUSLY REMOVED, INSPECTED	 AND INSTALLED IAW MM FOR THIS REASON ONLY 100 HRS PRIOR TO THIS REOCCURENCE.  CONDITION HAD BEEN NOTED ON RT CASTING AT	 SAME INSPECTION HAD BEEN CORRECTED BY REPLACING CASTING WITH NEW, REAMING ATTACH HOLES IN CASTING, SPAR (UTILIZING APPR	OVED DATA) TO ACCEPT  BOLTS.  NUTPLATES ON THE FWD SIDE OF WING SPAR, NOT ADEQUATE TO ACCEPT STRESSES IMPOSED ON THEM, L	EADING FACTOR IN CONTINUAL LOOSENING OF FWD PIVOT CASTING ATTACH HARDWARE.	1	L	7	2 	3O	3	O		A7SO    	1E10				 
2005110800312	20051108	00312	NM  	2005	11	8	2005FA0001479    	1	20051026	G	2997		WIRE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					CONTROL VALVE	CROSSED         	B			MEDY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	977RY					32740				DURING TROUBLESHOOTING FOLLOWING PTU TEST FIRE, THE PTU CONTROL VALUE AS FOUND FAILED IN CLOSED POSITION WITH 28 VDC ON 	PIN:  2 OF VALVE CONNECTOR.  AN INVESTIGATION REVEALED WIRES WERE CROSSED AT MFG.  WIRING REMADE IAW WDM2911 AND NEW VAL	VE FIT. (SW15200606366) (K)				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005110900115	20051109	00115	CE  	2005	11	9	2005FA0001480    	1	20051018	G	3610		CLAMP           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					INTERCOOLER DUCT	LOOSE           	B			VT3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	6677L					TJ209	518463			IN CRUISE FLIGHT, 2500 RPM, 35 HG, PILOT NOTED L/ENGINE LOST POWER.  PILOT FEATHERED PROPELLER AND POWERED ENGINE.  MAIN	T NOTED INTERCOOLER DUCT, PN 102-389003-3 LOOSE AT DUCT SERV CLAMP WAS LOOSE, DUCT WAS PARTIALLY DETACHED.  REPLACED DUC	T, RUNUP OK.  (K)				1	L	7	2 	3O	3	O		A23CE   	E8CE				 
2005110900104	20051109	00104	EU  	2005	11	9	2005FA0001481    	1	20051004	G	2913	259SF3325	DRAIN           			BRAERO	1000  	BAE1251000A 	1500104	EU  	PWA   	305   	PW305       	 	NE  					HYD PUMP	CHAFED          	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	503QS					259003				RT HYDRAULIC PUMP CASE DRAIN HYDRAULIC LINE RUPTURED IN FLIGHT, DRAINING HYDRAULIC FLUID FROM THE AIRCRAFT SYSTEM.  FOUN	D RT HYDRAULIC PUMP CASE DRAIN LINE CRACKED WHERE LINE HAS BEEN CHAFING.  INSPECTED AIRCRAFT AND FOUND SIMULAR CHAFE IN 	SAME LINE IN SAME LOCATION IN AFT EQUIPMENT BAY.  THIS APPEARS TO BE A COMMON PROBLEM IN THE 1000 SERIES AIRCRAFT WITH T	HE PROXIMITY OF THE AFT BAY HYDRAULIC LINE RUNS.  (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2005110800328	20051108	00328	SO  	2005	11	8	2005FA0001482    	2	20051014	G	8520	633620	CRANKSHAFT      			BEECH 	50    	50          	1152502	CE  	CONT  	O470  	IO470*      	17026	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	9057Q	591  				TC1366	215778R			CRANKSHAFT DEVELOPED CRACK BEHIND PROP FLANGE .3333 - .5 AROUND SHAFT IN FLIGHT, LEAKED OIL STEADY ON GROUND RUN. (EA212	00603317) (K)					1	L	7	2 	3O	3	O		5A4     	E1CE				 
2005110900060	20051109	00060	GL  	2005	11	9	2005FA0001483    	1	20051005	G	5344		HINGE           			DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  					AFT CABIN DOOR	FAILED          	B			XR0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	541DS					041				UPON INSTALLATION OF A NEW AFT CABIN DOOR SUPPORT STRUT, THE DOOR WAS CLOSED, AND THE AFT CABIN DOOR HINGE FAILED.  UPON	 FURTHER INSPECTION, THE DOOR HINGE WAS FOUND TO HAVE BEEN DELAMINATED WHICH COULD NOT WITHSTAND THE PRESSURE OF THE NEW	 SUPPORT STUT.  THE DOOR HINGE IS BONDED TO THE DOOR ASSY, AND IS NOT REPLACEABLE IN THE FIELD.  (SW05200512642) (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E1CE				 
2005110900008	20051109	00008	EA  	2005	11	9	2005FA0001484    	2	20051019	G	7322		NEEDLE VALVE    			AMTR  	GLASTR	GLASTAR     	05605M8	GL  	LYC   	O320  	O320*       	41508	EA  					CARBURETOR	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	722W		44   			5207	L466827A			DURING CRUISE FLIGHT ENGINE QUIT SUDDENLY.  PILOT APPLIED CARBURETOR HEAT,  CHECKED HIS FUEL GAUGE, WHICH SHOWED 5 PSI A	ND TURNED ON THE ELECTRIC FUEL PUMP AND SWITCHED TO ANOTHER FUEL TANK.  ALL HAD NO EFFECT.  PILOT WAS ABLE TO MAINTAIN 2	000 RPM ON ENGINE BY PUMPING THE PRIMER HANDLE IN AND OUT.  PILOT LANDED THE AIRCRAFT AND WAS UNABLE TO STOP THE AIRCRAF	T, IT FLIPPED OVER.  CARBURETOR WAS DISASSEMBLED AND THE FLOAT ACTUATED AND RELEASED, NEEDLE VALVE STUCK IN THE CLOSED P	OSITION.  BLACK PARTICLES WERE FOUND IN THE FLOAT BOWL.  ACTUATION OF THE NEEDLE SEVERAL TIMES APPEARED TO CORRECT THE P	ROBLEM.  IT IS STILL A LITTLE STICKY BUT DOES NOT REMAIN CLOSED WHEN THE FLOAT IS RELEASED.  (K)	1	H	7	1 	3O	3	O	NC	EXPA1H71	E274				 
2005110700094	20051107	00094	EU  	2005	11	7	2005FA0001485    	1	20050923	G	2497		FEEDER CABLE    			AEROSP	ATR72 	ATR72202    	8680940	EU  										RT CABIN AREA	CHAFED          	B			G78R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	EIFXG	29863				224				DURING INDUCTION INSPECTION FOR PASSENGER TO FREIGHTER CONVERSION MODIFICATION, INSPECTION REVEALED 2 AREAS OF SEVERE CH	AFING RESULTING IN EXPOSURE OF CONDUCTOR WIRES FOR AC WILD FEEDERS AT RT SIDE CABIN AREA BETWEEN FRAMES 15-17 APPROXIMAT	ELY STRINGER 5R.  (K)				2	H	7	2 	4T			RT	A53EU   					 
2005110700095	20051107	00095	EU  	2005	11	7	2005FA0001486    	1	20050923	G	2497		FEEDER CABLE    			AEROSP	ATR72 	ATR72212    	8680945	EU  										RT CABIN AREA	CHAFED          	B			G78R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	812FX	23020				404				DURING INDUCTION INSPECTION FOR PASSENGER TO FREIGHTER CONVERSION MODIFICATION, INSPECTION REVEALED 2 AREAS OF SEVERE CH	AFING RESULTING IN EXPOSURE OF CONDUCTOR WIRES FOR AC WILD FEEDERS AT RT SIDE CABIN AREA BETWEEN FRAMES 15-17 APPROXIMAT	ELY STINGER 5R.  (SW17200603842) (K)				2	H	7	2 	4T			RT	A53EU   					 
2005110900039	20051109	00039	CE  	2005	11	9	2005FA0001487    	1	20051025	G	2752	3903814020020	ACTUATOR        			RAYTHN	390   	390         	7150030	CE  										TE FLAPS	FAILED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	322BJ	336  				RB93				INSTALLED .0 TIME SINCE FACTORY MODIFIED NR 2R FLAP ACTUATOR AS PART OF COMPLIANCE WITH MFG MSB.  (FLAP FAIL) ANNUNCIATO	R ILLUMINATED AFTER INSTALLATION.  FLAP SYSTEM TROUBLESHOOTING SHOWED FAULT CODES 3, 8 AND THEN 1,3, 8.  ANNUNCIATOR NOT	 ILLUMINATED AFTER REINSTALLING ORIGINAL ACTUATOR.  REPLACED ACTUATOR WITH MODIFIED ACTUATOR, NO ADDITIONAL (FLAP FAIL) 	ANNUNCIATOR INDICATIONS NOTED.  (K)			1	7		2 	3F			RT	A00010WI					 
2005110900063	20051109	00063	CE  	2005	11	9	2005FA0001488    	1	20051025	G	2752	3903814020018	ACTUATOR        			RAYTHN	390   	390         	7150030	CE  										TE FLAP	FAILED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	322BJ					RB93				INSTALLED .0 TIME SINCE FACTORY, MODIFIED NR 1L FLAP ACTUATOR AS PART OF COMPLIANCE WITH MFG MSB.  (FLAP FAIL) ANNUNCIAT	OR ILLUMINATED AFTER INSTALLATION.  FLAP SYSTEM TROUBLESHOOTING SHOWED FAULT CODES 2,8 AND THEN 1,2, 8.  ANNUNCIATOR NOT	 ILLUMINATED AFTER REINSTALLING ORIGINAL ACTUATOR.  REPLACED ACTUATOR WITH MODIFIED ACTUATOR, NO ADDITIONAL (FLAP FAIL) 	ANNUNCIATOR INDICATIONS NOTED.  (K)			1	7		2 	3F			RT	A00010WI					 
2005110800304	20051108	00304	SO  	2005	11	8	2005FA0001489    	1	20051006	G	7603	455350	THROTTLE CABLE  			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	8285B	9670 				288116066	L1191039A			THE THROTTLE CABLE BROKE IN HALF, INSIDE THE THROTTLE CABLE HOUSING.  WHEN THE THROTTLE CABLE BROKE, IT CREATED FREYED E	NDS THAT CAUGHT IN THE CABLE HOUSING WHICH RESULTED IN THE THROTTLE BECOMING (STUCK) IN THE FULL POSITION WHICH ENDED IN	 THE PILOT PULLING THE MIXTURE TO FULL LEAN POSITION AND LANDING (DEAD STICK) AT OTIS ANG BASE.  (NE01200505868) (K)				1	L	7	1 	3O	3	O		2A13    	E274				 
2005110900075	20051109	00075		2005	11	9	2005FA0001490    	4	20050929	G	3497		CONNECTOR       			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ADC	LOOSE           	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	130F					044				THE PILOTS ALTIMETER FLAGGED WHILE ENROUTE.  THE FLIGHT CREW NOTIFIED ATC.  SEVERAL MINUTES LATER THE ALTIMETER BEGAN WO	RKING NORMALLY.  THE CONNECTIONS WERE CHECKED AND A BITE TEST WAS PERFORMED ON THE ADC WITH NO DEFECTS NOTED.  AC WAS RE	TURNED TO SERVICE AND CONTINUED FLIGHT.  WHILE ON THE GROUND, THE ALTIMETER AND ADC CONNECTIONS WERE RECHECKED.  BOTH PR	IMARY ALTIMETERY SYSTEMS WERE RUN TO ALTITUDE USING A DPS 500 AND NO DEFECTS WERE NOTED.  THERE HAVE BEEN NO PRIOR REPOR	TS OF ALTIMETERY ERRORS ON THE AIRCRAFT.  (K)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005110900074	20051109	00074		2005	11	9	2005FA0001491    	1	20050901	G	5514	EX405RC	BEARING         	AMD         																HORIZONTAL STAB	CORRODED        	B			SE2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03										TAILPLANE ACTUATOR EXCEEDED SCREW CASING END PLAY LIMIT OF 0.25 MM AS LISTED IN MM.  DISASSEMBLED UNIT AND FOUND PRESENC	E OF WATER CONTAMINATION AND INTERNAL BALL BEARINGS RUSTED.  DATE DISCOVERED 17 AUG 2005.  UNIT SHOULD BE CHECKED INTERN	ALLY FOR CONDITION OF BALL BEARINGS AND PROPER LUBRICATION.  AT PRESENT, MFG MM PROVIDE NO SCHECULED INTERVALS TO MONITO	R BEARING CONDITIONS.  (K)																 
2005110900077	20051109	00077		2005	11	9	2005FA0001492    	1	20051101	G	2742	3661RSP5	BEARING         																	HORIZ STAB ACT	CORRODED        	B			SE2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03										TAILPLANE ACTUATOR EXCEEDED SCREW/CASING END PLAY LIMIT OF 0.25 MM AS LISTED IN MM.  DISASSEMBLED UNIT AND FOUND PRESENC	E OF WATER CONTAMINATION AND INTERNAL BALL BEARINGS RUSTED.  DATE DISCOVERED 17 AUG 2005.  UNIT SHOULD BE CHECKED INTERN	ALLY FOR CONDITION OF BALL BEARINGS AND PROPER LUBRICATION.  AT PRESENT MM PROVIDES NO SCHEDULED INTERVALS TO MONITOR BE	ARING CONDITIONS.  (K)																 
2005110900073	20051109	00073	SW  	2005	11	9	2005FA0001493    	1	20051020	G	5711	450001	SPAR            			AIRTRC	AT400 	AT402       	0390205	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  					WING	SEPARATED       	B			AXTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19		2116 								THE MAIN SPARS (PN 4500-01 AND 4500-02, RT AND LT) WERE BROKEN AWAY FROM THE WINGLET.  WINGLETS AND SPAR ARE PART OF STC	 INSTALLATION.  SPAR IS ATTACHED TO INSIDE WINGLET WITH FIBERGLASS CLOTH.  CLOTH WAS TORN AND DELAMINATED.  SPAR WAS COM	PLETELY SEPARATED FROM WINGLET ON RT SIDE AND MOSTLY SEPARATED ON THE LT SIDE. DISCOVERED DURING INSPECTION.				1	L	7	1 	3T	4	T	NC	A17SW   	E4EA				 
2005110900080	20051109	00080		2005	11	9	2005FA0001494    	1	20051021	G	5520	AN5158R26	SCREW           	CESSNA      		CESSNA														TRIM TAB	CORRODED        	B			AK6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										THERE ARE 4 SCREWS WHICH HOLD THE ELEVATOR TRIM TAB HORN TO THE TRIM TAB.  HAVE STARTED TO REMOVE THESE SCREWS ON EVERY 	ANNUAL WE DO ON 300/400 SERIES. HAVE FOUND NUMEROUS SCREWS CORRODED ALMOST IN HALF.  THERE IS NOT A WAY TO INSPECT THESE	 SCREWS WITHOUT REMOVAL.  DUE TO THE CRITICAL NATURE OF THESE SCREWS AND THE AGEING FLEET.  RECOMMEND MANDITORY REMOVAL 	AND INSPECTION AT EACH ANNUAL INSPECTION.  (K)																 
2005110900092	20051109	00092	SO  	2005	11	9	2005FA0001495    	1	20051018	G	7120	6711957	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	ENGINE	BROKEN          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	283ND	4437 				2844025	L2713851A	00906		DURING ROUTING SCHEDULED MAINTENANCE INSPECTION NOTED ENG MOUNT WAS CRACKED JUST ABOVE WELD ON RT LOWER SIDE OF ENGINE M	OUNT.  JUST ABOVE AFT DRAGLINK MOUNT POINT.  ALSO, UPON FURTHER INSPECTION THE LOWER HORIZONTAL TUBE MOST OB WAS ALSO BE	NT.  MOS NOTED TOWARD THE FRONT PART OF THE MOUNT BY THE LANDING GEAR ATTACH POINT.  NO HARD LANDING HAD BEEN REPORTED. 	 (K)			1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA	 
2005110900109	20051109	00109	CE  	2005	11	9	2005FA0001496    	1	20051020	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					MLG DOOR	CRACKED         	B			BX4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	5136R					172RG0040				COMPLYING WITH SB, FOUND BFE BORE CRACKED IAW ILLUSTRATION OF ACCOMPLISHEMENT OF INSTRUCTION OF SEB.  (K)						1	H	7	1 	3O	3	O		3A17    	E286				 
2005110900113	20051109	00113	SW  	2005	11	9	2005FA0001497    	1	20050915	G	5311		SPAR            			GULSTM	112   	112A        	7630302	SW  	LYC   	O360  	TO360A1A6   	41514	EA  					FUSELAGE	DAMAGED         	B			BX4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	100PP					412				FOUND LT AND RT MAIN SPAR WEBS DAMAGED FROM STATION 50 TO 63.  EACH WEB HAD DIAGONAL WRINKLES FROM TOP OF SPAR, JUST IB 	OF LANDING GEAR ATTACH AREA, DOWN AND IB TO JUST OB OF DRAG BRACE BRACKET AND REINFORCEMENTS.  AIRCRAFT HAS BEEN FOUND T	O BE IN COMPLIANCE WITH AD.  BY REINFORCEMENT KIT INSTALLED IAW SB.  NO CRACKS DETECTED ATH THIS DATE.  (K)				1	L	7	1 	3O	3	O		A12SO   	E26EA				 
2005110900006	20051109	00006		2005	11	9	2005FA0001498    	4	20051020	G	3416		ENCODER         			CESSNA	185   	A185F       	2072821	CE  										ALTITUDE	FAILED          	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	6590E					18504058				FOLLOWING INSTALLATION OF A NEW GNS480, DURING INITIAL POWER CHECKS, FOUND THE FOLLOWING FAILURE FLAGS DISPLAYED: COM CO	MUNICATION FAILURE, NAV COMMUNICATION FAILURE, ALTITUDE ENCODER COMMUNICATION FAILURE.  INSTALLATION OF ANOTHER UNIT RES	OLVED THE PROBLEMS.  (K)				1	H	7	1 	3O				3A24    					 
2005110900005	20051109	00005	CE  	2005	11	9	2005FA0001499    	1	20051005	G	2840		MOUNT           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  					FUEL TRANSDUCER	CRACKED         	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	206Q	377  				U20603259				DURING A ROUTINE INSPECTION FOUND THE FUEL FLOW TRANSDUCER MOUNT BRACKET CRACKED.  (K)						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005110900001	20051109	00001		2005	11	9	2005FA0001500    	4	20051001	G	3417	612826	MOUNT           			DHAV  	DHC2  	DHC2*       	2800108	EA  										ADC	CRACKED         	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	37756	906  				1456				DURING ANNUAL INSPECTION FOUND THE ADC TRAY CRACKED COMPLETELY ACROSS ONE END.  (K)						1	H	7	1 	3R				A806    					 
2005110900305	20051109	00305	SO  	2005	11	9	2005FA0001501    	1	20051026	G	3397	394A1J1	CONNECTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					CABIN LIGHTS	DISCONNECTED    	B			GR4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	508QS	4733 				631				DURING SCHEDULED MAINTENANCE, CREW NOTED SEVERAL CABIN LIGHTS WENT INOPERATIVE.  WIRE PX601A8 AT CONNECTOR 394A1J1/369A1	P1 BEHIND AUX CB PANEL AT RT RADIO RACK WAS FOUND WITH EVIDENCE OF OVERHEATING AND ARCING.  SOLDERED CONNECTION TO CORRE	SPONDING PIN HAD FAILED.  CB DID NOT TRIP.  REPLACED CONNECTOR, TRIMMED DAMAGED WIRE, INSTALLED NEW PIN.  REPLACED 50 AM	P CB.  INTERNALLY INSPECTED POWER DISTRIBUTION BOX FOR EVIDENCE OF OVERHEATING.  TESTED REPAIRED CIRCUIT.  (K)			2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2005110900302	20051109	00302	SO  	2005	11	9	2005FA0001502    	1	20051026	G	3397	394A1P1	CONNECTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					CABIN LIGHTS	DISCONNECTED    	B			GR4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	508QS	4733 				631				DURING SCHEDULED MAINTENANCE, CREW NOTED SEVERAL CABIN LIGHTS WENT INOPERATIVE.  WIRE PX601A8 AT CONNECTORS 394A1J1/394A	1P1 BEHIND AUX CB PANEL AT RT RADIO RACK WAS FOUND WITH EVIDENCE OF OVERHEATING AND ARCING.  SOLDERED CONNECTION TO CORR	ESPONDING PIN HAD FAILED.  CB DID NOT TRIP.  REPLACED CONNECTOR 394A1J1/394A1P1, TRIMMED DAMAGED WIRE, INSTALLED NEW PIN	. REPLACED 50 AMP CB. INTERNALLY INSPECTED POWER DISTRIBUTION BOX FOR EVIDENCE OF OVERHEATING.  TESTED REPAIRED CIRCUIT.	  (K)		2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2005110900304	20051109	00304	SO  	2005	11	9	2005FA0001503    	1	20051019	G	5610	6971203	WINDOW          			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540*      	41532	EA  					COCKPIT	CRACKED         	B			EL6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	39503	3760 				32R7885224				LT FORWARD SIDE WINDOW.   CRACKED AND BROKEN 2 PLACES AROUND SIDE VENT WINDOW CAUSING LARGE SECTION TO BECOME LOOSE.  (K	)					1	L	7	1 	3O	3	O		A3SO    	1E4				 
2005110900303	20051109	00303	SW  	2005	11	9	2005FA0001504    	1	20051102	G	5302	206020113223	SKIN            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					VERTICIAL FIN	DEBONDED        	B			KKQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	113TV					53242				LESS THAN 10 HOURS FLIGHT TIME AFTER REPAIR FOR LEADING EEDGE DISBONDING THE BONDING FAILED AND TAIL ROTOR WASH DISPLACE	D THE LEADING EDGE.  (K)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005111000107	20051110	00107	GL  	2005	11	10	2005FA0001505    	1	20051019	G	7810	15074001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	CRACKED         	B			QRQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	495CD					1605	917847			NR 5 EXHAUST HEADER CRACKED AT CYLINDER JUST BELOW FLANGE ONE HALF THE WAY AROUND HEADER UNDER NORMAL USE.  HEADER NEEDS	 REDESIGN OR SOME SORT OF SUPPORT.  IT IS OVER CANTILEVERED FOR STRESSES IMPOSED ON IT.  NR 6 HEADER CRACKED THRU THE FL	ANGE FOR A DISTANCE OF ABOUT 1.5 INCHES RADIUSING OUT ALONG THE FLANGE WELD. AIRFRAME AND EXHAUST HOURS: 25.6 (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005111000109	20051110	00109	GL  	2005	11	10	2005FA0001506    	1	20051019	G	7810	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					NR 5	CRACKED         	B			QRQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	495CD	25   				1605	917847			NR 5 EXHAUST HEADER CRACKED AT CYLINDER JUST BELOW FLANGE HALF THE WAY AROUND HEADER UNDER NORMAL USE.  HEADER NEEDS RED	ESIGN OR SOME SORT OF SUPPORT.  IT IS OVER CANTILEVERED FOR STRESSES IMPOSED ON IT.  NR 6 EXHAUST HEADER CRACKED THRU TH	E FLANGE FOR A DISTANCE OF ABOUT 1.5 INCHES RADIUSING OUT ALONG THE FLANGE WELD.  (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005111000105	20051110	00105	GL  	2005	11	10	2005FA0001507    	1	20051019	G	7810	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					NR 5	CRACKED         	B			QRQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	99OP					0945	917219			NR 5 EXHAUST HEADER CRACKED AT CYLINDER FLANGE JUST BELOW WELD UNDER NORMAL USE.  HEADER NEEDS REDESIGN OR SOME SORT OF 	SUPPORT.  IT IS OVER CANTILEVERED FOR STRESSES IMPOSED ON IT.  AIRFRAME AND EXHAUST HOURS.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005111000106	20051110	00106	GL  	2005	11	10	2005FA0001508    	1	20051019	G	7810	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	CRACKED         	B			QRQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	613MM	33   				1497				NR 5 EXHAUST HEADER CRACKED AT CYLINDER FLANGE JUST BELOW WELD UNDER NORMAL USE.  HEADER NEEDS REDESIGN OR SOME SORT OF 	SUPPORT.  IT IS OVER CANTILEVERED FOR STRESSES IMPOSED ON IT.  AIRFRAME ADN EXHAUST HOURS: 33.7					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005111000111	20051110	00111	SO  	2005	11	10	2005FA0001509    	1	20051025	G	5730	62061002	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					WING	CRACKED         	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	35705	2557 				288016207				FORWARD WING WALK DOUBLER CRACKED.  DOUBLER SHOULD BE HEAVIER GAUGE METAL.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2005111000113	20051110	00113	NE  	2005	11	10	2005FA0001510    	1	20050810	G	2497		WIRE            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					STARTER GEN	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	88CP					760500				THE TERMINALS ON THE GENERATOR ARE DESIGNATED A8 TERMINAL D WHICH HAS 2 WIRES.  WIRE NR P257A16 GOES TO P708 PIN -3 AND 	THIS WIRE WAS FOUND TO HAVE BUBBLED UP INSULATION CAUSED BY WIRE CORROSION AND HEAT.  THE OTHER WIRE ON TERMINAL D IS P2	56A16 WHICH GOES TO P708 PIN 4 WHICH THAT WAS PULLED AND IT ALSO WAS FOUND TO HAVE RED CORROSION STARTING ON WIRE SURFAC	E.  THIS WIRE AS WELL AS THE OTHERS SHOWED STARTING SIGNS OF CORROSION.  MAINTENANCE HAS REPLACED ALL THE ABOVE CORRODED	 WIRES.  (EA17200603551) (K)		1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2005111000112	20051110	00112	CE  	2005	11	10	2005FA0001511    	1	20050818	G	5280	A103TGS	NUT             			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG DOOR	BACKED OUT      	B			AK6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	804BH	594  				258596				RT OB GEAR DOOR.  FOUND THE DOOR TO GEAR STRUT ATTACHMENT BOLT BACKING OUT AND LOOSE.  AFTER REMOVING COVER WAS FOUND TH	AT NUT WAS TO SECURE THE BOLT WAS NOT SAFETIED AND HAD BACKED OFF ABOUT 3 TURNS.  THIS HAD COM OFF THE DOOR AND WOULD HA	VE DROPPED INTO THE SLIP STREAM.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005111000069	20051110	00069	SO  	2005	11	10	2005FA0001512    	1	20051104	G	3260		LIGHT           			PIPER 	PA28  	PA28R201    	7102816	SO  										MLG INDCATOR	MISINSTALLED    	D				O				OTHER                   				W	N		INADEQUATE Q C            	FALSE WARNING             		LD	LANDING        	1			SW	99	D-EPV					2844117				DURING TRAINING FLIGHT IN APPROACH, PILOT NOTICED, THAT LT LANDING GEAR GREEN LIGHT WAS NOT ON, RED LANDING GEAR UNSAFE 	LIGHT WAS ON HYD PUMP WAS RUNNING CONSTANTLY. PROBLEM CONTINUED EVEN AFTER EMERGENCY EXTENSION. AFTER FLYBY, ABOVE CONTR	OL TOWER, GROUND CONTROL SAW LANDING GEAR WAS DOWN, PILOT PROCEEDED WITH SAFE LANDING.  TROUBLESHOOTING WAS PERFORMED WI	TH FOLLOWING RESULTS: THE MLG WARNING LIGHTS WHERE INVERTED. LT MAIN GEAR MICROSWITCH OPERATED RT MAIN GEAR GREEN LIGHT,	 RT MAIN GEAR MICROSWITCH OPERATED LT MAIN GEAR GREEN LIGHT.  RT MAIN GEAR MICROSWITCH POSITION WAS ADJUSTED IAW MM, WIR	ES WERE INSTALLED CORRECT WAY.  GEAR SWING WAS PERFORMED WITH SATISFACTORY RESULT.	1	L	7	1 	3O				2A13    					 
2005111000055	20051110	00055	CE  	2005	11	10	2005FA0001513    	1	20051108	G	5312	17121042	BULKHEAD        			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					BS 263	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	8050G	2000 				177RG0050				BULKHEAD CRACKED AROUND BOTH VERTICAL FIN FORWARD ATTACH BOLTS.						1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005111000070	20051110	00070	CE  	2005	11	10	2005FA0001514    	1	20051108	G	5312	17121042	BULKHEAD        			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B    	41514	EA  					ZONE 200	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	8050G	2000 				177RG0050				BULKHEAD CRACKED AROUND BOTH VERTICAL FIN FORWARD ATTACH BOLTS.						1	H	7	1 	3O	3	O		A20CE   	1E10				 
2005111000110	20051110	00110	EU  	2005	11	10	2005FA0001515    	1	20051018	G	5321	3652100590501	FLOOR PANEL     			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	CORRODED        	B			UOHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	97SV					6298				DURING A PRE-BUY INSPECTION, THE LONCOIN RUBBER MATS WERE PULLED UP FROM THE COCKPIT FLOORS.  UNDER THE PILOTS SIDE OF T	HE MATS, MAJOR CORROSION ACCUMULATION WAS DISCOVERED.  THESE MATS WERE STILL DAMP UNDERNEATH WHICH SHOWED WHY THIS CORRO	SION EXISTED.  SUSPECT THAT SALT LADEN WATER FROM THE PILOTS FEET DURING WINTER OPERATIONAS CONTRIBUTED TO THIS CORROSIO	N.  THE RUBBER MATS ALLOWED THE MOISTURE TO PENETRATE BUT WOULD NOT LET IT DRY.  THIS FLOOR PANEL IS COMPLETELY DESTROYE	D AND MUST BE REPLACED.  MORE STRIGENT CLEANING AND INSPECTION PRACTICES MUST BE PRACTICED IN ENVIROMENTS SUCH AS THIS. 	 (K)	1	G	7	2 	3U	3	U		H10EU   	E19EU				 
2005122000161	20051220	00161	EA  	2005	12	20	2005FA0001516    	2	20050920	G	8520	LW16711	BEARING         								LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DEFECTIVE       	B			NX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		2102 					L2779051A			DURING ENGINE DISASSEMBLY FOR ROUTINE OVERHAUL, IT WAS NOTED THAT SOME NR 3 MAIN BEARING SURFACE MATERIAL HAD RELEASED F	ROM THE BEARING SHELL.  NO OTHER DEFECTS WERE NOTED RELATIVE TO THIS OCCURRENCE.  (K)										3	O			1E10				 
2006011700329	20060117	00329	SO  	2006	1	17	2005FA0001517    	1	20051107	G	7120	LW38275	BOLT            	LYC         	O360E1A6D   	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					RT ENGINE	BROKEN          	D				K				NONE                    				G			MULTIPLE FAILURE          			IN	INSP/MAINT     	1			SO	05	120RH		1650 							FOUR BOLTS FOUND BROKEN ON LT SIDE OF RT ENGINE MOUNT DURING INSPECTION. LT SIDE OF MOUNT HAD 2 LOOSE BOLTS.						1	L	7	2 	3O	3	O		A19S0   	E286				 
2005120200143	20051202	00143		2005	12	2	2005FA0001518    	4	20051031	G	2562	MN1300	BATTERY         		E01         	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					ELT	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	8806J				015652	282756				ELT BATTERIES FOUND LEAKING AT ANNUAL INSPECTION.  ELT IS MODEL E-01 WHICH USES 8 EA.  MN1300 (D) CELL BATTERIES. THE BA	TTERIES WERE DATED MAR 2010 (DATE OF INSTALLATION UNKNOWN), AND THE ELT WAS LABELED AND MAINTENANCE ENTRIES NOTED FOR (E	LT BATTERY DUE JUNE 2005).  BATTERY LEAKAGE HAD CONTAMINATED THE ELT CASE AND CAUSED CORROSION OF THE MOUNTING TRAY.  TH	IS WAS THIRD INSTANCE OF DISCOVERING LEAKING BATTERIES IN AN ELT WHERE THE SHELF LIFE DATE PRINTED ON THE BATTERY WAS ST	ILL MANY YEARS INTO THE FUTURE.		1	L	7	1 	3O	3	O		2A13    	E286				 
2005111600170	20051116	00170	CE  	2005	11	16	2005FA0001519    	1	20051101	G	8011		COMMUTATOR      	LAMAR       		CESSNA	172   	172R        	2072401	CE  	LYC   	O320  	IO320*      	41508	EA  					STARTER	DESTROYED       	B			MS2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	9918F				80116408	17280194	2723451A			A SEGMENT OF THE COMMUTATOR CAME OFF DURING STARTING, COMPLETELY DISTROYING THE BRUSES AND THE INSIDE OF THE STARTER. (K	)					1	H	7	1 	3O	3	O	NT	3A12    	1E12				 
2005111600172	20051116	00172	CE  	2005	11	16	2005FA0001520    	1	20051101	G	5321		FLOORBOARD      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					FUSELAGE	CRACKED         	B			MS2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	6394M					15284706	L1856515			FOUND FLOORBOARD SKIN ABOVE THE LT AND RT GEAR BOXES, CRACKED AT THE INSPECTION HOLES.  CRACKS RAN FROM THE EDGE OF THE 	HOLE TO THE SCREW HOLE FOR THE INSPECTION PLATE.  INSTALLED A REINFORCEMENT UNDER THE DOUBLER AND STOP DRILLED THE CRACK	S.  (K)				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005111600175	20051116	00175	GL  	2005	11	16	2005FA0001521    	1	20051104	G	2810	2228610000	FUEL TANK       			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  						CRACKED         	B			SL5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	517JT	134  				C0275				DURING OUTER MAINTENANCE FOUND FUEL TANK CRACKED IN NP SURFACE AT CENTERAL APT SPOT WELD FOR INTERNAL BAFFEL.  INSTALLED	 NEW FUEL TANK TO CORRECT PROBLEM.  (K)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2005111600174	20051116	00174	CE  	2005	11	16	2005FA0001522    	1	20051024	G	5751	67240204	HINGE BRACKET   			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					OB AILERON	CORRODED        	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	936QS					7500036				DURING RECENT INSPECTION CORRODED HARDWARE WAS FOUND ON AILERON.  AFTER AILERON WAS REMOVED HEAVY GALLING WAS FOUND ON O	UTBOARD HINGE SUPPORT AND AILERON FITTING.  SEVERAL OTHER AIRCRAFT WERE INSPECTED AND 3 OTHERS AND IDENTICAL GALLING.  M	FG WAS NOTIFIED AND REPAIRS MADE,, INCLUDING BLENDING AND NDT.  AILERON ARE NOT REMOVED DURALAY INSPECTIONS.  BUT CLOSE 	VISUAL INSPECTIONS SHOULD FIND DEFECTS.  AIRCRAFT ARE DAMAGE TOLERANT AND PART IS CONSIDERED. PSE.  (K)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005111600164	20051116	00164	GL  	2005	11	16	2005FA0001523    	2	20050926	G	7230		STUD            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	BROKEN          	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	511SB	12792				1090592D	CAE834299			FOUND THE LOWER RT COMPRESSOR STUD BROKEN OFF.  DURING INSPECTION PROCESS FOR COMPRESSOR CASE HALVES.  IT WAS NOTICED TH	AT THE RT LOWER COMPRESSOR STUD WAS MISSING (THAT IS THE NUT AND STUD WERE NOT VISABLE ON THE COMPRESSOR FLANGE).  REPLA	CED UNIT. (K)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005111600168	20051116	00168	WP  	2005	11	16	2005FA0001524    	1	20050904	G	3246	369D2921143	SKID            			HUGHES	369   	369D        	4470706	WP  										MLG	CRACKED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGPHC					1802570				UPON LANDING THE MECHANIC SAW THE FORWARD LT SKID TUBE WAS ANGLED UP SEVERAL DEGREES.  IT WAS DISCOVERED THAT THE TUBE W	AS CRACKED UNDER THE FORWARD FOOT AND SKID PLATE.  REPLACED UNIT. (K)					1	G	7	1 	3U				H3WE    					 
2005111600162	20051116	00162	WP  	2005	11	16	2005FA0001525    	1	20051002	G	5320	369D256273	BRACKET         			HUGHES	369   	369D        	4470706	WP  										FUSELAGE	MISMANUFACTURED 	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03										RECEIVED A BLOWN BRACKET FROM THE VENDOR AND FOUND IT IS NOT BUILT TO THE LATEST SPECS, IT WAS BUILT IN 2002 AND REQUIRE	S MODIFICATIONS CALLED OUT IN AN SB.  (K)					1	G	7	1 	3U				H3WE    					 
2005122000165	20051220	00165	SO  	2005	12	20	2005FA0001526    	1	20051103	G	5610	S2C503	CANOPY          			AYRES 	S2    	S2C         	0143006	SO  	LYC   	O540  	AEIO540*    		EA  					COCKPIT	DEPARTED        	B			ZL6R	O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	03	114RM	532  				6030				CANOPY ASSEMBLY PN S2C503, DEPARTED AIRCRAFT DURING NORMAL FLIGHT ATTITUDE AND CRUISE SPEED.  NO APPARENT COMPONENT FAIL	URE NOTED ON AIRCRAFT COCKPIT STRUCTURE OR CANOPY RETAINING COMPONENTS.  SINCE CANOPY ASSEMBLY WAS NOT RECOVERED.  NO PR	OBABLE CAUSE FOR SEPARATION COULD BE FOUND.  (K)				1	L	7	1 	3R	3	O		2A7     	1E4				 
2005111600163	20051116	00163	EA  	2005	11	16	2005FA0001527    	2	20051103	G	7414	M3984	CAPACITOR       	SLICK       		CESSNA	188   	A188B       	2073005	CE  	LYC   	O540  	TIO540A1A   	41532	EA  					MAGNETO	INOPERATIVE     	B			EATR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	53255	281  			01031727	18801716				OPENED PRESSURIZED MAGNETO TO INSPECT FOR CORROSION DURING ANNUAL INSPECTION.  DETECTED A LARGE AMOUNT OF OIL IN AFT CAS	E OF MAGNETO.  FURTHER INVESTIGATION REVEALED THAT IT IS DIELECTRIC FLUID FROM CAPACITOR.  TESTED CAPACITOR WITH A SIMPS	ON METER AND WAS FOUND TO HAVE FAILED.  SUBMITTER FEELS THAT MAGNETO FAILURE WAS EMINENT DUE TO OIL CONTAMINATION TO POI	NTS AND DISTRIBUTOR.  SUBMITTER SUGGESTS INSPECTION OF ALL MAGNETOS CONTAINING THS PN CONDENSOR BEFORE FURTHER FLIGHT.  	(K)		1	L	7	1 	3O	3	O		A9CE    	E14EA				 
2005111600167	20051116	00167	EU  	2005	11	16	2005FA0001528    	1	20051108	G	2622	C352TS	EXTINGUISHER    			BRAERO	1000  	HAWKER1000  	7450005	EU  	PWA   	305   	PW305       	 	NE  					COCKPIT	INCORRECT       	B			YK1R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	11	551QS	7085 				259051				REMOVING HAND HELD FIRE EXTINGUISHER FROM THE COCKPIT FOR ROUTINE INSPECTION IT WAS NOTED THAT THE HANDLE DID NOT APPEAR	 TO BE CORRECT.  FURTHER INSPECTION SHOWED THAT THERE ARE TABS ON THE LOWER HANDLE THAT WOULD HAVE PREVENTED THE EXTINGU	ISHER FROM DISCHARGING.  NUMEROUS ATTEMPTS AT DISCHARGING FAILED.  IT APPEARS THAT AN INCORRECT HEAD WAS INSTALLED.  SUB	JECT FIRE EXTINGUISHER WAS REMOVED FROM SERVICE. (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2005122000150	20051220	00150	SO  	2005	12	20	2005FA0001529    	1	20051102	G	3244	304K632	TIRE            			EMB   	135   	EMB135BJ    	3260306	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					LANDING GEAR	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	780SG					145780				THE TIRE WAS REMOVED FROM THE AIRCRAFT FOR A SLOW LEAK.  THE WEEP HOLES IN THE SIDEWALL OF THE TIRE WERE BUBBLING WHEN C	HECKED WITH LEAK DETECTOR FLUID. (K)					2	L	7	2 	4F	4	F	RT	        	TE6CH				 
2005111600173	20051116	00173	SO  	2005	11	16	2005FA0001530    	1	20051102	G	3244	304K632	TIRE            			EMB   	135   	EMB135BJ    	3260306	SO  										MLG	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25										AFTER COMPLETING THE SPECIFIED LEAK CHECK TIME, THE WEEP HOLES IN THE SIDE WALL OF THE TIRE WERE STILL BUBBLING WHEN CHE	CKED WITH LEAK DETECTOR FLUID.					2	L	7	2 	4F			RT	        					 
2005112800176	20051128	00176	SW  	2005	11	28	2005FA0001531    	1	20051012	G	2120	3136171	SOLENOID        			BELL  	430   	430         	1182150	SW  										DIVERTER VALVE	STUCK           	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	01	9SP	1166 				49086				SOLENOID FAILED IN ENERGIZED POSITION. THIS UNIT IS IN THE DUCTING DIVERTER VALVE MAKING IT SUBJECT TO MOISTURE. THIS CO	RRODES THE UNIT OVER TIME. IT FAILED ON, THUS DIVERTING AIR IN THE WRONG DIRECTION. HEAT WILL COME OUT OF OVERHEAD CABIN	 DUCTS.				1	G	7	2 	3U			RT	H9SW    					 
2005120200031	20051202	00031	GL  	2005	12	2	2005FA0001532    	1	20051110	G	3220		LANDING GEAR    			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					NOSE	UNLOCKED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	932AF					C0198				ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-0	1) HAD WORKED OUT UNLOCKING THE ASSY.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2005120200032	20051202	00032	CE  	2005	12	2	2005FA0001533    	1	20051111	G	5210	S31948	SPRING          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					PAX DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	102FS	1147 				560XL5318				THE AIRCRAFT RETURNED FROM A FLIGHT WITH NO DEFECTS NOTED. AIRCRAFT WAS MOVED INTO THE HANGAR AND APPROXIMATELY 20 MINUT	ES LATER A LOUD BANG WAS HERD. THE AIRCRAFT WAS STATIC WITH THE DOOR CLOSED. THE LOUD BANG WAS THE CABIN ENTRY DOOR FORW	ARD COUNTERBALANCE SPRING BREAKING IN THE SECOND COIL.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005122800092	20051228	00092	SW  	2005	12	28	2005FA0001534    	1	20050926	G	5320	1159BM502161	BRACKET         			GULSTM	111   	111RKWELL   	0144601	SW  	CONT  	O520  	TSIO520*    	17040	SO  					BS 169	CRACKED         	B			VZGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	444GA					301				MED ACTUATING CYLINDER UPPER BRACKET FAILED ALONG A ROW OF LOCK FASTENERS HOLES CAUSING MAJOR DAMAGE TO SKIN AND STRINGE	RS.  ACTUATING CYLINDER REPLACED AS PRECAUTIONARY MEASURE.  NEW BRACKET, SKINS, STRINGERS AND DOUBLERS.  (K)					1	L	7	1 	3O	3	O		A11SO   	E8CE				 
2005120200037	20051202	00037	EA  	2005	12	2	2005FA0001535    	2	20051017	G	8500	LW18837	CAMSHAFT        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	MAKING METAL    	B			EASR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5563U	928  				2826882	L1738227A			DURING ANNUAL INSPECTION, FERROUS FLAKES OF METAL WERE FOUND IN OIL FILTER, ALSO, SEVERAL PIECES FOR FERROUS METAL WERE 	FOUND IN THE FINGER STRAINER.  THE OIL FILTER AND THE PIECES FOUND IN THE FINGER STRAINER WERE SENT TO MFG FOR ANALYSIS.	  IT WAS REPORTED THAT THE FERROUS METAL CAME FROM THE CAMSHAFT AND TAPPET BODIES.  THE ENGINE IS BEING REMOVED FOR OVER	HAUL, TIME SINCE OVERHAUL IS 2092.9.  CAMSHAFT WAS REPLACED AT 1164.4 HRS SINCE OVERHAUL. THE AVERAGE OIL CHANGE INTERVA	L SINCE OVERHAUL IS 91 HOURS.  RECOMMEND THAT THE 50 HOUR OIL CHANGE INTERVAL RECOMMENDED BY MFG BE STRICTLY ADHERED TO.		1	L	7	1 	3O	3	O		2A13    	E274				 
2005122100174	20051221	00174	CE  	2005	12	21	2005FA0001536    	1	20051103	G	3244	184F135	TIRE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG	DEBONDED        	B			E81R	O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	03	400MV					RK286				OPERATOR STATED, RT FROM INSTALL AT ANOTHER FACILITY, THE AIRCRAFT EXPERIENCED NOSE VIBRATION ON TAKE OFF.  DISASSEMBLED	 WHEEL ASSY AND FOUND INNER CASING OF TIRE DEBONDING.  (K)					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2005122100176	20051221	00176	SO  	2005	12	21	2005FA0001537    	1	20051107	G	8011	MHB2399S	ARMATURE        	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4A     	41514	EA  					STARTER	BROKEN          	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	4147K	40   			8021149	2843169				PILOT REPORTED GRINDING NOISE FROM ENGINE COMPARTMENT WHEN STARTER WAS ENGAGED.  STARTER WAS REMOVED ARMATURE WAS FOUND 	WITH 2 SPLINES SHEARED OFF.  INTERMEDIATE GEAR WAS MISSING 2 TEETH.  CAUSE UNKNOWN.  THIS IS THE THIRD ARMATURE IN THE P	AST 6 MONTHS WITH THE SAME DEFECT.  (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
2005122000151	20051220	00151	CE  	2005	12	20	2005FA0001538    	1	20051116	G	7931	83278	PRESSURE SENSOR 			CESSNA	172   	172S        	2072439	CE  	LYC   	O540  	IO540*      	41532	EA  					OIL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	24ME	1581 				172S8463				DURING A 100 HR INSPECTION AN OIL LEAK WAS DETERMINED TO BE ORIGNATING FROM THE HOBBS METER SENSOR AT THE SWEDGED FLANGE	.  AD CALLS FOR THE REPLACMENT OF SENSOR.  JUST THOUGHT IT IRONIC AN AD CALLS FOR HE REPLACEMENT OF ONE LEAKING SENSOR F	OR ANOTHER LEAKING SENSOR.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E4				 
2005122000152	20051220	00152	CE  	2005	12	20	2005FA0001539    	1	20051027	G	3230	50410016	BELLCRANK       			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT MLG	FRACTURED       	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	13	402CA	10938				402B0842				RT LANDING GEAR COLLAPSED DURING A NORMAL LANDING.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005120100183	20051201	00183	SO  	2005	12	1	2005FA0001540    	1	20051121	G	3230		GEARBOX         			PIPER 	PA30  	PA30        	7103002	SO  										MLG	FRACTURED       	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	23	23RD					30469				THE GEARBOX CASTING WHICH SUPPORTS THE MOTOR AND GEARBOX FRACTURED.  VISUAL EXAMINATION INDICATES FATIGUE.  DUE TO THIS 	FAILURE, THE LANDING GEAR WOULD NOT EXTEND DURING LANDING.					1	L	7	2 	3O				A1EA    					 
2005120200033	20051202	00033	SO  	2005	12	2	2005FA0001541    	1	20051117	G	3230	89291004	SWITCH          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	BROKEN          	B				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			WP	07	572ER	2237 	46   			4496148				DURING TRAINING TOUCH AND GO THE GEAR FAILED TO RETRACT AFTER TAKEOFF.  AIRCRAFT RETURNED TO AIRPORT AND MADE UNEVENTFUL	 LANDING.  MAINTENANCE FOUND THE LT GEAR SWITCH ASSEMBLY HAD 3 BROKEN WIRES AT THE SWITCH.  SWITCH WAS REPLACED AND GEAR	 SWING PERFORMED.				1	L	7	2 	3O	3	O		A19S0   	E286				 
2005120200050	20051202	00050	GL  	2005	12	2	2005FA0001542    	1	20051116	G	3220		ROLL PIN        			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	NLG	BACKED OUT      	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03						N924AF				ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-0	1) HAD WORKED OUT UNLOCKING THE ASSY.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2005120200065	20051202	00065	SO  	2005	12	2	2005FA0001543    	2	20051116	G	7414	6320	MAGNETO         								CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE	CORRODED        	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	05	311K	400  	400  							PILOT REPORTED NO MAG DROP ON LT ENGINE. UPON INSPECTION OF MAGNETOS FOUND POINTS BROKEN.  INSPECTED OTHER MAGNETOS AND 	FOUND ONE OTHER MAGNETO EXCESSIVELY BURNED AND DAMAGED INTERNALLY.  PICTURES WERE TAKEN OF MAGNETOS IF ANY ADDITIONAL IN	FORMATION IS NEEDED.  MAGNETOS WERE REPLACED AND AC WAS RETURNED TO SERVICE.									3	O			E8CE				 
2005120200066	20051202	00066	SO  	2005	12	2	2005FA0001544    	2	20051116	G	7414	6320	MAGNETO         								CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE	CORRODED        	B				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	05	311K	400  	400  							PILOT REPORTED NO MAG DROP ON LT ENGINE. UPON INSPECTION OF MAGNETOS FOUND POINTS BROKEN. INSPECTED OTHER MAGNETOS AND F	OUND ONE OTHER MAGNETO EXCESSIVELY BURNED AND DAMAGED INTERNALLY.  PICTURES WERE TAKEN OF MAGNETOS IF ANY ADDITIONAL INF	ORMATION IS NEEDED. MAGNETOS WERE REPLACED AND AC WAS RETURNED TO SERVICE.									3	O			E8CE				 
2005120200072	20051202	00072		2005	12	2	2005FA0001545    	1	20051116	G	7810	86202004R	RISER           																	EXHAUST	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										WHILE INSTALLING REPAIRED EXHAUST ON ENGINE NOTICED A 1.5 INCH CRACK IN THE WELD AT THE EXHAUST RISER FLANGE.  THIS UNIT	 WAS RECENTLY REPAIRED AND RECERTIFIED.  RISER TO BE RETURNED TO REPAIR FACILITY.																		 
2005120200104	20051202	00104	CE  	2005	12	2	2005FA0001546    	1	20051114	G	5753	052323124	SUPPORT BRACKET 			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360B1E    	41514	EA  					TE FLAPS	BROKEN          	G				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			LD	LANDING        	1			WP	23	967SP	3015 				172S8169				DURING APPROACH TO LANDING LT FLAP RETRACTED WHILE RT FLAP REMAINED EXTENDED.  AN ASYMMETRICAL FLAP LANDING WAS MADE WIT	H MUCH DIFFICULTY BUT WITHOUT INCIDENT.  INVESTIGATION REVEALED THAT A FLAP SUPPORT BRACKET PN 0523231-24 LOCATED WITHIN	 THE WING HAD FAILED ALLOWING THE FLAP CABLE TO LOOSE TENSION.  IT APPEARS THAT PRELOAD ROM T/E SKIN POSSIBLE CAUSED THE	 FAILURE OF THE BRACKET.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005120200105	20051202	00105	CE  	2005	12	2	2005FA0001547    	1	20051111	G	5210	S31948	SPRING          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					PAX DOOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	102FS	1147 				560XL5318				THE AIRCRAFT RETURNED FROM A FLIGHT WITH NO DEFECTS NOTED. AIRCRAFT WAS MOVED INTO THE HANGAR AND APPROXIMATELY 20 MINUT	ES LATER A LOUD BANG WAS HEARD. THE AIRCRAFT WAS STATIC WITH THE DOOR CLOSED. THE LOUD BANG WAS THE CABIN ENTRY DOOR FOR	WARD COUNTER BALANCE SPRING BREAKING IN THE SECOND COIL.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005120200106	20051202	00106	CE  	2005	12	2	2005FA0001548    	1	20051109	G	2560	1013030	HARNESS         			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					LATCH	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	912MA	359  	28   			9482004				JUST PRIOR TO INITIATING AEROBATICS THE PILOT ATTEMPTED TO RATCHET DOWN HIS AEROBATIC HARNESS.  THE HANDLE FOR THE RATCH	ET BROKE ALLOWING THE RATCHET LOCK TO FALL OUT OF THE ASSEMBLY.  FLIGHT WAS TERMINATED.  HARNESS REPLACED WITH NEW ASSEM	BLY.				1	H	7	1 	3O	3	O		A21CE   	1E10				 
2005120200144	20051202	00144		2005	12	2	2005FA0001549    	4	20051031	G	2562	MN1300	BATTERY         	ACK         	E01         	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					ELT	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	8806J				015652	282756				ELT BATTERIES FOUND LEAKING AT ANNUAL INSPECTION.  ELT IS  MODEL E-01 WHICH USES 8 EA.  MN1300 (D) CELL BATTERIES. THE B	ATTERIES WERE DATED MAR 2010 (DATE OF INSTALLATION UNKNOWN), AND THE ELT WAS LABELED AND MAINTENANCE ENTRIES NOTED FOR (	ELT BATTERY DUE JUNE 2005).  BATTERY LEAKAGE HAD CONTAMINATED THE ELT CASE AND CAUSED CORROSION OF THE MOUNTING TRAY.  T	HIS WAS THIRD INSTANCE OF DISCOVERING LEAKING BATTERIES IN AN ELT WHERE THE SHELF LIFE DATE PRINTED ON THE BATTERY WAS S	TILL MANY YEARS INTO THE FUTURE.		1	L	7	1 	3O	3	O		2A13    	E286				 
2005120200145	20051202	00145	SO  	2005	12	2	2005FA0001550    	1	20051109	G	5410		COWL DOOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					LT NACELLE	CRACKED         	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	01	888CW	3661 				545				DURING ROUTINE INSP, FOUND 25 INCH CRACK, SEVERE DELAMINATION WITHIN THE LT ENG LOWER COWL DOOR.  AFFECTED AREA IS LOCAT	ED JUST AFT OF FWD SIDE, BETWEEN THE 4 & 8 O'CLOCK POSITION.  INITIAL INSPECTION  REVEALS DEBOND ON CARBON FIBER SKIN TO	 CORE AT 375 SQUARE INCHES.  EXTERNAL CARBON FIBER SKIN DEBOUND TO CORE AT 247 SQUARE INCHES.  FOUND CRACK AND DELAMINAT	ED AREA TO HAVE MUCH MOISTURE.  INSP OF AFFECTED AREA REVEALS NO IN SERVICE DAMAGE NOR WEAR THAT WOULD HAVE ALLOWED MOIS	TURE TO EGRESS COMPOSITE MATERIAL.  CAUSE OF DELAMINATION IS YET TO BE DETERMINED; CAUSE OF MOISTURE EGRESS IS UNKNOWN. 	 FAILURE OF COWL DOOR COULD HAVE CAUSED UNUSUAL FLT CHARACTERISTICS.  COMPONENT IS BEING SENT FOR FURTHER INVESTIGATION.	2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2005122100193	20051221	00193	EA  	2005	12	21	2005FA0001551    	2	20050908	G	7322	MA3PA105267	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	FAILED          	D			JU8S	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	25	95475		367  			15285902	L1927815			PILOT REPORTED PARTIAL LOSS OF POWER.  EXECUTED PRECAUTIONARY OFF FIELD LANDING.  NO DAMAGE TO AIRCRAFT.  TEARDOWN OF CA	RBURETOR REVEALED METAL SHAVINGS IN ACCELERATOR PUMP CIRCUIT.  SUSPECT METAL ORIGIN FROM ACCELERATOR PUMP STEM RUBBING O	N HOUSING.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005120100150	20051201	00150	EA  	2005	12	1	2005FA0001552    	2	20050930	G	8520	LW11750	CONNECTING ROD  			AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  	SNSNCH	76E	76EM8       	EA  	ENGINE	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	05	23JK	2043 	2043 			AA5B0022	L1974036A			CONNECTING ROD TO CRANKSHAFT BEARING FAILED RESULTING IN ROD DISCONNECTING FROM CRANKSHAFT AND SUBSEQUENT CASE PENETRATI	ON AND ENGINE STOPPAGE.					1	L	7	1 	3O	3	O		A16EA   	E286	5	N	P4EA	 
2005120200045	20051202	00045	NE  	2005	12	2	2005FA0001553    	2	20050914	G	7230	804581	STATOR          			SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					COMPRESSOR	SHEARED         	D			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	179AC	827  				64091	677776			(REF NR MDR05-080) INSPECTION WAS PERFORMED ON 1ST STAGE STATOR AND SHOWED SIGNS OF FOD.  UPON FURTHER INSPECTION IST WA	S DETERMINED THAT TWO RIVETS (MFG HEAD) HAD SHEARED ON STIFFENER RING OF THE 1ST STATOR AND WERE INGESTED CAUSING MINOR 	DAMAGE TO THE LATER STAGES OF THE ENGINE.  THE ENGINE WAS FULLY DISASSEMBLED, INSPECTION AND REPAIRED. PARTS THAT WERE R	EPLACED DUE TO EXCESSIVE DAMAGE ARE AS FOLLOWS; COMP BLADES 2ND STAGE, 5 EACH, 3RD STAGE, 2 EA, 4TH STAGE, 10 EACH, 5TH 	STAGE, 4 EACH, 7TH STAGE, 8EA, 9TH STAGE, 6 EA, COMP STATORS 1ST, 3RD, 4TH, 7TH, AND 8TH.  PROBABLE CAUSE UNKNOWN.  RECO	MMENDATIONS TO PREVENT RECURRENCE: CONTINUE TO PERFORM 100 PERCENT RIVET REPLACEMENT TO ALL STATORS AT OVERHAUL.  (K)	2	G	7	2 	4U	4	U		H6EA    	E15EA				 
2005122100197	20051221	00197	NE  	2005	12	21	2005FA0001554    	2	20051104	G	7200	5124T96P01	PLATE           								GE    	CT58  	CT581401    	30011	NE  					ENGINE	CRACKED         	B			CHIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09		1078 					295273			DURING MAJOR INSPECTION THE NR 1 COOLING PLATE WAS FOUND TO HAVE CRACKS IN  (SURFACE M).  THERE ARE 6 EA CRACKS APPROXIM	ATELY .250 IN LENGTH.  THE OVERALL GOOD, AND THERE WAS NO EVIDENCE OF AN OVERTEMPATURE ON ANY PARTS.  (K)										4	U			1E3				 
2005122000146	20051220	00146	CE  	2005	12	20	2005FA0001555    	1	20051114	G	3230	08412259	BELLCRANK       			CESSNA	310   	310I        	2074224	CE  	CONT  	O470  	IO470*      	17026	SO  					LT MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	11	8119M					310I0119				PILOT HAD INTERMITTENT GEAR LIGHT , HAD OBTAINED GREEN LIGHT WHEN HE LANDED.  UPON 1000 FT ROLL OUT THE LT MAIN GEAR COL	LAPSED CAUSING THE AC TO VEER LEFT 75 FT TO 100 FT.  UPON INSPECTION, FOUND LT MAIN LANDING GEAR, BELLCRANK ASSY HAD BRO	KEN. (K)				1	L	7	2 	3O	3	O		3A10    	E1CE				 
2005122100199	20051221	00199	CE  	2005	12	21	2005FA0001556    	1	20051010	G	3233	991013990H	ROD END         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NLG ACTUATOR	FAILED          	B			NF2D	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	03	923CP					421C1009				ROD END ON NOSE GEAR ACTUATOR FAILED DURING ROLLOUT CAUSING THE NOSE GEAR TO COLLAPSE.  (K)						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2005122800102	20051228	00102	CE  	2005	12	28	2005FA0001557    	1	20051109	G	2910	3905800370001	TUBE            			RAYTHN	390   	390         	7150030	CE  										HYD SYSTEM	CHAFED          	B			E81R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	03	322BJ	342  				RB93				INVESTIGATED HYDRAULIC FLUID LEAKAGE FROM RT ENGINE AREA.  FOUND RT ENGINE HYDRAULIC PUMP TO DAMPER TUBING ASSY CHAFED B	Y ADJACENT CLAMP AND SEEPING FLUID.  REPLACED TUBE AND SECURED AS REQUIRED KIT INSTALLED 5.9 HRS PREVIOUS FOR COMPLIANCE	 WITH AD.  (K)				1	7		2 	3F			RT	A00010WI					 
2005122800043	20051228	00043	CE  	2005	12	28	2005FA0001558    	1	20051116	G	5523	906100105	BUSHING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					LT ELEVATOR TAB	SEIZED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	439PW	1160 				LJ1589				DURING COMPLIANCE WITH ELEVATOR TAB TO ACTUATOR PUSHROD INSP FOR SAFETY NR 243 FOUND ELEVATOR TAB HORN BUSHING SEIZED.  	REPLACED TAB HORN BUSHING AND ACTUATOR PUSHROD TO HORN ATTACH BOLT BUSHING VERIFIED TAB HORN TO ACTUATOR PUSHROD OPERATI	ONS NORMAL IAW SAFETY NR 243.  HAVE FOUND THIS CONDITION ON SEVERAL AC INSPECTED.  RECOMMEND THIS BE A RECURRING MANDATO	RY SB OR CONNECTION REDESIGNED.  HAVE FOUND THIS CONNECTION OVERTIGHTENED DURING INSPECTION, SUSPECT AS A (QUICK FIX) FO	R AN EXCESSIVELY LOOSE TAB FREEPLAY CONDITION.  (K)		1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2005122000066	20051220	00066	CE  	2005	12	20	2005FA0001559    	1	20051116	G	5521	906100105	BUSHING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELEVATOR TAB	SEIZED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	439PW					LJ1589				DURING COMPLIANCE WITH ELEVATOR TAB TO ACTUATOR PUSHROD INSPECTION FOR SAFETY NR 243, FOUND ELEVATOR TAB HORN BUSHING SE	IZED.  REPLACED TAB HORN BUSHING AND ACTUATOR PUSHROD TO HORN ATTACH BOLT BUSHING, VERIFIED TAB HORN TO ACTUATOR PUSHROD	 OPERATIONS NORMAL IAW SAFETY COMMUNIQUE NR 243.  HAVE FOUND THIS CONDITION ON SEVERAL AC INSPECTED.  RECOMMEND THIS BE 	A RECURRING MANDATORY SB OR CONNECTION REDESIGNED.  HAVE FOUND THIS CONNECTION OVERTIGHTENED DURING INSPECTION, SUSPECT 	AS A (QUICK FIX) FOR AN EXCESSIVELY LOOSE TAB FREEPLAY CONDITION.  (K)		1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2005122000067	20051220	00067	CE  	2005	12	20	2005FA0001560    	1	20051116	G	3210	508102503	BRACE           	BEECH       		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG STRUT	CORRODED        	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	439PW	1160 			LJ1589	LJ1589				DURING INITIAL 6-YEAR/8000 CYCLE INSPECTION OF MAIN GEAR ASSY FOUND INTERNAL SURFACE OF UPPER BRACE PITTED AND CORRODED 	AT AREA IN CONTACT WITH UPPER MAIN GEAR STRUT.  CORROSION APPEARS UNUSUAL FOR A CLEAN, NEWER, LOW-TIME AIRCRAFT THAT IS 	HANGARED IN A NON SALT-AIR TYPE ENVIRONMENT.  UPPER BRACE ASSY SHOULD BE ASSEMBLED TO STRUT CYCLINDER WITH CORROSION PRE	VENTION COMPOUND AT ASSEMBLY IAW COMPONENT MM SUSPECT CORROSION PREVENTION COMPOUND NOT ADEQUATELY APPLIED AT INITIAL AS	SEMBLY.  (K)		1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2005120100186	20051201	00186	NE  	2005	12	1	2005FA0001561    	2	20051130	G	7230	BRR19918	BLADES          			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					ENGINE FAN	DEBONDED        	C				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	01	888CW	260  				545	11196			DURING ROUTINE ENGINE A-CHECK INSPECTION, FOUND 15 OUT OF 24 (CHOCKING PADS) ON BASE OF ENGINE FAN BLADE TO HAVE MIGRATE	D AFT OF NORMAL POSITION DUE TO DEBONDING OF (CHOCKING PAD).  THIS CONDITION WAS CAUSING ABNORMAL ENGINE VIBRATION DURIN	G ENGINE GROUND OPERATIONAL CHECK.  THE EMM 72-31-02-300-802 ALLOWS TWO METHODS OF ATTACHING THE (CHOCKING PAD) TO THE F	AN BLADE.  ONE METHOD IS THE USE OF PERMABOND F241 ADHESIVE.  THE SECOND METHOD IS THE USE OF 3M-9473 DOUBLE SIDED TAPE.	  NONE OF THE (CHOCKING PADS) THAT WERE ATTACHED WITH THE PERMABOND F241 FAILED; ONLY THE (CHOCKING PADS) ATTACHED WITH 	3M 9473 DOUBLE SIDED TAPE FAILED.	2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2005122000062	20051220	00062	EA  	2005	12	20	2005FA0001562    	2	20051117	G	8530	LW12966	VALVE SEAT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					CYLINDER	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	66906	338  				317405197	L220768A			VALVE SEAT SEPARATED FROM CYLINDER.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005122800094	20051228	00094	SW  	2005	12	28	2005FA0001563    	1	20050908	G	7603		THROTTLE CABLE  			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					THROTTLE ARM	DISCONNECTED    	B			AW4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	6821V					200003				PILOT REPORTED THAT ON RUNUP, HE WAS UNABLE TO CONTROL RPM.  INVESTIGATION DETRMINED THAT THE THROTTLE CABLE HAD COME DI	SCONNECTED FROM THE CARBURETOR THROTTLE ARM.  BOLT WAS PRESENT, BUT NUT AND COTTER PIN WERE MISSING INSTALLED PROPER HAR	DWARE AND FUNCTIONAL CHECKED, OK.  (K)				1	L	7	1 	3O	3	O		2A3     	E286				 
2005122000155	20051220	00155	EA  	2005	12	20	2005FA0001564    	1	20051114	G	2160	6279622	SWITCH          			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					AIR CONDITIONING	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	25	779AZ	2795 				5176				AIR CONDITIONING WOULD INTERMITTENTLY GO UNCONTROLLABLY FULL HOT.  IN THE HANGAR, FOLLOWING MAINTENANCE MANUAL TROUBLESH	OOTING FLOW CHART WOULD NOT REVEAL AND DISCREPANCIES.  AFTER RUNNING SYSTEM ON RAMP AND GETTING SYSTEM TO FAIL.  LT AIR 	CONDITIONING SYSTEM LOW LIMIT TEMPERATURE CONTROL SWITCH WAS FOUND OPEN.  REMOVED SWITCH FROM AIRCRAFT AND COOLED IN SHO	P, CHECKED AGAIN AND SWITCH CHECKED GOOD.  HEATED WITH HEAT GUN AND SWITCH OPENED.  REPLACED WITH NEW UNIT.  OPS CHECKED	 GOOD.  (K)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005122700200	20051227	00200		2005	12	27	2005FA0001565    	1	20051201	G	5100		GEAR            																	UNKNOWN	UNKNOWN         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	234HM									GEAR																			 
2005122800213	20051228	00213	NE  	2005	12	28	2005FA0001566    	2	20051130	G	7230	BRR19918	BLADE           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					COMPRESSOR	DEBONDED        	C				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			WP	01	888CW	260  				545	11197			DURING ROUTINE ENGINE A-CHECK INSPECTION, FOUND 15 OUT OF 24 (CHOCKING PADS) ON BASE OF ENGINE FAN BLADE TO HAVE MIGRATE	D AFT OF NORMAL POSITION DUE TO DEBONDING OF (CHOCKING PAD).  THIS CONDITION WAS CAUSING ABNORMAL ENGINE VIBRATION DURIN	G ENGINE GROUND OPERATIONAL CHECK.  THE EMM 72-31-02-300-802 ALLOWS 2 METHODS OF ATTACHING THE (CHOCKING PAD) TO THE FAN	 BLADE.  NR 1 METHOD IS THE USE OF PERMABOND F241 ADHESIVE. NR 2 METHOD IS THE USE OF 3M-9473 DOUBLE SIDED TAPE.  NONE O	F THE (CHOCKING PADS) THAT WERE ATTACHED WITH THE PERMABOND F241 FAILED; ONLY THE (CHOCKING PADS) ATTACHED WITH 3M 9473 	DOUBLE SIDED TAPE FAILED.	2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2005122800207	20051228	00207	EA  	2005	12	28	2005FA0001567    	1	20051130	G	6210	269A1002	BLADES          			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	VIBRATES        	B				O				OTHER                   				E			VIBRATION/BUFFET          			HO	HOVERING       	1			SW	17	277DT	3801 				0028	CAE845057			HAVE BEEN EXPERIENCING PROBLEMS KEEPING THE M/R BLADES IN ACCEPTABLE TRACK AND BALANCE ON ALL 333/269D CONFIG A AIRCRAFT	 THAT WE MAINTAIN. ALSO HAVE BEEN FINDING MUCH MORE RAPID DETERIORATION OF THE M/R DAMPERS, FLAPPING HINGE BEARINGS, AND	 VERTICAL HINGE BEARINGS COMPARED TO THE PREVIOUS AIRCRAFT WITH THE P/N 269A1185-5 M/R BLADE ASSEMBLIES. THE NEW BLADES 	WITH THE EXTENDED NOSE SECTION WILL NOT STAY IN TRACK OR BALANCE FOR ANY ADEQUATE PERIOD OF TIME. SUGGEST THAT MFG DESIG	N A NEW BLADE WITH A CONSTANT CHORD AND SOON.		1	G	7	1 	3U	3	U	0	4H12    	E4CE				 
2006010500256	20060105	00256	NM  	2006	1	5	2005FA0001568    	1	20051203	G	2810		VENT LINE       			CHRIS 	HUSKY 	A1          	221020X	NM  	LYC   	O360  	O360C1G     	41514	EA  	HARTZL	HCC2Y	HCC2Y*      	GL  	FUEL SYSTEM	BLOCKED         	P				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	05	9622V					1154	L3258536A	H72509		ENGINE STOPPED DUE TO BLOCKED FUEL VENT LINE. THIS OCCURRED ON THE GROUND DURING TAXIING. NO DAMAGE TO PLANE.  PROBABLE 	CAUSE WAS SNOW BUILD UP ON THE WING EXTENDING OVER THE ENDS OF THE VENT LINES FOLLOWED BY FREEZING.					1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2005122800066	20051228	00066	CE  	2005	12	28	2005FA0001569    	1	20051128	G	6100	IA103TCM	PROPELLER       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  		OUT OF LIMITS   	B			W59R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	757QH					15279916		773931		PROPELLER SUBMITTED FOR INSPECTION IAW AD 03-12-05.  DURING SB RESEARCH IT WAS DISCOVERED THAT AD WAS DUE AS SN IS LISTE	D IN AD.  DURING INSPECTION FOR AD, THE PROPELLER WAS FOUND UNDER MINIMUM WIDTH.  PROPELLER IS SCRAP.  (K)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005122800040	20051228	00040	CE  	2005	12	28	2005FA0001570    	1	20051121	G	2697		WIRE            	PYROTECTOR  		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					FIRE DETECTOR	CHAFED          	B			HI1R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			NE	05	192WA					U152	PCE50587			AC EXPERIENCED A FALSE FIRE WARNING ON THE LT ENGINE ENROUTE.  WHILE FLYING THROUGH HEAVY PRECIPITATION.  THE PILOT VISU	ALLY CHECKED THE ENGINE AND MONITORED ALL RELATED INSTRUMENTS AND SYSTEMS TO VERIFY NORMAL INDICATIONS THUS CONCLUDING T	HE INDICATION WAS FALSE.  THE PILOT NOTIFIED MAINT UPON ARRIVAL.  MAINT EXAMINED THE FIRE DETECTOR SYSTEM AND FOUND 2 WI	RES CHAFING AT THE LT NACELLE AFT UPPER DETECTOR.  THE MECHANIC REPOSITIONED AND REPAIRED THE WIRES IAW STANDARD MAINT P	RACTICES AND OPERATIONALLY CHECKED THE SYSTEM.  NO DEFECTS WERE NOTED.  THE MECHANIC ALSO INSPECTED THE ENGINE FOR VISIB	LE SIGNS OF FIRE.  NONE NOTED.  (K)	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005122800037	20051228	00037	CE  	2005	12	28	2005FA0001571    	1	20051011	G	5751	11561001065	RIB             			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  					LT ELEVATOR	CRACKED         	B			TIMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	95WA	39157				U6				LT ELEVATOR WAS FOUND CRACKED BEHIND ELEVATOR BALANCE WEIGHT AT THE OB END OF THE ELEVATOR.  UPON FURTHER INVESTIGATION 	IT WAS DISCOVERED THAT THE BALANCE WEIGHT WAS MODIFIED TO INCREASE THE WEIGHT.  THE ADDED WEIGHT WAS DETERMINED TO BE IN	STALLED BECAUSE THE ELEVATOR HAD BEEN SKINNED WITH ALUMINUM AND WAS PREVIOUSLY SKINNED WITH MAGNESIUM.  THE ADDED WEIGHT	 OF THE ALUMINUM SKIN REQUIRED ADDED WEIGHT FOR BALANCING THE ELEVATOR.  THIS ADDED WEIGHT CAUSED THE RIB TO CRACK.  ELE	VATOR WAS REPLACED WITH AN ALUMINUM ELEVATOR.  ALUMINUM ELEVATOR HAS AN ADDITIONAL BALANCE WEIGHT INSTALLED FOR BALANCIN	G PURPOSES.  KIT 99-4018S WAS INSTALLED IN THE HORIZ STAB TO PROVIDE AN OPENING FOR THE ADDITIONAL BALANCE WEIGHT.  (K)	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005122000147	20051220	00147	CE  	2005	12	20	2005FA0001572    	1	20051123	G	3610		PNEUMATIC SYSTEM			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  						CONTAMINATED    	D				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			EA	05	3267N					TH1767				DURING PROLONGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER ENTER INTO THE PNEUMATIC SYST	EM.  INSP OF PNEUMATIC SYS REVEALED LG AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY INS	P REVEALED SEVERAL OUNCES OF WATER REMAINING IN SYS.  SYS WAS PURGED OF ALL WATER AND DRIED.  AC WAS RETURNED TO SERVICE	.  FLIGHT CREW REPORTED AC AGAIN WAS OPERATED FOR AN EXTENDED PERIOD OF TIME IN HEAVY PRECIPITATION.  THIS AC HAS A HIST	ORY OF PREMATURE FLIGHT COMMAND INDICATOR FAILURES CAUSED BY RUST AND WATER CONTAMINATION.  RELOCATE THE PNEUMATIC SYS F	ILTER TO AN AREA BEHIND THE ENGINE BAFFLE ASSEMBLY WHERE IT WILL NOT BE SUBJECT TO IMPACT WATER. (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005122000071	20051220	00071	CE  	2005	12	20	2005FA0001573    	1	20051123	G	3610		PNEUMATIC SYSTEM			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  						CONTAMINATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	1065B					TH1765				DURING PROLONGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER ENTER INTO THE PNEUMATIC SYST	EM.  INSP OF PNEUMATIC SYS REVEALED LARGE AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY 	INSP REVEALED SEVERAL OUNCES OF WATER REMAINING IN SYS.  SYS WAS PURGED OF ALL WATER AND DRIED.  AC WAS RETURNED TO SERV	ICE.  FLIGHT CREW REPORTED AC AGAIN WAS OPERATED FOR AN EXTENDED PERIOD OF TIME IN HEAVY PRECIPITATION.  THIS AC HAS A H	ISTORY OF PREMATURE FLIGHT COMMAND INDICATOR FAILURES CAUSED BY RUST AND WATER CONTAMINATION.  RELOCATE THE PNEUMATIC SY	S FILTER TO AN AREA BEHIND THE ENGINE BAFFLE ASSEMBLY WHERE IT WILL NOT BE SUBJECT TO IMPACT WATER.  (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005122000149	20051220	00149	CE  	2005	12	20	2005FA0001574    	1	20051123	G	3610		PNEUMATIC SYSTEM			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  						CONTAMINATED    	D				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			EA	05	3214H					TH1731				DURING PROLONGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER INTO THE PNEUMATIC SYSTEM.  I	NSP OF PNEUMATIC SYS REVEALED LARGE AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY INSP R	EVEALED SEVERAL OUNCES OF WATER REMAINING IN SYS.  SYS WAS PURGED OF ALL WATER AND DRIED.  AC WAS RETURNED TO SERVICE.  	FLIGHT CREW REPORTED AC AGAIN WAS OPERATED FOR AN EXTENDED PERIOD OF TIME IN HEAVY PRECIPITATION. THIS AC HAS A HISTORY 	OF PREMATURE FLIGHT COMMAND INDICATOR FAILURES CAUSED BY RUST AND WATER CONTAMINATION.  RELOCATE THE PNEUMATIC SYS FILTE	R TO AN AREA BEHIND THE ENGINE BAFFLE ASSEMBLY WHERE IT WILL NOT BE SUBJECT TO IMPACT WATER.  (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005122000153	20051220	00153	EA  	2005	12	20	2005FA0001575    	2	20051207	G	7320	312310001	SENSE LINE      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE	WORN            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	1114Z					LJ1514	RR0030			P3 AIR LINE CONNECTS COMP TO P3 AIR FLTR.  LINE ATTACHES TO GAS OPER CASE AT 5:00 POS LOOKING FWD, CONNECTS TO IS FITTIN	G AT REAR FIREWALL.  ENG INSTALLED, LINE RESTS FIRMLY ON ENG TRUSS.  SUB ENG HAVE BEEN INSTALLED ON THIS AC FOR 300 HRS.	  P3 LINE IS ALREADY FRETTED THROUGH INSULATION THAT IS WRAPPED ON LINE.  BOTH P3 LINE, ENG TRUSS SHOW SIGNS OF FRETTING	 WEAR IN PARENT MATL.  P3 LINE SUPPLIES P3 AIR TO P3 AIR FLTR.  P3 AIR CONTINUES THROUGH FLTR TO FCU.  IF THIS LINE WAS 	TO RUPTURE. (FRETTING THROUGH OUTER WALL OF TUBE), P3 AIR SUPPLY TO FCU WILL BE LOST.  FCU DROPS OFF TO MIN FLOW (40 PER	CENT) WHEN P3 AIR IS LOST.  PROP OF AFFECTED ENG WILL NOT REVERSE EFFECTIVELY.  LOSS OF P3 AIR SUPPLY THE FCU WOULD RESU	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005122800034	20051228	00034	CE  	2005	12	28	2005FA0001576    	1	20051207	G	5100		MANUAL          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  						INCORRECT       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	1114Z					LJ1514	RR0030			THIS ENG MODEL HAS BEEN INSTALLED ON THIS AC. FG OAW TRAD STC SA02238AT.  THIS STC HAS NO REFERENCES FOR A GROUND PWR AS	SURANCE RUNS.  NO GRAPHS ARE AVAILABLE THROUGH STC TO CHART ENG PARAMETERS FOR ACCEPTABLE GROUND PERFORMANCE DATA ON THI	S INSTALLATION.  IT CAN NOT BE VERIFIED THAT THIS ENG ON THIS INSTALLATION IS OPERATING WITHIN REQUIRED ENG PARAMETERS. 	 UNABLE TO RETURN THIS AC TO SERVICE WITHOUT SUCH DATA.  CHART DATA FOR THIS ENG HAS BEEN USED IN PAST TO ACCEPT THIS EN	G AT GROUND PERFORMANCE.  HOW IS IT POSSIBLE TO ACCEPT AN ENG/AC USING A DIFFERENT MODEL CHART?  STC HOLDER MUST BE RESP	ONSIBLE FOR SUPPLYING ALL REQUIRED DATA FOR GROUND PERFORMANCE.  HOW DID STC INSTALL GET APPROVED WITHOUT THIS INFO?	1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2006010500255	20060105	00255	NM  	2006	1	5	2005FA0001577    	1	20051203	G	2810		VENT LINE       			CHRIS 	HUSKY 	A1          	221020X	NM  	LYC   	O360  	O360C1G     	41514	EA  	HARTZL	HCC2Y	HCC2Y*      	GL  	FUEL SYSTEM	BLOCKED         	P				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	01	9622V					1154	L3258536A	H72509		ENGINE STOPPED DUE TO BLOCKED FUEL VENT LINE. THIS OCCURRED ON THE GROUND DURING TAXIING. NO DAMAGE TO PLANE.  PROBABLE 	CAUSE WAS SNOW BUILD UP ON THE WING EXTENDING OVER THE ENDS OF THE VENT LINES FOLLOWED BY FREEZING.					1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2006010500247	20060105	00247	SO  	2006	1	5	2005FA0001578    	1	20050415	G	5310		TUBE            			MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	O540*       	41532	EA  					FUSELAGE	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	56395	1350 				7335C				ANNUAL INSPECTION DISCOVERED WIDESPREAD CORROSION OF 4130 STEEL FUSELAGE STRUCTURE.  LOWER DOOR POST TUBES WERE CORRODED	 NEARLY THROUGH, RENDERING AIRPLANE UNAIRWORTHY. SIGNIFICANT PORTIONS OF APPARENT ORIGINAL YELLOW FIBERGLASS INSTALLATIO	N WERE WET.  AIRCRAFT WAS KEPT OUTSIDE.  MOISTURE MIGHT HAVE ENTERED THROUGH WING ROOT, WITH PROBLEM POSSIBLY COMPOUNDED	 BY HEADLINER BEING FACTORY SALINE-IMPREGNATED (FOR FIRE RESISTANCE), AND BY WICKING OF MOISTURE BY FIBERGLASS INSULATIO	N.  THE MOST SIGNIFICANT CORROSION WAS NOT VISIBLE WITHOUT TEARING OUT INTERIOR THAT IS NOT TYPICALLY AND CONVENIENTLY R	EMOVABLE.  AC HAD BEEN FLOATPLANE, SEASONALLY, SINCE 1999.	1	H	7	1 	3O	3	O		3A23    	E295				 
2006012400124	20060124	00124	EU  	2006	1	24	2005FA0001579    	1	20051214	G	5313		LONGERON        			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540*    		EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	78EX					078				DURING ROUTINE 1,000 HR INSPECTION CRACKS WERE FOUND IN THE UPPER LONGERON AT THE HORIZONTAL STABILIZER ATTACHMENT, THES	E WERE VERIFIED USING A FLUORESCENT DYE CHECK PENETRANT METHOD, CRACKS WERE ALSO FOUND IN THE VERTICAL TUBE SUPPORTING F	ORCES FROM THE TAIL LANDING GEAR FORWARD ATTACH POINT.				1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
2005122800032	20051228	00032		2005	12	28	2005FA0001580    	1	20051007	G	8011	MZ4222	STARTER         																	HOUSING	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		124  								UPON INSPECTION OF STARTER MOTOR, IT APPEARS AS THOUGHT THE THRU-BOLTS THAT ATTACH THE MOTOR TO THE BENDIX FAILED IN FLI	GHT.  (K)																		 
2005122000154	20051220	00154	CE  	2005	12	20	2005FA0001581    	1	20051215	G	8011	MZ298	BEARING         	PRESTOLITE  		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					STARTER	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	73827		123  		150043	17267703				AIRCRAFT CAME IN FOR AN OIL CHANGE, OWNER NOTICED BENDIX DRIVE SHAFT BEARING LYING IN THE COWLING.  STARTER WAS O/H.  TH	E BEARING WAS A SLIP FIT TO THE HOUSING.  I WOULD RECOMMEND BETTER TOLERANCE CONTROL AT OVERHAUL, AND REMIND ALL MECHANI	CS TO PERFORM SOME SORT OF INCOMING PARTS INSPECTION.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005122000157	20051220	00157	CE  	2005	12	20	2005FA0001582    	1	20051130	G	3610		PNEUMATIC SYSTEM			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  						CONTAMINATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	202P					TH1875				PNEUMATIC SYSTEM INSPECTED AND TRACES OF WATER WERE FOUND IN THE EJECTOR VALVE AND AREA BELOW THE VALVE.  FURTHER INSPEC	TION REVEALED WATER IN THE PNEUMATIC MANIFOLD VALVE AND ASSOCIATED PLUMBING.  APPROXIMATELY .5 OZ OF WATER WAS REMOVED F	ROM THE SYSTEM.  THE PNEUMATIC SYSTEM INLET FILTER WERE INSPECTED AND SHOWED SIGNS OF WATER INGESTION.  THERE WERE NO SI	GNS OF WATER OR MOISTURE OR WATERE INT THE INSTRUMENTS AND THE PILOT HAD NO INDICATION OF ANY CONTAMINATION.  RELOCATE T	HE PNEUMATIC SYSTEM FILTER TO AN AREA WHERE IT WILL NOT BE SUBJECT TO WATER INGESTION.  (K)		1	L	7	2 	3O	3	O		3A16    	E3SO				 
2005122000158	20051220	00158	SO  	2005	12	20	2005FA0001583    	1	20051205	G	2810		VENT LINE       			AMRGEN	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320*       	41508	EA  					RT WING TANK	PLUGGED         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NE	03	26403					AA5A0566				RT WING FUEL TANK COLLAPSED DURING FLIGHT.  SAFE LANDING WAS MADE.  FOUND FUEL TANK VENT LINE PLUGGED WITH INSECT DEBRIS	.  PERIODICALLY CHECK FUEL VENTS FOR OBSTRUCTIONS, ESPECIALLY WHEN TIED DOWN ON GRASS.  (K)					1	L	7	1 	3O	3	O		A16EA   	E274				 
2005122800103	20051228	00103	GL  	2005	12	28	2005FA0001584    	2	20051121	G	7310	A91941	HOSE            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					LT ENG FUEL	CHAFED          	B			E81R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	03	112CM	198  				RB123	105143			DURING INITIAL 200 HOUR INSPECTION FOUND LT ENGINE MOTIVE FLOW FUEL LINE HOSE ASSY CHAFED BY ADJACENT COWL LATCH.  REPLA	CED HOSE ASSY.  AND REROUTED, SECURED AS REQUIRED FOR CLEARANCE.  AIRCRAFT ABOVE SN RANGE OF AD AND MSB.  (K)					1	7		2 	3F	4	F	RT	A00010WI	E3GL				 
2005122800062	20051228	00062	CE  	2005	12	28	2005FA0001585    	1	20051121	G	2820	S14956R221605	LINE            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SYSTEM	LEAKING         	B			L6QR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	05	544SP	949  				172S8399				PILOT REPORTED FUEL LEAKING FROM THE IB WING ROOT AREA AFTER AIRCRAFT WAS FUELED.  UPON INSPECTION, RUBBER FUEL HOSES AT	 WING ROOT WERE FOUND TO BE HARD, SPLIT LENGTHWISE AND LEAKING THROUGH WALL OF HOSE.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005122000156	20051220	00156	CE  	2005	12	20	2005FA0001586    	1	20050424	G	3233		ACTUATOR        			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470*      	17026	SO  					MLG	FAILED          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	9794X					21058094				MAIN GEAR ROTORY ACTUATOR SEALS FAILED.  HYD FLUID LEVEL WENT TO ZERO AND GEAR FAILED TO EXTEND AND LOCK.  (K)						1	H	7	1 	3O	3	O		3A21    	E1CE				 
2005122800065	20051228	00065	CE  	2005	12	28	2005FA0001587    	1	20051128	G	2730	12600747	ACTUATOR        			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	ELEVATOR TRIM	MISDRILLED      	B			FU2R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03	521AF	1000 				18281194	L2865648A			MFG MANDATES THE REMOVAL DISASSEMBLY, AND INSPECTION OF THE ELEVATOR TRIM ACTUATOR AT 1000 HRS TT OR 6 YEARS.  UPON REMO	VAL OF THIS ACTUATOR,  FOUND THAT THE GROOVED PIN HOLES IN HOUSING WERE MISDRILLED.  THIS CAUSED THE PIN TO WEAR INTO TH	E ACTUATOR HOUSING.  OPERATE 18 AIRCRAFT WITH THE SAME ACTUATOR IN THEM.   AS ACTUATORS ARE REMOVED, WILL ADVISE.  PICTU	RES ARE AVAILABLE OF THE HOUSING IN QUESTION IF NEEDED FOR YOUR CONSIDERATION.  INSTALLING A NEW ACTUATOR IN THIS AIRCRA	FT.  (K)		1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2005122800095	20051228	00095	NE  	2005	12	28	2005FA0001588    	2	20051130	G	7250	3037313	TURBINE WHEEL   			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	LT ENGINE	DAMAGED         	B			VIBR	A				UNSCHED LANDING         				Y	E		ENGINE STOPPAGE           	VIBRATION/BUFFET          		CL	CLIMB          	1			SO	13	137SL					1102	RK01510	KV55		AIRCRAFT WAS CLIMBING FROM 26,000 TO 28,000 WHEN THE PILOT HEARD A LOUD BANG.  THE LT ENGINE TEMPERATURE PEGED.  THE PIL	OT IMMEDIATELY PULLED THE LT ENGINE TO FLIGHT IDLE.  AFTER LANDING AND SHUTDOWN, VISUAL INSPECTION OF THE LT ENGINE SHOW	ED SEVERE DAMAGE TO THE TURBINE DISC AND ALL BLADES OF THE LT PROPELLER.  (K)				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
2005122800033	20051228	00033	CE  	2005	12	28	2005FA0001589    	1	20051129	G	3297		WIRE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A11      	52043	NE  					MLG	CHAFED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	5641X	5527 				LJ1241				INVESTIGATED REPEATED INTERMITTENT LANDING GEAR RETRACT/ EXTENSION SYSTEM FAULTS.  FOUND WIRES G45F22 AND G10L22 FOR NOS	E LANDING GEAR DOWNLOCK SWITCH CHAFING ON ENVIRONMENTAL AIR CROSS-OVER DUCT IN LOWER RT NOSE KEEL AREA.  REPAIRED DAMAGE	D WIRING AS REQUIRED AND SECURED.  ALSO REPAIRED ADJACENT AIR CONDITIONING SYSTEM WIRING CHAFING IN SAME AREA.  RECOMMEN	D THAT THIS AREA AND OTHER SIMILAR SELDOM INSPECTED AREAS BE INSPECTED FOR GENERAL WIRING CONDITION AND OTHER FAULTS AFT	ER THE AIRCRAFT HAS ACCUMULATED 5000 HRS OR IS PAST TEN YEARS OLD.  (K)		1	L	7	2 	3T	3	T	RT	3A20    	E4EA				 
2005122000049	20051220	00049	CE  	2005	12	20	2005FA0001590    	1	20051122	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	946CE	1609 				BB1728				AT 27,000 FT THE PILOT SIDE WINDSHIELD SHATTERED.  THE PILOTS VIEW WAS TOTALLY OBSTRUCTED.  THE COPILOT WAS ABLE TO LAND	 THE AIRCRAFT SAFELY.  AFTER REMOVAL, THE OUTSIDE PANEL WAS NOT DAMAGED.  THE INSIDE PANEL WAS STILL IN TACT BUT COMPLET	ELY SHATTERED.  THE LARGEST PIECE WAS ONLY .5 INCH IN DIAMETER.  AFTER TALKING TO MFG, IT WAS REVEALED THAT THIS WAS A C	OMMON PROBLEM AND AN NEW STYLE WINDSHIELD WAS BEING USED.  (K)			1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2005122000053	20051220	00053	CE  	2005	12	20	2005FA0001591    	1	20051128	G	3230	1153800025	MOTOR           			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR	INOPERATIVE     	B			HI1R	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			NE	05	199WA					U154	PCE42154	BUA29207		AFTER DEPARTING, PILOT, SELECTING GEAR UP.  AFTER THIS THE PILOT NOTED A STRONG ELECTRICAL BURNING SMELL.  THE PILOT ELE	CTED TO RETURN TO DEPARTURE.  ON VERY SHORT FINAL APPROACH, THE PILOT NOTED THE GEAR WAS NOT FULLY LOCKED INTHE DOWN POS	ITION AS INDICATED BY THE GEAR HANDLE LIGHTS AND INITIATED A GO AROUND AND DECLARED AN EMERGENCY.  BY THAT TIME THE BURN	ING SMELL HAS DISIPATED SOMEWHAT.  THE PILOT THEN HAND-PUMPED THE GEAR DOWN AND LANDED WITHOUT INCIDENT.  A MAINTENANCE 	EVALUATION REVEALED THE HYDRAULIC MOTOR THAT DRIVEWS THE GEAR HAD FAILED RESULTING IN THE BURNING SMELL. THE MOTOR WAS R	EPLACED AND THE AIRCRAFT HAS BEEN PLACED BACK IN SERVICE.  (K)	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2005122000057	20051220	00057	GL  	2005	12	20	2005FA0001592    	3	20051121	G	6110		SNAP RING       													MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER	MISSING         	B			PS4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05								050019		THIS PROPELLER CAME INTO OUR SHOP FOR STC BLADE ANGLE CHANGE ON A NEW PROPELLER.  ON OUR FIRST CHECK OF THE BLADE ANGLE 	WE GOT 4 DEGREES AND KENW SOMETHING WAS WRONG.  SO WE PULLED TH DOEM AND THE PISTON SNAP RING HAD NOT BEEN INSTALLED FRO	M THE FACTORY.  (K)														5	C	P22EA	 
2005122000055	20051220	00055	CE  	2005	12	20	2005FA0001593    	1	20051206	G	2140	CD21186	PUMP            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	CABIN HEATER	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	421KS				521	421B0507	267301R	735052		THE PILOT REPORTED THE HEATER HAD STOPPED DURING FLIGHT.  AFTER RETURNING TO THE MAINTENANCE SHOP THE HEATER WAS TROUBLE	SHOT AND INSPECTED.  FOUND THE HEATER FUEL PUMP HAD MALFUNCTIONED AND HAD CAUGHT ON FIRE FOR A TIME.  WERE ABLE TO SAY I	T WAS ON FIRE BECAUSE OF THE BURN MARKS ON THE OUTSIDE OF THE PUMP HOUSING.  HAVE ENCLOSED 2 PHOTOS TO SHOW THIS.  HAVE 	TALKED WITH PUMP MFG TO DESIGN A NEW PUMP .  PROBLEM IS WITH FUEL REGULATOR ING THE WINGS.  THE REGULATORS SEEM TO NOT A	LLOW ENOUGH FUEL TO GO THRU THEM TO KEEP THE PUMPS OPERATING CORRECTLY WHICH ALLOWS THEM TO OVERHEAT AND FAIL.  (K)		1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
2005122000077	20051220	00077	CE  	2005	12	20	2005FA0001594    	1	20051206	G	3220	HMXLTFG	ROD END         			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG P/P TUBE	BROKEN          	B			VL1R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	01	1748W					TE887				AFTER TAKEOFF, LANDING GEAR WAS RETRACTED AND A BANGING NOISE WAS HEARD BY THE PILOT.  IT BECAME APPARENT THE NOSE GEAR 	RETRACT MECHANISM HAD BROKEN AND THAT THE NOSE GEAR DID NOT RETRACT PROPERLY.  THE AIRCRAFT WAS FLOWN TO ITS DESTINATION	 AIRPORT WHERE NOSE GEAR COLLAPSED ON LANDING AS EXPECTED.  INVESTIGATION OF THE MECHANISM REVEALED A LANDING GEAR TRANS	MISSION CONNECTED TO THE NOSE LANDING GEAR PUSH/PULL TUBE.  PROBABLE CAUSE SUSPECT TO BE OUT OF RIG CONDITION THAT CAUSE	D FAILURE.  NO EVIDENCE OF FOREIGN OBJECTS WERE EVIDENT.  SPECIAL INSPECTIONS OF RIGGING AT REGULAR INTERVALS IS RECOMME	NDED TO AVOID RECURRANCE OF THIS INCIDENT.  (K)	1	L	7	2 	3O	3	O		3A16    	E5CE				 
2005122000408	20051220	00408	CE  	2005	12	20	2005FA0001595    	1	20051209	G	2710		CONTROL CABLE   			BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	AILERON	DAMAGED         	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			NE	01	602FC	3050 				TC1624				AILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WA	S FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL E	ND.  AREA IS VERY HARD TO INSPECT, AC MUST BE ON JACKS WITH GEAR PARTIALLY RETRACTED AND INNER GEAR DOORS OPEN TO SEE, A	ND STILL DIFFICULT TO SEE.			1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P920	 
2005122000409	20051220	00409	CE  	2005	12	20	2005FA0001596    	1	20051209	G	2710		CONTROL CABLE   			BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	AILERON	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	602FC	3050 				TC1624				AILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WA	S FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL E	ND. AREA IS VERY HARD TO INSPECT, AC MUST BE ON JACKS WITH GEAR PARTIALLY RETRACTED AND INNER GEAR DOORS OPEN TO SEE, AN	D STILL DIFFICULT TO SEE.			1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P920	 
2005122000410	20051220	00410	EA  	2005	12	20	2005FA0001597    	2	20051210	G	8500		ENGINE          			AMTR  	VANS  	RV8         	       	GL  	LYC   	O360  	O360A1A     	41514	EA  						MALFUNCTIONED   	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			EA	21	20EA					007				FORCED LANDING, DUE TO ENG FAIL DURING TAKEOFF.  DAMAGE TO AC INCLUDED LT MLG WAS BROKEN, LT WING TIP SKIN DENTED, LWR E	NG COWLING DAMAGED.  DAMAGE TO AC WAS CONSIDERED TO BE MINOR.  INSP OF AC REVEALED LT FUEL TANK WAS FULL OF FUEL; FUEL Q	TY IN RT FUEL TANK COULD NOT BE DETERMINED.  ENG OIL LEVEL WAS AT 6 QUARTS. CONTINUITY OF ENG CONTROLS, THROTTLE, MIXTUR	E, AND CARBURETOR HEAT WAS ESTABLISHED FROM COCKPIT TO ENG.  ENG FUEL SYS LINES WERE DISCONNECTED FROM CARBURETOR, FUEL 	SAMPLE REVEALED CLEAN BLUE AVIATION FUEL.  EXT INSP OF ENG REVEALED NO MECH ANOMALIES.  ENG FUEL STRAINER COULD NOT BE D	RAINED WITH ENG COWLINGS INSTALLED ON AC, THEREFORE FUEL STRAINER WAS NOT BEING DRAINED DURING PILOT'S PREFLIGHT INSP.	1	L	7	1 	3O	3	O	NT	EXPA1L71	E286				 
2005122000411	20051220	00411	CE  	2005	12	20	2005FA0001598    	1	20051209	G	2710		CONTROL CABLE   			BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	AILERON	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	602FC	3050 				TC1624				AILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDERFLOOR TO PEDESTAL AND CONTROL SPROCKET WAS	 FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL EN	D. AREA IS VERY HARD TO INSPECT, AC MUST BE ON JACKS WITH GEAR PARTIALLY RETRACTED AND INNER GEAR DOORS OPEN TO SEE, AND	 STILL DIFFICULT TO SEE.			1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P920	 
2005122000407	20051220	00407	GL  	2005	12	20	2005FA0001599    	1	20051219	G	7820	19148410	MUFFLER         			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520*      	17032	SO  					RT ENGINE	BROKEN          	G				A				UNSCHED LANDING         				A			FLAME/FIRE                			NR	NOT REPORTED   	1			SO	13	910EJ		8    			30405				RT SIDE MUFFLER, REAR TAIL-PIPE OUTLET, CRACKED OFF OF THE MUFFLER ALLOWING HOT GASES TO BLOW ONTO FIREWALL AND SURROUND	ING COMPONENTS.  AN ENGINE FIRE OCCURRED AND AIRCRAFT MADE EMERGENCY LANDING.  THE TAIL PIPE BALL JOINT FOUND TO BE STIL	L INTACT WITH THE (V) BAND INSTALLED, TIGHT AND SAFETY WIRED.				1	L	7	1 	3O	3	O		A18CE   	E5CE				 
2005122800099	20051228	00099	SO  	2005	12	28	2005FA0001600    	1	20050523	G	7602	3020508	CABLE           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					MIXTURE CONTROL	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	63790	4782 				277754117				MIXTURE CABLE BROKE AT CONTROL LEVER END.  7 STRAND INNER CABLE PARTED .7500 INCH FROM PUSH/PULL SLIDER CABLE END.  CABL	E STRANDS APPEAR TO HAVE BEEN BALLONED FROM OVER COMPRESSION, OVER TRAVEL.  CABLE PARTED AT ENGINE SHUT DOWN.  THE REPLA	CEMENT CABLE IS PN 454-204 AND MAY AVE BEEN IMPROVED OVER THE ORIGINAL.  (K)				1	L	7	2 	3O	3	O		1A10    	E14EA				 
2005122800097	20051228	00097	SO  	2005	12	28	2005FA0001601    	1	20050818	G	3210	402427	BOLT            	PIPER       		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					LINK	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	01	63790	4898 				277754117				PN 400-111 BOLT BROKE ON LANDING.  BOLT IS IN LINK, PN 16240-5.  GEAR FOLDED AFT AND MAIN TIRE RODE ON RT FLAP.  (NM0120	0510571) (K)					1	L	7	2 	3O	3	O		1A10    	E14EA				 
2005122800068	20051228	00068	CE  	2005	12	28	2005FA0001602    	1	20051207	G	5330	04102362	SKIN            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					FUSELAGE	CRACKED         	B			V36R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	65407					15281533				THE SKIN SUPPORTING THE COPILOTS IB SEAT RAIL WAS FOUND CRACKED.  THE CRACK WAS APPROX 2.5 INCH LONG AND WAS PERPENDICUL	AR TO THE SEAT RAIL.  THE CRACK WAS LOCATED AT THE AFT END OF THE SEAT RAIL.  DURING THE REPAIR, WE FOUND THE STIFFENER 	UNDERNEATH THE FLOOR, PN 04102362 CRACKED IN THE WEB.  THIS STIFFENER WAS REPLACED.  THE AC HAD 9500 HOURS TT AND HAS BE	EN USED EXCLUSIVELY AS A TRAINER.  THE CRACK WAS FOUND DURING A 100 HOUR INSPECTION.  (K)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005122800069	20051228	00069	SO  	2005	12	28	2005FA0001603    	2	20051123	G	8530	64193110	BOLT            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 2 CYLINDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	4837A	828  				414A0101	519028			WHILE CHECKING RT ENGINE OVER FOR OIL LEAKS, FOUND NUT AND PART OF BOLT FROM TOP FORWARD NR 2 CYLINDER THRU BOLT LODGE B	Y OIL FILLER TUBE.  BREAK ON BOLT APPEARS TO BE OLD BY THE DARK COLOR.  REMOVAL OF CYLINDER NECESSARY TO REPLACE BOLT.  	(K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005122800098	20051228	00098	SO  	2005	12	28	2005FA0001604    	1	20051201	G	3213	4531405	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  										NLG	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05										PURCHASED 2 NEW NOSE LANDING GEAR CYLINDER ASSEMBLYS WITH INCORRECTLY MACHINED CENTER BORE.  THE BORE OF THE CYLINDERS I	S TOO SMALL AT THE TOP WHICH DOESN`T ALLOW UPPER GEARINGS FULL TRAVEL TO TOP OF CYLINDER.  THE COULD CAUSE BEARING TO FA	M IN BORE AND LANDING GEAR TO MALFUNCTION ON RETRACTION/ EXTENSION.  (K)				1	L	7	2 	3O				A20SO   					 
2005122800022	20051228	00022	EA  	2005	12	28	2005FA0001605    	2	20051129	G	7414		GEAR            			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					MAGNETO	BROKEN          	B			OLKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	451X				G03DA023	287911129	L2340940A			ONE MAGNETO DIST. GEAR HAD 1 TOOTH BROKEN OFF THE OTHER DIST YEAR HAD A 13 TOOTH SECTION BROKEN OFF.  SUSPECT THE ONE TO	OTH BROKE AND TOOK OUT SECOND GEAR TEETH, LT MAG STOPPED WORKING ON TAKEOFF AND PILOT RETURNED TO AIRPORT. RT MAG WORKED	 WITH 1 TOOTH MISSING.  CARBURETOR MAY HAVE CAUSED BACKFIRE.  CARB SENT IN FOR OVERHAUL AND CHECKED FOR LEAN MIXTURE. (K	)			1	L	7	1 	3O	3	O		2A13    	E295				 
2005122800100	20051228	00100	SO  	2005	12	28	2005FA0001606    	1	20050429	G	3230	1904300	DRAG LINK       			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	4001P	5545 				231476				DUE TO PREVIOUS FAILURE OF RT DRAG LINK, LT MAIN LANDING GEAR DRAG LINK WAS REMOVED, PAINT STRIPED AND INSPECTED WITH ZY	GLOW.  A SMALL CRACK WAS NOTED EXTENDING INTO A WELD IN THE SAME AREA THAT THE OTHER (RT MLG LINK) HAD BROKEN.  DRAG LIN	K WAS REPLACED WITH A NEW OEM PART AND GEAR SYSTEM CHECKED FOR RIG AND PROPER OPERATION.  THE AC HAD BEEN PAINTED RECEIN	TLY AND DETECTING A CRACK IN THIS AREA WOULD HAVE BEEN IMPOSSIBLE UNLESS THE LINK WAS STRIPPED AND ZYGLOW INSPECTED.  (K	)		1	L	7	2 	3O	3	O		1A10    	E274				 
2005122800101	20051228	00101	SO  	2005	12	28	2005FA0001608    	1	20050523	G	5100	40233	BOLT            	PIPER       		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					LINK ASSY	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	63790	4782 				277754117				BOLT BROKEN. (K)						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2005122800042	20051228	00042	EA  	2005	12	28	2005FA0001609    	2	20051202	G	7250	310427901	HOUSING         			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					POWER TURBINE	FAILED          	B			UTBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	108KU					LJ568	PCE24127			POWER TURBINE SHAFT HOUSING CRACKED AND BROKEN, PN 310427901.  (K)						1	L	7	2 	3T	3	T		3A20    	E4EA				 
2005122800001	20051228	00001	EU  	2005	12	28	2005FA0001610    	2	20050808	G	7200		ENGINE          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					RIGHT	MAKING METAL    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	515PL					1092	16309			INTERMITTENT FUEL QUANTITY INDICATION DISCREPANCY, IT WAS ALSO ELECTED TO HAVE TERMINATING ACTION OF AD COMPLIED  WITH B	Y SB (REPLACEMENT OF FUEL TUBES).  MAINT REMOVED TUBES FOR REPLACEMENT, THEY DISCOVERED SUBSTANTIAL AMOUNTS OF METAL SHA	VINGS HAD ACCUMULATED AGAINST THE INLET SCREENS OF THE HIGH-PRESSURE FUEL PUMPS ON BOTH ENGINE.  ALL FINDINGS WERE IMMED	IATELY FORWARDED TO MFG GUIDANCE.  FWD SAMPLE OF METAL TO TEST LAB FOR ANALYZE, JUDGEMENT ON WHERE METAL ORIGINATED, MET	AL WAS FROM AIRFRAME.  MFG RECOMMEND FUEL SYS COMPONENTS OF ENGINES DOWNSTREAM OF LOW PRESS FUEL FILTERS INSP AND OR REP	AIRED AS NECESSARY.	2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2005122800002	20051228	00002	EU  	2005	12	28	2005FA0001611    	2	20050808	G	7200		ENGINE          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  						MAKING METAL    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	515PL					1092	16308			AN INTERMITTENT FUEL QUANTITY INDICATION DISCREPANCY, IT WAS ALSO ELECTED TO HAVE THE TERMINATING ACTION OF AD COMPLIED 	WITH BY INCORPORATING SB, (REPLACEMENT OF FUEL TUBES).  WHEN REMOVED TUBES FOR REPLACEMENT THEY DISCOVERED SUBSTANTIAL A	MOUNTS OF METAL SHAVINGS HAD ACCUMULATED AGAINST THE INLET SCREENS OF HIGH PRESS FUEL PUMPS ON BOTH ENGINES.  FINDINGS W	ERE FWD TO MFG AND SAMPLE TO TEST LAB INDICATED METAL WAS CONSISTENT WITH AIRFRAME.  MFG RECOMMEND TO HAVE FUEL SYS COMP	ONENTS DOWNSTREAM OF LOW PRESSURE FUEL FILTERS INSPECTED AND OR REPAIRED AS NECESSARY.  REPAIRED ENGINE AND REINSTALLED.	  (K)	2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006010400088	20060104	00088	GL  	2006	1	4	2005FA0001612    	2	20051220	G	7230	E23051119	DIFFUSER        	ALLSN       	C30P        						ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	SEPARATED       	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	07		449  	449  		CAC90492		CAC90492			COMPRESSOR REPORTED STALLING. VERIFIED ON TEST CELL. UPON DISASSEMBLY DIFFUSER VANE RING WAS FOUND TO HAVE THE AFT STUD 	BAND (RING) SEPARATED FROM THE DIFFUSER ASSEMBLY BODY. DIFFUSER INSTALLED NEW AT LAST OVERHAUL 449.3 HOURS PRIOR.										3	U			E1GL				 
2006010500311	20060105	00311	CE  	2006	1	5	2005FA0001613    	1	20051209	G	2710		CONTROL CABLE   			BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	602FC	3050 				TC1624				AILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WA	S FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL E	ND. AREA IS VERY HARD TO INSPECT, AC MUST BE ON JACKS WITH GEAR PARTIALLY RETRACTED AND INNER GEAR DOORS OPEN TO SEE, AN	D STILL DIFFICULT TO SEE.			1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P920	 
2006010500312	20060105	00312	CE  	2006	1	5	2005FA0001614    	1	20051209	G	2710		CONTROL CABLE   			BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	602FC	3050 				TC1624				AILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WA	S FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL E	ND. AREA IS VERY HARD TO INSPECT, A/C MUST BE ON JACKS WITH GEAR PARTIALLY RETRACTED AND INNER GEAR DOORS OPEN TO SEE, A	ND STILL DIFFICULT TO SEE.			1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P920	 
2006010500313	20060105	00313	CE  	2006	1	5	2005FA0001615    	1	20051209	G	2710		CONTROL CABLE   			BEECH 	55    	95B55A      	       	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	602FC	3050 				TC1624				AILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WA	S FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL E	ND. AREA IS VERY HARD TO INSPECT, A/C MUST BE ON JACKS WITH GEAR PARTIALLY RETRACTED AND INNER GEAR DOORS OPEN TO SEE, A	ND STILL DIFFICULT TO SEE.			1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P920	 
2005122800030	20051228	00030	CE  	2005	12	28	2005FA0001616    	1	20051209	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	INTERMITTENT    	D			VJ3R	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	1565A	171  				CE1331				PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE DOWN POSITION THE GEAR WOULDN`T EXTEND, AFTER CYCLING GEAR SELECTO	R GEAR WENT DOWN, AC RETURNED TO BASE.  ON TROUBLESHOOTING THE MECHANIC SELECTED DOWN AND IT FAILED TO EXTEND, AFTER TAP	PING ON TOP OF RELAY THE GEAR WENT DOWN.  PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DAT	E CODE.  (K)			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2005122800024	20051228	00024	SO  	2005	12	28	2005FA0001617    	1	20051216	G	5343		NUT PLATE       	PIPER       		PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	MLG TRUNNION	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	191BC					28R7435088	RL895251A	DY3439A		AFTER REMOVING THE RT FUEL TANK FOR REPAIR, IT WAS DISCOVERED THAT ALL 4 NUTPLATES THAT HOLD THE FWD MLG TRUNNION BOLTS 	WERE CRACKED.  THE LOWER IB NUTPLATE WAS CRACKED VERTICALLY DOWN THE THREADS.  THE REMAINING 3 NUTPLATES WERE CRACKED IN	 THE RIVET TABS.  THE AC IS A TRAINING AC THAT SEES ITS SHARE OF HARD LANDINGS.  PROBABLE CAUSE IS FATIGUE FROM REPEATED	 NOT SO SOFT LANDINGS.  THE LT FUEL TANK WAS REMOVED AS WELL TO INSPECT THE LT MAIN LANDING GEAR TRUNNION NUTPLATES.  NO	 CRACKS WERE FOUND ON THE LT SIDE.  PERIODIC INSPECTIONS MAY BE REQUIRED TO ENSURE THE NUTPLATES ARE SERVICEABLE.  (K)		1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P25EA	 
2006010600091	20060106	00091	SO  	2006	1	6	2005FA0001618    	2	20051215	G	7414		DISTRIBUTOR GEAR	BENDIX      		DHAV  	DHC2  	DHC2*       	2800108	EA  	CONT  	O520  	GTSIO520N   	17032	SO  					MAGNETO	DISINTEGRATED   	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	99	2740	109  			F081746	579				DURING CRUISE LT ENGINE BEGAN TO RUN ROUGH.  MAINTENANCE TRACED PROBLEM TO LT MAG.  UPON OPENING THE MAGNETO, DISCOVERED	 THE DISTRIBUTOR GEAR MISSING 98 PERCENT OF ITS TEETH WITH MANY BROKEN PIECES AND SHAVINGS INSIDE THE MAG.  THE DISTRIBU	TOR GEAR BUSHING IS LOOSE INSIDE THE DISTRIBUTOR BLOCK.  THIS MAGNETO OVERHAULED.				1	H	7	1 	3R	3	O		A806    	E7CE				 
2005122700187	20051227	00187	SO  	2005	12	27	2005FA0001619    	2	20051222	G	8520	653129	CRANKSHAFT      								CONT  	O360  	IO360ES     		SO  					ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23							357267			ENGINE HAD A PROPELLER STRIKE INSPECTION WITH NO DAMAGE FOUND TO CRANKSHAFT.  ENGINE WAS PUT BACK INTO SERVICE, CRANKSHA	FT DEVELOPED A CRACK IN THE PROPELLER FLANGE.  CRACK PROPAGATED FROM A SUBSURFACE DEFECT THAT WAS UNDECTED BY MAGNETIC P	ARTICLE INSPECTION.									3	O			E1CE				 
2005122800031	20051228	00031	CE  	2005	12	28	2005FA0001620    	1	20051202	G	2820	00292000049	TUBE            			BEECH 	58    	58          	1152740	CE  										FUEL SYSTEM	CHAFED          	B			E81R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	200KH					TH2102				WHILE RETRACTING AND EXTUENDING LANDING GEAR FOR ADJUSTMENT OF DROOPING IB MAIN WHEEL DOOR NOTED ABNORMAL NOISE AND VIBR	ATION DURING APPROXIAMTE MID-TRAVEL.  INVESTIGATED FURTHER, FOUND RT MLG RETRACT ROD ASSY.  CHAFING ON PN 002-920000-49 	AND PN 002-920000-51 RT WHEEL WELL FUEL CROSSFEED TUBES. VISUALLY INSPECTED FUEL TUBE ASSY.  FOUND CHAFING ON EXTERIOR N	EGLIGIBLE.  REPOSITIONED AND SECURED FUEL TUBES AS REQUIRED FOR CLEARANCE WITH RETRACT ROD DURING RETRACT/EXTENSION OPER	ATIONS.  RECOMMEND 1-TIME INSP OF AREA; IF NOT NOTICED EARLY COULD RESULT IN CHAF-THROUGH AND SUBSEQUENT FUEL LEAKAGE.  	(K)	1	L	7	2 	3O				3A16    					 
2005122800035	20051228	00035	CE  	2005	12	28	2005FA0001621    	1	20051201	G	2700		CONTROL CABLE   			BEECH 	200   	B200        	1152922	CE  										FLT CONTROLS	OUT OF RIG      	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	351CB					BB1889				DURING INSPECTION OF FLIGHT CONTROL SYSTEM, DURING INITIAL 200 HOUR PHASE 1 INSPECTION, IAW SAFETY COMMUNIQUE NR 265, FO	UND RUDDER CABLE TENSIONS, RUDDER TAB CABLE TENSIONS, AND ELEVATOR TAB CABLE TENSIONS BELOW APPLICABLE MM SERVICE LIMITS	.  NO OTHER FAULTS NOTED.  A MANDATORY SB IS IN THE PROCESS OF BEING ISSUED ON THIS SUBJECT IAW THE TEXT OF SAFETY COMMU	NIQUE NR 265.  (K)			1	L	7	2 	4T				A24CE   					 
2005122800023	20051228	00023	SO  	2005	12	28	2005FA0001622    	1	20051122	G	3260	451848	DOWNLOCK SWITCH 			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG	BROKEN          	B			EL6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	39503					32R7885224				UPON ARRIVING AT DESTINATION GEAR WAS SELECTED DOWN.  NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE AND IN TRANSIT  LIGHT STA	YED ON.  INSPECTED AND FOUND NOSE GEAR DOWNLOCK SWITCH ACTUATING ARM BROKEN OFF.  DETERMINED CAUSE OF BREAKING WAS TIME 	IN SERVICE AND WORK HARDING OF METAL ARM, SUGGEST TIME LIMITED INTERVAL FOR REPLACING.  (K)				1	L	7	1 	3O	3	O		A3SO    	1E4				 
2005122800067	20051228	00067	CE  	2005	12	28	2005FA0001623    	1	20051107	G	5343	20130035	BRACKET         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NLG ACTUATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	7557V	3675 				177RG0853				WHILE ATTEMPTING TO RIGG THE NOSE GEAR AFTER DOING AN ENGINE AND MOUNT OVERHAUL, IT WAS IMPOSSIBLE TO MAINTAIN THE PROPE	R CLEARANCES AND THE LOCK WOULD NOT SNAP OVER CENTER ON THE DOWN CYCLE.  WHILE WATCHING THE ACTUATOR IT SEEMED THE MOVE.	  UPON FURTHER INSPECTION AT THE UPPER ATTACH POINT (USING A BRIGHT LIGHT) THE BRACKET ASSY WAS FOUND TO BE SEVERLY CRAC	KED.  WOULD RECOMMEND CLOSE VISUAL INSPECTION AT EACH ANNUAL.  (K)			1	H	7	1 	3O	3	O		A20CE   	1E10				 
2006010300198	20060103	00198	CE  	2006	1	3	2005FA0001624    	1	20051027	G	3230	13137825CL	LINK            			BEECH 	200   	200BEECH    	1152920	CE  										MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	71RG					BB443				LINK IN LANDING GEAR EXTENSION CHAIN WAS FOUND BROKEN AND IN THE BELLY OF THE AIRCRAFT.  THIS BRAKAGE PREVENTED THE EXTE	NSION OF THE NOSE GEAR.  (K)					1	L	7	2 	4T				A24CE   					 
2006010300186	20060103	00186	CE  	2006	1	3	2005FA0001625    	1	20051123	G	2435	230801902	BRUSHES         			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	WORN            	B			BUER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	53MS		365  		YO1230	RK64				1,000 HOUR OVERHAUL OF BOTH STARTER-GENERATORS BRUSHES WORN.  REINSTALLED AFTER OVERHAUL.  (K)						2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2006010300195	20060103	00195	CE  	2006	1	3	2005FA0001626    	1	20051123	G	2435	230801902	BRUSHES         	LUCAS       		BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	WORN            	B			BUER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	53MS		365  		Y01231	RK64				1000 HOUR OVERHAUL OF BOTH STARTER-GENERATORS, REINSTALLED AFTER OVERHAUL.  (K)						2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2006010300187	20060103	00187	SW  	2006	1	3	2005FA0001627    	1	20051206	G	5100	474502524	LINK            			BELL  	47    	47G5        	1181032	SW  	ALLSN 	250B  	250B*       	 	GL  					UNKNOWN	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	2251W					7965				CRACK INDICATION REVEALED TRANSVERSE BETWEEN HOLES.  INSPECTION METHOD:  FLOURESCENT PENETRANT.  (K)						1	G	7	1 	3O	3	T		2H3     	E10CE				 
2006010300190	20060103	00190	SW  	2006	1	3	2005FA0001628    	1	20051206	G	6700	TTB21032	SLEEVE          			BELL  	47    	47G5        	1181032	SW  	ALLSN 	250B  	250B*       	 	GL  					COLLECTIVE PITCH	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	2251W					7965				CRACK INDICATION REVEALED AT WELD TO TUBE SLEEVE.  INSPECTION METHOD: FLUORESCENT MAGNETIC PARTICLE.  (K)						1	G	7	1 	3O	3	T		2H3     	E10CE				 
2006010300191	20060103	00191	SW  	2006	1	3	2005FA0001629    	1	20051206	G	5100	471202523	GRIP            			BELL  	47    	47G5        	1181032	SW  	ALLSN 	250B  	250B*       	 	GL  					UNKNOWN	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	2251W					7965				CRACK INDICATION REVEALED AT THE 8TH THREAD IB FROM END.  INSPECTION METHOD:  EDDY CURRENT. (K)						1	G	7	1 	3O	3	T		2H3     	E10CE				 
2006010300185	20060103	00185	SO  	2006	1	3	2005FA0001630    	1	20051107	G	2810	DC1084924G32L	FUEL TANK       			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					LEFT	LEAKING         	B			WWKR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	03	2880P	613  				184477				LT FUEL TANK WAS LEAKING.  PILOT ADVISED US OF LEAK.  WE DRAINED BOTH TANKS AND TURNED THEM INTO REP.  THEY ADVISED US T	HERE WAS AS/L ON BOTH TANKS.  WERE REMOVED AND SENT IN TO MFG FOR REPAIR AND APPROVAL.  (K)					1	H	7	1 	3O	3	O		1A2     	E274				 
2006010300189	20060103	00189	CE  	2006	1	3	2005FA0001631    	1	20051014	G	5720	052323124	SUPPORT BRACKET 			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					WING TE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	54844	11427				17275065				WING T/E SKIN SUPPT BRACKET CRACKED IN BEND RADIUS.  LOCATION OF CRACKED PART IS IB SIDE OF RT FLAP TRACK RIB AT STA 39.	  PART HAS .2500 INCH CRACK FROM L/E OF TAB AFT, ANOTHER CRACK IN SAME BEND RADIUS .7500 INCH FROM T/E OF TAB FWD.  BEND	 RADIUS CRACK IS UNDER EXCESSIVE STRESSES.  DEFLECTED DOWN AS VIEW FROM FRONT OF AC FACING AFT, T/E WING SKIN MAKES A SI	GNIFICANT INCREASE IN ITS CURVE AFT OF LAST TAB ATTACHING RIVET AS VIEW FROM OB EDGE OF SKIN LOOKING THROUGH FLAP TRACK 	SLOT.  VERY LITTLE CLEARANCE BETWEEN THESE BRACKETS AND FLAP SUPPT RAILS.  CRACK IN OR EXCESSIVE DEFORMATION CAN CAUSE T	HE FLAP SUPPT RAILS TO GRAB BRACKET UPON RETRACTION, RESULTING IN FAILURE OF FLAP, POSSIBLE LOSS OF CONTROL OF AC.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006010300209	20060103	00209	SO  	2006	1	3	2005FA0001632    	1	20050831	G	3220	3200	TAIL WHEEL      			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					MLG	WORN            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	1829P					222609				PILOT REPORTED SEVERE TAILWHEEL SHIMMY DURING LANDING ROLLOUT LEADING TO LOSS OF CONTROL AND GROUND LOOP WITH SIGNIFICAN	T DAMAGE TO AIRCRAFT.  POST ACCIDENT INSP FOUND PLAY IN THE ALUMINUM SPACER BETWEEN THE TAILWHEEL ASSY AND THE TAILWHEEL	 SPRING.  ALSO, THERE WAS LITTLE RESISTANCE TO TURNING THE WHEEL OUT OF THE STRAIGHT FORWARD POSITION.  SOME EXTERNAL DA	MAGE HAD OCCURRED TO THE TAILWHEEL ASSY DURINT THE GROUND LOOP.  RECOMMENDED THAT WEIGHT BE REMOVED FROM THE TAILWHEEL A	SSY DURING INSPECTIONS TO DETERMINE THE TRUE INTERNAL CONDITION AS WELL AS THE MOUNTING ADAPTER CONDITION AND THE TAILWH	EEL PIVOT AXIS GEOMETRY BE INSPECTED IAW MM.  (K)	1	H	7	1 	3O	3	O		1A6     	E274				 
2006010300203	20060103	00203	EA  	2006	1	3	2005FA0001633    	1	20051115	G	5340	612826	MOUNT           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985*       	52008	NE  					ADC	CRACKED         	B			HJBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	60077	1861 				1419				DURING THE REPLACEMENT OF THE AIR DATA COMPUTER.  FOUND THE MOUNTING TRAY ASSY CRACKED COMPLETELY ACROSS ON THE OPPOSITE	 END OF THE THUMBSCREW.  AIRCRAFT IS CONFIGURED ON AMPHIBIAN FLOATS.  (K)					1	H	7	1 	3R	3	R		A806    	5E1				 
2006010400087	20060104	00087	SO  	2006	1	4	2005FA0001634    	2	20051222	G	8520	653129	CRANKSHAFT      								CONT  	O360  	IO360ES     		SO  					ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23							357267			ENGINE WAS INVOLVED IN A PROPELLER STRIKE, NO CRANKSHAFT DAMAGE WAS FOUND AT THAT TIME.  ENGINE WAS RETURNED TO SERVICE 	AND A CRACK DEVELOPED IN THE CRANKSHAFT FLANGE, CRANKSHAFT WAS REMOVED FROM THE ENGINE. THE CRACK MOST LIKELY ORIGINATED	 FROM A SUBSURFACE DEFECT THAT WAS NOT DETECTIBLE WITH MAG PARTICLE INSPECTION.									3	O			E1CE				 
2006010500151	20060105	00151	SO  	2006	1	5	2005FA0001635    	2	20051220	G	8520	IO520F	CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					ENGINE	FAILED          	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03			1798 				814752			LT CRANKCASE MAIN BEARING SADDLE FAILURE.  THIS ENGINE MADE IT TO TBO BUT WASN`T GOING TO GO VERY MUCH LONGER.  (K)											3	O			E5CE				 
2006010500159	20060105	00159	CE  	2006	1	5	2005FA0001636    	1	20051216	G	7160	CPE1173	FILTER          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					INDUCTION	FAILED          	B			DYTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	78JA	293  				17280622	L2997051A			THIS IS AN INDUCTION AIR FILTER BEARING.  REMOVED 5 OF THESE FILTERS FROM SERVICE IN ADDITION TO THE ONE IN THIS REPORT 	WITH THE SAME DAMAGE SIMILAR TIME IN SERVICE.  THE WIRE MESH THAT ENCLOSES THE COTTON FIBER FILTER MATERIAL IS TEARING A	ND EXPOSING THE FILTER MIATERIAL.. SOME OF THE WIRE MESH AND FILTER MATERIAL IS MISSING, ASSUMED TO HAVE BEEN INGESTED B	Y THE ENGINE.  MFG FILTERS CURRENTLY ELIMINATE THE REQUIREMENTS SET FORTH IN AD84-26-02 DEALING WITH INGESTION OF PAPER 	AIR FILTERS.  JUDGING BY THE RESULTS SEEN FROM THIS AND THE OTHER FILTERS REMOVED FROM SERVICE, THESE FILTERS POSE A GRE	ATER RISK OF INGESTION AND ENGINE FAILURE THAN PAPER FILTERS.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006010400103	20060104	00103	GL  	2006	1	4	2005FA0001637    	2	20051116	G	7261	206061505109	OIL TANK        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					ENGINE	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	01	2009C	3541 				45678				206-061-505-109 ENGINE OIL RESERVOIR BEGAN TO LEAK ENGINE OIL.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006010400104	20060104	00104	GL  	2006	1	4	2005FA0001638    	2	20051116	G	7261	206061505109	OIL TANK        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					ZONE 200	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	01	2009C	3541 				45678				206-061-505-109 ENGINE OIL RESERVOIR BEGAN TO LEAK ENGINE OIL						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006010600058	20060106	00058	EA  	2006	1	6	2005FA0001639    	2	20050806	G	7421	REM40E	SPARK PLUG      			PIPER 	PA18  	PA18A150    	7101837	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	DEFECTIVE       	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			GL	15	6983B					185105				AIRCRAFT LOST POWER WHILE TAKING OFF WITH GLIDER IN TOW. GLIDER WAS RELEASED AND WAS DAMAGED DURING LANDING IN PASTURE. 	AIRCRAFT RETURNED TO AIRPORT AND LANDED. TWO SPARK PLUGS ON NR 2 CYLINDER WERE COLD. ALL EIGHT SPARK PLUGS WERE REPLACED	.				1	H	7	1 	3O	3	O		1A2     	E274				 
2006012400201	20060124	00201	NE  	2006	1	24	2005FA0001640    	2	20051229	G	7321	0164248850	FCU             	TMECA       	ARRIEL1D1   	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	UNCONTROLLABLE  	B				E				ENGINE SHUTDOWN         				O			OTHER                     			TO	TAKEOFF        	1			SW	01	6098U	2230 	2230 		9280	2718	9280			FCU WOULD NOT GOVERN ENGINE FROM START.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006012500002	20060125	00002	NE  	2006	1	25	2005FA0001641    	2	20051229	G	7321	0164248850	FCU             	TMECA       	ARRIEL1D1   	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	UNCONTROLLABLE  	B				E				ENGINE SHUTDOWN         				O			OTHER                     			TO	TAKEOFF        	1			SW	01	6103X	4669 	969  		9442	2723	9442			FCU WOULD NOT GOVERN ENGINE AT GROUND IDLE.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006020300126	20060203	00126	CE  	2006	2	3	2005FA0001642    	1	20051208	G	8011	MZ4218	STARTER         			BEECH 	23    	A23         	1151204	CE  	LYC   	O320  	IO320A2B    		EA  					ENGINE	FAILED          	C				K				NONE                    				O	S		OTHER                     	AFFECT SYSTEMS            		IN	INSP/MAINT     	1			EA	23							L518951A			STARTER BENDIX FAILED, DAMAGED STARTER SHAFT, DAMAGED TEETH ON RING GEAR SUPPORT.						1	L	7	1 	3O	3	O		A1CE    	1E12				 
2006010500173	20060105	00173	CE  	2006	1	5	2005FA0001643    	1	20051206	G	2150	JBS2402	RESISTOR        			CESSNA	500   	S550        	2076607	CE  										BLOWER ASSY	BURNED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	22HP					S5500103				PILOT REPORTED FREON AIR CONDITIONING SYSTEM CIRCUIT BREAKER TRIPPED WHEN SYSTEM TURNED ON.  FOUND AFT EVAPORATOR BLOWER	 INOPERATIVE IN LOW POSITION, EXCESSIVELY NOISY IN HIGH POSITION.  REMOVED FLOORBOARD FOR INVESTIGATION, FOUND BLOWER MO	TOR RESISTOR ASSY.  BURNED AND ADJACENT PLASTIC BLOWER MOTOR HOUSING MELTED.  FREON AIR CONDITIONING SYSTEM INSTALLED UN	DER STC SA2698SW, 809.7 HOURS PREVIOUSLY, NO RECORD OF COMPONENT REPLACEMENTS SINCE INSTALLED.  REPLACED BLOWER ASSY AND	 RESISTOR, OPS CHECKS SATISFACTORY. (K)		1	L	7	2 	4F			RT	A22CE   					 
2006010500172	20060105	00172	CE  	2006	1	5	2005FA0001644    	1	20051207	G	2720	1015240174	SUPPORT         			BEECH 	200   	B200        	1152922	CE  										RUDDER	MISINSTALLED    	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	912JS	369  				BB1845				OPERATOR NOTED (2) NON-STANDARD RIVETS INSTALLED ATTACHING THE PN 101-524017-4 RT RUDDER MECHANISM SUPPORT BRACKET ANGLE	 TO THE FS 437.234 CANTED BULKHEAD.  DURING RIVET REPLACEMENT FOUND THAT IB RIVET HAD FORMED A SHOP HEAD BETWEEN THE BUL	KHEAD AND SUPPORT ANGLE DUE TO A MOUNTING GAP.  (K)				1	L	7	2 	4T				A24CE   					 
2006012400200	20060124	00200	CE  	2006	1	24	2005FA0001645    	1	20051229	G	7700	400510	PROBE           		EDM800C     	CESSNA	210   	T210M       	2073451	CE  										AIR TEMP PROBE	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	15		25   			22386	21061879				OUTSIDE AIR TEMP PROBE FAILED SELF TEST INDICATING OPEN.						1	H	7	1 	3O				3A21    					 
2006011300173	20060113	00173	GL  	2006	1	13	2005FA0001646    	1	20051220	G	3220		ROLL PIN        			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					NOSE STRUT	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	922AF					C0179				ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-0	1) HAD WORKED OUT UNLOCKING THE ASSY.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006011300174	20060113	00174	GL  	2006	1	13	2005FA0001647    	1	20051220	G	3220		ROLL PIN        			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					NOSE GEAR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	915AF					C0149				ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-0	1) HAD WORKED OUT UNLOCKING THE ASSY.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006012400199	20060124	00199	EU  	2006	1	24	2005FA0001648    	1	20051229	G	5711	14101B1	SPAR CAP        	PARTEN      		PARTEN	P68   	P68CTC      	6780106	EU  	LYC   	O360  	TO360A1A6   	41514	EA  					RT WING	CORRODED        	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	775MW	2414 				20801				SEVERE INTERGRANULAR CORROSION OF MAIN WING SPAR WEB AND UPPER SPAR CAP AFT OF ENGINE FIREWALL.  REQUIRES REMOVAL OF ENG	INE, ENGINE MOUNT, FIREWALL.  SUSPECT SOURCE OF CORROSION TO BE FIRE SHEATH INSTALLED OVER FUEL LINES BEHIND FIREWALL.  	SB 61 ADDRESSES INSPECTION OF FUEL LINES AND REMOVAL OF FIRE SHEATHING, WITH CORRESPONDING INSPECTION FOR SPAR CORROSION	.  BULLETIN IS MISLEADING, DOES NOT PLACE EMPHASIS ON SPAR. WING SPAR IS UNAIRWORTHY, FACTORY AND DER CONTACTED FOR POSS	IBLE REPAIR.  RECOMMEND AD FOR THIS CONDITION.		1	H	7	2 	3O	3	O		A31EU   	E26EA				 
2006010600096	20060106	00096	CE  	2006	1	6	2005FA0001649    	1	20051219	G	3242	1013800961	BRAKE           	BEECH       		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG	DRAGGING        	C				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			GL	19	981LL	286  	286  		769B99	FL265				ON TAKEOFF ROLL, BRAKES APPEARED TO BE DRAGGING. CREW DECIDED TO ABORT TAKEOFF W/O INCIDENT AND TAXIED BACK TO GATE.  MA	INT JACKED AC AND CHECKED BRAKES. BRAKES APPEARED TO BE DRAGGING AND NOT RELEASING ALL THE WAY.  THESE ARE UNMODIFIED BR	AKES (W/O STAINLESS STEEL SLEEVES) CHANGED ALL BRAKES AND THE AC IS BACK ON FLIGHT LINE.  SUSPECT THAT REASON FOR BRAKES	 DRAGGING ARE UNMODIFIED BRAKES. THESE WILL BE SENT OUT FOR O/H AND MODIFICATION. THIS PROCESS IS RECOMMENDED BY MFG FOR	 CORROSION IN THE PUCK AREA.  IN THE PROCESS OF CHANGING ALL OF THE BRAKES FLEET WIDE TO THE MODIFIED BRAKES TO HELP ELI	MINATE THIS PROBLEM.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005092300150	20050923	00150	CE  	2005	9	23	2005FAA09001     	1	20050922	G	2434	ALV9510R	ALTERNATOR      			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	DISLODGED       	D				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			NM	11	404B		21   			0676	608093	880921		THE ALTERNATOR, OVERHAULED UNIT, WAS IN PIECES WHEN THE AIRCRAFT LANDED.  THE BACK HALF OF THE ALTERNATOR WAS OFF, THE S	TATOR WAS CHEWED UP.  THE END BEARINGS WERE IN PLACE AND TURNED LIKE A NEW BEARING WITH GREASE IN THEM.					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
2005070600041	20050706	00041		2005	7	6	2005R0124        	4	20050628	G	3416	066306403	ALTIMETER       			CESSNA	210   	T210M       	2073451	CE  										COCKPIT	BINDS           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	732XE					61850				ALTIMETER HANDS ARE BENT & INTERFERE WITH EACH OTHER.						1	H	7	1 	3O				3A21    					 
2005120200115	20051202	00115	EA  	2005	12	2	2005WP09I021     	2	20050718	G	8530		CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	G				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			WP	09	2525Y	1100 				288516075	RL1763939A			DURING APPROACH FOR LANDING (TOUCH AND GO'S), ONE OF THE CYLINDER HEADS BLEW OFF AND THERE WAS A SUDDEN REDUCTION OF POW	ER.  THE AIRCRAFT LANDED SAFELY WITHOUT DAMAGE OR INJURIES.  THE CYLINDER WAS A NEW PMA CYLINDER WITH APPROX. 1100 HOURS	 TIME IN SERVICE. THE CAUSE OF THE FAILURE IS CURRENTLY UNDER INVESTIGATION BY THE NTSB.				1	L	7	1 	3O	3	O		2A13    	E274				 
2006010500204	20060105	00204	CE  	2006	1	5	2006FA0000000    	1	20051221	G	3244	184F135	TIRE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D1      	52060	NE  					MLG	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	94LH	28   				RK112				REPLACED THE FRONT TIRE, WITH THIS NEW TIRE AND HAVE HAD A SLOW LEAK EVER SINCE.  TOOK THE TIRE BACK OFF AND SUBMERGED T	HE TIRE AND WHEEL UNDER WATER, FOUND 10 VERY SMALL PINHOLES IN THE TIRE SIDEWALL CLOSE TO THE RIM EQUALLY SPACED AROUND 	THE SIDEWALL, THE PINHOLES WERE IN THE TIRE FROM THE FACTORY AND NOT DUE TO ANY DAMAGE INSTALLING IT OR WHILE ON THE AIR	CRAFT.  SIZE OF TIRE IS 18 X 4.4, LOAD RATING 3550 LBS, 10 PLY.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2006010500128	20060105	00128	SO  	2006	1	5	2006FA0000001    	2	20051220	G	8530		ROCKER          			CESSNA	150   	150K        	2071822	CE  	CONT  	O200  	O200A       	17020	SO  					ENG CYLINDER	BROKEN          	G				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CE	07	6424G	3509 	883  			15071924	72KABNA48			AIRCRAFT IN CRUISE FLIGHT AT 2200 FT, ENGINE BEGAN TO RUN ROUGH.  PILOT DECLARED AND EMERGENCY AND LANDED AT AIRPORT.  A	FTER LANDING THE VALVE COVER WAS REMOVED FROM THE NR 2 CYLINDER AND IT WAS DISCOVERED THAT ALL 3 BOSSES FOR THE VALVE RO	CKER SHAFTS HAD BROKEN.  (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2006012400135	20060124	00135		2006	1	24	2006FA0000005    	4	20051214	G	6113	05522311	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24322	197  				17280866				DURING 100 HR INSPECTION, THE FORWARD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AROUND 3 OF THE 6 BOLT HOLES.  CAUSE OF T	HE PROBLEM IS THAT WHEN THE PROP MOUNTING BOLTS ARE TORQUED TO THE LIMITS GIVEN IN THE SRM THAT THE FWD BULKHEAD GETS PU	LLED DOWN SLIGHTLY INTO THE CHAMFER OF THE PROP BOLT HOLES AND THIS IN TURN STRESSES THE PART LEADING EDGE TO CRACKING. 	 TO SOLVE THIS PROBLEM, THE TORQUE OF THE MOUNTING BOLTS AND THE DESIGN OF THE BULKHEAD NEED TO BE EVALUATED AND CHANGES	 MADE.  (K)		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006012400126	20060124	00126	CE  	2006	1	24	2006FA0000006    	1	20051208	G	5100	583801091	VALVE           			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					UNKNOWN	OUT OF RIG      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	2347G					TH1867				THE NEW VALVE RECEIVED FROM THE MFG WAS INTERNALLY CLOCKED INCORRECTLY.  AFTER INSTALLATION, NO FUEL WAS AVAILABLE FROM 	EITHER THE ON OR CROSSFEED PORTS.  AFTER MALVE REMOVAL, IT WAS CONFIRMED THAT THE VALVE REMAINED IN THE OFF POSITION REG	ARDLESS OF MOVMENT TO ANY OF THE 3 AVAILABLE POSITIONS.  A NEW VALVE WAS ORDERED AND IT WORKED CORRECTLY.  (K)				1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006013100218	20060131	00218	CE  	2006	1	31	2006FA0000007    	1	20051212	G	3060	P6592SW	BOOT            	MCAULY      		CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					NR 3 BLADE	FAILED          	B			LT4R	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SO	19	414SH	393  			950618	414A0470				BOOT PN P6592SW DEPARTED PROPELLER BLADE IN FLIGHT.  CUSTOMER LANDED, REMOVED OTHER BOOTS AND CONTINUED TRIP TO HOME STA	TION.  BOOTS HAVE 393.6 HOURS SINCE INSTALLATION.  AD NOTE 2005-18-20 INSPECTION WAS ACCOMPLISHED WITH NO DEFECTS NOTED.	  (K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2006012400134	20060124	00134	SO  	2006	1	24	2006FA0000008    	2	20051221	G	8530		EXHAUST VALVE   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	STUCK           	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	4676U	376  				U20604352	812282R			THE EXHAUST VALVE GUIDE HAD .0035 INCH OF BUILD UP MATERIAL, CAUSING THE VALVE TO STICK OPEN, WHERE IT STRUCK THE PISTON	.  POSSIBLY DUE TO RICH MIXTURE.  (K)					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006012400165	20060124	00165	CE  	2006	1	24	2006FA0000009    	1	20051213	G	5700	05232333	STRIP           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT WING	UNSERVICEABLE   	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	2173Z	937  				17281216				DURING ANNUAL INSPECTION, WHILE INSPECTING THE AILERON CABLES, FOUND A FLAT SPOT ON THE LT AILERON CROSSOVER CABLE AT TH	E AILERON CABLE ABRASION STRIP ATTACHED TO  A RIB ASSY LOCATED AT WING STA 71.19.  FURTHER INVESTIGATION FOUND THE CABLE	 BEGINING TO FRAY.  THE CAUSE IS THE CABLE WEARING ON THE ABRASION STRIP.  TO SOLVE THIS PROBLEM, THE ABRASION STRIP BE 	LOWERED OR A PULLEY INSTALLED.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006012400140	20060124	00140	CE  	2006	1	24	2006FA0000010    	1	20051213	G	2810		FITTING         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					RESERVOIR	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01	686SP	1226 			337836	172S8097				DURING AN ANNUAL INSPECTION, FUEL STAINING WAS NOTED AT AND BELOW THE WELD TO THE INLET FITTING.  THE UNIT WAS REMOVED F	ROM AIRCRAFT AND INSPECTED.  A LEAK WAS LOCATED IN THE WELD.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006012400141	20060124	00141		2006	1	24	2006FA0000011    	1	20051115	G	2820	23056E60	VALVE           																	FUEL CROSSFEED	LEAKING         	D			PRZR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	11										PART WAS RECEIVED TO REPLACE EXISTING PART DUE TIME CHANGE.  WHEN PART WAS INSTALLED, PART FUNCTIONED FINE.  WHEN FUEL W	AS INTRODUCED TO SYSTEM FOR LEAK CHECK, UNIT WAS FOUND TO NOT HOLD SEAL.  THIS IS THE FIRST OF 2 VALVES FROM THE SAME FA	CILITY THAT HAVE LEAKED WHEN INSTALLED ON AIRCRAFT.  FUEL CROSSFEED VALVE.  (K)																	 
2006012300230	20060123	00230	CE  	2006	1	23	2006FA0000012    	1	20051110	G	5511		SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					STABILIZER	CRACKED         	D			M9OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	24831	8207 				15280403				ON ROUTING 100 HR INSPECTION FOUND CRACK ON HORIZONTAL STABILIZER FRONT APEK, LOWER ANGLE PN 0432001-37 AND REINFORCEMEN	T PLATE PN 0432001-44, 1 LOWER SKIN RIVET SEAM FRETTED AND LOOSE.  UPON REMOVAL AND DISASSEMBLY DISCOVERED CRACKED SKIN 	(PN 0432001-55) AND CRACKED SPAR PN 0432001-56.  NOTE: THIS IS AN EARLIER SN AC WHICH APPARENTLY DID NOT HAVE REINFORCEM	ENT ANGLE PN 0432007-3 AS INSTALLED ON LATER SN`S.  THIS AC ALSO HAS A CONVERSION TO TAILWHEEL AND HAS SPENT A PORTION O	F ITS TT AS A TAILWHEEL.  (K)		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006012500124	20060125	00124	EA  	2006	1	25	2006FA0000013    	2	20051228	G	7414	M3163	IMPULSE COUPLING	SLICK       		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					MAGNETO	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	739XK					17270887				DURING 500 HOUR MAG AND IMPULSE COUPLING INSPECTION FOUND ONE IMPULSE COUPLING PAWL RETAINING RIVET VERY LOOSE IN IMPULS	E HOUSING.  NO DAMAGE NOTED.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006012300227	20060123	00227	CE  	2006	1	23	2006FA0000014    	1	20051112	G	3700	215CC	EXHAUST PIPE    			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1A    	41514	EA  					VACUUM PUMP	CORRODED        	D				K				NONE                    				D	S		INFLIGHT SEPARATION       	AFFECT SYSTEMS            		CR	CRUISE         	1			SO	07	18993		281  			MC550				EXHAUST PORT OF DRY AIR PUMP FELL OFF DURING FLIGHT AND LODGED IN LANDING GEAR RETRACTION SYSTEM.  AC HAD TO LAND NOSE G	EAR UP.  PIPE THREADS IN ALUMINUM PUMP HOUSING WERE WORN AND CORRODED.  SUGGESTED THAT FITTINGS BE INSPECTED FOR SECURIT	Y MORE FREQ THAN 100 HOUR/ANNUAL.  ALSO INDUSTRY SHOULD ALLOW PIPE DOPE COMPOUND ON EXHAUST FITTINGS SINCE INGESTION OF 	FOD WOULD NOT BE A FACTOR ON THE EXIT PORT. (K)			1	L	7	1 	3O	3	O		A1CE    	1E10				 
2006012400123	20060124	00123		2006	1	24	2006FA0000016    	1	20051228	G	2900		FLANGE          	DUNLOP      																SERVO ACTUATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					FJ383					CRACK DETECTED ON LOWER LEE PLUG FLANGE.  (K)																			 
2006012400122	20060124	00122		2006	1	24	2006FA0000017    	1	20050620	G	2824	23056EGD	VALVE           																	CROSSFEED	FAILED          	B			PRZR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11										PART WAS RECEIVED TO REPLACE EXISTING PART DUE TIME CHANGE.  WHEN PART WAS INSTALLED, PART FUNCTIONED FINE.  WHEN FUEL W	AS INTRODUCED TO THE SYSTEM FOR A LEAK CHECK, UNIT WAS FOUND TO NOT HOLD A SEAL.  THIS IS THE SECOND UNIT FROM SAME FACI	LITY THAT HAD THE SAME PROBLEM.  FUEL CROSSFEED VALVE.  WO NR 44103345  (K)																	 
2006012400163	20060124	00163	SO  	2006	1	24	2006FA0000020    	1	20051221	G	2840	50954000	CONDUIT         			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					FUEL SYSTEM	LEAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	234K	6359 				31T7520001				LT NACELLE TANK SENDER WAS LEAKING OUT OF TOP OF NACELLE. SENDER SCREWS HAD BEEN TIGHTENED AND GASKETS REPLACED BUT STIL	L LEAKED. TECH FOUND ALUMINUM CONDUIT THAT SENDER WIRING IS ROUTED THROUGH IN TANK TO HAVE APPROX 10-15 PINHOLES IN IT F	ROM CORRODING FROM THE INSIDE OF ALUMINUM CONDUIT. FUEL LEAKS INTO CONDUIT AND UP TO TOP OF SENDER THEN WOULD LEAK OUT T	OP AND DOWN/AFT ON NACELLE.			1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2006011800207	20060118	00207	CE  	2006	1	18	2006FA0000024    	1	20051103	G	2730	7627302026001	CABLE           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ELEV CNTRL CABLE	DAMAGED         	B			WVER	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	09	423FX					134				DURING THE INITIAL 5,000 HOUR CABLE INSPECTIONON THIS AIRCRAFT NOTED EXTENSIVE DAMAGE TO THE LOWER LEFT AFT ELEVATOR CON	TROL CABLE AND PRESSURIZATION SYSTEM VACUUM LINE WAS FOUND MISROUTED CAUSING DAMAGE TO THE ELEVATOR CONTROL CABLE AND VA	CCUM LINE.  ENGINEERING EVALUATE THE NEED FOR A ONE-TIME INSPECTION OF THIS AREA ON ALL LIKE AIRCRAFT WITH LESS THAN 5,0	00 ACCLUMATED FLIGHT HOURS.  (K)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006011800206	20060118	00206	CE  	2006	1	18	2006FA0000025    	1	20050930	G	2720		ANGLE           			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					RUDDER STOP	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	251FX					195				UPON REMOVAL OF RUDDER, TO REPAIR SKIN DAMAGE AT HINGE POINTS FOUND RUDDER SUPPORT STIFFENER ANGLE (PN 5412481-004) CRAC	KED UNDER RUDDER PRIMARY TRAVEL STOP AT FRAME STATION 48.  RUDDER OVER TRAVELING WHEN GUST LOCK NOT INSTALLED AND WHEN P	ARKED OUTSIDE IN WINDY CONDITIONS.  ENSURE FLIGHT CONTROL GUST LOCKS ARE INSTALLED WHEN PARKED OUTSIDE. (EA09200600885) 	(K)			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006011800205	20060118	00205	CE  	2006	1	18	2006FA0000026    	1	20051018	G	2720	4555401134009	TORQUE TUBE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RUDDER	CORRODED        	B			WVER	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	09	418FX					120				DURING 5,000 HOUR INSPECTION, THE RUDDER WAS REMOVED FOR S/B (REPAIR OF RUDDER TORQUE TUBE ASSY BONDING JUMPERS) FOUND C	ORROSION ON TORQUE TUBE INTERNAL AND EXTERNAL.  ON FURTHER INVESTIGATION (EDDY CURRENT INSP) A CRACK INDICATION WAS NOTE	D .020 INCH DEEP BY 1 INCH LONG.  TORQUE TUBE WAS REMOVED AND REPLACED.  PROBABLE CAUSE: MOISTURE INGRESSION THROUGH WIR	E BUNDLE HOLE.  ENGINEERING EVALUATE FOR POSSIBLE INTERNAL INSPECTION CRITERIA OF TORQUE TUBE AND ENVIRONMENTAL SEALING 	AS REQUIRED.  (K)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006011800204	20060118	00204	CE  	2006	1	18	2006FA0000027    	1	20051031	G	2720	4555401134009	TORQUE TUBE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RUDDER	CORRODED        	B			WVER	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	09	423FX					134				DURING 5,000 HR INSPECTION, THE RUDDER WAS REMOVED FOR SB, REPAIR OF (RUDDER TORQUE TUBE ASSY BONDING JUMPERS) FOUND COR	ROSION ON TORQUE TUBE INTERNAL AND EXTERNAL.  MOISTURE INGRESSION THROUGH WIRE BUNDLE HOLE.  ENGINEERING EVALUATE FOR PO	SSIBLE INTERNAL INSPECTION CRITERIA OF TORQUE TUBE AND ENVIRONMENTAL SEALING AS REQUIRED.  (EA09200600887) (K)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006011800202	20060118	00202	CE  	2006	1	18	2006FA0000028    	1	20051031	G	2720	4555401134009	TORQUE TUBE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RUDDER	CORRODED        	B			WVER	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	09	422FX					135				DURING 5,000 HOUR INSPECTION, THE RUDDER WAS REMOVED FOR SB (REPAIR OF RUDDER TORQUE TUBE ASSY BONDING JUMPERS) FOUND CO	RROSION ON TORQUE TUBE INTERNAL AND EXTERNAL.  MOISTURE INGRESSION THROUGH WIRE BUNDLE HOLE.  ENGINEERING EVALUATE FOR P	OSSIBLE INTERNAL INSPECTION CRITERIA OF TORQUE TUBE AND ENVIRONMENTA SEALING AS REQUIRED. (EA09200600888) (K)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006011800201	20060118	00201	SO  	2006	1	18	2006FA0000029    	2	20051206	G	7414		DISTRIBUTOR GEAR			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					LT MAGNETO	STRIPPED        	B			WC7R	O				OTHER                   				E			VIBRATION/BUFFET          			UK	UNKNOWN        	1			GL	25	421CQ				BL349460	421C1218				PILOT REPORTED LT ENGINE RUNNING ROUGH.  TROUBLESHOT PROBLEM TO LT MAGNETO.  FOUND TEETH ON DISTRIBUTOR GEAR IN LT MAGNE	TO STRIPPED AND NOT TURNING PROPERLY.  (GL25200605792) (K)					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006012600100	20060126	00100	EA  	2006	1	26	2006FA0000048    	2	20051230	G	8520		PLUG            			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540A1B   	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	CRANKSHAFT	DISLODGED       	B			RF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	22320					270297	L1054861A	001085		DURING PROP REMOVAL FOR A GROUND STRIKE, FOUND CRANKSHAFT WELSH PLUG LOGGED IN THE PROP HOUSING, RESTRICTING OIL FLOW TO	 PROP.  ENGINE HAD BEEN INSTALLED 30 DAYS EARLIER, 4 HOURS SINCE INSTALL.  (K)					1	L	7	1 	3O	3	O	RT	2A3     	E14EA	5	C	P58GL	 
2006012600092	20060126	00092	EU  	2006	1	26	2006FA0000049    	1	20051220	G	6320	109062087101	OIL COOLER      			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					TRANSMISSION	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	318PD					14039				OIL COOLER, TRANSMISSION SIDE OF COOLER CRACKED AND SPRAYED OIL BELOW ENGINE DECK.  (K)						1	G	7	2 	3U	3	T		H7EU    	E2NE				 
2006012600101	20060126	00101	GL  	2006	1	26	2006FA0000052    	3	20051123	G	6111	S90AT8	BLADE           			CESSNA	206   	P206        	2073304	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	PROPELLER	FRACTURED       	D				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			WP	07	2653X		1233 			P2060153	175293H	725446		PILOT TOOKOFF, DURING CRUISE FLIGHT, SEVERE VIBRATION OCCURRED FROM ENGINE.  ENGINE PULLS BACK TO IDLE AND EMERGENCY LAN	DING MADE ON ROAD .  UPON INSPECTION IT WAS DISCOVERED THERE WAS 7.5 INCHES OF BLADE TIP MISSING.  SERIAL NR OF BLADE IS	 NOT ACCESSIBLE AT THIS TIME, MUST DISASSEMBLE PROP.  BLADE SN IS EITHER K46513YS OR K64839S ACCORDING TO PROP LOG.  (K)				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA9	 
2006012600085	20060126	00085	EU  	2006	1	26	2006FA0000054    	1	20051215	G	3610	SBJ33057401	DUCT            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					HP BLEED AIR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	39WP	3051 				294				DURING SCHEDULED NR 2 ENGINE CHANGE INSPECTION NOTICED HP BLEED AIR DUCT WAS CRACKED AT CENTER BLEED AIR TAP.  CRACK APP	EARED TO ORIGINALS AT THE WELD AND PROGRESSED RADIALLY, APPROX 2.25 INCH TOWARDS THE BRAIDED FLEX COUPLING.  NEW DUCT WA	S ORDERED AND INSTALLED.  CRACKED DUCT WILL BE SENT TO MFG FOR ENGINEERING EVALUATION.  THIS IS THE SECOND HP BLEED AIR 	DUCT FOUND CRACKED DURING RECENT ENGINE CHANGES.  THE FIRST DUCT FOUND CRACKED WAS ON NR 3 ENGINE.  PN SBJ33055-401 WITH	 SOME DIFFERENCE IN CONFIGURATION BUT SAME APPLICATION.  THE ABOVE DUCT WAS ALSO REPLACED WITH NEW PART FROM MFG.  (K)		2	L	7	3 	4F	4	F		A46EU   	E1NM				 
2006012600093	20060126	00093	SW  	2006	1	26	2006FA0000059    	1	20051220	G	6210	430310101107	RESTRAINT       			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					M/R BLADE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	430LF	1523 				49096				PILOT REPORTED SEVERE VIBRATION AFTER INSPECTION FOUND ORANGE BLADE SHEAR RESTRAINT AT MAIN ROTOR SYSTEM FAILED.  CNETER	 BUSHING HAD BECOME DEBONDED FROM ELASTOMERIC.  VISUAL INSPECTION DIFFICULT BECAUSE OF ORIENTATION AT INSTALLATION.  (K)					1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2006012600090	20060126	00090	CE  	2006	1	26	2006FA0000061    	1	20051221	G	8011	EBB131A	DRIVE ASSY      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					STARTER	FAILED          	D			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	75716	229  			C080744	17267897	RL193576T			(.7500) OF THE DRIVE TEETH ON THE BENDIX DRIVE WERE COMPLETELY SHEARED DURING AN ENGINE START-UP.  NO PROBABLE CAUSE OR 	RECOMMENDATIONS TO MAKE.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006013000038	20060130	00038		2006	1	30	2006FA0000062    	4	20051209	G	6122	89365120	GOVERNOR        			MTSBSI	MU2   	MU2B25      	5780409	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					PROPELLER	DEFECTIVE       	B			IZ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	50K		277  			305	P106013			ENGINE/PROPELLER RPM WAS UNSTABLE AND PROP GOVERNOR HIGH SETTING WOULD DECREASE FROM 100 PERCENT RPM TO 98 PERCENT RPM W	ITH NO INPUT BY THE PILOT.  INSPECTION OF THE PROP GOVERNOR REVEALED THAT THE BUSHING IN THE IDLER GEAR HAD EXCESSIVE WE	AR WITH .139 INCH GAP BETWEEN THE BUSHING AND SHAFT.  NOTE:  EARLIER MODELS OF THIS PROP GOVERNOR HAD EARLIER MODELS OF 	THIS PROP GOVERNOR HAD NEEDLE BEARINGS INSTEAD OF A BUSHING IN THIS LOCATION.  THE DEFECTIVE PROP GOVERNOR WAS REPLACED.	 (K)		1	H	7	2 	3T	4	T		A2PC    	E4WE				 
2006013000089	20060130	00089	GL  	2006	1	30	2006FA0000063    	1	20051224	G	2730		PUSHROD         			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360A1D     	41514	EA  					ELEVATOR	DISCONNECTED    	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	05	8XC					1382				REPORTED LOSS OF ELEV CNTRL ON FINAL APROACH.  BOOT AROUND REAR CNTRL STICK WAS REMOVED, ELEV PUSH ROD WAS NO LONGER CON	NECTED, NO NUT WAS FOUND.  ROD ENDS WERE INSP, FOUND THAT SELFLOCKING NUT, BOLT FOR AFT INTERCONNECT PUSH ROD WAS LOOSE.	  HARDWARE WAS NOT REINSTALLED, IT WAS LOOSE ON INSP.  2 EA NEW WERE INSTALLED, BOLT, WASHERS, CASTLE NUT AND COTTER PIN	 IN REAR CNTRL STICK ROD END CONNT POINTS.  REPAIR OF FLT CNTRLS, DETERMINED AIRWORTHY.  ADVISED MFG SERV CTR INSPECT AC	 AND MAKE REPAIRS IAW MM.  PROBABLE CAUSE, REUSE OF HARDWARE OR INCORRECT TORQUE APPLIED TO NUT AND BOLT.  CASTLE NUT, C	OTTER PIN WAS INSTALLED IN PLACE OF SELFLOCKING TO ENSURE A PROVEN METHOD OF SAFETY WAS USED ON AIRFRAME CNTRLS.  (K)	1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2006012400182	20060124	00182		2006	1	24	2006FA0000070    	4	20050922	G	2565	BACK12BU9B	CHAIN           			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D5       	52046	NE  					FWD DOOR SLIDE	DETACHED        	B			NP1Y	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	33	932UP					19856				DURING C-CHECK, INSPECTION OF FWD DOOR EMERGENCY ESCAPE SLIDE BUSTLE LATCH CHAIN WAS FOUND DETACHED FROM THE SPLIT RING.	  THE SPLIT RING HAD BECOME ELONGATED AND THE RING COILS HAD SEPARATED THUS ALLOWING THE CHAIN TO DETACH.  THE SLIDE WOU	LD NOT HAVE INFLATED IF REQUIRED.  THE CHAIN AND RING ASSY WILL BE REPLACED.  (K)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006012400170	20060124	00170	EA  	2006	1	24	2006FA0000072    	1	20051015	G	5597		WIRE            			CNDAIR	CL601 	CL6013A     	8070802	EA  	CONT  	O200  	O200*       	17020	SO  					VERT STABILIZER	SHORTED         	B			RO3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	601KF					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	3	O	RT	A21EA   	E252				 
2006012400168	20060124	00168	CE  	2006	1	24	2006FA0000073    	1	20051020	G	2500	551900912	SEAT            			CESSNA	501   	501         	2076603	CE  											CRACKED         	B			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 STC. STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F				A27CE   					 
2006013000092	20060130	00092	NM  	2006	1	30	2006FA0000074    	1	20051118	G	3213	40005401	CYLINDER        			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	TIO540*     	41532	EA  					MLG	MISMANUFACTURED 	D				O				OTHER                   				W			INADEQUATE Q C            			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.  RECOMMEND INSPECTION OF COLLAR AT BOTTOM OF GEAR STRUT FOR ANY MOVEMENT	 OR WORKING BETWEEN COLLAR AND THE STRUT CYLINDER ASSY.  DYE CHECK COLLAR WHERE PART IS MACHINED FOR CLEARANCE ON TORQUE	 LINKS.  (K)			1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2006012400169	20060124	00169	    	2006	1	24	2006FA0000075    	1	20051118	G	3213	40005401	CYLINDER        			SMITH 	STC   	STC600      	       	    	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	MISMANUFACTURED 	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	15	7411S	3968 				600016				COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BAZED OR SILVER SOLDERED TOGETHER-WORK	ING COLLAR CAUSED PART TO WORK AND CRACK BOSS.  RECOMMEND INSPECTION OF COLLAR AT BOTTOM OF GEAR STRUT FOR ANY MOVEMENT 	OR WORKING BETWEEN COLLAR AND THE STRUT CYLINDER ASSY- DYE CHECK COLLAR WHERE PART IS MACHINED FOR CLEARANCE ON TORQUE L	INKS.  (K)			1	M	7	2 	3O	3	O		A17WE   	E14EA				 
2006013100170	20060131	00170	SW  	2006	1	31	2006FA0000085    	1	20051013	G	2436	800397503	VOLT REGULATOR  			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540*     	41532	EA  						FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	9145X					270095				COMBINATION VOLTAGE AND OVERVOLTAGE REGULATOR FAILED.  THIS FAILURE CAUSED A VOLTAGE SPIKE IN THE ELECTRICAL SYSTEM WHIC	H IN TURN DAMAGED ALL OF THE COM AND NAV RADIOS, THE ANNUNCIATOR PANEL, AND NUMEROUS COMPUTER RELATED AVIONICS ITEMS.  M	ULTIPLE LIGHT BULBS IN THE AIRCRAFT WERE ALSO REPLACED.  THE REASON FOR THE REGULATOR FAILURE IS STILL UNCLEAR AT THIS T	IME.			1	L	7	1 	3O	3	O	RT	2A3     	E14EA				 
2006013100163	20060131	00163	EA  	2006	1	31	2006FA0000089    	2	20051230	G	7310	LW120980210	FUEL LINE       			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	WORN            	B			RF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	542LB	101  				T18208402				FOUND FUEL INJECTION LINE RUBBING CYLINDER COOLING FINS.  CAUSING WEAR TO THE LINE.  IF WORN CAN CAUSE FUEL LEAK ON TO T	HE TURBO CHARGER.  AD WAS IN COMPLIANCE BUT THE CLAMP WAS LOOSE ALLOWING FUEL LINE TO ROTATE.  (SW01200603311) (K)					1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2006013100168	20060131	00168	CE  	2006	1	31	2006FA0000091    	1	20051115	G	3210	3730FLOATS	LANDING GEAR    			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					RIGHT	LACK OF LUBE    	B			KL2R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	23	800TA					18502901				RT MAIN GEAR, NO GREEN GEARDOWN LIGHT.  GEAR CYCLED SEVERAL TIMES, RT MAIN GEAR COLLAPSED AFTER LANDING.  REMOVED GEAR A	SSY FOUND LACK OF LUBE THE PROBLEM.  REPLACED PARTS, BENT WHEN GEAR COLLAPSED. LUBED, REINSTALLED.  OPS OK.  LUBE GEAR M	ORE OFTEN.  (K)				1	H	7	1 	3O	3	O		3A24    	E5CE				 
2006013100207	20060131	00207		2006	1	31	2006FA0000095    	4	20051029	G	2562	AK450	TRANSMITTER     			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ELT	INOPERATIVE     	B			NT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	201VE					240395				ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING.  UPON REMOVAL THE ELT WENT OFF WHEN TURNE	D UPSIDE DOWN.  PIECES CAN BE HEARD RATTLING AROUNG INSIDE UNIT.  SUSPECT G-SWITCH CAME LOOSE.  THIS IS OUT 2ND EXPERIEN	CE OF SAME CONDITION.  LOOSE COMPONENT INSIDE RATTLING AROUND.  FIRST UNIT, ELT DID NOT ACTIVATE.  UNIT IS APPROXIMATELY	 4 YEARS OLD.  TREND OF FAILURES ON THIS MAKE AND MODEL OF ELT.  SUSPECT INTERNAL DETERIORATION OF COMPONENT SECURITY.  	(K)		1	L	7	1 	3O	3	O		2A3     	1E10				 
2006013100198	20060131	00198	CE  	2006	1	31	2006FA0000097    	1	20051228	G	2720	08602073	CONTROL CABLE   			CESSNA	310   	310N        	2074234	CE  	CONT  	O470  	IO470*      	17026	SO  					LT RUDDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	4110Q	6986 				310N0010				THE LT RUDDER CABLE BROKE AT THE CLEVIS THAT ATTACHES IT TO THE RUDDER TORQUE TUBE ARM.  UNDER NORMAL OPERATING CONDITIO	NS, DURING THE 37 YEARS AND HOURS THAT THE AIRCRAFT HAS BEEN IN SERVICE.  THE RT RUDDER CABLE HAD ABOUT 25 PERCENT OF TH	E STRANDS BROKEN.  THE BOLT FOR THE CLEVIS WAS SO TIGHT THAT THE CLEVIS COULD NOT PIVOT ON THE BOLT ATTACHING IT TO THE 	RUDDER TORQUE TUBE ARM.  THE CONSTANT UP AND DOWN PULL ON THE CABLE BALL SWEDGE SEEMS TO HAVE BROKEN THE STRANDS OF THE 	CABLE A FEW AT A TIME.  THE CLEVISES NEED TO BE INSPECTED FOR FREEDOM OF MOVEMENT ON THE BOLTS THAT ATTACH THEM TO ARMS.	  (K)	1	L	7	2 	3O	3	O		3A10    	E1CE				 
2006020200150	20060202	00150	SO  	2006	2	2	2006FA0000105    	1	20051127	G	2910	GAC1159SCH2463A	SHUTOFF VALVE   			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					HYD SYSTEM	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	250VC	1043 				1495				AIRCRAFT WAS ON A POSITION FLIGHT, ON DEPARTURE THE CREW RECEIVED A (CK HYD QUANTITY) EICAS CAUTION LIGHT.  COCKPIT INDI	CATIONS REVEALED A LOSS OF COMBINED HYDRAULIC FLUID.  THE FLIGHT CREW DECLARED AN EMERGENCY AND RETURNED TO DEPARTURE.  	MAINT INVESTIGATION REVEALED THE FLIGHT POWER SHUTOFF VALVE ASSY HOUSING WAS CRACKED.  THIS IS THE SECOND INCIDENT OF A 	CRACKED HOUSING WITHIN OUR FLEET.  AN UPGRADED 5 ASSY WAS PROCURED FROM MFG AND AC WAS RETURNED TO SERVICE.  HAVE COMMUN	ICATED OUR CONCERNS TO AC MFG AND ENCOURAGED A PROACTIVE RESOLUTION TO A RATHER SEVERE SITUATION.  (EA25200605366) (K)		2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006020200167	20060202	00167	NE  	2006	2	2	2006FA0000112    	2	20051001	G	7200	ARRIEL1D1	ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUSELAGE	MAKING METAL    	B			EOOR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AL	03	CGLNH	956  				1230	9999			DURING FLIGHT, THE CHIP LIGHT ILLUMINATED, CHIPS WERE FOUND AND BEFORE 30 MINUTE GROUND RUN WAS COMPLETED ANOTHER LIGHT 	OCCURRED.  CHIPS WERE OF SUFFICIENT SIZE THAT REQUIRED REMOVING THE ENGINE.  (K)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006020300081	20060203	00081	GL  	2006	2	3	2006FA0000113    	2	20051005	G	7200		LINE            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  						LEAKING         	B			EOOR	O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AL	03	CFMAL					611010D	CAE834272			PILOT SAW TORQUE PRESS FLUCTUATE.  TORQUE PRESS LINE TO GAUGE LEAKED AND ENGINE WAS STARVED OF OIL.  THE AIRCRAFT HAD MA	DE A NORMAL LANDING AND SHUTOFF ENGINE SEIZED UP ON COASTDOWN, REPLACED ENGINE.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006020200104	20060202	00104	WP  	2006	2	2	2006FA0000114    	1	20050928	G	5330		SKIN            			HUGHES	369   	369E        	4470707	WP  										FUSELAGE	CRACKED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGREP	10728				0242E				FOUND A CRACK ON THE (TURTLE BACK) SKIN ABOVE THE ENGINE BETWEENT THE ATTACHMENT STRINGERS OF THE TAILBOOM FARRING AND B	ETWEEN THE RIBS AT STA 146.62 AND STA 155.75 CRACK IS LOCATED ON THE RT SIDE AND RUNNING FROM STA 146.62 AFT 7.25 INCHES	.  REPAIRED CRACK WITH PATCH.  (K)				1	G	7	1 	3U				H3WE    					 
2006020200168	20060202	00168	GL  	2006	2	2	2006FA0000115    	2	20051006	G	7240	6870992	COMBUST CHAMBER 			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	B			EOOR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			AL	03	CGBUY						CAE833577			DURING AN INSPECTION FOR HIGH TOT THE OUTER COMBUSTION CAN WAS FOUND TO BE CRACKED IN THE LEFT (ARM PIT).  (K)						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2006020300105	20060203	00105	EU  	2006	2	3	2006FA0000116    	1	20051111	G	6400	355A2700720001	BELLCRANK       			SNIAS 	350   	AS350B2     	8680813	EU  										T/R CONTROLS	ELONGATED       	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	CFYUU	518  				1384				DURING 500 HOUR INSPECTION AND REMOVAL OF T/R SERVO OVERCENTERING  MECHANISM, IT WAS DISCOVERED THAT THE MAIN SUPPORT BO	LT AND THE BELLCRANK PIVOT BOLT WERE VERY DIFFICULT TO REMOVE.   THE BELLCRANK PIVOT BOLT WAS OBVIOUSLY HAMMERED IN BY E	VIDENCE OF THE RAISED METAL AND ELONGATED HOLE.  REPLACED BELLCRANK AND BOTH BOLTS.  (K)				1	G	7	1 	3U				H9EU    					 
2006020200110	20060202	00110	CE  	2006	2	2	2006FA0000120    	1	20050617	G	2130		STATIC LINE     			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					EQUIPMENT BAY	LOOSE           	C			CYOG	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	05	8005Y					121	241C287A			WHILE ENROUTE, CABIN ALTITUDE EXCEEDED 10,000 FT.  THE FLIGHT CREW FOLLOWED EMERGENCY PROCEDURES BUT WAS UNABLE TO RETUR	N THE CABIN PRESSURIZATION WITHIN NORMAL PIRAMETERS.  THE FLIGHT CREW DECIDED TO DIVERTED AND LANDED WITHOUT FURTHER INC	IDENT.  UPON INSPECTION MAINTENANCE CREW FOUDN A LINE LOOSE ON THE PRESSURIZATION JET PUMP.  (K)				2	L	7	2 	4J	4	J		A10CE   	1E16				 
2006021400163	20060214	00163		2006	2	14	2006FA0000122    	4	20051215	G	3160	4306081100000	TRANSCEIVER     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985*       	52008	NE  					COCKPIT	MALFUNCTIONED   	B			HJBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	5160G					236				DURING POST INSTALLATION CHECKS, FOUND THE GDL90 UAT REPORTING CONTINUOUS EXTERNAL FAULT ERROR.  NO EXTERNAL FAULTS FOUN	D.  REPLACEMENT OF THE UNIT CORRECTED THE ERROR.  (K)					1	H	7	1 	3R	3	R		A806    	5E1				 
2006020600237	20060206	00237		2006	2	6	2006FA0000124    	4	20051226	G	3160	4306081100000	TRANSCEIVER     			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	MALFUNCTIONED   	B			HJBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	96AK					20700782				DURING POST INSTALLATION CHECKS, FOUND THE GDL90 UAT REPORTING CONTINUOUS GPS FAILURE.  REPLACEMENT OF THE UNIT CORRECTE	D THE ERROR.  (K)					1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2006021700094	20060217	00094	CE  	2006	2	17	2006FA0000137    	1	20051215	G	5100	MS21042L3	NUT             			BEECH 	200   	200BEECH    	1152920	CE  										LT WING ROOT	FAILED          	B			AHDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	561SS					BB464				NUT, PN MS21042L3 (PN130909N29) FAILED AND TAPERED PIN PN AN 38629A CAME OUT OF ADAPTER NP 1158110473 IN LT WING ROOT.  	THE ADAPTER DISENGAGED FROM THE TORQUE TUBE SHAFT PN 1018100211, THE LT MAIN GEAR COULD NOT LOCK DOWN.  THE NUT HAD ONLY	 160.4 HOURS ON IT FROM NEW.   THE NUT IS EXPOSED TO HIGH TENSION LOADS DUE TO THE CENTRIFUGAL FORCE FROM THE TORQUE TUB	E SPINNING.  (K)			1	L	7	2 	4T				A24CE   					 
2006021700008	20060217	00008	CE  	2006	2	17	2006FA0000147    	1	20051026	G	2810	1002268815	SEAL            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL LINE	TORN            	B			E81R	O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			GL	03	815TA	5129 				258534				DURING REFUELING OF RT WING, FUEL WOULD EXIT OUT OF NACA VENT BEFORE TANK TOPPED OFF.  RT FUEL QUANTITY INDICATION WOULD	 SHOW TANKS NOT FULL YET.  FOUND VENT SYSTEM INTERCONNECTING TUBING SEALS TORN/MISSING BETWEEN SURGE TANK AND NACA SCOOP	.  REPLACED SEALS AS REQUIRED AND REASSEMBLED VENT SYSTEM INTERCONNECTING TUBING.  NO FAULTS NOTED ON REFUELING.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006021700032	20060217	00032		2006	2	17	2006FA0000148    	4	20051027	G	2297		CONNECTOR       			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					AUTOPILOT	DIRTY           	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	815TA					258534				PILOTS REPORT AIRCRAFT (PORPOISING) IN LEVEL FLIGHT AT FL 380 WITH AUTOPILOT ENGAGED.  TROUBLESHOT IAW COMMUNIQUE NR 22-	07; FOUND HIGH RESISTANCE AT AUTOPILOT FLAP COMPENSATOR TRANSMITTER (FT) CONNECTOR FT-1B.  CLEANED AND REINSTALLED CONNE	CTOR, CHECKED RESISTANCES NOW WITHIN COMMUNIQUE NR22-07 SERVICE LIMITS.  RECOMMEND INVESTIGATION OF POSSIBLE REPLACEMENT	 AP FLAP COMPENSATOR TRANSMITTER CONNECTOR OR INSTALLATION WITH IMPROVED ENVIRONMENTAL SEALING CHARACTERISTICS.  (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006021700011	20060217	00011	CE  	2006	2	17	2006FA0000149    	1	20050207	G	5310	1294000339	STRUCTURE       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  					FUSELAGE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	891SK	26259				UE89				AIR STAIR DOOR LOWER CLOSURE, MFG FROM 4130 STEEL, WAS CORRODED THRU UNDER FOLDING STEP.  THIS CLOSURE HAD BEEN PREVIOUS	LY REPAIRED BY REMOVING CORROSION, TREATING AND A DOUBLER INSTALLED.  REMOVED  CLOSURE DUE TO CORROSION AND DISBOND FROM	 DOOR CORE MATERIAL.  INSTALLED FACTORY NEW ALUMINUM REPLACEMENT CLOSURE.  RECOMMEND FREQUENT INSPECTIONS OF THIS AREAS,	 ESPECIALLY AFTER OPERATIONS IN WET CONDITIONS, AND IMMEDIATE TREATEMENT OF CORROSION.  (K)			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2006021700009	20060217	00009	SO  	2006	2	17	2006FA0000150    	2	20050126	G	8520		LIFTER          			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					ENGINE	SPALLED         	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	584LL	509  				TH1931	684339			METAL FOUND IN OIL FILTER DURING INSP WAS LATER DETERMINED TO BE FROM FAILED LIFTERS.  CONDITION WAS STARTING TO DAMAGE 	CAM LOBES.  SID 05-1 STATES THAT MINOR IMPERFECTIONS CAN (HEAL OVER) BUT WE HAVE NOT FOUND THIS TO BE CASE, JUST OPPOSIT	E IS TRUE.  ONCE LIFTER BEGINS TO SPALL IT CREATES A (CHEESE GRATER) EFFECT BETWEEN CAM AND LIFTER.  W/O PROPER METALLUR	GICAL LAB, CAUSE CANNOT BE DETERMINED.  SPECULATED THAT MATERIAL IS EITHER IMPROPERLY HEAT TREATED OR SUBSTANDARD MATERI	AL IS USED.  TO PREVENT THIS FROM RECURRING MFG SHOULD INSPECT ALL LIFTER BODIES BEFORE INSTALLATION FOR  GRANULAR DEFEC	TS OF METAL.  THIS CAN BE ACCOMPLISHED USING X-RAY EXAM,  NDT WHICH WOULD INCLUDE USE OF A SPECIAL MICROSCOPE.  (K)	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006021700007	20060217	00007	CE  	2006	2	17	2006FA0000151    	1	20050124	G	5220	115430100661A	SKIN            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					EMERGENCY EXIT	CRACKED         	B			CGHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	1568E					BB1488				DURING PHASE 1-4 INSPECTION, EMERGENCY EXIT HATCH OUTER SKIN WAS FOUND CRACKED AT THE IB SURFACE, THROUGH THE ENTIRE 90 	DEGREES RADIUS OF THE LOWER AFT CORNER OF SKIN ASSY 115430100-661A.  CRACK LENGTH APPROX 6 INCHES. (K)					1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2006021600268	20060216	00268	CE  	2006	2	16	2006FA0000152    	1	20050124	G	5532		SKIN            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  					VENTRAL FIN	DELAMINATED     	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	843E	6068 				UE339				BOTH LT AND RT VENTRAL FINS SHOWED AREAS OF DELAMINATION ON FWD TOP CORNERS.  DELAMINATION WAS BEYOND REPAIR LIMITS IAW 	SRM AND REQUIRED DER APPROVAL.  FOUND INNER CORE MATERIAL WET DAMAGE WAS APPARENTLY CAUSED BY FREEZE CYCLES.  WATER WAS 	FOUND ALONG TOP OF FIN BETWEEN FIN AND FUSELAGE ATTACH ANGLES.  AC HAD BEEN RECENTLY REPAINTED.  REPLACED SEALANT AT LEA	DING AND TRAILING EDGES OF FIN TO PRECLUDED WATER INGRESS.  SUGGEST CLOSE VISUAL INSPECTION OF FIN/FUSELAGE FOR BREAKS I	N SEALING AT AFT FUSELAGE DETAILED INSPECTION AND AFTER STRIPPING/ PAINTING HAS BEEN ACCOMPLISHED.  AREA OF DISBOND WAS 	MAPPED OUT USING TAP TESTING HOWEVER ADDITIONAL CORE MATERIAL WAS REMOVED DUE TO ENTRAPPED WATER.  (K)	2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2006021700082	20060217	00082	NE  	2006	2	17	2006FA0000153    	2	20050120	G	7261		CHIP DETECTOR   			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ENGINE OIL	FALSE INDICATION	C				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			WP	13	11QL					3738				PRECAUTIONARY LANDING, DUE TO ENG OIL CHIP LIGHT ANNUNCIATION IN FLT.  UNEVENTFUL LANDING. MAINT INVESTIGATED, FOUND ONE	 SMALL HAIR LIKE DARK CHIP.  PLUG WAS CLEANED, ENG WAS TEST RUN FOR 10 MIN.  ENG RUN-DOWN TIME WAS CHECKED.  NO ADDITION	AL CHIPS FOUND.  RUN DOWN TIMES WERE NML.  AC WAS FLOWN EMPTY BACK TO MAINT BASE.  CHIP PLUG WAS RE-INSPECTED FOR ADDITI	ONAL CHIPS.  NO CHIPS NOTED AT THAT TIME.  IAW MFG INSTRUCTION, PLUG IS TO BE REINSPECTED AFTER FIRST FLIGHT OF DAY FOR 	NEXT 25 HOURS.  CHIP DETECTOR, SUPPORTING SYS WORKED PROPERLY, ALERTING PILOT OF A POTENTIAL PROBLEM.  FALSE INDICATION 	BECAUSE OF CHIP DETECTORS INABILITY TO DIFFERENTIATE 1 VERSES CHIPS .	1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2006021700099	20060217	00099	EA  	2006	2	17	2006FA0000154    	2	20050126	G	7314	A1005B	PUMP            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					AUX FUEL PUMP	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	65556	112  				T20608496				THIS FUEL PUMP IS LOCATED UNDERT HE PILOTS SIDE FLOORBOARDS AND IS AN ELECTRICLY DRIVE AUX FUEL PUMP.  THE AC ORIGINAL F	UEL PUMP A10055B FAILED AFTER 53 HOURS IN SERVICE ON MARCH OF 2005.  IT FAILED IN A WAY TO ALLOW FUEL TO ENTER THE ELECT	RIC SIDE OF THE MOTOR.  THAT WAS A MAJOR FIRE HAZZARD.  THE PUMP THAT REPLACED WAS A LIKE PN, SN 111810 WHICH IS THE ONE	 FILED IN THIS REPORT, LASTED 112.3 HOURS IN SERVICE WHEN IT BEGAN TO MAKE HIGH PITCHED NOISES ON SHUTDOWN.  IT SOUNDED 	AS IF A BEARING WAS RUNNING DRY.  (K)		1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2006021700105	20060217	00105	SW  	2006	2	17	2006FA0000155    	1	20050131	G	3220		LANDING GEAR    			GULSTM	114   	114TC       	0145002	SW  	LYC   	O540  	TIO540*     	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	NOSE	COLLAPSED       	B			CB5Y	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	35	115TB					20031	L1061461A	000408		FIRST FLT AFTER ENG REFITMENT NLG FAILED TO EXTEND TO LANDING POS.  ON FIRST FLT, GREEN NOSE WHEEL INDICATOR WOULD NOT I	LLUMINATE. NLG WAS PARTIALLY EXTENDED TO ANGLE OF SOME 45 DEGREES.  EMERGENCY EXTENSION PRECEDURES CARRIED OUT BY PILOT 	STILL FAILED TO EXTEND NLG BEYOND 45 DEGREES.  PWROFF LANDING WAS EXECUTED WHERE UPON NLG COLLAPSED AND AC CAME TO REST 	ON 2 OF 3 PROP BLADES NOSE WHEEL BAY DOORS.  AC NOSE WAS LIFTED.  LANDING HAD PUSHED NLG BACK TOWARD RETRACTED POSITION 	BUT WITH PART OF TIRE PROTRUDING THROUGH PARTIALLY OPEN NOSE BAY DOORS.  PIN ATTACHING NOSE GEAR ACT TO NOSE LEG WAS REM	OVED.  ENGINEERING INVESTIGATION IS BEING CARRIED OUT WHICH AT THIS TIME HAS FAILED TO DETERMINE CAUSE OF FAILURE. (K)	1	L	7	1 	3O	3	O	RT	A12SO   	E14EA	5	C	P58GL	 
2006022800035	20060228	00035	EA  	2006	2	28	2006FA0000177    	2	20050314	G	8520	75072	IDLER GEAR      			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	08	1202X	3560 	1639 			2605	L636336			ENGINE FAILED IN FLIGHT PRELIMINARY INSPECTION REVEALED CAMSHAFT AND ASSOCIATED CRANKSHAFT IDLER GEAR WAS SEPARATED FROM	 CRANKSHAFT DRIVE GEAR IDLER GEAR SLOWS EVIDENCE OF DAMAGE TO DRIVE TEETH.  UNABLE TO DETERMINE AT THIS TIME WHETHER THE	 CAMSHAFT OR LT MAGNETO DRIVE WAS RESPONSIBLE FOR IDLER GEAR DAMAGE AND ENGINE FAILURE.  (K)				1	L	7	1 	3O	3	O		2A3     	E286				 
2006022800064	20060228	00064	EU  	2006	2	28	2006FA0000178    	1	20050124	G	2910	MY20751107	LINE            			AMD   	FALC20	FALCON      	2720302	EU  	GE    	CF700 	CF700*      	30010	NE  					HYDRAULIC SYS	CHAFED          	B			QY5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	20NY					61				WHILE COMPLAYING WITH SB, FOUND 2 HYDRAULIC LINES PN MY20751107 AND MY20751207 CHAFED 20 PERCENT OF WALL THICKNESS LINES	 REPLACED.  (K)					2	L	7	2 	4F	4	F		A7EU    	E7EA				 
2006022800036	20060228	00036	EU  	2006	2	28	2006FA0000179    	1	20050124	G	2910	MY20751207	LINE            			AMD   	FALC20	FALCON      	2720302	EU  	GE    	CF700 	CF700*      	30010	NE  					HYDRAULIC SYS	CHAFED          	B			QY5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	20NY	8548 				61				WHILE COMPLYING WITH SB, FOUND 2 HYDRAULIC LINES PN MY20751107 AND MY20751207 CHAFED 20 PERCENT OF WALL THICHNESS LINES 	REPLACED. (K)					2	L	7	2 	4F	4	F		A7EU    	E7EA				 
2006022800007	20060228	00007		2006	2	28	2006FA0000180    	4	20050210	G	2562	EBC302V	ELT             			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					CABIN	INOPERATIVE     	B			ZKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	7967N					285383				ELT WENT OFF WITH AIRCRAFT SETTING ON RAMP, NO WIND AIRCRAFT HAS NOT FLOWN IN A NUMBER OF DAYS.  UNHOOKED BATTERY OVERNI	GHT.  REHOOKED BATTERY IN MORNING, UNIT STILL ACTIVATED.  UNHOOKED BATTERY AND TAG UNIT AS INOPERATIVE AND REMOVED FROM 	AIRCRAFT.  (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
2006022800023	20060228	00023	CE  	2006	2	28	2006FA0000181    	1	20050213	G	7797		CONNECTOR       			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					TRANSDUCER	DISCONNECTED    	B			EHHR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	17	36TP					T18208387				PLASTIC CONNECTOR THAT CONNECTS TO TACHOMETER TRANSDUCER HAS NO LOCKING DEVICE, THIS TYPE OF CONNECTOR SHOULD HAVE A SNA	P LOCK AT THE END OF IT THREAD TRAVEL.  FOUND THIS SAME SIMILAR PROBLEM ON 2 OTHER SINGLE ENGINE AIRCRAFT WITH THE SAME 	TRANSDUCERE.  ALSO HAVING PLASTIC CONNECTORS IN ENGINE COMPARTMENT IS A BIT OF CONCERN. ON FIRST AC, AFTER TIGHTENING TH	E CONNECTOR, IT HAD UNSCREWED AND FELL OFF IN FLIGHT.  REINSTALLED THE CONNECTOR AND APPLIED RTV SEALANT TO THE OUTSIDE 	OF THE CONNECTOR AND TRANSDUCER. (K)		1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2006022800024	20060228	00024	EA  	2006	2	28	2006FA0000182    	2	20050203	G	7414	4370	MAGNETO         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FAILED          	B			TVMR	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	05	42997	622  				288316062	RLK58339A			EXPERIENCED IN-FLIGHT FAILURE OF RT MAGNETO.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2006022800025	20060228	00025	EU  	2006	2	28	2006FA0000184    	1	20051219	G	2823	503CA90	SELECTOR        			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540*       	41532	EA  					FUEL	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	80KM					80				RT FUEL PRESSURE WOULD OCCASIONALLY DROP OFF TO BOTTOM OF GREEN RANGE AFTER AIRCRAFT IN CRUISE CONFIGURATION, (ELECTRIC 	PUMPS OFF) AFTER EXTENDED TROUBLESHOOTING IT WAS FOUND THAT THE RT FUEL COCK HAS VACUUM LEAK AT THE SHAFT AT HIGHER MANI	FOLD PRESSURE 23-24 INCH MP, FUEL PRESSURES RETURNED TO NORMAL BELOW 23 INCHES MP OR WHEN ELECTRIC PUMPS ACTIVATED NO FU	EL LEAKS OR STAINS FOUND.  REPLACED VALVE WITH OVERHAULED UNIT, OPS TEST SATISFACTORY RETURNED TO SERVICE.  (K)			1	H	7	2 	3O	3	O		A17EU   	E295				 
2006032300143	20060323	00143	CE  	2006	3	23	2006FA0000263    	1	20051028	G	2697		WIRE HARNESS    			CESSNA	750   	750         	2076810	CE  										APU FIRE BOTTLE	DISCONNECTED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	69SB					7500212				DURING THE CONDUCT OF THE RECURRING INSPECTION REQUIRED BY AD2005-09-01 AND PHASE 30, THE WIRING BUNDLE FOR THE APU FIRE	 BOTTLE WAS FOUND WRAPPED AROUND THE APU FUEL TUBE JUST FORWARD OF THE FIRE BOTTLE.  THIS WIRE BUNDLE HAS BOTH AN ACTIVA	TION CIRCUIT (NORMALLY UNPOWERED) AND A BOTTLE PRESSURE SENSING CIRCUIT WHICH IS POWERED WHENEVER BATTERY POWER IS SELEC	TED.  THE CONNECTOR WAS UNPLUGGED AT THE FIRE BOTTLE AND UNWRAPPED FROM THE FUEL TUBE, THEN TIED UP OUT OF THE WAY AND S	PIRAL WRAP APPLIED TO WIRING HARNESS.		2	L	7	2 	4J			RT	T00007WI					 
2006040500223	20060405	00223	SO  	2006	4	5	2006FA0000287    	2	20050822	G	8530	TIST712BCA	CYLINDER        								CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		4395 					511157			5 OF 6 CYLINDERS CRACKED: ( SN 11501-23, 11501-11, 11556-01, 10644-18 CRACKED EXHAUST SIDE) (11909-27 CRACKED INTAKE SID	E) AT 439.5 HOURS.  (K)										3	O			E8CE				 
2006040500230	20060405	00230	SO  	2006	4	5	2006FA0000288    	2	20050822	G	8530	TIST712BCA	CYLINDER        								CONT  	O520  	TSIO520M    	17040	SO  					ENGI NE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		439  					511157			5 OF 6 CYLINDERS CRACKED, (SN NR 11501-23, 11501-11, 11556-01, 10644-18 CRACKED EXHAUST SIDE) (SN NR 11901-27 CRACKED IN	TAKE SIDE) CRACKED AT 439.5 HOURS.  (K)										3	O			E8CE				 
2006040600155	20060406	00155	SO  	2006	4	6	2006FA0000289    	2	20050822	G	8530	TIST712BCA	CYLINDER        								CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							511157			5 OF 6 CYLINDERS CRACKED.  (SN NR 11501-23, 11501-11, 11556-01, 10644-18, 11909-27 CRACKED EXHAUST SIDE) (SN NR 11909-27	 CRACKED INTAKESIDE) CRACKED AT 439.5 HOURS.  (K)										3	O			E8CE				 
2006040500232	20060405	00232	SO  	2006	4	5	2006FA0000290    	2	20050822	G	8530	TIST712BCA	CYLINDER        								CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							511157			5 OF 6 CYLINDERS CRACKED.  (S/N 11501-23, 11501-11, 11556-01, 10644-18 CRACKED AT EXHAUST SIDE) ( S/N 11909-27 CRACKED A	T INTAKE SIDE) CRACKED AT 439.5 HOURS.  (K)										3	O			E8CE				 
2006040500233	20060405	00233	SO  	2006	4	5	2006FA0000291    	2	20050822	G	8530	TIST712BCA	CYLINDER        								CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							511157			5 OF 6 CYLINDERS CRACKED (S/N 11501-23, 11501-11, 11556-01, 10644-18 CRACKED EXHAUST SIDE) (S/N 11909-27 CRACKED ON INTA	KE SIDE) CRACKED AT 439.5 HOURS.  (K)										3	O			E8CE				 
2006040500244	20060405	00244	SO  	2006	4	5	2006FA0000292    	2	20050822	G	8530	934215	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							570865			CYLINDER CRACKED AT 480 HOURS.  (K)											3	O			E5CE				 
2006040500229	20060405	00229	SO  	2006	4	5	2006FA0000293    	2	20050822	G	8530	TISN712ACA	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		670  					826501R			6 OF 6 CYLINDERS CRACKED AT 670 HOURS.  (S/N 12094-7, 12208-27, 13248-8, 13890-9, 13890-25, 14841-10) (K)											3	O			E5CE				 
2006040500224	20060405	00224	SO  	2006	4	5	2006FA0000294    	2	20050822	G	8530	TISN712ACA	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							826501R			5 OF 6 CYLINDERS CRACKED AT 670 HOURS.  (S/N 12094-7, 1220827, 13248-8, 13890-9, 13890-25, 14841-10)  (K)											3	O			E5CE				 
2006040500237	20060405	00237	SO  	2006	4	5	2006FA0000295    	2	20050822	G	8530	TISN712ACA	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		670  					826501R			CYLINDER CRACKED AT 670 HOURS.  (K)											3	O			E5CE				 
2006040500238	20060405	00238	SO  	2006	4	5	2006FA0000296    	2	20050822	G	8530	TISN712ACA	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		670  					826501R			CYLINDER CRACKED AT 670 HOURS.  (K)											3	O			E5CE				 
2006040500239	20060405	00239	SO  	2006	4	5	2006FA0000297    	2	20050822	G	8530	TISN712ACA	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							826501R			CYLINDERS CRACKED AT 670 HOURS.  (K)											3	O			E5CE				 
2006040500240	20060405	00240	SO  	2006	4	5	2006FA0000298    	2	20050822	G	8530	TISN712ACA	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		670  					826501R			CYLINDERS CRACKED AT 670 HOURS.  (K)											3	O			E5CE				 
2006041100057	20060411	00057	GL  	2006	4	11	2006FA0000322    	1	20050926	G	3800		FAUCET          			BOMBDR	BD700 	BD7001A10   	1390006	GL  											UNKNOWN         	C				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CL	CLIMB          	1			GL	03	18WY	1806 	1806 			9057				THE FOWARD FAUCET WAS BUMPED OPEN ALLOWING WATER TO FLOW INTO THE SINK, OVERFILLING THE SINK, GOING INTO LOWER EQUIPMENT	 BAY. ALL THE CRITICIAL FLIGHT COMPONENTS ARE LOCATED THERE AND AFTER TAKEOFF THE CREW HAD TO RETURN BACK TO HOMEBASE DU	E ALL THE FAILED SYSTEMS.				2	L	7	2 	4F			RT	T00003NY					 
2006041200041	20060412	00041	CE  	2006	4	12	2006FA0000329    	1	20051026	G	3010		BOOT            			LEAR  	60    	60LEAR      	5170707	CE  										WINGS	DAMAGED         	B			EPDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	647TS	3368 				047				INADVERRTENT ACTIVATION OF ANTI-ICE SYSTEM ON GROUND, RESULTING IN DAMAGE TO ANTI-ICE BOOTS WAS CAUSED BY AN INTERMITTEN	T GROUND OF CIRCUIT THAT IS NORMALLY OPEN.  THE WIRE NR H255A20 RUNS FROM THE CONTROLLER TO THE REMOTE CIRCUIT BREAKER. 	 (K)				2	L	7	2 	4F			RT	A10CE   					 
2006041900209	20060419	00209	NM  	2006	4	19	2006FA0000341    	1	20050603	G	5753	6546434139	FLAP            			BOEING	737   	7373G7      	1384595	NM  										WINGS	WRONG PART      	B			LH6Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	370WL					24011				(ATC0660) DURING ROUTINE MAINTENANCE IT WAS NOTICED THAT THE LT IB AFT FLAP APPEARED TO BE OF THE WRONG TYPE FOR THIS SE	RIAL OF AIRCRAFT.  THE AIRCRAFT IPC WAS CONSULTED AND THIS CONFIRMED THAT TIME 139, AFT FLAP ASSY IS NOT EFFECTIVE FOR T	HIS AIRCRAFT.  A SURVEY WAS CARRIED OUT ON THE OTMGR T/E FLAP ASSEMBLED AND IT WAS DISCOVERED THAT THE RT IB AFT FLAP WA	S ALSO NOT OF THE CORRECT AFFECTIVITY.  FOR THIS AIRCRAFT (-140).  ALL OF THE OTHER FLAP ASSEMBLED WERE FOUND TO BE CORR	ECT.  WE SUSPECT THAT THESE AFT FLAP ASSEMBLIES ARE FOR AIRCRAFT.  (K)		2	L	7	2 	4F			RT	A16WE   					 
2006042400230	20060424	00230	SO  	2006	4	24	2006FA0000396    	1	20050808	G	3230		HYDRAULIC SYSTEM			PIPER 	PA28  	PA28R180    	7102809	SO  										MLG	CONTAMINATED    	C				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			WP	11	3872T	1661 				28R30196				ON TAKEOFF ROLL, EXPERIENCED A LT MAIN GEAR DOWN LOCK DISENGAGEMENT, RESULTING IN MINOR DAMAGE TO THE UNDERSIDE OF THE L	T WING SKIN, SHUTTLE VALVE IN THE POWER PACK WAS STICKY, CAUSED BY THE SEDIMENTS IN LWR PARTS OF FLUID RESERVOIR.  HYDRA	ULIC CYLINDERS WERE TESTED AND FOUND TO HAVE EXCESSIVE INTERNAL LEAKAGE IN THE GEAR DOWN POSITION; THE PISTON SEALS WERE	 NOTED TO BE VISIBLY WORN.  THE BACKUP EXTENDER/OVERRIDE VALVE WAS TESTED AND FOUND TO HAVE INTERNAL LEAKAGE.  THE PROBA	BLE CAUSE OF THE LT MAIN GEAR DOWN LOCK DISENGAGEMENT APPEARS TO BE RELATED TO SEDIMENT WITHIN THE HYDRAULIC POWER PACK 	RESERVOIR.  (K)	1	L	7	1 	3O				2A13    					 
2006051200041	20060512	00041	NE  	2006	5	12	2006FA0000424    	1	20051014	G	6230	K77461221	ROTOR SHAFT     			KAMAN 	K600  	H43A        	4800702	NE  										MAIN ROTOR	CRACKED         	B			MINR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	05										DURING MAGNETIC PARTICAL INSPECTION, THE SHAFT WAS FOUND CRACKED AT THE UPPER END WHERE THE ROTOR HUB ATTACHES TO THE SH	AFT.  THE CRACK IS APPROXIMATELY 1 INCH LONG AND LOCATED IN THE LOWER RADIUS OF THE RETANGLE CUTOUT.  (K)					1	G	7	1 	3O				AR27    					 
2006051900230	20060519	00230	NE  	2006	5	19	2006FA0000505    	2	20050909	G	7200	3053519050	BEARING         			AIRBUS	A340  	A340*       	       	EU  	GE    	CFM56 	CFM56*      	13802	NE  					POS 5,ROLLER BRG	WORN            	B			X3NY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33							740278			BEARING IS FROM SNR PRODUCTION.  ROLLER BEARING WAS SENT FOR AN INSPECTION.  WE COULD ONLY PERFORM A LEVEL 1 INSPECTION,	 WITHOUT DISASSEMBLING THE INNER RING, CAGE AND ROLLERS.  DURING THE INSPECTION OF THE BEARING, NOTICED SOME HEAVY WEAR 	TRACES AND MARKS ON THE CIRCUMFERENCE OF DIFFERENT ROLLER.  THE DIAMETER OF ONE ROLLER SHOWS AN IMPORTANT NOTCH WITH RAI	SED METAL ON ITS DIAMETER PARALLEL TO ITS ROTATION AXIS.  ON EACH SIDE OF THE NOTCH THE DEFECT IS FOLLOWED BY A CRACK.  	THE TOTAL LENGTH OF THE NOTCH PLUS THE CRACK ON EACH SIDE IS ABOUT ONE THIRD OF THE ROLLER LENGTH.		2	L	7	4 	4F	4	F	RT	A197    	E2GL				 
2006052200186	20060522	00186	SO  	2006	5	22	2006FA0000520    	2	20050716	G	8530	TISN712BCA221	CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	6822U					414A0808	290903			418.6 HRS SINCE COMPLIANCE W19TH AD2004-08-10 ON ECI CYLINDERS.  LT ENG NR2 AND RT ENG NR 4 CYLINDERS FOUND CRACKED THRO	UGH FROM UPPER PLUG HOLE TO EXHAUST VALVE.  BOTH CYLINDERS HAVE IDENTICAL CRACKS ON RELATIVELY NEW HEADS.  (K)					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2006061200218	20060612	00218		2006	6	12	2006FA0000565    	4	20051005	G	6113	100738005	BULKHEAD        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  	MCAULY	3AF32C	3AF32C*     	GL  	SPINNER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	344HP	165  				3449244				THIS AC WAS NEW IN 3/3/2002.  LT AND RT SPINNER BULKHEADS HAVE HAD TO BE REPLACED TWICE.  FIRST SET OF SPINNER BULKHEADS	 WERE REPLACED 12/28/2004, WITH 563.3 HOURS ON THEM.  PROPS WERE BALANCED TO PREVENT FURTHER PROBLEMS.  SECOND SET OF SP	INNER BULKHEADS WERE REPLACED 8/26/05 WITH 165.9 HOURS ON THEM.  FINDING CRACKS CAN BE DIFFICULT BECAUSE BULKHEAD IS SAN	DWICHED BETWEEN 2 SHIMS.  FIRST SUSPECTED THAT THERE WAS ONLY 1 CRACK ON EACH BULKHEAD BUT AFTER REMOVING BULKHEAD AND T	HE SHIMS, NOTICED THAT EVERY HOLE HAD A CRACK COMING FROM IT.  PROBABLE CAUSE COULD BE IMPROPER INSTALLATION OF PROPELLE	R MOUNTING BOLTS OR DEFECTIVE MATERIAL.  RECOMMEND TAKING CLOSE LOOK EACH 100 HR, IF POSSIBLE LOOKING UNDER SHIMS.  (K)	1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400240	20060614	00240	CE  	2006	6	14	2006FA0000578    	1	20050710	G	3233	12810013	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					LT MLG	CRACKED         	B			PVCR	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			NM	01	9775B	7005 				172RG1029				DURING FLIGHT, LT MLG FAILED TO EXTEND BUT TRAILED, DISCONNECTED FROM HYD SYS.  PILOT WAS ABLE TO ROCK LT MLG INTO DOWN 	AND LOCKED POSITION, MADE SAFE LANDING.  DETERMINED, ACTUATOR BODY HAD CRACKED THROUGH FWD ATTACH HOLE, HALF THROUGH AFT	 ATTACH HOLE, WHICH CAUSED ACT TO SEPARATE WHEN HYD PRESS WAS APPLIED THUS SEPARATING ACTUATOR PISTON GEAR SHAFT FROM SE	CTOR GEAR MOUNTED TO PIVOT.  ACT ATTACH BOLTS WERE FOUND TIGHT, SAFETY WIRE UNDISTURBED.  ACTUATOR BODY WAS REPLACED,  A	CTUATOR WAS RESEALED, REASSEMBLED, REINSTALLED AND TORQUED IAW SRM.    SUSPECT FAILURE OF ACTUATOR BODY MAY BE SHEAR STR	ESS ON ACTUATOR ATTACH BOLT HOLES DUE TO HIGH NR OF GEAR CYCLES.  INSP OF RT GEAR ACT BODY, NO CRACKS OR DEFECTS.  (K)	1	H	7	1 	3O	3	O		3A17    	E286				 
2006070500006	20060705	00006	EA  	2006	7	5	2006FA0000633    	2	20051213	G	7310	LW120980170	LINE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					FUEL INJECTOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	331FC	980  				277554024				THIS PART BROKE ON THE WELDED AREA NEXT TO B-NUT.  ALL CLAMPS WERE PROPERLY LOCATED AND TIGHT.  THIS FAILURE COULD HAVE 	BEEN FROM FATIGUE CAUSED BY OVERTORQUING B-NUT TO FUEL NOZZLE.  SUGGEST PAYING ATTENTION TO PROPER TORQUE VALVES.  (K)					1	L	7	2 	3O	3	O		1A10    	1E4				 
2006071900007	20060719	00007	NM  	2006	7	19	2006FA0000645    	1	20051108	G	2620	511000	CONTROL VALVE   			BOEING	727   	72730C      	1384009	NM  	PWA   	JT8   	JT8D5       	52046	NE  					FIRE EXTINGUISH	FAILED          	B			NP1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	918UP					19008				NR 2 ENGINE FIRE EXTINGUISHING SELECTOR CONTROL VALVE FAILED TO OPEN DURING ROUTINE TESTING IAW UPS ROUTINE TASK CARD TC	 2-221-12.  THE VALVE SOLENOID HOUSING WAS  NOTED AS BEING CORRODED.  (K)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006080800075	20060808	00075	CE  	2006	8	8	2006FA0000746    	1	20051123	G	3411	7024900	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT AVIONICS BAY	DEFECTIVE       	B			BSYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	813AS					167				THE PILOTS ALTIMETER AND ALTITUDE ALERTER WERE FLAGGED AND THE OVERSPEED HORN WAS GOING OFF.  THE ADC WAS FOUND TO BE DE	FECTIVE AND REPLACED.  THE SYSTEM WAS TESTED  AND INSPECTED IAW MFG AND FOUND TO COMPLY WTH FAR 91 AND TO REMAIN RVSM CO	MPLIANT.  THERE HAS BEEN ONE PRIOR REPORT OF THE ADC FALLING ON THIS AIRCRAFT.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006081000126	20060810	00126		2006	8	10	2006FA0000754    	4	20051121	G	3417		ADC             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  						DEFECTIVE       	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	900JC					178				THE PILOTS ALTIMETER AND ALTITUDE ALERTER WERE FLAGGED AND THE OVERSPEED WARNINGS WERE GOING OFF WHILE ON THE GROUND.  T	HE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY AND TO REMAIN RV	SM COMPLIANT.  THERE HAVE BEEN NO PRIOR REPORTS OF PROBLEMS WITH THIS SYSTEM IN THIS AIRCRAFT.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006081600301	20060816	00301	EA  	2006	8	16	2006FA0000771    	2	20051115	G	8520		CRANKSHAFT      								LYC   	O540  	IO540E1B5   	41532	EA  					NR 5 ROD JOURNAL	FAILED          	H				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			SW	99	J8VAY						L1151845			APPROX 5 MILES INTO FLIGHT, FELT A SURGE FROM RT ENG, AC STARTS YAWING TO RT.  PROCEEDED TO FEATHER PROP WHICH WAS SUCCE	SSFUL AT THIS TIME, NOTICED ENGINE STOPPED TURNING.  ADVISED PASSENGERS OF SITUATION IN PREP FOR AN EMERGENCY LANDING.  	ON GROUND MAINT WAS ADVISED OF INCIDENT.  PROP WAS DIFFICULT TO ROTATE BY HAND. SPARK PLUGS WERE REMOVED FOR INTERNAL IN	SP OF CYL.  NR 6 CYL PISTON WAS FOUND STUCK IN BDC POSITION AND WAS INOPERATIVE ON ROTATION OF THE PROPELLER WHILE THE O	THER WAS OPERATIVE.  NO PHYSICAL EXTERNAL DAMAGE OR SIGNIFICANT OIL LEAK WERE NOTED.  SUSPECT POSSIBLE NR 6 CONNECTING R	OD OR CRANKSHAFT DAMAGE.  THE ENGINES WILL BE REMOVED AND RETURNED TO OVERHAULER FOR FURTHER EVALUATION.  (K)						3	O			1E4				 
2006081800151	20060818	00151	NE  	2006	8	18	2006FA0000813    	2	20050519	G	7200	70BMO35420	MODULE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	UNKNOWN         	B			ULXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	228LA					3316	9708			MO2 AND MO3 WERE REPLACED.  GROUND RUNS WERE PERFORMED.  OIL FLOW AT REAR BRG WAS MEASURED AT 180 MI.  NO FUEL OR OIL LE	AKS NOTED.  DURING PWR CHECK, AT APPROX 1000 FT AGL, (ENG CHIP) LIGHT ILLUMINATED, AFTER PILOT INITIATED LANDING.  DURIN	G DESCENT, BURNING ODOR WAS NOTED IN COCKPIT, AT APPROX 70 FT AGL (FIRE) CAUTION LIGHT ILLUMINATED.  PILOT EXITED AC WIT	H FIRE EXTING, SMOKE WAS COMING FROM ENG COWLING, NO INDICATIONS OF FLAMES OR FIRE.  INSP PRIOR TO TEARDOWN REVEALED OIL	 WAS EVIDENT AT REAR BRG AREA, ON OUTSIDE OF MO4.  NOISE CAME FROM REAR BRG AREA.  METAL CHIPS FOUND AT REAR BRG SCAVENG	E CHIP DETECTOR, IN SCREEN.  TEARDOWN COULD NOT BE COMPLETED BECAUSE REAR BRG HSG COULD NOT BE SEPARATED FROM MO3.  (K)	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006082100062	20060821	00062	NM  	2006	8	21	2006FA0000814    	1	20050111	G	5311	65176626	FRAME           			BOEING	727   	72721       	1384003	NM  	PWA   	JT8   	JT8D1       	52044	NE  					BS 950 S9-10R	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	727PX					19261				DURING SCHEDULE INSP REQUIRED BY AD, FOUND 8.5 WEB SEPARATION AT FUSELAGE BS 950, RT BETWEEN STRINGER S-9 AND S-10.  PAR	TIAL FRAME REPLACEMENT BETWEEN S-9 AND S-12 WAS ACCOMPLISHED.  INSTALLED KIT NR 65C35283-2.  ALL WORK DONE IAW DWG, SRM,	 SB, AND AD.  (K)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006091300202	20060913	00202	CE  	2006	9	13	2006FA0000873    	1	20050325	G	8011		STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	3555L					172S8865				PINION GEAR IN PIECES AND RING GEAR TEETH BROKEN. (K)						1	H	7	1 	3O			NT	3A12    					 
2006091300203	20060913	00203	CE  	2006	9	13	2006FA0000875    	1	20050506	G	8011		GEAR            			CESSNA	172   	172S        	2072439	CE  										STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	3555L					172S8865				PINION GEAR SHATTERED AND RING GEAR TEETH BROKEN.  (K)						1	H	7	1 	3O			NT	3A12    					 
2006092700006	20060927	00006	CE  	2006	9	27	2006FA0000876    	1	20050916	G	8011		SHAFT           			CESSNA	172   	172S        	2072439	CE  										STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	3555L					172S8865				PINION GEAR SHAFT WEARING AND GEAR NOT RETRACTING.  (K)						1	H	7	1 	3O			NT	3A12    					 
2006092600131	20060926	00131	CE  	2006	9	26	2006FA0000956    	1	20050816	G	7713	656219B	CONTROL ARM     			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	SLIPPED         	P				E				ENGINE SHUTDOWN         				O			OTHER                     			DE	DESCENT        	1			GL	19	64793	43   	43   			E2057	688427			NOTICED WHILE DESCENDING THROUGH 5,000 FEET, THE MP WAS INCREASING AND NOT RESPONDING TO THROTTLE BACK. MP REMAINED AT 2	8 INCHES TO AIRPORT WITH THROTTLE SETTING AT IDLE.  SHUTOFF ENGINE AND LANDED.  FOUND THE NUT THAT HOLDS THE THROTTLE CO	NTROL ARM TO AIR/FUEL MIXTURE DEVICE WAS LOOSE AND THE SPLINES WERE SLIPPING.  ENGINE IS SPRING LOADED SO TO STAY AT PAR	TIAL POWER IN CASE THIS HAPPENS.  MINE FOR SOME REASON WENT TO FULL POWER.			1	L	7	1 	3O	3	O		3A15    	E3SO				 
2006020300127	20060203	00127	CE  	2006	2	3	2006RC02001      	1	20051012	G	5312	9744001967	BULKHEAD        	BEECH       	B200        	BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			18354			BB1309					(CAN) PRESSURIZATION ERRATIC IN THE AIR.  THE AIRCRAFT WAS TESTED ON THE GROUND AND LEAK WAS DETECTED WITH A 6 INCH CRAC	K LT OF THE OUTFLOW VALVE.  A REPAIR DESIGN WAS CARRIED OUT.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007030900043	20070309	00043	SO  	2007	3	9	2007FA0000212    	2	20051221	G	8540		SUMP            	CONT        	O300D       	CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	8848Z				64805D6D	17255498	64805D6D			DURING NEWLY OVERHAULED ENGINE INSTALLATION AN OIL LEAK WAS DISCOVERED.  WHEN BREAK-IN OIL WAS ADDED TO OIL SUMP FOR INI	TIAL ENGINE RUN, OIL WAS OBSERVED LEAKING ONTO NOSE TIRE.  FURTHER EXAMINATION REVEALED OIL LEAK WAS ORIGINATING FROM LE	FT REAR OF ENGINE WHERE THE OIL SUMP AND ACCESSORY HOUSING MATE TOGETHER.  CAUSE OF LEAK WAS IMPROPER SEALING OF OIL SUM	P AND ACCESSORY HOUSING DURING ASSEMBLY.			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2007061300223	20070613	00223	CE  	2007	6	13	2007FA0000408    	1	20050326	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		12898	2845 							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				 
2007061300217	20070613	00217	CE  	2007	6	13	2007FA0000422    	1	20050501	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		11150	154  							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				 
2007061300218	20070613	00218	CE  	2007	6	13	2007FA0000423    	1	20050917	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		13079	90   							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				 
2007061300212	20070613	00212	CE  	2007	6	13	2007FA0000431    	1	20050518	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		11322	1519 							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE.THE EXHAUST DUCT SB 3380 HAD NOT BEEN COMPLIED WITH.POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300211	20070613	00211	CE  	2007	6	13	2007FA0000438    	1	20050405	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		11060	442  							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE.THE EXHAUST HAD NOT HED SB 3380 COMPLIED WITH.POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300227	20070613	00227	CE  	2007	6	13	2007FA0000442    	1	20050523	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		1423 	495  							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE. EXHAUST DUCT SB HAD BEEN COMPLIED WITH 495 HOURS PRIOR. POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005041400102	20050414	00102	CE  	2005	4	14	2120003          	1	20050114	G	3246		NUT             	DUNLOP      		RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										WHEEL	BACKED OUT      	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	27	305SC				069BN061BP	258662				DURING TAXI FOR TAKEOFF, BOTH RIGHT MAIN GEAR TIRES CAME OFF OF THE WHEELS AND THE AIRCRAFT SETTLED ON THE WHEELS. BOTH 	WHEELS WERE DESTROYED. ALL WHEEL HALF BOLTS WERE LOOSE, NONE HAD NUTS INSTALLED, AND ONLY TWO NUTS COULD BE LOCATED. WHI	LE THE WHEELS ROTATED, THE LOOSE BOLTS DRAGGED ON THE BRAKE BACKING PLATES DAMAGING THEM. THE INBOARD WHEEL, INBOARD WHE	EL HALF, DEPARTED UNDER PRESSURE STRIKING THE KEELBEAM FAIRING JUST AFT OF THE ROTATING BEACON AND CONTINUED, STRIKING T	HE LEFT GEAR INBOARD WHEEL HUBCAP. THE HUBCAP AND ANTI SKID ADAPTER SLEEVE WERE BOTH DAMAGED. ONLY ONE TIRE WAS RECOVERE	D.	2	L	7	2 	4F			RT	A3EU    					 
2006012400203	20060124	00203	CE  	2006	1	24	2552             	1	20051207	G	1210		FUEL            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FUEL TANKS	CONTAMINATED    	C				D				RETURN TO BLOCK         				X			ENGINE FLAMEOUT           			TX	TAXI/GRND HDL  	1			SW	15	64LV					5600345	UNK			AC WAS LT OUTSIDE DURING COLD PERIOD, OAT 10F, ENGINES WERE STARTED, IDLED FOR 15-20 MIN TO WARM UP. UPON TAXI OUT, RT E	NGINE HAD UNCOMMANDED SHUTDOWN.  MAINT CHECKED BOTH ENGINES AND AIRFRAME FUEL FILTERS WITH NO WATER OR CONTAMINATION FOU	ND. FURTHER TESTING OF THE FUEL REVEALED A PRIST LEVEL OF .21. NORMAL LEVEL SHOULD BE .10 TO .15. FUEL TANKS WERE DRAINE	D, NEW FUEL ADDED, RUN-UP AND LEAK CHECK PERFORMED OK.  AC WAS RETURNED TO SERVICE. NOTIFIED LAST 4 FBOS OF POSSIBLE FUE	L PROBLEMS WITH THEIR FUEL.  3 OF THE FBO'S TESTED THEIR FUEL RIGHT AWAY WITH GOOD READINGS, LAST FBO WHERE FUELED CLAIM	ED THEY COULD NOT TEST THEIR FUEL. 1 WEEK LATER THAT FBO INFORMED ME THAT THEY TESTED THEIR FUEL AND IT WAS OK.	2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2005071200066	20050712	00066	SO  	2005	7	12	386506171        	1	20050701	G	2750	1763400	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					RUDDER	CUT             	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15			1100 			273645				PERFORMING AD 2003-09-13, FOUND TORQUE TUBE WORE/CUT BY LEFT RUDDER CABLE, 2 INCH LONG AND THRU TUBE WALL.  TUBE HAS BEE	N INSTALLED SINCE 1996 1100 HRS AGO. 					1	L	7	2 	3O	3	O		1A10    	1E4				 
2005042700093	20050427	00093	SO  	2005	4	27	4253620          	1	20050323	G	2560	554204	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  										SEAT BELT	CUT             	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	4161P	734  				2843309				TWO OF THE REAR SEAT BELT ATTACH CABLES HAD BEEN CUT AT MANUFACTURE.						1	L	7	1 	3O				2A13    					 
2006012400206	20060124	00206	SO  	2006	1	24	43881            	2	20051213	G	7310		FUEL LINE       			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					RT ENGINE	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1130D					3449311				THE FUEL INJECTOR LINE FROM THE FLOW DIVIDER TO THE NR3 CYLINDER ON THE RT ENGINE WAS ROUTED UNDER A COWL LATCH FOR THE 	COWLING NOSE BOWL WHICH CAUSED SEVER CHAFING IN A LOCALIZED AREA.  THIS WAS ORIGINAL FACTORY ROUTING.  NO FAILURE OCCURR	ED, PART WAS REPLACED AND DIGITAL PHOTO'S WERE PROVIDED TO MFG TECH SERVICES.				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005072000164	20050720	00164	NM  	2005	7	20	471082           	1	20050715	G	4920	38222516	TURBINE         	ALIDSG      	GTCP280     	DOUG  	MD80  	MD83        	3023681	NM  										APU	FAILED          	B			ZN3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	07					P80389					RECEIVED SUBJECT APU WITH A BURST IMPELLER. THE OEM HAS BEEN NOTIFIED AND IS CURRENTLY UNDER INVESTIGATION FROM HONEYWEL	L OEM. ONCE THE INVESTIGATION IS COMPLETE AN OFFICAL REPORT WILL BE SUBMITTED TO THE CUSTOMER FROM REPAIR & OVERHAUL AND	 OEM ENGINEERING.				2	L	7	2 	4F			RT	        					 
2005050300260	20050503	00260	SW  	2005	5	3	5322             	1	20050411	G	2197		WIRE            			MOONEY	M20   	M20M        	5870222	SW  										AVIONICS BLOWER	OVERHEATED      	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	03	21816					270277				AVIONICS BLOWER AND COWL FLAP BREAKER POPPED IN FLIGHT, UNABLE TO RESET. LANDING AND TAXI CIRCUITS DRAW 18 AMPS EACH AND	 WERE ROUTED THROUGH CIRCUIT BREAKER DISCONNECT WITH CONTACT RATING OF 13 AMPS EACH. THE OVERHEATED CONNECTION MELTED IN	SULATION ON SURROUNDING WIRES SHORTING LANDING AND TAXI LIGHT CIRCUIT TO AVIONICS BLOWER AND COWL FLAP ACTUATOR CIRCUIT.	 CORRECTIVE ACTION WAS TO REMOVE DAMAGED WIRES AND CONTACT, THEN ROUTE LANDING AND TAXI LIGHT CIRCUITS THROUGH MULTIPLE 	CONTACTS TO INCREASE CURRENT CAPABILITY.		1	L	7	1 	3O			RT	2A3     					 
2005052400296	20050524	00296	CE  	2005	5	24	5330             	1	20050509	G	5340	965630045	BRACKET         			CESSNA	500   	550         	2076604	CE  										NLG WW	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	52RF	7908 				5500021				AVIONICS SHELF BRACKET CRACKED, LOCATED IN NOSE AVIONICS COMPARTMENT ON RT SIDE OF NOSE WHEEL WELL, FRAME STA 50.  REPLA	CED BROKEN ANGLE BRACKET WITH NEW BRACKET FROM THE MFG.  METHOD OF PREVENTION IS UNKNOWN.					1	L	7	2 	4F				A22CE   					 
2005120200149	20051202	00149	SO  	2005	12	2	77865            	1	20051102	G	6120	C4503	FORK            	HARTZL      	HCC4YR2     	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCC4Y	HCC4YR2     	GL  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1687 			FH804			FH804		DURING OVERHAUL THE C4503 WAS FOUND TO BE CRACKED AFTER BEING MAGNAFLUXED.						1	L	7	2 	3O				A20SO   		5	C	P52GL	 
2005111000058	20051110	00058	SO  	2005	11	10	77866            	1	20051102	G	6120	C4503L	FORK            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCC4Y	HCC4YR2     	GL  	PITCH CHANGE	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03		1687 						FH892		PITCH CHANGE FORK CRACK FOUND DURING MAG-PARTICLE CHECK AT OVERHAUL (OH).						1	L	7	2 	3O				A20SO   		5	C	P52GL	 
2005051600101	20050516	00101	NM  	2005	5	16	78               	1	20050426	G	5330		SKIN            			BOEING	737   	737300      	1384610	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				DENTS AND GOUGES STA 770 - 827 STR 26 - 27 RT BELOW AFT PIT DOOR.						2	L	7	2 	4F			RT	A16WE   					 
2005052300287	20050523	00287	NM  	2005	5	23	80               	1	20050502	G	5330		SKIN            			BOEING	737   	7373L9      	1384470	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUSELAGE	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				AIRCRAFT DAMAGE BELOW AFT PIT FROM BELT LOADER BS 755-790, S-25R. LOG PAGE ITEM NR1 PG. 158526,S/O 109001, N/R 22583.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005052300137	20050523	00137	NM  	2005	5	23	81               	1	20050502	G	5311		FRAME           			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				LOWER FWD SIDE OF FRAME AT STA 616 S-16R CRACKED AT LOWER FASTENER.						2	L	7	2 	4F			RT	A16WE   					 
2005052300138	20050523	00138	NM  	2005	5	23	82               	1	20050502	G	5322		SHEAR TIE       			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				CABIN UPPER LOBE SHEAR TIE CRACKED AT BS 639 S-4L.						2	L	7	2 	4F			RT	A16WE   					 
2005052300139	20050523	00139	NM  	2005	5	23	83               	1	20050502	G	5310		CREASE BEAM     			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				R-1 SERVICE DOOR INNER CHORD CREASE BEAM HAS CORROSION THRU OUT THE BEAM.						2	L	7	2 	4F			RT	A16WE   					 
2005052300140	20050523	00140	NM  	2005	5	23	84               	1	20050502	G	5311		FRAME           			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				CRACKED FRAME AT BS 294.5, WL 208.1 FWD GALLEY DOOR.						2	L	7	2 	4F			RT	A16WE   					 
2005052300142	20050523	00142	NM  	2005	5	23	85               	1	20050502	G	5315		FLOORBEAM       			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				CORRODED AFT CABIN FLOORBEAM UPPER SKIN FROM BS 987 LBL 48.0.						2	L	7	2 	4F			RT	A16WE   					 
2005012400049	20050124	00049	WP  	2005	1	24	872SJ009         	1	20050107	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 UPPER LT SIDE FWD AND AFT OF SIXTH FLOOR SUPPORT HAS CORROSION.  GBAMC NR 4178 CLEANED, CHECKED FOUND TO BE OUT O	F LIMITS IAW DC-8 SRM 53-2-0.  REMOVED LT W/W, L/H SIDE AFT FLOOR SUPPORT AT STA 960.00 AND REPLACED FLOOR SUPPORT FITTI	NG AT STA 960.00 IAW DC-8 SRM 53-2-0.-CLOSED-				2	L	7	4 	4F			RT	4A25    					 
2005091500003	20050915	00003	GL  	2005	9	15	9132005          	1	20050914	G	5100	314	STEP            			AMTR  	LANCAR	LANCAIR     	05616TS	GL  										LT SIDE	DAMAGED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	03	1QB	3    	3    			319				RETRACTABLE STEP ASSEMBLY MECHANISM IS ATTACHED TO THE LANDING GEAR STRUT BY A STEEL BRAIDED CABLE WITH METAL CLAMP.  CL	AMP AROUND STRUT ROTATED ALLOWING EXCESSIVE SLACK IN THE CABLE.  WHEN THE LT LANDING GEAR WAS EXTENDED IT CAME IN CONTAC	T WITH THE RETRACTABLE STEP ASSEMBLY AND WOULD NOT ALLOW THE LANDING GEAR TO LOCK IN THE DOWN POSITION.				1	L	7	1 	3O			RT	EXPA1L71					 
2005050500008	20050505	00008	EA  	2005	5	5	A6WA200540124    	1	20050325	G	5330		SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUSELAGE	SCRATCHED       	A			A6WA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	415AW					7593				2 SCRATCHES IN FUSELAGE AT CARGO DOOR CUT-OUT, (APPROX 1 INCH LONG AND .5 INCH LONG.) PERFORMED A MAJOR REPAIR AT FS 549	, STR 14-16 IAW EO.  (K)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005051100256	20050511	00256	GL  	2005	5	11	AHDR051179       	1	20050418	G	3110	70000004002	DISPLAY         			CIRRUS	SR    	SR22        	2130001	GL  										INSTRUMENT PANEL	SMOKE           	B			AHDR	O				OTHER                   				B	S		SMOKE/FUMES/ODORS/SPARKS  	AFFECT SYSTEMS            		CR	CRUISE         	1			EA	13	816CD	217  				0150				PILOT REPORTED SMOKE COMING FROM INSTRUMENT PANEL ABOVE MFD.  DISPLAY WENT BLANK AND SMOKE CONDITION ENDED.  AIRCRAFT WA	S NEARING DESTINATION SO PILOT CONTINUED TO LANDING.  ON SHORT FINAL MFD CAME BACK ON.  UNIT REMOVED AND RETURNED TO MFG	 FOR INSPECTION AND REPAIR.  MFG DID NOT PROVIDE DETAILS OF FINDINGS.				1	L	7	1 	3O			NT	A00009CH					 
2006022100170	20060221	00170	SW  	2006	2	21	ALGA106654       	1	20051029	G	6220	406310	PITCH LINK      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	BINDING         	B			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	527AL	596  				53211				BINDING AND AXIAL PLAY BEYOND MAX. / REPLACED BY FIELD MAINTENANCE.						1	G	7	1 	3U			O	H2SW    					 
2005042000043	20050420	00043	SO  	2005	4	20	AMCR200500001    	1	20050315	G	5755	1159CS55403102	PANEL           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										SPOILER	DAMAGED         	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	250DV	1008 				691				DURING MAINTENANCE WITH HYDRAULIC MULE RUNNING, MAINTENANCE PERSONNEL NOTICED THE RIGHT WING FLIGHT SPOILERS EXCESSIVELY	 SUCKED DOWN, CAUSING OIL CANNING WHICH CAUSED THE AFT TIPS OF THE BOARDS TO CURL UP.  MANUFACTURER WAS CALLED AND CREW 	WAS SENT TO INVESTIGATE.  AILERON SYSTEM WAS IN RIG, HOWEVER DURING FLIGHT SPOILER RIGGING CHECK, THE INPUT SHAFT RIG PI	NS WOULD NOT INSERT.  FOUND INPUT SHAFT OUT OF RIG AND SPOILER CONNECTING RODS OUT OF ADJUSTMENT.  NO DAMAGE TO BOARDS O	CCURRED.  INVESTIGATION REVEALED SYSTEM WAS RECENTLY RIGGED BY MANUFACTURER'S SERVICE CENTER AFTER FLIGHT SPOILER ACTUAT	OR WAS REMOVED AND REPLACED.	2	L	7	2 	4F			RT	A12EA   					 
2005050300214	20050503	00214	EU  	2005	5	3	AMCR200500002    	1	20050331	G	4930		MOTOR           			BRAERO	DH125 	BAE125800A  	1500285	EU  										BOOST PUMP	OVERHEATED      	B			AMCR	C	F	E		ABORTED TAKEOFF         	ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         		J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	09	527AC	1445 				258104				ON TAKE-OFF ROLL, CREW GOT AN APU FIRE IND, BOTH BELL, ANNUNCIATION. WITH APU MASTER SWITCH ALREADY OFF, FIRED EXTINGUIS	HER, EXITED RUNWAY, STOPPED. WITH FIRE ANNUN STILL ILLUMINATED AN EVAC TOOK PLACE. CLEARED AC, BATTERY PWR WAS TURNED ON	, FIRE ANNUNCIATION WAS GONE. NO IND THAT ACTUAL FIRE TOOK PLACE. AC WAS TOWED BACK TO HANGAR. AFTER THOROUGH INVESTIGAT	ION, MAINT FOUND THAT APU FUEL BOOST PUMP MOTOR HAD OVERHEATED. WITH MOTOR COVER REMOVED, REAR BRG/BRUSH AREA WAS MILDLY	 CHARRED.  EVIDENCE OF POSSIBLE FUEL MIGRATION INTO MOTOR. CHECKS OF ALL APPLICABLE COMPONENTS, AC WAS OPERATED, TEST-FL	OWN WITH NO FURTHER PROBLEMS. ESTIMATED TIME FIRE WARNING TOOK PLACE AFTER APU WAS SHUTDOWN WAS ABOUT 4 MINUTES.	2	L	7	2 	4F			RT	A3EU    					 
2005052500205	20050525	00205	SO  	2005	5	25	AMCR200500004    	1	20050510	G	3340	3019941	STROBE          			GULSTM	G1159 	GIV         	3980115	SO  										LT WING	ARCED           	B			AMCR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	09	523AC	431  				1528				AN OPERATIONAL CHECK FOUND LT WING STROBE INOP.  TROUBLESHOOTING FOUND STROBE LAMP UNIT TO BE ARCING INSIDE OF CASE.						2	L	7	2 	4F			RT	A12EA   					 
2005061400026	20050614	00026	SO  	2005	6	14	AMCR200500005    	1	20050526	G	2752	1159SCC21216	JACKSCREW       			GULSTM	G1159 	GIV         	3980115	SO  										TE FLAPS	SHEARED         	B			AMCR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	09	523AC	469  				1528				AFTER TAKEOFF, CREW RECEIVED A FLAP ASYMMETRY MESSAGE DURING FLAP RETRACTION FROM 10 DEG TO 0 DEG.  MAINTENANCE FOUND TH	E RIGHT-OUTBOARD FLAP ACTUATOR TO HAVE THE SMALL SHAFT THAT DRIVES THE ASYMMETRY SWITCH SHEARED.  NO INDICATION WHY SHAF	T SHEARED, SINCE ROTARY SWITCH SEEMS TO OPERATE OK.  ACTUATOR AND SWITCH WAS REPLACED.				2	L	7	2 	4F			RT	A12EA   					 
2005072500022	20050725	00022	EU  	2005	7	25	AMCR200500006    	1	20050721	G	5610	24016335	WINDSHIELD      			BRAERO	DH125 	BAE125800A  	1500285	EU  										COCKPIT	FAILED          	B			AMCR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	09	526AC	2036 				258169				CREW GOT A WINDSHIELD OVERHEAT INDICATION. UPON RETURN, CONTINUITY CHECK FOUND LEFT WINDSCREEN'S NORMAL SENSOR OPEN. REP	LACED WINDSHIELD.					2	L	7	2 	4F			RT	A3EU    					 
2005090200011	20050902	00011	NE  	2005	9	2	AMCR200500007    	1	20050829	G	5344	7620902019045	ATTACH FITTING  			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6*        	52043	EA  					MLG DOOR	BROKEN          	B			AMCR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	09	520AC	2027 				760380				AFTER LANDING, CREW FOUND RT MAIN GEAR DOOR RESTING ON LANDING GEAR.  FOUND DOOR ATTACH BRACKET BROKEN.						1	G	7	2 	4U	3	T		H1NE    	E2NE				 
2005092600053	20050926	00053		2005	9	26	AMCR200500008    	4	20050915	G	2210	6014303	SWITCH          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					AUTOPILOT	SEPARATED       	B			AMCR	O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	09	522AC	670  				1524				DURING CLIMB, CREW COULD NOT ENGAGE AUTOPILOT. DURING HAND FLYING, CREW GOT SEVERAL UNCOMMANDED GO-AROUND COMMANDS IN WH	ICH  COMMAND BARS WOULD POP-UP AND THROTTLES WOULD ADVANCE TO FULL POWER.  MX FOUND THE BODY OF GO-AROUND SWITCH HAD SEP	ARATED WHICH CAUSED SWITCH TO RECESS A BIT INTO THE YOKE. BECAUSE SWITCH POSTS DID NOT HAVE HEAT SHRINK ON THEM, THEY WE	RE SHORTING OUT CAUSING THE UNCOMMANDED GO-AROUND SCENERIO. MX ENSURED SHRINK TUBE WAS INSTALLED ON NEW SWITCH.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2005101300173	20051013	00173	CE  	2005	10	13	AMCR200500009    	1	20051003	G	2121	125021124	FAN             			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ44        	66000	GL  					AFT CABIN	CLOGGED         	B			AMCR	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			GL	09	179DV	382  				525A0172				WHILE THE AIR CONDITIONER WAS RUNNING, THE CREW REPORTED INADEQUATE COOLING AND A FAINT ODOR OF SOMETHING BURNING. MAINT	ENANCE FOUND THE AFT EVAPORATOR FAN WAS BARELY RUNNING.  AFTER REPLACING THE FAN, THE OLD FAN'S COVER WAS REMOVED AND A 	BIG PILE OF BRUSH DUST POURED OUT.				1	L	7	1 	4F	4	F	RT	A1WI    	E3GL				 
2005120100154	20051201	00154	SO  	2005	12	1	AMCR200500010    	1	20051129	G	5230	1159SCB2021	SEAL            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					CARGO DOOR	CHAFED          	B			AMCR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	09	522AC	804  				1524				CREW NOTED A WHISTLE FROM BAGGAGE DOOR AREA. MAINTENANCE FOUND THE BAGGAGE DOOR SEAL TORN IN THE 12 O'CLOCK POSITION. IT	 APPEARS THAT THE TOP BAYONET LATCH PLATE ON THE FUSELAGE HAD EXCESS SEALANT ON THE IB SIDE, CAUSING THE DOOR SEAL TO RU	B HARD AGAINST IT DURING DOOR CLOSING. DOOR SEAL REPLACED AND EXCESS SEALANT REMOVED FROM BAYONET PLATE. OTHER AIRCRAFT 	IN FLEET WERE INSPECTED AND NO EXCESS SEALANT WAS FOUND ON THOSE PLATES.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2005121900181	20051219	00181	GL  	2005	12	19	AMSA10280502     	1	20051028	G	5210	12545001	ACTUATOR        			CIRRUS	SR    	SR22        	2130001	GL  										ZONE 800	BROKEN          	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	31						0920				PILOT SIDE DOOR PISTON, THAT GOT DISCONNECTED, JAMMED PILOT'S CONTROL STICK. THERE IS NO WAY, THAT AC COULD BE FLOWN IN 	THIS CONDITION.  IN ORDER TO FREE CONTROLS DOOR, UPHOLSTERY HAD TO BE REMOVED PISTON ON DOOR SIDE HAD TO BE DISCONNECTED	, DOOR HAD TO BE OPENED, THEN PISTON THAT WAS CAUGHT IN CONTROL STICK COULD BE REMOVED.  AFTER REMOVAL, PLASTIC ROD END 	OF THE PISTON HAD BROKEN AND PISTON ROD HAD BENT.  AFTER INVESTIGATION, DISCOVERED, THAT PISTON PLASTIC ROD END OF BOTH 	LT AND RT DOORS HAD BEEN DAMAGED AND WERE NOT FULLY LOCKING IN POSITION.		1	L	7	1 	3O			NT	A00009CH					 
2005102800029	20051028	00029	WP  	2005	10	28	AOC05001         	1	20050418	G	6230	369D27609501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	MISINSTALLED    	B			R29R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	484					870177D				WHEN REPLACING THE SWASHPLATE ASSEMBLY. IT WAS NOTED THAT MASTINOX WAS USED INSTEAD OF MIL-P-85582 AS REQUIRED BY THE MA	NUFACTURES MAINTENANCE MANUAL.  USE OF MASTINOX WILL ALLOW THE UNIBALL TO ROTATE IN THE SWASHPLATE.  WHEN THE MAINTENANC	E FACILITY WAS CONTACTED (PRISM HELICOPTERS LTD, 12-11465 BAYNES ROAD NORTH, PITT MEADOWS AIRPORT, PITT MEADOWS, BC, AIR	 AGENCY CERTIFICATE V3Y 2B3) HAD NO APPROVED PROCEDURE TO USE MASTINOX.  HIGHLY RECOMMEND THAT ANY SWASHPLATE ASSEMBLY O	VERHAULED OR PURCHASED FROM THIS FACILITY BE INSPECTED FOR PROPER ASSEMBLY.  USE OF MASTINOX WAS PRIMARY CAUSE OF THIS D	EFECT.	1	G	7	1 	3U				H3WE    					 
2005102800042	20051028	00042	GL  	2005	10	28	AOC05002         	2	20051025	G	7250	E23062750	NOZZLE          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEPARTED        	B			R29R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	541	435  				711023D	CAE830651			UPON INSPECTION OF THE TURBINE ASSEMBLY, THE NOZZLE SHIELD DOME WAS FOUND TO BE COMPLETELY DETACHED FROM THE NOZZLE ASSE	MBLY.  APPEARS THAT NOZZLE SHIELD WAS NOT PROPERLY BRAZED IN PLACE AT MANUFACTURE.  THIS NOZZLE ASSEMBLY NOT INCLUDED IN	 CEB-A-1370R2, WHICH ADDRESSES THIS PROBLEM.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006010400116	20060104	00116	SW  	2006	1	4	AOC05003         	1	20051213	G	6210	407015001129	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	B			R29R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	2869F	291  				53623				DURING A 300 HR INSPECTION, A 1.2500 INCH CRACK WAS DISCOVERED ON THE LEADING EDGE ABRASION STRIP AT APPROXIMATLEY BLADE	 STATION 133.5.   BLADE SENT TO BHTI FOR REPAIR.					1	G	7	1 	3U			O	H2SW    					 
2006012400208	20060124	00208	SW  	2006	1	24	AOC05004         	1	20051213	G	6220	407310104105	SPRING          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ROTOR HEAD	BROKEN          	B			R29R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	2869F	291  				53623				DURING A 300 HR INSPECTION, A LEAD/LAG DAMPER SPRING WAS FOUND BROKEN IN 2 PLACES. JUDGING FROM THE BREAK LINES, THE SPR	ING HAD BEEN CRACKED FOR SOME TIME.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005080900063	20050809	00063	EU  	2005	8	9	AS350B2BELCRK    	1	20050808	G	6710	350A27145300	BELLCRANK       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TRANS DECK	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	4059W	2545 				2933				WE HAVE FOUND THIS PART TO HAVE MAINTENANCE INDUCED DAMAGE FROM DISCONNECTING THE LT FORWARD INPUT ROD AT THE PRIMARY FL	IGHT CONTROL SERVO AND ALLOWING THE ROD TO FALL FORWARD. THIS ACTION ALLOWS THE LOWER JAM NUT TO CONTACT THE BELLCRANK, 	CAUSING DAMAGE. THE MANUFACTURER STATES THAT THERE IS NO ALLOWABLE DAMAGE TO THIS PART. THE OPERATOR OF THIS AIRCRAFT HA	S A FLEET WITH THIS TYPE OF DAMAGE FOUND ON AT LEAST 5 OTHER AIRCRAFT.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005040400088	20050404	00088	WP  	2005	4	4	ASAA0580104      	1	20050215	G	5321	98391951	FLOOR PANEL     			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CABIN	DAMAGED         	A			ASAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	943AS					53018				OKC C-CHECK- PAX CABIN FLOOR PANEL PEELED.  FIBERGLASS BOND REPAIRED. (K)						2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005072200097	20050722	00097	SW  	2005	7	22	ASI200501        	1	20050715	G	6220	204012104005	PIN             	BELL        		BELL  	204   	UH1H        	1181407	SW  										ROTOR HEAD	FAILED          	B			U1DM	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	2767X	1085 	1085 		ADA6239	696664				DURING 1200 OVERHAUL OUTBOARD FITTING/STRAP PIN WAS FOUND BROKEN IN HALF. PIN HAD 1085.1 HOURS SINCE NEW. DISCOLORATION 	AND CONDITION OF BREAK INDICATES THE BREAK WAS NOT RECENT. FITTING DAMAGE BEYOND USE. STRAP ALTHOUGH DUE RETIREMENT HAS 	NO SIGNIFICANT DAMAGE. PIN WAS MISSING TWO WASHERS P/N AN816L AND SEALANT ON THE ENDS. PIN HAS A LIFE LIMIT OF 2400 HOUR	S.			1	G	7	1 	4U				EXPA1G71					 
2005072000040	20050720	00040	SW  	2005	7	20	ASI200501A       	1	20050715	G	6220	204012104005	PIN             	BELL        		BELL  	204   	UH1H        	1181407	SW  										M/R HEAD	FAILED          	B			U1DM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2767X	1085 	1085 		ADA6239	696664				DURING 1200 OVERHAUL OUTBOARD FITTING/STRAP PIN P/N 204-012-104-005, S/N DIFS12334 WAS FOUND BROKEN IN HALF. PIN HAD 108	5.1 HOURS SINCE NEW. DISCOLORATION AND CONDITION OF BREAK INDICATES THE BREAK WAS NOT RECENT. FITTING DAMAGE BEYOND USE.	 STRAP ALTHOUGH DUE RETIREMENT HAS NO SIGNIFICANT DAMAGE. PIN WAS MISSING TWO WASHERS P/N AN816L AND SEALANT ON THE ENDS	. PIN HAS A LIFE LIMIT OF 2400 HOURS.			1	G	7	1 	4U				EXPA1G71					 
2006060700001	20060607	00001		2006	6	7	AU510001434      	4	20050906	G	3417	4040831901	SENSOR          	HONEYWELL   		DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	DADC	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					94096350					(AUS) DIGITAL AIR DATA COMPUTER (DADC) PS AND PT SENSORS OUT OF TOLERANCE.(AD/SB DESC: AD/RAD/43 AMDT 5, PART 1 ) (OTHER	 CAUSE: CALIBRATION SHIFT ) (CASA# 510001434)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060700003	20060607	00003	CE  	2006	6	7	AU510001435      	1	20050206	G	5740	24300259	FITTING         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		12224								(AUS) UPPER LH REAR SPAR FITTING CRACKED. (OTHER CAUSE: MATERIAL ) (CASA# 510001435)						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
2006060700005	20060607	00005	NM  	2006	6	7	AU510001436      	1	20050906	G	2170	23404061	WATER SEPARATOR 			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					CABIN CLIMATE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIR CONDITIONING SYSTEM FORWARD WATER SEPARATOR CRACKED ALONG INBOARD WELDED SEAM. CRACK LENGTH APPROXIMATELY 50.8	MM (2IN).(OTHER CAUSE: CRACKED ALONG THE WELDED SEAM ) (CASA# 510001436)					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006060700006	20060607	00006	NM  	2006	6	7	AU510001437      	1	20050906	G	3097		TERMINAL        			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	WINDSHIELD	LOOSE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LT FRONT WINDSHIELD ANTI-ICE SYSTEM TERMINAL L1 LOOSE AND SHOWING SIGNS OF OVERHEATING. (OTHER CAUSE: VIBRATION ) 	(CASA# 510001437)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060700009	20060607	00009	EU  	2006	6	7	AU510001438      	1	20050806	G	2422	M401D4F003	RELAY           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					INVERTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY INVERTER SYSTEM TRANSFER RELAY FAILED.(OTHER CAUSE: MATERIAL ) (CASA# 510001438)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060700013	20060607	00013		2006	6	7	AU510001439      	4	20051212	G	2350	63333007	MICROPHONE      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HAND MICROPHONE SWITCH STICKING.(OTHER CAUSE: STICKY SWITCH - MATERIAL ) (CASA# 510001439)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060700017	20060607	00017	CE  	2006	6	7	AU510001440      	1	20050706	G	3230	SM50D7	RELAY           			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	DYNAMIC RELAY	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 		592  								(AUS) LANDING GEAR RETRACTION SYSTEM DYNAMIC RELAY FAULTY.(OTHER CAUSE: HIGH HOURS ) (CASA# 510001440)						1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
2006060700019	20060607	00019		2006	6	7	AU510001441      	4	20050506	G	2310		ANTENNA         			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	HF SYSTEM	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) NR 2 HF ANTENNA BROKE AT EMPENNAGE ATTACHMENT POINT.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006060700021	20060607	00021	WP  	2006	6	7	AU510001442      	1	20050606	G	7820	C16932	MUFFLER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					EXHAUST	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MUFFLER ASSEMBLY DEFORMED AROUND EXHAUST PIPE.(OTHER CAUSE: MATERIAL - POSS CHANGE IN MATL. THICKNESS ) (CASA# 510	001442)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006060700024	20060607	00024	CE  	2006	6	7	AU510001443      	1	20051212	G	5753		SKIN            			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING FLAP SKINS CRACKED. WHEN THE SKINS WERE REMOVED FOR REPLACEMENT, INTERNAL CORROSION WAS ALSO FOUND.	(OTHER CAUSE: AGE ) (CASA# 510001443)					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2006060700028	20060607	00028	SO  	2006	6	7	AU510001444      	1	20051006	G	7922	53E22144A	BYPASS VALVE    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE OIL TEMP	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		138  								(AUS) RH ENGINE OIL BYPASS VALVE (VERNATHERM) BREAKING UP IN AREA OF CIRCLIP RING. METAL CONTAMINATION OF OIL SYSTEM. (O	THER CAUSE: MATERIAL ) (CASA# 510001444)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060700031	20060607	00031	SW  	2006	6	7	AU510001445      	1	20050906	G	3213	2751501XX	CYLINDER        			SWRNGN	SA227 	SA227*      	       	SW  										MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 		17019	17019							(AUS) RH MAIN LANDING GEAR STRUT CYLINDER FAILED IN AREA OF LOWER YOKE/PISTON RETAINING RING GROOVE. STRUT COLLAPSED DUR	ING LANDING. SEE ATTACHMENTS FOR PHOTOGRAPHS OF DEFECT. (OTHER CAUSE: UNKNOWN ) (CASA# 510001445)					2	L	7	2 	4T			RT	A5SW    					 
2006060700053	20060607	00053	NM  	2006	6	7	AU510001446      	1	20051206	G	3610		RING            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					NR 1 ENGINE	DISLODGED       	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE BLEED AIR SYSTEM HIGH STAGE VALVE GATE SEALING RING DISLODGED, PREVENTING VALVE FROM FULLY CLOSING. IN	VESTIGATION FOUND THE HIGH STAGE VALVE BUTTERFLY PLATE SEALING RING CLIP FAILED ALLOWING THE SEALING RING TO JAM THE THE	 VALVE IN THE SLIGHTLY OPEN POSITION ALLOWING AIR TO BYPASS PLATE AND ACTIVATE OVERPRESSURE SWITCH WHEN THE ENGINE ACCEL	LERATED.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006060700054	20060607	00054	SO  	2006	6	7	AU510001447      	2	20051212	G	8520	655961	BOLT            			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AU	S 		288  	288  							(AUS) ENGINE INTERNAL DAMAGE. SUSPECT CAUSED BY FAILURE OF NR 5 CONNECTING ROD BOLT OR CONNECTING ROD. INVESTIGATION CON	TINUING.					1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006060700056	20060607	00056	CE  	2006	6	7	AU510001448      	1	20051212	G	5751	4019008	SPAR            			PIPER 	PA23  	PA23150     	7102303	CE  	LYC   	O540  	TIO540J2BD  	41532	EA  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		14635								(AUS) LT AILERON SPAR AND DOUBLER LOCATED BEHIND THE HINGE ATTACHMENT AND CONTROL INPUT HINGE CRACKED IN TWO PLACES. SPA	R HAD BEEN PREVIOUSLY REPAIRED. SUSPECT REPAIR WAS POORLY DESIGNED AND NOT STRONG ENOUGH. AILERON HAD BEEN REMOVED FOR A	 BEARING REPLACEMENT. (AD/SB DESC: AD/PA31/118 ) (OTHER CAUSE: HIGH HOURS - DEFICIENT REPAIR ) (CASA# 510001448)				1	L	7	2 	3O	3	O	RT	1A10    	E14EA				 
2006060700057	20060607	00057	SO  	2006	6	7	AU510001449      	1	20050605	G	3230	40336000	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DOWN LINK CRACKED. FOUND DURING INSPECTION IAW PIPER SL 1088. (AD/SB DESC: PIPER SL 1088 ) (OTHE	R CAUSE: MATERIAL - AGE - HIGH HOURS ) (CASA 510001449)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060700058	20060607	00058	EU  	2006	6	7	AU510001450      	1	20050406	G	2120		ODOR            			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) ELECTRICAL BURNING ODOR IN CABIN. INVESTIGATION CONTINUING.  (OTHER CAUSE: PENDING FINAL REPORT ) (CASA 510001450)						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006060700060	20060607	00060	SO  	2006	6	7	AU510001451      	1	20051212	G	7110		SCREW           	LYC         		PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C    	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	COWLING	BROKEN          	W				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			AU	S 										(AUS) ENGINE COWL SUPPORT BRACKET ATTACHMENT SCREW BROKEN ALLOWING SUPPORT BRACKET TO INTERFERE WITH THE NOSE LANDING GE	AR DOWN MICROSWITCH STRIKER PLATE.(OTHER CAUSE: MATERIAL ) (CASA# 510001451)					1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA	 
2006060700062	20060607	00062	SO  	2006	6	7	AU510001452      	1	20050606	G	3230	4033600	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR LINK ASSEMBLY CRACKED IN LUG AREA. FOUND DURING INSPECTION IAW PIPER SL 1088. (AD/SB DESC: PIPER	 SL1088 ) (OTHER CAUSE: HIGH HOURS ) (CASA# 510001452)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060700063	20060607	00063	NE  	2006	6	7	AU510001454      	2	20050406	G	7210	PT6T3B6	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		9000 	2249 							(AUS) COMBINING GEARBOX METAL CONTAMINATION. (CASA# 510001454)						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006060700066	20060607	00066	NM  	2006	6	7	AU510001455      	1	20051212	G	2170	M01AC0101091	SEAL            			BOEING	747   	747438      	       	NM  										MOTOR	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 		27618	9683 		0					(AUS) SMOKE ODOR ON FLIGHT DECK. ODOR DISAPPEARED WHEN THE HUMIDIFIER WAS TURNED OFF. WORKSHOP INVESTIGATION FOUND THAT 	BOTH BALL BEARINGS IN THE HUMIDIFIER ELECTRIC MOTOR ASSEMBLY PNO M01AB0101-101 HAD COLLAPSED. THIS RESULTED IN THE MOTOR	 ROTOR RUBBING ONTO THE MOTOR STATOR LEADING TO THE HEATING UP OF THE WINDINGS RESULTING IN THE ODOR. THE CAUSE OF THE C	OLLAPSED BEARINGS HAS BEEN ATTRIBUTED TO A FAULTY ROTATING LIP SEAL PNO M01AC0101-091 WHICH ALLOWED THE INGRESS OF WATER	 INTO THE UPPER AND LOWER BEARING LOCATION. SEE ATTACHMENT FOR INVESTIGATION DETAILS.(OTHER CAUSE: MATERIAL ) (CASA# 510	001455)	2	L	7	4 	4F			RT	A20WE   					 
2006060700069	20060607	00069	NM  	2006	6	7	AU510001456      	1	20051212	G	2710	550030017	ACTUATOR        			BOEING	737   	737300      	1384610	NM  										AILERONS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) RT OUTBOARD AILERON LOCKOUT ACTUATOR FAILED IN PARTLY EXTENDED POSITION. WORKSHOP INVESTIGATION OF THE ACTUATOR FO	UND INTERNAL CORROSION. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (OTHER CAUSE: MATERIAL - AGE - ENVIRONMENT ) (CASA# 51	0001456)				2	L	7	2 	4F			RT	A16WE   					 
2006060700070	20060607	00070		2006	6	7	AU510001457      	4	20051006	G	2216	AR6460M2	SERVO           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AUTOPILOT TRIM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 		50690	14046							(AUS) AUTOPILOT STABILISER TRIM SERVO FAILED. WORKSHOP INVESTIGATION FOUND ROTOR GEAR STRIPPED AND ROTOR BEARING JOURNAL	 WORN.  (OTHER CAUSE: AGE ) (CASA# 510001457)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006060700072	20060607	00072	CE  	2006	6	7	AU510001458      	1	20051212	G	5751		STRUCTURE       	BEECH       		BEECH 	76    	76          	1153005	CE  										AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		12673								(AUS) LT AND RT AILERONS PNO 105-130000-1 (LT) AND PN 105-130000-2 (RT) SPARS AND DOUBLER BRACKETS CRACKED AT PUSHROD SU	PPORT BRACKETS. FLEET INSPECTION FOUND SIMILAR CRACKING ON FOUR OF SEVEN AIRCRAFT. (CASA# 510001458)					1	L	7	2 	3O				A29CE   					 
2006060700074	20060607	00074	NM  	2006	6	7	AU510001459      	1	20050706	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENG TO XMSN	DISTORTED       	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 		270  								(AUS) ENGINE TO TRANSMISSION DRIVE SYSTEM `V` BELTS STRETCHED.(OTHER CAUSE: MATERIAL ) (CASA  510001459)						1	G	7	1 	3O	3	O		H10WE   	E274				 
2006060700076	20060607	00076	CE  	2006	6	7	AU510001460      	1	20051212	G	5751		SPAR            			BEECH 	76    	76          	1153005	CE  			            					            		AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10236								(AUS) LT AND RT AILERONS PNO 105-130000-1 (LT) AND PN 105-130000-2 (RT) SPARS AND DOUBLER BRACKETS CRACKED AT PUSHROD SU	PPORT BRACKETS. (CASA# 510001460)					1	L	7	2 	3O				A29CE   					 
2006060700077	20060607	00077	NM  	2006	6	7	AU510001461      	1	20051006	G	2910	651784961	LINE            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYDRAULIC SYS	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 		54177			0					(AUS) HYDRAULIC PIPES PNO 65-17849-61 AND PNO 65-17849-4014 RUBBING TOGETHER CAUSING ONE PIPE TO BE HOLED. LOSS OF HYDRA	ULIC FLUID. INVESTIGATION FOUND A FAILED `P` CLIP ON ONE OF THE PIPES WHICH ALLOWED THE PIPES TO RUB TOGETHER.(OTHER CAU	SE: AGE ) (CASA# 510001461)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006060700078	20060607	00078	NM  	2006	6	7	AU510001462      	1	20051212	G	2120		ODOR            			BOEING	737   	7377Q8      	1384418	NM  										CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) FAINT BURNING INSULATION ODOR. INVESTIGATIONS COULD FIND NO SOURCE OF THE ODOURS.   (OTHER CAUSE: UNABLE TO FIND A	NY FAULT ) (CASA 510001462)					2	L	7	2 	4F			RT	A16WE   					 
2006060800001	20060608	00001	WP  	2006	6	8	AU510001463      	2	20050206	G	7230	31020224	SHROUD          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE SECOND STAGE IMPELLER SHROUD MOVED FORWARD OPENING UP THE SECOND STAGE COMPRESSOR CLEARANCE AND DRAGGING TH	E OUTER TRNSITION LINER PNO 3102102-3 ONTO THE REAR FACE OF THE SECOND STAGE IMPELLER PNO 893482-5 DAMAGING BOTH PARTS. 	(AD/SB DESC: PILOT REPORTED PROBLEM TO ENGINEERING ) (OTHER CAUSE: PROCESS MISSED DURING O/H OF THE PART ) (CASA# 510001	463)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006060800002	20060608	00002	EU  	2006	6	8	AU510001464      	1	20050906	G	3200	201138002	PIN             			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NLG	INSTALLED       	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR FAILED TO RETRACT. INVESTIGATION FOUND NLG PIN STILL INSTALLED. PERSONNEL/MAINTENANCE ERROR. (CA	SA# 510001464)					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006060800004	20060608	00004	NE  	2006	6	8	AU510001465      	2	20051212	G	7250		O-RING          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					GASKET	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TURBINE REAR FRAME OIL COVER GASKET PNO 340-179-401-0 AND O-RING SEAL PNO 649-393-271-0 DETERIORATED AND LE	AKING. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA# 510001465)					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006060800006	20060608	00006	NM  	2006	6	8	AU510001466      	1	20050706	G	2822	6098976	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		33465	24529							(AUS) NO4 MAIN FUEL BOOST PUMP FAILED RESISTANCE CHECK AS PER AD/B747/173. (CASA# 510001466)						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006060800009	20060608	00009		2006	6	8	AU510001467      	4	20051206	G	2210	6355B000103	ACTUATOR        			BOEING	737   	737800*     	       	NM  										AUTOPILOT	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT STABILISER TRIM ACTUATOR MOTOR FAILED. (CASA# 510001467)						2	L	7	2 	4F			RT	A16WE   					 
2006060800011	20060608	00011	NM  	2006	6	8	AU510001468      	1	20051106	G	2742	AR7077M3	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		48216	9327 							(AUS) STABILISER ELECTRIC TRIM ACTUATOR FAILED. CAUSED BY WORN AND STICKING CLUTCH.  (OTHER CAUSE: STICKING CLUTCH PLATE	S ) (CASA# 510001468)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006060800012	20060608	00012	CE  	2006	6	8	AU510001469      	1	20051212	G	5751	1051300001	BRACKET         			BEECH 	76    	76          	1153005	CE  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10554								(AUS) LH AND RH AILERONS PNO 105-130000-1 (LH) AND PNO 105-130000-2 (RH) SPARS AND DOUBLER BRACKETS CRACKED AT PUSHROD S	UPPORT BRACKETS. (CASA# 510001469)					1	L	7	2 	3O				A29CE   					 
2006060800013	20060608	00013	EU  	2006	6	8	AU510001470      	1	20051206	G	2780	CH251040	SOLENOID VALVE  			AIRBUS	A330  	A330*       	       	EU  										SLAT CONTROL	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH SLAT SOLENOID (34CW) SHORT CIRCUITING TO CHASSIS.  (OTHER CAUSE: MATERIAL ) (CASA# 510001470)						2	L	7	2 	4F			RT	A46NM   					 
2006060800015	20060608	00015	NM  	2006	6	8	AU510001471      	1	20051212	G	2897		WIRE HARNESS    			BOEING	747   	747438      	       	NM  										FUEL INDICATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE WING TANK DAISY CHAIN HARNESS DAMAGED. HARNESS CONTAINED A SUBSTANTIAL GASH ON THE OUTER INSULATION AND INT	O THE SHIELD. THE HARNESS HAD ALSO BEEN SHARPLY KINKED AND WEAKENED IN TWO OTHER LOCATIONS. SUSPECT HARNESS DAMAGED DURI	NG PREVIOUS TANK ENTRY.  (CASA# 510001471)				2	L	7	4 	4F			RT	A20WE   					 
2006060800018	20060608	00018	NM  	2006	6	8	AU510001472      	1	20051206	G	2613		WARNING SYSTEM  			BOEING	737   	7377Q8      	1384418	NM  										OVERHEAT	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LT WING TO BODY OVERHEAT LIGHT ILLUMINATED FOLLOWING NR 2 ENGINE START. INVESTIGATION FOUND CODE 10 (LOOP 1A SHORT	ED) IN ALARM MEMORY. CODES CLEARED AND UNIT FUNCTIONED NORMALLY. (OTHER CAUSE: UNABLE TO ESTABLISH THE CAUSE ) (CASA# 51	0001472)				2	L	7	2 	4F			RT	A16WE   					 
2006060800020	20060608	00020	NM  	2006	6	8	AU510001473      	1	20051212	G	2613	M1761	DETECTOR        			BOEING	737   	7377Q8      	1384418	NM  										OVERHEAT	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 WING TO BODY OVERHEAT LIGHT ILLUMINATED. INVESTIGATION FOUND DETECTOR M1761.  (OTHER CAUSE: NOT KNOWN AT THIS	 STAGE ) (CASA# 510001473)					2	L	7	2 	4F			RT	A16WE   					 
2006060800023	20060608	00023		2006	6	8	AU510001474      	4	20051212	G	3421	40023344	LIGHT           	HONEYWELL   																INDICATOR	OPEN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					95068116					(AUS) ATTITUDE INDICATOR PANEL LAMPS ON BEZEL BLOWN. FOUND DURING INSPECTION IAW AD/RAD/043.(AD/SB DESC: AD/RAD/O43 ) (C	ASA# 510001474)																		 
2006060800026	20060608	00026	NE  	2006	6	8	AU510001475      	2	20051212	G	7230	6497823000	PIN             	GE          		BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COMPRESSOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING FAN LUBE INSPECTION OF THE FAN HUB FOUR (4) FORWARD BOOSTER SPOOL PINS WERE FOUND TO BE VISIBLY LOOSE. AFTE	R A TORQUE CHECK OF THE REMAINDER, A FURTHER FIVE (5) PINS WERE FOUND TO BE LOOSE. TOTAL NUMBER OF UNDERTORQUED PINS NIN	E (9). (OTHER CAUSE: UNABLE TO ESTABLISH THE CAUSE ) (CASA 510001475)				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006060800029	20060608	00029	SW  	2006	6	8	AU510001476      	1	20050406	G	2910	27810322682	LINE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	WORN            	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) LH ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE CHAFED AND HOLED BY OIL TANK UNION. LOSS OF HYDRAULIC PRESSURE RESUL	TED IN AN EMERGENCY LANDING. DUE TO NO HYDRAULIC PRESSURE, THE ANTISKID WAS NOT AVAILABLE AND THE BRAKES LOCKED UP. NO1,	 NO2 AND NO3 TYRES WERE FLATSPOTTED AND NO2 TYRE BLEW OUT. (CASA# 510001476)				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006060800031	20060608	00031	EA  	2006	6	8	AU510001477      	2	20050106	G	8520	6930100	ELBOW           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE OIL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							L4382627A			(AUS) RH ENGINE ACCESSORY CASE OIL INDICATOR PORT SCREW-IN ELBOW FAILED. SEE ATTACHMENT FOR PHOTOGRAPH OF FAILED ITEM. (	CASA# 510001477)					1	L	7	1 	3O	3	O		2A13    	E274				 
2006060800035	20060608	00035	NM  	2006	6	8	AU510001478      	1	20051212	G	3010	8510237002	BOOT            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HORIZONTAL STAB	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 		9271 								(AUS) RT OUTER TAILPLANE RUDDER BOOT TORN AND LIFTING IN AREA LOCATED IN FRONT OF THE ELEVATOR HORN.  (OTHER CAUSE: MATE	RIAL - ENVIRONMENT ) (CASA# 510001478)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060800037	20060608	00037		2006	6	8	AU510001479      	4	20051212	G	3413		INDICATOR       			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COCKPIT	FAULTED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LH VERTICAL SPEED INDICATOR (VSI) NEEDLE FLUCTUATING. GROUND TEST COULD FIND NO FAULTS WITH THE SYSTEM. NO FURTHER	 REPORTS OF PROBLEMS. (OTHER CAUSE: UNKNOWN ) (CASA# 510001479)					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006060800038	20060608	00038	EU  	2006	6	8	AU510001480      	1	20050405	G	2150	11341041	MOTOR           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	A/C PACK	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			651  							(AUS) REAR AIR CONDITIONING SYSTEM ELECTRIC MOTOR FAILED. (CASA# 510001480)						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006060800040	20060608	00040	EU  	2006	6	8	AU510001481      	1	20051212	G	5753	3019	NIPPLE          	MENASCO     		FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					TE FLAPS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					MC001					(AUS) FLAP BALL NUT GREASE NIPPLE MISSING.(OTHER CAUSE: UNKNOWN ) (CASA# 510001481)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800061	20060608	00061	CE  	2006	6	8	AU510001482      	1	20051212	G	5751	1051300002	SPAR            			BEECH 	76    	76          	1153005	CE  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		9707 								(AUS) RT AILERON UPPER DOUBLER AND SPAR CRACKED. CRACK LENGTHS 10MM (0.39IN) IN DOUBLER AND 5MM (0.196IN) IN SPAR. (CASA	# 510001482)					1	L	7	2 	3O				A29CE   					 
2006060800063	20060608	00063	GL  	2006	6	8	AU510001483      	3	20050906	G	6111		BLADE           			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BLADE TIP SEPARATED IN FLIGHT. APPROXIMATELY 228.6 (9IN) OF BLADE SEPARATED. SEVERE VIBRATION CAUSED ENG	INE TO SEIZE DURING EMERGENCY LANDING. AIRCRAFT IS REGISTERED AND OPERATING IN CANADA. (CASA# 510001483)					1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2006060800064	20060608	00064	NM  	2006	6	8	AU510001484      	1	20051212	G	2910		HYDRAULIC SYSTEM			BOEING	737   	737800*     	       	NM  										B SYSTEM	LOW PRESSURE    	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC B-SYSTEM LOW PRESSURE. INVESTIGATION CONTINUING. (CASA# 510001484)						2	L	7	2 	4F			RT	A16WE   					 
2006060800065	20060608	00065	NM  	2006	6	8	AU510001485      	1	20051212	G	2170		HUMIDIFIER      			BOEING	747   	747400      	       	NM  										CABIN CLIMATE	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) SMOKE ON FLIGHT DECK WHEN HUMIDIFIER ACTIVATED. SMOKE STOPPED WHEN HUMIDIFIER SWITCHED OFF. AIRCRAFT IS FOREIGN RE	GISTERED. (OTHER CAUSE: UNKNOWN ) (CASA# 510001485)					2	L	7	4 	4F			RT	A20WE   					 
2006060800066	20060608	00066	SO  	2006	6	8	AU510001486      	2	20051212	G	8520		CRANKCASE       			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	2A34C	E2A34C70    	GL  	ENGINE	DAMAGED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AU	S 										(AUS) CRANKCASE HOLED. LOSS OF POWER IN NR 4 AND NR 6 CYLINDERS. (CASA# 510001486)						1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P3EA	 
2006060800067	20060608	00067	GL  	2006	6	8	AU510001487      	3	20051006	G	6111		BLADE           			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		986  	218  					983124		(AUS) PROPELLER BLADE CRACKED SPANWISE ON THE LEADING EDGE APPROXIMATELY 140MM (5.5IN) FROM BLADE TIP. FURTHER INVESTIGA	TION FOUND SEVERE INTERNAL EXFOLITAION CORROSION. THE SAME PROPELLER HAD A SIMILAR DEFECT APPROXIMATELY 50 HOURS PREVIOU	S.  (CASA# 510001487)				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2006060800074	20060608	00074	SO  	2006	6	8	AU510001488      	2	20051212	G	8530	AEC631397	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		89   								(AUS) ENGINE CYLINDER HEAD SEPARATED FROM BARREL. SUSPECT DEFECTIVE CASTING. (OTHER CAUSE: IT`S FAIRLY OBVIOUS THAT CAST	ING WAS DEFECTIVE ) (CASA# 510001488)					1	H	7	1 	3O	3	O		A4CE    	E3SO				 
2006071900075	20060719	00075	SO  	2006	7	19	AU510001489      	2	20051212	G	8520	643503	BEARING         			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1206 					272465			(AUS) ENGINE METAL CONTAMINATION. WORKSHOP STRIP AND INVESTIGATION FOUND NR 2 AND NR 3 MAIN BEARINGS FAILED. BEARING SHE	LLS BROKE UP CAUSING DAMAGE TO CRANKCASE AND SEVERE DAMAGE TO CRANKSHAFT WITH CRACKING ON JOURNALS.  (CASA NR 510001489)					1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006071900076	20060719	00076	SW  	2006	7	19	AU510001490      	1	20051212	G	3310	271911583	PANEL           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	COCKPIT	BURNED OUT      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) NON-ESSENTIAL BUSS PANEL BACKLIGHTING SHORT CIRCUITED INTERNALLY DUE TO CORROSION CAUSED BY MOISTURE INGRESS. HEAT	 BUILDUP IN PANEL CAUSED OVERHEATING AND SMOKE IN COCKPIT. (CASA NR 510001490)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006060700083	20060607	00083	SW  	2006	6	7	AU510001491      	1	20051212	G	5610	262113E19	WINDSHIELD      			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CA											LT WINDSHIELD SEVERELY CRACKED.  RT WINDSHIELD SEVERELY DELAMINATED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006060800076	20060608	00076	NM  	2006	6	8	AU510001492      	1	20051212	G	5330		SKIN            			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					BS 822	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					CABIN WING CENTER SECTION UPPER SKIN PANEL CORRODED.  PANEL IS LOCATED AT FS 822 RBL12.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006060800077	20060608	00077	NE  	2006	6	8	AU510001493      	2	20051212	G	7261		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	OIL SYSTEM	LOW PRESSURE    	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							PCEPS114292			RT ENGINE LOST OIL PRESSURE.  ENGINE SHUT DOWN WHEN OIL PRESSURE DROPPED TO 60 PSI.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006060800079	20060608	00079		2006	6	8	AU510001494      	4	20051212	G	2215	65000560059	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AUTOPILOT	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			39   							AUTOPILOT PITCH ACTUATOR INCORRECT OPERATION.  ACTUATOR HAD BEEN MODIFIED IAW HONEYWELL SB KSA372-M1 TO COMPLY WITH PILA	TUS SB 22-004 AND AD/PC12/39A1.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006060800080	20060608	00080	EU  	2006	6	8	AU510001495      	1	20051212	G	3234	643500100	SELECTOR        			BAG   	BAE146	BAE146300A  	1500267	EU  										MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										LANDING GEAR SELECTOR LEVER WOULD NOT MOVE TO THE `UP` POSITION.						2	H	7	4 	4F			RT	A49EU   					 
2006060800081	20060608	00081	NM  	2006	6	8	AU510001496      	1	20051212	G	2781	189929	SENSOR          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					SLATS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 LEADING EDGE FLAP RETRACTION SENSOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006060800082	20060608	00082	EU  	2006	6	8	AU510001497      	1	20051212	G	3213	201072013	STRUT           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT MAIN LANDING GEAR STRUT INTERNAL SLEEVE MIGRATED OUT OF POSITION AND BLOCKED BLEED PLUG HOLE, FOUND DURING INSPECTION	 IAW AD/F100/64.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800083	20060608	00083	EU  	2006	6	8	AU510001498      	1	20051212	G	3213		STRUT           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT MAIN LANDING GEAR STRUT BLEED PORT CRACKED, FOUND DURING INSPECTION IAW AD/F100/64.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800138	20060608	00138	NM  	2006	6	8	AU510001499      	1	20051212	G	2822		PUMP            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL BOOST	CAVITATES       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CENTER FUEL TANK PUMPS CAVITATES.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800139	20060608	00139	NM  	2006	6	8	AU510001500      	1	20051212	G	5620	657676510	SEAL            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					WINDOW	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FOUND CABIN WINDOW 15A INNER AND OUTER PANES TOUCHING AND FULL OF WATER.  INVESTIGATION FOUND SEAL LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800141	20060608	00141	NM  	2006	6	8	AU510001501      	1	20051212	G	2897		WIRE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL SYSTEM	DAMAGED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										NR 2 AFT FUEL PUMP LOW PRESSURE LIGHT ILLUMINATED AND CIRCUIT BREAKER TRIPPED.  INVESTIGATION FOUND FUEL PUMP WIRING BAD	LY BURNT AT EARTH PIG TAIL FERRULE.  IT APPEARS THAT WHEN THE WIRING HARNESS WAS MANUFACTURED, ONE OR ALL THREE PHASE PO	WER WIRES TO THE PUMP WERE CUT DURING THE CRIMP PREPARATION.  WHEN THE EARTH PIG TAIL FERRULE FOR THE METAL SHEATH OVER 	THE TOP OF THE THREE PHASE WIRES WAS CRIMPED, IT PROVIDED A PATH TO SHORT THE THREE PHASE WIRES TO EARTH.  SUSPECT MANUF	ACTURING ERROR.		2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800142	20060608	00142	NM  	2006	6	8	AU510001502      	1	20051212	G	5320	145T252422	STRAP           			BOEING	767   	767277      	1385128	NM  	GE    	CF6   	CF680A      	30025	NE  					BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		51129	11383							REAR SPAR BULKHEAD SIDE FITTING RT FAIL/SAFE STRAP CRACKED.  STRAP IS LOCATED AT SECTION 45 STN 955.  FOUND DURING INSPE	CTION IAW AD/B767/201, BOEING ALERT SB 767-53A0100 AND AAES AD ER B76-53-10-39A.  FURTHER INVESTIGATION ALSO FOUND CORRO	SION ON THE RT LONGERON CHORD, PRESSURE DECK CLOSEOUT `T` FITTING.  THE AIRCRAFT SKIN AND THE FACE OF THE FAIL/SAFE STRA	P ABUTTING THE SKIN, TO ASSESS THE EXTENT OF CORROSION ON THE FACE OF THE FAIL/SAFE STRAP.  THE RT WING REAR SPAR UPPER 	KICK FITTING WAS REMOVED.  ON REMOVAL CORROSION WAS ALSO FOUND ON THE ABUTTING FACE OF THE KICK FITTING.		2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006061900174	20060619	00174	EA  	2006	6	19	AU510001503      	2	20050606	G	7310	6158124A	LINE            			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL SYS	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			252  							(AUS) RT ENGINE NR 2 CYLINDER FUEL INJECTOR LINE BROKEN AT NIPPLE. (CASA NR 510001503).						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P25EA	 
2006060800143	20060608	00143	SO  	2006	6	8	AU510001504      	1	20051212	G	5280	110272407	DOOR            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 		22242								RT MAIN LANDING GEAR INBOARD DOOR MISSING.  HINGES AND DOOR OPERATING RODS BROKEN.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006060800146	20060608	00146	NM  	2006	6	8	AU510001505      	1	20051212	G	3810	288237	COMPRESSOR      			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					POTABLE WATER	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			AU	S 		4178 	4178 							FUMES IN CABIN PRIOR TO BOARDING. INVESTIGATION FOUND POTABLE WATER COMPRESSOR EXTREMELY HOT.  INVESTIGATION FOUND THAT 	ON REMOVAL OF THE CAPS AND COVER BOTH STAGES HAD WATER IN BELLOWS AND VALVES.  THE SECOND STATE (HIGH-PRESSURE) REED WAS	 FRACTURED AT THE OUTPUT AND THE DRIVE SLIPS OFF THE CAMS.  THE OVER-PRESSURE BALL VALVE WAS STAINED FROM WATER AND HAD 	MULTIPLE SET MARKS INDICATING THAT THE UNIT HAD BEEN OVER PRESSURIZED.  THE MOTOR STATOR AND ROTOR WAS BURNT WHICH WOULD	 HAVE CAUSED THE BURNING SMELL IN THE CABIN.  THE UNIT HAD INGESTED WATER AND WAS DAMAGED BEYOND ECONOMICAL REPAIR.		2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006060800333	20060608	00333	NM  	2006	6	8	AU510001506      	1	20050306	G	3520		PIN             			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					PAX OXYGEN	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PASSENGER OXYGEN GENERATOR BAND CLAMP PIN LOCKS MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006060800338	20060608	00338	NM  	2006	6	8	AU510001507      	1	20051006	G	3610	2780539103	VALVE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PNEUMATIC DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		43664	7035 							LT BLEED ISOLATION VALVE FAULTY.  WORKSHOP INVESTIGATION FOUND THE FAILURE WAS DUE TO AN WORN AND INOPERATIVE MOTOR ASSE	MBLY.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006060800339	20060608	00339	NM  	2006	6	8	AU510001508      	1	20051206	G	2822	5006003C	PUMP            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		61686	2132 							RT FORWARD BOOST PUMP TRIPPED CIRCUIT BREAKER WHEN PUMP SWITCHED `ON`.  INVESTIGATION FOUND THE BOOST PUMP FAILED.  WORK	SHOP INSPECTION FOUND THAT THE IMPELLER FINS HAD EXCESSIVE WEAR FROM RUBBING IN THE PUMP HOUSING.  THE HOUSING ALSO HAD 	SEVERE EROSION ON THE STRUT AREAS AND EXCESSIVE WEAR IN THE IMPELLER BORE INSIDE DIAMETER.  THE PUSH ROD, INSTALLED EXTE	RNALLY, WAS ALSO FOUND TO BE BENT.			2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006060800340	20060608	00340	CE  	2006	6	8	AU510001509      	1	20051212	G	2721	1015240895	CABLE           			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT642A      		NE  					RUDDER TAB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1020 								RUDDER TAB CONTROL CABLE OVERRAN RUDDER TAB ACTUATOR CABLE DRUM.  INVESTIGATION FOUND THE CABLE RIGGING WAS OUT OF ADJUS	TMENT.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060800373	20060608	00373	CE  	2006	6	8	AU510001510      	1	20051212	G	5415	10598000023	BRACKET         			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  					RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE FIREWALL BRACKET CRACKED ON BOTH SIDES OF ANCHOR NUT.  FOUND DURING INSPECTION IAW AD/BEECH76/10-2.						1	L	7	2 	3O	3	O		A29CE   	E286				 
2006062100002	20060621	00002	NE  	2006	6	21	AU510001511      	2	20051212	G	8530	25717	MANIFOLD        			CVAC  	PBY6  	PBY6ABABB   	2421302	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E51       	NE  	CYLINDER	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 										(AUS) RT ENGINE NR 9 CYLINDER INDUCTION MANIFOLD SEPARATED FROM CYLINDER AND WAS FOUND LAYING IN THE LOWER COWL FLAP ARE	A. INVESTIGATION FOUND THE MANIFOLD ATTACHMENT NUT HAD BACKED OFF ALLOWING THE MANIFOLD TO PULL OUT OF THE CYLINDER AND 	REAR CASE. (CASA NR 510001511)				2	H	7	2 	4R	4	R		AR22    	5E4	6	C	P603	 
2006060800374	20060608	00374	EU  	2006	6	8	AU510001512      	1	20050106	G	7830		SOLENOID        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					THRUST REVERSER	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 ENGINE THRUST REVERSER SECONDARY LOCK SOLENOID BINDING IN LAST 2MM (0.078IN) OF TRAVEL.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800375	20060608	00375		2006	6	8	AU510001513      	4	20050406	G	2210		TRIM SWITCH     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AUTOPILOT SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 TRIM SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800376	20060608	00376		2006	6	8	AU510001514      	4	20050106	G	3160		DISPLAY         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										MULTI FUNCTION DISPLAY UNIT (MFDU) FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800377	20060608	00377	EU  	2006	6	8	AU510001515      	1	20050806	G	5330		SKIN            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUSELAGE	LIGHTNING STRIKE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					LIGHTNING STRIKE ON FUSELAGE WITH EXIT HOLE FOUND IN RT ELEVATOR TRAILING EDGE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800378	20060608	00378	EU  	2006	6	8	AU510001516      	1	20050806	G	7830		RELAY           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					THRUST REVERSER	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										NR 2 THRUST REVERSER RELAY FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300048	20060613	00048	EU  	2006	6	13	AU510001517      	1	20050806	G	3260	858202	PSEU            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  						FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PROXIMITY SYSTEM ELECTRONIC UNIT (PSEU) INTERMITTENT OPERATION.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300049	20060613	00049		2006	6	13	AU510001518      	4	20051106	G	2211		COMPUTER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AUTOPILOT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										AUTOPILOT COMPUTER INTERMITTENT FAULT.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300052	20060613	00052	NM  	2006	6	13	AU510001519      	1	20051212	G	5310		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 		54209								NR 3 CARGO DOOR LOWER FORWARD FRAME RADIUS AND `T` FRAME CRACKED THROUGH THREE FASTENER HOLES.  FOUND DURING INSPECTION 	IAW SB 727-52-0149.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061300054	20060613	00054	CE  	2006	6	13	AU510001520      	1	20051212	G	2612	356043255	WIRE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FIRE DECTECTOR	UNSERVICEABLE   	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										E36 FIRE WIRE ELEMENT LOCATED IN FORWARD WING TO FUSELAGE AREA UNSERVICEABLE.  NO PHYSICAL DAMAGE COULD BE FOUND.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006061300055	20060613	00055	EU  	2006	6	13	AU510001521      	1	20051212	G	4940	CH34313	IGNITER         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					APU	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										APU IGNITER PLUG FAILED.  WORKSHOP INVESTIGATION FOUND THAT ONLY APPARENT FAULT WAS SLIGHT SOILING ON THE CERAMIC INSIDE	 OF THE CONNECTOR END OF THE IGNITER.  THERE WAS NO OBVIOUS SIGN OF ARCING ACROSS THE CERAMIC SURFACE. WHEN THE IGNITER 	WAS CLEANED, THERE WAS NO OTHER SIGNS OF A DEFECT.  THE IGNITER WAS CONNECTED TO THE LEAD ON AN OPERATIONAL APU AND RUN 	THROUGH THE START CYCLE WITH THE APU FUEL TURNED OFF.  THE IGNITER FIRED CORRECTLY AND WITHOUT ANY SIGN OF FAILURE FOR T	HE ENTIRE CYCLE.		2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300225	20060613	00225	EU  	2006	6	13	AU510001522      	1	20051212	G	5270	893301	PROXIMITY SENSOR			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					CARGO DOOR	FALSE INDICATION	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										AFT CARGO DOOR OPEN INDICATION.  INSPECTION FOUND THE DOOR SECURE.  SUSPECT FAULTY SENSOR.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006061300264	20060613	00264	NM  	2006	6	13	AU510001523      	1	20051212	G	2913	21830	BEARING         			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HYDRAULIC PUMP	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		13168			0					HYDRAULIC SYSTEM `A` ELECTRIC PUMP FAILED.  INVESTIGATION FOUND THE FAILURE WAS CAUSED BY FAILURE OF THE PRE-MOD SB 5718	6-29-291 TRUNNION NEEDLE BEARING.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300265	20060613	00265	NM  	2006	6	13	AU510001524      	1	20051212	G	2424	948F4583	GCU             			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AC SYSTEM	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			AU	S 		53507	5861 							NR 1 GENERATOR CONTROL UNIT (GCU) FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061300266	20060613	00266	NE  	2006	6	13	AU510001525      	2	20051212	G	7320	1853M56P09	HMU             			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NR 1 ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		6798 								NR 1 ENGINE HYDROMECHANICAL UNIT (HMU) FAULTY.  INVESTIGATION FOUND THE DEFECT WAS CAUSED BY FAILURE OF THE FMV RESOLVER	 BODY ASSEMBLY.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300267	20060613	00267	NM  	2006	6	13	AU510001526      	1	20051212	G	3246	101376	WHEEL           	BFGOODRICH  		BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										MAIN WHEEL INNER HUB CRACKED APPROXIMATELY 35MM (1.377IN) BELOW THE MATING FACE AND EXTENDING THROUGH TO THE OUTSIDE OF 	THE HUB AT THE TIE BOLT HOLE SEAT RADIUS.  CRACK LENGTH 18MM (0.708IN).  CRACK IS LOCATED OUTSIDE OF AREAS LAID DOWN IN 	THE MAINTENANCE MANUAL.  FOUND USING EDDY CURRENT INSPECTION.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061300269	20060613	00269	NM  	2006	6	13	AU510001527      	1	20051212	G	5312		PRESSURE PANEL  			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					FUSELAGE STRUCTURE PRESSURE WEB CORRODED.  WEB IS LOCATED AT FS 46 IN THE MAIN LANDING GEAR WHEEL WELL.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061300270	20060613	00270	NM  	2006	6	13	AU510001528      	1	20051212	G	5330		BEAR STRAP      			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 3 CARGO DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					NR 3 CARGO DOOR BEAR STRAP INNER SURFACE CORRODED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061300271	20060613	00271	CE  	2006	6	13	AU510001529      	1	20050906	G	3260		UPLOCK SWITCH   			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		417  								LT MAIN LANDING GEAR MICROSWITCH DAMAGED INTERNALLY.						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006061300272	20060613	00272	CE  	2006	6	13	AU510001530      	1	20051212	G	3260	602EN556B	UPLOCK SWITCH   	CESSNA      		CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		14   								LT MAIN LANDING GEAR UPLOCK MICROSWITCH FAULTY.						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006061400100	20060614	00100	CE  	2006	6	14	AU510001531      	1	20051212	G	2150	4764HD	COMPRESSOR      			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	A/C PACK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CABIN AIRCONDITIONING COMPRESSOR FAILED.  FLUID LEAKING FROM REAR CASE AND ALL COVER BOLTS LOOSE.  REAR COVER WAS REMOVE	D AND INTERNAL DAMAGE FOUND.  SUSPECT DAMAGE CAUSED BY INCORRECT ROTATION OF COMPRESSOR DUE TO THIS MODEL OF COMPRESSOR 	NOT BEING MANUFACTURED TO ROTATE IN A COUNTERCLOCKWISE DIRECTION.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006061400127	20060614	00127	EU  	2006	6	14	AU510001532      	1	20051212	G	5320		PLATE           			BAG   	JETSTM	JETSTM3107  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	BS 223	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		32241								PASSENGER CUTOUT INTERCOSTAL UPPER JOINT PLATE LOCATED AT FS 223 LT CRACKED.  FOUND DURING INSPECTION IAW AD/JETSTREAM/9	8 AND SB51-JA030544 R1.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2006061400128	20060614	00128	EU  	2006	6	14	AU510001533      	1	20050107	G	2760	A16160431	PUSHROD         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					SPOILER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 RT INBOARD LIFT DUMPER BELLCRANK PUSHROD CRACKED IN TWO PLACES.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061400130	20060614	00130	EU  	2006	6	14	AU510001534      	1	20051212	G	7797		CONNECTOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ENGINE	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										ENGINE INDICATION SYSTEM PRESSURE BULKHEAD CONNECTOR P2874 LOOSE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061400132	20060614	00132	GL  	2006	6	14	AU510001535      	1	20051212	G	5740		ATTACH FITTING  			NAMER 	T6    	T6G         	6400432	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										EDDY CURRENT INSPECTION OF WING ATTACHMENT FITTINGS FOUND CRACK INDICATIONS.  FURTHER TESTING USING FLUORESCENT PENETRAT	ION FAILED TO DETECT THE CRACK.  FOUND DURING INSPECTION IAW AD/AT-6/1.					1	L	7	1 	3R	3	R		A2575   	5E2	5	C	P257	 
2006061400136	20060614	00136	GL  	2006	6	14	AU510001536      	1	20051212	G	5740		ATTACH FITTING  			NAMER 	T6    	AT6         	6400402	GL  										FITTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										EDDY CURRENT INSPECTION OF WING ATTACHMENT FITTINGS FOUND CRACK INDICATIONS.  FURTHER TESTING USING FLUORESCENT PENETRAT	ION FAILED TO DETECT THE CRACK.  FOUND DURING INSPECTION IAW AD/AT-6/1.					1	L	7	1 	3R				A2575   					 
2006061400137	20060614	00137	EU  	2006	6	14	AU510001537      	1	20051212	G	5270	893301	PROXIMITY SENSOR			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					CARGO DOOR	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										AFT CARGO DOOR WARNING.  INVESTIGATION FOUND THE DOOR CLOSED AND LOCKING MECHANISM SERVICEABLE.  SUSPECT CAUSED BY FAULT	Y SENSOR.					2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006061400139	20060614	00139		2006	6	14	AU510001538      	4	20051212	G	2310	5ARM3006LV3	TENSIONER       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	HF ANTENNA	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										HF ANTENNA SUPPORT AND TENSION UNIT SNAPPED AT ANTENNA CONNECTION TO VERTICAL STABILIZER.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061400141	20060614	00141	EA  	2006	6	14	AU510001539      	2	20050504	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 		1584 	1584 				L866461A			RT ENGINE METAL CONTAMINATION.  INSPECTION FOUND NR 3 CYLINDER AND PISTON DAMAGED.  SUSPECT CAUSED BY DETONATION.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061400144	20060614	00144	EU  	2006	6	14	AU510001540      	1	20051212	G	7332	1453PGCP115	PRESSURE SWITCH 			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ENGINE FUEL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					RT ENGINE LP FUEL PRESSURE SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500029	20060615	00029	EU  	2006	6	15	AU510001541      	1	20050107	G	3260		TARGET          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT MLG LWR TOGGLE TARGET PARTIALLY DISBONDED.  LANDING GEAR WAS BEING FITTED TO A/C AFTER BEING IN STORAGE FOR SEVERAL Y	EARS.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500030	20060615	00030		2006	6	15	AU510001542      	4	20050307	G	3140	6220847541	DISPLAY         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MULTFUNCTION	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										MULTI FUNCTION DISPLAY UNIT (MFDU) SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500031	20060615	00031	EU  	2006	6	15	AU510001544      	1	20050407	G	5610	D20543405	WINDSHIELD      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					WINDSHIELD	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		4186 								NR 1 WINDSHIELD CRACKED.  CRACK ORIGINATES NEAR ELEMENT.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500032	20060615	00032	NM  	2006	6	15	AU510001545      	1	20050407	G	3020	65222723	DUCT            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 2 ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 ENGINE INLET ANTI-ICE DUCT FLANGE COUPLING LIP FRACTURED AND SEPARATED.  EVIDENCE OF A PRE-EXISTING CRACK.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061500076	20060615	00076		2006	6	15	AU510001546      	4	20050207	G	2310		RADIO           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HF SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										NR 2 HF RADIO NOT TRANSMITTING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061500078	20060615	00078		2006	6	15	AU510001547      	4	20050107	G	2220	AR6460M2	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AUTOPILOT	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 		45395	22270							AUTOPILOT STABILIZER TRIM ACTUATOR FAILED DUE TO STRIPPED ROTOR GEAR AND WORN ROTOR BEARING JOURNAL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061500079	20060615	00079	NM  	2006	6	15	AU510001548      	1	20050507	G	2913	21830	BEARING         			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HYDRAULIC PUMP	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										HYDRAULIC SYSTEM `B` NR 1 ELECTRIC HYDRAULIC PUMP FAILED.  NIL PRESSURE AND METAL CONTAMINATION.  INVESTIGATION FOUND TH	E FAILURE WAS DUE TO FAILURE OF THE PRE-MOD SB 57186-29-291 TRUNNION NEEDLE BEARING P/N 21830.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061500081	20060615	00081	EU  	2006	6	15	AU510001549      	1	20050107	G	2760	FON62125R06K	BEARING         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					SPOILERS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LIFT DUMPER ACTUATOR RODEND BEARING WORN.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500082	20060615	00082	NM  	2006	6	15	AU510001550      	1	20051212	G	5754	256T2800112	TORQUE TUBE     			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LE SLAT CONTROL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										INBOARD LEADING EDGE DRIVE SHAFT/TORQUE TUBE SHEARED.  DRIVE SHAFT SHOWED SIGNS OF SEVERE CHAFING DAMAGE DUE TO WATER SU	PPLY LINE AND ADJACENT CLAMP.  TORQUE TUBE HAD BEEN WORN THROUGH BY MORE THAN 50 PERCENT OF THICKNESS PRIOR TO FAILURE D	URING MAINTENANCE.				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061500205	20060615	00205	NM  	2006	6	15	AU510001551      	1	20051212	G	5100		SCREW           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					COVER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT THRUST REVERSE LEVER COULD BE LIFTED WITH FORWARD THRUST LEVER OFF IDLE.  THE THRUST LEVER TOP COVERS WERE REMOVED AN	D IT WAS FOUND THAT THE AFT TWO FASTENERS OF THE LEFT THRUST LEVER BAULK RAIL INSTALLATION WERE MISSING.  THIS ALLOWED T	HE LEFT THRUST REVERSE SELECTION BY THE BAULK PIN ON THE LEFT LEVER PUSHING THE RAIL OUT OF THE WAY.  WITH THE FORWARD T	HRUST LEVER OFF IDLE, THE RAIL SHOULD HAVE STOPPED THE THRUST REVERSE LEVER FROM BEING LIFTED.			2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061600110	20060616	00110		2006	6	16	AU510001552      	4	20050307	G	2397		COUPLER         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HF RADIO	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 HF SYSTEM FAILED.  NEW TRANSMITTER FITTED BUT PROBLEM REMAINED.  SUSPECT FAULTY COUPLER.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061600111	20060616	00111	NM  	2006	6	16	AU510001553      	1	20051212	G	2782	7321861001	ACTUATOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LE FLAPS	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 										LEADING EDGE SLAT DISAGEE MESSAGE.  INVESTIGATION FOUND THAT THE INBOARD LEADING EDGE SLAT BYPASS VALVE ROTARY ACTUATOR 	WAS INTERMITTENT IN OPERATION.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061600112	20060616	00112	NM  	2006	6	16	AU510001554      	1	20050207	G	3610	79275515	CONTROLLER      			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PNEUMATIC DIST	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 		24462	719  							LT ENGINE PNEUMATIC SYSTEM PRESSURE REDUCING VALVE (PRC) CONTROLLER FAILED.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061600114	20060616	00114	GL  	2006	6	16	AU510001555      	2	20050207	G	7200	CF680C2B6	ENGINE          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RIGHT	BIRD INGESTION  	W				A				UNSCHED LANDING         				C	J		F.O.D.                    	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										RT ENGINE BIRDSTRIKE.  THREE FAN BLADES DAMAGED BEYOND LIMITS LAID DOWN IN MAINTENANCE MANUAL.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061600133	20060616	00133		2006	6	16	AU510001556      	4	20050107	G	2562	ELP362D	BEACON          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					UNDERWATER LOCAT	NO TEST         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										UNDERWATER LOCATION BEACON (ULB) FAILED TEST IAW EI 744-023-0182R04 AND AD/REC/1.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061600135	20060616	00135	NM  	2006	6	16	AU510001557      	1	20050607	G	5210	BACW10BP4CD	BOLT            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					L1 DOOR	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										DOOR L1 UPPER GATE STUCK IN LOCKED POSITION DUE TO LOWER ROD ASSEMBLY BOLT DISLODGED IN THE TORQUE BOX ASSEMBLY.  SUSPEC	T BOLT INSUFFICIENTLY TORQUED.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061600137	20060616	00137	NE  	2006	6	16	AU510001558      	2	20050507	G	7230		COMPRESSOR WHEEL			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					ENGINE	WRONG PART      	W				O				OTHER                   				E	W		VIBRATION/BUFFET          	INADEQUATE Q C            		CL	CLIMB          	1			AU	S 										NR 2 ENGINE FAN BLADE PLATFORMS NR 1 AND NR 4 LOCATED OPPOSITE NR 13 AND NR 16 FAN BLADES WERE NOT CHANGED WHEN NR 13 AN	D NR 16 FAN BLADE PLATFORMS WERE CHANGED AS DIRECTED BY SB CFM56-7B-0353.  NR 13 AND NR 16 FAN BLADE PLATFORMS WERE CHAN	GED TO P/N 340-001-814-0.  NR 1 AND NR 4 PLATFORMS WERE P/N 340-001-809-0.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061600138	20060616	00138	CE  	2006	6	16	AU510001559      	1	20051212	G	3233	99101363	ACTUATOR        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					RT MLG	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										RT MAIN LANDING GEAR NIL DOWN INDICATION.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006061600139	20060616	00139		2006	6	16	AU510001560      	4	20050507	G	3100		DISPLAY         			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	MFDU	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										AVIONICS SMOKE WARNING AND HOT ODOR IN COCKPIT.  AVIONICS MPU RERACKED.  SMOKE DETECTOR REMOVED FOR CLEANING DURING MAIN	TENANCE.  MULTIPLE PRINTED CIRCUIT BOARDS REMOVED AND DUST DISTURBED DURING TAWS INSTALLATION.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2006061600140	20060616	00140	NM  	2006	6	16	AU510001561      	1	20051212	G	3244		TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										LT BODY GEAR NR 6 MAIN WHEEL TIRE TREAD SEPARATED.  LOSS OF TIRE PRESSURE.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061900259	20060619	00259	EU  	2006	6	19	AU510001562      	1	20051212	G	2700	LA2K2B100D80000	COMPUTER        			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					FLT CONTROL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		4913 	4913 							FLIGHT CONTROL PRIMARY COMPUTER (FCPC) FAILED.  FCPC REMOVED AND SENT FOR TEST AND REPAIR.  INVESTIGATION FOUND THE POWE	R SUPPLY FAULTY.					2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006062100091	20060621	00091	NM  	2006	6	21	AU510001563      	1	20051212	G	2421	AM739515B	IDG             			BOEING	767   	767*        	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					AC	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		28771	15314							(AUS) RT INTEGRATED DRIVE GENERATOR (IDG) FAILED.  INVESTIGATION FOUND PUMP AND MOTOR ASSEMBLY CYLINDER BLOCKS WORN BEYO	ND LIMITS AT VARIOUS PISTON AND SLIPPER BORES. NUMEROUS OTHER COMPONENTS ALSO SEVERELY WORN. SUSPECT CAUSED BY OIL CONTA	MINATION. IDG SCAVENGE FILTER CONTAMINATED. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA NR 510001563)				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062100092	20060621	00092	NM  	2006	6	21	AU510001564      	1	20051212	G	5414	313U23162	PANEL           			BOEING	747   	747*        	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					NR 2 NACELLE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE IB SAILBOAT FAIRING HYDRAULIC VALVE ACCESS PANEL MISSING. SUSPECT PANEL INCORRECTLY SECURED. IMPACT DA	MAGE CAUSED TO LEADING EDGE OF LT HORIZONTAL STABILIZER.					2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2006062100093	20060621	00093	NM  	2006	6	21	AU510001565      	1	20051212	G	2750	113T24015	ROD END         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) IB AFT FLAP DEFLECTION CONTROL ROD PULLED OUT OF IB RODEND. INSPECTION FOUND RODEND BADLY CORRODED AND THREAD STRI	PPED.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062100094	20060621	00094	NM  	2006	6	21	AU510001566      	1	20051006	G	2530	137884E13	LIGHT           			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					GALLEY	ARCED           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR GALLEY POWER NR 2 INDICATOR LIGHT DAMAGED AND WIRES W315-61-16A AND W315-62-16N DAMAGED FROM ARCING.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062100095	20060621	00095		2006	6	21	AU510001567      	4	20050707	G	3497	W6491001620	WIRE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					WX RADAR SYS	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WEATHER RADAR SYSTEM WIRES PN W6491-0016-20 AND PN W6491-0065-24 FOUND PULLED OUT OF TERMINAL BLOCK GD383. SUSPECT	 WIRES DISTURBED DURING AIRCRAFT MODIFICATION. SEE ATTACHMENT FOR INVESTIGATION DETAILS.(OTHER CAUSE: WIRES FOUND PULLED	 OUT OF TERMINAL BLOCK ) (CASA NR 510001567)				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062100096	20060621	00096		2006	6	21	AU510001568      	4	20050807	G	3100	40023344	LAMP            	HONEYWELL   		DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	INDICATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					89105755					(AUS) PANEL LIGHTS FOR ATTITUDE INDICATOR BLOWN. (OTHER CAUSE: MATERIAL ) (CASA NR 510001568)						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062100097	20060621	00097		2006	6	21	AU510001569      	4	20050807	G	3442	6225132633	TRANSCEIVER     			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					WX RADAR SYS	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) WEATHER RADAR TRANSCEIVER CONTAMINATED WITH WATER FROM FORWARD TOILET HAND BASIN OVERFLOW.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062100099	20060621	00099		2006	6	21	AU510001570      	4	20050606	G	2340	285A178010	CONTROLLER      			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					INTERPHONE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT ATTENDANT HANDSET CONTROLLER FAILED. (CASA NR  510001570)						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062200072	20060622	00072		2006	6	22	AU510001571      	4	20050507	G	2565	D31591478	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  						FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		40151	88   							DOOR L1 ESCAPE SLIDE PRESSURE OUTSIDE OF OPERATING RANGE.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006062200073	20060622	00073	SO  	2006	6	22	AU510001572      	2	20051212	G	8530		EXHAUST VALVE   			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C201    	GL  	NR 3 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 CYLINDER EXHAUST VALVE STEM WORN EXCESSIVELY.  WEAR WAS APPROXIMATELY 3.175MM (0.125IN).  SUSPECT INCORRECT VALVE G	UIDE/VALVE COMBINATION.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2006062200075	20060622	00075	NM  	2006	6	22	AU510001573      	1	20050707	G	2822		SWITCH          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL BOOST PUMP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CENTER FUEL TANK RT BOOST PUMP RUNNING WHEN SWITCH `OFF`.  SUSPECT FUEL PANEL CONTROL SWITCH.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006062200076	20060622	00076	SW  	2006	6	22	AU510001574      	1	20051007	G	5711		SPAR            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE3312     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										WING SPAR INNER WEB CUTOUT CRACKED IN THREE PLACES.  THREE CRACKS WERE FOUND IN THE STARBOARD INNER WEB STRINGER 13 CUTO	UT MEASURING 12.7MM (0.5IN), 3.175MM (0.125IN) AND 9.525MM (0.375IN).  FOUND DURING INSPECTION IAW AD/SWSA226/86.  SEE A	TTACHMENTS FOR FURTHER INFORMATION AND DIAGRAMS.				2	L	7	2 	4T	3	T	RT	A5SW    	E3WE	6	C	3PNE	 
2006062200077	20060622	00077		2006	6	22	AU510001575      	4	20051212	G	2215	7002260903	SERVO           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT642A      		NE  					YAW DAMPER	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										RUDDER AUTOPILOT SERVO/YAW DAMPER FAULTY, OTHER CAUSE: FAILURE OF INTERNAL MECHANISM.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062200079	20060622	00079	WP  	2006	6	22	AU510001576      	1	20051212	G	6230	A2041	ARM             	ROBSIN      		ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		45   	45   		2825					MAIN ROTOR UPPER SCISSOR ARM WORN IN AREA OF SWASHPLATE BEARING ATTACHMENT.  BOLT ALSO WORN.						1	G	7	1 	3O	3	O		H10WE   	E274				 
2006062700284	20060627	00284	SW  	2006	6	27	AU510001577      	1	20050806	G	6520	476452051	SHAFT           			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					TAIL ROTOR	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1200 							TAIL ROTOR GEARBOX PINION SHAFT WORN AND INCORRECT PART.  BELL 47 SI 428 CALLED FOR REPLACEMENT OF P/N 47-645-205-1 WITH	 P/N 47-645-205-3 SHAFT.					1	G	7	1 	3O	3	O		2H3     	1E13				 
2006062300099	20060623	00099	CE  	2006	6	23	AU510001578      	1	20051212	G	8011		GEAR            		MHB6016     	CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1B90	1B90*       	GL  	STATER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		91   			E122519					(AUS) ENGINE STARTER MOTOR DRIVE GEAR DISINTEGRATED DURING START. STARTER MOTOR FRONT HOUSING DAMAGED. (CASA NR 51000157	8)					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P842	 
2006062300100	20060623	00100	EU  	2006	6	23	AU510001579      	1	20051207	G	3610	3925308	SHUTOFF VALVE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PNEUMATIC SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1535 								(AUS) PNEUMATIC SYSTEM PRESSURE REGULATING SHUTOFF VALVE (PRSOV) FAULTY.  (CASA NR 510001579)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062300101	20060623	00101	CE  	2006	6	23	AU510001580      	1	20051207	G	5711	P1756021	FRAME           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		7099 								(AUS) FUSELAGE FRAMES PN P1756-02/1 AND PN P1756-01/1 LOCATED IN WING FORWARD SPAR CARRY THROUGH SECTION CRACKED.  FOUND	 DURING INSPECTION IAW AD. (CASA NR 510001580)					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
2006062300102	20060623	00102	EU  	2006	6	23	AU510001581      	1	20051212	G	2911	9603001291	ACCUMULATOR     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 		10686								(AUS) HYDRAULIC ACCUMULATOR LEAKING.(OTHER CAUSE: HIGH CYCLES ) (CASA NR 510001581)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062300103	20060623	00103	NM  	2006	6	23	AU510001582      	1	20050807	G	3244		TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					MLG	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 MAIN LANDING GEAR TIRE PRESSURE LOW.  FOD FOUND IN TREAD. (OTHER CAUSE: MATERIAL - ENVIRONMENT ) (CASA NR 510	001582)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006062300133	20060623	00133	NM  	2006	6	23	AU510001583      	1	20050107	G	3397		WIRE HARNESS    			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					LIGHTS	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIGHTING WIRING SHORT CIRCUIT. INVESTIGATION FOUND DAMAGED INSULATION ON WIRE W4003-575-22R LOCATED ABOVE THE COPI	LOT`S PFD. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA NR 510001583)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006062300134	20060623	00134	NM  	2006	6	23	AU510001584      	1	20050807	G	2497		WIRE            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  						BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRE LOCATED ON THE BACK OF PLUG D4001P LOCATED BEHIND THE E I RACK BURNED DUE TO CONTACT WITH TRAY DISCONNECT BRA	CKET.  (OTHER CAUSE: MATERIAL ) (CASA NR 510001584)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006062300191	20060623	00191	CE  	2006	6	23	AU510001585      	1	20051212	G	8011	6462382	STARTER         			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		515  	515  							(AUS) ENGINE STARTER MOTOR FAILED TO TURN OVER. INVESTIGATION FOUND A FAILED BRUSH SPRING JAMMED BETWEEN THE BRUSH AND C	OMMUTATOR.  (CASA NR 510001585)					1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P21EA	 
2006062300192	20060623	00192	NM  	2006	6	23	AU510001586      	1	20050307	G	2761	85770012003	ACTUATOR        			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	LT SPOILER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		15639								(AUS) LT IB ROLL SPOILER ACTUATOR FAILED.  (CASA NR 510001586)						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300194	20060623	00194		2006	6	23	AU510001587      	4	20051207	G	2211	6227476411	COMPUTER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AUTOPILOT	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT COMPUTER SUSPECT FAULTY.  (CASA NR 510001587)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062300196	20060623	00196		2006	6	23	AU510001588      	4	20051207	G	2565	D31841101	SLIDE           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					RIGHT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ESCAPE SLIDE FAILED TO DEPLOY CORRECTLY. FOLLOWING MANUAL OPERATION THE SLIDE INFLATED BUT WAS NOT CORRECTLY OR	IENTATED TO THE DOOR OPENING. SUSPECT CAUSED BY FAULTY PACKING OF THE SLIDE AT THE LAST OVERHAUL.  (CASA NR 510001588)					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062300197	20060623	00197	NE  	2006	6	23	AU510001589      	2	20051203	G	7261	WF331451	FILTER          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ENGINE OIL	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		360  								(AUS) ENGINE OIL FILTER BULGED OUT ON BOTTOM SURFACE.  (CASA NR 510001589)						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006062300198	20060623	00198	SO  	2006	6	23	AU510001590      	1	20051107	G	2912		BOWL            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	HYD SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HYDRAULIC FILTER BOWL FAILED ALLOWING LOSS OF FLUID TO THE LEVEL OF THE ENGINE DRIVEN PUMP STANDPIPE.   (CASA N	R 510001590)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2006062300199	20060623	00199		2006	6	23	AU510001591      	4	20051207	G	2340	9506747	CIRCUIT BOARD   			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	INTERPHONE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1806 								(AUS) PASSENGER SERVICE UNITS (PSU) FAULTY. INVESTIGATION FOUND PSU CONTROL CIRCUIT BOARDS HAD BEEN HEAT DAMAGED.  INVES	TIGATION INTO THE CAUSE OF THE CIRCUIT BOARDS DAMAGE REVEALED THAT THE WIRE ON THE OUTLET SIDE OF ALL OF THE PSU CONTROL	 CIRCUIT BOARDS HAD CHAFED INSULATION ALLOWING SHORT CIRCUIT TO GROUND. THIS UNCONTROLLED SHORT CIRCUIT RESULTED IN THE 	OUTLET TRANSISTOR BURNING OUT ON ALL PSU CONTROL CIRCUIT BOARDS.(CASA NR 510001591)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300200	20060623	00200	NM  	2006	6	23	AU510001592      	1	20050907	G	2760	10AT3041	SWITCH          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					DRAG CONTROL SY	FAULTY          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) SPOILER WARNING ON TAKEOFF.  SUSPECT FAULTY POSITION SWITCH.  (CASA NR510001592)						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062300201	20060623	00201	NM  	2006	6	23	AU510001593      	1	20051212	G	2133	7786863	SHUTOFF VALVE   			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT BLEED SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		9655 								(AUS) LT BLEED AIR HIGH PRESSURE SHUTOFF VALVE (HPSOV) FAILED.   (CASA NR 510001593)						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070500046	20060705	00046	SO  	2006	7	5	AU510001594      	2	20051212	G	7310	560010960	LINE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	FUEL SYSTEM	WORN            	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE FUEL SUPPLY LINE LOCATED BETWEEN FUEL BOWL AND NACELLE CHAFED THROUGH ON WING STRUCTURE LIGHTENING HOLE.	 FUEL LEAKING INTO WING. (CASA NR 510001594)					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006070300018	20060703	00018	NM  	2006	7	3	AU510001595      	1	20051207	G	3244		TIRE            			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 REAR TIRE ASSEMBLY CONTAINED A DEEP CUT.  INVESTIGATION FOUND CUT TO BE OUT OF LIMITS.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006070300019	20060703	00019	NM  	2006	7	3	AU510001596      	1	20051207	G	3097		CONNECTOR       			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					WINDOW HEAT	LOOSE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										CAPTAIN`S WINDOW HEAT BOTTOM LT CONNECTION LOOSE AND ARCING.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006070300020	20060703	00020	NM  	2006	7	3	AU510001597      	1	20051007	G	2530		BEARING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					CHILLER FAN	COLLAPSED       	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 		30155	11929							NR 1 AFT GALLEY CHILLER FAULTY.  WORKSHOP INVESTIGATION FOUND THE FAN BLOWER MOTOR BEARINGS COLLAPSED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006070300021	20060703	00021	NM  	2006	7	3	AU510001598      	1	20051212	G	5312	STA18095	FRAME           			BOEING	767   	767277      	1385128	NM  	GE    	CF6   	CF680A      	30025	NE  					BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FUSELAGE-BODY STATION 1809.5 BULKHEAD RT FORWARD OUTER CHORD CRACKED IN LOWER FORWARD HOLE.  FOUND DURING INSPECTION IAW	 AD/B767/146 AMDT2 AND AAES AD ER NO B76-53-36F.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006070300022	20060703	00022	NM  	2006	7	3	AU510001599      	1	20051212	G	3220		LANDING GEAR    			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NOSE	LOCKED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										NOSE LANDING GEAR FAILED TO RETRACT.  INVESTIGATION FOUND THE LANDING GEAR GROUND LOCK STILL FITTED.  GROUND LOCK HAD NO	T BEEN STOWED FOLLOWING PUSHBACK.  PERSONNEL/MAINTENANCE ERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070300023	20060703	00023	EU  	2006	7	3	AU510001600      	1	20050907	G	2823	HTE900212	VALVE           			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					FUEL SELECTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		8215 	8215 							LOW PRESSURE FUEL VALVE LEAKING.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006070300024	20060703	00024		2006	7	3	AU510001601      	4	20051107	G	2565		ASPIRATOR       			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					ESCAPE SLIDE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										SLIDERAFT FAILED FLAT FIRE TEST.  INSPECTION OF THE INFLATABLE ASSEMBLY FOUND THREE HOLES AND ONE INDENTATION COMMON TO 	THE LOWER INFLATION TUBE.  THIS SLIDERAFT ASSEMBLY WAS FITTED WITH P/N 4A3791-3 PLASTIC PRESSURE RELIEF VALVES (PRV) ON 	BOTH THE UPPER AND LOWER TUBES, WHICH ACCOUNTED FOR LEAKAGE FAILURE OF THE UPPER TUBE.  ADDITIONALLY, THE PN 5A3265-1 AS	PIRATOR WAS FOUND TO BE SIGNIFICANTLY DISTORTED.  INITIAL INDICATIONS SHOW THAT THE ASPIRATOR BODY TRACE LINE MATCHES TH	E APPROXIMATE LOCATION OF THE HOLES.		2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006070300025	20060703	00025	NM  	2006	7	3	AU510001602      	1	20051007	G	3010	2780537104	ANTI-ICE VALVE  			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT WING	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										RT WING ANTI-ICE MESSAGE.  THERMAL ANTI-ICE VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006070300060	20060703	00060	NM  	2006	7	3	AU510001603      	1	20051212	G	5753	113T22036	SEAL            			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					TE FLAP	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										LT WING LT INBOARD FLAP OUTBOARD UPPER SEAL SEPARATED DURING TAKEOFF.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006070300101	20060703	00101	EA  	2006	7	3	AU510001604      	1	20050306	G	3110		PANEL           			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	INSTRUMENT PANEL	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										NO LABELS ON DUAL RADIOS/INDICATORS AND ADVISORY LABELS AS REQUIRED BY ANO 108.34 SECTION 6.2.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006070300102	20060703	00102	EA  	2006	7	3	AU510001605      	1	20051107	G	2800		FUEL SYS        			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										FUEL SYSTEM SUSPECT FAULTY.  LIMITED INFORMATION PROVIDED.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006070300103	20060703	00103	EU  	2006	7	3	AU510001606      	2	20051212	G	7314	7086005	PUMP            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE FUEL	FAULTY          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 		17788	17788							NR 2 ENGINE HAS A HISTORY OF STARTING DIFFICULTIES AND FLUCTUATING PARAMETERS.  INVESTIGATION FOUND FUEL PUMP HAD NO FLO	W AT LOW SPEED AND WAS WELL BELOW LIMIT OF FLOW AT HIGHER SPEED. THE PUMP GEARS WERE FOUND SCORED. THIS CAUSED DAMAGE TO	 THE BEARINGS AND THE `O` RING WHERE THE BEARINGS ARE SEATED IN THE HOUSING ALLOWING SOME FUEL TO BYPASS AND CAUSE LOW F	UEL FLOW FROM THIS PUMP.			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300104	20060703	00104	SO  	2006	7	3	AU510001607      	1	20050107	G	3210		LANDING GEAR    			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  		COLLAPSED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										LT MAIN LANDING GEAR COLLAPSED.  AIRCRAFT AND LANDING GEAR DAMAGED.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
2006070300105	20060703	00105	CE  	2006	7	3	AU510001608      	1	20051212	G	2820	520010785	LINE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	FUEL DIST	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 										LINE LOCATED IN RT WING ROOT CRACKED.  LIMITED INFORMATION PROVIDED.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006070300106	20060703	00106	CE  	2006	7	3	AU510001610      	1	20050606	G	3220		LANDING GEAR    			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	NOSE	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NOSE LANDING GEAR RETRACTION SYSTEM MISRIGGED.  NLG FAILED TO FULLY RETRACT INTO THE WHEEL WELL, LEAVING THE DOORS WIDE 	OPEN AND THE NOSEWHEEL HANGING OUT BY APPROXIMATELY 127MM TO 152.4MM (5IN TO 6IN).  NLG WAS CORRECTLY RIGGED IN THE DOWN	 POSITION.				1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
2006070300107	20060703	00107	CE  	2006	7	3	AU510001611      	1	20050606	G	3260		CAM             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	WARNING SYS	MISSING         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			AU	S 										LANDING GEAR WARNING HORN FAILED TO OPERATE WHEN THROTTLES CLOSED.  INVESTIGATION FOUND NO SWITCHES, BRACKETS OR ROLLERS	 IN WARNING SYSTEM.  LT ENGINE FCU WARNING SYSTEM ACTIVATING CAM MISSING.  NO WIRING FITTED FORWARD OF THE FIREWALL.  PE	RSONNEL/MAINTENANCE ERROR.				1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
2006070500085	20060705	00085	SO  	2006	7	5	AU510001613      	1	20050406	G	2710		AILERON         	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AILERON SYSTEM	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					317305070					(AUS) RAG LODGED BETWEEN LT OB AILERON BALANCE CABLE PULLEY AND CABLE LOCATED BELOW CABIN FLOOR. FOD. PERSONNEL/MAINTENA	NCE ERROR. (CASA NR 510001613)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500086	20060705	00086	SO  	2006	7	5	AU510001614      	1	20050406	G	7810	AEA40111729801	TAILPIPE        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	TURBOCHARGER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE TURBOCHARGER TAILPIPE CRACKED FOR APPROX 90 PERCENT OF CIRCUMFERENCE. TAILPIPE ALSO CONTAINED 3 HOLES RA	NGING IN DIAMETER FROM 12.7 MM TO 25.4MM (0.5IN TO 1IN). (CASA NR 510001614)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500087	20060705	00087	SO  	2006	7	5	AU510001615      	1	20050406	G	7120		MOUNT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE IB UPPER ENGINE MOUNT BRACKET RIVETS (3OFF) SHEARED AND BRACKET SEPARATED FROM STRUCTURE BY APPROXIMATEL	Y 3.175MM (0.125IN). CORROSION FOUND BETWEEN BRACKET AND AIRCRAFT STRUCTURE. (CASA NR 510001615)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500088	20060705	00088	SO  	2006	7	5	AU510001616      	1	20050406	G	3222	752731	PLUG            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR AXLE PLUGS CRACKED DUE TO OVERTORQUING. AXLE BOLT BADLY CORRODED. (CASA NR 510001616)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500089	20060705	00089	SO  	2006	7	5	AU510001617      	1	20050406	G	7602	89307000	ROD END         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MIXTURE CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE MIXTURE CONTROL RODEND LOOSE. BALL WAS ONLY RETAINED BY SECONDARY RETAINER CLIP. FINGER PRESSURE COULD D	ISCONNECT RODEND FROM FCU. (CASA NR 510001617)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500090	20060705	00090	SO  	2006	7	5	AU510001618      	1	20050406	G	3211		RETAINER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR FORWARD TRUNNION BOLT RETAINER HAD 1 OF 2 RIVETS SHEARED ALLOWING TRUNNION BOLT TO PIVOT IN S	PAR INSTEAD OF IN TRUNNION BUSH. (CASA NR 510001618)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500091	20060705	00091	CE  	2006	7	5	AU510001619      	1	20051212	G	2140	8259JR2	HEATER          			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	CABIN	FAULTY          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN HEATER FAULTY. SMOKE IN CABIN. INVESTIGATION FOUND THE FORWARD VENT BLOWER INOPERATIVE DUE MOTOR BRUSH HANGU	P. INSPECTION OF THE HEATER FOUND DISCOLORATION ON THE HEATER OUTER SHROUD. INTERNAL INSPECTION FOUND THE PAINT ON THE I	NSIDE OF THE HEATER SHROUD HAD CAUGHT FIRE RESULTING IN THE SMOKE IN THE CABIN. DUCT OVERTEMP SWITCH ALSO TRIPPED.  (CAS	A NR 510001619)			1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006070500120	20060705	00120	SO  	2006	7	5	AU510001620      	1	20050406	G	3110	475109	SHOCK MOUNT     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					INSTRUMENT PANEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PILOT`S INSTRUMENT PANEL ONLY SECURED BY TWO OF FOUR SHOCK MOUNTS.  COPILOT`S PANEL HAD ALL FOUR SHOCK MOUNTS BROKEN.  P	ANEL WAS HELD IN PLACE BY PLUMBING AND WIRING.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006070500121	20060705	00121	SO  	2006	7	5	AU510001621      	1	20050406	G	3230		UPLOCK ROLLER   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT & RT MLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT AND RT MAIN LANDING GEAR UPLOCK ROLLERS SEIZED.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006070500229	20060705	00229	EA  	2006	7	5	AU510001622      	2	20050406	G	8530		VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  		OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT ENGINES BOTH OVERDUE FOR 400 HOUR VALVE INSPECTION. NO RECORD OF INSPECTION BEING CARRIED OUT. (CASA NR 	510001622)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500230	20060705	00230	SO  	2006	7	5	AU510001623      	1	20050406	G	2730	71056003	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		476  								(AUS) ELEVATOR DOWN SPRING SEVERELY CORRODED. (CASA NR 510001623)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500231	20060705	00231	SO  	2006	7	5	AU510001625      	1	20050406	G	5712		RIB             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	CENTER WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIB LOCATED IN CENTER OF RT WHEEL WELL CRACKED. (CASA NR 510001625)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500232	20060705	00232	SO  	2006	7	5	AU510001626      	1	20050406	G	2823		CABLE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL SHUTOFF	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUEL SHUTOFF CABLE SEIZED. (CASA NR 510001626)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006070500233	20060705	00233	NM  	2006	7	5	AU510001627      	1	20051212	G	4920		SEAL            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					APU	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 					P6537					(AUS) APU LEAKING OIL INTO AIR DUCTING. STRONG OIL SMELL IN COCKPIT. INVESTIGATION FOUND THE APU LOAD COMPRESSOR SEAL FA	ILED AND LEAKING. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (OTHER CAUSE: LOAD COMP SEAL LEAKAGE ) (CASA NR 510001627)					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500234	20060705	00234	CE  	2006	7	5	AU510001628      	1	20051212	G	5311		FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10743								(AUS) FUSELAGE FRAME LOCATED AT FS226.875 UNDER THE RT SEAT ROW CORRODED IN AREA BETWEEN 2 STRINGERS. CORROSION EXTENDED	 UP THE FRAME WEB. FOUND DURING INSPECTION IAW AD/B200/21 AMDT 11.(AD/SB DESC: AD/B200/21 AMDT 11 ) (CASA NR 510001628)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006070500235	20060705	00235	CE  	2006	7	5	AU510001629      	1	20051212	G	5320		RIVET           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WINDSHIELD	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10713								(AUS) LT WINDSHIELD UPPER OB CORNER DOUBLER HAD 4 SHEARED RIVETS. FOUND DURING INSPECTION IAW AD/B200/21 AMDT 11.(AD/SB 	DESC: AD/B200/21 AMDT 11 ) (OTHER CAUSE: MATERIAL ) (CASA NR 510001629)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006071100142	20060711	00142	CE  	2006	7	11	AU510001630      	1	20051212	G	5314		KEELBEAM        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10743								KEEL WEB LOCATED IN NOSE WHEEL WELL CRACKED IN AREA OF AIR CONDITIONING PIPE P-CLAMP ATTACHMENT.  FOUND DURING INSPECTIO	N IAW AD/B200/21 AMDT 11.					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006071100143	20060711	00143	SO  	2006	7	11	AU510001631      	1	20051207	G	3310	484498	RESISTOR        	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	DIMMER	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 		9407 								INSTRUMENT PANEL LIGHTING DIMMER 22 OHM RESISTOR BURNED.						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006071100144	20060711	00144	CE  	2006	7	11	AU510001632      	1	20051212	G	5210	1295140591	CABLE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	PAX DOOR	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 					0					CABIN DOOR TOP FORWARD LATCHING CABLE SNAPPED ALLOWING TOP FORWARD LOCK TO UNLATCH.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006071100145	20060711	00145	EA  	2006	7	11	AU510001633      	2	20050107	G	7310		LINE            			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	FUEL SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										ENGINE FUEL LINE CHAFED AND WORN BY THROTTLE CABLE.  LOSS OF APPROXIMATELY 5 GALLONS OF FUEL.  THROTTLE CABLE HAD BEEN R	ECENTLY REPLACED.					1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2006071100146	20060711	00146	SO  	2006	7	11	AU510001634      	1	20050707	G	7713	193F0004D0330	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	FRACTURED       	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		1007 								RT ENGINE SUMP TO DIFFERENTIAL PRESSURE CONTROLLER FAILED.  HOSE IS MANUFACTURED FROM 306 RUBBER AND IT IS SUSPECTED THA	T THE MATERIAL IS INCAPABLE OF WITHSTANDING HIGH TEMPERATURES.  ORIGINAL PIPER HOSE P/N 39999-14.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006071100147	20060711	00147	SW  	2006	7	11	AU510001635      	1	20051212	G	2897	2782015810	WIRE HARNESS    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL SYSTEM	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		27268								FUEL BOOST PUMP WIRING HARNESSES PN 27-82015-810 AND PN 27-82015-811 DETERIORATED.  FOUND DURING INSPECTION IAW AD/SWA22	6/51 AND SB226-28-011.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2006071100148	20060711	00148	NM  	2006	7	11	AU510001636      	1	20051212	G	4930		MANIFOLD        			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					APU	LEAKING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 		9521 	987  							APU FUEL MANIFOLD LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100149	20060711	00149	NE  	2006	7	11	AU510001637      	2	20051212	G	7230		SPACER          			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					COMPRESSOR	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE FAN BLADE SPACERS WERE INCORRECT PART. FAN BLADES NR 9, NR 10, NR 17, NR 18, NR 19 AND NR 20 WERE AFFE	CTED.  INCORRECT PN 340-001-261-0 SPACERS FITTED. CORRECT PNO 340-001-215-0. INCORRECT PART. PERSONNEL/MAINTENANCE ERROR	. (CASA NR 510001637)				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100167	20060711	00167	NM  	2006	7	11	AU510001638      	1	20051212	G	2750		FLAP SYSTEM     			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FLAP CONTROL	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FLAP STOPPED. FLAP ASSYMETRY. INVESTIGATION CONTINUING. (CASA NR 510001638)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006071100171	20060711	00171	NM  	2006	7	11	AU510001639      	1	20051212	G	5311		FRAME           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					BULKHEAD	SCRATCHED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD AFT FACE OUTER CHORD SCRATCHED IN BEND RADIUS LOCATED AT LBL46/WL235 AND RBL24/WL268. SU	SPECT A SHARP OBJECT WAS USED TO REMOVE SEALANT.  FOUND DURING INSPECTION IAW AD/B747/159. SEE ATTACHMENT FOR INVESTIGAT	ION DETAILS. (CASA NR 510001639)				2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006071100172	20060711	00172	WP  	2006	7	11	AU510001640      	1	20051212	G	7820	C16932	MUFFLER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		677  								(AUS) MUFFLER CRACKED AND DISTORTED IN AREA OF TAILPIPE ATTACHMENT. (OTHER CAUSE: MATERIAL ) (CASA NR 510001640)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006071100173	20060711	00173	WP  	2006	7	11	AU510001641      	1	20050704	G	3340	A470A402A469A	STROBE          			HUGHES	369   	369A        	4470503	WP  	ALLSN 	250C  	250C18      	03011	GL  					EXTERIOR	WRONG PART      	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 										(AUS) INCORRECT STROBE LIGHT FITTED. THE INCORRECT LIGHT WAS APPROXIMATELY 50MM (1.96IN) HIGHER THAN THE ORIGINAL LIGHT.	 THIS EXTRA HEIGHT BROUGHT THE LIGHT INTO THE TRACKING AREA OF THE MAIN ROTOR BLADES WHICH CONSEQUENTLY IMPACTED ON THE 	LIGHT CAUSING UNREPAIRABLE DAMAGE TO ALL FOUR MAIN ROTOR BLADES. INCORRECT PART. PERSONNEL/MAINTENANCE ERROR. (OTHER CAU	SE: INCORRECT STROBE FITTED) (CASA NR 510001641)			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006071100174	20060711	00174	EA  	2006	7	11	AU510001642      	2	20051212	G	8520	AEL74241PL	PISTON RING     			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1269 								(AUS) ENGINE CYLINDERS (4OFF) HAD TOP PISTON RINGS DELAMINATING. PLASMA FACE SECTION COMING AWAY FROM BASE MATERIAL. ALL	 4 CYLINDERS ALSO HAD EXCESSIVELY WORN EXHAUST VALVE GUIDES AND 2 EXHAUST VALVES REQUIRED REPLACEMENT.  (CASA NR 5100016	42)				1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2006071100175	20060711	00175	EU  	2006	7	11	AU510001643      	1	20051212	G	6510	365A34103301	COUPLING        			AEROSP	AS365 	AS365N2     	8680815	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					T/R DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		91   	91   							(AUS) TAIL ROTOR DRIVESHAFT FORWARD FLEXIBLE COUPLING CRACKED. INVESTIGATION FOUND MECHANICAL DAMAGE ON THE EDGE OF THE 	COUPLING AT ONE END OF THE CRACK. (OTHER CAUSE: MATERIAL - IMPACT DAMAGE ) (CASA NR 510001643)					1	G	7	2 	3U	3	U	RT	H10EU   	E19EU				 
2006071100176	20060711	00176		2006	7	11	AU510001644      	4	20051212	G	3417	4040831901	CONVERTER       	HONEYWELL   	AZ810       															DADC	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					86011359					(AUS) DIGITAL AIR DATA COMPUTER (DADC) PRESSURE CONVERTER FAILED MANUFACTURER`S TEST. FOUND DURING INSPECTION IAW AD/RAD	/43.(AD/SB DESC: AD/RAD/43 (FAR 43, APP. E) ) (OTHER CAUSE: MATERIAL ) (CASA NR 510001644)																		 
2006071900021	20060719	00021	NE  	2006	7	19	AU510001645      	2	20051212	G	7313		NOZZLE          								PWA   	PT6   	PT642A      		NE  					FUEL INJECTOR	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT FUEL NOZZLE SHEATHS FITTED AT ENGINE OVERHAUL. FUEL NOZZLES WERE PRE SB3250 AND SHEATHS WERE POST SB3250	. INCORRECT PART. PERSONNEL/MAINTENANCE ERROR. (CASA NR 510001645)										4	T			E4EA				 
2006071100177	20060711	00177	NM  	2006	7	11	AU510001646      	1	20051212	G	5514	69144105	HINGE PIN       			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		53856								(AUS) LT HORIZONTAL STABILIZER OUTER HINGE PIN CRACKED IN AREA OF THREAD ROOT ADJACENT TO SPLIT PIN HOLES. FOUND DURING 	MAGNETIC PARTICLE INSPECTION IAW SB727-55A0090R1 PART 4 AND AD/B727/173.(AD/SB DESC: AD/B727/173, SB727-55A0090R1 ) (CAS	A# 510001646)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061600126	20060616	00126	NM  	2006	6	16	AU510001647      	1	20051212	G	3320		LIGHT           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					CABIN	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										STRONG BURNING ODOR IN CABIN FORWARD GALLEY AREA.  INSPECTION FOUND A BURNT FLUORESCENT TUBE ABOVE SEAT 2JK.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061600127	20060616	00127	EU  	2006	6	16	AU510001648      	1	20051212	G	3411	8538R	PITOT HEAD      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PITOT SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 PITOT HEAD HEATING SYSTEM FAILED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800084	20060608	00084	NM  	2006	6	8	AU510001649      	1	20051212	G	3020	2790583108	ANTI-ICE VALVE  			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C      	 	GL  					AIR INTAKE	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		22405								LT ENGINE ANTI-ICE VALVE FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006060800085	20060608	00085	NM  	2006	6	8	AU510001650      	1	20051212	G	2761	15425001	ACTUATOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C      	 	GL  					DRAG CONTROL	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 		39707								RT HYDRAULIC SYSTEM QUANTITY DECREASING.  INVESTIGATION FOUND RT NO7 SPOILER ACTUATOR FILTER CAP PNO 1542615 LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006060800086	20060608	00086		2006	6	8	AU510001651      	4	20050507	G	3400		DISPLAY         			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					NAVIGATION	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										CAPTAIN`S LT AND FIRST OFFICER`S DISPLAY UNITS READ `DATA INVALID` FOR APPROXIMATELY 20 SECONDS AND THEN RETURNED TO NOR	MAL DISPLAY.					2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006061900167	20060619	00167	WP  	2006	6	19	AU510001652      	1	20050707	G	3230	369H600131	LEG ASSY        			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		6764 								(AUS) LT REAR LANDING GEAR LEG CRACKED FROM CROSS BRACE LOWER BOLT HOLE. CRACK LENGTH APPROXIMATELY 9.525MM (0.375IN). S	EE ATTACHMENT FOR IPC REFERENCE. (OTHER CAUSE: AGE, MATERIAL, OPERATES ON FIXED FLOATS ) (CASA NR 510001652)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006060800087	20060608	00087	CE  	2006	6	8	AU510001653      	1	20051212	G	2820	6017001079	VENT LINE       			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	RT FUEL VENT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		12584								RT FUEL VENT LEAKING.  INVESTIGATION FOUND THAT THE SEALANT AROUND THE VENT TUBE IN THE RT WET WING FUEL TANK HAD DETERI	ORATED ALLOWING FUEL TO LEAK INTO THE VENT LINE.					1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
2006060800089	20060608	00089	NE  	2006	6	8	AU510001654      	2	20051212	G	7220	UP60336	BEARING         	RROYCE      	TAY65015    	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					INLET GUIDE VANE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					LT ENGINE INLET GUIDE VANE BEARINGS PNO UP60336 (1OFF) AND PNO EU61711 (2OFF) WORN.  FOUND DURING INSPECTION IAW SB TAY-	75-1655.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800090	20060608	00090	EU  	2006	6	8	AU510001655      	1	20051212	G	3510		CONNECTOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					PILOT O2 SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CREW OXYGEN MASK BOX ASSEMBLY CONNECTOR LEAKING.  LOSS OF OXYGEN.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800091	20060608	00091	CE  	2006	6	8	AU510001656      	1	20051212	G	2820	292000017	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		10279								MAIN FUEL LINE LOCATED IN RT NACELLE LEAKING IN AREA ABOVE THE ELECTRIC FUEL PUMP.  INVESTIGATION FOUND LINE CORRODED.						1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
2006060800294	20060608	00294	SO  	2006	6	8	AU510001658      	2	20051212	G	8530	TIST712BCA	CYLINDER        			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		190  								NR 2 CYLINDER HEAD SEPARATED FROM BARREL.  FURTHER INVESTIGATION FOUND THAT ALL CYLINDERS (6OFF) SHOULD HAVE BEEN REPLAC	ED IN JULY 2004 IAW ECI SB 04-1.					1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL	 
2006060800148	20060608	00148	NE  	2006	6	8	AU510001659      	2	20051212	G	7314	5008269H	PUMP            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE FUEL	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		3390 	3390 							NR 2 ENGINE FUEL PUMP INPUT SHAFT SHEARED.  PUMP TURNED FREELY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060800149	20060608	00149	NM  	2006	6	8	AU510001660      	1	20051212	G	5330		SKIN            	BOEING      	B727200GROUP	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BS 480-720B	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		53856			22641					FUSELAGE SKIN LAP JOINTS CRACKED.  JOINTS WERE LOCATED AT STRINGER 4R BETWEEN BS 480 AND BS 720B AND AT STRINGER 26L BET	WEEN STN 560 AND STN 580.  FOUND DURING MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION IAW AD/B727/160 AND SB727-53AO22	2.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006060800150	20060608	00150	NM  	2006	6	8	AU510001661      	1	20051212	G	2760		CABLE           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					DRAG CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										GROUND SPOILER INTERLOCK CABLE BROKEN.  INVESTIGATION FOUND VERY STIFF BEARING OPERATION DUE TO MOISTURE INGRESS INTO TH	E BEARING LINER LEAD TO FATIGUE AND ULTIMATELY FAILURE OF THE CABLE RODEND.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800151	20060608	00151	NM  	2006	6	8	AU510001662      	1	20051212	G	2820		MODULE          			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL SYSTEM	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										P5-2 FUEL SYSTEM FLIGHT DECK MODULE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800168	20060608	00168	NM  	2006	6	8	AU510001663      	1	20051212	G	2760		SPOILER         			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  						OUT OF ADJUST   	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										FLIGHT SPOILER OPERATION FAULTY.  INVESTIGATION FOUND SPOILER ADJUSTMENT OUT OF LIMITS.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800170	20060608	00170	EU  	2006	6	8	AU510001664      	1	20050208	G	5280	HC528B0039002	HINGE           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RT MLG DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT MAIN LANDING GEAR DOOR HINGE FITTINGS CORRODED IN BORES.  BEARING HOUSINGS ALSO CONTAINED PITTING AND RUST DEPOSITS O	N THE OUTER SURFACES.  FOUND DURING INSPECTION IAW BAE SYSTEMS ISB 52-113 REV 1 AND AAES AD ER BA6-32-10-43B AND UK CAA 	AD G-2005-0017.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006060800172	20060608	00172	NM  	2006	6	8	AU510001665      	1	20051212	G	3244		TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG	DEFLATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 10 MAIN LANDING GEAR TIRE DEFLATED.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006060800173	20060608	00173	EU  	2006	6	8	AU510001666      	1	20051212	G	3244		TIRE            			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					NLG	LOW PRESSURE    	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										LEFT NOSE WHEEL TIRE LOW PRESSURE.  NOSE SHIMMY ALSO EVIDENT.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006060800175	20060608	00175	EU  	2006	6	8	AU510001667      	1	20051212	G	2611		SMOKE DETECTOR  			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					LAVATORY	FAULTY          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										REPORT OF CIGARETTE SMOKE SMELL IN CABIN.  TOILET SMOKE DETECTOR DID NOT ACTIVATE ALARM.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800335	20060608	00335	SO  	2006	6	8	AU510001668      	1	20051212	G	3233	762554	ROD END         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG ACTUATOR	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 					0					RT MAIN LANDING GEAR ACTUATOR RODEND FAILED.  RT MAIN LANDING GEAR WOULD NOT EXTEND AND THE AIRCRAFT MADE A WHEELS UP LA	NDING.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006062100011	20060621	00011	EU  	2006	6	21	AU510001669      	1	20050108	G	3246	313721	WHEEL           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10133								(AUS) LT MLG WHEEL ASSEMBLY HAD 2 SECTIONS OF THE BEAD MISSING. TIRE DEFLATED DURING LANDING ROLL. (CASA NR 510001669)						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006061200319	20060612	00319	CE  	2006	6	12	AU510001670      	1	20051212	G	2720	5052432651	ARM             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	RUDDER CONTROL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PILOT`S LT RUDDER PEDAL ARM SHEARED.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
2006061200321	20060612	00321	SO  	2006	6	12	AU510001671      	1	20050108	G	3230	4550429	DOWNLOCK        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT MLG	STICKING        	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 		10988				318152142				RT MAIN LANDING GEAR FAILED TO EXTEND.  INVESTIGATION FOUND THE RT MAIN LANDING GEAR DOWNLOCK WAS STUCK DUE TO CARBON BU	ILDUP FROM EXHAUST AND ALSO LUBRICATION DRYING OUT.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061200322	20060612	00322	NM  	2006	6	12	AU510001672      	1	20051212	G	5754	1060779124A	BEARING         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LE SLAT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT WING OUTBOARD KRUGER FLAP NOSE LINK EYE END SHEARED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061200324	20060612	00324	CE  	2006	6	12	AU510001673      	1	20051212	G	5313		STRINGER        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	BS 190	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10743			0					FUSELAGE CLEATS AND STRINGERS CRACKED AND CORRODED IN THE FOLLOWING AREAS, CLEAT AT LOWER LONGERON LT SIDE CRACKED AT FR	AME ATTACHMENT FS 216.125 2 LT SIDE STRINGER CORRODED ON END AT FS 190.6 3.  CLEAT AT STRINGER 6 LT HAS RIVETS MISSING A	T FS 227.				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061200325	20060612	00325	CE  	2006	6	12	AU510001674      	1	20051007	G	2410		DRIVE BELT      			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	ALTERNATOR	LOOSE           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										ALTERNATOR DRIVE BELT LOOSE.  LOSS OF ELECTRICAL POWER.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
2006062100012	20060621	00012	EA  	2006	6	21	AU510001675      	2	20051212	G	8520		BOLT            			NEWZE 	FU24  	FU24954     	6280102	WP  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	CONNECTING ROD	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1639 							(AUS) NR 2 CYLINDER CONNECTING ROD BIG END BOLT FAILED WITH OTHER BIG END BOLT BENT. NR 2 CYLINDER SEPARATED FROM CRANKC	ASE.  (OTHER CAUSE: MATERIAL - HIGH HOURS ) (CASA NR 510001675)					1	L	7	1 	3O	3	O		A9PC    	1E15	5	C	P25EA	 
2006061200326	20060612	00326	CE  	2006	6	12	AU510001676      	1	20051212	G	8011	2005001	GEAR            	LAMAR       		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	STARTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		247  			85007343					(AUS) STARTER MOTOR DRIVE GEAR DISINTEGRATED DURING ENGINE CRANKING.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2006061200327	20060612	00327	WP  	2006	6	12	AU510001677      	2	20051212	G	7200		ENGINE          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LEFT	FLUCTUATES      	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE EGT, TORQUE AND FUEL FLOW FLUCTUATING.  LT FUEL BYPASS VALVE AND LT EGT SHORT LEAD CHANGED.  GROUND RUNS	 AND TEST FLIGHT CARRIED OUT WITH NIL DEFECTS EVIDENT.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006061300092	20060613	00092	WP  	2006	6	13	AU510001678      	2	20051212	G	7321	89778016	FCU             			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	FAULTY          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			5805 							LT ENGINE EGT, TORQUE AND FUEL FLOW FLUCTUATING.  FUEL CONTROL UNIT CHANGED.  GROUND RUN AND TEST FLIGHT CARRIED OUT SER	VICEABLE.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006061300094	20060613	00094	EA  	2006	6	13	AU510001679      	2	20051212	G	8520	AEL74241PL	PISTON RING     			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		588  								TOP COMPRESSION RINGS ON ALL PISTONS DELAMINATING.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2006061300096	20060613	00096	GL  	2006	6	13	AU510001680      	1	20050408	G	3710	216CWRWIP	PUMP            			AMTR  	LANCAR	LC41550FG   	5150001	GL  										VACUUM SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										EXCESSIVE AMOUNT OF VACUUM PUMPS FAILING EITHER ON FITMENT OR SHORTLY AFTER.  THESE PUMPS ARE PURCHASED FROM AERO ACCESS	ORIES INC.					1	L	7	1 	3O			RT	EXPA1L71					 
2006061300097	20060613	00097	CE  	2006	6	13	AU510001681      	1	20050207	G	7603		ROD END         			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	POWER LEVER	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										CARBURETOR THROTTLE ARM DISCONNECTED FROM RODEND DUE TO USE OF INCORRECT HARDWARE.  LIMITED INFORMATION PROVIDED.  PERSO	NNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O		A13CE   	E286	5	N	P857	 
2006061300099	20060613	00099		2006	6	13	AU510001682      	4	20051212	G	3497		WIRE HARNESS    			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ADC	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										UNABLE TO RESET LEFT ADC POWER CIRCUIT BREAKER.  INVESTIGATION FOUND TRANSFORMER T131 IN P6 INOPERATIVE.  FURTHER INVEST	IGATION FOUND P7 WIRING LOOM CHAFING ON `AOA ALT L` CICUIT BREAKER (A13).  `L ADC PWR` CIRCUIT BREAKER WIRE W007-131-22 	FOUND BURNT AND BROKEN.  `LEFT VOR/MAX RCVR` CIRCUIT BREAKER WIRE W007-162-22 FOUND CHAFED AND `AOA L` AND `ALTN L` CIRC	UIT BREAKER WIRING AND LUGS FOUND BURNT (W007-587-22).			2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061300100	20060613	00100	NM  	2006	6	13	AU510001683      	1	20050408	G	2520		BOLT            			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					SEAT BACK	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										SEAT 3E SEAT BACK INBOARD ATTACHMENT BOLTS SHEARED.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006061300101	20060613	00101	NM  	2006	6	13	AU510001684      	1	20050108	G	2910	AS11708K0165	HOSE            			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYD SYSTEM	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										RT HYDRAULIC PUMP PRESSURE LINE FAILED.  LOSS OF HYDRAULIC FLUID.  SUSPECT CAUSED BY FATIGUE TO TO PRESSURE SPIKES CAUSE	D BY PUMP ACTIVATION.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006061300226	20060613	00226	NM  	2006	6	13	AU510001685      	1	20050108	G	2823	MA20A10011	ACTUATOR        			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL SELECTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		255  	255  							NR 2 ENGINE SPAR VALVE ACTUATOR FAILED.  NR 2 ENGINE FAILED TO START.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300273	20060613	00273		2006	6	13	AU510001686      	4	20050108	G	3400		WARNING SYSTEM  			BOEING	777   	777         	UTILUSE	NM  											MULTIPLE FAIL   	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										AIR TURN BACK DUE EICAS LOW AIRSPEED WARNING/AUTO THROTTLE UNRELIABLE/ AUTOPILOT NOT FLYING TO CORRECT COMMANDS/HARD OVE	R SLIP INDICATION.  AIRCRAFT IS FOREIGN REGISTERED.  FOR INFORMATION ONLY.					2	L	7	2 	4F			RT	T00001SE					 
2006061300274	20060613	00274	NM  	2006	6	13	AU510001687      	1	20051212	G	2133	7110033	OUTFLOW VALVE   			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN PRESSURE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		37637	8998 							PRESSURIZATION SYSTEM AFT OUTFLOW VALVE FAILED TO OPEN.  INVESTIGATION FOUND A DEFECTIVE AC MOTOR AND AC POTENTIOMETER.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061300275	20060613	00275	NM  	2006	6	13	AU510001688      	1	20051212	G	2822	KDAE4F	RELAY           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL BOOST PUMP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CENTER FUEL TANK RT BOOST PUMP CONTROL RELAY R55 FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300276	20060613	00276	NM  	2006	6	13	AU510001689      	1	20050808	G	4920		SEAL            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					APU	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 		3998 								APU BLEED VALVE AND DUCTS CONTAMINATED WITH OIL.  INVESTIGATION FOUND THE APU LOAD COMPRESSOR SEAL FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300277	20060613	00277		2006	6	13	AU510001690      	4	20050308	G	3140	8221033100	COMPUTER        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					EICAS	FAULTY          	W				K				NONE                    				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 		18014								LT ENGINE INDICATION AND CREW ALERT SYSTEM (EICAS) COMPUTER FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061300278	20060613	00278	GL  	2006	6	13	AU510001691      	1	20051212	G	2820	20139001	LINE            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		155  	155  							FUEL SUPPLY PIPE P/N 20139-001 AND FUEL RETURN PIPE P/N 20138-001 LEAKING AT `TEE` FITTING. `TEE` FITTINGS ARE PART OF T	HE FERRY TANK SYSTEM AND SHOULD BE REMOVED WHEN THE FERRY TANK IS REMOVED.  PIPE FLARES WERE POORLY MANUFACTURED.  INCOR	RECT PART.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006071800169	20060718	00169		2006	7	18	AU510001692      	1	20050907	G	5102		SUPPORT         																	BALLOON BASKET	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1405 			BA125					(AUS) BALLOON NYLON SUPPORT POLES CRACKED AND BROKEN. (OTHER CAUSE: GROUND HANDLING OF BASKET ) (CASA NR 510001692)																			 
2006061300279	20060613	00279	EA  	2006	6	13	AU510001693      	2	20051212	G	7314		DIAPHRAGM       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			648  		D7073					LT ENGINE FUEL PUMP DIAPHRAGM LEAKING.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061300280	20060613	00280	SO  	2006	6	13	AU510001694      	1	20051212	G	3240		BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					BRAKE ASSY	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT AND RT MAIN WHEEL BRAKE BACKING PLATE ATTACHMENT BOLTS LOOSE.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061400147	20060614	00147	SO  	2006	6	14	AU510001695      	2	20051212	G	8520	634503M010	BEARING         	LYC         		CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	CRANKSHAFT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		412  			0					ENGINE METAL CONTAMINATION.  BULK STRIP FOUND THAT THE TWO REARMOST MAIN BEARINGS WERE DAMAGED.  INSPECTION OF THE CRANK	SHAFT IN THE VICINITY OF THE TWO REARMOST JOURNALS FOUND CRACKS RUNNING LONGITUDINALLY ACROSS JOURNALS TO THE CRANK.					1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006061400150	20060614	00150	EA  	2006	6	14	AU510001696      	2	20050707	G	7414	1052945	SHAFT           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAGNETO	BROKEN          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AU	S 		1667 			EO3HA055					MAGNETO SHAFT SHEARED BETWEEN BEARING P/N 10-81806 AND BEARING SLEEVE PNO 10-357078.  FRACTURE LINES EVIDENT AT BREAK PO	INT.					1	G	7	1 	3O	3	O		H10WE   	E286				 
2006061400153	20060614	00153	WP  	2006	6	14	AU510001697      	1	20051212	G	7820	C16932	MUFFLER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		700  								MUFFLER CRACKED AND DISTORTED IN AREA OF TAILPIPE ATTACHMENT WELD.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061400154	20060614	00154	WP  	2006	6	14	AU510001698      	1	20051107	G	7820	C1693	MUFFLER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					LEFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1197 								MUFFLER CRACKED ON LT SIDE.  LT COLLECTOR ALSO CRACKED.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061400165	20060614	00165	EA  	2006	6	14	AU510001699      	2	20051107	G	7414	10353060	BEARING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MAGNETO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					D071103					LT ENGINE RT MAGNETO FAILED.  INVESTIGATION FOUND THE MAGNETO BEARING HAD COLLAPSED.  HEAT GENERATED DISCOLORED THE CAM 	ASSEMBLY AND MELTED THE PLASTIC BLOCK ON THE CONTACT ASSEMBLY CAUSING THE CONTACTS TO STAY CLOSED.  SUSPECT CAUSED BY IN	CORRECT LUBRICATION OF BEARING.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061400166	20060614	00166	WP  	2006	6	14	AU510001700      	1	20050107	G	3240		BRAKE           			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E51       	NE  	MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT BRAKE GRABBED CAUSING LT MAIN LANDING GEAR TO RUN OFF TAXIWAY AND BECOME BOGGED.  INVESTIGATION COULD FIND NO FAULT W	ITH THE BRAKE SYSTEM EXCEPT FOR A LARGER THAN USUAL AMOUNT OF DUST WHICH WAS ATTRIBUTED TO OPERATING IN THE OUTBACK.					2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603	 
2006061400167	20060614	00167	CE  	2006	6	14	AU510001701      	1	20051007	G	2697	MS3450KT3685	CONNECTOR       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FIRE DETECTION	DAMAGED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 		7961 								LT ENGINE SUFFERED FROM FALSE FIRE WARNING INDICATIONS.  INVESTIGATION FOUND LOW INSULATING RESISTANCE IN FIREWALL CONNE	CTOR J102.  CONNECTOR WAS SECTIONIZED AND EVIDENCE OF INTERNAL CRACKING AND TRACKING WAS FOUND.					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061400169	20060614	00169	NE  	2006	6	14	AU510001702      	2	20051212	G	7261		OIL SYSTEM      			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ENGINE	LOW PRESSURE    	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										ENGINE OIL SYSTEM PRESSURE FLUCTUATING.  INSPECTION FOUND LOW OIL LEVEL BUT NO EVIDENCE OF LEAKS.  OIL TOPPED UP WITH NO	 FAULTS SINCE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006061400170	20060614	00170	CE  	2006	6	14	AU510001703      	1	20051212	G	3220	CESSNA	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	SHEARED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										NOSE LANDING GEAR IDLER BELLCRANK SHEARED AT THE TWO BOLT HOLES FOR THE FORWARD AND AFT PUSH-PULL TUBES.  SUSPECT CAUSED	 BY WORN UPLOCK.					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
2006061500084	20060615	00084	CE  	2006	6	15	AU510001704      	1	20051001	G	7160	642232	ELBOW           			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	AIR INDUCTION	WORN            	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		1185 			0					RT ENGINE AIR INDUCTION HOSE FLEXIBLE ELBOW TORN ON INSIDE RADIUS.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006061500085	20060615	00085	SO  	2006	6	15	AU510001705      	1	20051212	G	5751		SPAR            	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					AILEON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT AILERON ASSEMBLY SPAR CRACKED IN AREA UNDER THE AILERON PUSH-PULL ROD ATTACHMENT BRACKET.  FOUND USING COLOR CONTRAST	 DYE PENETRANT INSPECTION IAW AD/PA31/118 AMDT1.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061500086	20060615	00086	SO  	2006	6	15	AU510001706      	1	20051212	G	5751		SPAR            	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					LT AILERON ASSEMBLY SPAR CRACKED IN AREA UNDER THE AILERON PUSH-PULL ROD ATTACHMENT BRACKET.  FOUND USING COLOR CONTRAST	 DYE PENETRANT INSPECTION IAW AD/PA31/118 AMDT1.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061500090	20060615	00090		2006	6	15	AU510001707      	4	20051208	G	3417	4040831901	CONVERTER       	HONEYWELL   																DADC	OUT OF TOLERANCE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					85071123					DIGITAL AIR DATA COMPUTER (DADC) PRESSURE CONVERTER PS AND PT SENSORS OUT OF TOLERANCE.  FOUND DURING INSPECTION IAW AD/	RAD/43 AMDT5 PART1.																		 
2006061500091	20060615	00091	EU  	2006	6	15	AU510001708      	1	20051208	G	4900		APU             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  						INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										APU FAILED TO START.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500093	20060615	00093	EU  	2006	6	15	AU510001709      	1	20051008	G	2897		WIRE            			BAG   	BAE146	BAE146300A  	1500267	EU  										FUEL SYSTEM	SHORTED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										RT INNER FUEL BOOST PUMP PRESSURE SWITCH TO PRINTED CIRCUIT BOARD WIRE SHORT CIRCUITED.						2	H	7	4 	4F			RT	A49EU   					 
2006061500094	20060615	00094	EU  	2006	6	15	AU510001710      	1	20051008	G	5311		FRAME           			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FUSELAGE FRAME 15 AND FRAME 41 CRACKED.  FOUND DURING INSPECTION IAW AD/BAE146/116.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006061500095	20060615	00095	EA  	2006	6	15	AU510001711      	2	20051212	G	8520	AEL74241PL	PISTON RING     			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		773  								NR 2 CYLINDER PISTON TOP COMPRESSION RING PLASMA COATING DELAMINATING.  TOP RINGS ON ALL OTHER PISTONS SHOWING SIGNS OF 	DELAMINATION BEGINNING TO OCCUR.					1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2006061500097	20060615	00097	NM  	2006	6	15	AU510001712      	1	20051008	G	3233		ACTUATOR        			BOEING	747   	747400      	       	NM  										MLG	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										LOSS OF NR 1 HYDRAULIC SYSTEM FLUID.  INVESTIGATION FOUND THE RT BODY GEAR POSITIONING ACTUATOR HYDRAULIC FUSE LOWER `B`	 NUT LOOSE AND LEAKING.  AIRCRAFT IS FOREIGN REGISTERED.					2	L	7	4 	4F			RT	A20WE   					 
2006061500206	20060615	00206		2006	6	15	AU510001713      	4	20050408	G	3421	H321BTM	GYRO            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ATTITUDE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		41553	210  							STANDBY ATTITUDE INDICATOR TOPPLED.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061600064	20060616	00064		2006	6	16	AU510001714      	4	20051212	G	3421	H321BTM	INDICATOR       			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ATTITUDE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		16249								STANDBY ATTITUDE INDICATOR TOPPLED.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061600065	20060616	00065	NM  	2006	6	16	AU510001715      	1	20051008	G	3232	1U11986	ACTUATOR        			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG DOOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										NOSE LANDING GEAR DOOR ACTUATOR FAILED.  INVESTIGATION OF THE ACTUATOR IN THE WORKSHOP FOUND A FAILURE OF THE DOOR ACTUA	TOR INTERNAL LOCKING MECHANISM.  PART OF THE LOCKING RAM AND PISTON LOCK KEYWAY HAD FRACTURED.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061600066	20060616	00066	NM  	2006	6	16	AU510001716      	1	20050808	G	5712	65B1086366	RIB             			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT WING FIXED TRAILING EDGE RIB AT LOCATED AT WBL 432.65 SEVERED APPROXIMATELY 457.2MM (18IN) FORWARD OF THE TRAILING ED	GE.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061600068	20060616	00068	NM  	2006	6	16	AU510001717      	1	20051212	G	3211	65B143012	TRUNNION        			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT WING LANDING GEAR AFT TRUNNION CRACKED ON INTERNAL SURFACE OF THE SPIGOT BORE LOCATED APPROX 241.3MM (9.5IN) FORWARD 	OF THE AFT FACE BETWEEN THE 6 O`CLOCK AND 9 O`CLOCK POSITIONS.  CRACK CONFIRMED USING HIGH FREQUENCY EDDY CURRENT (HFEC)	 INSPECTION.  FOUND DURING INSPECTION IAW AD/B747/81 AND EI 747-32-48.  FOLLOWING REMOVAL OF PAINT AND CADMIUM PLATING, 	THE TRUNNION WAS AGAIN INSPECTED USING FLUORESCENT PENETRANT INSPECTION (FPI) AND MEDIUM AND HIGH FREQUENCY EDDY CURRENT	 INSPECTION.  THESE INSPECTIONS AS WELL AS VISUAL INSPECTION COULD NOT VERIFY THE CRACKING.  SUSPECT CRACK INDICATION OR	IGINATED IN THE PLATING AND NOT THE BASE METAL.	2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006061600070	20060616	00070	CE  	2006	6	16	AU510001718      	1	20051212	G	3244	184F102	TIRE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					NLG	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										NOSE WHEEL TIRE SHREDDED ON FIRST TAKEOFF FOLLOWING FITMENT.  TIRE FRAGMENTS BROKE THE LENS ON THE LOWER ANTI-COLLISION 	BEACON AND ENTERED THE RT ENGINE CAUSING DAMAGE TO THE INLET DUCT AND A NUMBER OF FAN BLADES.  SUSPECT MANUFACTURING FAU	LT.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006061600080	20060616	00080	NM  	2006	6	16	AU510001719      	1	20051212	G	2612	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             			DE	DESCENT        	1			AU	S 			3134 							REAR BAGGAGE LOCKER SMOKE DETECTOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061600082	20060616	00082	NM  	2006	6	16	AU510001720      	1	20050608	G	5610	58935734	WINDOW          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		12904								NR 4 RT FLIGHT COMPARTMENT WINDOW INNER PANE SHATTERED.  WINDOW HEAT SYSTEM WAS FOUND TO BE SERVICEABLE.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061600141	20060616	00141	EU  	2006	6	16	AU510001721      	1	20051212	G	2611	FON1390606	HOSE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					SMOKE DETECTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT TOILET SMOKE DETECTOR TO AIR EJECTOR HOSE SPLIT AT EJECTOR END.  RT SMOKE DETECTOR TO AIR EJECTOR TUBE SIDEWALL COLLA	PSED.  HOSES ALLOW FOR AIRFLOW THROUGH SMOKE DETECTORS.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061600142	20060616	00142	NM  	2006	6	16	AU510001722      	1	20050908	G	2730	EAL4	CABLE           			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					ELEVATOR	MISROUTED       	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			AU	S 										LT LOWER ELEVATOR CONTROL CABLE INCORRECTLY ROUTED AT FUSELAGE FRAME LOCATED AT BS 1138.  CABLE IS ROUTED OVER FRAME INS	TEAD OF THROUGH LIGHTENEING HOLE.  CABLE HAS CAUSED DAMAGE TO FRAME.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061600143	20060616	00143	SO  	2006	6	16	AU510001723      	1	20050408	G	8120		SHAFT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	TURBOCHARGER	BROKEN          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					GGR00460					RT ENGINE TURBOCHARGER MAIN SHAFT BROKEN.  ENGINE HAD JUST BEEN FITTED FOLLOWING OVERHAUL AND AIRCRAFT WAS ON ACCEPTANCE	 FLIGHT.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061600144	20060616	00144	CE  	2006	6	16	AU510001724      	1	20051212	G	5520		RIVET           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ELEVATOR LT OUTBOARD HINGE BRACKET ATTACHMENT RIVET HEAD CRACKED.  FOUND DURING INSPECTION IAW AD/C400/102 AMDT3.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061600145	20060616	00145	NE  	2006	6	16	AU510001725      	2	20050508	G	7323	430121205	GOVERNOR        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					LT ENGINE	FAULTY          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 		1517 								LT ENGINE POWER TURBINE GOVERNOR FAULTY.  ENGINE OVERSPED TO 110.9%.  OVERSPEED INSPECTION FOUND NIL DEFECTS.						1	G	7	2 	3U	3	U		H13EU   	E5NE10				 
2006061900002	20060619	00002	EU  	2006	6	19	AU510001726      	1	20051212	G	2910		PIPE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					HYDRAULIC SYS	FRACTURED       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					0					HYDRAULIC PIPE LOCATED ON THE FORWARD WALL OF THE REAR CARGO HOLD LEAKING.  INVESTIGATION FOUND A FRACTURED FLARE.  PIPE	 WAS A -4 STAINLESS STEEL TYPE.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061900003	20060619	00003	NM  	2006	6	19	AU510001727      	1	20051208	G	5610	5893543135	WINDOW          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										CAPTAIN`S NR 1 WINDOW CRACKED DUE TO ARCING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061900004	20060619	00004		2006	6	19	AU510001728      	4	20051208	G	2565	737M25651013	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					R1 DOOR	NO TEST         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		8793 	1535 							DOOR 1R ESCAPE SLIDE FAILED TO DEPLOY NORMALLY DURING TEST.  SLIDE CONTACTED EDGE OF DOOR DURING OPENING CAUSING IT TO T	WIST SIDEWAYS.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061900005	20060619	00005	NM  	2006	6	19	AU510001729      	1	20050708	G	2121	732591D	COOLING FAN     			BOEING	747   	747*        	       	NM  	GE    	CF6   	CF680C2B2   	30025	NE  					CABIN AIR	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 		46387	12410							UPPER RECIRCULATION FAN FAILED.  CIRCUIT BREAKER `OHD RECIRC FAN PWR 2` R7 ON P415 TRIPPED.  INVESTIGATION FOUND FAN BEA	RINGS HAD FAILED.					2	L	7	4 	4F	4	F	RT	A20WE   	E13NE				 
2006061900103	20060619	00103	CE  	2006	6	19	AU510001730      	1	20051212	G	2434		BEARING         	PRESTOLITE  		CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ALTERNATOR	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					6101531					RT ENG DRIVEN ALT FAILED.  ALT DRIVE COUPLING SHEARED AND ALT FRONT BEARING COLLAPSED.  RED ELASTOMER MAT`L FROM ALT DRI	VE COUPLING AND MINOR METALLIC PARTICLES VISIBLE INTERNALLY THRU ALT ATTACHMENT PORT.  ALT DISASSEMBLED AND INSPECTED.  	FRONT BEARING SERIOUSLY DETERIORATED.  SEVERAL BALL BEARINGS MISSING, 2 SEVERELY DEFORMED AND REMAINDER SHOWING SIGNS OF	 DISTRESS.  FRONT BEARING SEAL DEFORMED BY MIGRATION OF MISSING BALL BEARINGS THROUGH SEAL INTO ENG.  ROTOR LOOSE DUE TO	 FRONT BEARING FAILURE AND HAD CONTACTED STATOR.  A MIXTURE OF GREASE AND OIL WAS FOUND ADHERING TO INTERNAL SURFACE OF 	FRONT ALT HOUSING.  GREASE/OIL MIXTURE EXHIBITED A PATTERN CONSISTENT WITH BEING FLUNG OUT OF ALT FRONT BEARING.	1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006062100100	20060621	00100	SO  	2006	6	21	AU510001731      	1	20050303	G	3220	40336000	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LINKAGE CRACKED. FOUND DURING INSPECTION IAW MFG SL 1088. (AD/SB DESC: MFG SL 1088 ) (CASA NR 510001731).						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006062100101	20060621	00101	CE  	2006	6	21	AU510001732      	1	20050208	G	5312	12134071	BULKHEAD        			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	HARTZL	HCA2X	HCA2XF1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		11766								(AUS) FUSELAGE DOORPOST BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/C205/21. (AD/SB DESC: AD/C205/21 ) (CASA NR 510	001732)					1	H	7	1 	3O	3	O		3A21    	3E1	5	C	P908	 
2006062100103	20060621	00103	SW  	2006	6	21	AU510001733      	1	20051212	G	2150	20475546	ACM             			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CABIN COOLING	SEIZED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 		2900 	2900 							(AUS) LT AIRCYCLE MACHINE COOLING TURBINE SEIZED. ( MATERIAL ) (CASA NR 510001733)						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006062100104	20060621	00104	CE  	2006	6	21	AU510001734      	1	20051212	G	5740	7133661	FITTING         			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	WING STRUT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FORWARD DOORPOST WING STRUT ATTACHMENT FITTING MISSING 2 RIVETS PN MS20470AD6.  FITTING AND SURROUNDING STRUCTU	RE SHOW EVIDENCE OF REWORK DURING MFG.(MANUFACTURING QUALITY CONTROL ISSUE ) (CASA NR 510001734)					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2006062100105	20060621	00105	CE  	2006	6	21	AU510001735      	1	20051212	G	5312	7606931	SCREW           			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FIREWALL	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL COLUMN/ELEVATOR BELLCRANK TORQUE TUBE SUPPORT SCREWS PNO MS35206-228 (2OFF3) DEFECTIVE. SCREWS APPEAR TO H	AVE BEEN OVERTORQUED DURING ASSEMBLY. (OTHER CAUSE: MANUFACTURING QUALITY CONTROL ISSUE ) (CASA NR 510001735)					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2006062100107	20060621	00107	CE  	2006	6	21	AU510001736      	1	20050408	G	2730	3652400023	CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL CABLE FRAYED. INSPECTION FOUND AT LEAST 4 STRANDS BROKEN INTERNALLY. (CASA NR 510001736)						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
2006062100108	20060621	00108	CE  	2006	6	21	AU510001737      	1	20050208	G	5510	26320208	SUPPORT         			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILIZER OUTER HINGE FITTING CONTAINED SEVERE EXFOLIATION CORROSION. AIRCRAFT OPERATES AS A SEAPLA	NE IN A SALTWATER ENVIRONMENT. SEE ATTACHMENTS FOR PHOTOGRAPHS OF DEFECT.(OTHER CAUSE: ENVIRONMENT ) (CASA NR 510001737)					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2006062100113	20060621	00113	NM  	2006	6	21	AU510001738      	1	20051212	G	5730		STITCHING       			CHILD 	S2    	S2APITTS    	0110201	NM  	LYC   	O360  	AEIO360A1A  	41514	EA  	HARTZL	HCC2Y	HCC2YK4     	GL  	WING SKIN	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					(AUS) TOP WING FABRIC RIB STITCHING LOOSE AND BROKEN. INSPECTION FOUND UNAPPROVED KNOTS IN THE STITCHING WHICH SLIPPED W	HEN PULLED. SEE ATTACHMENT FOR PHOTOGRAPHS. (CASA NR 510001738)					1	Q	7	1 	3O	3	O		A8SO    	1E10	5	C	P920	 
2006062000110	20060620	00110	NE  	2006	6	20	AU510001739      	2	20051212	G	7200		ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					NR 2	MALFUNCTIONED   	W				K				NONE                    				J	O	O	WARNING INDICATION        	OTHER                     	OTHER                     	CR	CRUISE         	1			AU	S 					0					NR 2 ENGINE CHIP DETECTOR MAGNETIC PLUGS (3OFF) CONTAMINATED WITH TYPE 3 FUZZ.  PREVIOUS SOAP ANALYSIS NORMAL.  ENGINE R	EMOVED FOR REPAIR AND INVESTIGATION.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2006062200082	20060622	00082	EU  	2006	6	22	AU510001740      	1	20051212	G	4940	105160001	EXCITER         		GTCP36150R  	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					APU	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					P228					APU IGNITION EXCITER UNIT FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062200084	20060622	00084	NM  	2006	6	22	AU510001741      	1	20051212	G	2700	7321870018	SHUTOFF VALVE   			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FLIGHT CONTROL	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										FLAP/SLAT SHUTOFF VLV LOCATED IN RT W/W LEAKING.  INSPECTION FOUND CAP P/N 732-18718 HAD AN OPEN CRACK AT LAST/OUTERMOST	 THREAD RUNNING 270 DEGREES AROUND ITS CIRCUMFERENCE (CRACKED THROUGH).  HEX-NUT END OF ALUMINUM CAP HAD LIFTED BY 0.1 I	NCHES UNDER HYD PRESS.  CRACK WAS LOCATED ON PRESSURE SIDE OF `O` RING SEAL.  CLOSE EXAM OF FRACTURE SURFACE SHOWED THAT	 CRACK STARTED AT ROOT OF LAST THREAD, PROPAGATED 0.050` AXIALLY (TOWARD THE SHUT-OFF VALVE MODULE), TRAVELED 75% OF WAY	 AROUND CAPS OUTSIDE DIAMETER BEFORE FAILING RADIALLY WITH ONE FRACTURE PLANE. NO BEACH MARKS WERE EVIDENT ON FINAL FRA	CTURE PLANE, INDICATING SUDDEN FAILURE.  CRACK COULD HAVE INITIALIZED DUE TO OVER-TORQUING DURING ASSY, OR FROM SUBSTAND	2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062200086	20060622	00086	CE  	2006	6	22	AU510001742      	1	20051212	G	2710	510105365	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		599  								RT AILERON CARRY THROUGH CABLE WORN TO LIMITS.  CABLE WAS WORN BY THE PHENOLIC RUB BLOCK LOCATED AT WS 71.125.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2006062200088	20060622	00088	NM  	2006	6	22	AU510001743      	1	20051212	G	2150	AS13806NO130L	HOSE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					LT ACM	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										LT AIR CONDITIONING PACK AIRCYCLE MACHINE SENSE LINE LEAKING.  HOSE APPEARS TOO LONG CAUSING TO TIGHT A CURVE RAD.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006062200089	20060622	00089	NM  	2006	6	22	AU510001744      	1	20051008	G	2760		BEARING         			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					DRAG CONTROL	COLLAPSED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 					0					GROUND SPOILER QUADRANT UPPER AND LOWER BEARINGS COLLAPSED.  SPOILER DIFFERENTIAL MIXER P/N 10-60841-8 ROUGH IN OPERATIO	N.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006062200091	20060622	00091		2006	6	22	AU510001745      	4	20050908	G	3417		ADC             			BOEING	737   	737*        	       	NM  											FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										AIR DATA COMPUTER FAILED.  AIRCRAFT IS FOREIGN REGISTERED.						2	L	7	2 	4F			RT	A16WE   					 
2006062100114	20060621	00114		2006	6	21	AU510001746      	4	20051212	G	2565	737M25651013	GIRT BAR        			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					SLIDE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		45165	588  							(AUS) DOOR R1 ESCAPE SLIDE GIRT BAR CONTACTING DOOR FRAME.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006062100115	20060621	00115	NM  	2006	6	21	AU510001747      	1	20051212	G	2822		PUMP            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FWD BOOST PUMP SUSPECT FAULTY. CB POPPED. ON DISASSEMBLY INVESTIGATION FOUND SEVERE SCORING WAS ON PUMP HSG IMP	ELLER BORE INSIDE DIAMETER, SHAFT AND ROTOR ASSY WAS SCORED ON BRG JOURNAL AREA. SEVERE SCORING COULD BE CAUSED BY FOD P	ASSING THROUGH PUMP. EVIDENCE OF FOD WAS NOT FOUND DURING DISMANTLE INDICATING THAT IT HAD PASSED THROUGH. ABNORMAL WEAR	 ON SHAFT BRG JOURNAL, POSSIBLY CAUSED BY FOD, HSG CARBON BRG AREA CAUSED IMPELLER TO RUB ON HSG IMPELLER BORE RESULTING	 IN AN EXCESSIVE AMPERAGE DRAW,CAUSED CB TO TRIP.  (CASA NR 510001747)		2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062300042	20060623	00042	NM  	2006	6	23	AU510001748      	1	20051212	G	2530	8653020000	OVEN            			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					GALLEY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 		1429 	1032 							(AUS) NR 5 REAR GALLEY OVEN FAULTY.  SMOKE AND FUMES IN CABIN.  SUSPECT CAUSED BY SHORTED/BURNED OVEN FAN MOTOR.  (CASA 	NR 510001748)					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006062300068	20060623	00068	NM  	2006	6	23	AU510001749      	1	20051212	G	3242	AS11506K0264	HOSE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					BRAKE SYS	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LOSS OF RT HYDRAULIC SYSTEM FLUID. INVESTIGATION FOUND NR 3 BRAKE HYDRAULIC HOSE CHAFED THOUGH. (CASA NR 510001749	)					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062300069	20060623	00069	EU  	2006	6	23	AU510001750      	1	20051212	G	3270		INDICATOR       			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502*     	41580	EA  					TAIL STRIKE	DAMAGED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT EXPERIENCED A HIGH SINK RATE DURING LANDING. INVESTIGATION FOUND THAT THE MAIN LANDING GEAR AND TAILSKID 	CONTACTED THE GROUND CAUSING DAMAGE TO THE TAIL STRIKE INDICATOR. (CASA NR 510001750)					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006062300070	20060623	00070	EU  	2006	6	23	AU510001751      	1	20051212	G	4930	38828405	FUEL CONTROL    			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					APU	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) APU AUTO-SHUTDOWN IN FLIGHT. INVESTIGATION FOUND A FAULTY FUEL CONTROL UNIT.  (CASA NR 510001751)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062300071	20060623	00071	EU  	2006	6	23	AU510001752      	1	20051212	G	2611	RAI2811M0103	CONTROL UNIT    			AIRBUS	330   	A330300     	       	EU  	GE    	CF6   	CF680       	30025	NE  					SMOKE DETECTOR	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) CARGO COMPARTMENT SMOKE WARNINGS. FORWARD CARGO FIRE BOTTLES DISCHARGED. EMERGENCY LANDING CARRIED OUT. LOCAL AUTH	ORITIES REPORTED A (WHITE POWDER) IN THE WHEEL WELL AREA. DURING EMERGENCY EVACUATION, DOOR 1L ESCAPE SLIDE FAILED TO DE	PLOY. ALL OTHER SLIDES DEPLOYED SUCCESSFULLY. INVESTIGATION FOUND THE FALSE SMOKE WARNING WAS CAUSED BY A DESIGN DEFICIE	NCY IN THE SMOKE DETECTOR CONTROL UNIT (SDCU). NOTE: FAILURE OF THE SLIDERAFT TO DEPLOY IS COVERED BY SDR 510001917. (CA	SA NR 510001752)		2	L	7	2 	4F	4	F	RT	        	E13NE				 
2006062300072	20060623	00072	NM  	2006	6	23	AU510001753      	1	20051212	G	3233		B-NUT           			BOEING	747   	747400      	       	NM  										NR 1 HYD SYSTEM	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 HYDRAULIC SYSTEM LEAKING. INVESTIGATION FOUND A LOOSE B-NUT ON THE LANDING GEAR TRUCK POSITIONING ACTUATOR FU	SE LOCATED ON THE AFT WHEEL WELL AT STN 1440.  AIRCRAFT IS FOREIGN REGISTERED. (CASA NR 510001753)					2	L	7	4 	4F			RT	A20WE   					 
2006062300073	20060623	00073	EA  	2006	6	23	AU510001754      	2	20050708	G	7414	M3975	COIL            	SLICK       		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					MAGNETO	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3030784					(AUS) MAGNETO COIL FAULTY.  INVESTIGATION FOUND THE SECONDARY WINDINGS OPEN CIRCUITED. (CASA NR 510001754)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006062300074	20060623	00074	EA  	2006	6	23	AU510001756      	2	20051212	G	8530	AEL74241PL	PISTON RING     			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					ENGINE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		785  								(AUS) ENGINE OIL FOUND TO BE VERY BLACK. INSPECTION FOUND THE PLASMA COATING ON THE TOP PISTON RINGS ON ALL FOUR CYLINDE	RS FRACTURED. (CASA NR 510001756)					1	L	7	2 	3O	3	O		A29CE   	E286				 
2006062300075	20060623	00075	NM  	2006	6	23	AU510001757      	1	20051212	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILERS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		12639								(AUS) RT IB ROLL SPOILER ACTUATOR BODY FAILED ALLOWING LOSS OF HYDRAULIC FLUID. (OTHER CAUSE: MATERIAL ) (CASA NR 510001	757)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300076	20060623	00076	NM  	2006	6	23	AU510001758      	1	20051212	G	3230		LOCK            			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG	INCORRECT       	W				O				OTHER                   				W			INADEQUATE Q C            			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR WOULD NOT RETRACT. INVESTIGATION FOUND THE NOSE LANDING GEAR GROUND LOCK (ENGAGED).  PERSONNEL/M	AINTENANCE ERROR. (CASA NR 510001758)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300215	20060623	00215	GL  	2006	6	23	AU510001759      	1	20050306	G	8010	687181A24VVN1113	SOLENOID        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		346  	346  							(AUS) STARTER SOLENOID FAILED. SUSPECT CAUSED BY FAILURE AND CRACKING OF END CAP WHICH ALLOWED COPPER DUST TO LEAK OUT. 	 (CASA NR 510001759)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2006062300216	20060623	00216	GL  	2006	6	23	AU510001760      	1	20051212	G	8010	PN687181A24VVN11	SOLENOID        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		451  	451  							(AUS) STARTER SOLENOID FAILED. SUSPECT CAUSED BY FAILURE AND CRACKING OF END CAP WHICH ALLOWED COPPER DUST TO LEAK OUT. 	 (CASA# 510001760)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2006062300217	20060623	00217	NM  	2006	6	23	AU510001761      	1	20051212	G	3246	314353	WHEEL           			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			13   							(AUS) LT IB MAIN WHEEL ASSY INCORRECTLY FITTED.  INVESTIGATION FOUND THAT DURING INSTALLATION INNER WHEEL HALF BRAKE ROT	OR DRIVE KEYS HAD NOT BEEN ENGAGED WITH THE ROTOR SLOTS. THIS RESULTED IN THE WHEEL HALF DRIVE KEYS DRIVING THE BRAKE RO	TORS VIA THEIR CHAMFERED EDGES. IN ADDITION SOME DAMAGE TO THE BRAKE ROTOR WAS FOUND. PERSONNEL/MAINTENANCE ERROR. (CASA	 NR510001761)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300218	20060623	00218	GL  	2006	6	23	AU510001762      	1	20051212	G	2434	ES4024LP	ALTERNATOR      			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		199  								(AUS) ALTERNATOR FAILED. INVESTIGATION FOUND STATOR TO DIODE FEEDER WIRES CHAFING ON HOUSING AND SHORTED. BRUSH WIRE TAI	L FOUND TO BE RUNNING ON STATOR BRUSH RING. (CASA NR 510001762)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
2006062300220	20060623	00220	GL  	2006	6	23	AU510001764      	1	20051212	G	2432	G243	BATTERY         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	MASTER	FAULTY          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		155  								(AUS) AIRCRAFT BATTERY INTERNAL FAULT. BATTERY HAD HIGH CURRENT DRAW CAUSING LOSS OF ELECTRICAL POWER.  (CASA# 510001764	)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2006062300221	20060623	00221	GL  	2006	6	23	AU510001765      	1	20050408	G	3710	216CWWIP	PUMP            			AMTR  	LANCAR	LC41550FG   	5150001	GL  										VACUUM SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VACUUM PUMPS FAILED.  (OTHER CAUSE: MATERIAL - DEBRIS REMAINING AFTER FAILURE ) (CASA NR 510001765)						1	L	7	1 	3O			RT	EXPA1L71					 
2006062300222	20060623	00222	EU  	2006	6	23	AU510001766      	1	20051212	G	5100	D9251015520000	HINGE PIN       			AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					BATTERY BOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		3942 								(AUS) 103VU PANEL HINGE PIN LOOSE. NO CONTACT WITH ADJACENT ELECTRICAL HARNESS. FOUND DURING INSPECTION IAW AD/A320/175.	(AD/SB DESC: AD/A320/175 ) (CASA NR 510001766)					2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2006062300223	20060623	00223	CE  	2006	6	23	AU510001767      	1	20051212	G	5712	57222062	CAP             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		20514								(AUS) RT WING CANTED RIB CAP CRACKED. CRACK LENGTH APPROXIMATELY 40MM (1.574IN). CRACK WAS LOCATED IN THE RADIUS OF THE 	UPPER CAP AND TRAVELLED REARWARDS FROM THE AUXILIARY SPAR. FOUND DURING NDI IAW SB CQB03-01 PART B REV 1. (AD/SB DESC: S	B CQB03-01 PART B REV 1 ) (CASA NR 510001767)				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006070500047	20060705	00047	CE  	2006	7	5	AU510001768      	1	20051212	G	5520	58321672	BRACKET         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR OB HINGE ASSY IB ATTACHMENT BRACKET CRACKED IN LOWER FORWARD RADIUS. FOUND DURING INSPECTION IAW AD/C4	00/102 AMDT 3 PART 3. BOTH LT AND RT ELEVATOR OB BRGS STIFF IN OPERATION.  (AD/SB DESC: AD/C400/102 AMDT 3 PART 3 ) (CAS	A NR 510001768)				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006070500048	20060705	00048	CE  	2006	7	5	AU510001769      	1	20051212	G	3260	MS25237327	BULB            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG INDICATOR	BURNED OUT      	W				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR POSITION INDICATOR LIGHT BULB BLOWN. (CASA NR 510001769)						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006070300010	20060703	00010	CE  	2006	7	3	AU510001770      	1	20051212	G	7921		GASKET          			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCB3Z	HCB3Z302    	GL  	OIL COOLER	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										RT ENGINE OIL COOLER LOWER FITTING GASKET FAILED.  LOSS OF ENGINE OIL.						1	L	7	2 	3O	3	O		3A20    	1E15	5	C	P907	 
2006070500049	20060705	00049	CE  	2006	7	5	AU510001771      	1	20051212	G	3260	444EN3R	SQUAT SWITCH    			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RT MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 		3664 								(AUS) RT MAIN LANDING GEAR IB SQUAT SWITCH FAILED. (OTHER CAUSE: AGE ) (CASA NR 510001771)						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006070500050	20060705	00050	EU  	2006	7	5	AU510001772      	2	20051212	G	7200		TURBINE BLADES  			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE MAKING (POPPING) SOUNDS.  SOUNDS INCREASED WHEN THRUST LEVER INCREASED AND DECREASED WHEN THRUST LEVER	 RETARDED. BORESCOPE INSPECTION FOUND HPC BLADES DAMAGED BEYOND LIMITS. INVESTIGATION CONTINUING. (CASA NR 510001772)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500051	20060705	00051	NM  	2006	7	5	AU510001773      	1	20051212	G	7830	UL27562	FAIRING         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE THRUST REVERSER BLOCKER DOOR DAMAGED.  INVESTIGATION FOUND THE RT INNER (A) FRAME FAIRING FAILED AND A	 PIECE WEDGED UNDER THE BLOCKER DOOR. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA NR 510001773)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006070500052	20060705	00052	NM  	2006	7	5	AU510001774      	1	20051008	G	2421	766088B	IDG             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					GENERATOR	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		7255 	969  							(AUS) RT INTEGRATED DRIVE GENERATOR (IDG) FAILED.  INITIAL INVESTIGATION FOUND BENT PINS  2, 9 AND 10 ON ELECTRICAL CONN	ECTOR (B).  STRIP AND INVESTIGATION FOUND THE LT AND RT FIXED END CYLINDER BLOCKS TO PORT PLATES MATING FACES WERE SCORE	D. THE CONTROL CYLINDER`S CONTROL ROD WAS FOUND TO BE VERY NOTCHY IN OPERATION.  (CASA NR 510001774)				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006070500053	20060705	00053	WP  	2006	7	5	AU510001775      	2	20051212	G	7261		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	LT ENGINE OIL	LOOSE           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE MAIN OIL PRESSURE LINE TO BETA MANIFOLD LOOSE AND LEAKING. LOSS OF ENGINE OIL. (OTHER CAUSE: UNKNOWN ) (	CASA NR 510001775)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006070300061	20060703	00061	CE  	2006	7	3	AU510001776      	1	20051212	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		17021								LT WING ROOT CANTED RIB UPPER CAP LOCATED AT CWS 26.85 CRACKED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006070300062	20060703	00062	CE  	2006	7	3	AU510001777      	1	20051212	G	5711	LH10810000023RH1	SPAR            			BEECH 	77    	77          	1153007	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	WINGS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		7374 								LT AND RT WING REAR SPARS PNO 108-100000-23 (LT) AND P/N 108-100000-24 (RT) FAULTY.  EVIDENCE OF WING MOVEMENT AT SKIN I	NTERSECTIONS ON TOP OF EACH WING.					1	L	7	1 	3O	3	O		A30CE   	E223	5	N	P9045	 
2006070300063	20060703	00063	SO  	2006	7	3	AU510001778      	1	20050808	G	3213	AN7	BOLT            			MAULE 	MT7235	MT7235      	5470209	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					MLG	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 		745  			0					MAIN LANDING GEAR BOLT INCORRECT PART.  BOLT IS AN AN7-24 TYPE ITEM.						1	H	7	1 	3O	3	O	NC	3A23    	1E4				 
2006070300064	20060703	00064	SO  	2006	7	3	AU510001779      	1	20051212	G	2434	ALX9525B	ALTERNATOR      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		12   	12   							LT AND RT ALTERNATORS REMOVED FROM AIRCRAFT FOR INTERNAL INSPECTION FOLLOWING PURCHASE OF AIRCRAFT.  BOTH ALTERNATORS WE	RE FOUND TO CONTAIN NUMEROUS DEFECTS.  ALTERNATORS HAD ONLY 12 HOURS TSO.  ALTERNATORS WERE `KELLY AEROSPACE` ITEMS.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P25EA	 
2006070300065	20060703	00065	SO  	2006	7	3	AU510001780      	2	20051212	G	8530	AEC631397	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  					ENGINE	DETERIORATED    	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			AU	S 		86   								ENGINE CYLINDER NICKEL CARBIDE CYLINDER WALL COATING SEPARATED FROM BARREL.  AREA OF MISSING COATING WAS APPROXIMATELY 1	0MM BY 35MM (0.39IN BY 1.37IN) LOCATED AT THE TOP OF THE BORE NEAR THE TOP SPARK PLUG HOLE.					1	H	7	1 	3O	3	O		A4CE    	E3SO				 
2006070300066	20060703	00066	SO  	2006	7	3	AU510001781      	2	20050407	G	8540	643109	SPRING          	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					STARTER ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1061 								ENGINE STARTER ADAPTER SPRING END TANG BROKEN OFF.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006070300067	20060703	00067	NM  	2006	7	3	AU510001782      	1	20051108	G	2820		FUEL SYS        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  						FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										UNCOMMANDED INFLIGHT FUEL TRANSFER.  INVESTIGATION COULD NOT FIND ANY MECHANICAL CAUSE FOR THE DEFECT.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006070300068	20060703	00068		2006	7	3	AU510001783      	2	20051008	G	7261		BOLT            			BOEING	747   	747400      	       	NM  										ENGINE	LOOSE           	W				O				OTHER                   				K	Y	J	FLUID LOSS                	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										NR 3 ENGINE INFLIGHT SHUTDOWN DUE TO OIL LOSS.  INVESTIGATION FOUND LOOSE BOLTS (2OFF) ON THE TRANSFER DRIVE LOWER FITTI	NG.  AIRCRAFT IS FOREIGN REGISTERED.					2	L	7	4 	4F			RT	A20WE   					 
2006070300069	20060703	00069	CE  	2006	7	3	AU510001784      	1	20050908	G	8011	EBB131A	GEAR            			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	STARTER	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		196  			EO94821					ENGINE STARTER MOTOR DRIVE GEAR DISINTEGRATED.  ENGINE RING GEAR DAMAGED.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857	 
2006070300070	20060703	00070	SO  	2006	7	3	AU510001785      	1	20051212	G	3222	4033600	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NOSE LANDING GEAR LINK ASSEMBLY CRACKED AS REFERENCED IN PIPER SL 1088.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006070500124	20060705	00124		2006	7	5	AU510001786      	4	20050307	G	2310	8220987003	COUPLER         			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					HF COMMS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) NR 1 HF SYSTEM ANTENNA COUPLER FAILED. (CASA NR 510001786)						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500125	20060705	00125	CE  	2006	7	5	AU510001787      	1	20051212	G	5753	16916000520	RIB             			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		3361 								(AUS) LT FLAP IB HINGE BRACKET ATTACHMENT RIB SEVERELY CORRODED.  FOUND DURING INSPECTION IAW AD/23/43.(AD/SB DESC: AD/ 	23/43 ) (CASA NR 510001787)					1	L	7	1 	3O	3	O		A1CE    	1E10	5	C	P43GL	 
2006070500127	20060705	00127	EU  	2006	7	5	AU510001788      	1	20051212	G	2822	41400017RX	PUMP            			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	FUEL BOOST	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 		783  	783  							(AUS) AUXILIARY FUEL PUMP DRIVE SHEARED. PUMP IS LOCATED BENEATH COPILOT SEAT.(OTHER CAUSE: MATERIAL ) (CASA NR 51000178	8)					1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2006070500128	20060705	00128	EA  	2006	7	5	AU510001789      	2	20051208	G	7314	RG17980DM	PUMP            			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	FUEL SYS	FAILED          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		762  	762  							(AUS) ENGINE DRIVEN FUEL PUMP FAILED. (CASA NR 510001789)						1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2006070500129	20060705	00129	NM  	2006	7	5	AU510001790      	1	20051212	G	3320	79341	BALLAST         			BOEING	737   	737         	UTILSYS	NM  										CABIN LIGHTS	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 					6308					(AUS) ELECTRICAL BURNING SMELL IN CABIN. INVESTIGATION FOUND EVIDENCE OF OVERHEATED FLUORESCENT CABIN LIGHTING BALLAST. 	AIRCRAFT IS FOREIGN REGISTERED. (CASA NR 510001790)					2	L	7	2 	4F			RT	A16WE   					 
2006070500130	20060705	00130		2006	7	5	AU510001791      	4	20051212	G	3417	7006988975	CIRCUIT CARD    																	ADC	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DIGITAL AIR DATA COMPUTER (DADC) CIRCUIT CARD ASSEMBLY (CCA) INTERNAL FAULT.  FOUND DURING INSPECTION IAW AD/INST/	9 AND FAR43E.(AD/SB DESC: AD INST 9 FAR43E ) (OTHER CAUSE: MATERIAL ) (CASA NR 510001791)																		 
2006070500139	20060705	00139	EA  	2006	7	5	AU510001792      	2	20051212	G	8520	AEL74241PL	PISTON RING     			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		717  								(AUS) ENGINE PISTON TOP COMPRESSION RINGS EXHIBITED SLIGHT SIGNS OF DELAMINATION.  ENGINE OIL VERY DIRTY. PREMATURE WEAR	 ALSO FOUND ON EXHAUST VALVE ROTATING CAPS. (CASA NR 510001792)					1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2006070500140	20060705	00140		2006	7	5	AU510001793      	4	20051212	G	2340	5145142	AUDIO PANEL     			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	FAULTY          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) SMOKE AND FUMES IN IN COCKPIT. INVESTIGATION FOUND CAPTAIN`S INTERPHONE SYSTEM AUDIO SELECTOR PANEL FAULTY WITH TH	E MIC SELECTOR SWITCH STUCK AND THE LED NOT WORKING. SUSPECT CAUSED BY FLUID SPILLAGE CAUSING CORROSION.  (CASA NR 51000	1793)				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500215	20060705	00215	CE  	2006	7	5	AU510001794      	1	20051212	G	2752	C1444881	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					TE FLAPS	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		4885 								(AUS) RT OB FLAP ACTUATOR WORN EXCESSIVELY IN GIMBAL TO SCREWJACK ATTACHMENT AREA. FURTHER INVESTIGATION FOUND THE ACTUA	TOR GIMBAL LOWER PIN MISSING. UPPER GIMBAL PIN RETAINING CLIP CORRODED.  (OTHER CAUSE: MATERIAL - AGE ) (CASA NR 5100017	94)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006070500123	20060705	00123	NE  	2006	7	5	AU510001795      	2	20051212	G	8500		ENGINE          			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E51       	NE  		MALFUNCTIONED   	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 		9118 	713  				7043			ENGINE SHUT DOWN DUE TO ROUGH RUNNING.  INVESTIGATION CONTINUING.						2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603	 
2006070500236	20060705	00236	NM  	2006	7	5	AU510001796      	1	20051212	G	5610	141A481018	WINDOW          			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) F/O NR 2 SLIDING WINDOW SHATTERED. (CASA NR 510001796)						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500237	20060705	00237	EU  	2006	7	5	AU510001797      	1	20051212	G	2761	P308450102	JACKSHAFT       			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LIFT SPOILER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		31055	8406 							(AUS) LT CENTER AND RT OB LIFT SPOILER JACKS CORRODED BEYOND LIMITS IN PISTON THREADS FOR EYE ENDS. FOUND DURING INSPECT	ION IAW AAES ER BA6-27-60-23B AND BAE SYSTEMS SB 27-176. (CASA NR 510001797)					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006070500126	20060705	00126	CE  	2006	7	5	AU510001798      	1	20051212	G	2731	332X375TYPE3	SHEAR PIN       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ELEVATOR	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 										ELEVATOR ACTUATOR DRIVE SHEAR PINS FAILED.						1	L	7	2 	3O	3	O		3A10    	E5CE				 
2006070500238	20060705	00238	CE  	2006	7	5	AU510001799      	1	20051212	G	3260	602EN556B	SWITCH          			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	GEAR UPLOCK	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK MICROSWITCH FAILED. SWITCH HAD ONLY 54.5 HOURS OPERATION SINCE REPLACEMENT. (CASA NR 5	10001799)					1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006070500239	20060705	00239	CE  	2006	7	5	AU510001800      	1	20051212	G	5320	4118991	STIFFENER       			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2482 								(AUS) LT LANDING GEAR GEAR ATTACHMENT SADDLE (STIFFENER) CORRODED IN AFT LOWER SECTION.  EVIDENCE OF DELAMINATION THROUG	H THE FULL HEIGHT OF THE LOWER SECTION. SEE ATTACHMENT FOR PHOTOGRAPHS OF DEFECT. (CASA NR 510001800)					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006071000109	20060710	00109	EU  	2006	7	10	AU510001802      	1	20051212	G	4940	51895411	MOTOR           	HONEYWELL   		FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STARTER	SHEARED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 		1511 			P228					APU STARTER MOTOR DRIVE SHAFT SHEARED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000112	20060710	00112	EU  	2006	7	10	AU510001803      	1	20051212	G	3233	AIR864101	ACTUATOR        			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					RT MLG	SLUGGISH        	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 										RT MAIN LANDING GEAR RETRACTION ACTUATOR SLUGGISH IN OPERATION.  INVESTIGATION CONTINUING.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2006071000113	20060710	00113	EU  	2006	7	10	AU510001804      	1	20051212	G	3246		BOLT            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MAIN WHEEL ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		25764	456  		OCT940013					NR 2 MAIN WHEEL TIE BOLT BROKEN.  BOLT HEAD MISSING.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000114	20060710	00114		2006	7	10	AU510001805      	4	20051212	G	3441	HG1050AD04	IRU             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  						FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 		41061								NR 2 INERTIAL REFERENCE UNIT (IRU) INTERMITTENTLY FAILS CODE 2.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000115	20060710	00115	NE  	2006	7	10	AU510001806      	2	20051212	G	7297	C821805	POWER CABLE     			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	LT ENGINE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		30326								LT ENGINE POWER CABLE SEPARATED IN AREA LOCATED BETWEEN WHEEL WELL AND CABLE TERMINAL PULLEY SECTOR.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2006071000116	20060710	00116		2006	7	10	AU510001807      	4	20050109	G	3421	H301BAM	INDICATOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ART HORIZ	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 		18009								STANDBY ARTIFICIAL HORIZON (AH) FAULTY.  AH HAS A SLIGHT TILT TO THE LEFT.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000117	20060710	00117	EU  	2006	7	10	AU510001808      	1	20051212	G	5751		SKIN            	BAC         		BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT AILERON PN HC576C0077-000 CRACKED AT THE SECOND OUTBOARD AILERON HINGE FOR THE OUTBOARD TAB.  RT AILERON PN HC576C007	7-001 ALSO CRACKED AT THE OUTBOARD TAB HINGE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006071000118	20060710	00118	CE  	2006	7	10	AU510001809      	1	20050209	G	5712	5720013S	RIB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		17021								LT WING UPPER FORWARD PN 572001-3S AND AFT PN 572001-5S DRAG ANGLES CRACKED.  FOUND DURING EDDY CURRENT INSPECTION IAW C	QB03-1 REV 1.  EDDY CURRENT INSPECTION REVEALED A TOTAL OF NINE CRACKS ALL AROUND 5MM (0.196IN) IN LENGTH.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006071000119	20060710	00119	SO  	2006	7	10	AU510001810      	1	20050208	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 		1495 	1495 							RT ENGINE TURBOCHARGER FAILED.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006071100162	20060711	00162	SO  	2006	7	11	AU510001811      	1	20051212	G	3246	MS2125005016	BOLT            	BFGOODRICH  	314461      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	MGL WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			434  		2447					(AUS) LT OB MAIN WHEEL TIE BOLTS BROKEN.  INVESTIGATION CONTINUING. (CASA NR 510001811)						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006071100163	20060711	00163	NM  	2006	7	11	AU510001812      	1	20051212	G	7830		BLOCKER DOOR    	RROYCE      		BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					THRUST REVERSER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE THRUST REVERSER BLOCKER DOORS (3OFF) DAMAGED. INVESTIGATION ALSO FOUND RT ENGINE GAS GENERATOR FAIRING A	T RT SIDE (A) FRAME DAMAGED. RT ENGINE GAS GENERATOR FAIRING (A) FRAME FAIRING LOWER HALF DAMAGED. RT ENGINE GAS GENERAT	OR FAIRING (A) FRAME FAIRING TOP HALF MISSING. DURING GAS GENERATOR FAIRING REPLACEMENT FORWARD ATTACHMENT BRACKETS (4OF	F) FOUND DAMAGED. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA NR 510001812)			2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006071100168	20060711	00168		2006	7	11	AU510001813      	4	20051212	G	3452	G699010	CONTROL PANEL   			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ATC TRANSPONDER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ATC TRANSPONDER CONTROL PANEL FAILED. (CASA NR 510001813)						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006071100169	20060711	00169	GL  	2006	7	11	AU510001814      	3	20051212	G	6111	C5022	SPRING          	MCAULY      		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	3G34C6	3GFR34C601  	GL  	PROPELLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					816212					(AUS) PROPELLER FEATHERING AND UNREVERSING SPRING FAILED. (CASA# 510001814)						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P54GL	 
2006060800093	20060608	00093	NM  	2006	6	8	AU510001815      	1	20051212	G	2620		CIRCUIT BREAKER 			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					APU FIRE EXTING	TRIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										APU FIRE EXTINGUISHING SYSTEM CIRCUIT BREAKER PULLED AND RED COLLARED.  CIRCUIT BREAKER RESET AND SYSTEM TESTED SERVICEA	BLE.  SUSPECT CIRCUIT BREAKER PULLED WHEN MEL APPLIED AND NOT RESET WHEN MEL CLEARED.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800094	20060608	00094	SO  	2006	6	8	AU510001816      	2	20051212	G	8520	6461402	STUD            			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	NR 5 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			981  				276339R			RT ENGINE NR 5 CYLINDER HOLD-DOWN STUDS (2OFF) BROKEN OFF FLUSH WITH THE CYLINDER BASE.						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006060800095	20060608	00095	CE  	2006	6	8	AU510001817      	1	20050109	G	3710		SHAFT           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					VACUUM PUMP	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					36914					VACUUM PUMP DRIVE SHAFT SHEARED DUE TO INTERNAL PUMP FAILURE.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006060800096	20060608	00096	WP  	2006	6	8	AU510001818      	2	20051212	G	7261	30719496	PUMP            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT ENGINE OIL	FAULTY          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 							P74668			RT ENGINE OIL LUBRICATION PUMP FAULTY.  OIL WAS NOT SCAVENGED FROM NR 6 BEARING AREA AND WAS LEAKING OUT THROUGH THE BEA	RING SEAL.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006060800097	20060608	00097	WP  	2006	6	8	AU510001819      	2	20051212	G	7260		SHAFT           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE	FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AU	S 							P74668			ENGINE CHIP DETECTOR CONTAMINATED WITH METAL PARTICLE.  SUSPECT ACCESSORY SECTION TOWER SHAFT OR POWER SHAFT FAILED.  IN	VESTIGATION CONTINUING.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006060800298	20060608	00298	SW  	2006	6	8	AU510001820      	1	20050109	G	5711		SPAR            			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										DURING MOD REPAIR, NUMEROUS DEFECTS FOUND RELATING MAINLY TO CORROSION IN WING & ATTACH STRUCTURE.  FOLLOWING DEFECTS FO	UND,  EXFOLIATION OF EXTRUSIONS ON REAR SPAR CAPS IN BOTH W/W.  CNTR SECTION OF 1 PIECE WING OPENED UP FOR INSPECT & REV	EALED OLD FIBERGLASS TYPE INSULATION & 2 DEAD RATS.  CLEANING THIS AREA REVEALED SEVERE EXFOLIATION OF EXTRUSIONS AROUND	 LT MAIN SPAR ATTACHMENT FITTING.  REMOVAL OF WING TO FURTHER ASSESS VIABILITY OR REPAIR & REVEALED MORE CORROSION OF ST	EEL FRAME AT WING ATTACHMENT FITTINGS AND FUSELAGE STR`S EXFOLIATING AT ATTACHMENT TO STEEL TUBE FRAME.  WING ATTACHMENT	 BOLTS SEVERELY RUSTED & BOLTS AND LOCKWIRE WERE STILL PAINTED BLUE FROM PREVIOUS PAINT JOB TO A/C SOME YEARS PRIOR.	1	L	7	1 	3O	3	O		2A3     	E286	5	C	P920	 
2006060800098	20060608	00098		2006	6	8	AU510001821      	4	20050209	G	3442	MI585353	ANTENNA         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	WX RADAR SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										WEATHER RADAR ANTENNA FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060800099	20060608	00099	NM  	2006	6	8	AU510001822      	1	20050109	G	6120		CONTROL ROD     			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	LT PROPELLER	FOULED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT PROPELLER CONTROL ROD ATTACHMENT BOLT SPLIT PIN TAIL FOULING ON POWER LEVER CONTROL ROD RODEND LOCKNUT LOCKWIRING.  T	HIS CAUSED THE LT PROPELLER CONTROL LEVER TO STICK AND THE LT POWER LEVER TO MOVE THE PROPELLER CONTROL LEVER WAS MOVED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060800178	20060608	00178	EU  	2006	6	8	AU510001823      	1	20051212	G	5540	TB10310000	HINGE           			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2966 			0					FOUND TOP RUDDER HINGE CORRODED.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2006060800180	20060608	00180	EU  	2006	6	8	AU510001824      	1	20051212	G	7120	TB1050001000	MOUNT           			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2966 								ENGINE MOUNT CRACKED.  FOUND DURING INSPECTION IAW AD/TB10/8 AND TBSB NO 16/1.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2006060800182	20060608	00182	EU  	2006	6	8	AU510001825      	1	20051212	G	5520	TB1034020001	HINGE           			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ELEVATOR TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2966 								RT STABILATOR HINGE CORRODED, AD/SB DESC: CASA SCHEDULE 5.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2006060800184	20060608	00184	NM  	2006	6	8	AU510001826      	1	20051212	G	2997	DP1204	CONNECTOR       			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HYD PUMP	BROKEN          	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			AU	S 		7044 	7044 							LOSS OF SYSTEM `A` HYDRAULIC PRESSURE AND QUANTITY.  INVESTIGATION FOUND THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP CONNECTOR	 DP1204 HARD PLASTIC INSERT BROKEN.  METAL CONTAMINATION OF HYDRAULIC FILTER.  BURNING SMELL DURING TAKEOFF SUSPECTED TO	 BE HYDRAULIC PUMP OIL RESIDUE.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800187	20060608	00187	SW  	2006	6	8	AU510001827      	1	20050509	G	2150	20475546	ACM             			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CABIN COOLING	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 			1035 							RT AIRCYCLE MACHINE (ACM) FAILED.  SMOKE AND FUMES IN AIRCRAFT.						2	L	7	2 	4T	3	T	RT	A5SW    	E3WE	6	C	3PNE	 
2006060800189	20060608	00189	CE  	2006	6	8	AU510001828      	1	20050209	G	8011	MMU4001R	MOTOR           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	STARTER	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		45   								ENGINE STARTER MOTOR INTERNAL SHORT CIRCUIT.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2006060800336	20060608	00336	NM  	2006	6	8	AU510001829      	1	20051212	G	5320	85CH70020A	INTERCOSTAL     			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					BS 140	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										INTERCOSTAL CRACKED.  CRACK LOCATED AT FORWARD FACE OF BS 140 FPB AT LBL 20 AT 2 O`CLOCK POSITION LOOKING AFT.  FOUND DU	RING INSPECTION IAW AD/B747/159 AND EI 747-053-0215.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006060800396	20060608	00396	NM  	2006	6	8	AU510001830      	1	20051212	G	5311	141U10423	FRAME           	BOEING      		BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FOUND FUSELAGE INNER CHORD RING CRACKED.  CRACK LOCATED AT FASTENER HOLE LBL 33.5 AND WL 153 BS 140 FPB (REAR FACE).  FO	UND DURING INSPECTION IAW AD/B747/159 AND EI 747-053-0215.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006060800399	20060608	00399	NM  	2006	6	8	AU510001832      	1	20050609	G	3246	277A6000204	WHEEL           			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM56*      	13802	NE  					MLG	WRONG PART      	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										INCORRECT PART NUMBER MAIN WHEEL FITTED TO LT MAIN LANDING GEAR NR 2 POSITION.  WHEEL FITTED WAS PNO 277A6000-204 WHICH 	IS FOR FITMENT TO 737-800 SERIES AIRCRAFT.  THE CORRECT P/N 277A6000-206 IS FITTED TO 737-700 SERIES.  THE INCORRECT WHE	EL IS A HIGH GROSS WEIGHT (HGW) MAIN WHEEL WITH A TIRE DIAMETER 25.4MM (1IN) GREATER THAN THE CORRECT LOW GROSS WEIGHT (	LGW) MAINWHEEL.  INCORRECT PART PERSONNEL/MAINTENANCE ERROR.			2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800400	20060608	00400	NE  	2006	6	8	AU510001833      	2	20050909	G	7230		FAN BLADE       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ENGINE LP FAN BLADE CONTAINED NICKS IN THE LEADING EDGE.  THE DAMAGE WAS BLENDED OUT AND AN EDDY CURRENT INSPECTION IS D	UE WITHIN 50 HOURS.  INVESTIGATION CONTINUING.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800401	20060608	00401	NE  	2006	6	8	AU510001834      	2	20050809	G	7310		PUMP            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					EJECTOR	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE ENVIRONMENTAL DRAIN TANK EJECTOR PUMP BLOCKED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800402	20060608	00402	NM  	2006	6	8	AU510001835      	1	20050809	G	5410	HA2261	LATCH           			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NACELLE DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ENGINE CORE COWL NR 6 LATCH BROKEN.  FURTHER INVESTIGATION FOUND NR 1, NR 3, NR 4 AND NR 5 LATCHES CRACKED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300102	20060613	00102	EU  	2006	6	13	AU510001836      	1	20051009	G	2910		O-RING          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYDRAULIC SYS	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										LOSS OF HYDRAULIC FLUID.  INVESTIGATION FOUND A FAILED O-RING SEAL AT THE PIPE CONNECTOR ON NR 2 HIGH PRESSURE MANIFOLD.	  THIS PIPE SUPPLIES GREEN SYSTEM HIGH PRESSURE FLUID THROUGH THE STANDBY GENERATOR ISOLATION VALVE.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
2006061300103	20060613	00103	SO  	2006	6	13	AU510001837      	1	20051109	G	3250	110P241020	STEERING SYS    			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										NOSE WHEEL STEERING SYSTEM FAULTY.  STEERING SYSTEM TRAVEL WAS RESTRICTED.  LT MAIN LANDING GEAR AND NOSE GEAR RAN OFF R	UNWAY AND BECAME BOGGED IN THE SOFT SURFACE AT THE SIDE OF THE RUNWAY.					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006061300104	20060613	00104	NM  	2006	6	13	AU510001838      	1	20050909	G	2910	1550121221	HOSE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) RT ENGINE DRIVEN HYDRAULIC PUMP TO PYLON QUICK DISCONNECT PRESSURE HOSE LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300105	20060613	00105		2006	6	13	AU510001839      	4	20050909	G	3442	6225136203	DRIVE ASSY      			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					WX RADAR SYS	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		33097	5139 							WEATHER RADAR ANTENNA DRIVE PEDESTAL FAULTY.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061300107	20060613	00107	NM  	2006	6	13	AU510001840      	1	20050608	G	2131	71211997101AC	CONTROLLER      			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					CABIN PRESSURE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10902	10902							NR 2 CABIN PRESSURE CONTROLLER FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300108	20060613	00108	NM  	2006	6	13	AU510001841      	1	20050809	G	2121	732591D	FAN             			BOEING	767   	767300      	1385204	NM  	GE    	CF6   	CF680C2*    	 	GL  					EXHAUST	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 		58337	19354							ELECTRICAL BURNING SMELL ON FLIGHT DECK.  INVESTIGATION FOUND THE FORWARD EQUIPMENT EXHAUST FAN FAILED.  FAN BEARINGS CO	LLAPSED AND ROTOR WORN OUT.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061300109	20060613	00109	NM  	2006	6	13	AU510001842      	1	20050209	G	3610		REGULATOR       			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					PNEUMATIC SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT BLEED AIR FAILURE.  BLEED AIR REGULATOR AND PRECOOLER CONTROL VALVE REPLACED.  INVESTIGATION FOUND PRECOOLER CONTROL 	VALVE FAULTY.  POPPET SET AND ADAPTER PLATE WORN.  SIGNIFICANT CONTAMINATION INSIDE VALVE.  BLEED AIR REGULATOR ALSO FAI	LED SHOP TEST.  RELIEF VALVE AND POPPET WORN. PRECOOLER CONTROL VALVE AND BLEED AIR REGULATOR DEFECTS CONSIDERED TO ADVE	RSELY AFFECT PRECOOLER OPERATION WITH THE BLEED OVER TEMPERATURE SWITCH ACTIVATING THE BLEED TRIP LIGHTS.  THESE DEFECTS	 CONSIDERED TO BE DUE TO ENGINE VIBRATION.		2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300110	20060613	00110		2006	6	13	AU510001843      	4	20051212	G	2340		INTERPHONE      			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					CABIN	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CABIN INTERPHONE SYSTEM FAULTY.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006061300111	20060613	00111	NM  	2006	6	13	AU510001844      	1	20050509	G	3150	285N04329	CIRCUIT CARD    			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C      	 	GL  					CENTRAL WARNING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										EICAS SIGNAL CONSOLIDATION CARD (SCC) FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061300227	20060613	00227		2006	6	13	AU510001845      	4	20050209	G	3197	W105201322	WIRE            			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					WARNING SWITCH	WORN            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										SMOKE IN COCKPIT EMANATING FROM NEAR TO CAPTAIN`S GLARE SHIELD.  INVESTIGATION FOUND A CHAFED WIRE AT PIN 13 OF THE CAPT	AIN`S CAUTION/WARNING SWITCH ASSEMBLY ON THE GLARE SHIELD.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006061300228	20060613	00228	NE  	2006	6	13	AU510001846      	2	20051209	G	7321	2042M67P02	EEC             			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NR 1 ENGINE	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		384  								NR 1 ENGINE ELECTRONIC CONTROL (EEC) FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300230	20060613	00230	EU  	2006	6	13	AU510001847      	1	20050209	G	7603	C822249	CONTROL CABLE   			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	POWER LEVER	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										RT ENGINE POWER LEVER CABLE BROKEN AT END FITTING WHERE IT ATTACHES TO THE HYDROMECHANICAL UNIT (HMU).						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL	 
2006061300231	20060613	00231	NM  	2006	6	13	AU510001848      	1	20051209	G	3244		TIRE            	HONEYWELL   		BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					MLG	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B4852					NR 4 MAIN WHEEL TIRE TREAD DELAMINATED AT INBOARD SIDEWALL.  TIRE HAS A RETREAD DATE R1 505.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300232	20060613	00232	NM  	2006	6	13	AU510001849      	1	20050909	G	5210	232U212220B	SOLENOID        			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					PAX DOOR LATCH	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										STRONG ODOR ON FLIGHT DECK.  INVESTIGATION FOUND THE FLIGHT DECK DOOR CIRCUIT BREAKER P6-3 D21 TRIPPED.  FLIGHT DECK DOO	R EMERGENCY PANEL INOPERATIVE AND DOOR LATCH WAS WARM.  INVESTIGATION FOUND THE COCKPIT DOOR LOCK SOLENOID HAD FAILED.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061300233	20060613	00233		2006	6	13	AU510001850      	4	20051109	G	2211	4051601937	CONTROL PANEL   			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AUTOPILOT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 		36869	7253 							AUTOPILOT MODE CONTROL PANEL (MCP) FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006071800172	20060718	00172	EU  	2006	7	18	AU510001853      	1	20051109	G	2701	936401312	CONTROL COLUMN  			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COCKPIT	STICKING        	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 		10005								(AUS) CONTROL YOKE STICKING DURING ROLL INPUT. INVESTIGATION FOUND THE CONTROL YOKE CONTACTING THE LT DEFOG VENT.  FURTH	ER INVESTIGATION FOUND THE BOLT HOLES CONTAINED WITHIN THE CONTROL COLUMN YOKE WERE ELONGATED. (CASA NR 510001853)					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006061400176	20060614	00176	SO  	2006	6	14	AU510001854      	1	20050509	G	5751	4020043	ATTACH BRACKET  			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			AU	S 										RT AILERON CRACKED IN AREA OF CONTROL ROD/SPAR ATTACHMENT BRACKET.  FOUND DURING COLOR CONTRAST DYE PENETRANT INSPECTION	 IAW AD/PA31/118.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061400178	20060614	00178	SO  	2006	6	14	AU510001855      	1	20050609	G	5551	40024T008	ROD END         			AYRES 	S2    	S2RT15RESTD 	       	SO  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT HORIZONTAL STABILIZER ATTACHMENT BOLT BROKEN AT TOP OF THREADED AREA UNDER CLEVIS.  FOUND WHEN STABILIZER REMOVED FOR	 PAINTING.  INSPECTION FOUND ALL OTHER ATTACHMENT BOLTS RUSTED AND PITTED IN THE SAME AREA.					1	L	7	1 	3T	4	T		A4SW    	E4EA	6	C	P15EA	 
2006061500098	20060615	00098	CE  	2006	6	15	AU510001856      	1	20050306	G	8010	99100791	SWITCH          			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					219					LT ENGINE STARTER SWITCH FAILED.  SWITCH REMAINED ENGAGED.						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006061500110	20060615	00110	CE  	2006	6	15	AU510001857      	1	20050104	G	8011	643109	SPRING          	CONT        		CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	STARTER ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ENGINE STARTER ADAPTER CLUTCH SPRING TANG BROKEN OFF.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
2006061500111	20060615	00111	CE  	2006	6	15	AU510001858      	1	20051212	G	8011	643109	CLUTCH SPRING   	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					STARTER ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		6193 			0					ENGINE STARTER ADAPTER CLUTCH SPRING TANG BROKEN OFF.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006061500112	20060615	00112	CE  	2006	6	15	AU510001859      	1	20051212	G	2434	ALE2045BS	BRUSH BLOCK     			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ALTERNATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		200  	200  		E112870E0604					ALTERNATOR HAD HIGH RESISTANCE IN BOTH BRUSH BLOCK CONNECTIONS.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2006061500133	20060615	00133	CE  	2006	6	15	AU510001860      	1	20051212	G	2497		WIRE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					BUSS BAR	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		3741 								BUSS BAR CABLE SHORT CIRCUITED TO RT CIRCUIT BREAKER PANEL.  FURTHER INVESTIGATION FOUND A LOOSE CONNECTING SCREW ON THE	 ICE DETECTION CIRCUIT BREAKER WHICH HAD BURNT OUT.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006061500134	20060615	00134	EU  	2006	6	15	AU510001861      	1	20051209	G	2760	FON21185V46	BOLT            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					SPOILER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT LIFT DUMPER SYSTEM NR 1 BELLCRANK INBOARD UPPER ATTACHMENT BOLT SHEARED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500135	20060615	00135	EU  	2006	6	15	AU510001862      	1	20051209	G	2760	MS212306	BEARING         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					SPOILER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT LIFT DUMPER NR 3 BELLCRANK HORIZONTAL ROD ATTACHMENT BEARING MIGRATED OF POSITION.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500136	20060615	00136	SO  	2006	6	15	AU510001863      	2	20050809	G	8520	PN649134ASSY	CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1691 								ENGINE CRANKSHAFT COUNTERWEIGHT HANGER BLADE HOLES OUT OF ROUND.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2006061500138	20060615	00138	EU  	2006	6	15	AU510001864      	1	20051209	G	2760	A16084003	ROD             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					SPOILER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RH LIFT DUMPER SYSTEM VERTICAL ROD CRACKED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500140	20060615	00140	SO  	2006	6	15	AU510001865      	2	20050709	G	8530	AEC631397	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		186  					284957R			ENGINE CYLINDER DAMAGED.  A PIECE OF THE NICKEL CARBIDE BORE COATING MISSING FROM THE TOP AREA OF THE CYLINDER BORE.  SI	ZE OF MISSING PIECE APPROXIMATELY 20MM BY 5MM BY 0.254MM DEEP (0.78IN BY 0.19IN BY 0.010IN DEEP).  THE SECOND COMPRESSIO	N RING WAS ALSO FOUND BROKEN IN TWO PLACES APPROXIMATELY 40MM (1.57IN) APART.  THE FLOATING PIECE WAS JAMMED IN THE PIST	ON RING GROOVE AND WAS STARTING TO BREAK UP.			1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P47GL	 
2006061500207	20060615	00207	EU  	2006	6	15	AU510001866      	1	20051212	G	2760		BOLT            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					SPOILER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 LT LIFT DUMPER SYSTEM BELLCRANK SPIGOT ATTACHMENT BOLTS LOOSE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500235	20060615	00235	EU  	2006	6	15	AU510001867      	1	20051209	G	5753	MS1410414	BEARING         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					LT WING FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT WING TRAILING EDGE FLAP TRACK FORWARD SUPPORT BEARING WORN.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500236	20060615	00236	EU  	2006	6	15	AU510001868      	1	20051209	G	5753	MS1410414	BEARING         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					RT WING TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT WING FLAP TRACK BEAM ASSEMBLY FORWARD SUPPORT BEARING WORN.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500245	20060615	00245		2006	6	15	AU510001869      	4	20051212	G	3416	70007641	POTENTIOMETER   			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ALTIMETER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ALTIMETER POTENTIOMETER NON-LINEAR IN OPERATION.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061600001	20060616	00001	NM  	2006	6	16	AU510001870      	1	20051212	G	5414	311T245013	SKIN            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					RT ENGINE STRUT INBOARD SKIN CRACKED FROM UPPER AFT RADIUS OF 442AL ACCESS PANEL CUTOUT THROUGH RIVET HOLE.  CRACK IS LO	CATED IN INTERNAL DOUBLER AS WELL.  CRACK WAS CONFIRMED USING NDT.  CRACK LENGTH APPROXIMATELY 63.5MM (2.5IN).					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061600002	20060616	00002	NM  	2006	6	16	AU510001871      	1	20050209	G	5414	311T245025	SKIN            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE STRUT INBOARD SKIN CRACKED FROM UPPER AFT RADIUS OF 442AL ACCESS PANEL CUTOUT AND THROUGH RIVET HOLE.  CRACK C	ONFIRMED USING NDT.  CRACK LENGTH APPROXIMATELY 58.4MM (2.3IN).  CRACK ALSO EXISTS IN INTERNAL DOUBLER AS WELL.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006071100110	20060711	00110	EU  	2006	7	11	AU510001872      	1	20051212	G	7722	9550124240	PROBE           			AEROSP	AS355 	AS355N      	8680818	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					ENGINE TEMP	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 		1676 	1676 							(AUS) NR 1 ENGINE T4 TEMPERATURE PROBE SEPARATED FROM ENGINE. LOCKING NUT STILL FIRMLY ATTACHED TO MOUNTING POINT. (CASA	 NR 510001872)					1	G	7	2 	3U	3	U	RT	H11GU   	E19EU				 
2006061600003	20060616	00003	SW  	2006	6	16	AU510001873      	1	20051212	G	3010		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ANTI-ICE SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										BLEED AIR DE-ICE LINE BROKEN AT OUTBOARD EDGE OF RIGHT AILERON.  LINE HAD FALLEN TO THE UNDERSIDE OF THE AILERON AND JAM	MED BETWEEN THE WING LOWER CLOSEOUT PANEL AND THE AILERON LOWER LEADING EDGE WITH THE `B` NUT FITTING ON THE LINE INHIBI	TING AILERON TRAVEL.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006061600005	20060616	00005	NM  	2006	6	16	AU510001874      	1	20051207	G	5415		SUPPORT FITTING 			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		53856								LT AND RT ENGINE FORWARD SUPPORT FITTING ASSEMBLIES CRACKED.  LT PYLON FITTING CRACKED AT HOLE `F`.  RT PYLON FITTING CR	ACKED AT HOLE `P`.  FOUND DURING INSPECTION IAW AD/B727/151 AND BOEING SB 727-54A0010.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006061600009	20060616	00009		2006	6	16	AU510001875      	4	20051212	G	3417	4040831901	SENSOR          	HONEYWELL   	AZ810       															DADC	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					93035792					DIGITAL AIR DATA COMPUTER (DADC) PRESSURE CONVERTER (PS AND PT SENSOR) OUT OF TOLERANCE.																			 
2006061900006	20060619	00006	SO  	2006	6	19	AU510001876      	2	20051212	G	8530		PISTON          			BEECH 	33    	3533        	1151402	CE  	CONT  	O470  	IO470J      	17026	SO  	HARTZL	HC92Z	BHC92Z*     	GL  	ENGINE	BROKEN          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		636  	636  				852710J			NR 6 CYLINDER PISTON BROKEN AT GUDGEON.  CONNECTING ROD BIG END CAP BROKEN OFF.						1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P892	 
2006061900007	20060619	00007	NE  	2006	6	19	AU510001877      	2	20051212	G	7261		ENGINE          			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 1	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LE48195AEF			NR 1 ENGINE CHIP DETECTOR LIGHT ILLUMINATED.  INSPECTION FOUND A FINE HAIRLIKE METAL SLIVER.  ENGINE INSPECTED IAW MAINT	ENANCE MANUAL AND DECLARED SERVICEABLE.					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2006061900009	20060619	00009	NM  	2006	6	19	AU510001878      	1	20051212	G	2761	NAS16126A	O-RING          			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ROLL SPOILER	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 		99999	99999							RT INBOARD ROLL SPOILER ACTUATOR BULKHEAD UNION FITTING SLIGHTLY LOOSE IN ACTUATOR BODY CAUSING FAILURE OF THE UNION O-R	ING SEAL AND LOSS OF HYDRAULIC FLUID.  SPOILER ACTUATOR HAD BEEN REPLACED AT LAST MAINTENANCE CHECK AND IT IS SUSPECTED 	THAT EITHER THE RIGID LINE CONNECTION OR THE BULKHEAD FITTING HAD NOT BEEN CORRECTLY RETORQUED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061900011	20060619	00011	SO  	2006	6	19	AU510001879      	1	20051212	G	3233	762554	ROD END         	OZONE       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	ACTUATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					398					LT MAIN LANDING GEAR RETRACTION ACTUATOR ROD END BROKEN.  FURTHER INVESTIGATION OF THE NOSE LANDING GEAR AND RT MAIN LAN	DING GEAR ACTUATOR ROD ENDS FOUND SLIGHT BENDING IN THE THREADED AREA OF THE NLG ROD END.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P31EA	 
2006061900012	20060619	00012	EU  	2006	6	19	AU510001880      	1	20050509	G	5311		FRAME           			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					FUSELAGE FRAMES 15 AND 18 CRACKED, FOUND DURING INSPECTION IAW AD/BAE146/116.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006061900014	20060619	00014	SW  	2006	6	19	AU510001881      	1	20051212	G	2701	917010507	CONTROL WHEEL   			MOONEY	M20   	M20G        	5870316	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CONTROL WHEEL CRACKED FROM TOP BOLT HOLE.						1	L	7	1 	3O	3	O		2A3     	E286	5	C	P920	 
2006061900016	20060619	00016	GL  	2006	6	19	AU510001882      	3	20051212	G	6114	D220117	HUB             	HARTZL      		PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			183  		CH19462E			CH19462E		PROPELLER HUB DAMAGED.  SUSPECT CAUSED BY GROUND STRIKE.  FOUND DURING INSPECTION IAW AD/PHZL/77 AMDT2.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
2006061900017	20060619	00017	NM  	2006	6	19	AU510001883      	1	20051212	G	3242	26123011	BRAKE           			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NR 2	BINDING         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										MAIN LANDING GEAR NR 2 BRAKE BINDING.  INVESTIGATION FOUND FOD TO ROTOR AND STATOR ASSEMBLIES.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061900018	20060619	00018	CE  	2006	6	19	AU510001884      	1	20051212	G	5730	NAS22112	SCREW           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	WING SKIN	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										OUTER WING FORWARD UPPER BATHTUB FITTING TO UPPER SKIN PANEL ATTACHMENT SCREWS LOOSE.  SUSPECT SCREWS INCORRECTLY TORQUE	D DURING MANUFACTURE.					2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2006061900104	20060619	00104	CE  	2006	6	19	AU510001885      	1	20051212	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		17021			0					RT CANTED RIB CAP CRACKED BENEATH REPAIR.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061900105	20060619	00105	CE  	2006	6	19	AU510001886      	1	20051212	G	5712	57200014S	RIB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		17021								RT CANTED RIB CAP FORWARD PN 5720001-4S AND AFT PN 5720001-6S ANGLES CRACKED, FOUND DURING EDDY CURRENT INSPECTION.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061900106	20060619	00106	EU  	2006	6	19	AU510001887      	1	20051212	G	3020		SWITCH          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ENGINE ANTI ICE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 ENGINE ANTI-ICE SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061900107	20060619	00107	SO  	2006	6	19	AU510001888      	1	20051212	G	2434	411810	ALTERNATOR      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										ALTERNATOR FAILED.  FOLLOWING REMOVAL IT WAS NOTICED THAT THE ALTERNATOR DID NOT HAVE A DATA PLATE ATTACHED IDENTIFYING 	EITHER SERIAL NUMBER OR PART NUMBER.					1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
2006061900108	20060619	00108	SO  	2006	6	19	AU510001889      	1	20051007	G	3233	762554	ROD END         	OZONE       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										RT MAIN LANDING GEAR ACTUATOR ROD END FAILED.  FOLLOWING REPLACEMENT OF THE RODEND, THE RT MAIN LANDING GEAR COULD NOT B	E RIGGED DUE TO EXCESSIVE WEAR IN THE DRAG LINK BUSHES AND BOLTS AND THE DOWNLOCK HOOK AND PIN.  GEAR WAS RERIGGED FOLLO	WING REPLACEMENT OF THE WORN PARTS.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061900109	20060619	00109	CE  	2006	6	19	AU510001890      	1	20051212	G	5740	NAS22112	SCREW           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					WING FITTING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										OUTER WING FORWARD UPPER BATHTUB FITTING TO UPPER SKIN PANEL ATTACHMENT SCREWS LOOSE.  SUSPECT SCREWS INCORRECTLY TORQUE	D DURING MANUFACTURE.					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061900110	20060619	00110	NM  	2006	6	19	AU510001891      	1	20051212	G	5210	232U212220B	LOCK            			BOEING	747   	747438      	       	NM  										PAX DOOR	FAULTY          	W				O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			AU	S 										ELECTRICAL BURNING ODOR ON FLIGHT DECK AND IN UPPER DECK CABIN.  INVESTIGATION FOUND FLIGHT DECK DOOR LOCK HOT.  FURTHER	 INVESTIGATION FOUND THE FLIGHT DECK DOOR ELECTRIC STRIKER ASSEMBLY HAD FAILED.					2	L	7	4 	4F			RT	A20WE   					 
2006061900111	20060619	00111	CE  	2006	6	19	AU510001892      	1	20051212	G	3260	444EN496	SQUAT SWITCH    			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										RT MAIN LANDING GEAR SQUAT SWITCH ADJUSTED TO MINIMUM TOLERANCE PREVENTING RETRACTION OF THE LANDING GEAR.  SWITCH ADJUS	TED AND LANDING GEAR RETRACTION WAS NORMAL.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006061900112	20060619	00112	NM  	2006	6	19	AU510001893      	1	20051212	G	2912	271T00424	FILTER          			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										CENTER NR 1 HYDRAULIC SYSTEM PRESSURE FILTER BOWL FAILED.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006061900292	20060619	00292	NM  	2006	6	19	AU510001894      	1	20051009	G	2120		ODOR            			BOEING	737   	737         	UTILSYS	NM  										COCKPIT	DETECTED        	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										BURNING SMELL ON FLIGHT DECK.  SMELL TRACED TO FAULTY P5-9 PANEL.  AIRCRAFT IS FOREIGN REGISTERED.						2	L	7	2 	4F			RT	A16WE   					 
2006061900293	20060619	00293	NM  	2006	6	19	AU510001895      	1	20051212	G	2121		COOLING FAN     			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  						FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										SMOKE AND FUMES IN COCKPIT.  INVESTIGATION FOUND THE CHILLER BOOST FAN CIRCUIT BREAKER TRIPPED.  INVESTIGATION FOUND THE	 FAN FORWARD BEARING HAD COLLAPSED ALLOWING THE IMPELLER BLADES TO RUB ON THE CASE AND THE FAN MOTOR ROTOR AND STATOR TO	 RUB.				2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2006061900294	20060619	00294	EU  	2006	6	19	AU510001896      	1	20051212	G	5520	NB31B133	SPACER          	BNORM       	EQUIPMENT   	BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					10136					LT OB ELEVATOR SPACER (DISTANCE PIECE) WORN BEYOND LIMITS.  AS A RESULT THE ELEVATOR SUPPORT STRUCTURE WAS CRACKED TO TH	E POINT OF NEAR SEPARATION.					1	H	7	2 	3O	3	O	RT	A17EU   	E295	5	C	P920	 
2006062300022	20060623	00022	EU  	2006	6	23	AU510001897      	1	20051212	G	2121	3133759	COOLING FAN     			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AVIONICS	ODOR            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) ODOR IN COCKPIT. INVESTIGATION FOUND ODOR ONLY BECAME PRESENT WHEN THE AIR CONDITIONING SYSTEM WAS SELECTED OFF. F	URTHER INVESTIGATION FOUND THE ODOR CAME FROM RECENTLY INSTALLED AVIONICS INSTRUMENT COOLING FANS. FANS WERE CHECKED SER	VICEABLE. FANS HAD BEEN FITTED IAW EO F406-21-416 ISSUE1. (OTHER CAUSE: ENVIRONMENT ) (CASA NR 510001897)				1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006061900148	20060619	00148	SO  	2006	6	19	AU510001898      	1	20051212	G	2140	A23D0475	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										CABIN HEATER FUEL PRESSURE REGULATOR LEAKING FUEL FROM DIAPHRAGM.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061900295	20060619	00295	EU  	2006	6	19	AU510001899      	1	20051212	G	3310		LIGHT           			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					COCKPIT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										FO READING LIGHT FAILED.  SMOKE AND FUMES IN COCKPIT.  INVESTIGATION FOUND SWARF MATERIAL IN THE LENS ASSEMBLY FOLLOWING	 REMOVAL OF THE COVER.					2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006061900296	20060619	00296	CE  	2006	6	19	AU510001900      	1	20051212	G	3710		COUPLING        		216CW       	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550B      	 	SO  	MCAULY	3AF34C	3AF34C502   	GL  	VACUUM PUMP	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			29   		35967					RT VACUUM PUMP FAILED.   INVESTIGATION FOUND THE PUMP JAMMED AND FULL OF CARBON VANE DEBRIS.  DRIVE SHAFT FAILED AT SHEA	R POINT.  PUMP IS OUTSIDE OF THE SN RANGE AS INDICATED IN TEMPEST SB-003.					1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
2006062100161	20060621	00161	CE  	2006	6	21	AU510001901      	1	20051212	G	3710		DRIVE SHAFT     	AERO        		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	VACUUM PUMP	SHEARED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					38343					(AUS) VACUUM PUMP FAILED. INVESTIGATION FOUND THE PUMP JAMMED AND FULL OF CARBON VANE DEBRIS. DRIVE SHAFT FAILED AT SPLI	NED SECTION AND NOT AT SHEAR POINT AS DESIGNED. PUMP IS OUTSIDE OF THE SN RANGE AS INDICATED IN TEMPEST SB-003.  (AD/SB 	DESC: TEMPEST SB-003 ) (OTHER CAUSE: MATERIAL ) (CASA NR 510001901)				1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
2006062100164	20060621	00164	SO  	2006	6	21	AU510001902      	1	20051212	G	3710		COUPLING        		215CC       	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					VACUUM PUMP	SHEARED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		41   	41   		38552					(AUS) VACUUM PUMP FAILED. INVESTIGATION FOUND THE PUMP JAMMED AND FULL OF CARBON VANE DEBRIS.  DRIVE SHAFT FAILED AT SHE	AR POINT. PUMP IS OUTSIDE OF THE SN RANGE AS INDICATED IN TEMPEST SB-003. (OTHER CAUSE: MATERIAL ) (CASA NR 510001902)					1	L	7	1 	3O	3	O		2A13    	E274				 
2006062100165	20060621	00165	EU  	2006	6	21	AU510001903      	1	20051212	G	4940		DRIVE SHAFT     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STARTER	SHEARED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) APU STARTER MOTOR DRIVESHAFT SHEARED.  INVESTIGATION FOUND THAT THE BROKEN END WAS JAMMED IN THE CLUTCH ASSEMBLY. 	(CASA NR 510001903)					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062100167	20060621	00167	NM  	2006	6	21	AU510001904      	1	20051212	G	7603		CLUTCH          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					POWER LEVER	FAULTY          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE AUTO THROTTLE CLUTCH PACK FAULTY.  INVESTIGATION FOUND THE TORQUE LIMITER FAILED TO JUMP TO THE NEXT P	OSITION AT THE FORCE OF 49 POUNDS TO 60 POUNDS FOR BOTH CLUTCHES.  (CASA NR 510001904)					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062100170	20060621	00170	SO  	2006	6	21	AU510001905      	1	20051212	G	3232	AE1011469EO122	HOSE            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	MLG DOOR ACT	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR IB DOOR ACTUATOR CLOSE HYDRAULIC HOSE FAILED. LOSS OF HYDRAULIC FLUID.  INVESTIGATION ALSO FO	UND THAT THE HOSE PN WAS INCORRECT IAW THE IPC.  SUSPECT INCORRECT PN HOSE WAS FITTED BY A PREVIOUS OPERATOR. (CASA NR 5	10001905)				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006062100171	20060621	00171	WP  	2006	6	21	AU510001906      	1	20051009	G	6210	A0164	BLADE           			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		399  	399  							(AUS) MAIN ROTOR BLADE BENT.  BEND LOCATED IN AREA APPROXIMATELY 200MM (7.8IN) OB OF THE BLADE DOUBLER AND RUNNING ALONG	 THE CHORDWISE AXIS. A STRINGLINE WAS RUN DOWN THE LEADING EDGE OF THE BLADE AND THE DEVIATION FROM THIS AT THE BEND WAS	 19MM TO 20MM (0.74IN TO 0.78 IN) DOWNWARD. FOUND DURING BLADE REMOVAL AND REPLACEMENT. (CASA NR 510001906)				1	G	7	1 	3O	3	O		H10WE   	E274				 
2006062100173	20060621	00173	NM  	2006	6	21	AU510001907      	1	20051212	G	5750	2061141	INDICATOR       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 		27444	27444							(AUS) TRAILING EDGE FLAP ASSYMETRY.  FLAPS RECYCLED AND OPERATED NORMALLY.  INVESTIGATION CONTINUING. (CASA NR 510001907	)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006062300028	20060623	00028	EA  	2006	6	23	AU510001908      	2	20051212	G	8520	72877R	CAM FOLLOWER    								LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			53   							(AUS) ECI PNO 72877R CAM FOLLOWERS FAULTY. LIFTERS ARE BADLY WORN AND CAMSHAFT LOBES DAMAGED. ENGINES FITTED WITH THIS P	N LIFTERS INCLUDE MFG TIO540J2BD AND O320D2J MODELS. (MATERIAL - ORGANIZATIONAL ) (CASA NR 510001908)										3	O			E14EA				 
2006062300030	20060623	00030	NE  	2006	6	23	AU510001909      	2	20050309	G	7250	70BM037330	MODULE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							15129			(AUS) NR 1 ENGINE, NR 2 AND NR 3 MODULES SEIZED.  INVESTIGATION CONTINUING.   (CASA NR 510001909).						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2006062300138	20060623	00138	NM  	2006	6	23	AU510001910      	1	20051212	G	3610		PRESSURE VALVE  			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					BLEED AIR SYS	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE BLEED AIR SYSTEM PRESSURE REGULATING VALVE (PRV) FAILED. INVESTIGATION FOUND EXCESSIVE BUTTERFLY SHAFT P	LAY DUE TO WORN CARBON SHAFT BUSHINGS.  (CASA NR 510001910)					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062300140	20060623	00140	SO  	2006	6	23	AU510001911      	2	20051212	G	8520	537432	GEAR            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	CRANKSHAFT	DAMAGED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 		1516 								(AUS) ENGINE CRANKSHAFT GEAR MISSING TEETH.  SUSPECT CAUSED BY A PIECE OF METAL FROM THE STARTER ADAPTER GEAR JAMMING IN	 THE GEAR TEETH. METAL CONTAMINATION OF ENGINE. (CASA NR 510001911)					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
2006062300141	20060623	00141	GL  	2006	6	23	AU510001912      	1	20051212	G	3244	252752	TIRE            			AMTR  	LANCAR	LC41550FG   	5150001	GL  	LYC   	O540  	IO540N1A5   	41532	EA  	HARTZL	HCF3Y	HCF3YR1     	GL  	NLG	DISINTEGRATED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					UNKNOWN					(AUS) NOSE WHEEL TYRE DISINTEGRATED CIRCUMFERENTIALLY.  INVESTIGATION FOUND EXCESSIVELY LONG NOSEWHEEL SPAT ATTACHMENT S	CREWS WHICH CUT INTO THE TYRE AS IT ROTATED. INCORRECT PART. (CASA NR 510001912)					1	L	7	1 	3O	3	O	RT	EXPA1L71	1E4	5	C	P31EA	 
2006062300142	20060623	00142	NM  	2006	6	23	AU510001913      	1	20051212	G	2751	1817389	TRANSMITTER     			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 		39668	39668							(AUS) LT FLAP POSITION TRANSMITTER FAULTY.  (CASA NR 510001913)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006062300144	20060623	00144	EU  	2006	6	23	AU510001914      	1	20051212	G	5751	NOTKNOWN	BOLT            	FOKKER      		FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AILERON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AILERON TAB OB HINGE BRACKET ATTACHMENT BOLTS LOOSE.  BOLTS WERE THREADBOUND IN ANCHOR NUTS.  INVESTIGATION FOU	ND INCORRECT BOLTS WERE FITTED BY A PREVIOUS OPERATOR IN THE US. (CASA NR 510001914)					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062300146	20060623	00146	EU  	2006	6	23	AU510001915      	1	20051212	G	2750		CONTROL CABLE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					TE FLAPS	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL CABLES FOR FLAPS ( F1 AND F2) WERE FOUND TO BE 43LB LOW IN TENSION. THE LT AILERON WING CABLE WAS 30LB LOW	. THE LT AND RT AILERON UPFLOAT CABLES WERE 45LB LOW.  (CASA NR 510001915)					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006062300148	20060623	00148	NM  	2006	6	23	AU510001916      	1	20051212	G	2611	30326E11	AMPLIFIER       			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	SMOKE DETECTOR	UNSERVICEABLE   	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) BAGGAGE COMPARTMENT SMOKE DETECTOR CONTROL AMPLIFIER FAILED.(OTHER CAUSE: SHIFT IN DESIGN PROPERTIES. ) (CASA NR 5	10001916)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300150	20060623	00150		2006	6	23	AU510001917      	4	20051212	G	2565		SLIDE           			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					L1 DOOR	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DURING EMER EVAC FOR FIRE WARNING, DOOR 1L SLIDE FAILED TO DEPLOY. DOOR OPENING HANDLE HAD BEEN MOVED TO FULL UP P	OSITION, DOOR WAS FOUND TO HAVE OPENED APPROX 3 INCHES, JAMMED IN THAT POSITION.  DOOR ARMING HANDLE HAD BEEN MOVED FROM	 ARMED POSITION TO DISARMED POSITION. SLIDE GIRT BAR WAS STILL ATTACHED TO DOOR FRAME FLOOR FITTINGS, SLIDE WAS STILL WI	THIN DOOR COVER. FILLING VALVE NUT ON DOOR ASSIST ACT WAS LOOSENED TO RELEASE REMAINING PRESS IN ACT. AFTER SLIGHT RELEA	SE OF PRESS, DOOR OPENED AUTOMATICALLY, SLIDE DEPLOYED NORMALLY.  DETERMINED DOOR HAD BECOME JAMMED BECAUSE PRESS FROM D	OOR ASSIST ACT FORCED DOOR AGAINST DOOR FRAME, PREVENTED DOOR FROM BEING MOVED TO CLOSED POSITION. (CASA NR 510001917)	2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006061900297	20060619	00297	CE  	2006	6	19	AU510001918      	1	20050809	G	5514	4320049	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 		2813 								HORIZONTAL STABILIZER UPPER PLATE CRACKED IN AREA ADJACENT TO VERTICAL STABILIZER BRACKET ATTACHMENT.  CRACK LENGTH 5MM 	(0.196IN).					1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL	 
2006070500054	20060705	00054	CE  	2006	7	5	AU510001919      	1	20050909	G	5511	4320049	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 UPPER PLATE CRACKED IN AREA ADJACENT TO VERTICAL STABILIZER BRACKET ATTACHMENT. CRACK LENGTH	 7MM (0.275IN). (AD/SB DESC: SEB 03-6 ) (CASA NR 510001919)					1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL	 
2006070500055	20060705	00055	NM  	2006	7	5	AU510001920      	1	20051212	G	2782	272A165154	LINE            			BOEING	737   	73776N      	13844CH	NM  	GE    	CFM56 	CFM567B24   	 	NE  					SLAT HYD SYS	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING NR 2 LEADING EDGE SLAT ACTUATOR HYDRAULIC PIPE CHAFED AND LEAKING DUE TO INSUFFICIENT CLEARANCE BETWEEN TH	E PIPE AND THE ACTUATOR. LOSS OF HYDRAULIC FLUID. (CASA NR 510001920)					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500056	20060705	00056	NM  	2006	7	5	AU510001921      	1	20051212	G	2130		CABIN PRESSURE  			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  						FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT PRESSURISED ON LANDING. NUMEROUS COMPONENTS CHANGED. INVESTIGATION CONTINUING. (CASA NR 510001921)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500057	20060705	00057	GL  	2006	7	5	AU510001922      	1	20051212	G	5740	66130131	ANGLE           			NAMER 	T6    	SNJ4        	6400414	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	3D	3D40        	NE  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING LT UPPER ANGLE CORRODED IN 2 BOLT HOLES.  FOUND DURING INSPECTION IAW WS-622-REV1.0.(OTHER CAUSE: AGE ) (CASA	 NR 510001922)					1	L	7	1 	3R	3	R		A2575   	5E2	6	C	A815	 
2006070500058	20060705	00058	EU  	2006	7	5	AU510001923      	1	20051212	G	2121	6451101	COOLING FAN     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AVIONICS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		20824								(AUS) AVIONICS COOLING FAN NOISY IN OPERATION.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006070500059	20060705	00059	NM  	2006	7	5	AU510001924      	1	20051212	G	5350	85350966	FAIRING         			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT WING ROOT	BIRD STRIKE     	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 		2338 								(AUS) RT WING ROOT FAIRING SUFFERED A FRUIT BAT STRIKE DURING LANDING. THE BAT CAUSED A HOLE IN THE KEVLAR FAIRING BUT D	ID NOT PENETRATE. THE HOLE SIZE WAS APPROXIMATELY 180MM (7.08IN). (OTHER CAUSE: BIRDSTRIKE ) (CASA NR 510001924)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070500060	20060705	00060	SW  	2006	7	5	AU510001925      	1	20051212	G	2840		INDICATION SYS  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	FUEL QUANTITY	FAULTY          	W				O				OTHER                   				Y	N		ENGINE STOPPAGE           	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) NO1 ENGINE SHUT DOWN DUE TO FUEL STARVATION. INVESTIGATION FOUND THE FUEL GAUGE INDICATION WAS 400LBS FUEL QUANTIT	Y LHS AND 250LBS FUEL QUANTITY RHS. THE MAGNETIC STICKS SHOWED NIL LHS AND NIL RHS. ACTUAL FUEL EMPTIED FROM TANKS INTO 	CONTAINERS AT WAS 2 LITRES LHS AND 28 LITRES RHS. SUSPECT FAULTY FUEL INDICATING SYSTEM. INVESTIGATION CONTINUING.(OTHER	 CAUSE: UNDER INVESTIGATION ) (CASA# 510001925)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006070500061	20060705	00061	SW  	2006	7	5	AU510001926      	1	20051212	G	6420	206012E11	TRUNNION        			BELL  	205   	205B        	       	SW  	ALLSN 	250C  	250C20J     	03013	GL  					TAIL ROTOR HUB	CRACKED         	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR HUB ASSEMBLY TRUNNION CRACKED ON INNER BEARING RACE. (OTHER CAUSE: MATERIAL ) (CASA NR 510001926)						1	G	7	1 	4U	3	U		H1SW    	E4CE				 
2006070500062	20060705	00062	SO  	2006	7	5	AU510001927      	1	20051212	G	3242		SPACER          	CLEVELAND   		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	BRAKE CALIPER	INCORRECT       	W				O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR BRAKE CALIPER SPACER INCORRECTLY FITTED ON THE WRONG SIDE ALLOWING THE CALIPER TO FALL OUT OF	 THE GUIDES. MAINTENANCE ERROR. (OTHER CAUSE: WHEEL SPACER PLACED ON INCORRECT SIDE OF WHEEL ) (CASA NR 510001927)					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2006070300071	20060703	00071	CE  	2006	7	3	AU510001928      	1	20051212	G	7830	20200081	ARM             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					IDLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2414 			3426					LT ENGINE THRUST REVERSER INBOARD LOWER IDLER ARM BROKEN AT BEARING END BATWING ATTACHMENT POINT.  DURING INVESTIGATION 	CRACKS WERE ALSO FOUND IN THE UPPER THRUST REVERSER SKIN THROUGH A ROW OF NINE RIVETS.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006070300072	20060703	00072	SO  	2006	7	3	AU510001929      	1	20051212	G	2701	12006325007	CONTROL WHEEL   			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		31549								CAPTAIN`S CONTROL WHEEL CRACKED AT BEND APEX.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006070300073	20060703	00073	CE  	2006	7	3	AU510001930      	1	20051212	G	2720		LOCK NUT        			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RUDDER PEDAL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		95   								(AUS) RUDDER PEDAL INTERCONNECT TUBE DISCONNECTED AT PILOT`S RUDDER PEDAL BELLCRANK. INVESTIGATION FOUND THE ATTACHING B	OLT PNO 130909B81 AND WASHER ON THE FLOOR AND THE NUT ON TOP OF THE BELLCRANK. NIL EVIDENCE OF A SPLIT PIN WAS FOUND. TH	E NYLOC NUT WAS INSPECTED AND NIL EVIDENCE OF THREAD CUT INTO THE NYLOC WAS FOUND. SUSPECT THE NUT HAD BEEN ONLY SCREWED	 ON BY THREE OR FOUR THREADS AND HAD NOT LOCKED. PERSONNEL/MAINTENANCE ERROR MANUFACTURING ERROR. AIRCRAFT IS OPERATED B	Y THE AUSTRALIAN MILITARY AND HAS ONLY OPERATED FOR APPROXIMATELY 95 HOURS SINCE NEW. SEE ATTACHMENT FOR FURTHER INFORMA	TION. (OTHER CAUSE: NUT NOT FITTED & LOCKED AT MANUFACTURE ) (CASA# 510001930)	2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2006070300074	20060703	00074	NM  	2006	7	3	AU510001931      	1	20051212	G	7931	APT761000100DW	TRANSMITTER     			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	OIL PRESSURE	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		99999	99999							LT ENGINE OIL PRESSURE TRANSMITTER FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070300075	20060703	00075	SW  	2006	7	3	AU510001932      	1	20051212	G	6220	206011E11	PITCH HORN      			BELL  	206   	206B1       	1181503	SW  	ALLSN 	250C  	250C20J     	03013	GL  					MAIN ROTOR HUB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR HEAD PITCH HORN DAMAGED BEYOND REPAIR. INVESTIGATION FOUND THAT AN INDENTATION IN THE PITCH HORN UPPER 	SURFACE WAS PREVIOUS DAMAGE THAT HAD BEEN BLENDED AND PAINTED OVER. FOLLOWING REMOVAL OF THE PAINT IT WAS FOUND THAT THE	 DAMAGE WAS BEYOND THE ALLOWABLE LIMITS SET OUT IN THE REPAIR AND OVERHAUL MANUAL. FURTHER INVESTIGATION FOUND THAT THE 	DAMAGE TOLERANCES HAD BEEN AMENDED BY THE MANUFACTURER AND THE DAMAGE WAS NOW WITHIN ACCEPTABLE LIMITS. NIL DEFECT. (OTH	ER CAUSE: INCORRECT DAMAGE CRITERION USED ) (CASA# 510001932)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006070300076	20060703	00076	NM  	2006	7	3	AU510001933      	1	20051212	G	2913	GENM29501013	PUMP            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYDRAULIC SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		44252	3242 							HYDRAULIC SYSTEM `B` HYDRAULIC PUMP FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300077	20060703	00077	NM  	2006	7	3	AU510001934      	1	20050509	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 										FUSELAGE FRAMES CONTAINED 28 CRACKS AT PASSENGER SERVICE UNIT (PSU) ATTACHMENT POINTS.  FOUND DURING EDDY CURRENT INSPEC	TION IAW EI 737-53-68R3 AND B737 NTM PT6 51-00-00 FIG 4 AND FIG 16.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300078	20060703	00078	EU  	2006	7	3	AU510001935      	1	20051212	G	5313		STRINGER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					BS 13851	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 LT STRINGER LOCATED AT STN 13851 IN THE FORWARD CARGO COMPARTMENT CORRODED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006070300079	20060703	00079	GL  	2006	7	3	AU510001936      	3	20051212	G	6111		BLADE           	MCAULY      		CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					981258					PROPELLER BLADE CRACKED AT 40` STATION.  FURTHER INVESTIGATION OPENED UP THE CRACK AND FOUND A LARGE AREA OF CORROSION.						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2006070500144	20060705	00144	WP  	2006	7	5	AU510001937      	2	20051212	G	7200	TPE33112UH	ENGINE          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RIGHT	FLUCTUATES      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE EXPERIENCED 20 PERCENT TO 30 PERCENT TORQUE DROP WITH ASSOCIATED EGT FLUCTUATIONS.  MAINTENANCE INVESTIG	ATION COULD NOT FIND ANY FAULTS AND ENGINE PARAMETERS WERE NORMAL.  AIRCRAFT RETURNED TO SERVICE. (CASA NR 510001937)					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006070500145	20060705	00145	NM  	2006	7	5	AU510001938      	1	20051212	G	2530	GENM2585013	OVEN            			BOEING	737   	737*        	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					GALLEY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 		31451	2739 							(AUS) SMOKE AND FUMES IN FORWARD GALLEY.  INVESTIGATION FOUND GALLEY OVEN C206 CIRCUIT BOARD DIODE BURNED.  INVESTIGATIO	N ALSO FOUND A BURNED RESISTOR R429 ON THE POWER SWITCH BOARD PNO LK25-85-4B.  (OTHER CAUSE: MATERIAL ) (CASA NR 5100019	38)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500147	20060705	00147	NM  	2006	7	5	AU510001939      	1	20051212	G	5210	232U212220B	STRIKER         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					COCKPIT DOOR	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT DOOR LOCK ELECTRICAL STRIKER ASSEMBLY OVERHEATED AND FAILED. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CA	SA NR510001939)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006070500148	20060705	00148	EU  	2006	7	5	AU510001940      	1	20051212	G	5311		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) FUSELAGE FRAME 43 CRACKED.  FOUND DURING INSPECTION IAW AD/BAE146/116. (OTHER CAUSE: MATERIAL ) (CASA NR 510001940	)					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006070500149	20060705	00149	EU  	2006	7	5	AU510001941      	1	20051212	G	5311		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) FUSELAGE FRAME 41 AND FRAME 43 CRACKED. FOUND DURING INSPECTION IAW AD/BAE146/116.  (OTHER CAUSE: MATERIAL ) (CASA	 NR 510001941)					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006070500151	20060705	00151	NE  	2006	7	5	AU510001942      	2	20051212	G	7250	3030252	RING            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	STATOR VANE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) POWER TURBINE STATOR VANE RING CRACKED AND SEPARATED AT THE ROOT ENDS WITH CURLING OF THE TIPS. (OTHER CAUSE: NOT 	KNOWN AT THIS STAGE ) (CASA# 510001942)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006070500152	20060705	00152	EA  	2006	7	5	AU510001943      	2	20051212	G	7322	70148001	SERVO           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	FUEL	CONTAMINATED    	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			AU	S 			1868 							(AUS) FUEL SERVO CONTAMINATED WITH OILY RESIDUE LOCATED BEHIND THE VENTURI.  CONTAMINATION WAS CONSISTANT WITH PRECISION	 SIL RS-40.(OTHER CAUSE: ENVIRONMENT ) (CASA NR 510001943)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2006070500153	20060705	00153		2006	7	5	AU510001944      	4	20051212	G	6122	8971604	GOVERNOR        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	PROPELLER	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			3442 							(AUS) RT ENGINE PROPELLER GOVERNOR FAULTY.  INVESTIGATION CONTINUING. (CASA NR 510001944)						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	5	C	P10NE	 
2006070500155	20060705	00155	CE  	2006	7	5	AU510001945      	1	20051212	G	2750		LEAD            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FLAP SELECTOR	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 		3732 								(AUS) FLAP SELECTOR MICROSWITCH POWER WIRE OPEN CIRCUIT. (CASA NR 510001945)						2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006070500217	20060705	00217	EU  	2006	7	5	AU510001946      	1	20051212	G	3397		WIRE            			AIRBUS	330   	A330300     	       	EU  	GE    	CF6   	CF680       	30025	NE  					EMERGENCY LIGHT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR 3 EMERGENCY EXIT LIGHTS (2OFF) FAILED. SUSPECT WIRING DEFECT. (CASA NR 510001946)						2	L	7	2 	4F	4	F	RT	        	E13NE				 
2006071000087	20060710	00087	EU  	2006	7	10	AU510001947      	1	20051212	G	3020	40E183SNGWD03086	SHUTOFF VALVE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ENG ANTI-ICE SYS	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										LT ENGINE ANTI-ICE PRESSURE REGULATING AND SHUTOFF VALVE (PRSOV) FAILED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000088	20060710	00088	EU  	2006	7	10	AU510001948      	1	20051212	G	2824	9401037	MOTOR           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					XFLOW VALVE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										FUEL SYSTEM RT CROSS FLOW VALVE MOTOR FAULTY.  VALVE STUCK IN CLOSED POSITION.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000089	20060710	00089	EU  	2006	7	10	AU510001949      	1	20051212	G	5330		SKIN            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					FUSELAGE	LIGHTNING STRIKE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										EVIDENCE OF LIGHTNING STRIKE ON FUSELAGE AT STN 9305, STN 9805 AND STN 10253.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006070500371	20060705	00371	NM  	2006	7	5	AU510001950      	1	20050210	G	3411	0851HT1	PROBE           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					ADC	BLOCKED         	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										AIRCRAFT SUFFERED MOTH STRIKES DURING TAKEOFF.  CAPTAIN`S PITOT PROBE BLOCKED BY MOTH FOD.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006070600001	20060706	00001	NM  	2006	7	6	AU510001951      	1	20050210	G	7830		BOLT            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BLOCKER DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					714185001					NR 2 ENGINE THRUST REVERSER BLOCKER DOOR DRAG LINK/DOOR ATTACHMENT BOLT NUT AND WASHER MISSING ALLOWING BOLT TO DROP DOW	N AND GOUGE AND DAMAGE DOOR BEYOND LIMITS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071000090	20060710	00090	NE  	2006	7	10	AU510001952      	2	20051212	G	7200		ENGINE          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					LEFT	FAILED          	W				A				UNSCHED LANDING         				F	X	J	FLT CONT AFFECTED         	ENGINE FLAMEOUT           	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										PASSENGER REPORTED `FLAMES OF RED METAL COMING FROM LEFT ENGINE 3-4 METRES BACK` AND AN EMERGENCY LANDING WAS CARRIED OU	T.  ENGINEERING INSPECTION THE IGV`S, FIRST STAGE COMPRESSOR, AFT FACE OF POWER TURBINE ASSEMBLY FOUND NIL DAMAGE.  A GR	OUND POWER ASSURANCE RUN WAS CARRIED OUT.  TAKEOFF MARGIN WAS 33.2 DEGREES C.  SHIFT FROM LAST GPA RUN MINIMAL.  AIRCRAF	T HAS OPERATED SERVICEABLE SINCE.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2006071000091	20060710	00091	EU  	2006	7	10	AU510001953      	1	20050510	G	2424	740514C	GCU             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 2 GENERATOR	FAILED          	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 										NR 2 GENERATOR CONTROL UNIT (GCU) FAILED.  NR 2 GENERATOR TRIPPED OFF LINE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000092	20060710	00092	NE  	2006	7	10	AU510001954      	2	20051212	G	7230	848101	COMPRESSOR      			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 3 ENGINE	MISREPAIRED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 ENGINE FIRST STAGE COMPRESSOR BLADE BLENDED BEYOND LIMITS IN MAINTENANCE MANUAL.  RECORDS GAVE NO INDICATION OF BLE	ND REPAIR BEING CARRIED OUT.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006071100178	20060711	00178	WP  	2006	7	11	AU510001955      	1	20051209	G	6320	269A5154	SHAFT           	HUGHES      	269A517537  	HUGHES	269   	269C        	4470504	WP  	CONT  	O360  	IO360G      	17025	SO  					M/R GEARBOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		736  			S0124					(AUS) LATERAL CYCLIC CONTROL BELLCRANK LOOSE. DISASSEMBLY AND INVESTIGATION OF THE TRANSMISSION FOUND THAT THE BELLCRANK	 MOUNTING SHAFT ATTACHED TO THE TRANSMISSION HAD NO SPLIT PIN WHICH ALLOWED THE NUT TO WORK LOOSE AND COME OFF THE SHAFT	. THE NUT AND WASHER WERE FOUND SITTING IN THE RING GEAR CARRIER. THE RING GEAR CARRIER HAD GROOVES WORN INTO IT BY THE 	LOOSE NUT AND/OR WASHER MAKING IT AND THE TRANSMISSION UNSERVICEABLE. THE NUT/WASHER/SPLIT PIN ARE FITTED INTERNALLY IN 	THE TRANSMISSION. PERSONNEL/MANUFACTURING ERROR. (CASA NR 510001955)		1	G	7	1 	3O	3	O		4H12    	E1CE				 
2006071100179	20060711	00179	NM  	2006	7	11	AU510001956      	1	20050410	G	2701	82710081	CONTROL COLUMN  			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2410 								(AUS) RT CONTROL COLUMN LOWER ATTACHMENT RIVETS LOOSE. CONTROL COLUMN HAD APPROXIMATELY 5MM (0.196IN) FORE AND AFT MOVEM	ENT WHEN LOCKED. (CASA NR 510001956)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006071100180	20060711	00180	SW  	2006	7	11	AU510001957      	1	20050510	G	5751		STRUCTURE       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	AILERON	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING CONTROL CHECKS AILERONS FELT STRANGE WHEN MOVED IN LT DIRECTION. INVESTIGATION FOUND THE RT AILERON HAD SUF	FERED INTERFERENCE DAMAGE WITH THE WING LOWER TRAILING EDGE CAUSING THE AILERON SKIN TO BIND WITH THE WING SKIN AND JAM.	 FURTHER INVESTIGATION FOUND EVIDENCE OF A FOREIGN OBJECT COMING INTO CONTACT WITH THE WING/AILERON SKIN (WITNESS MARKS)	 AT THE INBOARD EDGE OF THE AILERON AND THE WING LOWER TRAILING EDGE AT THE SAME LOCATION.(OTHER CAUSE: FOREIGN OBJECT D	AMAGE ) (CASA NR 510001957)		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006071100181	20060711	00181	NE  	2006	7	11	AU510001958      	2	20050410	G	7200		ENGINE          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R390	R3904123F27 	NE  	RIGHT	SHUTDOWN        	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) RT ENGINE PARAMETERS DECREASED AND ENGINE SHUTDOWN. EXTENSIVE INVESTIGATION COULD FIND NO CAUSE FOR THE SHUTDOWN. 	THE AIRCRAFT WAS RETURNED TO SERVICE AND HAS OPERATED WITHOUT FURTHER INCIDENT. (OTHER CAUSE: UNKNOWN ) (CASA NR 5100019	58)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P31NE	 
2006071100182	20060711	00182	EU  	2006	7	11	AU510001959      	1	20050510	G	2761		BOLT            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					SPOILER	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT LIFT DUMPER ACTUATOR NR 3 AND NR 4 ATTACHMENT BOLTS NOT LOCKWIRED. PERSONNEL/MAINTENANCE ERROR. (CASA NR 510001	959)					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071100183	20060711	00183	NM  	2006	7	11	AU510001960      	1	20050210	G	7603	448774	NUT             	PWA         	JT8D15      	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					POWER LEVER	SEPARATED       	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 					0					(AUS) NR 2 ENGINE POWER CONTROL LEVER CONTROL CRANK RETAINING NUT LOCATED ON THE MAIN ACCESSORY GEARBOX CROSS SHAFT ADRI	FT. THE CRANK MOVED OFF THE CROSS SHAFT AND POWER LEVER CONTROL WAS LOST. THE RESULT OF THE UNCONTROLLED POWER LEVER ALL	OWED AN UNCOMMANDED INCREASE IN FUEL FLOW RESULTING IN A RISE IN EGT. THE START LEVER BECAME JAMMED AT 50 PERCENT TRAVEL	 DUE TO INTERFERENCE OF THE POWER LEVER CONTROL RODS HAVING MOVED OFF THE MAIN ACCESSORY GEARBOX CROSS SHAFT.  INVESTIGA	TION FOUND THAT THE LOCKWIRE ON THE CROSS SHAFT POWER LEVER CRANK RETAINING NUT HAD BROKEN. THIS ALLOWED THE RETAINING N	UT TO EVENTUALLY BACK OFF WITH THE RESULTING CONSEQUENCES. (CASA NR 510001960)	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006071100184	20060711	00184	EU  	2006	7	11	AU510001961      	1	20050710	G	8011		DRIVE SHAFT     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STARTER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE AIR STARTER DRIVESHAFT SHEARED. (OTHER CAUSE: AWAITING STRIP REPORT ) (CASA NR 510001961)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000093	20060710	00093	GL  	2006	7	10	AU510001962      	2	20050410	G	7310	AC9227F1740	FILTER          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT ENGINE FUEL	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										RT ENGINE FUEL FILTER CONTAMINATED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006071000094	20060710	00094	EU  	2006	7	10	AU510001963      	1	20050710	G	8011		DRIVE SHAFT     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STARTER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 ENGINE AIR STARTER DRIVE SHAFT SHEARED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800107	20060608	00107	CE  	2006	6	8	AU510001964      	1	20050710	G	5511	432001E15	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		5247 								HORIZONTAL STABILIZER INBOARD LEADING EDGE RIBS CRACKED.  REMOVAL OF HORIZONTAL STABILIZER INBOARD RIBS REVEALED ONE PIE	CE 0.5 SQ INCH OF FLANGE COMPLETELY CRACKED AWAY STARTING FROM APEX RELIEF HOLE.  THIS AREA IS NOT NORMALLY VISIBLE FOR 	INSPECTION.  ONE OTHER FLANGE CRACK EXTENDED 12.7MM (0.5IN) FURTHER UNDER SKINS.  THIS AREA IS ALSO NOT NORMALLY VISIBLE	 FOR INSPECTION.  IN TOTAL, FOUR CRACKS (THREE RT AND ONE LT) WERE FOUND MAKING THE STABILIZER UNSERVICEABLE.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2006060800108	20060608	00108	NE  	2006	6	8	AU510001965      	2	20050410	G	7200	JT8D15	ENGINE          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  						BIRD INGESTION  	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			AU	S 										NR 1 ENGINE BIRDSTRIKE.  INVESTIGATION FOUND THE REMAINS OF THREE FLYING FOXES.  THOROUGH INSPECTION OF THE ENGINE FOUND	 NO OBVIOUS DEFECTS.  A WATER WASH WAS CARRIED OUT AND THE AIRCRAFT RELEASED TO SERVICE.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006060800110	20060608	00110		2006	6	8	AU510001966      	4	20050710	G	6122	8971609	GOVERNOR        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	FAULTY          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			4796 							LT ENGINE PROPELLER GOVERNOR FAULTY.						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2006060800111	20060608	00111	EU  	2006	6	8	AU510001967      	1	20050610	G	5711	HLT912AP109	BOLT            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING SPAR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CENTER FUEL TANK WING SPAR ATTACHMENT BOLTS (4OFF) HAD SHEAR BOLT HEADS.  FUEL LEAKING FROM CENTER TANK AT RT FRONT CORN	ER ABOVE THE WING TO FUSELAGE ATTACHMENT LINK AT FRAME 26 RIB 2.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006060800113	20060608	00113	GL  	2006	6	8	AU510001968      	3	20051212	G	6114	D65591	HUB             													HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								CM1093A		CHECK OF PROPELLER HUB BEFORE FITMENT TO AIRCRAFT FOUND UNACCEPTABLE DAMAGE IN BLADE/HUB SOCKET RADIUS.  THIS IS A CRITI	CAL AREA AND THE MANUFACTURER ADVISED THAT THE HUB BE SCRAPPED.															5	C	P27EA	 
2006060800114	20060608	00114	GL  	2006	6	8	AU510001969      	3	20051212	G	6114	D65591	HUB             			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								CM1014A		PROPELLER HUB CORRODED BEYOND LIMITS INTERNALLY IN AREA LOCATED AROUND LOWER CONTROL ROD BORE BOSS.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2006060800115	20060608	00115	GL  	2006	6	8	AU510001970      	3	20051212	G	6114	C501	HUB             			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PROPELLER HUB CORRODED BEYOND LIMITS IN BLADE SOCKET AREA.						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006060800116	20060608	00116	EU  	2006	6	8	AU510001971      	1	20050710	G	2613	1734362450	DETECTOR        			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	OVERHEAT SYS	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										LT ENGINE TAILPIPE OVERHEAT DETECTOR FAULTY.  SUSPECT CAUSED BY WATER INGRESS DUE TO HEAVY RAIN.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2006060800117	20060608	00117	EU  	2006	6	8	AU510001972      	1	20050810	G	8011		DRIVE SHAFT     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STARTER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 ENGINE STARTER DRIVESHAFT SHEARED.  SUSPECT CAUSED BY ERRATIC PRESSURE PULSES FROM APU AIR SUPPLY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800191	20060608	00191	EU  	2006	6	8	AU510001973      	1	20050810	G	4970	38760033	THERMOCOUPLE    			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					BLEED AIR SYS	BROKEN          	W				K				NONE                    				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			AU	S 										APU AIR SUPPLY ERRATIC WITH PULSES CAUSING FAILURE OF THREE AIRSTARTERS.  INVESTIGATION FOUND APU THERMOCOUPLE BREAKING 	DOWN.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800193	20060608	00193	EU  	2006	6	8	AU510001974      	1	20050310	G	2741	FON9126422	TRIM SWITCH     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					STAB	FAULTY          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										STABILIZER TRIM SWITCH INTERMITTENT DUE TO FAULTY WIRE TERMINATION.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800195	20060608	00195	NM  	2006	6	8	AU510001975      	1	20050710	G	3230		LANDING GEAR    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  		MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										WHEN THE LANDING GEAR WAS SELECTED `UP` THE NOSE LANDING GEAR DOORS FAILED TO CLOSE.  THE GEAR WAS RECYCLED AND THE NLG 	DOORS INDICATED `CLOSED`.  THOROUGH TESTING AND INVESTIGATION IAW MAINTENANCE MANUAL FAILED TO FIND A CAUSE FOR THE DEFE	CT AND THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER INCIDENTS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300002	20060613	00002	GL  	2006	6	13	AU510001976      	3	20051212	G	6110		CYLINDER        	HARTZL      		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					FP1026A					DURING STRIP IT WAS FOUND THAT THE PROPELLER CYLINDER HAD BEEN OVERTORQUED WHEN LAST FITTED.  FURTHER INVESTIGATION FOUN	D THAT THE NUT HOLDING THE PISTON UNIT TO THE CONTROL ROD WAS LOOSE AND THE SPLIT PIN WAS SHEARED.  THE REMAINS OF THE S	PLIT PIN WERE FOUND IN THE PROPELLER ON EITHER SIDE OF THE PISTON.  DAMAGE TO THE UNDERSIDE OF THE PISTON HAD BEEN DRESS	ED OUT.  SUSPECT THAT THE CYLINDER AND PISTON HAD BEEN REMOVED AND REFITTED WITHOUT USING THE CORRECT TECHNIQUES OR TOOL	S.		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006060800304	20060608	00304	CE  	2006	6	8	AU510001977      	1	20051212	G	5711	4224076	SPAR            			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		9645 								RT WING SPAR STRAP CONTAINED AREAS OF HEAVY CORROSION BETWEEN THE MATING FACES OF THE SPAR ANGLE AND SPAR STRAP LOCATED 	MAINLY IN THE TANK BAY AREA.					1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL	 
2006060800305	20060608	00305	CE  	2006	6	8	AU510001978      	1	20051212	G	5711	4224152	ANGLE           			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		9645 			0					RT WING SPAR ANGLE CONTAINED AREAS OF HEAVY CORROSION BETWEEN THE MATING FACES OF THE ANGLE AND SPAR CHANNEL AND THE ANG	LE AND THE SPAR STRAP.  CORROSION WAS MAINLY LOCATED IN THE AREA OF THE TANK BAY.					1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL	 
2006060800306	20060608	00306	CE  	2006	6	8	AU510001979      	1	20051212	G	5711	4224056	SPAR            			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		9645 								RT WING SPAR CHANNEL HEAVILY CORRODED IN AREAS ON THE MATING FACE BETWEEN THE CHANNEL AND THE SPAR ANGLE.						1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL	 
2006060800337	20060608	00337	EA  	2006	6	8	AU510001982      	2	20051212	G	8530	LW18852	CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540V2AD  	41532	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AU	S 			602  				L848461A			LT ENGINE NR 5 CYLINDER CRACKED AROUND TOP.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060800403	20060608	00403	SO  	2006	6	8	AU510001983      	1	20051212	G	5312	62444005	BULKHEAD        			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		10762								REAR FUSELAGE BULKHEAD CRACKED.  FOUND FOLLOWING REMOVAL OF STEEL FORWARD FIN ATTACHMENT FITTING.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006060800404	20060608	00404	SW  	2006	6	8	AU510001984      	1	20051212	G	2820		NUT             			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL HOSE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		721  			0					FUEL SYSTEM HOSE ASSEMBLY NUT CRACKED ON FLARE FITTING.  FUEL LEAKING.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2006060800405	20060608	00405	NM  	2006	6	8	AU510001985      	1	20051212	G	5521	651693541	SPAR            	BOEING      	657278411   	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		53629			0					LT ELEVATOR REAR SPAR CRACKED.  FOUND DURING INSPECTION IAW AD/B727/100.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006062300007	20060623	00007	NE  	2006	6	23	AU510001986      	2	20051010	G	7200	3029300	ENGINE          			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	RIGHT	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) RT ENGINE FAILED DURING LANDING ROLL WHEN REVERSE THRUST WAS DE-SELECTED.  THOROUGH INVESTIGATION COULD FIND NO CA	USE FOR THE DEFECT. SUSPECT THE FUEL FLOW MAY HAVE DROPPED TOO FAR WHILE REDUCING NEGATIVE THRUST TO A POINT THAT THE EN	GINE FLAMED OUT. THE AIRCRAFT HAS RETURNED TO SERVICE WITH NO FURTHER ISSUES NOTED.  (CASA NR 510001986)				1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006061200274	20060612	00274	NE  	2006	6	12	AU510001987      	2	20051210	G	7421	Y1836	IGNITER         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 1 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 ENGINE IGNITER PLUG FAILED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061200276	20060612	00276	EU  	2006	6	12	AU510001988      	1	20051210	G	4920		APU             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					APU BAY	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										APU AUTO SHUTDOWN.  INVESTIGATION COULD FIND NO FAULTS.  DURING TEST FLIGHT THE APU AGAIN SHUT DOWN.  INVESTIGATION CONT	INUING.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061200277	20060612	00277	EU  	2006	6	12	AU510001989      	1	20051110	G	2923		PUMP            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 SYSTEM HYDRAULIC PUMP FAILED.   INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061200279	20060612	00279	SO  	2006	6	12	AU510001990      	1	20051212	G	5311		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			AU	S 		10107								REAR FUSELAGE FRAME AND DOUBLER CRACKED AND CORRODED.  SUSPECT MATING SURFACES NOT PRIMED DURING MANUFACTURE.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006061200310	20060612	00310	SO  	2006	6	12	AU510001991      	1	20051212	G	5312	62404003	BULKHEAD        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		8144 								REAR FUSELAGE BULKHEAD CRACKED.  FOUND FOLLOWING REMOVAL OF FORWARD FIN ATTACHMENT FITTING.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
2006061300112	20060613	00112	SW  	2006	6	13	AU510001992      	1	20050710	G	7603	74390420	CONTROL CABLE   	GARRETTLTD  		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	POWER LEVER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT ENGINE POWER CONTROL CABLE BROKEN BETWEEN POWER LEVER AND CABLE JOINT.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006061300113	20060613	00113		2006	6	13	AU510001993      	4	20051212	G	3416	433006228	ALTIMETER       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										ENCODING ALTIMETER FAILED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061300114	20060613	00114	EU  	2006	6	13	AU510001994      	1	20050601	G	5751	68530171	FITTING         			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERONS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										TORQUE TUBE ATTACHMENT FITTING CORRODED.  LIMITED INFORMATION PROVIDED.						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
2006061300116	20060613	00116	EA  	2006	6	13	AU510001995      	2	20051212	G	8520	19341	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			568  							RT ENGINE METAL CONTAMINATION.  INVESTIGATION FOUND CAMSHAFT LOBE FOR INLET VALVE ON NR 5 AND NR 6 CYLINDERS FAILED/WORN	.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061300118	20060613	00118	SO  	2006	6	13	AU510001996      	1	20051212	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										MAIN LANDING GEAR INBOARD DOOR HINGE ASSEMBLY CRACKED IN ATTACHMENT ANGLES.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006061300119	20060613	00119	CE  	2006	6	13	AU510001997      	1	20051212	G	5312		BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										REAR PRESSURE BULKHEAD EXTENDER NR 7 CLEAT CRACKED.						1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061300121	20060613	00121	SO  	2006	6	13	AU510001998      	2	20051010	G	8530		ROCKER          			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ROCKER ARMS (2OFF) HAD HARD FACING FAILURE.  FOUND DURING INSPECTION IAW AD/ENG/4 AMDT9.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2006061300239	20060613	00239	GL  	2006	6	13	AU510001999      	2	20050510	G	7310		FILTER          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT ENGINE FUEL	CONTAMINATED    	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										RT ENGINE FUEL FILTER CONTAMINATED WITH BLACK SOOTY DEPOSITS.  FURTHER INVESTIGATION FOUND A LESSER DEGREE OF THE SAME D	EPOSITS IN THE LT ENGINE FUEL FILTER.  EXTENSIVE FUEL DRAINS FOUND TO BE CLEAR.  INVESTIGATION CONTINUING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061300242	20060613	00242	EA  	2006	6	13	AU510002000      	2	20050510	G	8530	C36001D	CYLINDER        			GIPPLD	GA200 	GA200       	3900100	EU  	LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 		1638 	792  		0					ENGINE CYLINDERS (2OFF) CRACKED IN CYLINDER HEAD AREA.						1	L	7	1 	3O	3	O	NC	A00001LA	E295	5	N	P874	 
2006061300244	20060613	00244	CE  	2006	6	13	AU510002001      	1	20050610	G	2710	AN16132LL	FORK            			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	AILERONS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		7309 			0					RT AILERON BELLCRANK FORK CORRODED.  FOUND DURING INSPECTION IAW AWB 27-1.  AIRCRAFT HAS SPENT MOST OF ITS LIFE OUTDOORS	.					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2006061300246	20060613	00246	NE  	2006	6	13	AU510002002      	2	20051210	G	7321	324476812	FUEL CONTROL    			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT642A      		NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			AU	S 		4171 	2832 		0					ENGINE FUEL CONTROL UNIT FAILED.  FORWARD BEARING COLLAPSED.  BEARING WAS OLD PRE-MOD TYPE.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061300247	20060613	00247	CE  	2006	6	13	AU510002003      	1	20050610	G	3320	334977E14	INVERTER        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					CABIN LIGHTS	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 		3177 								FLUORESCENT CABIN LIGHTING SYSTEM COLD CATHODE INVERTER FAILED INTERNALLY.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061300249	20060613	00249	NM  	2006	6	13	AU510002006      	1	20051212	G	3230		DOOR            			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ALT MLG EXTEND	OPEN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 		99999	99999							LANDING GEAR FAILED TO RETRACT.  INVESTIGATION FOUND THAT THE ALTERNATE GEAR EXTENSION DOOR IN THE FLIGHT DECK FLOOR WAS	 OPEN.  WITH THIS DOOR OPEN THE LANDING GEAR CYCLE WILL NOT COMMENCE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400179	20060614	00179	SO  	2006	6	14	AU510002007      	2	20051212	G	8540		DRIVE SHAFT     			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	CSU	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										CSU DRIVE ASSEMBLY FAILED.  INVESTIGATION CONTINUING.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
2006061400180	20060614	00180	NM  	2006	6	14	AU510002008      	1	20051212	G	5610		WINDSHIELD      			BOEING	737   	737800*     	       	NM  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										CAPTAIN`S NR 2 WINDSHIELD OUTER PANE SHATTERED.						2	L	7	2 	4F			RT	A16WE   					 
2006061400182	20060614	00182		2006	6	14	AU510002009      	4	20050610	G	3420	6229436100	SYMBOL GENERATOR			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ATTITUDE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CAPTAIN`S SYMBOL GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061400183	20060614	00183	SW  	2006	6	14	AU510002010      	1	20051205	G	2910		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	HYD SYSTEM	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NUMEROUS RIGID HYDRAULIC AND FUEL PIPES DETERIORATED.  PIPES WERE CRACKED, CORRODED AND CHAFED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006061400184	20060614	00184		2006	6	14	AU510002011      	4	20051210	G	3421	6226342022	EADI            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	COCKPIT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										CAPTAIN`S ELECTRONIC ATTITUDE DIRECTION INDICATOR (EADI) FAILED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006061400185	20060614	00185	EU  	2006	6	14	AU510002012      	1	20051212	G	7500		WARNING SYSTEM  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					BLEED AIR SYS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										RT ENGINE BLEED AIR LEAK LIGHT ILLUMINATED.  INVESTIGATION CONTINUING.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2006061400189	20060614	00189	NM  	2006	6	14	AU510002013      	1	20051212	G	3244		TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG	DEFLATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		21872	384  							NR 12 MAIN WHEEL TIRE PRESSURE REDUCING STEADILY.  INVESTIGATION FOUND THAT THE TIRE CARCASS HAD BEEN PUNCTURED BY FOD.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061400190	20060614	00190		2006	6	14	AU510002014      	4	20051212	G	3421	HG1050AD04	IRU             			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ATTITUDE GYRO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		20332	6251 							NR 1 INERTIAL REFERENCE UNIT (IRU) FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061400191	20060614	00191	NM  	2006	6	14	AU510002015      	1	20050310	G	5414	UL37842	PANEL           	RROYCE      		BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE COWLING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 ENGINE LT FORWARD LOWER CARBON FIBER PANEL P/N UL37842 DAMAGED.  FORWARD SUPPORT BRACKETS (2OFF) P/N UL24084A FOUND	 SHEARED/CRACKED TO COMPRESSOR CASING.  CORE PANEL SUPPORT BRACKETS (3OFF) UNSERVICEABLE.  LT LOWER `A` FRAME TO CORE CU	FF PANELS DAMAGED/MISSING.  LOWER CUFF PANEL P/N UL27564 AND UPPER CUFF PANEL P/N UL27563 MISSING.				2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061500099	20060615	00099	NE  	2006	6	15	AU510002016      	2	20050310	G	7314	PAC102MK4S	PUMP            			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUEL SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		6504 	6504 							NR 3 ENGINE FUEL PUMP LOW PRESSURE IMPELLER SHEARED.  INVESTIGATION FOUND THE FAILURE OF THE PUMP WAS CAUSED BY VIBRATIO	NS THAT WERE INTRODUCED BY THE INTERACTION OF THE IMPELLER SYMMETRICAL SUPPORT PINS WITH THE SPACER TUBE.  THESE VIBRATI	ONS CAUSED A LOSS OF TORQUE ON THE SCREWED PLUG P/N 77083508 WHICH ALLOWED THE IMPELLER P/N 77085495 TO MOVE ON THE GEAR	 SHAFT P/ N 77086297.  THIS MOVEMENT CAUSED THE IMPELLER TO LOCK ON THE IMPELLER BACK PLATE AND INSERT ASSEMBLY RESULTIN	G IN THE SHEARED QUILL SHAFT.		2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006061500101	20060615	00101	NE  	2006	6	15	AU510002018      	2	20051212	G	7421	Y1836	IGNITER         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 2 ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 ENGINE IGNITER WORN.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500102	20060615	00102	EU  	2006	6	15	AU510002019      	1	20051212	G	7830	1159SCP4081	SOLENOID        	RROYCE      		FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					THRUST REVERSER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 ENGINE THRUST REVERSER INTERMITTENT WARNING.  INVESTIGATION FOUND THE SECONDARY LOCK SOLENOID HAD A FAULTY INTERNAL	 SWITCH.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500104	20060615	00104	EA  	2006	6	15	AU510002020      	2	20050610	G	8530	TISN41	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 2	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		39   								NR 2 CYLINDER BORE COATING MISSING, PISTON RINGS WORN AND SCORING ON PISTON SKIRT.						1	L	7	1 	3O	3	O		2A13    	E274				 
2006061500105	20060615	00105	SW  	2006	6	15	AU510002021      	1	20051110	G	3241	60064911	CONTROL VALVE   			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ANTI SKID SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 		10519								RT MAIN LANDING GEAR NR 2 WHEEL LOCKED UP ON LANDING CAUSING THE TIRE TO BURST.  INVESTIGATION FOUND THE RT MAIN LANDING	 GEAR AXLE HAD WATER INGRESS AND THE ANTI-SKID WIRING HAD HIGH RESISTANCE.  THE WIRING WAS REPLACED BUT THE ANTI-SKID SY	STEM WAS STILL INOPERATIVE.  FURTHER INVESTIGATION FOUND THE OUTBOARD ANTI-SKID CONTROL VALVE FAILED.				2	L	7	2 	4T	3	T	RT	A5SW    	E2WE	6	C	3PNE	 
2006061500106	20060615	00106	CE  	2006	6	15	AU510002022      	2	20051212	G	7314		SHAFT           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL PUMP	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			1066 							ENGINE DRIVEN FUEL PUMP LEAKING.  THE PUMP WAS DISMANTLED AND THE FOLLOWING DEFECTS WERE FOUND, ROTOR SHAFT FOUND WITH E	XCESSIVE WEAR AND EXTREME SCORING, DEEP SCORING IN SHAFT BEARING (BUSHING), LOWER FACE OF ROTOR SHAFT HAS CONTACTED AND 	DAMAGED LOWER THRUST PLATE.  THE WEAR ON PARTS HAS ALLOWED THE ROTOR TO BE LOADED TO ONE SIDE CAUSING  WEAR ON LINER WAL	L 5.  ROTOR SHAFT (AT VANE SEGMENTS) SHOWS SIGNS OF BEING SUBJECT TO EXTREME HEAT.			1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061500107	20060615	00107	NM  	2006	6	15	AU510002023      	1	20051212	G	3220		LANDING GEAR    			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NOSE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										AFTER TAKEOFF, NOSE LANDING GEAR EXTENDED WHEN LANDING GEAR LEVER WAS SELECTED TO `OFF`.  NLG WAS NOT OVERSPED.  INVESTI	GATION COULD FIND NO FAULTS WITH THE EXTENSION/RETRACTION SYSTEM.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061500108	20060615	00108	EU  	2006	6	15	AU510002024      	1	20051212	G	7810		FAIRING         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ENGINE EXHAUST SPOKE FAIRING CRACKED IN TWO PLACES AT THE 7:30 O`CLOCK AND 9 O`CLOCK POSITIONS.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061500109	20060615	00109	NM  	2006	6	15	AU510002025      	1	20051212	G	6120	8148291	TRANSFER TUBE   			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT PROPELLER TRANSFER TUBE DRIVE PIN LOOSE.  DURING TEST FOR AXIAL RETENTION OF THE DRIVE PIN, IT WAS FOUND TO MOVE WITH	 LESS THAN THE REQUIRED 25-30 POUNDS FORCE.  FOUND DURING INSPECTION IAW AD/PHS/22.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061500233	20060615	00233	WP  	2006	6	15	AU510002026      	2	20051212	G	7200		ENGINE          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RIGHT	SEIZED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										RT ENGINE SEIZED.  INVESTIGATION CONTINUING.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061600010	20060616	00010	CE  	2006	6	16	AU510002027      	1	20051010	G	5540	4310074	HORN            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RUDDER HORN CORRODED IN AREA OF CABLE ATTACHMENT.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2006061600011	20060616	00011	CE  	2006	6	16	AU510002028      	1	20051212	G	7430	L2925010105	IGNITION SWITCH 			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					COCKPIT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					IGNITION SWITCH INTERNAL CONTACTS WORN WITH EVIDENCE OF ARCING.  FOUND DURING INSPECTION IAW AD/ELEC/59.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006061600012	20060616	00012	CE  	2006	6	16	AU510002029      	1	20051212	G	5511	53200198	SPAR            	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		4149 			17263115					HORIZONTAL STABILIZER FRONT SPAR CRACKED.  FOUND DURING INSPECTION IAW AD/CESSNA170/59.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061600013	20060616	00013	WP  	2006	6	16	AU510002030      	1	20051212	G	7820	C1693	MUFFLER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		985  								MUFFLER ASSEMBLY COLLAPSED AROUND TAILPIPE IN AREA LOCATED UNDER THE HEATER SHROUD.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061600014	20060616	00014	NM  	2006	6	16	AU510002031      	1	20051212	G	5302	A02323	TAIL BOOM       			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  						DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		814  								TAILBOOM DISTORTED IN FIRST BAY.  FOUND DURING INSPECTION FOLLOWING HARD LANDING.						1	G	7	1 	3O	3	O		H10WE   	E286				 
2006061600016	20060616	00016	SO  	2006	6	16	AU510002032      	1	20051212	G	2434	ALE1003K	BEARING         	ELECTROSYS  		PIPER 	PA30  	PA39        	7103902	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	ALTERNATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			691  		B030341					LT ENGINE ALTERNATOR DRIVE END BEARING SPINNING IN HOUSING.  ALTERNATOR ROTOR RUBBING ON STATOR.  LOSS OF BEARING GREASE	.					1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
2006061600017	20060616	00017	EA  	2006	6	16	AU510002033      	2	20051212	G	8520	68484	TUBE            	LYC         							LYC   	O360  	O360A1F6    	41514	EA  					CRANKSHAFT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										OIL TRANSFER TUBE LOOSE IN CRANKSHAFT.  SUSPECT POOR QUALITY OF FLARING. INVESTIGATION FOUND TWO OTHER CRANKSHAFTS WITH 	THE SAME PROBLEM.										3	O			E286				 
2006061600018	20060616	00018	NM  	2006	6	16	AU510002034      	1	20051212	G	6120	8148291	TUBE            	HAMSTD      		DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT PROPELLER TRANSFER TUBE DRIVE PIN LOOSE.  DURING TEST FOR AXIAL RETENTION OF THE DRIVE PIN, IT WAS FOUND TO MOVE WITH	 LESS THAN THE REQUIRED 25-30 POUNDS FORCE.  FOUND DURING INSPECTION IAW AD/PHS/22.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061600020	20060616	00020	GL  	2006	6	16	AU510002035      	3	20051212	G	6114	C7361	HUB             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	PROPELLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					0					RED DYE LEAKING FROM PROPELLER HUB.  INSPECTION FOUND THE CYLINDER SCREWS TIGHT AND LOCKWIRED.  SUSPECT FAULTY MANUFACTU	RE OF GASKET P/N C7361.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	 	 
2006061900019	20060619	00019	NM  	2006	6	19	AU510002036      	1	20050710	G	2780	256T280014	TORQUE TUBE     			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					LE SLAT CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LEADING EDGE SLAT TORQUE TUBE COUPLING SPLINES WORN AT NR 5 LEADING EDGE SLAT GEARBOX.  INVESTIGATION ON REMOVAL FOUND T	HAT THE SPLINES (SPLINE FITTING P/N 256T2806-1 WERE COMPLETELY MISSING FROM THE TORQUE TUBE FITTING.  THE TORQUE TUBE CO	UPLING P/N 256T2801-1 APPEARS IN SATISFACTORY CONDITION WITH ONLY A SMALL AMOUNT OF WEAR EVIDENT.				2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006061900021	20060619	00021	NM  	2006	6	19	AU510002037      	1	20051212	G	3242	S160T400510	ROTOR           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NR 6 BRAKE	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										MAIN LANDING GEAR NR 6 BRAKE ROTOR DISINTEGRATED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061900024	20060619	00024	NM  	2006	6	19	AU510002038      	1	20051212	G	5244		DOOR            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LAVATORY	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										PAPER AND LINEN WASTE RECEPTACLE DOORS IN TOILETS NOT SEALING.  INVESTIGATION FOUND LAV A (FWD) TO BE LATCHING SECURELY 	BUT NOT SEALING.  INVESTIGATION REVEALED EXTRA STRIKER PLATE BONDED OVER EXISTING STRIKER PLATE CAUSING DOOR TO SIT OUT 	FURTHER THAN REQUIRED.  EXTRA PLATE REMOVED.  DOOR IS NOW SEALING.  LAV B (MID) HINGE REQUIRED TO BE ADJUSTED IN SO THAT	 THE WASTE COMPARTMENT INNER DOOR COULD SEAL ADEQUATELY.  PAINT REMOVED FROM STRIKER PLATE TO ENSURE MAGNETIC LATCH OPER	ATION.  WASTE CONTAINER OUTER DOOR FOULS INNER DOOR HINGE AREA WHEN CLOSED CAUSING A SLIGHTLY PRE-LOADED CONDITION ON TH	E OUTER DOOR LATCH ASSEMBLY.  FOUND DURING INSPECTION IAW AD/GENERAL/48 AND EI 734-25-2R9.	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061900028	20060619	00028	NM  	2006	6	19	AU510002039      	1	20050810	G	2997		CONNECTOR       			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HYDRAULIC PUMP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										HYDRAULIC PUMP CONNECTOR AND MATING RECEPTACLE CONTAMINATED WITH HYDRAULIC FLUID AND BADLY BURNT.  ONE OF THE CONNECTOR 	SOCKETS WAS WELDED ONTO THE PUMP CONNECTOR PINS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061900029	20060619	00029	NM  	2006	6	19	AU510002040      	1	20050510	G	2131	1305026	CONTROLLER      			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					CABIN PRESSURE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 		18593								NR 2 CABIN PRESSURE CONTROLLER FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006061900031	20060619	00031	NM  	2006	6	19	AU510002041      	1	20051110	G	3610		PNEUMATIC SYSTEM			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT ENGINE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										LT ENGINE PRV WARNING WHEN TAKEOFF THRUST SET.  MESSAGE CLEARS WHEN THRUST REDUCED.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061900032	20060619	00032	NM  	2006	6	19	AU510002042      	1	20051210	G	2750	113A93061	CONTROL ROD     			BOEING	767   	767*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					TE FLAP CONTROL	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										RT INBOARD FLAP OUTBOARD FAIRING ATTACHMENT ROD SEPARATED.  INVESTIGATION FOUND THE CONTROL ROD FROM FLAP LOWER SURFACE 	TO THE AFT LINKAGE OF THE FAIRING HAD BECOME DETACHED AND THE LOWER BEARING HAD PULLED OUT OF THE ROD.					2	L	7	2 	4F	4	F	RT	A1NM    	E2GL				 
2006061900034	20060619	00034		2006	6	19	AU510002043      	4	20051212	G	3442	6225136203	RADAR           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					WX SYS	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		39707								WEATHER RADAR FAULTY.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061900036	20060619	00036	NM  	2006	6	19	AU510002044      	1	20051212	G	2910	65445101378	PIPE            			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D7       	52053	NE  					HYDRAULIC SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										HYDRAULIC PIPE LOCATED IN NR 2 ENGINE NACELLE LEAKING.						2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006061900144	20060619	00144	NM  	2006	6	19	AU510002045      	1	20051212	G	5714		VAPOR BARRIER   			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					WING	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										WING CENTER SECTION FUEL VAPOR BARRIER UNDER LIMITS IN THE FOLLOWING SIX AREAS ON THE TRIANGLE POCKET-FRONT SPAR/SIDE OF	 BODY, TP3-R THICKNESS 1.7 2. TP3-L 2.2, TP6-L 5.9 4. TP9-L 2.0 SHEAR FITTING, FRONT SPAR CORNER WITH TOP PANEL  5. SF4-	R 6.3 6. SF5-R 5.8 FOUND DURING INSPECTION IAW AD/B737/245 AND SB 737-57-1250.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061900298	20060619	00298	NM  	2006	6	19	AU510002046      	1	20051212	G	3244		TIRE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 4 MAIN WHEEL TIRE DEFLATED.  INSPECTION FOUND A 100MM (4IN) CUT IN THE SIDEWALL.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061900299	20060619	00299		2006	6	19	AU510002047      	4	20051212	G	3420	DG1035AB03	ADAPTER         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					DAA	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		43748	43748							RT INERTIAL REFERENCE SYSTEM (IRS) FAILED.  CAUSED BY FAULTY RT DIGITAL ANALOGUE ADAPTER (DAA).						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061900300	20060619	00300		2006	6	19	AU510002048      	4	20051212	G	3417	4040800906	ADC             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										AIR DATA COMPUTER (ADC) FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061900301	20060619	00301	NM  	2006	6	19	AU510002049      	1	20051212	G	3350		LIGHT           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					R1 DOOR	OVERHEATED      	W				O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 										ENHANCED CABIN LIGHTING SYSTEM LOCATED ABOVE DOOR 1R OVERHEATED.  FIRE AND SMOKE IN CABIN.  BCF FIRE EXTINGUISHER DISCHA	RGED.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061900302	20060619	00302		2006	6	19	AU510002050      	4	20051212	G	2330		CONTROL SYSTEM  			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					VIDEO SYS	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										PASSENGER ENTERTAINMENT SYSTEM VIDEO CONTROL CENTER FAULTY.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061900304	20060619	00304	NM  	2006	6	19	AU510002051      	1	20051212	G	2781	189929	PROXIMITY SENSOR			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NR 6 SLAT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 6 LEADING EDGE SLAT POSITION PROXIMITY SENSOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061900309	20060619	00309		2006	6	19	AU510002052      	4	20051212	G	3442	6225135002	DISPLAY         			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					WX RADAR SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 		45912	92   							WEATHER RADAR PEDESTAL FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006062100163	20060621	00163	NM  	2006	6	21	AU510002053      	1	20051212	G	2710	BACP30M1A	PULLEY          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					AILERON CONTROL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON SYSTEM SLIGHTLY STIFF. LT TRIM ACTUATOR CHANGED BUT DEFECT REMAINED.  INVESTIGATION FOUND A SEIZED PULLEY 	IN AILERON CONTROL SYSTEM. PULLEY LOCATED AT LT AB CABLE RUN AT STN 380 WL 283.  (CASA NR 510002053)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006062300077	20060623	00077		2006	6	23	AU510002054      	4	20051212	G	3442	8221710001	TRANSMITTER     			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					WX RADAR SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		978  	978  							(AUS) WEATHER RADAR TRANSMITTER/RECEIVER FAILED. (CASA NR 510002054)						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062300078	20060623	00078		2006	6	23	AU510002055      	4	20051212	G	6122	4060575	COVER           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	GOVERNOR	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			842  		2488029					(AUS) PROPELLER GOVERNOR CONTROL HEAD BROKEN AWAY IN AREA LOCATED BELOW THE LEVER RETURN SPRING. LOSS OF APPROXIMATELY 2	 QUARTS OF OIL. (CASA NR 510002055)					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2006062300079	20060623	00079	EU  	2006	6	23	AU510002056      	1	20051212	G	2550	AFGO326925	CABLE           			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					CARGO HOOKS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					374					(AUS) BAMBI BUCKET FULL OF WATER CARRIED BELOW AIRCRAFT ON CARGO HOOK FELL OFF WHEN HOOK INADVERTENTLY RELEASED. INVESTI	GATION OF THE CARGO HOOK MANUAL RELEASE CABLE FOUND IT TO BE DAMAGED. FURTHER INVESTIGATION FOUND THAT THE OUTER SHEATH 	HAD BEEN DAMAGED PREVIOUSLY AND CORROSION AND BROKEN WIRE STRANDS HAD BEEN COVERED WITH TAPE. THE DAMAGED OUTER SHEATH H	AD CAUSED THE INNER CABLE TO KINK AND ALLOW THE MANUAL CABLE RELEASE MECHANISM TO OPERATED WHEN A FULL BUCKET LOAD WAS A	TTACHED. SUSPECT CABLE DAMAGE HAD OCCURRED BEFORE THE AIRCRAFT WAS PURCHASED BY THE PRESENT OWNER. PERSONNEL/MAINTENANCE	 ERROR. ILLEGAL REPAIR. (CASA NR 510002056)	1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2006062300080	20060623	00080	SO  	2006	6	23	AU510002057      	2	20051212	G	7414	6314653271	MAGNETO         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		422  								(AUS) LT AND RT MAGNETOS PREMATURELY WORN.  LT MAGNETO, HIGH VOLT CONTACT TERMINALS IN DIST BLOCK/CAP ARE ERODED/ARCED. 	HIGH VOLT DIST ARM TIP HAS ERODED CENTER WIPER ELECTRODE, ARCED END W/PITTING, MATERIAL BREAK DOWN.   POINTS SHOW SIGNS 	OF PITTING WITHIN SERVICE LIMITS.  CONDENSER MEASURED .35.   RT MAGNETO, DIST SHAFT CARBON BRUSH/SPRING ASSY WORN BEYOND	 LIMITS, CARBON BRUSH AND SPRING BURNED AWAY.  SPRING LEAF ON COIL HAS BEEN BURNED BY ARCING.  HIGH VOLT CONTACT TERMINA	LS IN DIST BLOCK/CAP ARE ERODED/ARCED.  HIGH VOLT DIST ARM TIP HAS ERODED CENTER WIPER ELECTRODE, ARCED END WITH PITTING	, MATERIAL BREAK DOWN.  POINTS SHOW SIGNS OF PITTING WITHIN SERVICE LIMITS.  CONDENSER MEASURED .35. (CASA NR 510002057)	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2006062100090	20060621	00090	NM  	2006	6	21	AU510002058      	1	20051212	G	5414	UL37842	PANEL           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 4 NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR4 ENGINE LOWER (A) FRAME SEALING FAIRING UPPER PANEL MISSING AND LOWER FAIRING SLIGHTLY DAMAGED ON THE AFT CORNE	R. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA NR 510002058)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006070500063	20060705	00063	EU  	2006	7	5	AU510002059      	1	20051212	G	5534	F535760800020	LUG             			AIRBUS	A330  	A330*       	       	EU  	GE    	CF6   	CF680       	30025	NE  					VERTICAL STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER ACCESS LADDER UPPER ATTACHMENT LUGS BROKEN. SUSPECT CAUSED BY POOR SHIMMING OF THE UPPER ATTAC	HMENT FITTINGS. SEE ATTACHMENT FOR INVESTIGATION DETAILS. (CASA NR 510002059)					2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2006070500064	20060705	00064	EU  	2006	7	5	AU510002060      	2	20051212	G	7250		SHROUD          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TURBINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		42120	42120							(AUS) LT ENGINE FAILED TO START.  INVESTIGATION FOUND ENGINE SEIZED AND A SMALL AMOUNT OF DEBRIS IN THE TAILPIPE.  BOROS	COPE INSPECTION FOUND DAMAGE TO HIGH PRESSURE TURBINE (HPT).  INVESTIGATION FOUND THE HPT SHOUD HAD FAILED AND LODGED BE	TWEEN THE HPT BLADES AND THE FIRST STAGE LPT NOZZLE GUIDE VANE CAUSING THE N2 TO SEIZE.  FURTHER INVESTIGATION CONTINUIN	G. (CASA NR 510002060)			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500065	20060705	00065	NE  	2006	7	5	AU510002061      	2	20051212	G	7200	CFM567B24	ENGINE          			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  						CONTAMINATED    	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) OILY FUMES IN COCKPIT AND CABIN. AIRCRAFT TURNED BACK AND OVERWEIGHT LANDING WAS CARRIED OUT. OVERWEIGHT LANDING I	NSPECTION CARRIED OUT WITH NIL FAULTS. SUSPECT FUMES CAUSED BY INHIBITING FLUID REMAINING IN ENGINE FOLLOWING ENGINE CHA	NGE. INVESTIGATION CONTINUING. (CASA NR 510002061)				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006071900012	20060719	00012	EU  	2006	7	19	AU510002062      	1	20051212	G	3244		TIRE            			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	MLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 		685  								(AUS) RT MAIN LANDING GEAR TIRE DEFLATED.  SUSPECT TIRE DAMAGED BY FOD.(OTHER CAUSE: MATERIAL ) (CASA NR 510002062)						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2006070500066	20060705	00066	EA  	2006	7	5	AU510002063      	2	20051212	G	8530	LW12416PO10	EXHAUST VALVE   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 3 CYLINDER	SEIZED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1412 				L927839A			(AUS) NR 3 CYLINDER EXHAUST VALVE SEIZED IN VALVE GUIDE.						1	L	7	1 	3O	3	O		2A13    	E274				 
2006070500067	20060705	00067	GL  	2006	7	5	AU510002064      	1	20051212	G	2434	S4024LP	ALTERNATOR      			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  		FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 		26   								(AUS) ALTERNATOR FAILED. INVESTIGATION FOUND DEFECTIVE INSULATORS AND BATTERY POST TO ALTERNATOR BODY ARCING.  (CASA NR 	510002064)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
2006070500068	20060705	00068	SO  	2006	7	5	AU510002065      	1	20051212	G	3211	AN6H14A	BOLT            			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1B90	1B90*       	GL  	LT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		6130 								(AUS) LT MAIN LANDING GEAR ATTACHMENT BOLT SHEARED.  LT MAIN LANDING GEAR COLLAPSED. (OTHER CAUSE: MATERIAL - ENVIRONMEN	T ) (CASA NR 510002065)					1	L	7	1 	3O	3	O		A18SO   	E223	5	N	P842	 
2006070500069	20060705	00069	WP  	2006	7	5	AU510002066      	1	20051212	G	6420	HS1551238	WASHER          			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		425  								(AUS) TAIL ROTOR FORK ASSEMBLY NUT TABWASHER FAILED ALLOWING THE NUT TO WORK LOOSE.  AIRCRAFT THEN SUFFERED A LOSS OF TA	IL ROTOR CONTROL WHICH RESULTED IN A FORCED LANDING WITH MINOR AIRCRAFT DAMAGE. INVESTIGATION FOUND A BROKEN INTERNAL TA	B ON THE TABWASHER.(OTHER CAUSE: UNKNOWN ) (CASA NR 510002066)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006070300011	20060703	00011	EA  	2006	7	3	AU510002067      	2	20051212	G	7313	47739	METERING JET    								LYC   	O360  	O360A1F6    	41514	EA  					CARBURETOR	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										CARBURETOR JET INCORRECTLY MANUFACTURED.  METERING HOLE MACHINED OUT OF ROUND.  JET IS A NEW ITEM REMOVED FROM OVERHAUL 	KIT P/N 286-1670-F.										3	O			E286				 
2006070300080	20060703	00080	SO  	2006	7	3	AU510002068      	1	20051212	G	5311	62444005	FRAME           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		6859 								REAR FUSELAGE FRAME P/N 62444-005 AND DOUBLER P/N 79272-000 CRACKED AND CORRODED.						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA	 
2006070300081	20060703	00081	CE  	2006	7	3	AU510002069      	1	20051212	G	8011	C12ST21S	MOTOR           			CESSNA	150   	A150L       	2071828	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	STARTER	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		81   								(AUS) ENGINE STARTER MOTOR HAD NO DRAIN HOLE DRILLED.  THIS ALLOWED OIL TO ACCUMULATE IN THE PINION AREA AND LEAK PAST T	HE ADAPTER PLATE GASKET.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006070300082	20060703	00082	EU  	2006	7	3	AU510002070      	1	20051212	G	3241		ANTI-SKID SYS   			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										FOLLOWING TWO BURST TIRES ON NR 1 MAIN WHEEL, MAINTENANCE CHANGED THE GREEN SYSTEM ANTI-SKID VALVE FOR NR 1 WHEEL POSITI	ON.  INVESTIGATION CONTINUING.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006070300083	20060703	00083	NM  	2006	7	3	AU510002071      	1	20051212	G	5714		VAPOR BARRIER   			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					WING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FUEL VAPOR BARRIER LOCATED IN CENTER WING BOX WAS FOUND TO BE BELOW MINIMUM THICKNESS AND LIFTING.  FOUND DURING INSPECT	ION IAW AD/737/245 AND BOEING SB 737-57-1250.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006070300084	20060703	00084	GL  	2006	7	3	AU510002072      	3	20051212	G	6111	A22131	SPRING          			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PROPELLER COARSE PITCH STOP P/N A2420-30 AND SPRING P/N A2213-1 WORN.  SPRING WAS PREVENTED FROM RETURNING THE BLADES TO	 THE FINE PITCH POSITION AFTER SHUTDOWN.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2006070500080	20060705	00080	EA  	2006	7	5	AU510002073      	2	20051212	G	8520	13F27727	CRANKSHAFT      			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2193 	145  							(AUS) CRANKSHAFT REMOVED AND REPLACED DUE TO APPLICABILITY WITH AD AND SB 566. (AD/SB DESC: SB 566 AND AD/LYC/112 ) (CAS	A NR 510002073)					1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2006070300085	20060703	00085	EA  	2006	7	3	AU510002074      	2	20051212	G	7414	10382585	POINTS          	CONT        		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	MAGNETO	UNSERVICEABLE   	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			AU	S 		13   			G04JA140R					RT MAGNETO CONTACT BREAKER POINT LOOSE ON SPRING ASSEMBLY.  CONTACTS HAD BEEN REPLACED APPROXIMATELY 13 HOURS PREVIOUSLY	.  SUSPECT BREAKER INCORRECTLY SWAGED ONTO SPRING.					1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2006070500156	20060705	00156	NM  	2006	7	5	AU510002075      	1	20051212	G	2150	1828203	HEAT EXCHANGER  			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					A/C PACK	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT AND RT AIR CONDITIONING PACK SECONDARY HEAT EXCHANGERS CRACKED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500157	20060705	00157	NM  	2006	7	5	AU510002076      	1	20050111	G	5714		VAPOR BARRIER   			BOEING	737   	7377Q8      	1384418	NM  	CFMINT	CFM567	CFM567B2US  	13802	NE  					FUME BARRIER	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SECONDARY FUEL VAPOUR BARRIER OUT OF LIMITS IN THE FOLLOWING AREAS:- TP3-R 0.001, TP3-L 0.001, TP6-R 0.001, TP6-L 	0.001, TP9-R 0.001, TP9-L 0.003, SF2-R 0.005, SF1-L 0.003, SF2-L 0.002. SF3-R 0.002, SF4-R 0.004, SF3-L 0.002, SF4-L 0.0	06 FOUND DURING INSPECTION IAW AD/737/245 AND SB 737-57-1250. (AD/SB DESC: AD/B737-245 ) (CASA NR 510002076)				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006070500160	20060705	00160	NE  	2006	7	5	AU510002077      	2	20051212	G	7250		GUIDE VANE      			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					1ST STAGE NOZZLE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							687588			(AUS) NR 1 ENGINE FIRST STAGE NOZZLE GUIDE VANE (NGV) BURNED THROUGH.  NGV WAS LOCATED ADJACENT TO NR 9 COMBUSTION CHAMB	ER.  SUSPECT CAUSED BY CRACKING ON THE LEADING EDGE ALLOWING HOT AIR TO PENETRATE THE NGV. FOUND DURING INSPECTION OF TH	E COMBUSTION CHAMBERS IAW AD/JT8D/20 (PW SB5639).   (OTHER CAUSE: MATERIAL ) (CASA NR 510002077)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006070500161	20060705	00161	EU  	2006	7	5	AU510002078      	1	20051111	G	2910	D71281649	LINE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE CRACKED AND LEAKING. LOSS OF HYDRAULIC FLUID. (CASA NR 510002078)						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006070500162	20060705	00162	NE  	2006	7	5	AU510002079      	2	20050911	G	7230		PANEL           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					COMPRESSOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SMALL TITANIUM PANEL MISSING FROM ENGINE COMPRESSOR SECTION. (CASA# 510002079)						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006070500163	20060705	00163	NM  	2006	7	5	AU510002080      	1	20051011	G	3242	26123121	BRAKE           			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					NR 1	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		7198 	1654 							(AUS) NR 1 MAIN LANDING GEAR BRAKE ASSEMBLY LOWER PISTON WET WITH HYDRAULIC FLUID.  LARGE PUDDLE OF HYDRAULIC FLUID FOUN	D.  BRAKE CHANGED. INVESTIGATION CONTINUING AS TO EXACT SOURCE OF LEAK FROM BRAKE. (CASA NR 510002080)					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500219	20060705	00219	CE  	2006	7	5	AU510002081      	1	20050911	G	2761	66276E12	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					SPOILERS	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 		1675 								(AUS) RT WING SPOILER ACTUATOR LEAKING. LOSS OF HYDRAULIC FLUID.(OTHER CAUSE: MATERIAL ) (CASA NR 510002081)						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006071000095	20060710	00095		2006	7	10	AU510002082      	4	20050811	G	3457		CIRCUIT CARD    			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	GPS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										GPS DATA CARD FAILED.						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006071000096	20060710	00096	SW  	2006	7	10	AU510002083      	1	20051011	G	3297		WIRE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CONTROL VALVE	WORN            	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										LANDING GEAR CONTROL VALVE CONNECTOR PLUG WIRE WORN AND SHORT CIRCUITING TO PIN `B`.						2	L	7	2 	4T	3	T	RT	A5SW    	E2WE	6	C	3PNE	 
2006071000097	20060710	00097	NE  	2006	7	10	AU510002084      	3	20051011	G	6111	4HFR34C652	BLADE           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										LIGHTNING STRIKE ON AIRCRAFT EXITED THROUGH LT PROPELLER BLADE.  UNKNOWN POINT OF ENTRY.  ENGINE AND PROPELLER REMOVED F	OR LIGHTNING STRIKE INSPECTION.					2	L	7	2 	4T	3	T	RT	A5SW    	E2WE	6	C	3PNE	 
2006071000098	20060710	00098	SO  	2006	7	10	AU510002085      	2	20051212	G	8530	AEC631397A	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 2	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1044 								NR 2 CYLINDER CRACKED AND LEAKING IN AREA LOCATED BETWEEN THE SECOND AND THIRD FINS BACK FROM THE TOP SPARK PLUG HOLE.  	CRACKS ALSO FOUND UNDER THE TOP SPARK PLUG HOLE, BETWEEN THE SPARK PLUG AND EXHAUST VALVE SEAT INSIDE THE CYLINDER AND I	NSIDE THE EXHAUST PORT FROM THE EXHAUST VALVE SEAT HEADING TOWARDS THE LOWER SIDE OF THE CYLINDER.  CYLINDER FALLS OUTSI	DE THE RANGE COVERED BY ECI SB SI04-1.			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006071000099	20060710	00099	EU  	2006	7	10	AU510002086      	1	20050911	G	2421	740508	IDG             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AC GENERATOR	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			AU	S 			11874							LT ENGINE INTEGRATED DRIVE GENERATOR (IDG) FAULTY.  LT GENERATOR LINE CONTACTOR P/N S6002206 ALSO CHANGED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000100	20060710	00100	EU  	2006	7	10	AU510002087      	1	20051011	G	2844		PRESSURE SWITCH 			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL SYSTEM	FAULTY          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AU	S 										FUEL TRANSFER PUMP PRESSURE SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006071000101	20060710	00101	NM  	2006	7	10	AU510002088      	1	20050911	G	2133		OUTFLOW VALVE   			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					CABIN PRESSURE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										PRESSURIZATION SYSTEM PROBLEMS.  INVESTIGATION FOUND INBOARD AND OUTBOARD POSITIVE PRESSURE RELIEF VALVES TO BE UNSERVIC	EABLE.  BOTH VALVES REPLACED.  OUTBOARD VALVE CURRENTLY CONSIDERED TO BE THE PRIMARY CAUSE OF THE CABIN DEPRESSURIZATION	 EVENT.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100123	20060711	00123	CE  	2006	7	11	AU510002089      	1	20051011	G	5414	57544104	SKIN            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		17109								UPPER AFT RT NACELLE SKIN CRACKED AND CORRODED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006071100132	20060711	00132		2006	7	11	AU510002090      	4	20050311	G	6122	F624	GOVERNOR        	HARTZL      		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 			186  							RT ENGINE PROPELLER GOVERNOR COUPLING GEAR PNO A-3181 DRIVE TEETH (8OFF) SHEARED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006071100133	20060711	00133	NE  	2006	7	11	AU510002091      	2	20051212	G	7200	6053T87G01	ENGINE          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R389	R3894123F25 	NE  	LEFT	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										LT ENGINE OIL SYSTEM CHIP DETECTOR CONTAMINATED WITH METAL FUZZ.  ANALYSIS FOUND THE METAL TO BE BEARING MATERIAL.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P30NE	 
2006071100134	20060711	00134	CE  	2006	7	11	AU510002092      	1	20050911	G	3020	65525026	BELLOWS         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					AIR INTAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		3778 								LT ENGINE AIR INTAKE ANTI-ICE SYSTEM BELLOWS BROKEN AT WELD.						2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006060800118	20060608	00118		2006	6	8	AU510002093      	4	20051212	G	3416	433006228	ENCODER         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ALTIMETER	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										ALTIMETER ENCODER OUTPUT FAILED GIVING FALSE READINGS.						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2006060800119	20060608	00119	SO  	2006	6	8	AU510002094      	2	20050510	G	8530	AEC642068STA	CYLINDER        			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	FAULTY          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		396  	396  				288427R			PISTON RINGS PREMATURELY WORN AND DETERIORATED CAUSING HIGH OIL CONSUMPTION AND POWER LOSS.  CYLINDER VALVE GUIDES WORN 	AND EXHAUST VALVE REPLACED.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2006060800121	20060608	00121	NM  	2006	6	8	AU510002095      	1	20050811	G	6310	A9661	SEAL            	ROBSIN      		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					CLUTCH ASSY	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					7048					ENGINE/TRANSMISSION CLUTCH ASSEMBLY FORWARD AND AFT SEALS DISLODGED IN HOUSING.  NO OIL LOSS WAS NOTICED.  SUSPECT SEALS	 ARE BEING HYDRAULICALLY PRESSED OUT DUE TO THE EXCESS OIL IN THE CLUTCH BEING UNABLE TO BLEED BACK TO THE RESERVOIR.					1	G	7	1 	3O	3	O		H10WE   	E286				 
2006060800124	20060608	00124	SO  	2006	6	8	AU510002096      	1	20050710	G	2410		PULLEY          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ALTERNATOR	LOOSE           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			AU	S 					D02131					ALTERNATOR DRIVE PULLEY CAME LOOSE AND DAMAGED ALTERNATOR COOLING FAN.  A PIECE OF THE COOLING FAN CAME OFF AND ENTERED 	THE ALTERNATOR CAUSING AN INTERNAL SHORT CIRCUIT.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060800126	20060608	00126	NM  	2006	6	8	AU510002097      	1	20050611	G	4930		PUMP            			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					APU FUEL SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										APU FUEL PUMP LEAKING BEYOND LIMITS.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061900169	20060619	00169	WP  	2006	6	19	AU510002099      	1	20050610	G	6410	500P3100101	BLADE           			HUGHES	369   	369E        	4470707	WP  	ALLSN 	25OC  	250C20R     	 	GL  					TAIL ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2582 	842  							(AUS) TAIL ROTOR BLADE DELAMINATED.  AREA OF DELAMINATION APPROXIMATELY 38.1MM LONG BY 9.525MM WIDE (1.5IN BY 0.375IN). 	SEE ATTACHMENT FOR PHOTOGRAPHS.  (OTHER CAUSE: VOID DEVELOPED FROM POOR PREP WHEN REPAIRED BY HTC ) (CASA 510002099)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006060800127	20060608	00127		2006	6	8	AU510002100      	4	20050511	G	2312	1010524	ANTENNA         			BOEING	737   	73776N      	13844CH	NM  	GE    	CFM56 	CFM56*      	13802	NE  					VHF SYSTEM	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										NR 2 VHF ANTENNA BROKEN IN HALF.  BROKEN SECTION MISSING.  SUSPECT CAUSED BY FOD.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800130	20060608	00130	NM  	2006	6	8	AU510002101      	1	20050611	G	2120		ODOR            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										ELECTRICAL BURNING ODOR IN CABIN IN AREA OF ROW 18.  EXTENSIVE INVESTIGATION COULD FIND NO CAUSE FOR THE ODOR.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800309	20060608	00309	EU  	2006	6	8	AU510002102      	1	20050411	G	3260	858202	PSEU            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										PROXIMITY SENSING ELECTRONIC UNIT (PSEU) FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800310	20060608	00310		2006	6	8	AU510002103      	4	20051212	G	3442	8221710001	TRANSCEIVER     			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					WX RADAR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1573 	1573 							WEATHER RADAR TRANSCEIVER FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006060800311	20060608	00311	NM  	2006	6	8	AU510002104      	1	20051212	G	3244		TIRE            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MLG	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		23523	304  							NR 3 MAIN WHEEL TIRE TREAD DEBONDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006060800312	20060608	00312	NM  	2006	6	8	AU510002105      	1	20051212	G	3230	654492532	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										LT MAIN LANDING GEAR ACTUATOR FAULTY.  LT MAIN LANDING GEAR NOT FULLY RETRACTED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006060800323	20060608	00323	EU  	2006	6	8	AU510002106      	1	20050211	G	2822		PUMP            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL BOOST	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 1 CENTER WING TANK BOOST PUMP LOW PRESSURE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800325	20060608	00325	EU  	2006	6	8	AU510002107      	1	20051212	G	3610	3925308	SHUTOFF VALVE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					BLEED AIR SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT BLEED AIR PRESSURE REGULATING AND SHUTOFF VALVE (PRSOV) FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800329	20060608	00329	CE  	2006	6	8	AU510002108      	1	20051212	G	3260	1CH16	SWITCH          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					NLG ACTUATOR	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NOSE LANDING GEAR ACTUATOR DOWNLOCK SWITCH SHORT CIRCUIT.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006060800330	20060608	00330	NM  	2006	6	8	AU510002109      	1	20051212	G	2760		SPOILER         			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  						FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										SPOILER SYSTEM FAULTY.  AIRCRAFT ROLLED TO THE RIGHT WHEN SPEEDBRAKE DEPLOYED.  INVESTIGATION CONTINUING.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2006060800331	20060608	00331	NM  	2006	6	8	AU510002110      	1	20051212	G	3230		SOLENOID        		1387T1005   	BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					UPLOCK ACTUATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					LT WING LANDING GEAR UPLOCK ACTUATOR SOLENOID CORRODED.  A CORROSION LIKE SUBSTANCE WAS FOUND AROUND THE CANNON PLUG AND	 PART OF THE OPERATING SOLENOID OUTER CASE WAS CORRODED AWAY.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006061200269	20060612	00269	GL  	2006	6	12	AU510002111      	2	20050211	G	7321	8061865	MEC             	GE          		BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										LT ENGINE MAIN ENGINE CONTROL (MEC) LEAKING AT THE FORWARD ATTACHMENT FLANGE.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061200313	20060612	00313		2006	6	12	AU510002112      	4	20051212	G	3452	75178E11	TRANSPONDER     			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ATC	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 2 ATC TRANSPONDER FAILED.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061200314	20060612	00314	NM  	2006	6	12	AU510002113      	1	20051212	G	3230	AS11706K0280	HOSE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT MLG CYLINDER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										RT MAIN LANDING GEAR RETRACTION CYLINDER DOWN LINE HOSE LEAKING.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061200316	20060612	00316	NM  	2006	6	12	AU510002115      	1	20051212	G	5753	113T2271Y44	FITTING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT INBOARD TRAILING EDGE FLAP OUTBOARD HINGE FITTING OUTBOARD LUG SHEARED.  FOUND DURING INSPECTION IAW AD/B767/188 (EI 	767-57-073).					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061200317	20060612	00317		2006	6	12	AU510002116      	4	20051212	G	3452	G699035	CONTROL PANEL   	HONEYWELL   		FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					TRANSPONDER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2285					NR 2 ATC TRANSPONDER SYSTEM CONTROL PANEL DISPLAY DIGITS NOT VISIBLE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300145	20060613	00145	GL  	2006	6	13	AU510002117      	3	20051212	G	6111		CLAMP           		D4170       	CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	PROPELLER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			528  		0					NR 2 PROPELLER BLADE COUNTERWEIGHT CLAMP FAILED.						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
2006061300146	20060613	00146	NM  	2006	6	13	AU510002118      	1	20051111	G	2530		OVEN            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					GALLEY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 										SPARKS AND ELECTRICAL FUMES EMANATING FROM REAR GALLEY AREA.  INSPECTION COULD FIND NO FAULTS BUT THE OVEN WAS REPLACED 	AS A PRECAUTION.  INVESTIGATION CONTINUING.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300147	20060613	00147	SW  	2006	6	13	AU510002119      	1	20050811	G	7603	477271611	SHAFT           			BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1F    	41516	EA  					THROTTLE	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 		11475								THROTTLE/COLLECTIVE CONTROL SHAFT CRACKED IN AREA HIDDEN BY GEAR.						1	G	7	1 	3O	3	O		H1      	E279				 
2006061300148	20060613	00148	NM  	2006	6	13	AU510002120      	1	20050911	G	2910	DSC252B40124	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										NOSE LANDING GEAR ACTUATOR FLEXIBLE HYDRAULIC LINE RUPTURED.  LOSS OF NR 2 SYSTEM HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300150	20060613	00150	NE  	2006	6	13	AU510002121      	1	20050311	G	2612		CONNECTOR       			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					FIRE DETECTOR	CONTAMINATED    	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										NR 1 ENGINE FIRE WARNING SYSTEM GAVE FALSE INDICATIONS.  SUSPECT CONNECTOR CONTAMINATED.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2006061300152	20060613	00152	CE  	2006	6	13	AU510002122      	1	20050711	G	8011	2005001	GEAR            	LAMAR       		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					STARTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		179  			85013017					ENGINE STARTER DRIVE GEAR DISINTEGRATED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006061300153	20060613	00153	GL  	2006	6	13	AU510002123      	1	20051212	G	3213	HF5000	FORK            			DHAV  	DH82  	DH82        	2801000	GL  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		5419 								RT MAIN LANDING GEAR COMPRESSION LEG LOWER FORK END FITTING FAILED.  LOWER END OF LEG CONTACTED THE GROUND.						1	Q	7	1 	3I	3	I		EXPA1Q71	A8EU				 
2006061300156	20060613	00156	EU  	2006	6	13	AU510002124      	1	20051111	G	5220	68260411	DOOR            			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	EMERGENCY EXIT	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 		7584 								RT SIDE EMERGENCY EXIT POPPED OUT ON TAKEOFF.  INVESTIGATION COULD FIND NO FAULTS.  SUSPECT CAUSED BY PREVIOUS PASSENGER	 INTERFERENCE WITH LOCKING LEVER.					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
2006061300159	20060613	00159	NM  	2006	6	13	AU510002125      	1	20051111	G	3610	BACC1DU400ABE	CLAMP           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					APU BLEED AIR	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU BLEED AIR DUCT FRACTURED. BLEED AIR SUPPLY DUCT SEPARATED IN HORIZONTAL STABILISER COMPARTMENT. (CASA# 5100021	25)					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300251	20060613	00251	EU  	2006	6	13	AU510002126      	1	20051011	G	2930	6607P98D	PRESSURE SWITCH 			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					HYD SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										LT AND RT HYDRAULIC PRESSURE SWITCHES FOR THE NR 2 STABILIZER SYSTEM FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300253	20060613	00253	EU  	2006	6	13	AU510002127      	1	20051011	G	2840	0106KIP02018	TOTALIZER       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL INDICATION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FUEL INDICATING SYSTEM COMBINED PROCESSOR TOTALIZER UNIT (CPT) FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300254	20060613	00254	NM  	2006	6	13	AU510002128      	1	20051212	G	4990		OIL SYSTEM      			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					APU	LOW             	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										APU OIL QUANTITY LOW.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061300255	20060613	00255	CE  	2006	6	13	AU510002129      	1	20051111	G	3260		DOWNLOCK        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										LT AND RT MAIN LANDING GEAR DOWNLOCKS FOUND TO BE IN AN UNSAFE CONDITION.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2006061300256	20060613	00256	EU  	2006	6	13	AU510002130      	1	20051212	G	3510	176225	OXYGEN BOTTLE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					CREW SYSTEM	LEAKING         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										COCKPIT OXYGEN BOTTLE LEAKING FROM VALVE.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006061300258	20060613	00258	SO  	2006	6	13	AU510002131      	1	20051212	G	2120		SMOKE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										MODERATE AMOUNT OF SMOKE IN COCKPIT CAUSED OXYGEN MASKS TO BE FITTED.  FLIGHT ATTENDANTS ALSO ADVISED OF SMOKE IN THE CA	BIN AND PASSENGER OXYGEN WAS ALSO DEPLOYED.  INVESTIGATION IN PROGRESS TO FIND THE CAUSE OF THE SMOKE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006061300260	20060613	00260	SO  	2006	6	13	AU510002132      	1	20051212	G	5711		RIVET           			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  					WING SPAR	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 		6730 			0					WING REAR SPAR ATTACHMENT PLATE RIVETS (7OFF) MISSING.  INVESTIGATION CONTINUING.						1	L	7	1 	3O	3	O		1A15    	E295				 
2006062100023	20060621	00023	EU  	2006	6	21	AU510002133      	1	20051212	G	2731		TRIM SYSTEM     			GIPPLD	GA8   	GA8         	3900102	EU  										ELEVATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUNAWAY ELEVATOR TRIM SYSTEM. AIRCRAFT IS FOREIGN REGISTERED. (CASA NR 510002133)						1	H	7	1 	3O			NT	        					 
2006061300261	20060613	00261	CE  	2006	6	13	AU510002134      	2	20051212	G	7314	654351	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	LT ENGINE FUEL	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		731  								LT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400192	20060614	00192	SO  	2006	6	14	AU510002135      	2	20051212	G	7314	6543511A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYSTEM	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		126  								RT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400193	20060614	00193	SO  	2006	6	14	AU510002136      	2	20051212	G	7314	6543511A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400194	20060614	00194	CE  	2006	6	14	AU510002137      	2	20051212	G	7314	6543513A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400195	20060614	00195	CE  	2006	6	14	AU510002138      	2	20051212	G	7314	6543511A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400196	20060614	00196	CE  	2006	6	14	AU510002139      	2	20051212	G	7314	6543512	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400197	20060614	00197	CE  	2006	6	14	AU510002140      	2	20051212	G	7314	6543514A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061400198	20060614	00198	SO  	2006	6	14	AU510002141      	2	20051212	G	7314	6543511	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2651 	872  							RT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061500147	20060615	00147	CE  	2006	6	15	AU510002142      	2	20051212	G	7314	6543514A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	FUEL SYSTEM	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT ENGINE DRIVEN FUEL PUMP CONTAMINATED AND WORN INTERNALLY.  SUSPECT CAUSED BY CONTAMINATION FROM ELECTRIC FUEL PUMP VA	NES AND/OR BRUSH MATERIAL.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2006061500149	20060615	00149	SW  	2006	6	15	AU510002143      	1	20051212	G	6410	47642117105	BLADE           			BELL  	47    	47          	1180602	SW  										TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1581 								TAIL ROTOR BLADE CORRODED AND DELAMINATED.  DELAMINATION IS LOCATED AT THE OUTBOARD TIP OF THE LEADING EDGE ABRASION STR	IP.					1	G	7	1 	3O				H1      					 
2006061900240	20060619	00240	WP  	2006	6	19	AU510002144      	1	20051212	G	6520	369D25434	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		7461 	4261 							(AUS) TAIL ROTOR GEARBOX METAL CONTAMINATION. INVESTIGATION FOUND THE INPUT SHAFT REAR BEARING PN 369D25417 TO BE UNSERV	ICEABLE. INPUT SHAFT PN 369D25434 CRACKED IN AREA UNDER BEARING. (CASA NR 510002144)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006061500150	20060615	00150	SO  	2006	6	15	AU510002145      	2	20050311	G	7414	10400309	IMPULSE COUPLING	BENDIX      	103493505   	CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MAGNETO	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B119701FR					MAGNETO IMPULSE COUPLING CAM FLYWEIGHT TIP BROKEN OFF.  RETURN SPRING MISSING FROM UNDER FLYWEIGHT.  FOUND DURING INSPEC	TION IAW AD/ELECT/75.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2006061500151	20060615	00151	SO  	2006	6	15	AU510002146      	1	20051212	G	5540	95539000	HINGE           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		2751 			0					RUDDER HINGE BRACKET CORRODED.						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
2006061500153	20060615	00153	SO  	2006	6	15	AU510002147      	1	20051212	G	5720		SUPPORT         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										LT WING REAR SUPPORT CORRODED.  FOUND DURING INSPECTION IAW AD/PA32/27 AMDT2.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
2006061500155	20060615	00155	NM  	2006	6	15	AU510002148      	1	20051211	G	5532		PANEL           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					VERTICAL STAB	MISINSTALLED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										VERTICAL STABILIZER RT LOWER PANEL INCORRECTLY FITTED BETWEEN FORWARD AND AFT ATTACHMENT POINTS.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061500156	20060615	00156	SO  	2006	6	15	AU510002149      	2	20051212	G	8520		PISTON          			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			400  							NR 3 CYLINDER SEVERELY DAMAGED.  INVESTIGATION CONTINUING.						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2006061600021	20060616	00021	NM  	2006	6	16	AU510002150      	1	20051212	G	5551		PIN             			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HORIZONTAL STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					HORIZONTAL STABILIZER REAR SPAR PINS (3OFFLH AND 3OFFRH) WORN BEYOND LIMITS.  FORWARD SPAR RT LOWER BOLT WORN BEYOND LIM	ITS.  FOUND DURING INSPECTION IAW AD/B737/224.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061600022	20060616	00022	WP  	2006	6	16	AU510002151      	2	20051212	G	7260		BEARING         			SWRNGN	SA227 	SA227AT     	8780610	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							P44378			RT ENGINE GEARBOX FUEL PUMP DRIVE BEARING FAILED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P61GL	 
2006061600023	20060616	00023	NM  	2006	6	16	AU510002152      	1	20051212	G	2730	6933691	SPRING          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ELEVATOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										ELEVATOR FEEL SPRING BROKEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061600026	20060616	00026		2006	6	16	AU510002153      	4	20051212	G	3441	HG1050AD04	IRU             			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LEFT	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 		52981	10646							LT INERTIAL REFERENCE UNIT (IRU) FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061600027	20060616	00027	CE  	2006	6	16	AU510002154      	1	20050111	G	2720	4330222	TUBE            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	RUDDER CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		5601 								RUDDER TO NOSE WHEEL STEERING TUBE WORN.  TUBE IS A SEALED UNIT BUT WHEN IT WAS CUT OPEN FOR INVESTIGATION IF WAS FOUND 	THAT THE STEERING RODEND FITTING HAD ALMOST PULLED THROUGH THE WASHER THAT TRANSFERS THE LOAD TO THE SPRING.  IF THE ROD	 PULLED COMPLETELY THROUGH THE WASHER THE RODEND COULD PICK UP ON THE SPRING AND CAUSE RUDDER CONTROL PROBLEMS.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2006061600028	20060616	00028	EA  	2006	6	16	AU510002155      	2	20050911	G	8520	75038	CRANKSHAFT      								LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			774  							CRANKSHAFT BROKEN COMPLETELY THROUGH AT NR 1 CRANKPIN JOURNAL.											3	O			1E4				 
2006061600030	20060616	00030	CE  	2006	6	16	AU510002156      	1	20051212	G	5230	521309126	DOOR            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	CARGO BAY	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			AU	S 		22647								LT FORWARD NOSE LOCKER SEPARATED FROM AIRCRAFT SEVERING BOTH HINGES.  ONE BAG LOST OVERBOARD.  DOOR STRUCK PROPELLER CAU	SING A TORQUE SHIFT IN THE ENGINE.  LT ENGINE, PROPELLER AND LT WING INBOARD LEADING EDGE DAMAGED.  INVESTIGATION CONTIN	UING.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006061600031	20060616	00031	NM  	2006	6	16	AU510002157      	1	20051212	G	5610	58935734	WINDOW          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 		11271								COCKPIT NR 4 (EYEBROW) WINDOW INNER PANE SHATTERED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061900038	20060619	00038	NE  	2006	6	19	AU510002158      	2	20051212	G	7310	UL37981	PIPE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE FUEL	BROKEN          	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 					0					NR 3 ENGINE MANIFOLD FUEL DRAIN LINE BROKEN AND LEAKING AT WELDED JOINT LOCATED BETWEEN THE FUEL DRAIL TUBE AND THE END 	FITTING AT THE MANIFOLD END OF THE ASSEMBLY.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061900039	20060619	00039	NE  	2006	6	19	AU510002159      	2	20051212	G	7310	UL37981	PIPE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE FUEL	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										FUEL LEAKING FROM NR 3 ENGINE.  ENGINE CHANGED.  INVESTIGATION FOUND THE FUEL MANIFOLD DRAIN TUBE FRACTURED IN THE TUBE 	BORE AT THE EDGE OF THE WELD.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006061900041	20060619	00041	CE  	2006	6	19	AU510002160      	1	20050111	G	7603	5038901219	CABLE           			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	POWER LEVER	FAILED          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										LH ENGINE THROTTLE CABLE FAILED IN AREA UNDER SHEATH.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P5EA	 
2006061900044	20060619	00044	NE  	2006	6	19	AU510002161      	2	20051212	G	7310		SEAL            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUEL FILTER	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										LT ENGINE FUEL FILTER BOWL SEAL DISPLACED AND FUEL LEAKING.  FILTER BOWL WAS CORRECTLY LOCKWIRED.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE	 
2006061900045	20060619	00045	NM  	2006	6	19	AU510002162      	1	20051212	G	3610		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 										RT ENGINE PRESSURE REDUCING VALVE (PRV) SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006062100033	20060621	00033	NM  	2006	6	21	AU510002163      	1	20051212	G	5414	311U2060177	PANEL           			BOEING	747   	74748E      	2FOR   	NM  	GE    	CF6   	CF680C2*    	 	GL  					NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 ENGINE IB STRUT ACCESS PANEL MISSING.						2	L	7	2 	4F	4	F	RT	A20WE   	E23EA				 
2006062100034	20060621	00034	NM  	2006	6	21	AU510002164      	1	20051212	G	2742	6355B000103	MOTOR           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		16380								STABILIZER TRIM MOTOR FAILED.  CIRCUIT BREAKER TRIPPED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006062100035	20060621	00035	CE  	2006	6	21	AU510002165      	1	20051011	G	5551	S346161	BOLT            			CESSNA	208   	208B        	2073701	CE  										HORIZONTAL STAB	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		12084								HORIZONTAL STABILIZER FORWARD LT ATTACHMENT BOLT SHEARED.  AIRCRAFT IS PNG REGISTERED.						1	H	7	1 	3T				A37CE   					 
2006062100036	20060621	00036	NM  	2006	6	21	AU510002166      	1	20051212	G	3810		INSULATION      			BOEING	737   	737*        	       	NM  										HOT WATER LINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										HEATED POTABLE HOT WATER PIPE INSULATION AND ATTACHING CLAMPS HEAT DAMAGED.  SUSPECT WATER IN PIPE IS NOT THERMOSTATICAL	LY CONTROLLED.  PIPE SUPPLIES HOT WATER TO VIP SUITE.  AIRCRAFT IS RAAF VIP.					2	L	7	2 	4F			RT	A16WE   					 
2006062100039	20060621	00039	WP  	2006	6	21	AU510002167      	2	20050711	G	7210	8937396	BULL GEAR       								GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	BROKEN          	W				K				NONE                    				J	O	O	WARNING INDICATION        	OTHER                     	OTHER                     	IN	INSP/MAINT     	1			AU	S 			749  				P36412			CHIP LIGHT ON IN FLIGHT.  STRIP INSPECTION FOUND THAT THE ENGINE BULL GEAR HAD BROKEN TEETH.											4	T			E4WE				 
2006062100041	20060621	00041	GL  	2006	6	21	AU510002168      	1	20050211	G	3246	13889	BEARING         			AMTR  	LANCAR	LC41550FG   	5150001	GL  										WHEEL	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NEW WHEEL BEARING HAD TWO ROLLERS MISSING.  FAULTY MFG.						1	L	7	1 	3O			RT	EXPA1L71					 
2006062100042	20060621	00042	SO  	2006	6	21	AU510002169      	2	20050711	G	8550	633412	SUMP            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	ENGINE	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			690  							OIL DIPSTICK WORE A HOLE IN THE SUMP.  OIL LEAKING.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
2006062100067	20060621	00067	SW  	2006	6	21	AU510002170      	1	20051212	G	3213		SEAL            			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	CYLINDER ASSY	WORN            	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					3251					RT MAIN LANDING GEAR RAM SEALS WORN AND LEAKING.  LOSS OF HYDRAULIC FLUID.						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P25EA	 
2006062300044	20060623	00044	NE  	2006	6	23	AU510002171      	2	20051212	G	7314	PAG102MK1	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL SYSTEM	FAULTY          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		32454	7885 							(AUS) NR 1 ENGINE DRIVEN FUEL PUMP SUSPECT FAULTY.  INVESTIGATION CONTINUING. (CASA NR 510002171)						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006062300081	20060623	00081	EA  	2006	6	23	AU510002172      	2	20051111	G	8550	ES48108	FILTER          			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE OIL	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		27   								(AUS) ENGINE OIL FILTER ELEMENT INCORRECTLY BONDED. CARDBOARD FILTER SEAM WAS ONLY JUST HOLDING TOGETHER. (CASA NR 51000	2172)					1	G	7	1 	3O	3	O		H10WE   	E274				 
2006062300093	20060623	00093	CE  	2006	6	23	AU510002173      	1	20051212	G	2133	47061RX	OUTFLOW VALVE   			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	CABIN PRESSURE	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 		1414 								(AUS) CABIN EMERGENCY PRESSURIZATION VALVE HAD UNCOMMANDED ACTUATION. (CASA NR 510002173)						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2006062300094	20060623	00094	SW  	2006	6	23	AU510002174      	1	20051212	G	6410	47642117105	BLADE           			BELL  	47    	47          	1180602	SW  										TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1581 								(AUS) TAIL ROTOR BLADE CORRODED AND DELAMINATED IN AREA UNDER OB TIP OF ABRASION STRIP. (CASA NR 510002174)						1	G	7	1 	3O				H1      					 
2006062300096	20060623	00096	GL  	2006	6	23	AU510002175      	1	20051210	G	2820	11443005	LINE            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		499  								(AUS) FUEL PIPES LEAKING.  FUEL WAS FOUND TO HAVE BEEN LEAKING FROM THE BLANKED T-FITTINGS THAT WERE INSTALLED IN THE FU	EL SELECTOR TO FIREWALL SUPPLY LINE PN 11443-005 AND THE RETURN LINE PN 11444-005. ON REMOVAL THE FUEL LINES WERE FOUND 	TO HAVE VERY POOR/DAMAGED FLARES AT THE T-FITTING ENDS. FITTINGS ARE INSTALLED AS PART OF THE FERRY TANK INSTALLATION.  	(CASA  NR 510002175)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006062300097	20060623	00097	CE  	2006	6	23	AU510002176      	1	20051212	G	3297		CONNECTOR       			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWN MICROSWITCH WIRE CONNECTOR FAULTY. SUSPECT CONNECTOR WAS NOT AN APPROVED ITEM. (OTHER CA	USE: MAINTENANCE CONTROL ISSUE ) (CASA NR 510002176)					1	L	7	2 	3O	3	O	RT	A25CE   	E7CE	5	C	P45GL	 
2006061600083	20060616	00083	NM  	2006	6	16	AU510002177      	1	20051111	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 										FUSELAGE FRAMES (21OFF) CRACKED AT PASSENGER SERVICE UNIT (PSU) ATTACHMENT POINTS.  FOUND DURING EDDY CURRENT INSPECTION	 IAW EI 737-53-68R3 AND NDT TECHNIQUES E-13 AND E-18.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500070	20060705	00070	NM  	2006	7	5	AU510002178      	1	20051212	G	5414		PANEL           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 ENGINE VIGV ACCESS PANEL MISSING. INVESTIGATION ALSO FOUND THE LP COMPRESSOR ACOUSTIC LINING DAMAGED AT THE 6	 O`CLOCK POSITION WITH A HOLE APPROXIMATELY 150MM BY 100MM (6IN BY 4IN) IN THE SKIN. VIGV CONTROLLER PANEL SUPPORT STRUC	TURE ALSO DAMAGED. (CASA NR 510002178)				2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2006070500071	20060705	00071	NM  	2006	7	5	AU510002179      	1	20051212	G	5414	UL27562	FAIRING         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE UPPER LT (A) FRAME FAIRINGS PN UL27562 AND PN UL27561 DAMAGED/MISSING.  UPPER HALF DAMAGED AND LOWER H	ALF MISSING. (CASA NR 510002179)					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2006070500072	20060705	00072	EA  	2006	7	5	AU510002180      	2	20051212	G	7322	242528	VALVE           								LYC   	O540  	O540E4C5    	41532	EA  					CARBURETOR	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURRETOR MIXTURE VALVE FAULTY MANUFACTURE.  INSPECTION FOUND THE BRASS VALVE END OF THE MIXTURE VALVE ASSEMBLY 	HAD NOT BEEN CORRECTLY SWAGED CAUSING THE BRASS END TO TURN ON THE CABLE. (CASA NR 510002180)										3	O			E295				 
2006070300012	20060703	00012	CE  	2006	7	3	AU510002181      	1	20051212	G	2150	73838416	ACM             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  						FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 		6911 								AIR CYCLE MACHINE (ACM) FAILED AND EMERGENCY PRESSURISATION VALVE AUTOMATICALLY OPENED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006070500073	20060705	00073	NE  	2006	7	5	AU510002182      	2	20051212	G	7321		METERING VALVE  	HONEYWELL   		BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					HMU	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					BECW3455					(AUS) NR 2 ENGINE HYDROMECHANICAL UNIT (HMU) FUEL METERING VALVE FAULTY. (CASA NR 510002182)						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500074	20060705	00074	GL  	2006	7	5	AU510002183      	1	20051212	G	2820	11443005	LINE            			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUEL SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		498  								(AUS) FUEL PIPES PN 11443-005 AND PN 11444-005 CRACKED/DAMAGED ON FLARES AT THE (T) FITTING ENDS. SWARF WAS ALSO FOUND O	N THE FLARES.  (CASA NR 510002183)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
2006070300013	20060703	00013	NM  	2006	7	3	AU510002184      	1	20051111	G	5310		DOOR FRAME      			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FORWARD CARGO DOOR CUTOUT AFT FRAME WEB CRACKED.  CRACK LENGTH APPROXIMATELY 17.78MM (0.700IN).  FOUND DURING EDDY CURRE	NT INSPECTION IAW AD/737/242 AND BOEING SB 737-53A1228.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300014	20060703	00014	NM  	2006	7	3	AU510002185      	1	20051212	G	2824	737M28500011	VALVE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					NR 2 ENGINE	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		52514	14042							NR 2 ENGINE SPAR VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300015	20060703	00015	NM  	2006	7	3	AU510002186      	1	20051212	G	3411	BACT16AS060406D	TEE FITTING     			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D7       	52053	NE  					AIRSPEED PITOT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										AIRSPEED SWITCH PITOT TEE FITTING CRACKED AND LEAKING ON SMALL DIAMETER END.						2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006070300086	20060703	00086	EA  	2006	7	3	AU510002187      	1	20051212	G	6100	AS3217146	RETAINING RING  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					PROPELLER SHAFT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ENGINE PROPELLER SHAFT ADAPTER PLUG RETAINING RING MISSING.  ADAPTER PLUG P/N 3013146 DISLODGED AND LOOSE IN THE PROPELL	ER SHAFT INTERNAL BORE.  RETAINING RING COULD NOT BE FOUND.  SUSPECT RETAINING RING HAD NOT BEEN INSTALLED.  PERSONNEL/M	AINTENANCE ERROR.  AIRCRAFT IS REGISTERED IN PNG.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006070300087	20060703	00087	SO  	2006	7	3	AU510002188      	2	20051212	G	8520	536379	BOLT            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	CRANKSHAFT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			936  							CRANKSHAFT GEAR RETAINING BOLTS SHEARED.  LOSS OF DRIVE TO GOVERNOR.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
2006070300088	20060703	00088	NM  	2006	7	3	AU510002189      	1	20051212	G	2421		IDG             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AC GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT ENGINE INTEGRATED DRIVE GENERATOR (IDG) FAILED.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006070300089	20060703	00089	NM  	2006	7	3	AU510002190      	1	20051212	G	5410		FAIRING         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					NR 3 NACELLE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										NR 3 ENGINE LOWER RT COMPRESSOR FAIRING DAMAGED WITH A PIECE MISSING.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2006070300090	20060703	00090	NM  	2006	7	3	AU510002191      	1	20051212	G	2750		FSEU            			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					TE FLAP CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										TRAILING EDGE FLAP ASYMMETRY MESSAGE.  FLAP/SLAT ELECTRONIC UNIT (FSEU) RERACKED AND MESSAGE CLEARED.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2006070300091	20060703	00091	NM  	2006	7	3	AU510002192      	1	20051212	G	3350		BATTERY         			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					EMERGENCY LIGHT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										DOOR 5 CREW REST CEILING EMERGENCY LIGHTING PACK DAMAGED.  EVIDENCE OF FIRE TO THE UNIT AND DAMAGE TO THE SURROUNDING AR	EA.					2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2006070300092	20060703	00092	NM  	2006	7	3	AU510002193      	1	20051212	G	5313		STRINGER        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FUSELAGE STRINGER SPLICE CRACKED.  CRACK LENGTH APPROXIMATELY 5MM (0.200IN). UPON REMOVAL OF THE SPLICE THERE WAS EVIDEN	CE OF MULTI-SITE CRACKING ON OUTBOARD SURFACE OF SPLICE (TWO HOLES).  FOUND DURING EDDY CURRENT INSPECTION OF FUSELAGE U	PPER LOBE FASTENER HOLE LOCATED AT STRINGER 4L, BS 907.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300093	20060703	00093	NE  	2006	7	3	AU510002194      	2	20051212	G	7230	3400010260	FAN BLADE       			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					ENGINE	BIRD STRIKE     	W				A				UNSCHED LANDING         				C	E	J	F.O.D.                    	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										NR 2 ENGINE FAN BLADES (4OFF) DAMAGED BY BIRDSTRIKE.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006070300094	20060703	00094	NM  	2006	7	3	AU510002195      	1	20051212	G	5330		SKIN            			BOEING	737   	737300      	1384610	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										FUSELAGE SKIN TORN ACROSS RIVET ON STRINGER 39L FRAME 1197 AND 132 LOCATED JUST OUTBOARD OF PREVIOUS PATCH.  A SLIGHT BU	LGE IN THE SKIN WAS NOTED.					2	L	7	2 	4F	4	F	RT	A16WE   	E12EU				 
2006070500165	20060705	00165	NM  	2006	7	5	AU510002196      	1	20051212	G	4900	762904E	APU             			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  						FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			AU	S 										(AUS) APU AUXILIARY POWER CONVERSION AND DISTRIBUTION UNIT FAILED. SEE ATTACHMENT FOR INVESTIGATION DETAILS.(OTHER CAUSE	: AGE ) (CASA NR 510002196)					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2006070500166	20060705	00166	SW  	2006	7	5	AU510002198      	1	20051212	G	3230	NAS660421	BOLT            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR UPLOCK ROLLER BOLT SHEARED. (CASA NR 510002198)						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006070500167	20060705	00167	SW  	2006	7	5	AU510002199      	1	20051212	G	2910	2781032777	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	WORN            	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) HYDRAULIC PIPES LOCATED IN LT ENGINE BAY CHAFING TOGETHER. ONE PIPE WORN THROUGH AND LEAKING. LOSS OF HYDRAULIC FL	UID. (CASA NR 510002199)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006070500168	20060705	00168	EU  	2006	7	5	AU510002200      	1	20051212	G	7810		EXHAUST PIPE    			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT ENGINE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APPROXIMATELY 457.2MM (18IN) OF LT ENGINE RT TAILPIPE BANK AND CLAMP MISSING. FURTHER INVESTIGATION ALSO FOUND CRA	CKING ON NR 3 AND NR 5 CYLINDER EXHAUST RISERS.  ENGINE LOWER COWL ALSO SUFFERED SCORCHING DAMAGE. (CASA NR 510002200)					1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
2006070500169	20060705	00169	EU  	2006	7	5	AU510002201      	1	20051212	G	3230	683702	VALVE           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	MLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		23403								(AUS) LANDING GEAR EMERGENCY UPLOCK VALVE SEIZED. (OTHER CAUSE: INDETERMINABLE ) (CASA NR 510002201)						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2006070500171	20060705	00171	CE  	2006	7	5	AU510002202      	1	20051212	G	3233	A2176B	PLUG            	GARKENYON   		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	NLG ACTUATOR	CRACKED         	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 		867  			222					(AUS) NOSE LANDING GEAR ACTUATOR END PLUG CRACKED IN AREA OF SPANNER FLATS. LOSS OF HYDRAULIC FLUID. (CASA NR 510002202)						1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2006070500172	20060705	00172	EU  	2006	7	5	AU510002203      	1	20050212	G	2910		CLAMP           			BAG   	JETSTM	JETSTM3107  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	HYDRAULIC SYS	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 		32594								(AUS) HYDRAULIC PIPES PN 1379007D441 AND PN 1379007D443 LOCATED IN LT WING LEADING EDGE RUBBING TOGETHER DUE TO A BROKEN	 CLAMP.  ONE PIPE WAS WORN THROUGH. LOSS OF HYDRAULIC FLUID. (OTHER CAUSE: BROKEN CLAMP ) (CASA NR 510002203)					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2006070500174	20060705	00174	CE  	2006	7	5	AU510002204      	1	20050212	G	3230	574122214	UPLOCK HOOK     			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LANDING GEAR	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AU	S 		17180								(AUS) RT MAIN LANDING GEAR UPLOCK HOOK CRACKED. (CASA NR 510002204)						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2006071000086	20060710	00086	EU  	2006	7	10	AU510002205      	1	20051212	G	3230	SA7670006127	HOSE            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										NOSE LANDING GEAR RETRACTION ACTUATOR FLEXIBLE HYDRAULIC HOSE RUPTURED.  LOSS OF GREEN SYSTEM HYDRAULIC FLUID.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2006070500370	20060705	00370	NM  	2006	7	5	AU510002206      	1	20050112	G	3244	DR29620T	TIRE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										NR 2 MAIN WHEEL TIRE TREAD SEPARATED.  TIRE WAS RETREAD LEVEL R2.  DAMAGE WAS CAUSED TO THE LT INBOARD TRAILING EDGE FLA	P AND LT INBOARD LOWER WING FIXED TRAILING EDGE PANEL.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100124	20060711	00124	NM  	2006	7	11	AU510002207      	1	20051212	G	3230	DSC252B40124	HOSE            			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 HYD SYS	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 		10711								NOSE LANDING GEAR DRAG STRUT RETRACTION ACTUATOR FLEXIBLE HOSE RUPTURED.  LOSS OF NR 2 HYDRAULIC SYSTEM FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006071100125	20060711	00125		2006	7	11	AU510002208      	4	20051212	G	2310		RADIO           			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HF SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										BOTH HF RADIO SYSTEMS FAILED TO TUNE.  A WEAK BACKGROUND HASH COULD BE HEARD ON NR 2 HF SYSTEM ONLY.  INVESTIGATION CONT	INUING.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100126	20060711	00126		2006	7	11	AU510002209      	4	20051212	G	3442	8221710001	TRANSCEIVER     			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					WX RADAR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										WEATHER RADAR TRANSCEIVER FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100127	20060711	00127	NM  	2006	7	11	AU510002210      	1	20051212	G	2913	887477	PUMP            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					HYDRAULIC SYS	FAILED          	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			AU	S 										HYDRAULIC PUMP FAILED.  CIRCUIT BREAKER TRIPPED AND PUMP ELECTRIC MOTOR HAD A BURNED ODOR.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006071100128	20060711	00128	SO  	2006	7	11	AU510002211      	2	20050311	G	8520	SA642720	BEARING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1429 								CRANKSHAFT NR 2 MAIN BEARING SHELL PROTRUDING MORE THAN NORMAL OUTSIDE OF THE CRANKCASE SADDLE.  WHEN THE ENGINE WAS STR	IPPED DOWN THE NR 2 BEARING SHELL LOCATED IN THE LT CRANKCASE FELL APART INTO AT LEAST FIVE PIECES.  DAMAGE TO THE CRANK	CASE WAS ALSO FOUND DUE TO THE FORE AND AFT MOVEMENT OF THE BEARING.  SEVERE WEAR IN THE TANG LOCATING AREA.				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006071100129	20060711	00129	SO  	2006	7	11	AU510002212      	2	20051212	G	8520	631716	CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1429 							CRANKSHAFT DAMAGED.  MAGNETIC PARTICLE INSPECTION OF CRANKSHAFT FOLLOWING NR 2 MAIN BEARING FAILURE (SEE SDR510002211) F	OUND INDICATIONS OF HEAT CRACKS ON THE RADIUS OF NR 2 MAIN JOURNAL.  CRANKSHAFT WAS REJECTED.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006071100130	20060711	00130	CE  	2006	7	11	AU510002213      	1	20051212	G	8011	643109	SPRING          	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					STARTER ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 		1044 								STARTER ADAPTER SPRING BROKEN IN HALF.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006071100131	20060711	00131	NE  	2006	7	11	AU510002214      	2	20051212	G	7314	5008269H	PUMP            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	FUEL	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			AU	S 		3390 	3390 							NR 2 ENGINE DRIVEN FUEL PUMP INPUT SHAFT SHEARED.  FUEL PUMP COULD TURN FREELY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070300098	20060703	00098	NM  	2006	7	3	AU510002215      	1	20050212	G	2700	65448616	ACTUATOR        			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D7       	52053	NE  					FLIGHT CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										ACTUATOR LOCATED IN LT WING LEAKING.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006070300099	20060703	00099	NM  	2006	7	3	AU510002216      	1	20050312	G	2150		A/C PACK        			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM56*      	13802	NE  						CONTAMINATED    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										STRONG OIL SMELL IN COCKPIT AND CABIN.  INVESTIGATION FOUND OIL CONTAMINATION OF THE AIR CONDITIONING AND PNEUMATIC SYST	EMS.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006070300100	20060703	00100	NM  	2006	7	3	AU510002217      	1	20050212	G	2781		WARNING MESSAGE 			BOEING	767   	767277      	1385128	NM  	GE    	CF6   	CF680A      	30025	NE  					SLAT	ACTIVATED       	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										SLAT ASYMMETRY WARNING.  INVESTIGATION CONTINUING.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006060800131	20060608	00131	NM  	2006	6	8	AU510002218      	1	20050412	G	5610		WINDSHIELD      			BOEING	777   	777         	UTILUSE	NM  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										CAPTAIN`S WINDSCREEN CRACKED.  AIRCRAFT IS REGISTERED IN NEW ZEALAND.						2	L	7	2 	4F			RT	T00001SE					 
2006060800132	20060608	00132	EU  	2006	6	8	AU510002219      	1	20050512	G	2730		CONTROL SYSTEM  			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ELEVATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										ELEVATOR CONTROL SYSTEM MESSAGE ON MULTI FUNCTION DISPLAY UNIT (MFDU).						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006060800133	20060608	00133	EU  	2006	6	8	AU510002220      	1	20051212	G	3610	6730010000	VALVE           			AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					PNEUMATIC SYS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 		4787 								NR 2 ENGINE BLEED SYSTEM FAN AIR VALVE SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2006060800135	20060608	00135	WP  	2006	6	8	AU510002221      	2	20050812	G	7310	8945682	LINE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE3312     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENG FUEL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										LT ENGINE FUEL PIPE LOCATED BETWEEN THE START PRESSURE REGULATOR AND THE FUEL FLOW TRANSMITTER CRACKED AND LEAKING.						2	L	7	2 	4T	3	T	RT	A5SW    	E3WE	6	C	3PNE	 
2006060800137	20060608	00137	NM  	2006	6	8	AU510002222      	1	20050712	G	2150	1828203	HEAT EXCHANGER  			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					A/C PACK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										RT AIR CONDITIONING PACK HEAT EXCHANGER CRACKED AND LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005122800220	20051228	00220	NM  	2005	12	28	AUCR200500001    	1	20051201	G	5730	9255011	PANEL           			LKHEED	P3A   	P3A         	5260103	NM  	ALLSN 	T56   	T56A10      	03004	GL  					LT WING	CRACKED         	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	917AU	15178				150510				LOCATED LOWER WING PLANK RISER FRACTURE 7 INCHES IN LENGTH LT WING STA. 167. FRACTURE EMANATED ALONG BASE OF RISER EXTEN	DING IB AND OB SPANWISE. FRACTURE WAS VISUALLY DETECTED DURING SCHEDULED INSPECTION. FRACTURE WAS PROPAGATED BY THE MAIN	 LANDING GEAR TRUSS RIB ATTACHING STIFFENER AT THE FORWARD SPAR ATTACHMENT. MANUFACTURING PROCESSES ENTAILED THE VERTICA	L LEG TO BE CUT BACK AT THE RISER INTERSECTION; FAILURE TO DO SO ENCROACHED THE RISER AT THE VERTICAL STIFFENER PRELOADI	NG THE NR 1 RISER. THIS INCIDENT IS TO BE CONSIDERED AN ISOLATED MFG PROCESS FAILURE. SPECIFICATIONS CLEARLY SHOW THE ST	IFFENER TO BE TRIMMED AT THE INTERFACE WITH THE RISER.	2	L	7	4 	4T	4	T	RT	A32NM   	E282				 
2005122800223	20051228	00223	NM  	2005	12	28	AUCR200500002    	1	20051201	G	5711	9010622	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										LT WING	CORRODED        	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	917AU	15178				150510				LT WING UPPER REAR SPAR CAP WS178, AT NACELLE AFT ATTACH PLATE. DISSIMILAR METAL CORROSION ATTACK UPPER CROWN AND VERTIC	AL LEG. CORROSION WAS VISUALLY DETECTED AT DEPOT LEVEL SCHEDULED INSPECTION.  CORROSION WAS FOUND TO EXCEED NEGLIGIBLE D	AMAGE LIMITS.				2	L	7	4 	4T			RT	A32NM   					 
2005122800224	20051228	00224	NM  	2005	12	28	AUCR200500003    	1	20051201	G	5711	9010622	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	CORRODED        	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	917AU	15178				150510				RT WING REAR SPAR UPPER CAP WS178 AT NACELLE AFT ATTACH PLATE. DISSIMILAR METAL CORROSION ATTACKING UPPER CROWN AND AND 	VETICAL LEG OF THE SPAR CAP. CORROSION WAS VISUALLY DETECTED AT SCHEDULED DEPOT LEVEL INSPECTION. CORROSION EXCEEDED MAX	IMUM NEGLIGIBLE LIMITS.				2	L	7	4 	4T			RT	A32NM   					 
2005122700209	20051227	00209	NM  	2005	12	27	AUCR200500004    	1	20051201	G	5711	9010552	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	CORRODED        	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	917AU	15178				150510				RT WING UPPER FORWARD SPAR CAP W.S.73 (PREVIOUS PROCESSING BY PARTY UNKNOWN) OF THE FORWARD FLANGE HAS EXCEEDED MAXIMUM 	NEGLIGIBLE LIMITS FOR DAMAGE LOCATION. DUE TO THE RELATIVE LOCATION OF THE WING ATTACH CORNER FITTING THIS DAMAGE CANNOT	 BE REPAIRED AND WILL REQUIRE A SPAR CAP INSERTION.				2	L	7	4 	4T			RT	A32NM   					 
2006010500186	20060105	00186	NM  	2006	1	5	AUCR200500005    	1	20051202	G	5730	9006072	SKIN PANEL      			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	CORRODED        	B			NASA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	25	426NA	18057				152735				RT WING LOWER SKIN PANEL NR 7 AT BUTT LINE 65 INTERNAL INTERGRANULAR CORROSION. THE DEFECTIVE PANEL WAS FIRST DETECTED B	Y A FUEL LEAK AT BUTT LINE 65. FURTHER INVESTIGATION REVEALED EXFOLIATION FROM INTERGRANULAR CORROSION. THE CORROSION WA	S CONCEALED BY LAYERS OF FUEL TANK BARRIER SEALANT.				2	L	7	4 	4T			RT	A32NM   					 
2005031000089	20050310	00089	CE  	2005	3	10	B30R20050105     	1	20050103	G	2731	511523128	ACTUATOR        			CESSNA	500   	550         	2076604	CE  										ELEVATOR TRIM	MALFUNCTIONED   	B			B30R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26496					5500607				DURING PREFLIGHT OF AIRCRAFT, PILOT HEARD A NOISE IN WHILE OPERATING  ELEVATOR ELECTRIC TRIM.  TROUBLESHOOTING REVEALED 	THAT THE TRIM CABLES IN THE ELEVATOR ELECTRIC TRIM ACTUATOR HAD CROSSED.  A REPLACEMENT ELECTRIC TRIM ACTUATOR WAS ORDER	ED.  UPON RECEIPT OF THE ACTUATOR IT WAS DISCOVERED THAT ONE OF THE CABLES HAD BEEN BENT OVER AND PINCHED.  FURTHER INSP	ECTION REVEALED A BROKEN WIRE IN THE CABLE AT THE PINCHED AREA.  THE ACTUATOR WAS RETURNED TO THE VENDOR AS UNSERVICABLE	, AND ANOTHER ORDERED.		1	L	7	2 	4F				A22CE   					 
2005041100203	20050411	00203	CE  	2005	4	11	B30R20050405     	1	20050204	G	3240	302	MOTOR           	ELECTROMECH 		CESSNA	500   	550         	2076604	CE  										POWER PACK	INOPERATIVE     	B			B30R	D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	03	26496				NA	5500607				AFTER LANDING DURING TAXI BACK TO THE RAMP, PILOT EXPERIENCED POWER BRAKE FAILURE.  WAS ABLE TO CONTROL THE AIRCRAFT AND	 RETURN IT TO THE PARKING RAMP SAFELY.  MECHANIC'S TROUBLESHOOTING REVEALED THAT THE POWER PACK PUMP MOTOR HAD FAILED.  	THE POWER PACK ASSEMBLY WAS REMOVED AND THE MOTOR WAS REPLACED.  THE POWER PACK ASSEMBLY WAS REINSTALLED AND THE BRAKE S	YSTEM WAS BLED.  BRAKE SYSTEM RESUMED NORMAL OPERATION.  THE AIRCRAFT WAS RELEASED FROM MAINTENANCE AND RETURNED TO SERV	ICE.		1	L	7	2 	4F				A22CE   					 
2005031000091	20050310	00091	CE  	2005	3	10	B3OR20050105     	1	20050104	G	2731	511523128	TRIM MOTOR      			CESSNA	500   	550         	2076604	CE  										ELEVATOR	JAMMED          	B			B3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	26496					5500607				AIRCRAFT WAS AOG FOR ELEVATOR ELECTRIC TRIM ACTUATOR. WHEN PART WAS RECIEVED FROM VENDOR IT WAS DISCOVERED THAT THE AFT 	TRIM CABLE WAS ROUTED BETWEEN THE CABLE DRUM AND THE CLUTCH ASSEMBLY JAMMING THE CLUTCH ASSEMBLY. THE CABLE DRUM CLUTCH 	COULD NOT DISENGAGE TO ALLOW ROTATION OF THE CABLE DRUM. DUE TO THE JAMMED CONDITION OF CLUTCH ASSEMBLY, THE PART COULD 	NOT BE USED AND A REPLACEMENT WAS ORDERED. THE TRIM ACTUATOR S/N:0313-28, WAS AN OVERHAULED UNIT AND THE WORK WAS DONE B	Y CESSNA.		1	L	7	2 	4F				A22CE   					 
2005031000092	20050310	00092	CE  	2005	3	10	B3OR20050205     	1	20050104	G	2731	511523128	TRIM MOTOR      			CESSNA	500   	550         	2076604	CE  										ELEVATOR	JAMMED          	B			B3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	26496					5500607				AIRCRAFT WAS AOG FOR ELEVATOR ELECTRIC TRIM ACTUATOR. WHEN PART WAS RECIEVED FROM VENDOR IT WAS DISCOVERED THAT THE AFT 	TRIM CABLE WAS ROUTED BETWEEN THE CABLE DRUM AND THE CLUTCH ASSEMBLY JAMMING THE CLUTCH ASSEMBLY. THE CABLE DRUM CLUTCH 	COULD NOT DISENGAGE TO ALLOW ROTATION OF THE CABLE DRUM. DUE TO THE JAMMED CONDITION OF CLUTCH ASSEMBLY, THE PART COULD 	NOT BE USED AND A REPLACEMENT WAS ORDERED. THE TRIM ACTUATOR S/N:0313-28, WAS AN OVERHAULED UNIT AND THE WORK WAS DONE B	Y CESSNA.		1	L	7	2 	4F				A22CE   					 
2005050400100	20050504	00100		2005	5	4	B3OR20050505     	4	20050413	G	6113	1250419K200	SPINNER         			CESSNA	210   	210N        	2073453	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER	CRACKED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5515Y	5239 	35   			21064233	289125R	941015		PROPELLER SPINNER WAS INSPECTED DURING A PRE-FLIGHT INSPECTION AND FOUND TO HAVE A CRACK. THE CRACK WAS FROM A SCREW HOL	E AND EXTENDED TO BLADE CUT-OUT. THE SPINNER WAS REPLACED AND INSPECTED AFTER ITS FIRST FLIGHT, NO CRACKS WERE FOUND OR 	NOTED ON THE REPLACED SPINNER. SUSPECT OVER TORQUEING OF SPINNER ATTACH SCREWS AS CAUSE OF CRACK				1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P47GL	 
2005061500139	20050615	00139	CE  	2005	6	15	B3OR20050614     	1	20050613	G	3240		PUMP            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKES	SEIZED          	B			B3OR	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SW	03	26496					5500607				DURING APPROACH, WHILE LOWERING GEAR, PILOT IN COMMAND NOTICED "ANTI SKID INOP" LIGHT ILLUMINATED. PILOTS FOLLOWED EMERG	ENCY CHECKLIST PROCEDURES & MADE AN UNEVENTFUL LANDING AT HOME FIED. HOWEVER, EMERGENCY BRAKE SYS HAD TO BE USED TO BRIN	G ACFT TO A STOP. MX STARTED TROUBLESHOOTING PROCEDURES & DISCOVERED POWER BRAKE PUMP SEIZED, CAUSING MOTOR TO TRIP CIRC	UIT BREAKER. MOTOR ITSELF TESTED ON A BENCH & FOUND TO BE WORKING IAW MM. AT TIME OF WRITING, POWER BRAKE PUMP AND MOTOR	 ASSY HAVE BEEN SENT OUT FOR REPAIR/OVERHAUL. SINCE CESSNA DOES NOT HAVE A TBO ON EITHER THE MOTOR OR THE PUMP, IT IS SU	GGESTED THAT A TBO OF 500 TO 600 LANDINGS BE APPLIED TO THESE COMPONENTS.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005071200135	20050712	00135	SO  	2005	7	12	B3OR20050627     	2	20050627	G	7310	6464336P	MANIFOLD        			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	TSIO520*    	17040	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUEL SYSTEM	CONTAMINATED    	B			B3OR	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SW	03	6621A					21063559	821022R	FP1513B		TAXI, ENG RUNS ROUGH.  FUEL INJECTOR LINES DISCONNECTED, NR 5 CYL FUEL INJECTOR NOT FLOWING CORRECTLY.  PROBLEM FUEL DIS	TRIBUTOR MANIFOLD OR SPIDER.  FILTER SCREEN IN SPIDER REMOVED, 9 PARTICLES FOUND.  LARGEST 7CM LONG & 1MM WIDE.  MANIFOL	D DISASSEMBLED & 2 PARTICLES FOUND NEAR OUTLET NR 5 CYL.  LARGEST 1CM WIDE BY 1CM LONG.  TWO PARTICLES HAD GOTTEN PAST F	ILTER SCREEN.  AFTER FILTER SCREEN & DISTRIBUTION MANIFOLD CLEANED & REASSEMBLED.  FLOW PATTERN NR 5 CYL NORMAL.  FUEL S	CREEN ON FUEL DISTRIBUTION MANIFOLD IS NOT LISTED FOR PERIODIC INSP OR CLEANING.  ENG HAS INTERMITTENT PROBLEM OF ROUGH 	RUNNING, 1ST TIME INDICATION OF DEBRIS IN FUEL DISTRIBUTION MANIFOLD.  IO550P OPERATORS SHOULD BE MADE AWARE OF PROBLEM.	1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P36EA	 
2005072000109	20050720	00109	CE  	2005	7	20	B3OR20050718     	1	20050718	G	7160	646205	INTAKE PIPE     			CESSNA	210   	210N        	2073453	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	NR 4 CYLINDER	CRACKED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6621A	934  	934  			21063559	821022R	FP1513B		WHILE REMOVING LT MAGNETO FOR TBO, THE NR 4 CYLINDER INTAKE PIPE HAD TO BE REMOVED FOR ACCESS TO THE MAGNETO. REMOVAL OF	 THE INTAKE PIPE REVEALED THAT THE INTAKE PIPE HAD A CRACK IN THE FLARE END THAT IS SECURED TO THE CYLINDER INTAKE PORT.	 FURTHER INVESTIGATION REVEALED THAT THE NR 4 INTAKE PIPE WAS THE ONLY PIPE FOUND IN THIS CONDITION. THIS ENGINE HAD AN 	INTERMITTENT PROBLEM OF RUNNING ROUGH FOR A FEW MOMENTS THEN BACK TO RUNNING NORMALLY. ALL IO-550P OPERATORS SHOULD BE M	ADE AWARE OF THIS PROBLEM.		1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P36EA	 
2005102700134	20051027	00134	CE  	2005	10	27	BG001            	1	20051006	G	2910	S217840102	LINE            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540*       	41532	EA  					HYDRAULIC SYS	FAILED          	G				B				EMER. DESCENT           				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			SW	09	2426S					R18201339				DOWN HYDRAULIC PRESSURE LINE FAILED AT ACTUATOR.  LINE PULLED OUT OF SWAGED END FITTING.						1	H	7	1 	3O	3	O		3A13    	E295				 
2005120200146	20051202	00146	SO  	2005	12	2	BNG0002          	1	20051106	G	2460	PS5012012	CIRCUIT BREAKER 			PIPER 	PA28  	PA28RT201   	7102818	SO  										UNKNOWN	FAILED          	G				O				OTHER                   				S			AFFECT SYSTEMS            			LD	LANDING        	1			SW	09	3023K					28R7918022				CIRCUIT BREAKER FAILED.						1	L	7	1 	3O				2A13    					 
2005042500038	20050425	00038	WP  	2005	4	25	CA050103002      	1	20050102	G	8012	39279621	START VALVE     			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 1 ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) NR 1 ENGINE, THE LT START VALVEOPEN LIGHT CAME ON IN CLIMB. THE AIRCRAFT LEVELED OFF, WHEN THE POWER REDUCED, THE 	LIGHT WENT OUT. WHEN CLIMB POWER INITIATED AGAIN, THE LIGHT CAME BACK ON. THE AIRCRAFT CAME BACK TO PLACE OF DEPARTURE. 	THE AIRCRAFT WAS RELEASED UNDER MEL 80-1.2. THE  STARTER VALVE (PN ON OFF, 392796-2-1, SN OFF 3938, SN ON 3624) WAS LATE	R REPLACED IAW AMM 80-10-02. OPERATIONAL CHECK C/OUT PER AMM 71-00-00.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500039	20050425	00039	EU  	2005	4	25	CA050104001      	1	20050103	G	2910		PACKING         		RV99199     	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					THERMAL RELIEF	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA						1011927					(CAN) HYDRAULIC SYSTEM NR 1 FAILED IN FLT (AFTER TAKE OFF), LOW QUANTITY. THE FLIGHT CREW DECLARED AN EMERGENCY AND RETU	RNED TO PLACE OF DEPARTURE. MAINTENANCE FOUND THAT THE HYDRAULIC SYSTEM FAILURE WAS CAUSED BY A PACKING FAILURE OF THE T	HERMAL RELIEF VALVE ON THE PRESSURE MANIFOLD ASSY, THE VALVE WAS REPLACED (PN OFF ON: RV99-199, SN OFF 1011927, SN ON 04	-0916528) IAW AMM 32-44-13. THE SYSTEM WAS REPLENISHED AND TESTED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042500040	20050425	00040	NE  	2005	4	25	CA050104002      	2	20050104	G	7310	3033736	LINE            								PWA   	PT6   	PT6A42      	52043	NE  					FUEL SYSTEM	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING VISUAL INSPECTION AT PWC, WE HAVE IDENTIFIED THAT ONE FUEL PRESSURE HOSE WAS NOT GENUINE BUT WAS FITTED TO 	THE ENGINE S/N 42372 WHERE THE HOSE P/N 3033736 SHOULD BE FITTED. THIS HOSE IS BUILT IN 3 PIECES, A FLEXIBLE STEEL HOSE 	COVERED WITH AN ORANGE RUBBER HOSE WHICH IS CONNECTED AT EACH END WITH A FEMALE 90 DEG. CONNECTOR. THE PART ITSELF IS ID	ENTIFIED AS LEAVENS 10-943 LAM, 090 E4181G0070, AICOI PT BEB01, TEFLON 3 008SI, TSO 075A TYPE D NOC PART WAS REMOVED FRO	M THE ENGINE AND WILL BE KEPT IN QUARANTINE FOR 21 DAYS BEFORE BEING MUTILATED. THIS IS THE SECOND OCCURENCE IN THE PAST	 MONTH.						4	T			E4EA				 
2005031400053	20050314	00053	NE  	2005	3	14	CA050105005      	1	20050104	G	7810		EXHAUST DUCT    			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 2 EGINE	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE890793S			(CAN) PILOT REPORTED, NO N2 INDICATION FOR NR 2 ENGINE. UPON INSPECTION, WHEN N2 PICKUP WAS REMOVED FROM THE ACCY GEARBO	X, IT WAS OBSERVED THAT THE NR 5 BEARING NUT HAD BACKED OFF ON THE PT OUTER SHAFT TRAVELING AWAY FROM THE N2 PICKUP, HEN	CE 'NO N2 INDICATION'.  IT WAS OBSERVED THAT THE 12 O'CLOCK MOUNTING STRUT ON THE EXHAUST COLLECTOR HAS DEVELOPED SEVERA	L CRACKS. THE LOCK WASHER APPEARED TO HAVE BEEN DEFORMED IN TWO PLACES AT SOME POINT AND TIME, HOWEVER, THE DEFORMATIONS	 WERE EITHER WERE NOT SUFFICIENT TO PREVENT THE NR 5 NUT FROM BACKING OFF, OR THE NUT HAS NOT BEEN TORQUED CORRECTLY TO 	BEGIN WITH. TURBINE HAS BEEN REPLACED AND TEARDOWN REPORT REQUESTED FROM THE AUTHORIZED MAINTENANCE CENTER.	1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005031400031	20050314	00031	EU  	2005	3	14	CA050105009      	1	20050105	G	2435	524321215	GENERATOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2	DIRTY           	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, GEN 2 TRIPPED OFF LINE. PILOT TRIED TO RESET WITH NO SUCCESS, AND THEN RETURNED TO BASE.  IN	VESTIGATION REVEALED THE ARMATURE TO BE VERY DIRTY.   ARMATURE CLEANED, AIRCRAFT GROUND RUN AND FUNCTION TEST PREFORMED 	SATISFACTORY.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005042500043	20050425	00043	SO  	2005	4	25	CA050105014      	1	20050105	G	2800	5379700	ADAPTER         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL CAP	INCORRECT       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE INNER RING ON THE FUEL CAP HOUSING IS HELD IN PLACE BY LOCKING TABS. THE FUEL CAP LOCKS ONTO THIS RING. THE LO	CKING TABS THAT HOLD THE RING IN PLACE SLOWLY, OVER TIME OF CONSTANT USE RELEASED THE RING TO LET THE CAP COME OUT OF TH	E HOUSING.  CHECKING OUR OTHER A/C AND THE PILOTS HAVE ALL BEEN INFORMED ON HOW TO DETERMINE IF THERE IS A PROBLEM WITH 	THE CAP. MAINTENANCE ALSO IS PAINTING LINES ON THE CAP AND HOLDER TO SHOW A VISIBLE INDICATION OF THE CAP NOT BEING IN T	HE PROPER PLACE.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005032400037	20050324	00037	SW  	2005	3	24	CA050105015      	1	20050104	G	7920	8941172	ADAPTER         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					OIL FILTER	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J	Y	FLUID LOSS                	WARNING INDICATION        	ENGINE STOPPAGE           	CR	CRUISE         	1			CA								P54108			DURING CRUISE, RT ENG OIL PRESS WARNING LIGHT ILLUM ON ANNUNCIATOR.  UPON LOOKING AT RT OIL PRESS IND FLT CREW NOTICED O	IL PRESS DECREASING THROUGH 40 PSI.  CREW ELECTED TO SHUTDOWN RT ENG AS A PRECAUTION.  A/C CONTINUED IT'S FLIGHT TO YWG 	WHERE IS LANDED W/O FURTHER INCIDENT WITH EMERGENCY SERVICES STANDING BY.  UPON INSPECTION BY MX OF RT ENG, OIL FILTER H	OUSING ADAPTER FOUND CRACKED AT MOUNTING FLANGE WHICH PROPAGATED TO ADAPTERS O-RING GROOVE, WHICH CAUSED LOSS OF OIL.  3	 OF 8 US QUARTS OF ENGINE OIL SYS LOST DUE TO LEAKING ADAPTER.  ENG OIL PRESS ONLY DROPPED TO 40 PSI BEFORE ENG SHUTDOWN	.  OIL FILTER ADAPTER CHANGED & LEAK CHECKS PERFORMED.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005032400038	20050324	00038	SO  	2005	3	24	CA050106001      	1	20050105	G	5753	CB17663	BEARING         			LKHEED	282   	C130A       	5262502	SO  										FLAP CARRIAGE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											TECHS FOUND DIFFICULTY WHILE ATTEMPING TO GREASE NEWLY INSTALLED FLAP CARRIAGE BEARINGS.  BEARINGS WOULD NOT ACCEPT GREA	SE AS DIRECTED BY THE MM.  A RECALL & INSPECT OF ALL INVENTORIED BEARINGS CARRIED OUT AT SPAR QUALITY DEPARTMENT. BEARIN	GS IN QUESTION WERE ACQUIRED  AS NEW PARTS ACCOMPANIED BY PROPER PART CERTIFICATIONS. BEARINGS WERE MANUFACT UNDER P/N C	B17663. ALL INSPECTED & RECALLED BEARINGS WERE FROM PRODUCTION LOTS 64598, 61262, 61077.  A TOTAL OF 120 BEARINGS EXAMIN	ED.  A FAILURE RATE PER LOT FROM 25-50 PERCENT.  OBSERVED THAT WHEN GREASE APPLIED THROUGH APPROPRIATE NEEDLE ZERK, THE 	ORFICE BALL FORCED TO BOTTOM OF THE GREASE ORFICE BLOCKING THE ENTRY OF GREASE TO THE BEARING SURFACE.	2	H	7	4 	4T				A31NM   					 
2005032400032	20050324	00032	EU  	2005	3	24	CA050107002      	1	20050104	G	3211	5321012077	BOLT            	PILATS      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						VLG018					LOWER LANDING GEAR ACTUATOR BOLT ON LEFT GEAR LEG MISSING BOLT HEAD.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005042500045	20050425	00045	GL  	2005	4	25	CA050107003      	2	20050129	G	7230		COMPRESSOR      			EMB   	135   	EMB135ER    	3260203	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					RT ENGINE	SEIZED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								CAE31171			(CAN) UNCOMMANDED IN FLIGHT SHUTDOWN DURING CLIMBOUT AT APPROXIMATELY 25,000 FT.  PILOT HEARD A LOUD BANG FOLLOWED BY A 	UNCOMMANDED SPOOL DOWN TO THE RT ENGINE.  AN EMERGENCY WAS DECLARED AND A/C RETURNED TO FIELD ACCOMPLISHING A UNEVENTFUL	 SINGLE ENGINE LANDING. GROUND CHECK REVEALED THAT COMPRESSOR ROTOR COULD NOT BE ROTATED. ENGINE ENROUTE TO ROLLS-ROYCE 	CANADA FOR INVESTIGATION. RRC HAS BEEN ADVISED THAT THE FAA WILL BE ON SITE FOR THE INVESTIGATION.			2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2005041200039	20050412	00039	SW  	2005	4	12	CA050107004      	1	20050105	G	6320	168459	HOUSING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					OIL FILTER	LEAKING         	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CL	CLIMB          	1			CA						B12177					(CAN) DURING A TEST FLIGHT FOLLOWING AN OPS NR4 INSPECTION, THE TRANSMISSION OIL PRESSURE LIGHT ILLUMINATED AND THE OIL 	PRESSURE DROPPED SLIGHTLY BELOW THE RED LINE.  AN IMMEDIATE DECENT WAS CONDUCTED AND UPON LANDING A MAJOR OIL LEAK WAS D	ISCOVERED. THE SOURCE OF THE LEAK WAS THE MAIN TRANSMISSION FILTER HOUSING. THE FILTER WAS REMOVED AND THE O-RING WAS FO	UND NICKED APPROXIMATELY .1250 INCH WIDE.  THE AIRCRAFT HAD COMPLETED A 30-MINUTE POST INSPECTION GROUND RUN TWO WEEKS E	ARLIER WITH NO LEAKS DETECTED.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005042500046	20050425	00046	NM  	2005	4	25	CA050107005      	1	20050106	G	2450	SM601BA20A1	RCCB            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT NACELLE	ARCED           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSPECTING NR 2 AC CONTACTOR BOX IN THE RT NACELLE DURING A HEAVY MX CHECK, DISCOVERED THAT HARDWARE THAT HO	LDS WIRES  ONTO THE REMOTE CONTROL CIRCUIT BREAKER (RCCB) HAD COME OFF AT 3 OF 6 ATTACH STUDS. RCCB IS FOR NR 1 ENG STAN	DBY HYD PUMP. HARDWARE FOR LOAD A2 & LOAD B2 WERE LAYING ON INSIDE BOTTOM OF CONTACTOR BOX AND HARDWARE FOR LOAD C2 HAD 	BACKED OFF APPROX HALF WAY ON STUD.  ALL 3 STUDS SHOWED SIGNS OF ARCING  DAMAGE WITH GROOVES BURNED INTO STUDS FROM CURR	ENT. TERMINAL ENDS ON WIRE 10006A18C-1 AT LOAD C2 ALL SHOWED SIGNS OF ARCING AND WERE BURNED AT THE POINT OF CONTACT WIT	H THE STUDS.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500049	20050425	00049	EA  	2005	4	25	CA050110002      	1	20050106	G	3210	17002110	LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	COLLAPSED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA			12490								(CAN)  FOLLOWING A REPOSITIONING FLIGHT (FERRY FLIGHT WITH NO PAX), THE RT MLG COLLAPSED ON LANDING.  NOBODY WAS INJURED	 DURING THE INCIDENT.  THE INVESTIGATION IS STILL IN PROGRESS					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005041200040	20050412	00040	SW  	2005	4	12	CA050110003      	1	20050105	G	6310	212040687001	COUPLING        	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					INPUT DRIVE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A2000991					(CAN) DURING SCHEDULED INSPECTION PITTING CORROSION IN EXCESS OF .005 INCH HAS BEEN DISCOVERED.  THE PATTERN AND LOCATIO	N OF CORROSION PITTING CONFORMS TO PROCESS STAMP IMPRESSION (186).  IT IS LIKELY THAT IMPROPER INK HAS BEEN USED DURING 	SHAFT OVERHAUL.  OVERHAUL SHOP(S) HAVE BEEN ADVISED.  THE ORIGIN OF THE STAMP IMPRESSION IS YET TO BE ESTABLISHED.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005042500050	20050425	00050	NM  	2005	4	25	CA050110005      	1	20050103	G	2721	82760050005	SPRING          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	RUDDER	OUT OF ADJUST   	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			33343	33343							(CAN) AIRCRAFT VIBRATION REPORTED WHEN LEVEL AT 12,000 FT.   SHAKING STOPPED AT POWER SETTING LESS THAN 40 PERCENT AND S	PEED BELOW 150KTS. AIRCRAFT INSPECTED ON ARRIVAL AND NOFAULTS FOUND.  AIRCRAFT RELEASED SUBJECT TO SATISFACTORY TEST FLI	GHT,  VIBRATION STILL PRESENT.  RUDDER ACTUATORS,  BEARINGS AND LINKAGE INSPECTED,  NO FAULTS FOU ND.  WHEN RUN ON EITHE	R NR 1 OR 2 HYDRAULIC SYSTEM RUDDER HAD 4 PERCENT SPLIT. SPRING STRUTS ADJUSTED AS PER MM27-20-00.  AIRCRAFT RELEASED FO	R TEST FLIGHT,  TEST FLIGHTSTISFACTORY.  AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500052	20050425	00052	EA  	2005	4	25	CA050110009      	1	20050109	G	5270	864202	SENSOR          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	EMERGENCY EXIT	OUT OF ADJUST   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA			32430	32430							(CAN) AT 20,000 FT AT MAX DIFFERENTIAL , FORWARD EMERGENCY EXIT DOOR WARNING LIGHT FLICKERED ON/ OFF , THEN CAME ON STEA	DY. WHEN CABIN DIFFERENTIAL BELOW 4.5 PSI WARNING LIGHT EXTINGUISHED. AIRCRAFT RETURNED TOORIGINATING AIRPORT. MAINTENAN	CE INSPECTION FOUND FORWARD EMERG EXIT DOOR SENSOR RIGGING EXCEDED MAX ALLOWABLE , GAP ADJUSTED AS PER MM. AIRCRAFT RETU	RNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005021400184	20050214	00184	NM  	2005	2	14	CA050111001      	1	20050105	G	3221	654581945	GUSSET          			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE PHASE 3 CHECK (137.5 HRS.), A 2.75 INCH CRACK WAS FOUND ON THE NOSE LANDING GEAR GUSSET WHILE CAR	RYING OUT SERVICE DIFFICULTY ALERT AL-2002-03.RETRACT ACTUATOR SUPPORT FITTING GUSSET REPLACED IAW SRM 51-30-2 FIG II. T	IMES. 61981.7 CYCLES. 52905.				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005021500004	20050215	00004	EU  	2005	2	15	CA050111002      	1	20050111	G	2760		SERVO           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					SPOILER	INTERMITTENT    	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			38898	14851							(CAN) FAULT: JUST PRIOR TAKE-OFF, FLIGHT RECEIVED A FLT CTL SPOILER 1 FAULT.  CREW TAXIED ONTO A TAXIWAY AND PERFORMED A	 SUCCESSFUL RESET.  HOWEVER, AT 3000 FT/210 KNOTS ON CLIMB, THE FAULT RETURNED AGAIN.  FURTHER INTO THE FLIGHT IN CRUISE	 SLAT SYSTEM.  ACTION:  ACFT OUT OF SERVICE FOR INVESTIGATION.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005021500005	20050215	00005	NM  	2005	2	15	CA050111003      	1	20050111	G	2530	6253190003	OVEN            			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					MID GALLEY	FIRE            	W				F				ACTIVATE FIRE EXT.      				A			FLAME/FIRE                			CR	CRUISE         	1			CA											(CAN) FAULT: JUST PRIOR TO DESCENT, SOMETHING WAS BEING COOKED IN THE MID CABIN GALLEY.  AS THE F/A WAS ABOUT TO REMOVE 	IT, A FIRE WAS FOUND AT THE BACK OF THE OVEN.  3  FIRE EXT. WERE USED TO DOUSE THE FIRE. NO EMERGENCY WAS DECLARED, NO A	DVERSE PAX REACTION.  AIRCRAFT REMOVED FROM SERVICE, WIRING INSPECTION U/WAY.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005031400045	20050314	00045	NM  	2005	3	14	CA050111004      	1	20050105	G	2932	106055410	TRANSMITTER     			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					HYD SYSTEM	STICKING        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			56659	56659							(CAN) 'A' SYSTEM LOW LEVEL LIGHT ILLUMINATED, 'A' SYSTEM QUANTITY DOWN TO 2 GALLONS AFTER GEAR RETRACTION. CREW RETURNED	 TO DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE ARRIVED AND INSPECTED AIRCRAFT AND FOUND 3 GALLONS INDICATING. FOUND	 SMALL LEAK ON B-NUT ON TAIL SKID ACTUATOR. ALSO FOUND HYDRAULIC QUANTITY TRANSMITTER STICKING ON 'A' SYSTEM RESERVOIR, 	INDICATION FLUCTUATED +/- 1.5 GALLONS BY TAPPING ON TRANSMITTER. TRANSMITTER REPLACED ENGINE RUNS CARRIED OUT WITH NO FU	RTHER LEAKS FOUND AND INDICATION WORKING CORRECTLY.		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005042500053	20050425	00053	EA  	2005	4	25	CA050111005      	2	20050109	G	7323	210631	GOVERNOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	OVERSPEED	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) ON APPROACH, WHEN THE CREW TRIED TO THROTTLE BACK, THE LT ENGINE WOULD NOT GO BELOW 1000 LB. OF TORQUE. THE CREW M	OVED THE THROTTLE FORE AND AFT SEVERAL TIMES BUT NO CHANGE.  THE CREW DECLARED AN EMERGENCY AND SHUT DOWN THE LT ENGINE 	ON FINAL APPROACH.  UPON INVESTIGATION BY MAINTENANCE IT WAS FOUND THAT THE OVERSPEED GOVERNOR HAD FAILED INTERNALLY.  T	HE OVERSPEED GOVERNOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005042500054	20050425	00054	EU  	2005	4	25	CA050112001      	1	20050105	G	5610	350A25900000	WINDSCREEN      			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) AFTER LANDING THE PILOT NOTICED A CRACK IN THE UPPER RT CORNER OF THE COPILOTS WINDSCREEN.  THE CRACK WAS WITHIN A	LLOWABLE LIMITS TO STOP DRILL AND TAPE IAW ECC MANUALS.  (12CM LONG)  AIRCRAFT WAS RETURNED TO SERVICE. TEMPERATURE AT T	IME OF THE CRACK WAS -30C.				1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2005042500055	20050425	00055	CE  	2005	4	25	CA050112002      	1	20050110	G	5610	5042006936	WINDSHIELD      			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE PILOT HEARD LOUD BANG, NOTICED CO-PILOTS INNER PANE SHATTERED.  STARTED DECENT TO 130000 ASL,  BROUGHT C	ABIN PRESSURE DOWN TO 2 PSI.  LANDED AT DESIGNATION.					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005041200036	20050412	00036	EU  	2005	4	12	CA050112003      	1	20050106	G	5630	SPSEC130811	WINDOW          	UROCOP      		UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					SLIDING DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3759					(CAN) THE HELICOPTER PARKED OVERNIGHT OUTSIDE, WAS BEING PREPARED FOR FLIGHT, COVERS REMOVED AND DI COMPLETED.  ALL WIND	OWS WERE INSPECTED FOR CRACKS BECAUSE THE DAY BEFORE THE CO PILOTS WINDOW HAD CRACKED.  PASSENGERS WERE LOADED AND HELIC	OPTER WAS STARTED.  AFTER START,  PASSENGER NOTICED A 16CM LONG CRACK IN THE UPPER LT CORNER OF THE SLIDING DOOR WINDOW.	  AC WAS SHUT DOWN AND MFG WAS CONTACTED.  THIS CRACK WAS BEYOND THE ALLOWABLE LIMIT FOR OPERATION SO THE CRACK WAS STOP	 DRILLED, TAPED AND THE HELICOPTER WAS RETURNED TO BASE.  DOOR HAS BEEN SENT TO MFG FOR WINDOW REPLACEMENT. TEMPERATURE 	WAS -22C AT TIME OF THE CRACK.(THE DAY BEFORE WHEN THE CO PILOTS WINDSCREEN CRACKED THE TEMP WAS -30C.)	1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2005041200037	20050412	00037	CE  	2005	4	12	CA050112004      	1	20050103	G	2820	1009200423	TUBE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION OF THE FUEL TRANSFER PRESSURE SWITCH, IT WAS NOTICED THAT ONE OF THE ENGINE CONTROLS WAS RUBBING A	GAINST THE MAIN FEED LINE TO THE RT NAC TANK.  REPLACED TUBE ASSY AND TIED BACK TELEFLEX CABLES TO PREVENT FURTHER RUBBI	NG.				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005032400034	20050324	00034	NE  	2005	3	24	CA050112005      	2	20050109	G	7250		ENGINE          			AGUSTA	A109  	A109        	0260109	EU  	PWC   	PW206C	PW206C      		NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								BC0368			THE ENGINE EXPERIENCED A RAPID, UNCOMMANDED DECREASE IN TORQUE IN FLIGHT, ACCOMPANIED BY AN INCREASE IN OTHER ENGINE PAR	AMETERS.  THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT RETURNED TO BASE.  SUBSEQUENT INSPECTION REVEALED POWER TURBINE BLAD	E DAMAGE.  PWC WILL INVESTIGATE THE INCIDEMT AND SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERMINED.				1	G	7	2 	3U	3	U		H7EU    	E42NE				 
2005042500056	20050425	00056	SW  	2005	4	25	CA050112006      	1	20050107	G	3610	3017393	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					PNEUMATIC SYS	FRACTURED       	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE ENGINE NO.2 POWER-SECTION EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE, FALLING BELOW GROUND IDLE.THE 	POWER-SECTION WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO BASE. SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PN	EUMATIC TUBE LEADING TO THE FUEL CONTROL (AFCU).				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005042500057	20050425	00057	EA  	2005	4	25	CA050112007      	1	20050112	G	2163	7546911	SENSOR          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										CABIN AIR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NA					(CAN) DURING ROUTINE PERIODIC INSPECTION, DUCT WAS DISSASEMBLED AND TEMP PROBE SCREEN WAS FOUND TRAPPED IN DUCT CHECK VA	LVE,  HOLDING IT OPEN.  LOOSE SCREEN REMOVED.  VALVE INSPECTED AND FOUND SERVICEABLE.  UPSTREAM INVESTIGATION OF MOST LI	KELY SOURCE SHOWS PART CORRECTLY INSTALLED.  SUSPECT PRIOR FAILURE AND SUBSEQUENT PART REPLACEMENT.  NO FURTHER ACTION T	AKEN.			2	L	7	2 	4F			RT	A21EA   					 
2005042500058	20050425	00058	NM  	2005	4	25	CA050113001      	1	20050107	G	1430		BOLT            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					WING SPAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A POST FLT WALKAROUND MX DISCOVERED DAMAGE ON LT OUTBOARD WING LOWER SPAR CAP,  AFT OF THE NR 6 LEADING EDG	E SLAT.  FURTHER INSPECTION REVEALED A LOOSE UNATTACHED BOLT PRESENT IN THE AREA.  THIS BOLT CREATED FOD DAMAGE TO THE S	PAR WHEN THE NR 6 SLAT ACTUATOR RETRACTED AND EXTENDED.  THIS BOLT IS THE SAME PART AS THE ACTUATOR ATTACHMENT BOLT AND 	IS SUSPECTED TO HAVE BEEN LOST AND LEFT IN THE AREA DURING THE RECENT HEAVY MX CHECK COMPLETED AT TIMCO AVIATION BEFORE 	ACRFT DELIVERY TO CANADA.  THE DAMAGE AND REPAIRS ARE CURRENTLY BEING ASSESSED AND AN INVESTIGATION TO THE CAUSE IS STIL	L UNDERWAY. THIS SDR WILL BE UPDATED AS MORE INFORMATION BECOMES AVAILABLE.	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005021400185	20050214	00185	NM  	2005	2	14	CA050113002      	1	20050109	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1 HYD SYSTEM	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH TO BASE, NR 1 HYD ISO VLV AND NR 1 ENG HYD PUMP CAUTION LIGHT ILLUMINATED. NR 1 SYSTEM PRESSURE 0 	PSI.  STBY PRESS NORMAL AFTER SPU SELECTED ON. EMERGENCY LANDING DECLARED.  AIRCRAFT STOPPED ON RUNWAY AND WAS TOWED IN.	  NR1 PROP COULD NOT BE ROTATED BY HAND.  METAL FOUND IN CASE DRAIN AND PRESSURE FILTERS. REPLACED NR 1 EDP.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005021500008	20050215	00008	NM  	2005	2	15	CA050113003      	1	20050110	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) NR2 HYDRAULIC SYSTEM FAILED DURING CLIMBOUT FROM BASE. PILOTS COMPLETED CHECKLIST AND PERFORMED AIR TURNBACK WITH 	UNEVENTFUL LANDING . PUMP HOUSING CRACKED WITH SUBSEQUENT FLUID LOSS INTO NACELLE. ENGINE DRIVEN PUMP REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005031100009	20050311	00009	NM  	2005	3	11	CA050113004      	1	20050112	G	2910	AN81510D	UNION           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1 HYD SYS	FRACTURED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE NR 1 HYDRAULIC SYSTEM SUFFERED A TOTAL HYDRAULIC SYSTEM FLUID LOSS.  A FULL EMERGENCY LANDING W	AS DECLARED INTO BASE, WHICH WAS CARRIED OUT WITHOUT FURTHER INCIDENT.  UPON INSPECTION BY ENGINEERING IT WAS DISCOVERED	 THAT THE NR 1 HYDRAULIC PRESSURE MANIFOLD HAD SUFFERED A FAILURE OF THE AN815-10D UNION.  THE AIRCRAFT MFG HAS PREVIOUS	LY IDENTIFIED THIS DEFECT, AND A SYD 8-29-002 WAS ISSUED THAT PERMITS THE REPLACEMENT OF THE ALLOY UNION WITH A CORROSIO	N RESISTANT STEEL UNION.  AS A RESULT OF THIS INCIDENT, ALL DASH 8 / 315 SERIES AIRCRAFT OPERATED THIS AIRLINE HAVE HAD 	SYD 8-29-002 INCORPORATED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005031100010	20050311	00010	EU  	2005	3	11	CA050113005      	1	20050111	G	3220		LANDING GEAR    			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	NOSE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER A NORMAL LANDING, THE AIRCRAFT TAXIED OFF THE RUNWAY AND STOPPED IN FRONT OF THE AIRPORT TERMINAL. THE ENGIN	ES WERE SHUT DOWN AND THE CREW COMPLETED THEIR COCKPIT CHECKS.  WHEN THE ELECTRICAL MASTER SWITCH WAS TURNED TO OFF THE 	NOSE UNDERCARRIAGE RETRACTED, DROPPING THE NOSE OF THE AIRCRAFT ONTO THE TARMAC.   A SHORT WHILE LATER, AS THE GROUND CR	EW WERE POSITIONING A TEMPORARY TAIL SUPPORT, THE MAIN UNDERCARRIAGE STARTED TO RETRACT.THE AIRCRAFT WAS RECOVERED TO A 	MAINTENANCE HANGAR FOR INVESTIGATION.		2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2005031400046	20050314	00046	NE  	2005	3	14	CA050113006      	3	20050111	G	6111		BLADE           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER TIP	BROKEN          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA									011390		(CAN) DURING TAKE OFF ROLL OUT, THE LT PROP STRUCK DEBRIS ON RUNWAY AND A 3 INCH PORTION OF THE TIP OF THE PROP BROKE OF	F AND WENT THROUGH THE FUSELAGE JUST BEHIND AND BELOW THE AIRSTAIR DOOR.  A 2 -3 INCH HOLE IN RT PROP SPINNER WAS ALSO D	ISCOVERED AT THE SAME TIME.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005042500059	20050425	00059	SW  	2005	4	25	CA050113007      	1	20050109	G	5610	2419441004	WINDSHIELD      			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) OUTER PANE SHATTERED IN FLIGHT ON ITS WAY TO FINAL DESTINATION.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005041200038	20050412	00038	EU  	2005	4	12	CA050113008      	1	20050112	G	5610	SP350110	WINDOW          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE BLF THE MAIN WINDOW WAS FOUND TO BE CRACKED. THE OAT WAS -34 DEGREES.  IT APPEARS TO HAVE BEEN INSTALLE	D WITH IMPROPER TORQUE AS THE CRACK ORIGINATED FROM THE TOP SCREW OF THE SLIP INDICATOR.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005042500060	20050425	00060	EA  	2005	4	25	CA050114001      	1	20050106	G	3320	BR900022	BALLAST         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LIGHT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) BURNING SMELL PRESENT IN CABIN DURING TURNAROUND. FOUND TOILET LIGHTS NOT WORKING AND SMELL CAUSED BY TOILET BALLA	ST UNIT.  BALLAST UNIT REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005042500061	20050425	00061	NE  	2005	4	25	CA050114002      	2	20050109	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								GEE873446			(CAN) ON INITIAL CLIMB, HEARD A SUDDEN AND LOUD NOISE BETWEEN 4000 AND 4500 FT AND THE RT ENGINE SHUTDOWN ITSELF IN FLT.	 AFTER ASSESSING THE SITUATION AND FOLLOWING QRH AND MEMORY ITEMS, THE CREW NOTIFIED THE FLT ATTENDANT, PAX AND MX OF TH	E SITUATION.  AN EMERGENCY WAS DECLARED AND THE CREW PROCEEDED TO DIVERT BACK TO PLACE OF DEPARTURE.  AN UNEVENTFUL LAND	ING FOLLOWED.  MX REPLACED THE RT ENGINE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005021400186	20050214	00186	NM  	2005	2	14	CA050114003      	1	20050112	G	2910	887087	MOTOR           			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					HYD ACTUATOR	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) A/C DEPARTED AND TURNED AROUND AFTER NOTICING SLOW STEADY DECLINE IN CENTER SYSTEM QUANTITY. MAINTENANCE FOUND FLU	ID LEAKING FROM FUSELAGE DRAIN HOLES IN THS COMPARTMENT. UPON INVESTIGATION MAINTENANCE FOUND CENTER SYSTEM HYD MOTOR ON	 THIS GEARBOX LEAKING FLUID OUT MOTOR DRAIN LINE BUT MOST WAS COMING OUT THS GEAR BOX VENT HOLE ON FWD SIDE OF GEARBOX P	OSSIBLY DUE TO A PARTIALLY BLOCKED MOTOR DRAIN LINE. MFG INDICATED THAT WE WILL HAVE TO REPLACE THE THS ACTUATOR DUE TO 	THE HYDRAULIC FLUID LEAKAGE CONTAMINATING THE ACTUATOR GEAR BOX.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005042000086	20050420	00086	EA  	2005	4	20	CA050114004      	2	20050106	G	7320	A23D047	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA							317405143				(CAN) DURING AN INSPECTION NECESSARY BY AD 2004-25-16 THE FUEL REGULATOR WAS FOUND TO BE LEAKING AROUND THE SEAM.  IT WA	S NOT LEAKING ENOUGH TO RUN OUT THE DRAIN FOR THE PROTECTIVE COVER.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005042000087	20050420	00087	EU  	2005	4	20	CA050114005      	1	20050114	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) AN ENGINEER WAS DOING A 30 HOUR INSPECTION IAW AWD 96-156-071(B) R1 PART 1.1.THE ENGINEER DISCOVERED A BLACK LINE 	IN THE REGION THAT IS TO BE INSPECTED, A CLOSER LOOK, IT WAS DETERMINED THAT IT WAS CRACKED.  THE TSO IS ACTUALLY TSI SI	NCE THE LAST (NDT LIQUID DYE PENETRENT) INSPECTION IAW AWD.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005031100016	20050311	00016	EA  	2005	3	11	CA050115001      	1	20050111	G	2420	755469D	IDG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					GENERATOR	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA			16558								(CAN) LOSS OF BOTH IDGS ON APPROACH FOLLOWED BY AN ADG DEPLOYMENT.  NO PROBLEM WAS REPORTED WITH THE ADG.  FLIGHT CREW D	ECIDED TO ABORT THE APPROACH.  EMERGENCY WAS DECLARED. THE CREW DECIDED TO START DE APU TO POWER THE AIRCRAFT BUSES. THE	 AIRCRAFT LANDED. THE IDG 2 WAS INSPECTED.  OIL LEVEL WAS LOW.  ANS REPORTS 2 LITERS WERE ADDED.  IDG 1 OIL LEVEL WAS OK	. GROUND RUNS COULD NOT DUPLICATE THE SNAG.  BOTH IDG'S AND BOTH GCUS WERE REPLACED.  WIRING INSPECTION INCLUDING ENGINE	S AND PYLONS WITH NO ANOMALY FOUND.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005042000088	20050420	00088	CE  	2005	4	20	CA050117001      	1	20050113	G	5411		FRAME           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20570								(CAN) DURING A ROUTINE INSPECTION A CRACK WAS FOUND PROPAGATING FROM THE OVAL HOLE IN THE RT FRAME AT STATION 207.125 (H	ALF WAY BETWEEN THE FLOOR AND THE WINDOW).  THE CRACK WAS APPROXIMATELY 1 = INCH LONG AND EXTENDED FROM THE 11 O`CLOCK P	OSITION OF THE LIGHTNING HOLE TO A RIVET ON THE REINFORCEMENT PLATE.				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005031100017	20050311	00017	CE  	2005	3	11	CA050117002      	1	20050106	G	3233	91929	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT MLG ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA						3248					(CAN) WHILE CARRYING OUT NIGHT LANDINGS ON A LOCAL TRAINING FLIGHT, THE LT MAIN GEAR DOWNLOCK INDICATION FAILED TO ILLUM	INATE ON THE NINTH LANDING APPROACH. THE CREW CARRIED OUT AN EMERGENCY EXTENSION PROCEDURE AND LANDED SAFELY. MAINTENANC	E CREW SERVICED THE LANDING GEAR IAW THE MM AND REPLACED THE LT MAIN GEAR ACTUATOR P/N 9912053-21. THE GEAR DOWNLOCK SWI	TCH WHICH FAILED IS INTEGRAL TO THE ACTUATOR.  A SUCCESSFUL LANDING GEAR EXTENSION AND RETRACTION TEST WAS CARRIED OUT A	ND THE AIRCRAFT RETURNED TO SERVICE.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005031100018	20050311	00018	NM  	2005	3	11	CA050117003      	1	20050117	G	7120	9604209	MOUNT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE NR1 ENGINE MOUNT PN 96042-09, A CRACK WAS FOUND ON THE CORE ASSY PN. 19-9495-01. MFG IS I	NVESTIGATING THE ISSUE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005031400047	20050314	00047	WP  	2005	3	14	CA050117004      	1	20050116	G	3244	95502675	TIRE            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	OVERSERVICED    	W				C				ABORTED TAKEOFF         				W	D		INADEQUATE Q C            	INFLIGHT SEPARATION       		TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLL, A NOSE WHEEL SHIMMY WAS FELT AND REJECTED TAKE-OFF WAS CARRIED OUT.  THE AIRCRAFT RETURNED T	O THE GATE WITHOUT INCIDENT.  UPON INVESTIGATION, IT WAS OBSERVED THAT THE NR2 NOSE WHEEL TIRE WAS OVER-SERVICED.  THE N	OSE WHEEL TIRE WAS SERVICED CORRECTLY IAW MM 12-00-00.  NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500062	20050425	00062	WP  	2005	4	25	CA050117005      	2	20050113	G	7261	8941172	ADAPTER         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					OIL FILTER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								P54259			(CAN) A SPECIAL INSPECTION WAS CARRIED OUT TO FLEET AIRCRAFT OF SUSPECTED CRACKING OIL FILTER ADAPTERS.  EDDY CURRENT ME	THOD WAS USED TO DISCOVER THIS CRACKED ADAPTER . ALTHOUGH VISIBLE WITH THE NAKED EYE,  INITIAL DETECTION MAY BE DIFFICUL	T DUE TO THE ADAPTER LOCATION. FLEET INSPECTION IS STILL UNDERWAY.THIS ADAPTER SHOWS THE SAME PATTERN OF CRACKING AS THE	 ADAPTER DISCUSSED IN SDR20050105015.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005042500063	20050425	00063	WP  	2005	4	25	CA050117006      	1	20050115	G	3213	528039	AXLE            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					NR 1 MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON TAXI TO PARKING, GROUND CREWS NOTICED THE NR 1 MAIN WHEEL WAS MISSING. UPON FURTHER INVESTIGATION, IT WAS DIS	COVERED THAT THE NR 1 AXLE HAD SHEARED OFF, ALLOWING THE WHEEL TO DEPART THE A/C. THE WHEEL WAS FOUND JUST OFF OF THE TA	XIWAY STILL ATTACHED TO THE BROKEN PIECE OF AXLE. THE CREW WAS UNAWARE OF A PROBLEM UNTIL THEY SHUTDOWN THE AIRCRAFT AND	 DEPLANED. THE LOWER SHOCK STRUT ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4R	4	T		6A6     	E282				 
2005042500064	20050425	00064	WP  	2005	4	25	CA050117007      	2	20050115	G	7261	8941172	ADAPTER         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					OIL FILTER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54090			(CAN) DURING ROUTINE ENGINE MAINTENANCE AN AME NOTICED THE LT ENGINE OIL FILTER ADAPTER WAS CRACKED AT THE MOUNTING FLAN	GE. THE OIL FILTER ADAPTER WAS REPLACED. THIS OIL FILTER ADAPTER CRACKED IN THE SAME AREA AS THE ADAPTER DISCUSSED IN SD	R20050105015 AND SDR20050117005.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005031100019	20050311	00019	NE  	2005	3	11	CA050117008      	2	20050111	G	7321	5001T39G39G29	FCU             			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								304415B			(CAN) AC WAS DISPATCHED FOR A TEST FLIGHT DUE TO DUAL ENGINE CHANGE.  AT FL370 MAX ACCELERATION CHECK COMPLETED, WITHOUT	 INCIDENT.  ON RETURN, ENGINE FLAMED OUT, ENGINE RELIGHT AT FL180.   ENGINE FCU RIGGING, BLEED VALVES RIGGING AND AIR SE	NSOR LINES WERE INSPECTED, NOTHING UNUSUAL FOUND.  SECOND TEST FLIGHT WAS CONDUCTED ON 13 JAN 05.  ENGINE WAS INTENTIONA	LLY SHUTDOWN AT FL250 AND A RELIGHT ATTEMPTED WITH PARTIAL SUCCESS.  ENGINE WOULD NOT ACCELERATE PAST 40 PERCENT N2 UNTI	L AC HAD DESCENDED TO FL180.  AC RETURNED WITHOUT INCIDENT AND THE AC WAS GROUNDED PENDING THE REPLACEMENT OF THE FCU CH	ANGE, WHICH IS CURRENTLY IN PROCESS.	2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2005031100020	20050311	00020	EU  	2005	3	11	CA050117009      	1	20050116	G	7603		POWER LEVER     			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	FROZEN          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, NOTICED BY CREW THAT THE NR1 ENGINE POWER LEVER WAS FROZEN IN POSITION. THE ENGINE WAS SHUTD	OWN AND AN UNEVENTFUL LANDING WAS COMPLETED.  WITH WARMER TEMPERATURES, POWER LEVER WAS ABLE TO MOVE FREELY THROUGH ITS 	FULL RANGE OF TRAVEL.  FLIGHT WAS CONDUCTED WITH NO FAULTS NOTED.  ON THE 3RD FLIGHT, WHILE IN CRUISE, IT WAS NOTED THAT	 POWER LEVER BECAME DIFFICULT TO MOVE. ENGINE POWER WAS REDUCED TO IDLE, SCHEDULED LANDING. REVEALED WATER LEAK FROM LAV	 SINK SUPPLY LINE MIGRATED BELOW FLOOR ONTO NR 1 ENGINE PWR LEVER BELLCRANK, ICE ACCUMULATION WAS EVIDENT IN AREA. LEAK 	WAS REPAIRED, CONTAMINATED AREAS WERE CLEANED, DRIED AND LUBRICATED. ENGINE PWR LEVER FUNCTION CHECKED SERVICEABLE.	2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2005021400187	20050214	00187	NE  	2005	2	14	CA050117011      	2	20050113	G	7210		TURBINE BLADES  			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       	 	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE PILOT REPORTED A (PUFF) FROM THE ENGINE ACCOMPANIED BY A LOSS OF TORQUE.  POWER LEVER ADVANCEMEN	T RESULTED IN ENGINE TEMPERATURE INCREASE AND AN OIL SMELL AND SMOKE IN THE CABIN.  THE ENGINE WAS SHUT DOWN, AN EMERGEN	CY DECLARED AND THE FLIGHT DIVERTED. SUBSEQUENT INSPECTION REVEALED DAMAGED TURBINE BLADES.  MFG WILL INVESTIGATE THE IN	CIDENT AND SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005031400048	20050314	00048	EA  	2005	3	14	CA050118002      	2	20050112	G	7414	10382971	BEARING         	CONT        		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MAGNETO	SEIZED          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA						C139805GR					(CAN) AFTER TAKEOFF, IN CRUISE FLIGHT, THE PILOT NOTICED THE LT ENGINE TACHOMETER NEEDLE FLUCTUATING.  SHORTLY AFTER, TH	E ENGINE STARTED SURGING AND A NOTICEABLE VIBRATION WAS FELT.  THE AIRCRAFT RETURNED, AN INVESTIGATION REVEALED THE LT E	NGINE MAGNETO, UPPER BEARING, P/N 10-382971, HAD SEIZED IN THE DISTRIBUTOR BLOCK P/N 10 -682058. THIS IS THE FIRST INCID	ENT OF THIS NATURE AND WITH OVER 15,000 HOURS ON THIS ENGINE TYPE, FEEL NOTHING COULD HAVE PREVENTED THIS OCCURRENCE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005032400133	20050324	00133	GL  	2005	3	24	CA050118003      	3	20050112	G	6114	A1851T	BEARING RACE    													HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER HUB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING THE NDT PROCESS OF THE PROPELLER OVERHAUL, ONE BEARING RACE, INBOARD RACE WAS DISCOVERED CRACKED.																6	C	P15EA	 
2005042500065	20050425	00065	CE  	2005	4	25	CA050118004      	1	20050113	G	2160	7547512	BYPASS VALVE    			CESSNA	441   	441         	2076020	CE  										ACM	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE THE DUCT OVERHEAT WARNING CAME ON.EMERGENCY CHECKLIST CARRIED OUT. SMOKE BEGAN TO EMIT FROM FLOOR 	INTO CABIN AND COCKPIT.  AIRCRAFT RETURNED AND SHUTDOWN AS PER FIRE CHECKLIST.  AIRCRAFT EVACUATED.UPON INVESTIGATION TH	E AIR CONDITIONING BYPASS VALVE WAS FOUND FAILED IN THE OPEN POSITION.  INSPECTION OF DUCTS AND MANIFOLDS FOUND NO FAULT	S.  BYPASS VALVE REPLACED AND AIRCRAFT RELEASED.			1	L	7	2 	3T			RT	A28CE   					 
2005021400206	20050214	00206	CE  	2005	2	14	CA050118005      	1	20050117	G	3211		LANDING GEAR    			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RIGHT	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) RT LANDING GEAR COLLAPSED ON LANDING, THIS IS A PRELIMINARY REPORT MORE INFORMATION WILL FOLLOW.						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
2005021400188	20050214	00188	EA  	2005	2	14	CA050119001      	1	20050117	G	3000	601970975	VALVE           			CNDAIR	CL601 	CL6012A12   	1900303	EA  										ANTI-ICE VLV	IMPROPER PART   	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING AN FAA, SUSPECTED UNAPPROVED PART REPORT, FOR A COWL ANTI-ICE VALVE PN 300013000-002, SN 1596, THREE (3)	 ADDITIONAL VALVES WERE FOUND TO HAVE BEEN REPAIRED AND CERTIFIED WITHOUT THE USE OF PROPER CMM. THE VALVES INVOLVED ARE	 S/N: 133R, 867, 691.				2	L	7	2 	4F			RT	A21AE   					 
2005021400203	20050214	00203	EA  	2005	2	14	CA050119002      	1	20050118	G	5330	6003303913	ACCESS PANEL    			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF34*       	 	NE  					FUSELAGE	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC REMOVED FROM HEATED HANGAR (20 DEG C) TO RAMP (-27 DEG C) T/E OF UPPER ELEC BAY ACCESS PANEL DEFLECTED .345 FRO	M AIRFRAME.  FURTHER INVESTIGATION SHOWED DISTORTION THROUGHOUT PANEL WITH GREATEST DISTORTION AT CORNERS RANGING FROM .	100IN TO .345 IN. SIMILAR DISTORTION WAS FOUND ON LT DOOR.  WHEN AC WAS RETURNED TO HEATED HANGAR DOORS RETURNED TO NORM	AL AS THE AIRFRAME WARMED.  AC 144615,144616 WERE TESTED UNDER SAME CONDITIONS, AGAIN SIMILAR RESULTS WERE NOTED.  DISCU	SSIONS WITH MFG THROUGH  SRPSA WERE CONDUCTED WITH RECOMMENDATION THAT AC NOT BE FLOWN UNTIL  DOORS IN QUESTION COULD BE	 REPLACED.   COMPLETE LIST OF MEASURMENTS FOR 144614,144615,144616 ARE ON FILE WITH OPERATOR.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2005021400204	20050214	00204	NM  	2005	2	14	CA050119003      	1	20050119	G	3260	H1010153	SWITCH          			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH, LANDING GEAR CYCLED DOWN FOR LANDING. THE NOSE LANDING GEAR RED INDICATOR STAYED ILLUMINATED AND NO G	REEN INDICATION WAS SEEN. GEAR WAS RE-CYCLED AND THE GEAR WAS EXTENDED WITH PROPER INDICATION. MAINTENANCE LUBED THE NOS	E GEAR AND JACKED THE GEAR AND CYCLED THE GEAR NUMEROUS TIMES, NO FAULTS FOUND. THE AIRCRAFT WAS DISPATCHED, NO FAULT ON	 LANDING THERE. THIS IS THE SECOND OCCURENCE AND SECOND SDR FOR THE SAME AIRCRAFT AND SNAG. DUE TO ITS HISTORY, NOSE GEA	R DOWN POSITION SWITCH S93 AND THE NOSE GEAR LOCKED SWITCH S96 ARETO BE REPLACED BEFORE THE AIRCRAFT WILL BEDISPATCHED.P	OSSIBLE INTERNAL INTERMITTENT FAILURE TO ONE OF THE SWITCHES AND AT THE SAME TIME ALL WIRING WILL BE INSPECTED.	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005021400205	20050214	00205		2005	2	14	CA050119005      	4	20050117	G	3425	800610350	COMPUTER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FLT DIRECTOR	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, IT WAS OBSERVED THAT THE MFDS FAILED.  FLIGHT WARNING COMPUTER WAS SUSPECTED.  AIRCRAFT RETURNED TO 	BASE AND LANDED WITHOUT INCIDENT.  THE FLT WARNING COMPUTER WAS REPLACED AND CHECKED SERVICEABLE IAW MM 31-51-00.  THERE	 WAS NO PROBLEM WITH THIS SYSTEM DURING THE SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005031400049	20050314	00049		2005	3	14	CA050119006      	4	20050117	G	3425	6228047541	DISPLAY         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, IT WAS OBSERVED THAT THE NR1 AND NR2 EMUX SINGLE CHANNELS FAILED.  THE AIRCRAFT RETURNED TO BASE AND	 LANDED WITHOUT INCIDENT.  THE NR1 AND NR2 MAIN FLIGHT DISPLAY UNITS WERE REPLACED AND CHECKED SERVICEABLE IAW MM 31-61-	01. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005021400207	20050214	00207	EU  	2005	2	14	CA050119007      	1	20050105	G	3211		LANDING GEAR    			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  		UNKNOWN         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF, THE LANDING GEAR WOULD NOT RETRACT AFTER BEING SELECTED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE A	ND LANDED NORMALLY. THE AIRCRAFT WAS HANGARED AND A GEAR SWING CARRIED OUT, THE FAULT COULD NOT BE DUPLICATED. THE AIRCR	AFT WAS RETURNED TO SERVICE.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005021400208	20050214	00208		2005	2	14	CA050119008      	4	20050103	G	3418		PROBE           			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	ANGLE OF ATTACH	STICKING        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTING, THE CREW OBSERVED A STICK SPURRIOUS SHAKER WARNING. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. 	THE ANGLE OF ATTACK PROBE WAS FOUND TO BE STICKING, MAINTENANCE LURICATED THE PROBE AND THE SYSTEM WAS CHECKED SERVICEAB	LE. THE AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2005021400210	20050214	00210	EU  	2005	2	14	CA050119009      	1	20050112	G	2140	S200	HEATER          			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	CABIN	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER DEPARTING, THE CABIN HEATER FAILED. THE CREW RETURNED THE AIRCRAFT TO POINT OF DEPARTURE. THE HEATER	 UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005042500066	20050425	00066	SO  	2005	4	25	CA050119010      	1	20050117	G	2810	461713	VENT LINE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL CELL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			20174				317552099				(CAN) DURING INSPECTION,  FUEL WAS NOTICED LEAKING FROM THE LT WING.  THERE WAS A FUEL STAIN AROUND THE VENT TUBE.  WHEN	 THE TUBE WAS MOVED IT BROKE OFF AT THE TANK END OF THE TUBE.  BOTH IB AND OB TANKS WERE REMOVED FOR INSPECTION.  THEY B	OTH SHOWED SIGNS OF DETERIORATION OF THE FUEL TANK MATERIAL.  IT WAS STILL HOWEVER,  PLIABLE AND NOT SHOWING ANY LEAKING	 ELSEWHERE.  THE MFG 2 YEAR INSPECTION OF THE FUEL CELLS WAS CARRIED OUT IN AUGUST OF 2003 WITH NO FAULTS FOUND.  THE TA	NKS WERE SHOWING A BUILD DATE OF 1974.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005042500067	20050425	00067	NM  	2005	4	25	CA050119011      	1	20050116	G	5620	58935734	WINDOW          			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D*       	 	NE  					CABIN	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDOW NR 4 PANE CRACKED, APPEARS TO BE OUTER PANE.  AIRCRAFT RETURNED TO BASE.  WINDOW REPLACED,  AIRCRAFT RET	URNED TO SERVICE.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005021400211	20050214	00211	EA  	2005	2	14	CA050120003      	1	20050120	G	2720	215T2429080	FITTING         			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RUDDER	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE RUDDER GEAR/TRIM TAB UPPER FITTING FOUND BROKEN ON A VISUAL INSPECTION. A/C 1655, HOURS 1054, CYCLES 7200 DROP	S.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2005042000090	20050420	00090		2005	4	20	CA050120004      	4	20050119	G	2340	25091	CIRCUIT BOARD   																	TEMP SENSOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VIBRATION TESTING REVEALED THAT MODEL 251 UNITS MFG WITH SPRAY CONFORMAL COATING ARE NON-COMPLIANT WITH  DO-160C V	IBRATION CATEGORY SPECIFIED IN TSO APPROVAL. FAILURE OF UNITS COULD RESULT IN LOSS OF OUTPUT TO PASSENGER ADDRESS SPEAKE	RS. TYPICAL APPLICATIONS INCLUDE PROVISION OF SEAT BELT AND NO SMOKING CHIME TONES, CABIN PAGER AUDIO, AND MUSIC AUDIO T	O  PASSENGER CABIN.  FAILURE OF UNIT WILL BE OBVIOUS TO CREW AND/OR PASSENGERS, FAILED UNITS WILL BE REPLACED. FAILURES 	WILL NOT POSE THREAT TO SAFETY OF AIRCRAFT, COULD IMPACT SAFETY OF OCCUPANTS IF FAILURE OCCURS PRIOR TO OR DURING EMERGE	NCY FLT CONDITION, WHERE EMERGENCY INSTRUCTIONS TO OCCUPANTS OVER CABIN PAGING SYSTEM ARE NECESSARY FOR THEIR SAFETY.														 
2005021400212	20050214	00212	EA  	2005	2	14	CA050120005      	1	20050118	G	3220	16700109	STRUT           	MENASCO     		DHAV  	DHC7  	DHC7102     	2802708	EA  										NLG	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) NLG HAD SEVERE SHIMMY, STEERING SYSTEM FAILURE UNCONTROLLED.                 B- MAINTENANCE FINDINGS:  THE STEERIN	G ACTUATOR MOUNTING PIN INTEGRATED ON THE INNER CYLINDER BODY FOUND COMPLETELY SHEARED OR RUPTURED.  THE STEERING ACTUAT	OR FOUND LEAKING . THE AC DID NOT EXPERIENCE AN OVERSTEER, THE OVER TRAVEL MECHANICAL STOP, FOUND IN GOOD CONDITION .  C	-MAINTENANCE ACTION : NLG SHOCK STRUT P/N: 16100 -43 , S/N MC-113 REPLACED, S/N MC 117 OF SAME P/N INSTALLED.  STEERING 	ACT P/N 16700-109 , S/N MC-152 REPLACED , A SERVICEABLE ONE INSTALLED.		2	H	7	4 	4T				A20EA   					 
2005042000091	20050420	00091	CE  	2005	4	20	CA050120006      	1	20050109	G	2910	661705213	LINE            			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					LT HYD SYS	CRACKED         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED. AS THE AIRCRAFT ACCELERATED THE CREW BECAME CONCERNED DUE TO A VIBRATION.  THE AIRCRAFT WAS DIV	ERTED TO INTERNATIONAL AIRPORT.  INVESTIGATION FOUND A CRACK IN THE HYDRAULIC LINE FROM THE LT ENGINE DRIVEN HYDRAULIC P	UMP WHERE IT CONNECTS TO THE INPUT PORT OF THE LT PRESSURE FILTER.  A NEW LINE WAS INSTALLED.  THE HYDRAULIC SYSTEM WAS 	SERVICED AND GROUND FUNCTION TESTS WERE COMPLETED.  THE AIRCRAFT WAS RELEASED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005042000092	20050420	00092	CE  	2005	4	20	CA050120007      	1	20050117	G	5610	10138402523	WINDSHIELD      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	BROKEN          	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) ENROUTE IN CRUISE FLIGHT AT 16000 MSL, OAT -38C THE LT WINDSHEILD SHATTERED. THE WINDSHIELD HEAT WAS OFF AND HAD N	OT BEEN USED DURING THE FLIGHT.  THE DEFOG AIR WAS ALSO OFF.  THE CREW DECLARED AN EMERGENCY AND REQUESTED CLEARENCE AND	 IMMEDIATE DECENT TO 8000 MSL. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE WINDSHIELD INNER PLY WAS FOUND SHATTERE	D. THE WINDSHIELD WILL BE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2005021400213	20050214	00213	EA  	2005	2	14	CA050120008      	1	20050120	G	3000	601970975	ANTI-ICE VALVE  			CNDAIR	CL601 	CL6012A12   	1900303	EA  											FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING AN FAA, SUSPECTED UNAPPROVED PART REPORT, FOR A COWL ANTI ICE VALVE P/N: 300013000-002 S/N: 1596, MFG P/	N: 601-97097-5, AN ADDITIONAL VALVE S/N:691, WAS FOUND TO HAVE BEEN REPAIRED AND CERTIFIED WITHOUT THE USE OF A PROPER C	MM.				2	L	7	2 	4F			RT	A21AE   					 
2005021500002	20050215	00002	EA  	2005	2	15	CA050120010      	1	20050116	G	3250	DSC167	LIMIT SWITCH    			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NLG STEERING	CORRODED        	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI TO GATE NOSE WHEEL STEERING FAILED CAUSING OVER STEER CONDITION. MAINTENANCE FOUND STEERING ACTUATOR LINKA	GES DAMAGED. DURING TROUBLESHOOTING / REPAIRS, LIMIT SWITCH WAS FOUND WITH CONNECTOR PINS CORRODED AND BROKEN OFF.  STEE	RING ACTUATOR, TRANSFER TUBE, LIMIT SWITCH AND CONNECTOR REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005032400051	20050324	00051	CE  	2005	3	24	CA050120011      	1	20050118	G	3397	1303640448	WIRE HARNESS    			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LIGHTS	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											ACFT POWERED UP FOR DAILY INSPECT IN HANGER.  CABIN INDIRECT LIGHTING TURNED ON, SOON AFTER, SMOKE NOTED COMING FROM AFT	 HEADLINER ASSY, OUT OF CABIN DOOR.  HEADLINER REMOVED & CONNECTER W2J4 WAS BURNED, & WIRING DAMAGED.  IT SHOULD BE NOTE	D THAT WIRING IN CLOSE PROXIMITY TO OXYGEN LINES.  SYS DISABLED UNTIL FURTHER INVESTIGATION COMPLETED.  FOLLOWING DAY AF	T PORTION OF LIGHTING DISCONNECTED & DEFERRED FOR PARTS AVAILABILITY, FRONT PORTION REMAINS OPERATIONAL.  CONSULTED WITH	 RAYTHEON WHO ADVISED THAT SYS HAD 3000 VOLTS, & THAT CONNECTOR DAMAGE COMMON WHEN CONNECTERS ARE MISHANDLED DURING ASSY	.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005042000093	20050420	00093	CE  	2005	4	20	CA050120012      	1	20050118	G	2752	C1450046	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP ACTUATOR MAKING NOISE DURING FLAP OPERATION.  PRIMARY FLAP MOTOR LOADING THROUGH PARTIAL TRAVEL OF FLAPS.  SE	CONARDY FLAP SYSTEM WOULD NOT EXTEND OR RETRACED FLAPS BUT MOTOR STILL RUNNING.  FLAP ACTUATOR/MOTOR ASSEMBLY REMOVED AN	D UPON INSPECTION FOUND DRIVE GEARS WORN AND SECONARDARY MOTOR DRIVE SHEARED.  SUPECT WORN GEARS BINDING AND LOAD STRESS	 ON FLAP MOTORS.  NEW FLAP MOTOR ASSEMBLY INSTALLED, TESTED SERVICABLE AND AIRCRAFT RETURNED TO SERVICE.			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005042000094	20050420	00094	EU  	2005	4	20	CA050120013      	1	20050112	G	6230	350A37118101	SWASHPLATE      			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A DAILY INSPECTION, WITH THE COLLECTIVE CONTROL RAISED, AME NOTICED THAT PROTECTIVE TEFLON TAPE WAS MISSING	 ON THE SWASHPLATE GUIDE (SEVERAL SQUARE INCHES IN AREA, FROM 7:30 O'CLOCK TO 2:00 O'CLOCK).   CORRESPONDING WEAR STEP O	F APPROXIMATELY .040 INCH HAS BEEN FOUND ON GUIDE'S SURFACE.  THE WEAR HAS BEEN CAUSED BY THE BALL RING (UNIBALL) RUBBIN	G ON BEAR SURFACE OF THE GUIDE.  THE SWASHPLATE GUIDE HAS BEEN REPLACED AND A/C RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005042000095	20050420	00095	CE  	2005	4	20	CA050121001      	1	20050120	G	3397		CONNECTOR       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LANDING LIGHT	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT LND LIGHT WOULD NOT EXTING. (RELAY STUCK (ON)).  RELAY WAS REPLACED, FAULT STILL PERSISTED,  (SHORT) DISCOVERED	 TO X2.  (COIL GROUND) TERM OF RELAY. BETWEEN RT GEAR WHEELWELL CNTR P/J 64 PIN W, RELAY TERM X2. WHEN P/J 62 WAS DISCON	TD PIN SMALL (E) AND WIRE L590C16 SHOWED SIGNS OF OVERHEAT.  PIN WAS HEAT TO PREVENT EXTRACT FROM CONN, WIRE WAS DISCOLO	RED ABOUT 8 IN FROM CONN.  RELAY CONTACTS REMAINED CLOSED (RELAY ENERGISED)TO PERMIT FLOW OF DC PWR TO LIGHT IS STILL ON	-GOING. PIN WAS OVERHEAT COULD BE RELATED TO EXT ILLUMN OF LDNG LIGHT.  NOT AN INTERNAL (SHORT) IN CONN.  COIL (GROUND S	EEKING) WIRE USES PIN H OF THIS CONN , SMALL (E) PWR PIN.  RELAY AND LAND LIGHT ON/OFF SWITCH (S2) HAVE BEEN REPLACED.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005042000096	20050420	00096	WP  	2005	4	20	CA050121002      	1	20050119	G	3040		DISPLAY         			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					FLIGHT SCREEN	INOPERATIVE     	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, IT WAS OBSERVED THAT THE PRIMARY FLIGHT DISPLAY SCREEN WENT BLANK. A BURNING SMELL WAS SENSED.  THE A	IRCRAFT RETURNED TO THE GATE WITHOUT INCIDENT . THE PFD UNIT WAS REPLACED AND THE AIRCRAFT WAS RELEASED.   DURING TAXI, 	THE PFD SCREEN WENT BLANK AGAIN.  THE AIRCRAFT RETURNED TO THE GATE.  UPON FURTHER INVESTIGATION, WATER AND MOISTURE WAS	 FOUND WHICH CAUSED THE UNIT TO BECOME UNSERVICEABLE.  A LEAK WAS FOUND COMING FROM THE WIPER MOTOR AREA AND THE SEALANT	 HAD DETERIORATED. THE AREA WAS CLEANED OF ALL THE OLD SEALANT AND REPLACED.  A SERVICEABLE PFD WAS INSTALLED.  THE AIRC	RAFT WAS RELEASED WITH NO FURTHER INCIDENT DURING SUBSQUENT FLIGHT.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500068	20050425	00068	NM  	2005	4	25	CA050121003      	1	20050114	G	3411		QUICK DISCONNECT			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					PITOT LINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC ENCOUNTERED AUTOPILOT, STATIC AIR TEMP INDICATION ANOMALIES.  AUTOPILOT PITCH, ROLL COMPUTERS ALONG WITH 3 AIR 	DATA COMPUTERS (ADC). FOUND PITOT LINE QUICK DISCONNECT TO ADC HAD FAILED.  INTERNAL BARREL THAT OPENS PITOT LINE TO ADC	 HAD FAILED. LINE SEALED, WOULD NOT ALLOW PITOT PRESS TO ENTER THE ADC.  RESULTS WAS PITOT INFO USED BY ADC FOR AUTOPILO	T GAIN CNTRL, SAT CALCULATION WAS NOT AVAILABLE.  FIT NOTED THAT AIRSPEED PROBLEMS WERE NOT RECORDED AS MACH AIRSPEED IN	D WAS STRICTLY PNEUMATIC.  NOT INPUT OR SERVO FROM ADC FOR AIRSPEED INFO.  SNAG MANIFESTED ITSELF AS AUTOPILOT, SAT RELA	TED ALONE.  PITOT STATIC CKS DID NOT SHOW PRBLM FOR LEAKAGE OR AIRSPEED INFO.  LINE WAS REPLACED, AC OPERATED NORMALLY.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005042500069	20050425	00069	CE  	2005	4	25	CA050121004      	1	20050121	G	2730	0510105308	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ELEVATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNDER A ROUTINE INSPECTION, IT WAS FOUND THAT THE FORWARD STAINLESS STEEL LOWER ELEVATOR CABLE PN 0510105-308 WAS 	WEARING ON THE BULKHEAD FAIRLEAD UNDER THE FLOOR AT FUSELAGE STATION 65.33, WITH A FLAT SPOT ON THE CABLE, AND WEAR THRO	UGH 4 STRANDS.  MM PN 172RMM08, CHAPTER 27-00-01 PAGE 201 STATES THAT FOR THIS ELEVATOR CABLE, THERE SHOULD BE NO MORE T	HAN 6 BROKEN STRANDS IN A 10 INCH CABLE LENGTH.  THOUGH STILL WITHIN LIMITS, THE CABLE WAS REPLACED.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005042500072	20050425	00072	SW  	2005	4	25	CA050121006      	1	20050118	G	6310	206040106001	SPRING          	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R DRIVE SHAFT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AMN10072					(CAN) DURING A 600 HRS/ 12 MONTHS INSPECTION AND LUBRICATION, OVERHAUL TECH DISCOVERED THAT IN ONE OF THE DRIVE SHAFT CO	UPLINGS, A SPRING P/N 206-040-106-001 WAS BROKEN INTO THREE PIECES.  BROKEN SPRING PIECES WORE HEAVILY INTO PARENT MATER	IAL OF ALUMINIUM PLATE AS WELL AS INNER COUPLING.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005041200008	20050412	00008	NM  	2005	4	12	CA050121007      	1	20050107	G	2710		BEARING         	BOMBDR      		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT AIL PULLEY	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35199	35199							(CAN) DURING MAINTENANCE INSPECTION, LT AILERON CABLE PULLEY BEARING FOUND WORN AT WINGSPAR CENTER SECTION.  PULLEYS REP	LACED , CABLES RE-RIGGED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042000097	20050420	00097	SO  	2005	4	20	CA050121008      	1	20050120	G	2421	ALU8421R	ALTERNATOR      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	IO540M1A5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	ENGINE	SHORTED         	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) AN INTERNAL SHORT IN THE ALTERNATOR CAUSED THE VOLTAGE REGULATER CIRCUIT BREAKER TO POP.  DUE TO THE DESIGN OF THE	 SYSTEM, THE FAILURE WAS NOT ISOLATED TO THE FAILED SIDE.  THE PILOT TURNED OFF ALL ELECTRIC DEVICES AND LANDED AT THE N	EAREST AIRPORT.  THE AIRCRAFT WAS FERRIED TO ANOTHER AIRPORT WERE THE ALTERNATOR WAS REPLACED.				1	L	7	2 	3O	3	O		A20SO   	1E4	5	C	P9EA	 
2005042000098	20050420	00098	NE  	2005	4	20	CA050121009      	2	20050116	G	7320	7898426009	ECU             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	CORRODED        	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			42014	42014							(CAN) NR1 ENGINE, ENGINE CONTROL UNIT WOULD NOT INDICATE (ON).  MAINTENANCE FOUND CORROSION INSIDE AND OUTSIDE CONNECTOR	 J1.  ECU REPLACED. (NOTE: TIMES ARE AIRCRAFT TOTAL TIME NOT ACTUAL PART TIME)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042000099	20050420	00099	EA  	2005	4	20	CA050121010      	1	20050117	G	3297	324612CC225	WIRE HARNESS    			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			30671	30671							(CAN) DURING APPROACH, WHEN GEAR SELECTED DOWN, OB ANTISKID CAUTION LIGHT ILLUMINATED.  MAINTENANCE FOUND WIRE 32-46-12C	C22-5 SHORTED TO SHIELD  BETWEEEN 9811-P59 AND 9811-1J177 (PIN K).  WIRING REPAIRED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042000100	20050420	00100	CE  	2005	4	20	CA050124001      	1	20050117	G	3233	23271004	ACTUATOR        			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH CREW SELECTED GEAR DOWN. THE LT MLG WOULD NOT EXTENDED.  LT MLG RED GEAR UNSAFE LIGHT CAME ON.  GE	AR EMERGENCY AIR SYSTEM ACTIVATED, RED LIGHT STAYS ON.  ALTERNATE MEANS USED TO CONFIRM GEAR WERE DOWN AND LOCK.  AIRCRA	FT LANDED AND MAINTENANCE REPLACED THE LT MLG ACTUATOR.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005042500073	20050425	00073	EU  	2005	4	25	CA050124003      	1	20050120	G	2730		MOTOR           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ELEVATOR	CONTAMINATED    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, IT WAS REPORTED BY THE CREW THAT ELEVATOR PITCH CONTROL WAS VERY HARD TO OPERATE.  THE AUTO PILOT WA	S DISENGAGED AND IN MANUAL OPERATION IT WAS STILL VERY HARD TO OPERATE.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LAND	ED WITHOUT INCIDENT.  FURTHER INVESTIGATION FOUND THAT THE SERVO MOTOR AND THE CONTROL CABLES HAD EXCESSIVE BUILD UP OF 	GREASE AND MOISTURE.  THE AFFECTED AREA WAS CLEANED AND RELUBRICATED IAW SL 273 AND MM 22-11-00. THE AIRCRAFT WAS DISPAT	CHED AND NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.		2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042500074	20050425	00074	WP  	2005	4	25	CA050124004      	1	20050121	G	5280		DOOR            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					MLG	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON ARRIVAL AT GATE, THE AIRCRAFT WAS BEING INSPECTED DURING THE TURN.  IT WAS OBSERVED THAT THE LT OUTER GEAR DO	OR WAS MISSING.  NR2 BRAKE LINE LEAKING.  LOWER SIDE OF TRAILING EDGE FLAPS (F/H) DAMAGED.  BROKEN HOSE SUPPORT LINK LT 	GEAR.  BUNGEE EXTENSION SPRINGS AND BRACKETS DAMAGED.  FUSELAGE SCRATCHED BELOW L2 DOOR.  TSB WERE INVOLVED WITH THIS IN	CIDENT.  PRELIMINARY FINDINGS ARE THE AIRCRAFT DID NOT LINE UP PROPERLY WITH THE RUNWAY.  PMI INFORMED ON INCIDENT.  THE	 INVESTIGATION IS STILL UNDERWAY.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500075	20050425	00075	SW  	2005	4	25	CA050124005      	1	20050120	G	6410	222016001131	BLADE           			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					TAIL ROTOR	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR BLADE DOUBLER DEBOND ON APPROX. 6.5 IN. FROM THE TIP OF THE DOUBLER.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2005042500076	20050425	00076		2005	4	25	CA050124006      	4	20050122	G	2370	RDAV400111	RECORDER        			AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					CABIN	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) TROUBLE SHOOTING THE AFT VIDEO MONITOR NOT EXTENDING REVEALED THAT THE TAPEING UNIT WAS SHOWING SIGNS OF SMOKE DAM	AGE. CLOSER INVESTIGATION REVEALED THAT THE TAPEING UNIT HAD GIVEN OF SUFFICIENT HEAT TO CAUSE BURNING OF THE INSULATION	 BLANKET DIRECTLY ABOVE. THIS IS THE SECOND SUCH OCCURRENCE ON THIS AIRCRAFT (REF SDR 20040223001) SB 613-996-9178 DEALS	 WITH THIS PARTICULAR ISSUE BUT THE SUPPLY OF THE MODIFIED UNITS HAS BEEN SLOW. ONLY 7 UNITS HAVE BEEN MADE AVAILABLE ON	 AN EXCHANGE BASIS TO DATE WHICH IS HALF THE QUANTITY REQUIRED FOR THE AIRCRAFT. NO COMPLAINTS FROM PASSENGERS REGARDING	 SMOKE AND NO CIRCUIT BREAKERS POPPED.	2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2005042500077	20050425	00077	EU  	2005	4	25	CA050124007      	1	20050121	G	7500	30748451	TRANSFER TUBE   			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					BLEED AIR SYS	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P101120C			(CAN) TUBE FOUND SEPARATED AND PROTRUDING FROM BEHIND PANEL AT BOTTOM OF BYPASS DUCT. PIPE HAD CRACKED/FATIGUED AND SEPA	RATED AT ONE END AND IN THE MIDDLE OF AN UNSUPPORTED SECTION. THE OPEN TUBE RESULTED IN A LOW PRESSURE COMPRESSOR BLEED 	AIR LEAK THAT COULD BE SEEN IN LOSS OF TEMPERATURE MARGIN  BETWEEN LAST TWO PERFORMANCE PLOTS IN ENGINE LOG BOOK. IT IS 	SUSPECTED THE TUBE SEPARATED MORE THAN 300 HOURS PREVIOUSLY.  ENGINE WAS NOT TEMPERATURE LIMITED.  ENGINE WAS BEING REMO	VED FOR CORE OIL CARBON SEAL FAILURE.  TUBE FAILURE IS NOT CONSIDERED TO HAVE BEEN A CONTRIBUTORY FACTOR. A VIBRATION IN	SPECTION WAS REQUESTED BY MFG, IN ADDITION TO THE REPAIR THE ENGINE WAS REMOVED FOR. ENGINE FORWARDED TO O/H FACILITY .	2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2005041200017	20050412	00017		2005	4	12	CA050124008      	4	20050118	G	3422	40001728513	HSI             			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	COCKPIT	STUCK           	W				O				OTHER                   				I			FLT. ATTITUDE INST.       			AP	APPROACH       	1			CA											(CAN) NR1 HSI NEEDLE STUCK ON NORTHERN HEADING.  NR1 ENGINE STARTED TO SURGE.  ENGINE DROPPED TO 20 INCHES OF MANIFOLD P	RESSURE.  AIRCRAFT RETURNED TO BASE SAFELY.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005042000101	20050420	00101	WP  	2005	4	20	CA050124009      	1	20050122	G	3260		WARNING LIGHT   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	ILLUMINATED     	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) CREW OBSERVED NOSE GEAR LIGHT ILLUMINATED WITH THE GEAR HANDLE IN THE UP POSITION.  HEARD A GRINDING NOISE WITH VI	BRATION FELT.  THE AIRCRAFT CONTINUED AND LANDING WITHOUT INCIDENT.  NUMEROUS NOSE WHEEL RETRACTIONS/EXTENSIONS WERE CAR	RIED SUCCESSFULLY.  THE NOSE GEAR TRUNNION WAS LUBRICATED AND THE NOSE GEAR WAS FOUND SERVICEABLE IAW MM 32-30-00.  NO F	URTHER INCIDENT DURING SUBSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042000103	20050420	00103	EA  	2005	4	20	CA050124011      	2	20050109	G	7323		GOVERNOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	OVERSPEED	DEFECTIVE       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA								50153			(CAN) DURING DESCENT, ENGINE POWER COULD NOT BE REDUCED BELOW 1000 LBS TORQUE.  THE AIRCRAFT DIVERTED TO BASE AND THE PI	LOT SHUT THE ENGINE DOWN IN FLIGHT AND ACCOMPLISHED A SINGLE ENGINE LANDING.  SUBSEQUENT INSPECTION DETERMINED A DEFECTI	VE OVERSPEED GOVERNOR AS THE SOURCE OF THE PROBLEM.				1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005042100001	20050421	00001	EA  	2005	4	21	CA050124012      	2	20050114	G	7230	304865101	BLADE           	PWC         		BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COMPRESSOR	BENT            	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA						FA0160					(CAN) PILOT NOTICED AN UNUSUAL NOISE SUSPECTING A FWD CARGO DOOR SEAL PROBLEM.  ALL A/C AND ENGINE PARAMETER SEEM NORMAL	.  NOISE THEN DISAPPEARED TO CAME BACK DURING DESCENT, WITH STILL NO AIRCRAFT OR ENGINE PARAMETER VARIATION. PILOT LANDE	D A/C NORMALLY. AFTER INVESTIGATION RT ENGINE FOUND WITH ONE FIRST STAGE COMPRESSOR ROTOR BLADE BENT. SOFT FOD INSPECTIO	N C/OUT IAW AMM.  DAMAGE SUSPECTED CAUSED BY ICE DUE ICE FOUND IN NACELLE LOWER COWL.  DAMAGE FOUND WITHIN AMM, UNUSUAL 	COMPRESSOR NOISE NOT PERMITTED.  IAW MFG SL AND SPECIAL FLIGHT PERMIT AUTHORIZATION  AC WAS FERRIED BACK TO MAINT BASE F	OR RT ENGINE CHANGE.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005042000104	20050420	00104	SW  	2005	4	20	CA050124013      	1	20050117	G	3244		TIRE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	DISINTEGRATED   	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) UPON ROTATION IN APPROXIMATELY -35 DEGREE CELSIUS THE RT GEAR TIRES BLEW UP CAUSING VIBRATION AND A PULL OF THE RT	.  PILOT ABORTED TAKE OFF AND AIRCRAFT WAS TOWED OFF RUNWAY.  THE CAUSE IS LEANING TO THE BELIEF THAT THE MFG (RETREAD) 	TIRES HAVE A STIFFER SIDEWALL AND THAT AIR PRESSURES WERE NOT MAINTAINED FOR THE ENVIRONMENT THAT THEY WERE FLYING TO IN	STEAD OF THE ENVIRONMENT THAT THEY WERE LEAVING FROM.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005021500003	20050215	00003	NM  	2005	2	15	CA050125000      	1	20050123	G	2915	1849	PRESSURE VALVE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MANIFOLD	FAULTY          	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA						O409A					(CAN) THE CREW REPORTED , AFTER GEAR UP SELECTION , LOST NR 2 MAIN AND STANDBY PRESSURE (SPU ON).  AFTER APPROXIMATELY 3	 MINUTES THEY RECEIVED NR 2 STANDBY PUMP HOT LIGHT. ON SHORT FINAL NR 2 MAIN PRESSURE RETURNED BUT NR 2 STANDBY HOT LIGH	T REMAINED ON EVEN THOUGH NR 2 STANDBY PUMP CIRCUIT BREAKER WAS PULLED .  IT ONLY WENT OUT WHEN BOTH ENGINES FEATHERED A	FTER APPROXIMATELY 2 MINUTES. THE MAINTENANCE CREW AFTER TROUBLESHOOTING DETERMINED THE PRESSURE RELIEF VALVE TO BE AT F	AULT AND REPLACED .		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500078	20050425	00078	SW  	2005	4	25	CA050125001      	1	20050121	G	7712	206075739125	INDICATOR       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TORQUE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER THE AIRCRAFT WAS COLD SOAKED FOR OVER AN HOUR, THE GUAGE RESPONSE WAS VERY SLOW WHILE THE ENGINE OIL TEMP WA	S ALLOWED TO STABILIZE AT 60 DEG.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005042500079	20050425	00079	SW  	2005	4	25	CA050125002      	1	20050121	G	7712	206075739123	INDICATOR       			BELL  	206   	206L4       	1182110	SW  										TORQUE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER THE AIRCRAFT WAS COLD SOAKED FOR OVER AN HOUR, THE GAGE RESPONSE WAS VERY SLOW WHILE THE ENGINE OIL TEMP WAS	 ALLOWED TO STABALIZE AT 60 DEG.					1	G	7	1 	3U			NC	H2SW    					 
2005042000105	20050420	00105	EU  	2005	4	20	CA050125004      	1	20050123	G	3810		LINE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					GALLEY	BURST           	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) IT WAS OBSERVED BY THE FLIGHT ATTENDANTS THAT A WATER LEAK WAS FOUND COMING FROM THE FWD GALLEY AREA.  THE MANUAL 	SHUT-OFF VALVE WAS CLOSED BUT THE LEAK WAS STILL OBSERVED.  THE AIRCRAFT RETURNED TO THE GATE AND A WATER LINE UNDER THE	 FWD GALLEY HAD BURST.  THE LINE WAS REPLACED AND NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042000106	20050420	00106	EU  	2005	4	20	CA050125005      	1	20050124	G	4950		APU             			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					APU BAY	SMOKE           	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER START SEQUENCE AND COMMENCE TAXI, THE CABIN CREW OBSERVED A LIGHT SMOKE COMING THROUGH THE AIR VENT.  THE AP	U WAS SHUTDOWN WHICH SEEMED TO DISSAPATE THE SMOKE.  AS A PRECAUTION THE AIRCRAFT RETURNED TO THE GATE AND PASSENGERS DI	SEMBARKED.  MAINTENANCE STARTED THE AIRCRAFT USING A GROUND START UNIT.  NO SMOKE WAS OBSERVED AFTER START UP.  THE AIRC	RAFT WAS RELEASED AND NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042000107	20050420	00107	CE  	2005	4	20	CA050125006      	1	20050114	G	3213	57411405	LINK            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					LT MLG	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MLG WAS REMOVED FOR MODIFICATION IAW STC. NR SA00487SE. ON RE-INSTALLATION THE MLG TRAILING LINK P/N 5741140-5 - L	T WAS INSTALLED ON THE RT MLG, AND P/N 5741140-6 RT WAS INSTALLED ON THE LT MLG. THIS ERROR WAS NOT OBVIOUS DURING LANDI	NG GEAR FUNCTIONAL RETRACTION AND EXTENSION TESTING. THE GEAR RETRACTED AND LOCKED UP NORMALLY, EXTENDED AND LOCKED DOWN	 NORMALLY. THE AIRCRAFT FLEW WITH NO LOSS OF AIRSPEED OR ANY INDICATION OF AIRFRAME BUFFET DUE TO THE TRAILING LINKS HAN	GING BELOW THE WHEEL WELLS. THIS CONFIGURATION WAS REVERSED AND THE AIRCRAFT RETURNED TO SERVICE.  IT IS VERY EASY TO MA	KE THIS ASSEMBLY ERROR, WHICH RESULTS IN A LANDING GEAR CONFIGURATION MOST TECHNICIANS WOULD THINK (COULD NOT HAPPEN).	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2005042000108	20050420	00108	NM  	2005	4	20	CA050125007      	1	20050121	G	5330		SKIN            			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN OUTER FUSELAGE CRACK WAS FOUND DURING A PHASE EIGHT CHECK AT STRINGER 16L, STATION 727+14.5 APPROXIMATELY 1.5 I	NCHES IN LENGTH.  FUSELAGE CRACK REPAIRED IAW REO-L00889 REV 1R TIMES - 59761:05 HOURS AND 54470 CYCLES					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2005042000109	20050420	00109	EA  	2005	4	20	CA050125008      	1	20050119	G	5242	6003303913	ACCESS DOOR     			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					E/E BAY	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS AIRCRAFT WAS INSPECTED AND TESTED AND FOUND TO EXHIBIT UNACCEPTABLE NOSE AVIONICS ACCESS DOOR DEFORMATION IN 	EXTREME COLD CONDITIONS. THE DEGREE OF DOOR CORNER CURLING EXCEEDS THE MANUFACTURERS LIMITS FOR SKIN WAVINESS FOR RVSM C	ERTIFICATION. (THIS CONDITION WAS PREVIOUSLY IDENTIFIED SDR 20050119002)				2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2005042000110	20050420	00110	EA  	2005	4	20	CA050125009      	1	20050119	G	5242	6003303913	ACCESS DOOR     			CNDAIR	CL601 	CL6012A12   	1900303	EA  										E/E BAY	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS AIRCRAFT WAS INSPECTED AND TESTED AND FOUND TO EXHIBIT UNACCEPTABLE NOSE AVIONICS ACCESS DOOR DEFORMATION IN 	EXTREME COLD CONDITIONS. THE DEGREE OF DOOR CORNER CURLING EXCEEDS THE MANUFACTURERS LIMIT FOR SKIN WAVINESS FOR RVSM CE	RTIFICATION.  THIS CONDITION WAS PREVIOUSLY IDENTIFIED (SDR 20050119002).				2	L	7	2 	4F			RT	A21AE   					 
2005042500080	20050425	00080	NM  	2005	4	25	CA050125010      	1	20050122	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 DISCOVERED AT STRINGER S-18R, STATION 750, APPROXIMATELY 1.125 INCHES LONG.  THE CRACK	 WAS REPAIRED IAW SRM 53-30-3 FIGURE 48, DETAIL IX AND DETAIL XIX.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005042500081	20050425	00081	EA  	2005	4	25	CA050125011      	1	20050119	G	5242	6003303913	DOOR            			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502*     	41580	EA  					E/E BAY	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS AIRCRAFT WAS INSPECTED, TESTED AND FOUND TO EXHIBIT UNACCEPTABLE NOSE AVIONICS ACCESS DOOR DEFORMATION IN EXT	REME COLD CONDITIONS.  THE DEGREE OF DOOR CORNER CURLING EXCEEDS THE MFG LIMIT FOR SKIN WAVINESS FOR RVSM CERTIFICATION.	  THIS CONDITION WAS PREVIOUSLY IDENTIFIED ON AIRCRAFT 144614, (SDR 20050119002).				2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2005042500082	20050425	00082	CE  	2005	4	25	CA050125012      	1	20050121	G	3246	1368520629	BEARING         	BFGOODRICH  		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	WHEEL ASSY	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA						APR921876					(CAN) AIRCRAFT DEPARTED ENROUTE AT TEMPERATURE AT  5 DEG C.  AIRCRAFT ARRIVED WITHOUT ANY INCIDENT, WHEN AIRCRAFT WAS AT	 THE PAX TERMINAL IT WAS NOTICED THAT THE RT OB MAIN WHEEL ASSEMBLY WAS MISSING.  INSPECTION REVEALED THAT THE WHEEL BEA	RINGS HAD DISINTEGRATED AND ALLOWED THE WHEEL ASSEMBLY TO FALL OFF THE WHEEL AXLE.  THE WHEEL ASSEMBLY WAS FOUND ON THE 	RUNWAY AT ORIGINATING AIRPORT.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005042500083	20050425	00083	CE  	2005	4	25	CA050125013      	1	20050120	G	8011	535539	BEARING CAGE    			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	STARTER ADAPTER	DISINTEGRATED   	W				E				ENGINE SHUTDOWN         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		IN	INSP/MAINT     	1			CA											(CAN) ATTEMPT TO START RT ENGINE AT EXTREME COLD TEMP.   ENGINE BACKFIRED, STARTER ADAPTER SHAFT BRG CAGE DISINTEGRATED,	 SHAFT OIL SEAL BLEW.					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
2005042500084	20050425	00084	WP  	2005	4	25	CA050125014      	1	20050111	G	5250	AM767BA	LATCH           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LAVATORY DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE IN FLT, A PERSON WENT TO THE FWD LAVATORY, ONCE INSIDE, WAS UNABLE TO OPEN DOOR.  DOOR HANDLE WOULD TURN, BU	T DOOR REMAINED CLOSED. PERSON WAS BASICALLY STUCK INSIDE. CAPTAIN AUTHORIZED CABIN CREW TO USE CRASH AXE IN ORDER OPEN 	THE DOOR.  FORWARD LAVATORY WAS PUT ON MEL. LATER, MAINTENANCE REMOVED THE DOOR AND REMOVED THE DOOR HANDLE MECHANISM. I	T WAS FOUND THAT THE DOOR LOCK SLIDER PLATE WAS BROKEN, MAKING IT POSSIBLE FOR THE DOOR LOCK SLIDER LEVER TO COME OUT OF	 THE SLIDER LOCK PLATE, THE DOOR BEING IN THE CLOSED POSITION (SLIDER LOCK PLATE ENGAGED IN THE DOOR FRAME RECEPTACLE) M	AKING IT IMPOSSIBLE TO OPEN THE DOOR BY  ROTATING THE DOOR HANDLE.  MX REPLACED THE DOOR ASSY.	2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042000111	20050420	00111	EA  	2005	4	20	CA050125016      	1	20050122	G	5730	8711802005	PANEL           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	WING	LOOSE           	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA			31794								(CAN) DURING ROUTINE MAINTENANCE INSPECTION VISUALLY NOTICED SCREW HEADS PROTRUDING ABOVE WING SURFACE ON WING STRESS PA	NEL (DRYBAY ACCESS). APPROXIMATELY 50 PERCENT OF THE ATTACH SCREWS (CSP318-5) WERE FOUND LOOSE ON ACESS PANEL NR 522AT, 	ALSO SOME LOOSE SCREWS FOUND ON DRYBAY/WING CENTER BOX ACESS PANELS 521AT AND 622AT.  AIRCRAFT HAS APPROX. 1980-2372 CYC	LES SINCE PREVIOUS RE-TORQUE OF THESE SCREWS AFTER MAINTENANCE ACCESS. ALL SCREWS ON THESE PANELS RE-TORQUED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042000112	20050420	00112	SW  	2005	4	20	CA050125017      	1	20050125	G	6710	212001181001	COLLECTIVE STICK			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					THROTTLE GRIPS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28648								(CAN) THE ENGINEER WAS ABOUT TO GREASE THE SWASHPLATE. TO GREASE SOME OF THE ZERK FITTINGS IT IS EASIER TO LIFT THE COLL	ECTIVE CONTROL STICK UP.  THE ENGINEER WAS MOVING THE COLLECTIVE CONTROL STICK UP WHEN THE RIDGED TUBE BENT AND BROKE IN	 TWO.  THE BREAKAGE OCCURED BETWEEN THE TWO THROTTLE GRIPS WHERE THERE IS A SLOT IN THE TUBE FOR THE THROTTLE CONTROL.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005042000113	20050420	00113	NE  	2005	4	20	CA050126001      	2	20050112	G	7200		ENGINE          			AIRTRC	AT400 	AT402A      	0390206	SW  	PWA   	PT6   	PT6A11AG    	52043	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SPRAYING RUN, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE AIRCRAFT CLIPPED TREES AND IMPA	CTED THE GROUND.  MFG WILL PARTICIPATE IN THE INVESTIGATION OF THE INCIDENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE R	OOT CAUSE, ONCE ESTABLISHED.				1	L	7	1 	3T	3	T	NC	A17SW   	E4EA				 
2005042000114	20050420	00114	GL  	2005	4	20	CA050126002      	1	20050125	G	2910	9555805	PUMP            			BOMBDR	BD700 	BD7001A10   	1390006	GL  										HYD SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) FOR THE RELIGHT PROCEDURES FOR THE RT ENGINE, THE RT HYD DCMP HAD BEEN TURNED ON PRIOR SHUTDOWN.  AFTER 5 MINUTES 	OF DRIFT DOWN AT 185 KTS, AROUND 40000 FT, AP SYNC WAS PRESSED AND ACCELERATED TO 250.  SOMEWHERE AROUND THAT TIME, THE 	LT GEN DROPPED OFF LINE AND WE WERE LEFT WITH ESSENTIAL POWER ONLY (ALSO LOSS OF YAW DAMPER).  THE PNF WENT THRU THE QRH	 AND RESET THE LT GEN, THEN POWER WAS RESTORED, LEAVING A CYAN ELECTRICAL FAULT MSG.  ALSO THE RT HYD DCMP HAD FAILED FO	R GOOD.  A/C LANDED WITHOUT FURTHER INCIDENT.		2	L	7	2 	4F			RT	T00003NY					 
2005042000115	20050420	00115	SO  	2005	4	20	CA050126003      	2	20050125	G	8530	654004	EXHAUST VALVE   			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	CORRODED        	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								635636A			(CAN) POOR ACCELERATION AND SLUGGISH PERFORMANCE DURING POWER UP AND DIFFERENT POWER SETTINGS. WHEN APPLYING POWER, ENGI	NE STUMBLED.  INITIALLY SUSPECTED CARB ICING BUT GROUND CHECK RESULTED IN SAME FAILURE TO PRODUCE POWER. PRELIMINARY D/P	 CHECK SHOWED LOW POWER ON 3 OF 4 CYLINDERS (42-52 PSI) CYLINDERS DISMANTLED AND FOUND EXHAUST VALVES CORRODED AND DETER	IORATED REF: SB M90-13. THIS SB SUGGESTS THAT VALVE STEMS, AT TIME OF OVERHAUL, SHOULD REQUIRE 100% REPLACEMENT. THIS IS	 THE SECOND FIELD EXPERIENCE OF SEVERE CORROSION 400+ HOURS PRIOR TO OVERHAUL.		1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2005042000116	20050420	00116	NE  	2005	4	20	CA050126004      	2	20050117	G	7321	81850012	FCU             			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED INFLIGHT SHUTDOWN FOLLOWING POWER REDUCTION FOR DESCENT.  A RELIGHT ATTEMPT 	WAS UNSUCCESSFUL. SUBSEQUENT INSPECTION REVEALED A MALFUNCTIONING FUEL CONTROL UNIT.  MFG WILL INVESTIGATE THE INCIDENT 	AND WILL SUPPLIMENT THIS REPORT TO REFLECT ROOT CAUSE, ONCE ESTABLISHED.				1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005042500085	20050425	00085	NE  	2005	4	25	CA050126005      	2	20050114	G	7200		BLADES          								PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA								PC0592			(CAN) ON LANDING ENGINE TEMPERATURE WAS SEEN TO INCREASE,  FOLLOWED BY AN UNCOMMANDED REDUCTION IN POWER.  SUBSEQUENT IN	SPECTION REVEALED COMPRESSOR TURBINE AND POWER TURBINE BLADE DAMAGE.  MFG WILL MONITOR THE INVESTIGATION OF THE INCIDENT	 AND WILL SUPPLIMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERMINED.									3	T			E4EA				 
2005042500086	20050425	00086	NM  	2005	4	25	CA050126006      	1	20050119	G	7600	87620130101	SPRING STRUT    			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1 ENGINE	BROKEN          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		TX	TAXI/GRND HDL  	1			CA			14368								(CAN) NR 1 ENGINE SHUTDOWN ON GROUND RUN DUE TO BROKEN CONTROL SPRING STRUT.  UNABLE TO CONTROL THE ENGINE, SHUTDOWN BY 	THE TEE HANDLE.  MFG IS INVESTIGATING THE EVENT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500087	20050425	00087	NE  	2005	4	25	CA050126007      	2	20050119	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  						FLUCTUATES      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								120602			(CAN) THE ENGINE EXPERIENCED TORQUE FLUCTUATIONS IN CRUISE FOLLOWED BY AN UNCOMMANDED REDUCTION IN PROPELLER SPEED TO 12	 PERCENT.  THE PILOT SHUT THE ENGINE DOWN AND DIVERTED THE FLIGHT.  MFG WILL MONITOR THE INVESTIGATION OF THE INCIDENT A	ND WILL SUPPLIMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005041200022	20050412	00022	CE  	2005	4	12	CA050126008      	1	20050122	G	3297	MS3126F1210P	CONNECTOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	CORRODED        	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH CREW SELECTED GEAR DOWN HOWEVER, THE GEAR CONTROL C/B OPENED AND WOULD NOT RESET.  MANUAL EXTENSIO	N COMPLETED.  MAINTENANCE FOUND THE CONNECTOR BEWTEEN THE NOSE GEAR ACTUATOR AND THE FRAME INTERNALLY CORRODED. THE CONN	ECTOR WAS REPLACED, GEAR SWUNG AND THE AIRCRAFT RELEASED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005042000117	20050420	00117	NE  	2005	4	20	CA050126009      	2	20050124	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								CA0319			(CAN) IN CRUISE, THE ENGINE OIL PRESSURE REDUCED ACCOMPANIED BY A LOW OIL PRESSURE INDICATION.  THE PILOT SHUT THE ENGIN	E DOWN, DECLARED AN EMERGENCY AND DIVERTED THE FLIGHT.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE. MFG WILL IN	VESTIGATE THE EVENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005042000118	20050420	00118	NE  	2005	4	20	CA050126010      	2	20050120	G	7200	CF7002D2	ENGINE          			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					NR 1	FOD             	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			CA								304415B			(CAN) WHILE DOING THE DAILY INSPECTION, TECHNICIAN NOTICED SUBSTANTIAL FOREIGN OBJECT DAMAGE TO THE BYPASS FAN AND THE F	IRST STAGE COMPRESSOR BLADES OF THE ENGINE INSTALLED IN POSITION NR 1.  AIRCRAFT HAD JUST COMPLETED 9.6 HOURS OF FLYING 	WITHOUT ANY INDICATION OF POWER LOSS.  AIRCRAFT LANDED, THE FREIGHT WAS OFF LOADED AT THE FACILITY.  AIRCRAFT ENGINES WE	RE STARTED AND THE AIRCRAFT WAS TAXIED BACK TO THE HANGAR FOR ROUTINE MAINTENANCE.  ENGINE WAS REMOVED AND RETURNED FOR 	INVESTIGATION AND REPAIR.		2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2005042000119	20050420	00119	CE  	2005	4	20	CA050126011      	1	20050120	G	3233	11238002223	ACTUATOR        			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	NLG	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) NOSE LANDING GEAR WOULD NOT EXTEND UPON DESCENT INTO AIRPORT.  EMERGENCY GEAR EXTENSION PROCEDURE COMPLETED AND TH	E AIRCRAFT LANDED SAFELY.  NOSE LANDING GEAR ACTUATOR WAS REPLACED, FOLLOWED BY SEVERALGEAR SWINGS IN NORMAL AND EMERGEN	CY MODES.  GEAR GROUND CHECKED SERVICEABLE AND AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005042000120	20050420	00120	EU  	2005	4	20	CA050127001      	1	20050127	G	2150		ODOR            			AIRBUS	A340  	A340*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					AIR CONDITIONING	DETECTED        	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN)  IN CRUISE LOUD GRINDING NOISE HEARD MID GALLEY, AFT J CLASS.   AIRCRAFT FILLED WITH ACRID SMELL.   AFT AND MID CA	BINS FILLED WITH SMOKE.  SMELL AND SMOKE LASTED ONE TO TWO MINUTES.  ALL SYSTEMS INDICATED NORMAL.  PACK FLOW SET TO HIG	H FOR 15 MINS.  SMELL FOUND COMING FROM MID GALLEY AIR COOLER.  CHILLER DE-ACT AND AIRCRAFT DISPATCHED UNDER MEL.  NOTE:	 FURTHER INFO WILL FOLLOW AS AVAILABLE.			2	L	7	4 	4F	4	F	RT	A197    	A12EU				 
2005042500088	20050425	00088	CE  	2005	4	25	CA050127002      	1	20050124	G	5520	956100054	CONTROL HORN    			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SHEET METAL REPAIR OF THE RT ELEVATOR ASSY IT WAS NOTED THAT THE ELEVATOR SKIN AT THE CONTROL HORN ATTACH P	OINT WAS CRACKED. FURTHER INSPECTION OF THE CONTROL HORN ASSY REVEALED A LARGE CRACK PROGRESSSING FROM 1 OF 4 ELEVATOR T	O CONTROL HORN MOUNTING BOLTS.  CRACK LENGTH WAS APPROXIMATLY 1 INCH.  THE ELEVATOR CONTROL FITTING WAS REPLACED.  A FLE	ET INSPECTION WAS CARRIED OUT USING VISUAL AND EDDY CURRENT INSPECTION AND NO FURTHER DEFECTS WERE FOUND ON ANY AIRCRAFT	.		1	L	7	2 	3O	3	O		3A16    	1E10	5	C	P920	 
2005042500089	20050425	00089	NE  	2005	4	25	CA050127003      	2	20050117	G	7261	310047001	ELBOW           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENG OIL LINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA			12780					PS0218			(CAN) IMMEDIATELY AFTER STARING DESCENT, CREW NOTED OIL PRESSURE DROPPING FOLLOWED BY WARNING ANNUCIATORS ON LT POSITION	.  ENGINE CONTINUED TO LOSE OIL PRESSURE AND ENGINE WAS SHUTDOWN AND FEATHERED.  MAINT FOUND OIL BOSS (ELBOW) FOR REDUCT	ION GEAR CASE RETURN OIL LINE HAD FRACTURED THROUGH 1 OF 2 ATTACHING BOLT HOLES AND HEAD OF 1 BOLT WAS DETACHED FROM STU	D PORTION. HEAD WAS RETAINED BY SAFETY WIRE.  IT WAS UNCERTAIN AS TO WHY THE BOSS HAD FRACTURED SO ENGINE WAS REPLACED F	OR PRECAUTIONARY REASONS.  ENGINE HAS SINCE BEEN CHECKED AND IS IN NORMAL OPERATING CONDITION LEADING TO  DETERMINATION 	THAT BOSS AND/OR ATTACHING BOLTS SIMPLY FAILED AND WAS NOT CAUSED BY OIL PRESSURE SPIKES OR.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005042500090	20050425	00090	EA  	2005	4	25	CA050127004      	1	20050126	G	3320	AL1235T490	LAMP            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					GALLEY LIGHT	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) UPON LANDING THE CREW WHILE WORKING IN THE GALLEY AREA CLEANING UP NOTICED A BURNING ODOR.  AFTER OPENING A SLIDIN	G DOOR IN THE GALLEY THE FUMES BECAME STRONGER.  MAINTENANCE REMOVED THE LIGHT COVER AND FOUND THE END OF THE BULB HAD B	ECOME HOT AND DISCOLORED. NO SMOKE WAS SEEN DURING THE PROBLEM. THE BULB DOES HAVE A MELT SPOT ON THE GLASS THAT MAY BE 	FROM MANUFACTURING BUT AM UNSURE. CHECKED POWER SUPPLY AND INSTALLED NEW LAMP, AND SYSTEM OPERATED NORMALY WITH NO FURTH	ER PROBLEMS.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005042500091	20050425	00091	NE  	2005	4	25	CA050127005      	2	20050120	G	7200		SEAL            								PWA   	JD15  	JT15D1A     	 	NE  					ENGINE	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA								76094			(CAN) CAUSE OF SMOKE ODOR IN CABIN DUE TO OIL CONTAM OF GAS PATH AIRFLOW  DUE TO A LARGE NR OF AIR/OIL SEALS HAD EXCESSI	VE CLEARANCES, ALLOWING OIL TO ENTER SECONDARY AIR SYS. ENG DID HAVE A SIGNIFICANT AMOUNT OF FRETTING DAMAGE ON COMBUSIO	N COMPONENTS, WHICH INDICATED THAT ENG OPERATED WITH VIBRATION FOR SOME TIME.  RETURNED ENG TO SERVICE, ALL WORN AIR SEA	LS WILL BE REPAIRED/REPLACED BACK TO THE O/H MANUAL LIMITS.  NR 4 BEARING HOUSING WILL HAVE ALL PACKINGS & GASKETS CHANG	ED TO ENSURE NO FURTHER LEAK. FIT BETWEEN LOW COMPRESSOR SHAFT & LOW TURBINE SHAFT WILL BE RESTORED TO AVOID TO POSSIBIL	ITY OF VIBRATION PROBLEMS. ENG WILL BE TESTED.						4	F			E25EA				 
2005042500092	20050425	00092	CE  	2005	4	25	CA050127006      	1	20050127	G	2121	09040022	BLADES          			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	BLOWER	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA						0252					(CAN) FAN BLADE FAILURE, BLADE BROKEN OFF FROM SPINNER, OCCURRED 3 TIMES.    (TSN 4904 HOURS  METAL BLADE)  (TSN  657 HO	URS  PLASTIC BLADE)  (TSN  258 HOURS  PLASTIC BLADE)					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	5	C	P60GL	 
2005041200023	20050412	00023	CE  	2005	4	12	CA050127007      	1	20050125	G	2910	1015800241	LINE            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	UNSERVICEABLE   	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FLUID LEAKING OUT OF THE LT IB L/E.  L/E REMOVED AND FOUND RIGID HYDRAULIC BRAKE LINE CHAFFED THROUGH BY	 ENGINE CONTROL CABLES ABOVE HEAT EXCHANGER. REPLACED LINE. ALL COMPANY AIRCRAFT USING THIS HYDRAULIC LINE VISUALLY INSP	ECTED AND FOUND DAMAGE ON ALL RANGING FROM MINOR TO MAJOR. BOTH LT P/N 101-580024-1 AND RT P/N 101-580025-1 LINES EFFECT	ED.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005042000121	20050420	00121	NE  	2005	4	20	CA050128001      	2	20050127	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF, THE CREW OBSERVED NR 2 ENGINE EPR GAUGE NOT WORKING.  TAKE-OFF WAS REJECTED AND AIRCRAFT RETURNED	 TO THE GATE.  NR 2 ENGINE EPR DEFERRED IAW MEL 77-1 AND DMI NR 10956 RAISED.  ALL OTHER ENGINES PARAMETERS NORMAL.  AIR	CRAFT RELEASED AND NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042000122	20050420	00122	NM  	2005	4	20	CA050128002      	1	20050128	G	3340	2401	CONTROL UNIT    			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	PULSE LIGHT	MALFUNCTIONED   	W				K				NONE                    				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) THE TECH WAS WORKING ON A DEICE PROBLEM AND WHILE STANDING OUTSIDE THE AC SUDDENLY SAW THE PULSELITE START WORKING	 ON THERE OWN.  HE WENT IN THE AC AND SAW THAT THE PULSELITE SWITCH WAS NOT TO THE ON POSITION. HE CLOSED THE POWER TO T	HE AC.  HE WENT TO THE PULSELITE CONTROL UNIT AND  NOTICED A BURNED ODOR.  HE WENT TO TOUCH THE PULSELITE CONTROL BOX BU	T IT WAS VERY HOT AND COULD NOT TOUCH IT. NOTE: THE TECHNICIAN HAD REMOVED THE GROUND WIRE AND THE PULSELITE CONTROL BOX	 TO GAIN ACCESS TO ANOTHER BOX ON A SYSTEM THAT HE WAS WORKING ON.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042000123	20050420	00123	SO  	2005	4	20	CA050128003      	1	20050118	G	5320	4070200	CHANNEL         	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							317852128				(CAN) CHANNEL FOUND CRACKED AT FWD DOOR HINGE ATTACH POINT. A 2.5 INCH CRACK RUNNING PARALELL WITH THE CHANNEL UPPER RAD	IUS ABOVE HINGE PLATE AIRFRAME PORTION.  CHANNEL REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005042000124	20050420	00124	NE  	2005	4	20	CA050128004      	2	20050124	G	7230		ENGINE          			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA								666056			(CAN) DEPARTING, THE NR2 ENGINE PERAMETERS BECAME ERRATIC ASSOCIATED WITH A LOUD REPORT, BELIEVED TO BE A COMPRESSOR STA	LL. THE AIRCRAFT LANDED WITHOUT INCIDENT AT POINT OF DEPARTURE.  MAINTENANCE FOUND THE NR2 ENGINE TO HAVE SUFFERED SEVER	E INTERNAL DAMAGE TO THE TURBINE SECTION.				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005042000125	20050420	00125	NM  	2005	4	20	CA050128005      	1	20050128	G	2121	731376	COOLING FAN     			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					E/E BAY	BINDING         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) CREW NOTICED A BURNING SMELL THROUGHOUT AIRCRAFT AND THEN HAD AN EICAS MESSAGE (EQUIPMENT OVERHEAT) . MAINTENANCE 	CONFIRMED FWD EQUIPMENT COOLING FAN BINDING AND A BURNT SMELL COMING FROM UNIT.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005042000127	20050420	00127	SW  	2005	4	20	CA050128008      	1	20050125	G	2612	17343450F	FIRE DETECTOR   			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT NACELLE	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) PILOT CALLED AND NOTIFIED MAINTENANCE THAT ON APPROACH THE LT FIRE WARNING LIGHT CAME ON.  LIGHT WENT OUT WHEN INL	ET HEAT WAS TURNED OFF.  MAINTENACE INSPECTED AIRCRAFT AND FOUND NO SIGNS OF HEAT DISTRESS. TOP FIRE DETECTOR WAS REPLAC	ED AND GROUND CHECKED SERVICIBLE.  NO OTHER REPORTED INCIDENTS SINCE THEN.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005021500007	20050215	00007	NM  	2005	2	15	CA050128009      	1	20050127	G	3242		DISK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	BRAKE ASSY	SEIZED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			14693			0410					(CAN) AFTER STARTED AIRCRAFT, RELEASED PARK BRAKE AND TAXIED NORMALLY , BRAKING AS REQUIRED, DUE TO LONG LINE UP AWAITIN	G TAKEOFF PARK BRAKE WAS APPLIED. WHEN PART BRAKE WAS RELEASED AIRCRAFT UNABLE TO TAXI.  MAINTENANCE INSPECTION FOUND BR	AKE PISTONS WERE RELEASING USING TOE BRAKES OR PARK BRAKE, BUT BRAKE DISKS ON THE NR3 AND NR4 BRAKES WERE SEIZED AND WOU	LD NOT ROTATE.  BOTH NR3 AND NR4 BRAKE ASSEMBLIES REPLACED.  NR3 BRAKE S/N 0410 HAD 88CY SINCE OVERHAUL (BUILD NR1) CARR	IED OUT.  NR4 BRAKE S/N 3120P HAD 208CY SINCE OVERHAUL (BUILD NR1) CARRIED OUT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500093	20050425	00093	SO  	2005	4	25	CA050130001      	1	20050125	G	3220	AN17413	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) WHEN THE NOSE WAS LOWERED DURING LANDING, A SEVERE VIBRATION DEVELOPED WHEN THE NOSE TIRE TOUCHED THE RUNWAY.  STE	ERING WAS NOT AVAILABLE BUT DIRECTIONAL CONTROL WAS MAINTAINED WITH RUDDER.  AS THE AIRCRAFT SLOWED, THE VIBRATION EASED	 UP. TURNING TO EXIT THE RUNWAY WAS ACCOMPLISHED BY DIFFERENTIAL ENGINE POWER.  WHEN THE AIRCRAFT WAS SHUTDOWN IT WAS DI	SCOVERED THE BOLT HOLDING THE UPPER AND LOWER NOSE SCISSOR LINKS TOGETHER WAS MISSING AND THE LINKS WERE OPEN.  SINCE TH	E PARTS WERE NOT FOUND IT COULD NOT BE DETERMINED WHICH PART FAILED, THE BOLT, THE NUT OR THE LOCKING PIN.  DAMAGE WAS L	IMITED TO THE TIRE.  NEW HARDWARE WAS INSTALLED.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005042500094	20050425	00094	SW  	2005	4	25	CA050130002      	1	20050130	G	6720	DW4	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13427								(CAN) UPON INSPECTION OF THE LONG TAIL ROTOR PITCH CHANGE TUBE THE WALKING BEAM WAS OBSERVED TO BE A LITTLE RATCHETY TO 	ROTATE EVEN THOUGH IT ONLY ROTATES ABOUT 30 DEGREES OF TRAVEL.  UPON THIS INSPECTION THE PART WAS REMOVED AND FURTHER IN	SPECTED.  THE BEARING WAS ROTATED IN ORDER TO FREE IT UP AND AS MOVEMENT PROGRESSED IT GOT TIGHTER AND FINALLY SEIZED.  	TOOK THE WALKING BEAM TO A MFG SERVICE CENTER FOR BEARING REPLACEMENT AND EVEN THOUGH MFG SHOWS THE PART IN THE IPC. THE	 BEARING IS NOT A REPLACEABLE ITEM.  A NEW WALKING BEAM WAS ORDERED AND WILL BE INSTALLED.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005042500095	20050425	00095	SW  	2005	4	25	CA050131001      	1	20050128	G	2612	1734361450	FIRE DETECTOR   			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311U    	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	FAULTY          	W				F	E	C		ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         	ABORTED TAKEOFF         		N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) PILOT HAD A LT FIRE LIGHT COME ON SHORTLY AFTER TAKEOFF.  LT ENGINE WAS SHUTDOWN AND FIRE BOTTLE WAS ACTIVATED.  A	IRCRAFT THEN RETURNED TO AIRPORT.  MAINTENANCE INSPECTED FIRE DETECTION SYSTEM AND FOUND THE FIREWALL FIRE DETECTOR FAUL	TY.  FIRE DETECTOR WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
2005042500096	20050425	00096	SO  	2005	4	25	CA050131002      	1	20050127	G	3230	4179702	UPLOCK HOOK     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLIGHT CREW INDICATED LANDING GEAR INTRANSIT LIGHT.  THE GEAR WAS CYCLED ONE MORE TIME WITH FAILED ATTEMPT.  FLIGH	T CREW RETURNED AND LANDED.  MAINTENANCE WAS DISPATCHED AND FOUND THE NOSE GEAR UPLOCK HOOK STUCK IN DOWN POSITION.  WHE	N NOSE GEAR RETRACTED, THE UPLOCK ROLLER BENT THE UPLOCK HOOK AND TUBE ASSY,  UNABLING IT TO LOCK UP AND SECURE.  NEW TU	BE IDLER ASSY WITH UPLOCK HOOK ASSY REPLACED.  NUMEROUS GEAR SWING C/W.  ALL CHECKED SERVICEABLE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005042500097	20050425	00097	SO  	2005	4	25	CA050131003      	1	20050127	G	3230	4179703	UPLOCK HOOK     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MLG	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLIGHT CREW WAS UNABLE TO SECURE LANDING GEAR IN UP POSITION. THE FLIGHT RETURNED FOR SAFE LANDING.  MAINTENANCE W	AS DISPATCHED AND FOUND THE LT GEAR UP LOCK HOOK STUCK AND FROZEN IN THE UP POSITION.   ASSY WAS DISASSEMBLED, MOISTURE 	REMOVED, CLEANED AND LUBED AND REASSEMBLED. NUMEROUS GEAR SWINGS PERFORMED, ALL CHECK SVC.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005041200025	20050412	00025	EU  	2005	4	12	CA050131004      	1	20050115	G	2435	23079009	STARTER GEN     			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	FAILED          	W				O				OTHER                   				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) GENERATOR WENT OFF LINE, SMOKE AND OIL VISUAL ON COWLING.						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2005042000128	20050420	00128	NE  	2005	4	20	CA050131005      	2	20050122	G	7313		PACKING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					FUEL NOZZLE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								AA0031			(CAN) DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER.  THE PILOT SHUT THE ENGINE DOWN IN FLIGHT	.  SUBSEQUENT INVESTIGATION REVEALED A DAMAGED FUEL NOZZLE TUBE PACKING.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2005042000129	20050420	00129	WP  	2005	4	20	CA050131006      	2	20050119	G	7200		ENGINE          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  		FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA								P63145			(CAN) ENGINE FAILED IN FLIGHT, AIRCRAFT HAD JUST EXITED ICING CONDITIONS, CONTINUOUS IGNITION WAS TURNED OFF A FEW MINUT	ES PRIOR TO ENGINE FAILURE. AIRCRAFT RETURNED TO BASE AND ENGINE WAS INSPECTED FOR ANY CAUSE OF THE FAILURE, NOTHING WAS	 FOUND.  GROUND/POWER RUNS WERE CARRIED OUT AND FOUND SERVICEABLE, CONDITIONAL MAINTENANCE RELEASE WAS SIGNED FOR A TEST	 FLIGHT. TEST FLIGHT WAS CARRIED OUT AND AIRCRAFT RETURNED TO BASE WITH ALL ENGINE PARAMETERS WITHIN LIMITS.			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2005042000130	20050420	00130	EU  	2005	4	20	CA050131007      	1	20050111	G	7900		ENGINE          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  		FAILED          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA								P63243			(CAN) SOAP SAMPLE INDICATED MAJOR ALUMINIUM IN THE OIL SYSTEM, 2ND SOAP SAMPLE TAKEN AND FOUND MAGNESIUM AND CARBON STEE	L PARTICLES IN THE SAMPLE. ENGINE REMOVED AND SENT FOR EVALUATION, AMO 50-04.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2005042000131	20050420	00131	EU  	2005	4	20	CA050131008      	1	20050131	G	3246	FN22A524	NUT             			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					MLG WHEEL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						KR083					(CAN) AFTER ARRIVAL TO BASE OF OPERATIONS DURING A POST FLIGHT INSPECTION NR 2 MAIN WHEEL ASSY.  A WHEEL TIE BOLT NUT WA	S FOUND MISSING AND ANOTHER 180 DEGREES APART WAS FOUND SPLIT.  WHEEL WAS CHANGED.  THESE NUTS WERE INSTALLED NEW AS THA	T IS OUR POLICY.  MFG HAS BEEN NOTIFIED AS THE NUTS WERE PURCHASED FROM THEM.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005042000132	20050420	00132	NE  	2005	4	20	CA050131009      	2	20050122	G	7200		ENGINE          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  						SHUTDOWN        	W				O	E			OTHER                   	ENGINE SHUTDOWN         			O			OTHER                     			CR	CRUISE         	1			CA								123145			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK IN CRUISE (ZERO TORQUE INDICATED).THE PILOT DECLARED AN EMER	GENCY AND SHUT THE ENGINE DOWN IN FLIGHT.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL SUPPLEMENT THIS REPORT T	O PROVIDE ROOT CAUSE, ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005042500098	20050425	00098	NE  	2005	4	25	CA050201001      	2	20050126	G	7250		TURBINE         								PWA   	JD15  	JT15D1A     	 	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								76492			(CAN) ENGINE WAS FOUND TO HAVE SUSTAINED A MAJOR INTERNAL FAILURE WITH EXTENSIVE DAMAGE TO THE IMPELLER AND THE ENTIRE T	URBINE SECTION OF THE ENGINE.  EVIDENCE OF A FAILED NR 2 BEARING, AN HP VANE ASSEMBLY WITH EXTENSIVE BURNING AND LOSS OF	 MATERIAL, AN HP TURBINE WITH FRACTURED AIRFOILS, AND AN LP TURBINE MISSING ALL OF THE FIRST STAGE ROTOR BLADES, THE PRI	MARY FAILURE IS NOT IMMEDIATELY OBVIOUS AND THE POSSIBILITY OF COINCIDENTAL FAILURES EXISTS.  THE ENGINE WILL BE CANNABA	LIZED TO SALVAGE ANY UNDAMAGED COMPONENTS FOR POSSIBLE RE-SALE.  ALL ENGINE BEARINGS WILL BE SCRAPPED REGARDLESS OF COND	ITION DUE TO THE AMOUNT OF METAL CONTAMINATION AND CONDITION OF THE ENGINE.						4	F			E25EA				 
2005042500099	20050425	00099	CE  	2005	4	25	CA050201002      	1	20050201	G	7120	265102215	COLLAR          			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 2 OF THE 4 CORNERS, INSIDE JO	INT.  DUE TO THIS BEING A KNOWN PROBLEM, AN ADDITIONAL TASK CARD TO CHECK FOR THIS CONDITION, INITIATED IN 1999, WAS ADD	ED TO OUR MAINTENANCE SCHEDULE EVERY 100 HOURS. AS A RESULT, WE HAVE DISCOVERED THE CONDITION ON 12 SEPARATE COLLARS. TH	E COLLAR WAS REPLACED AND THE AIRCRAFT REL EASED.			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005042500101	20050425	00101	NM  	2005	4	25	CA050201003      	1	20050108	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        			TX	TAXI/GRND HDL  	1			CA						1464					(CAN) GENERATOR CAUTION LIGHT ILLUMINATED AND ELECTRICAL LOAD WENT TO (0) SUSPECT STARTER BEARING FAILURE DUE TO HEAVY V	IBRATION IN THROTTLE HANDLE.  STARTER GEN INSPECTED IN SHOP, WO NR182352, BEARING FAILURE NOTED ON DRIVE END (03-6009-23	).				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500102	20050425	00102	NE  	2005	4	25	CA050201004      	2	20050130	G	7261		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LEFT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								PS0051			(CAN) AC HAD DEPARTED, LT LOW OIL PRESSURE LIGHT ILLUMINATED, GAUGE ALSO CONFIRMED PRESSURE AT 50-55.  ENG WAS SHUTDOWN 	AND SECURED.  EMERGENCY WAS DECLARED, AC DIVERTED TO NEAREST AIRPORT, LANDED UNEVENTFULLY.  MAINT FOUND ENGINE LOW BY 3 	LITERS.  OIL WAS NOTED ON LT LANDING GEAR BUT INSP OF ENG DID NOT REVEAL LOCATION OF LEAK. AC WAS GROUND RUN, INSPECTED 	WITH ALL PARAMETERS NORMAL, NO LEAKAGE.  AC FOUND FIT TO RETURN TO INTENDED DESTINATION. TAKEOFF WAS NORMAL, HALFWAY INT	O FLIGHT OIL PRESSURE STARTED TO DROP.  ENG WAS SHUTDOWN AND SECURED, LANDING AT DESTINATION WAS UNEVENTFULL.  INVEST OF	 ENG REVEALED INTRNL LEAKAGE OF OIL. IT WILL BE REMOVED AND FOLLOW UP REPORT WILL BE SUPPLIED.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005042500103	20050425	00103	WP  	2005	4	25	CA050201005      	1	20050129	G	3150		WARNING HORN    			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					COCKPIT	ACTIVATED       	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, AN AUDIBLE WARNING WAS HEARD FROM THE TAKEOFF WARNING COMPUTER.  THE TAKEOFF WAS ABORTED SUCCESSFU	LLY WITHOUT INCIDENT.  THE AIRCRAFT RETURNED TO THE GATE WHERE THE FLIGHT CREW ADJUSTED THEIR SETTINGS.  THE AIRCRAFT DE	PARTED WITHOUT INCIDENT AND NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005041200028	20050412	00028	EU  	2005	4	12	CA050201006      	1	20050130	G	5610	D20543406	WINDSHIELD      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT IT WAS OBSERVED THE RT WINDSHIELD OUTER PANE WAS CRACKED.  CREW INITIATED QRH PROCEDURES AND FLIGHT 	WAS CONTINUED.  AIRCRAFT LANDED WITHOUT INCIDENT.  RT WINDSHIELD WAS REPLACED IAW MM 56-11-00.  NO FURTHER INCIDENT DURI	NG SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042000133	20050420	00133	EA  	2005	4	20	CA050202001      	1	20050201	G	2100	GG67095009	ACM             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RT A/C PACK	SEIZED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) RT PACK AUTOFAIL MESSAGE ON EICAS WITH RT PACK FAILING AFTER START OF ENGINE NR1.  MANUAL TEMP SELECTED WHICH RESU	LTED WITH THE LAV SMOKE DETECTOR ACTIVATING AND SMOKE ENTERING THE AFT CABIN.  PACK TEMP OBSERVED AT 98 DEGREES JUST BEF	ORE AUTOFAIL.  THE AIR CYCLE MACHINE (ACM) WAS REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005042000134	20050420	00134	NE  	2005	4	20	CA050202002      	2	20050201	G	7532	0301007860	SCREEN          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BLEED VALVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						895					(CAN) WIRE BROKEN ON SCREEN THAT IS ATTACHED TO BLEED VALVE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005042000135	20050420	00135	CE  	2005	4	20	CA050202003      	1	20050201	G	3297	MS24171D1	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	BURNED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, FLIGHT CREW SELECTED GEAR DOWN BUT THE CONTROL CB OPENED AND WOULD NOT RESET. THE LANDING GEAR WA	S MANUALLY EXDENDED WITH 3 GREENS.  MAINTENANCE FOUND THE LANDING GEAR RELAY WAS BURNED AT THE CONTACTS AREA AND THE REL	AY WAS REPLACED. THIS OPERATOR HAS HARDTIME, THE RELAY AT 5000 HOURS PREVIOUSLY TO PREVENT THESE TYPES OF OCCURENCES. TO	 DATE, THIS NUMBER HAS BEEN SUCCESSFUL BUT THIS FAILURE OCCURRED APPROX 3600 HOURS SINCE INSTALLATION.  AS A RESULT, THE	 COMPANY HARDTIME ON THIS RELAY HAS BEEN LOWERED TO 3000 HOURS.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005042000136	20050420	00136	CE  	2005	4	20	CA050202004      	1	20050125	G	5511	053200198	SPAR            			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12402								(CAN) DURING THE 200 HOUR INSPECTION CRACKS WERE FOUND STARTING FROM THE CENTRAL LIGHTENING HOLE IN THE FORWARD HORIZONT	AL STABILIZER SPAR.  THE CRACKS WERE STOP DRILLED AND REINFORCEMENT P/N 0531037-1 AND SKIN P/N 0523001-25 WERE INSTALLED	 IAW SEB94-8.				1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2005042000137	20050420	00137	CE  	2005	4	20	CA050202005      	1	20050201	G	2435	03601018	BEARING         	LUCAS       		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COMMUTATOR	DESTROYED       	W				O				OTHER                   				D	E	H	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	ELECT. POWER LOSS-50 PC   	CR	CRUISE         	1			CA						7128					(CAN) WHILE IN CRUISE BACK TO BASE, CREW ENCOUNTERED AIRFRAME VIBRATION FROM THE AFT CABIN, FOLLOWED BY THE RT GENERATOR	 FAIL LIGHT 10 MINUTES LATER. CREW CONFIRMED LOSS OF RT GENERATOR, AND DECLARED AN EMERGENCY DUE TO THE INTENSITY OF VIB	RATION.  A/C LANDED WITHOUT INCIDENT.  ON DISASSEMBLY OF UNIT, DISCOVERED CUMMUTATOR BEARING DESTROYED. CAUSE OF FAILURE	 IS UNDER INVESTIGATION. THERE WAS ONLY 406 HRS ON THE BEARING SINCE REPLACEMENT.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005042000138	20050420	00138	GL  	2005	4	20	CA050202006      	1	20050131	G	2730	10146005	CONTROL UNIT    			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ELEVATOR	RESTRICTED      	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PILOT NOTICED ELEVATOR CONTROL WAS STIFFER THAN USUAL ON APPROACH.  UPON LANDING, FOUND THE LT ELEVATOR BALANCE WE	IGHT HORN IS RUBBING AGAINST THE HORZIONTAL STABILIZER.  FOUND THE ELEVATOR WILL NOT RUB ONCE THE AIRCRAFT IS WARMED UP.	  THE ELEVATOR TIP FAIRING MOUNTING SCREWS WERE LOOSENED AND THE ELEVATOR HORN WAS REPOSITIONED TO PROVIDE THE NECESSARY	 CLEARANCE.			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2005042500104	20050425	00104	NE  	2005	4	25	CA050203001      	2	20050106	G	7210	547344P3	STUD            	PWA         		BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					GEARBOX	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA						688797					(CAN) DURING CLIMBOUT, CREW OBSERVED DECREASING OIL QUANTITY NR 3 ENGINE. PRECAUTIONARY ENGINE SHUTDOWN COMPLETED.  LAND	ED WITHOUT INCIDENT.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005042500105	20050425	00105	NM  	2005	4	25	CA050203002      	1	20050128	G	5513	653120043	PLATE           			BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					HORIZONTAL STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT HORIZONTAL STABILIZER TO FIN SEAL SEPARATED FROM AIRCRAFT.  UNABLE TO DETERMINE EXACT CAUSE.  ALL AFFECTED PART	S REPLACED.  REMAINING FLEET CHECKED, SERVICEABLE.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005042500106	20050425	00106	SO  	2005	4	25	CA050203003      	2	20050127	G	7414	SGRN1225	HOUSING         	BENDIX      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						653290R					(CAN) DURING ROUTINE 500 HOURS INSPECTION, BOTH MAGNETO HOUSINGS WERE FOUND CRACKED IAW FIGURE 716 OF MFG MASTER SERVICE	 MANUAL X40000.<AGMETPS (2) - P/N SGRN-1225S/N 653290R S/N 653291					1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P25EA	 
2005042500107	20050425	00107	EA  	2005	4	25	CA050203004      	2	20050128	G	7210		PLANETARY GEAR  								PWA   	PT6   	PT6A50      	52043	EA  					ENGINE RGB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21873								(CAN) SOURCE OF METAL CONTAMINATION WAS FAILURE OF 1ST STAGE GEARS. GEARS WERE SENT TO METALLURGICAL LABORATORY FOR FURT	HER INVESTIGATION THAT REVEALED THE EXISTENCE OF AN OLDER FATIGUE CRACK SURFACE ON PARTS OF A FRACTURED TOOTH ON THE 1ST	 STAGE SUN GEAR, SUN GEAR. PARTS OF THIS GEAR BROKE OFF IT IS BELIEVED THEY BECAME WEDGED BETWEEN THE SUN GEARE & THE 1S	T STAGE PLANETARY GEAR CAUSING THE PLANET GEAR TOOTH TO SHATTER. SINCE DAMAGE TO RGB GEARING SIGNIFICANT, DECIDED TO PER	FORM FULL OVERHAUL LEVEL INSPECTIONS ON ALL RGB COMPONENTS, CLEAN & FLUSH & VISUALLY INSPECT REMAINING POWER SECTION COM	PONENTS & TO CLEAN FLUSH & VISUALLY INSPECT OIL WETTED COMPONENTS UPSTREAM OF MAIN PRESSURE FILTER.						4	T			E4EA				 
2005041200063	20050412	00063	NM  	2005	4	12	CA050203005      	1	20050202	G	3220	69141062	CYLINDER        	BOEING      		BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA						5Q1173					(CAN) NLG FAILED TO EXTEND ON APPROACH, THEN RE-CYCLED AND EXTENDED NORMALLY.  NOSE GEAR JACKED, NOSE GEAR TRUNION GREAS	ED AND GEAR RETRACTED AND EXTENDED 4 TIMES WITH NO FAULTS.  AC WAS DISPATCHED WITH NO FURTHER FAULTS. QA GROUNDED THE AC	 DUE TO 2 OTHER EVENTS OF THE SAME NATURE. REF. SDR'S 20041123004 AND 20050119003.  MAINTENANCE IN OTHER LOCATION, COMPA	NY MAINTENANCE OPERATIONS CONTROL, AND MAINTENANCE OPERATIONS CONTROL CENTER ALL CONTACTED TO TROUBLESHOOT THE DISCREPAN	CY.  AFTER CONSULTATION, ALL CONCURRED THAT THE NOSE GEAR TRANSFER CYLINDER WAS AT FAULT. REPLACED THE TRANSFER CYLINDER	 AND GEAR WAS SWUNG NUMEROUS TIMES, NO FAULTS FOUND.  AIRCRAFT WAS RETURNED TO SERVICE. T/C PMI CONTACTED WITH DETAILS.	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005042000139	20050420	00139	CE  	2005	4	20	CA050204001      	1	20050128	G	5521	1156100181	SUPPORT         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ONE SCREW HOLE HAS 2 QUARTER INCH CRACKS RADIATING OUT BUT STOPPING BEFORE REACHING PART EDGE.  PROBLEM FOUND FROM	 NDT TESTING FOR THE 1000 HOUR REQUIREMENT IN MM FOR ELEVATOR TORQUE TUBES. THIS PART IS MADE OUT OF MAGNESIUM, IF MANUF	ACTURER WOULD CHANGE PART MATERIAL TO ALUMINUM WE BELIEVE THIS WOULD SOLVE THE PROBLEM.				1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005042000140	20050420	00140	NM  	2005	4	20	CA050204002      	1	20050117	G	7500	65544702	MIXER BOX       			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					DUCT FLANGE	SEPARATED       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, FORWARD CLOSET SMOKE DETECTOR ACTIVATED AND ACRID SMELL DETECTED IN CABIN.  RETURNED WITHOUT FURTHER	 INCIDENT. FOUND BLEED AIR DUCT AT AIR DISTRIBUTION MANIFOLD LT SIDE A-DRIFT, SECURED DUCT AND LEAK CHECK CARRIED OUT.  	AS A FURTHER PRECAUTION ON ARRIVAL, AIR DUCT P/N 65-54467-1 AND MIXING CHAMBER P/N 65-54470-2 REPLACED WITH OVERHAULED U	NITS.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005042500108	20050425	00108	WP  	2005	4	25	CA050204003      	2	20050203	G	7261	31025751	CARBON SEAL     								GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CARBON SEAL FOUND CRACKED AFTER RECIEVING NEW PART FROM MFG NR 61634.											4	T			E4WE				 
2005042000141	20050420	00141	CE  	2005	4	20	CA050204004      	1	20050201	G	5753	05239011314	SUPPORT         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RT TE FALP	WORN            	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE DAMAGE OCCURED AROUND THE AFT IB BEARING.  THE BEARING WAS FOUND WORN INTO BOTH THE SUPPORT ARMS 0523901-13 AN	D -14.  MFG OFFERS A SERVICE KIT TO REPLACE THESE BRACKETS.  SK180-44-1.  THIS KIT WAS ISSUED TO REPAIR A DEFECT OCCURIN	G ON THE FRONT ROLLER BEARING AREAS.  NOT THE AFT.  BOTH SUPPORT BRACKETS WERE REPLACED WITH NEW DUE TO THE DAMAGE AT TH	E AFT PORTION (WHICH WAS FOUND TO BE EXCESSIVELY WORN.)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005042500109	20050425	00109	EA  	2005	4	25	CA050207001      	1	20050205	G	2820	C6PF10761	TUBE            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) INVESTIGATION OF A (FUEL SMELL IN THE CABIN) AND A MINOR EXTERNAL FUEL LEAK REVEALED THAT WELDED FUEL TUBE ASSY BE	TWEEN FUEL TANK AND FLEX HOSE TO THE WING STRUT WAS LEAKING.  REMOVAL OF ADEL CLAMP REVEALED CORROSION PITS UNDERNEATH W	ITH ASSOCIATED FUEL SEEPAGE.  INVESTIGATION INTO OPPOSITE SIDE TUBE REVEALED SIMILAR CONDITION, BUT CORROSION WAS NOT AD	VANCED ENOUGH TO CAUSE A LEAK.  BOTH TUBE ASSYS WERE REPLACED AND AC RETURNED TO SERVICE.  TIMES AND CYCLES ARE NOT MAIN	TAINED ON THESE ITEMS.  AC HAS FLOWN 3 YEARS SINCE A COMPLETE CORROSION CHECK, AND OPERATES EXCLUSIVELY IN A CORROSIVE E	NVIRONMENT.	1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005042500110	20050425	00110		2005	4	25	CA050207002      	4	20050202	G	6122	8210002	GOVERNOR        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	UNCONTROLLABLE  	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								50805PS			(CAN) THE AIRCRAFT WAS IN ENROUTE, WHEN THE RT ENGINE PROPELLER RPM DROPPED, UNCOMMANDED, TO 80 PERCENT.  THE PROPELLER 	RPM COULD NOT BE CONTROLLED, NOR COULD THE PROPELLER BE FEATHERED, AND THE RT ENGINE WAS SHUTDOWN AS A PRECAUTION.  THE 	AIRCRAFT RETURNED TO AIRPORT WHERE MAINTENANCE FOUND THE RT PROPELLER GOVERNOR TO BE FAULTY.  THE PROPELLER GOVERNOR WAS	 REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2005042000142	20050420	00142	EU  	2005	4	20	CA050207004      	1	20050206	G	2910		HYDRAULIC SYSTEM			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					RIGHT	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE HELICOPTER WAS ON A INTERNATIONAL JOB.  THE INITIAL REPORT FROM FLIGHT OPERATIONS IS HYDRAULIC FAILURE.  THE A	IRCRAFT WAS IN A HOVER WHEN IT YAWED TO THE RT.  THE AIRCRAFT LANDED HARD ENOUGH TO DAMAGE ONE ARM OF THE MAIN ROTOR STA	R AND THE TAILBOOM HAS BEEN DAMAGED.  CREW OK.  THIS IS AN INITIAL REPORT MORE INFORMATION WILL FOLLOW.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005042000143	20050420	00143	CE  	2005	4	20	CA050207005      	1	20050130	G	5610	5042006932	WINDSCREEN      			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) PILOTS HEARD A LOUD BANG AND THE CO-PILOTS WINDSCREEN CRACKED.  THEY DESCENDED AND BROUGHT CABIN PRESSURE DOWN TO 	2 PSI.  THEY THEN LANDED AT NEAREST MAINTENANCE BASE.					1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
2005041200027	20050412	00027	EA  	2005	4	12	CA050207006      	2	20050205	G	7321	252444076	FUEL CONTROL    			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT ENGINE	INOPERATIVE     	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) PILOTS STARTED THE ENGINES AND TAXIED OUT FOR TAKEOFF.  WHEN APPLIED POWER, THE RT ENGINE REMAINED AT IDLE.  THEN 	RETURNED TO THE RAMP AND SHUT DOWN. ENGINEER CHANGED THE FCU.					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005042500111	20050425	00111	NE  	2005	4	25	CA050208001      	2	20050131	G	7200		ENGINE          								PWA   	PT6   	PT6A60A     	52043	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								95688			(CAN) ENG SUFFERED ONLY MINOR DAMAGE FROM PROP STRIKE WHICH WERE TIP RUBS IN COMPRESSOR, PWR TURBINE COMPONENTS. TIP RUB	S FOUND ON PT BLADE PATHS ARE CONSIDERED TO BE MINOR AND NOT UNCOMMON TO FIND AT ANY DISASSEMBLY EVEN AFTER ONLY 77 HOUR	S OPERATION SINCE THIS ENG WAS LAST O/H. THESE RUBS ARE QUITE DEEP AND ALL AROUND BLADE PATH.  PT BLADE RUB WAS EITHER A	 RESULT OF SUDDEN STOPPAGE OR STOPPAGE MADE IT MORE SEVERE THAN WOULD HAVE OCCURRED.  RUBBING DAMAGES FOUND ON COMPRESSO	R COMPONENTS ARE ALSO MINOR BUT AGAIN NOT UNCOMMON.  AFTER ONLY MINIMAL OPERATING HOURS SINCE OVERHAUL THIS DAMAGE WOULD	 APPEAR TO BE EITHER A DIRECT RESULT OF SUDDEN STOPPAGE OR AT LEAST MADE WORSE BY INCIDENT.						4	T			E4EA				 
2005042000144	20050420	00144	NE  	2005	4	20	CA050208003      	2	20050203	G	7310	5001T39G29G	FCU             			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	LEAKING         	W				A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			TO	TAKEOFF        	1			CA								245U427B			(CAN) TAKEOFF WAS REPORTED AS NORMAL.  ENGINE ANTI-ICE WAS SELECTED ON, AS AC CLIMBED THROUGH 2000 FT IT WAS NOTED THAT 	WITH POWER LEVER FIREWALLED, NR1 ENGINE COULD ONLY MAINTAIN AN EGT OF 640 C, N1 RPM AND N2 RPM WERE BOTH AT 90 PERCENT. 	  AC CONTINUED TO CLIMB, 6000 FT, ENGINE ROLLED BACK TO IDLE AND FLAMED OUT.   CREW WAS UNABLE TO RELIGHT  ENGINE, ELECT	ED TO RETURN TO DEPARTURE AIRPORT. MAINT WAS ROUTED, ENGINE WAS INSPECTED AND NO FOD DAMAGE WAS FOUND.  UPON OPENING ENG	INE COWL, SIGNIFICANT AMOUNT OF FUEL WAS NOTED IN THE BOTTOM OF COWLS.  FUEL SYSTEM WAS PRESSURIZED AND A LEAK WAS FOUND	 ON FCU.   FCU WAS REPLACED, LEAK CHECKED AND GROUND RUN.  TEST FLIGHT WAS COMPLETED.  AC WAS RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2005042500112	20050425	00112	EA  	2005	4	25	CA050208004      	1	20050204	G	3250	C3UF609	CABLE           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WATER RUDDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE BROKE IN THE FORWARD BAY WHERE IT CHANGES DIRECTION. ADDITIONAL NOTE, INSPECTION IN THIS AREA IS ONLY POSSIB	LE WITH MIRROR.					1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
2005042500113	20050425	00113	EU  	2005	4	25	CA050208005      	1	20050206	G	2730	234007	CONTROL UNIT    			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ELEVATOR BOOST	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF, THE CREW OBSERVED NR2 ELEVATOR FAULT, LEVEL 3 ALERT ON THE MFDS.  THE CREW INITIATED A REJECTED T	AKE-OFF SUCCESSFULLY AND RETURNED TO THE GATE. MAINTENANCE CONFIRMED THE ELEVATOR BOOSTER CONTROL UNIT WAS SUSPECT.  THE	 UNIT WAS REPLACED AND CHECKED SERVICEABLE IAW MM 27-32-01.  THE AIRCRAFT WAS RETURNED TO SERVICE.  NO FURTHER INCIDENT 	DURING SUBSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042500114	20050425	00114	EA  	2005	4	25	CA050208006      	1	20050206	G	2910	82910009175	TUBE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			31906	31906							(CAN) DURING CLIMB THROUGH 10,000 FEET,  THE NR 2 HYD QUANTITY GAUGE DECREASED, NR 2 HYD ISO VALVE CAUTION LIGHTS ILLUMI	NATED.  AIRCRAFT ELECTED TO RETURN TO DEPARTURE AIRPORT, ALTERNATE GEAR EXTENSION SYSTEM USED. NORMAL LANDING.  MAINTENA	NCE INSPECTION FOUND TUBE ASSEMBLY (ELBOW TO SOLENOID VALVE DOOR SEQUENCE OPEN) LEAKING.  LINE REPLACED, HYDRAULIC FLUID	 REPLENISHED, GEAR SWINGS CARRIED OUT , AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500115	20050425	00115	EA  	2005	4	25	CA050208007      	2	20050208	G	7314	LW15473	PUMP            			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE FUEL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L3165751			(CAN) DURING INSPECTION, FUEL WETNESS WAS DISCOVERED ON THE BOTTOM OF THE FUEL PUMP.  UPON FURTHER INSP ALL OF THE DIAPH	RAGM RETENTION BOLTS WERE FOUND TO BE LOOSE.  A MINIMUM OF THREE QUARTERS TO TWO TURNS WAS OBSERVED ON ALL OF THE BOLTS 	IN ORDER TO ACHIEVE PROPER TORQUE.  THE AIRCRAFT WAS GROUND RUN AND LEAK CHECKED WITH NO FURTHER PROBLEMS.				1	G	7	1 	3O	3	O	O	4H12    	E286				 
2005042500116	20050425	00116	EA  	2005	4	25	CA050209001      	1	20050202	G	5310	CC670341757	CROSSBEAM       			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND AT FS280 (MAINLY RT SECTION) AND CRACKS AT LBL/RBL  9.0 AT FLOORBEAM ATTACHMENT FITTING.  REPAIR T	O BE PERFORMED USING GENERIC REPAIR ENGINEERING ORDERS (GEN REOS) 670-53-11-045, -046,-047, -052 AND IS MODSUM IS6705311	00026.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005042500117	20050425	00117	EA  	2005	4	25	CA050209002      	1	20050105	G	5310	CC670341757	CROSSBEAM       			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ONGOING C-CHECK OF A/C 5 CRACKS AND SLIGHT CORROSION WERE FOUND ON FS 280.0 CROSSBEAM P/N CC670-34175-7 AND	 ANGLE P/N CC670-33292-9 AT LBL 9.0 AND RBL 9.0.   NOTE: REPAIR TO BE PERFORMED WITH ACOMBINATION OF GEN REOS 670-53-11-	045, -046, -047, -052 AND IS MODSUM IS670531100026.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005042500118	20050425	00118	EU  	2005	4	25	CA050209003      	1	20050207	G	7540		INDICATOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					BLEED AIR	FAILED          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, THE CREW OBSERVED THE WING ANTI-ICE FAIL LIGHT CAME ON WITH THE ENGINE ANTI-ICE SELECTED ON.  THE AIR	CRAFT RETURNED TO THE GATE.  MAINT PERFORMED THE CONTROL UNIT BITE TEST.  THE OPERATIONAL TEST WAS CARRIED OUT IAW MM 30	-11-00 WITH NO FAULT FOUND.  THE AIRCRAFT WAS DISPATCHED AND FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005042500119	20050425	00119	CE  	2005	4	25	CA050209004      	1	20050203	G	5511	053200198	SPAR            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FOUND 2 SMALL CRACKS (0.200 INCH LONG) IN THE SPAR CENTER LIGHTNING HOLE FLANGE, ALSO, THE REINFORCEMENT HAS BEEN 	SLIGHTLY BENT AND A REPLACEMENT IS NECESSARY.  SPAR IS THE SAME ONE USED ON THE EARLIER MODEL EXCEPT THAT MFG HAS INCLUD	ED THE REINFORCEMENT AT THE NEW PRODUCTION AND IT CAN BE BOUGHT SEPARATELY.  IAW SEB 94-8, IT WAS POSSIBLE TO REPLACE TH	AT REINFORCEMENT WHEN THE CRACKS DID NOT EXCEED THE FLANGE RADIUS.  UNFORTUNATELY, THAT REPAIR (FOR OUR AIRCRAFT) IS NOT	 COVERED BY THE SEB 94-8. JUST BLANK OUT THE CRACKS AND PROCEED WITH THE REPLACEMENT OF THE REINFORCEMENT.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005042500120	20050425	00120	NE  	2005	4	25	CA050209005      	2	20050123	G	7250		TURBINE BLADES  			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								AW0091			(CAN) CREW NOTED THAT THEY HAD NO NP INDICATION AFTER START OF THE NR 2 ENGINE, AND OBSERVED THAT THERE WAS NO PROPELLER	 ROTATION THE ENGINE WAS THEN SHUTDOWN.  CREW REPORTED ALL OTHER ENGINE INDICATIONS WERE NORMAL DURING THE START.  INITI	AL INVESTIGATION NOTED THAT THE PROPELLER WAS UNABLE TO BE TURNED BY HAND AND THE AIRCRAFT WAS REMOVED FROM SERVICE FOR 	FURTHER INVESTIGATION.  BOROSCOPE INSPECTION WAS CARRIED OUT THROUGH T6 PROBE AND THERE APPEARED TO BE NO TIP CLEARANCE 	ON THE 1ST STAGE POWER TURBINE WITH BLADE SHROUD DAMAGE EVIDENT.  THERE WAS ALSO MINOR IMPACT DAMAGE NOTED TO THE 2ND ST	AGE NOZZLE AND POWER TURBINE. ENGINE WAS THEN REMOVED FROM THE AIRCRAFT. MFG INVESTIGATING ISSUE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500121	20050425	00121	SW  	2005	4	25	CA050209006      	1	20050209	G	5302	212030158001	FITTING         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14437								(CAN) UPPER RT TAILBOOM ATTACH FITTING ON FUSELAGE FOUND CRACKED FROM LOCK FASTENER HOLE.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005050300198	20050503	00198	NE  	2005	5	3	CA050209007      	2	20050208	G	7313		NOZZLE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUEL INJECTOR	INOPERATIVE     	W				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			CA								GEE950315			(CAN) DURING ENGINE RELIGHTS PROCEDURE, AN ATS (CROSSBLEED START) WAS PERFORMED ON THE LT ENGINE WHICH WAS UNSUCCESSFUL 	AFTER 3 ATTEMPTS.   ALL THE PARAMETERS WERE NORMAL EXCEPT THERE WAS NO LIGHT OFF AFTER 25 SECONDS ON EACH ATTEMPT.  A SI	NGLE ENGINE LANDING WAS COMPLETED, WITHOUT FURTHER INCIDENTS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005042500122	20050425	00122	CE  	2005	4	25	CA050210001      	1	20050207	G	3243	429333	CONTROL UNIT    			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					BRAKES	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING THE AIRCRAFT. (NORM BRAKE FAIL) MESSAGE CAME ON.  EMERGENCY BRAKE USED ON THE WAY BACK TO THE MAINTE	NANCE FACILITY.  BRAKE CONTOL UNIT REPLACED, AIRCRAFT RETURN TO SERVICE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005041200029	20050412	00029	WP  	2005	4	12	CA050210002      	1	20050209	G	3230	H141016	SWITCH          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE CREW OBSERVED THE NLG UNSAFE LIGHT ILLUMINATE BRIEFLY.  THE FLIGHT CONTINUED AND LANDED WITHOUT	 INCIDENT.  THE NLG LT GROUND INTERLOCK SWITCH WAS SUSPECTED AND REPLACED IAW MM 32-60-05.  NO FURTHER PROBLEM DURING SU	BSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005041200056	20050412	00056	EU  	2005	4	12	CA050210003      	1	20050210	G	3231	MRH530014D	BYPASS VALVE    			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					MLG DOOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) FAULT:  HYD GREEN FLUID UNDERFILLED. PRESSURE AT 3000 PSI, BRAKES FAILED AT 100 FEET FROM BRIDGE, REVERSE AND PARK	ING BRAKE USED TO STOP AIRCRAFT. ALTERNATE BRAKING NOT AVAILABLE.  FOUND RT MLG DOOR BYPASS VALVE (5229GA), LEAKING AND 	SEAL PROTRUDING.  CHANGED VALVE IAW AMM32-31-13-400-802  HYDRAULIC SYS TOPPED UP AND LEAK AND OPERATION CHECKED.  S/V BR	AKE SYSTEM TEST ALSO PERFORMED, OK.			2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2005041200057	20050412	00057	WP  	2005	4	12	CA050210004      	1	20050209	G	2913	AS664116S666	PUMP            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LT HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW OBSERVED LT HYDRAULIC PRESSURE LOW WITH LIGHT ILLUMINATING.  HYDRAULIC PRESSURE INDICATED Z	ERO.  QRH PROCEDURES INITIATED AND AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT.  MAINTENANCE REPLACED THE LT EDP.  OPERAT	IONAL CHECK CARRIED OUT IAW MM 29-10-05.  NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500123	20050425	00123	NE  	2005	4	25	CA050210005      	2	20050207	G	7532	310317401	BLEED VALVE     			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			CA								PCE95500			(CAN) WHILE CLIMBING OUT AFTER TAKEOFF THE FLIGHT CREW NOTICED A THROTTLE SPLIT TO MAINTAIN THE SAME ENGINE TORQUE. AT A	LL TIMES THE ENGINES WOULD MAKE RATED POWER, BUT THE LT ENGINE REQUIRED MORE FORWARD THROTTLE MOVEMENT TO MAKE BOOK TORQ	UE. MAINTENANCE PERFORMANCE RUNS CONFIRMED LT ENGINE PARAMETERS HIGH (ITT, WF, N1) TO MAKE TARGET TORQUE.  ENGINE BLEED 	VALVES SWAPPED SIDE TO SIDE FOR TROUBLESHOOTING AND SUBSEQUENT RUNS CONFIRMED PROBLEM FOLLOWED THE BLEED VALVE. FAULTY V	ALVE REPLACED WITH O/H UNIT. GROUND RUNS C/O SATISFACTORY.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005042500124	20050425	00124	SW  	2005	4	25	CA050211001      	1	20050211	G	3230	71461L	LEG ASSY        	BLANCA      		BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	MLG	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						92696AL51					(CAN) AS INSTRUCTED BY INSPECTION REPORT C-12-B80-00/NF-001, AME 118, OUT OF PHASE TASKING (MAIN LANDING GEAR SPRING): C	OMPLIANCE BI-ANNUAL OR 700 HOURS WHICH EVER COMES FIRST.  THE GEAR LEGS WERE REMOVED AND SENT FOR NDT.  AT NDT THE SUBJE	CT GEAR LEG WAS FOUND TO HAVE INDICATIONS OF DE-LAMINATION LONGITUDINALLY ON BOTH THE LEADING EDGE AND TRAILING EDGE.  I	T IS ESTIMATED THAT THE SUBJECT GEAR LEG HAS ABOUT 8437.5 TAKE OFFS AND LANDING.  SUBJECT GEAR LEG WAS REMOVED FROM SERV	ICE.		1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005042500125	20050425	00125	NE  	2005	4	25	CA050211002      	2	20050113	G	7200		ENGINE          								PWA   	PT6   	PT6A114A    	52043	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								19212			(CAN) THE LOW OIL PRESSURE EVENT WAS RESULTS OF A CRACKED MAIN OIL PUMP HOUSING. OIL FILTER & CHIP DETECTOR WERE BOTH FO	UND TO BE CLEAN & FREE OF DEBRIS DURING RECEIVING INSPECTION. THIS INDICATED THAT OPERATION OF ENGINE 19212 AT 85 PSIG (	5 PSIG BELOW THE MINIMUM) FOR APPROX 20 MINS PRIOR TO LANDING DID NOT CAUSE ANY DETRIMENTAL DAMAGE TO ANY OF ENGINES INT	ERNAL GEARS OF BEARINGS.  ENG TESTING AFTER REPLACEMENT OF MAIN OIL PRESSURE HOUSING INDICATED THAT OIL PRESSURE NOW 100	 PSIG, MAXIMUM OF OPERATING LIMITS SPECIFIED BY PWC (90 TO 100 PSIG). ENGINE HAD NO FURTHER PROBLEMS WITH LOW OIL PRESSU	RE AFTER REPLACEMENT OF CRACKED OIL PUMP HOUSING. ENGINE RESTORED TO SERVICE.						3	T			E4EA				 
2005042500126	20050425	00126	EA  	2005	4	25	CA050211003      	2	20050113	G	7230		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								86464			(CAN) DESTRUCTION OF COMPRESSOR OF ENGINE RESULT OF TIE ROD BOLT STRETCH. LACK OF TORQUE REMAINING ON HALF OF TIE RODS I	NDICATES THAT 3 LOOSE TIE RODS STRETCHED & CAUSED COMPRESSOR TO LOSE AXIS OF ROTATION & ALLOWED COMPRESSOR TO RUB HEAVIL	Y & CAUSE MATERIAL TO BE LIBERATED.  APPEARS CT BLADE DAMAGE IS SECONDARY DAMAGED CAUSED BY LIBERATED MATERIAL FROM COMP	RESSOR. DAMAGE ON CT BLADES MAY ALSO BEEN INCREASED BY HEAVY TIP RUB OF THE CT DISK AFTER COMPRESSOR LOST AXIS & CAUSED 	SIGNIFICANT VIBRATION ON ROTATING ASSY. DAMAGE ON POWER SECTION A RESULT OF MATERIAL LOST FROM CT BLADES & COMPRESSOR.  	COMPLETE OVERHAUL OF ENGINE. ALL TIE RODS & NR 1 & 2 BEARINGS WILL BE SCRAPPED REGARDLESS OF THEIR CONDITION.						4	T			E4EA				 
2005042500127	20050425	00127	NM  	2005	4	25	CA050211004      	1	20050126	G	2910	DSC252B40124	HOSE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF AND ON GEAR UP SELECTION, THE NOSE GEAR FAILED TO RETRACT AND IT WAS OBSERVED BY THE CREW THAT THE 	NR 2 HYDRAULIC SYSTEM WAS ALMOST DEPLETED OF OIL. AIRCRAFT WAS MAINTAINED VISUALLY IN THE CIRCUIT WHILE ALL RELEVANT QRH	 PROCEDURES WERE COMPLETED. FOLLOWING COMPLETION OF DRILLS A NORMAL APPROACH AND LANDING WAS CARRIED OUT. ENGINEERING IN	VESTIGATION REVEALED A RUPTURE FAILURE OF A FLEXIBLE HOSE IN THE NLG RETRACTION HYDRAULIC SYSTEM.  THE HOSE WAS REPLACED	 AND FOLLOWING SATISFACTORY COMPLETION OF MM REQUIREMENTS THE AIRCRAFT WAS RELEASED TO SERVICE WITHOUT FURTHER INCIDENT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500128	20050425	00128	NM  	2005	4	25	CA050211005      	1	20050206	G	2760	414001410	BEARING         			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ROD END	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE PILOT REPORTED THE RT SPOILERS WERE NOT DEPLOYING PROPERLY AND 50 DEGREES RT AILERON WAS REQUIRED TO KEEP WING	S LEVEL AT FULL SPOILER DEFLECTION.  UPON INSPECTION OF THE SPOILER RATIO CHANGER AND MIXER, THE RT AFT LOWER SPOILER CA	BLE ROD END BEARING (P/N 41400-1410) LOCATED ON THE RIGGING BEAM WAS FOUND WITH THE BARREL SNAPPED OFF AT THE BASE OF TH	E END BEARING.  THE END BEARING HAD SEIZED, CAUSING BENDING OF THE BARREL END DURING THE DEPLOYMENT AND RETRACTION OF TH	E SPOILERS AND EVENTUAL FAILURE.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005042500129	20050425	00129	EA  	2005	4	25	CA050211006      	1	20050201	G	3240	21517	BRAKE ASSY      			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18107								(CAN) DURING GROUND HANDLING FLIGHT CREW REPORTED RT BRAKES CHATTERING WITH BRAKE APPLICATION.  MAINTENANCE INSPECTION F	OUND NR 3 BRAKE ASSEMBLY WITH SEIZED ADJUSTERS.  BRAKE ASSEMBLY REPLACED.  AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500130	20050425	00130	NM  	2005	4	25	CA050211007      	1	20050204	G	4930	38942811	APU             			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AFT	FIRE            	W				F	D			ACTIVATE FIRE EXT.      	RETURN TO BLOCK         			A	P		FLAME/FIRE                	NO WARNING INDICATION     		TX	TAXI/GRND HDL  	1			CA											(CAN) ENCOURTERED AN APU FIRE.  FIRE DID NOT INITIATE A FIRE WARNING.  FIRE BELIEVED TO BE INITIATED BY CRACK IN APU PLE	NUM.  CRACK IN TURN CAUSED HOT COMPRESSOR DISCHARGE AIR TO AFFECT FUEL HEATER & CHECK VALVE CAUSING AN O-RING TO LEAK.  	ALLOWING FUEL TO START A FIRE ON TOP OF APU PLENUM.  FIRE LOOP DOES NOT RUN IN THIS PARTICULAR AREA.  FIRE MAY HAVE ALSO	 BEEN COMPOUNDED BY APU START HAD BEEN ABORTED POSSIBLY LEAVING FUEL IN COMBUSTION CAN.  COLLECTIVELY THE FIRE EXITING T	AIL PIPE & BURNED ON TOP OF APU.  LOCATION OF FIRE & LOCAL HEATING IN FIREWALL IN VICINITY OF THE TAIL PIPE FIRE LOOP CO	NNECTOR CAUSED CONNECTOR TO SHORT.  OVERHEAT DETECTION LIGHT ON GLARESHIELD 6 PACK ILLUMINATED.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005041200030	20050412	00030	NM  	2005	4	12	CA050212001      	1	20050206	G	6120	7901803	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			18089								(CAN) IN FLIGHT, CREW NOTICED NR1 OIL PRESSURE DROPPING, VISUALLY NOTICED OIL LEAK ON NR1 FORWARD COWLING, OIL PRESSURE 	DROPPED TO 45 PSI. CREW SHUT NR 1 ENGINE DOWN AS PRECAUTIONARY MEASURE, LANDED AIRCRAFT AT UNSCHEDULED AIRPORT.  MAINTEN	ANCE REPLACED NR1 PROPELLER ACTUATOR.  GROUND RUNS AND LEAK CHECKS CARRIED OUT AND CHECKED SERVICEABLE.  AIRCRAFT DISPAT	CHED THE FOLLOWING MORNING.  NO REPORT FROM OVERHAUL FACILITY AS OF YET.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005041200058	20050412	00058	NE  	2005	4	12	CA050213001      	2	20050126	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								127051			(CAN) DURING CLIMB THE ENGINE LOST POWER ACCOMPANIED BY A LOUD NOISE AND VIBRATIONS.  THE ENGINE WAS SHUT DOWN IN FLIGHT	 AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE TURBOMACHINE MODULE.  MF	G WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2005041200059	20050412	00059	NE  	2005	4	12	CA050213002      	2	20050131	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  		FAILED          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								PS0051			(CAN) DURING CRUISE THE ENGINE LOW OIL PRESSURE INDICATOR ANNUNCIATED.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT 	INSPECTION EVIDENSED NOISE FROM THE REDUCTION G EAG THE PROP.  MFG WILL INVESTIGATE THE EVENT AND WILL SUPPLIMENT THIS R	EPORT TO PROVIDE ROOT CAUSE AS AND WHEN ESTABLISHED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005042500132	20050425	00132	NE  	2005	4	25	CA050213003      	2	20050201	G	7200		ENGINE          								PWA   	PT6   	PT6A68      	 	NE  						MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								RA0136			(CAN) A CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT, REPORTED AS ACCOMPANIED BY PROPELLER SPEED FLUCTUATIONS.  SUBSEQUEN	T INSPECTION REVEALED METAL PARTICLES AT THE CHIP DETECTOR AND OIL FILTER LOCATIONS.  PWC WILL INVESTIGATE THE EVENT AND	 WILLSUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE AS AND WHEN DETERMINED.									4	T			E26NE				 
2005042500133	20050425	00133	NE  	2005	4	25	CA050213004      	1	20050205	G	2820	3020030	TUBE            			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					FUEL MANIFOLD	WORN            	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) PRIOR TO TAKEOFF, ENGINE POWER REDUCED ACCOMPANIED BY AN INCREASE IN FUEL FLOW.  THE TAKEOFF WAS ABORTED.  SUBSEQU	ENT INSPECTION REVEALED A DISLODGED FUEL MANIFOLD TUBE WITH A WORN RETAINING PLATE COLLAR.					1	G	7	2 	4U	4	U		H1NE    	E4EA				 
2005042500134	20050425	00134	EA  	2005	4	25	CA050213005      	2	20050104	G	7200		ENGINE          								PWA   	PT6   	PT6*        	52043	EA  						FAILED          	W				O				OTHER                   				T	J		ENGINE CASE PENETRATION   	WARNING INDICATION        		AP	APPROACH       	1			CA								CP000666109			(CAN) THE ENGINE EXPERIENCED A FAILURE ON APPROACH AND A SINGLE ENGINE LANDING RESULTED. SUBSEQUENT INSPECTION EVIDENSED	 PUNCTURE HOLES IN THE GAS GENERATOR CASE.  PWC WILL INVESTIGATE THE EVENT AND WILL SUPPLIMENT THIS REPORT TO REFLECT RO	OT CAUSE AS AND WHEN ESTABLISHED.									3	T			E2NE				 
2005042500135	20050425	00135	NE  	2005	4	25	CA050213006      	2	20050207	G	7200		ENGINE          			AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A34AG    	52053	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A	J		FLAME/FIRE                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING FLIGHT ENGINE OIL PRESSURE AND TURBINE TEMPERATURE INCREASED.  OIL PRESSURE SUBSEQUENTLY REDUCED, ACCOMPANI	ED BY FLAMES FROM THE ENGINE EXHAUST.  THE PILOT SHUT THE ENGINE DOWN IN FLIGHT AND CARRIED OUT AN EMERGENCY LANDING.  M	FG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL SUPPLIMENT THIS REPORT TO REFLECT ROOT CAUSE AS AND WHEN ESTABLISHED	.			1	L	7	1 	3T	4	T	NC	A17SW   	E4EA				 
2005042500136	20050425	00136	EA  	2005	4	25	CA050213007      	2	20050203	G	7250		ENGINE          			DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  						POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								86588			(CAN) DURING CRUISE, THE ENGINE LOW OIL PRESSURE INDICATOR ANNUNCIATED ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION.  T	HE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE VANES	 AND BLADES AND A PUNCTURED EXHAUST EJECTOR AND NACELLE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL SUPPLEMEN	T THIS REPORT TO REFLECT ROOT CAUSE ONCE DETERMINED.			2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
2005042500137	20050425	00137	EU  	2005	4	25	CA050213008      	1	20050208	G	7312	10839	FUEL HEATER     			FOKKER	F27   	F27FOKKER*  	4990614	EU  	PWA   	PWA120	PW125B      	 	NE  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			10266								(CAN) FUEL WAS FOUND LEAKING FROM THE FUEL HEATER DURING MAINTENANCE OPERATIONS. THE LEAK WAS FOUND TO BE ASSOCIATED WIT	H CORROSION PITTING.					2	H	7	2 	4T	4	T		A817    	E20NE				 
2005042500138	20050425	00138	SW  	2005	4	25	CA050214001      	1	20050211	G	3212	2060739155	VALVE           	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					EMERGENCY FLOAT	OBSTRUCTED      	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FLOAT BAGS WOULD NOT INFLATE DURING 3 YEAR OPERATIONAL CHECK, THE VALVE ASSY WAS ASSEMBLED WITH THE SHEARED PORTIO	N OF THE SHEAR HEAD STILL IN THE VALVE OBSTRUCTING THE AIR FLOW TO THE BAGS.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005042500139	20050425	00139	EA  	2005	4	25	CA050214002      	2	20050124	G	7200		ENGINE          								PWA   	PT6T  	PT6T3       	52045	EA  						INOPERATIVE     	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								TH0196			(CAN) FOLLOWING FIRST START OF THE DAY THE ENGINE EXPERIENCED AN UNCOMMANDED N2 ACCELERATION.  THE PILOT SHUT THE ENGINE	 DOWN.  MFG WILL INVESTIGATE THE EVENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERMINED.										4	U			E22EA				 
2005042500140	20050425	00140	NM  	2005	4	25	CA050214003      	1	20050204	G	5270	21EN96	SWITCH          	AEI         		BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CARGO DOOR	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) MAIN CARGO DOOR LIGHT AND HOOKS UNLOCKED LIGHT ILLUMINATED AFTER TAKEOFF.  AIRCRAFT RETURNED TO AIRPORT AND LANDED	 OVERWEIGHT. CARGO DOOR VERIFIED CLOSED AND LOCKED. MAIN CARGO DOOR INDICATION MEL RAISED AND OVERWEIGHT LANDING INSPECT	ION C/O IAW MM 5-51-61.   PROBLEM DID NOT REOCCUR DURING NEXT TWO FLIGHT LEGS FOR THE DAY. MAINTENANCE CARRIED OUT A DVI	 INSPECTION OF ALL SWITCHES, RIG CHECK, CLEAN AND LUGGED WITH NO FAULTS FOUND. MEL CLEARED.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005042500141	20050425	00141	NE  	2005	4	25	CA050214004      	2	20050211	G	7200		ENGINE          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  						SMOKE           	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PUSH BACK, SMOKE WAS OBSERVED IN THE CABIN AREA WHILE ENGINES WERE BEING STARTED.  THE AIRCRAFT RETURNED TO	 THE GATE.  ENGINE STARTS WERE CARRIED OUT AT THE GATE AND THE SMOKE WAS NO LONGER OBSERVED IN THE CABIN.  DE-ICING FLUI	D WAS SUSPECTED.  NO FURTHER INCIDENT DURING SUBSEQUENT START.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005041200052	20050412	00052	EA  	2005	4	12	CA050214005      	2	20050210	G	7230		STRUT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COMPRESSOR	CRACKED         	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		DE	DESCENT        	1			CA								FA0190FA0191			(CAN) ON DESCENT, THE AIRCRAFT CABIN AIR WAS CONTAMINATED WITH SMOKE.  A SIMILAR PROBLEM HAD BEEN ENCOUNTERED THE PREVIO	US DAY DURING GROUND HANDLING.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE COMPRESSOR INNER SUPPORT OF ENGINE FA0190 A	ND CRACKING OF TWO INTER-COMPRESSOR CASE STRUTS ON ENGINE FA0191.  MFG WILL INVESTIGATE TO ESTABLISH ROOT CAUSE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005042500142	20050425	00142	NM  	2005	4	25	CA050214006      	1	20050214	G	2742	PNB18834	BALLSCREW       			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					STAB TRIM ACTUAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0247					(CAN) FAULT: WHILE CARRYING OUT AN INSPECTION.  FOUND RUSTY COLORED LUBRICANT AND REDDISH STAINING ON THE STAB. JACKSCRE	W GIMBAL.   A PURGING OF THE LUBRICANT FROM THE GIMBAL ASSY WAS CARRIED OUT.  THE RUST COLORING WAS CONFIRMED TO BE DUE 	TO IRON IN THE GREASE.  FURTHER INSP ALSO REVEALED DAMAGE TO THE THREADS OF THE BALLSCREW.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005042500143	20050425	00143	SO  	2005	4	25	CA050214007      	1	20050202	G	5740		DRAG ANGLE      			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35708								(CAN) APPLICATION OF SB 382-53-61 RESULTED IN FINDING A 8-10 INCH CRACK, BEING LOCATED IN THE TARGET AREA ON THE RT SIDE	 IN THE RADIUS OF THE DRAG ANGLE BETWEEN STATION 477 AND 517.					2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2005042500144	20050425	00144	NM  	2005	4	25	CA050215002      	1	20050215	G	2742	PN0411	BALLSCREW       			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					STAB TRIM ACTUAT	CORRODED        	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA						SN0283					(CAN) INSP OF HORIZONTAL STABILIZER SCREWJACK DURING M01 CHECK REVEALED EVIDENCE OF INTERNAL CORROSION AS A RESULT OF DI	SCOLORATION IN LUBRICANT.  TEARDOWN AND SHOP ANALYSIS REQUESTED WITH RESULTS TO BE FORWARDED TO AWC/YUL. NOTE: SDR ISSUE	D AGAINST (GDSP) REFLECTING SIMILAR CORROSION CONCERNS.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005042500145	20050425	00145	NM  	2005	4	25	CA050215003      	1	20050211	G	3350	552198	BATTERY PACK    	GRIMES      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	EMERGENCY LIGHT	BURNED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			12411			112					(CAN) WHILE CARRYING OUT A FUNCTION TEST OF THE EMERGENCY LIGHTING SYSTEM DURING A LINE CHECK, THE LT EGRESS LIGHT WAS F	OUND UNSERVICEABLE. THE EMERGENCY LIGHT BATTERY PACK FOR THAT LIGHT WAS REPLACED AND THE U/S UNIT WAS SENT TO THE AVIONI	CS SHOP.  WHEN THE BATTERY PACK WAS DISASSEMBLED IN THE SHOP, THE BURN DAMAGE TO THE CELLS WAS NOTED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005042500146	20050425	00146	WP  	2005	4	25	CA050215004      	1	20050214	G	3241	4062515	TRANSDUCER      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ANTI-SKID SPEED	DAMAGED         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF, THE CREW OBSERVED THE (WHEEL NOT TURNING LIGHT) WAS ON.  THE TAKE-OFF WAS REJECTED SUCCESSFULLY A	ND RETURNED TO THE GATE.  MAIN FOUND THE NR 1 ANTI-SKID SPEED TRANSDUCER DAMAGED DUE TO HEAT.  THE ASSY WAS REPLACED AND	 CHECKED SERVICEABLE IAW MM 32-43-02. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500147	20050425	00147	SW  	2005	4	25	CA050215005      	1	20050212	G	6410	427016001109	BLADE           			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					TAIL ROTOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER AIRCRAFT RECONFIGURATION AT OUR FACILITY, NORMALLY INSTALLED THE RADS EQUIPMENT FOR VIBRATION ANALYSIS ON TH	E T/R SYSTEM.  NOTICED A SLIGHTLY HIGH VIBRATION LEVEL WHICH  WERE UNABLE TO BRING TO A STANDARD LEVEL. AFTER INVESTIGAT	ION, FOUND OUT THAT ONE OF THE T/R BLADE WAS WATER CONTAMINATED. REPLACED THE T/R BLADE AND THE T/R WAS BALANCE BEYOND, 	1 IPS.			1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2005042500148	20050425	00148	WP  	2005	4	25	CA050215006      	1	20050215	G	6310	369H5660	COUPLING        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TRANSMISSION	UNDERSIZE       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION BEFORE BEING ENTERED INTO STORES IT WAS NOTED THAT THE BOLT HOLES WERE UNDERSIZE.  THE COUPLING HA	S BEEN RETURNED TO THE PARTS SUPPLIER.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005041200031	20050412	00031	NM  	2005	4	12	CA050215007      	1	20050211	G	3350	5521981	CELL            	GRIMES      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	EMERGENCY LIGHT	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12160			1990					(CAN) EMERGENCY LIGHT BATTERY PACK WAS REMOVED FROM AIRCRAFT FOR A SCHEDULED MAINTENANCE RESTORATION TASK 3350/05 AND SE	NT TO AVIONICS SHOP. DURING INSPECTION OF THE CELLS, BURN MARKS ON STRAPS BETWEEN CELLS WERE NOTED.  DURING DEEP CYCLE P	ROCESS, UNIT DISCHARGED AND DURING DISCHARGE UNDER A 4 AMP LOAD, CELLS BECAME EXCESSIVELY HOT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005041200049	20050412	00049	EA  	2005	4	12	CA050215008      	1	20050209	G	5210	NAS620754D	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, CREW RECEIVED A (PAX DOOR LATCH) MESSAGE, AND THEN A (PASSENGER DOOR WARNING MESSAGE). CREW FOLLOWED	 QRH PROCEDURES AND COMPLETED AN UNEVENTFUL OVERWEIGHT LANDING. TROUBLESHOOTING FOUND BOLT P/N NAS6207-54D SEIZED IN BUS	HING P/N NAS74A7E302P AS PART OF PASSENGER DOOR MID PIVOT ASSY.  ALSO FOUND UPPER PIVOT ASSY 601R38383-1 VERY STIFF.  IP	C 52-11-02 FIG 2. BOTH FITTINGS AND ASSOCIATED HARDWARE REPLACED. DOOR RIGGED, FUNCTION TESTED AND RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005041200050	20050412	00050	EU  	2005	4	12	CA050215009      	1	20050113	G	2910	NE15FBATFI1T	SWITCH          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT COULD NOT TURN HYD OFF DURING FLIGHT BY PRESSING BUTTON ON COLLECTIVE STICK. TROUBLESHOOTING DETERMINE THE S	WITCH WAS DEFECTIVE AND NOT SUPPLYING VOLTAGE TO SOLENOIDS.  NEW SWITCH INSTALLED.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005041200051	20050412	00051	EU  	2005	4	12	CA050215010      	1	20050211	G	2150	BAS16346416	SLEEVE          			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					A/C PACK	DISCONNECTED    	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) UPON REACHING CRUISING ALTITUDE, THE AIRCRAFT STARTED LOSING PRESSURIZATION.  THE CREW DONNED THEIR OXYGEN MASKS, 	AT WHICH TIME THERE WAS A TOTAL LOSS OF PRESSURIZATION. UPON RETURNING TO MAINTENANCE, FOUND THAT THE SLEEVE CONNECTING 	THE DUCT TO THE WATER SEPARATOR HAD BECOME DISCONNECTED EVEN THOUGH THE CLAMPS WERE TIGHT.  SLEEVE SECURED.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005042500149	20050425	00149	EU  	2005	4	25	CA050215011      	1	20050211	G	2730		CONTROL CABLE   			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					ELEVATOR	MISLOCATED      	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) ELEVATOR CABLE UNDER CO-PILOT SEAT SLIPPED OFF THE CABLE GUIDE						2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005042500150	20050425	00150	EA  	2005	4	25	CA050215012      	1	20050210	G	3230		CONNECTOR       	VICKERS     		CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					SELECTOR VALVE	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA						089					(CAN) ON APPROACH, NLG WOULD NOT DEPLOY UPON NORMAL SELECTION OF LANDING GEAR DOWN.  EMER EXTENSION WAS COMPLETED, AC LA	NDED WITHOUT FURTHER INCIDENT, FOUND THAT (NLG) SELECTOR VALVE WAS AT FAULT.  PINS IN CONNECTION TO EXTEND SOLENOID WHIC	H CONTROLS DOWN SELECTOR VALVE WAS CHANGED OUT, AC WAS RETURNED TO SERVICE. CHANGING NLG SELECTOR VALVE ALSO RECTIFIED P	ROBLEM WITH NOSE WHEEL STEERING SYS.  AC HAD BEEN OPERATING ON A MEL FOR STEERING SYS. NLG SELECTOR VALVE FEEDS HYD PRES	SURE TO ARMING VALVE OF STEERING SYSTEM ONLY WHEN DOWN POSITION.  TO APPLY THIS MEL THERE IS MAINT PROCEDURE WHICH SHOUL	D IDENTIFY FAULTY NLG SELECTOR VALVE, NOT ALLOW THE MEL. DUE TO INTERMITTENT NATURE OF FAULT PROCEDURE WAS CARRIED OUT.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2005042500151	20050425	00151	EU  	2005	4	25	CA050215013      	1	20050214	G	2752	9787320309	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS WERE SELECTED TO 40, PRIOR TO REACHING 15, FLAPS LABORED AND STOPPED FOR A FEW SECONDS, THEN RESUMED IN TRAN	SIT. THIS HAD HAPPENED AT LEAST TWICE IN THE HANGAR BEFORE.  AT NO TIME WAS THE (FLAP) ANNUNCIATOR ILLUMINATED.  WHEN TH	IS OCCURRED AS PREVIOUSLY STATED, THE LT OB ACTUATOR WAS ONCE FOUND TO BE VERY WARM TO THE TOUCH WHILE THE OTHER 3 WERE 	COLD. THIS CONDITION WAS NOT ALWAYS PRESENT.  FLAP CODE E208 WAS LOGGED. ONCE THE ACTUATOR WAS ON THE BENCH IT WAS ALSO 	NOTED THAT A (ROUGH) SPOT COULD BE FELT WHILE ROTATING THE JACKSCREW.  SUSPECTED ACTUATOR REPLACED. FUNCTION CHECKS NORM	AL.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005042500152	20050425	00152	EA  	2005	4	25	CA050215014      	1	20050212	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) COPILOT SIDE WINDOW CRACKED.  WINDOW REPLACED IAW AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005042500153	20050425	00153	CE  	2005	4	25	CA050216001      	1	20050203	G	3213	67410172	PIN             	CESSNA      		CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN THE MLG TRAILING LINK WAS REMOVED TO DEAL WITH A MINOR CORROSION ISSUE THE LINK PIN ASSY WAS FOUND CORRODED I	NSIDE AT THE LOCKING NUT END.  THE LINK PIN IN QUESTION IS OPEN AT THE IB END WHEN INSTALLED AND IT HAD ACCUMULATED SAND	, OTHER DEBRIS AND WATER THAT COLLECTED AT THE NUT END CAUSING THE CORROSION.  THE LINK PIN WAS REPLACED WITH A NEW ONE.	  THE NEW LINK PIN IS CLOSED AT THE IB END AND HAS A GREASE NIPPLE FITTED.  WHEN THE NEW PIN IS INSTALLED IT IS FILLED W	ITH GREASE TO PREVENT THIS SITUATION FROM DEVELOPING.		2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005042500154	20050425	00154		2005	4	25	CA050216002      	4	20050215	G	3497		WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITOT HEAT	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) P-S NR 1 FAIL ANNUCIATOR ILLUMINATED.  PITOT HEAT FOUND INOPERATIVE.  FURTHER INVESTIGATION REVEALED A BROKEN/SEPE	RATED WIRE H126D16 AT PLUG P101 OF THE RH (NR 1) PITOT TUBE CONNECTOR.  REPAIRED, FUNCTION CHECKS NORMAL.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005042500155	20050425	00155	CE  	2005	4	25	CA050216003      	1	20050203	G	3213	67410172	PIN             	CESSNA      		CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN MLG TRAILING LINK WAS REMOVED FOR TREATING MINOR CORROSION THE LINK PIN WAS FOUND CORRODED INSIDE AT THE LOCK	 NUT END.  THE LINK PIN IS OPEN AT THE IB END WHEN INSTALLED AND HAD ACCUMULATED SAND AND OTHER DEBRIS AND WATER CAUSING	 THE CORROSION. THE NEW LINK PIN THAT WAS INSTALLED IS CLOSED AT THE IB END AND FITTED WITH A GREASE NIPPLE.  THE LINK P	IN IS FILLED WITH GREASE AFTER INSTALLATION TO PREVENT THIS PROBLEM FROM REOCCURRING.			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2005041200032	20050412	00032	EA  	2005	4	12	CA050216004      	1	20050216	G	2810	21564075	FUEL TANK       			CNDAIR	CL215 	CL2156B11415	       	EA  											LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) RECEIVED A COUPLE OF FUEL RUBBER TANKS REPAIRED FROM MFG THAT WE HAVE PROBLEM WITH.  EACH TIME THAT WE DO RECEIVE 	NOW, WE TEST THEM BEFORE THE INSTALLATION ON THE A/C TO MAKE SURE THEY DON'T LEAK.  SOMETIMES THEY LEAK FROM THE REPAIR 	PATCH OR THE JOINT.  THIS TIME IS FROM WHAT WE CALL THE (CENT).				2	H	7	2 	4T			RT	A14EA   					 
2005041200053	20050412	00053	SO  	2005	4	12	CA050216005      	2	20050131	G	8520	654724	PISTON PIN      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PISTON (NR1) BROKE AT PIN BOSS RESULTING IN LARGE CHUNKS OF ALUMINUM FALLING INTO THE ENGINE, ENDING UP AT THE BOT	TOM OF THE SUMP. SMALLER PIECES OF THE METAL WERE SUCKED UP THROUGH THE OIL PICK-UP AND RAN THROUGH THE OIL PUMP.					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
2005050300197	20050503	00197	EA  	2005	5	3	CA050216006      	1	20050215	G	5740		ATTACH FITTING  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT WING	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22812								(CAN) FORWARD RT WING ATTACH FITTING FORWARD SIDE FLANGED BUSHING HAS COMPLETE SEPARATION OF FLANGE FROM BUSHING SLEEVE.	   RECTIFICATION REQUESTED FROM MFG.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005041200054	20050412	00054	EU  	2005	4	12	CA050216007      	1	20050207	G	1430	C551S1101052	RIVET           	UROCOP      		UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					HORIZONTAL STAB	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DVDB1					(CAN) DURING AME DAILY INSPECTION LT HORIZONTAL STABILIZER FOUND TO HAVE APPROXIMATE 1 INCH VERTICAL DISPLACEMENT AT TIP	.  RIVETS THAT SECURE THE OUTER SHIM HAD SHEARED ALLOWING BUSHING MOVEMENT. SB 55-001 TO BE INCORPORATED , NOT PREVIOUSL	Y COMPLIED WITH. TO BE CARRIED OUT.				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2005041200055	20050412	00055	SW  	2005	4	12	CA050216008      	1	20050208	G	7120	206031302189	CHANNEL         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					RT ENG MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN CHANNEL AT RT FORWARD ENGINE MOUNT ATTACH AREA. CRACK APPROXIMATE 1.55 INCH.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005042500156	20050425	00156	EU  	2005	4	25	CA050216009      	1	20050216	G	5302	1400200201	SKIN            			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON VERTICAL UPPER FIN.						1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2005042500158	20050425	00158	NE  	2005	4	25	CA050217001      	2	20050204	G	7210		DRIVE SHAFT     								PWA   	JT15  	JT15D5      	52112	NE  					AGB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								108050			(CAN) UPON REMOVAL OF THE AGB FROM THE ENGINE IT WAS FOUND THAT THE AGB DRIVE SHAFT HAD DECOUPLED FROM THE HIGH ROTOR AN	D HAD FALLEN INTO THE GEARBOX CAUSING INTERNALDAMAGE. THE SHAFT FELL INTO THE AGB DUE TO THE SHAFT SUPPORT PLUG COMING O	UT OF THE AGB DRIVE BEVEL GEAR (P/N 3105380-01). THE PIN THAT IS INTENDED TO RETAIN THE SHAFT SUPPORT PLUG IN THE GEAR A	PPEARED TO BE MISSING.								4	F			E25EA				 
2005042500159	20050425	00159	CE  	2005	4	25	CA050217002      	1	20050208	G	7500	42302200	SWIVEL          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					PYLON DUCT	LEAKING         	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THE RT ENG PYLON OVHT CAS WARNING ILLUMINATED.  EMERGENCY PROCEDURES CARRIED OUT AND POWER REDUCED ON	 RT ENGINE.  ANNUNCIATOR LIGHT EXTINGUISHED 60 TO 90 SECONDS AFTER POWER WAS REDUCED.  AN UNSCHEDULED LANDING WAS CARRIE	D OUT. UPON INSPECTION AND GROUNDS RUNS PERFORMED, THE RT PYLON HIGH PRESSURE DUCT ASSEMBLY, P/N LJ01317-002 WAS FOUND T	O BE LEAKING FROM A SWIVEL JOINT. THE JOINT WAS FOUND TO BE NOT AS TIGHT AS THE OPPOSITE END AND IT APPEARED THAT SOMEON	E HAD ATTEMPTED A LEAK REPAIR OF THE SWIVEL JOINT WITH 763 HIGH TEMP RTV.  DUCT ASSEMBLY P/N LJ01317-002 WAS REPLACED AN	D LEAK CHECKS COMPLETED.  AN OVERWEIGHT LANDING CHECK WAS ALSO CARRIED OUT AND THE AIRCRAFT RELEASED FOR SERVICE.	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005050300196	20050503	00196		2005	5	3	CA050217003      	4	20050117	G	8300	31024001	STUD            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBOX	FAILED          	W				O				OTHER                   				D	E	P	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	NO WARNING INDICATION     	IN	INSP/MAINT     	1			CA			13504					P63243C			(CAN) GEARBOX COMPRESSOR BEARING RETAINING STUDS FAILED CAUSING THE NR 1 IDLER TO MISALIGN WITH THE FCU DRIVE TRAIN AND 	THE ROTATING GROUP TO MOVE FORWARD.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2005050300195	20050503	00195	NM  	2005	5	3	CA050217004      	1	20050214	G	2421	736664E	IDG             			BOEING	757   	757200      	1384950	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					GENERATOR	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								30776			(CAN) DURING INITIAL CLIMB, DEPARTING OGG, R (GEN DRIVE) MESSAGE DISPLAYED, GEN DRIVE LIGHT ILLUMINATED.  RT IDG DISCONN	ECTED.  AIRCRAFT DIVERTED.  RT IDG REPLACED WITH LOANER UNIT, A/C DEPARTED, NO FAULTS REPORTED.  REPLACEMENT UNIT FITTED	.  IDG SENT TO OEM FOR TEARDOWN AND REPAIR.  AWAITING STRIP REPORT.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005042500160	20050425	00160	CE  	2005	4	25	CA050217005      	1	20050210	G	2910	847898	SELECTOR VALVE  	VICKERS     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT WING ROOT	INTERMITTENT    	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			13027			MX580596					(CAN) YAW DAMPER KICKED OFF UNCOMMANDED, GEAR SELECTED DOWN WITH NO FUNCTION,  IT WAS NOTICED THAT L/G CNTRL C/B WAS TRI	PPED, RESET, LANDING WAS UNEVENTFUL.  PILOTS CONTINUED, C/B WAS TRIPPED WITH YAW DAMP ON.  YAW DAMPER WAS DISENGAGED, C/	B RESET, GEAR SELECTED DOWN.  CONTINUED W/O USE OF YAW DAMPER. ON APPROACH C/B WAS NOTED TO BE TRIPPED, WOULD NOT RESET.	  CONTINUED, GEAR WAS MANUALLY EXTENDED, LANDING WAS NRML. MAINT FOUND WIRING ON LT UP/DOWN LOCK SWITCHES CHAFFED, REPAI	RED, REMOVED L/G SEL CONNECTOR PLUG, REINSTALLED.  ON APPROACH, L/G C/B TRIPPED AGAIN, IT WAS RESET, GEAR EXTENDED.  UNE	VENTFULL LANDING. DETERMINED SEL VALVE ON HYDR PWR PACK WAS INTERMITTENT. PWR PACK WAS REPLACED, AC RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005050300194	20050503	00194	CE  	2005	5	3	CA050218001      	1	20050209	G	3230	071349561	GEARBOX         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	LEFT	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING I HEARD A FAINT CRACKING SOUND, AS I TAXIIED OF THE RUNWAY. THE LT WING THEN DROPPED ABOUT 18 INCHES BE	FORE COMING TO A STOP.  THE WING ENGINE DID NOT TOUCH THE GROUND.  THIS WAS OUR SECOND SKI TRIP OF THE DAY. UPON CHECKIN	G WE DISCOVERED THE LT GEARBOX CRACKED.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P21EA	 
2005050300193	20050503	00193	EA  	2005	5	3	CA050218002      	1	20050217	G	6120	7827402	RETAINER        	HAMSTD      		CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	ACTUATOR	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						940104					(CAN) RETAINER, UNIVERSAL WAS FOUND WITH RELATIVE MOTION BETWEEN RETAINER AND RING, IPL 5-270C.   CRIMPS (DIMPLES) HAD W	ORN OFF OF ONE OF FOUR DIMPLES ALMOST COMPLETELY, HALF THE DIAMETER OF TWO OTHERS. REPAIR 9-1 DETAILS INSTRUCTIONS FOR R	EPLACEMENT OF THE RETAINER. THE INSPECTION FOR RELATIVE MOTION BETWEEN THE RETAINER AND RING IS LISTED AS A (DCC), DESIG	N CRITICAL CHARACTERISTICS, WHICH THERE IS NO MOVEMENT ALLOWED IAW THE REPAIR. THE RETAINER IS PART OF THE PITCH LOCK VA	LVE ASSEMBLY OF THE ACTUATOR. IF THE RETAINER WERE TO COME OFF OF BLADE ANGLE. IT COULD ALSO ALLOW THE PIVOT PINS IPL 5-	260C TO COME OUT THE RING, WHICH COULD CAUSE A TOTAL LOSS OF CONTROL OF PITCH CHANGE FOR THE PROPELLER.	2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2005050300192	20050503	00192	NM  	2005	5	3	CA050218003      	1	20050210	G	7920	81196501	TUBE            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					GEARBOX	SEPARATED       	W				E	J	A		ENGINE SHUTDOWN         	DUMP FUEL               	UNSCHED LANDING         		K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			44603								(CAN) DURING CLIMB THROUGH 18000 FT ENGINE NR 1 LOW OIL PRESSURE LIGHT ILLUMINATED ACCOMPANIED BY RAPIDLY DECREASING OIL	 QUANTITY AND PRESSURE INDICATIONS. CREW CARRIED OUT ENGINE SHUTDOWN CHECKLIST DECLARED AN EMERGENCY, DUMPED FUEL AND RE	TURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. DURING INVESTIGATION BY MAINTENANCE, IT WAS FOUND THAT THE GEARBOX TO OIL 	COOLER LINE HAD PULLED DIRECTLY OUT OF THE ENGINE GEARBOX HOUSING. THIS IS NOT REPAIRABLE ON-WING AND DUE TO THE LENGTH 	OF TIME ENGINE WINDMILLED WITHOUT OIL, RESULTS IN AN ENGINE CHANGE. AS A PRECAUTION WE ARE CARRYING OUT A FLEETWIDE INSP	ECTION FOR ANY SEPARATION BETWEEN THIS LINE AND THE GEARBOX ON ALL ENGINES.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005042500161	20050425	00161	SW  	2005	4	25	CA050218004      	1	20050126	G	6340	206076373001	SPLINE          			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TACH GENERATOR	STRIPPED        	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT LOST NR INDICATION, THEN HYDRAULICS TO FLIGHT CONTROLS. PILOTS LANDED IMMEDIATELY. TACH GENERATOR AND HYDRAU	LIC PUMP REPLACED. TACH GENERATOR DRIVE REMOVED AND SPLINE INSIDE TACH GENERATOR FOUND TO BE STRIPPED.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005050300189	20050503	00189	CE  	2005	5	3	CA050218005      	1	20050214	G	2820	050011874	LINE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL SYS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10473								(CAN) DURING INSPECTION OF NOSE GEAR STEERING TUBE ASSEMBLY ON RT SIDE. THE MAIN FUEL LINE ASSEMBLY (UNION TO FUEL STRAI	NER) FOUND BADLY CHAFED THROUGH SIDEWALL OF L INE ASSEMBLY CAUSED BY POOR CLEARANCE BETWEEN FUEL LINE ASSEMBLY AND NOSE 	GEAR STEERING TUBE. DAMAGE WAS OVER 1INCH OF LENGTH AND 90 PERCENT OF TUBE WALL WORN WHICH WAS EASY PUNCTURED BY A SMALL	 METAL PICK.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005050300183	20050503	00183	CE  	2005	5	3	CA050218006      	1	20050214	G	3250	C109	BALL JOINT      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LT NOSE GEAR	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			10473								(CAN) PILOT REPORT PROBLEM, TO TAXI AIRCRAFT ON THE RAMP.  AIRCRAFT INSPECTED AND FOUND LT NOSE GEAR TUBE ASSEMBLY, STEE	RING BALL JOINT BROKEN.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005041200062	20050412	00062	EU  	2005	4	12	CA050218007      	1	20050216	G	7540	D48366403	SWITCH          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					SHROUD OVERHT	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CLIMB, NR1 ENGINE BLEED FAULT ILLUMINATED.  AT CRUISE, THE BLEED WAS RESET RESULTING IN THE SAME BLEED DUCT	 LEAK ALERT.  THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT.  MAINTENANCE REPLACED THE LT SHROUD OVERHEAT SWITCH IAW MM	 36-11-11 AND TESTED SERVICEABLE IAW MM 36-11-11-720-855.  THE AIRCRAFT WAS DISPATCHED WITH NO FURTHER PROBLEM DURING SU	BSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005041200061	20050412	00061	WP  	2005	4	12	CA050218008      	1	20050216	G	5320	99118755	INTERCOSTAL     			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					AFT FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24108								(CAN) WHILE PERFORMING TROUBLESHOOTING ON A POSSIBLE RUDDER PCU HYDRAULIC LEAK, FOUND RUDDER SUPPORT BRACKET, ALL FASTEN	ERS LOOSE (SIX OFF) AND INTERCOSTAL BETWEEN TWO FRAMES SUPPORTING PCU BRACKET, CRACKED.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005041200060	20050412	00060	EU  	2005	4	12	CA050218009      	1	20050216	G	7920		VENT LINE       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	ENGINE BREATHER	BLOCKED         	W				D				RETURN TO BLOCK         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI FROM COMPANY RAMP THE LAVATORY SMOKE DETECTOR INDICATOR ILLUMINATED, VISIBLE SMOKE WAS OBSERVED IN THE	 CABIN. THE AIRCRAFT WAS RETURNED TO THE COMPANY RAMP AND SHUTDOWN.  MAINTENANCE FOUND OIL DRIPPING FROM THE NR 2 ENGINE	 TAIL PIPE. IT WAS DETERMINED THAT A COUPLING HOSE IN THE ENGINE VENT LINE HAD FOULED DURING REASSEMBLY. THE INNER LININ	G OF THE COUPLING HAD CAUGHT ON THE TUBE FOLDING INWARD CAUSING A BLOCKAGE IN THE VENT LINE. THE COUPLING WAS REPLACED A	ND THE AIRCRAFT GROUND RUN AND TEST FLOWN BEFORE RETURNING TO SERVICE.		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2005041200026	20050412	00026	EA  	2005	4	12	CA050218010      	2	20050217	G	8520		CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT ENGINE LEAK, ENGINE RUN TO CONFIRM LEAK, HARD TO FIND, ENGINE PRESSURIZED, FOUND CRACK OF 1.5 INCH LONG FORWARD	 OF CYLINDER NR2 IN THE CASE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005050300182	20050503	00182	SO  	2005	5	3	CA050218011      	2	20050212	G	8520		CONNECTING ROD  			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  	MCAULY	3AF32C	3AF32C*     	GL  	ENGINE	BENT            	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) AIRPLANE FLYING AT CRUISE POWER, ENGINE FEATHERED ON ITS OWN, ENGINE PARAMETER CHECK, NO OIL PRESSURE.  ENGINE SHU	TDOWN, RETURN TO AIRPORT. INITIAL CHECK REVEALED METAL CONTAMINATION, ENGINE SENT TO ENGINE REPAIR SHOP, REPORT OF NR 6 	CONNECTING ROD BENT, CAUSING THE FAILURE.				1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2005050300181	20050503	00181	EA  	2005	5	3	CA050221001      	2	20050216	G	7200		TORQUE SHAFT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1 ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								FA0167			(CAN) DURING CLIMB,  NR1 PEC CAUTION LIGHT ILLUMINATED FOLLOWED BY A DROP IN NP AND TQ.  A FEW SECONDS LATER THE NR1 ENG	 FADEC FAIL WARNING LIGHT ILLUMINATED AND ALL PARAMETERS BECAME (DASHES).  THE PILOTS ELECTED TO SHUTDOWN NR1 ENGINE AND	 RETURN TO BASE.  SINGLE ENGINE LANDING COMPLETED. ENG FAULTS BOTH CHANNELS 162, 470, 719, 734, 735, 938. AND CHANNEL-A 	HAD FAULT: 718-MECHANICS FOUND THE TORQUE SHAFT REFERENCE TUBE SEPARATED FROM THE TORQUE TUBE. THE CRACK/SEPARATION OCCU	RRED JUST AFT OF THE WELD THAT JOINS THE TWO PIECES TOGETHER (VERIFIED BY REMOVING LAY SHAFT COVER).  ENGINE ASSEMBLY RE	PLACED.  FOLLOW-UP INVESTIGATION TO BE CARRIED OUT.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005050300180	20050503	00180		2005	5	3	CA050221003      	4	20050217	G	2330	3042865102	ELECTRICAL BOX  			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT	OVERHEATED      	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) ON GROUND, DURING TURN AROUND, AN ODOR WAS NOTICED MID CABIN. THIS WAS ISOLATED TO THE SEAT ELECTRONICS BOX AT ROW	 14.  THE BOX WAS WARMER THAN NORMAL TO THE TOUCH.  THE SEB WAS REPLACED.  THE OPERATOR IS FOLLOWING UP WITH THE OEM TO 	GET TSN/TSO AND TEARDOWN INFORMATION.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005042500163	20050425	00163	CE  	2005	4	25	CA050221004      	1	20050218	G	2821	710C4X	VALVE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT NACELLE	MISSING         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			17414								(CAN) PILOT REPORTED RAPID FUEL LOSS IN FLIGHT.  INNER ASSY OF FUEL QUICK DRAIN FOUND TO BE MISSING FROM RT NACELLE FUEL	 FILTER QUICK DRAIN ASSY.  FUEL VALVE IS COMPRIZED OF 2 MAIN PARTS.  MAIN HOUSING, AND DRAIN ASSY.   MOVEABLE PART OF DR	AIN IS INSTALLED IN A HOUSING WHICH IS THEN INSTALLED IN MAIN HOUSING WITH AN O-RING. THIS IS A PRESS FIT WITH MULTIPLE 	STAKES AROUND CIRCUMFERENCE TO SECURE DRAIN ASSY IN MAIN HOUSING.  DRAIN ASSY WAS MISSING FROM MAIN HOUSING, AND O-RING 	WAS STILL INPLACE.  INFLIGHT PILOT NOTICED A RAPID FUEL LOSS FROM RT FUEL SYS.  AS FUEL SUPPLY GOT LOW, PILOT ELECTED TO	 SHUTDOWN ENGINE AND FEATHER PROP.  AC WAS ONLY MINUTES FROM DESTINATION, AND HOME BASE, SO NO DIVERSION WAS REQUIRED.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005041200033	20050412	00033	SO  	2005	4	12	CA050221005      	1	20050205	G	3220	40336000	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) IN DOING MFG SL NR1088, FOUND THE LINK ASSEMBLY CRACKED. ON DOING THE INSPECTION ON THE REST OF OUR FLEET, FOUND F	OUR MORE CRACKED.  WE WILL CONTINUE TO DO THE INSPECTION EVERY 500 HOURS IAW COMPLIANCE TIME OF SERVICE LETTER. DOING TH	E INSPECTION, ALSO NOTICED IN THE AREA OF THE CRACK THE ATTACHMENT LUGS HAD BEEN MADE WITH SHARP CORNERS AND NOT A SMOOT	H FINISH.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005050300179	20050503	00179	EA  	2005	5	3	CA050221006      	2	20050216	G	7200		TORQUE TUBE     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	ENGINE	DETACHED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								FA0167			(CAN) DURING CLIMB THE ELECTRONIC PROPELLER CONTROL ANNUNCIATED ACCOMPANIED BY AN AIRCRAFT YAW AND SUBSEQUENT FADEC FAIL	 WARNING.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION RE	VEALEDTHE ENGINE'S TORQUE TUBE DETACHED FROM ITS REFERENCE TUBE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005041200046	20050412	00046	NM  	2005	4	12	CA050221007      	1	20050202	G	2435	23088008	STARTER GEN     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT ENGINE	OPEN            	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT 16,000 FT, AC DEPRESSURIZED W/ILLUMINATION OF MSTR WARN LIGHT, MSTR CAUTION LIGHT, GPWS WARN LIGH	T. SYS THAT REPORTED TO STOP WORKING: FMS, NAV, TRANSPONDER SYS. NR2 ADF WAS REPORTED TO BE WORKING, WAS USED TO LAND.  	ON APPROACH, LG WAS SELECTED DOWN, FLAPS EXTENDED, CAUTION LIGHT WAS REPORTED TO EXTINGUISH: AUX INV, RUD FULL, NR2 RYD 	HYD.  WHEN AC WAS ON GROUND, BUS TIE SWITCH WAS SELECTED, AC STARTED TO PRESSURIZE.  LT STARTER/GEN FAILED TO GENERATE P	WR AND TO START ENGINE.  NEXT START, NR1 GCU AND STARTER/GEN REPLACED, GROUND CHECKED IAW 24-31-03, 24-31-01 NO DEFECTS 	EVIDENT.  START/GEN WAS CONFIRMED THAT UNIT HAD FAILED DUE TO NO GENERATION, SHUNT FIELD OF STATOR WAS OPEN CIRCUIT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005050300178	20050503	00178		2005	5	3	CA050221008      	4	20050202	G	6122		GOVERNOR        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) DURING FLIGHT, THE PROPELLER SPEED DECREASED TO 80 PERCENT UNCOMMANDED. THE CREW COULD NOT MODULATE THE PROPELLER 	SPEED AND SHUT THE ENGINE DOWN IN FLIGHT.  THE PROPELLER GOVERNOR WAS SUBSEQUENTLY REPLACED.					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2005050300177	20050503	00177	NE  	2005	5	3	CA050221009      	2	20050215	G	7200		ENGINE          			GULSTM	200   	200         	4500308	NM  	PWA   	306   	PW306B      	 	NE  	HARTZL	HCB3T	HCB3TN3     	GL  		FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								CC0116			(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A DECAY IN ALL ENGINE PARAMETERS.  THE CREW SHUT THE E	NGINE DOWN IN FLIGHT, DECLARED AN EMERGENCY AND DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DAMAGE T	O THE HIGH PRESSURE TURBINE.  MFG WILL INVESTIGATE THIS EVENT AND WILL SUPPLEMENT THIS REPORT TO REFLECT ROOT CAUSE ONCE	 DETERMINED.			2	L	7	2 	4F	4	F	RT	A53NM   	E35NE	6	C	P15EA	 
2005041200047	20050412	00047	EA  	2005	4	12	CA050222001      	1	20050211	G	5542	85540063101	SKIN            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18364								(CAN) DURING AN INSPECTION OF THE EMPENNAGE OF DASH 8-311 THE RUDDERS WERE MANUALLY MOVED FROM SIDE TO SIDE.  WHEN IT WA	S PUSHED FULL RT, TRAVEL A LARGE CRACK APPROXIMATELY TWO INCHES LONG WAS EXPOSED.  THIS CRACK BEGAN AT THE LOWER EDGE OF	 THE L/E SKIN AND CONTINUED FOR APPROXIMATELY TWO INCHES IN AND UPWARD DIRECTION.  UPON A CLOSER INSPECTION THE ROW OF R	IVETS SECURING THE LOWER EDGE OF THIS L/E SKINS TO THE BOTTOM FRAME HAD BEEN SHEARED ON BOTH LT AND RT FORWARD SKINS.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005041200048	20050412	00048	CE  	2005	4	12	CA050222002      	1	20050218	G	3297	MS24171D1	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	BURNED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) LANDING GEAR WAS SELECTED DOWN BUT THERE WAS NO LANDING GEAR EXTENSION. CREW NOTICED THAT THE TWO AMP LANDING GEAR	 RELAY CIRCUIT BREAKER, ADJACENT TO THE LANDING GEAR SELECTOR, WAS TRIPPED.  LANDING GEAR WAS SELECTED DOWN AND THE MANU	AL HANDPUMP USED TO GET LANDING GEAR DOWN AND LOCKED.  MAINTENANCE CHECKS WERE CARRIED OUT AND THE 60 AMP LANDING GEAR P	OWER CIRCUIT BREAKER IN THE LT ELECTRICAL EQUIPMENT PANEL WAS TRIPPED. THE LANDING GEAR MOTOR RELAY WAS REPLACED, ALL CI	RCUIT BREAKERS RESET AND LANDING GEAR RETRACTIONS/EXTENSIONS CARRIED OUT NORMALLY.  ON INSPECTION OF THE MOTOR RELAY THE	 MAIN CONTACTS (200AMP RATING) WERE BADLY BURNED AND PITTED.  SUSPECT THE RELAY WAS ORIGINAL FROM MANUFACTUR IN 1998.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005050300176	20050503	00176	GL  	2005	5	3	CA050222003      	2	20050218	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) PART CRACKED IN DOUBLE LIP AREA. NO CRACKS ALLOWED IN THIS LOCATION. MAJORITY OF COMBUSTION LINERS REMOVED ARE FOU	ND CRACKED IN THIS AREA.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005050300175	20050503	00175	NE  	2005	5	3	CA050222004      	2	20050222	G	7261		B-NUT           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					OIL LINE	LOOSE           	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LT ENGINE OIL INDICATING 7.5 QTS IN FLT WAS INDICATING 15 QTS ON GROUND 2 HOURS EARLIER. CONTINUED LEAKING AT ABOU	T 5 QT/HR.  A/C LANDED /DIVERTED FOR MAINTENANCE.  FOUND AFT BEARING OIL LINE B-NUT LOOSE. TIGHTENED B-NUT. BRACKET SECU	RED WITH RED RTU.  DUE LINE VIBRATING.  ENG RUN FOR 15 MINS. LEAK CHECKED OK. OILS SERVICED AS REQ'D.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005050300174	20050503	00174	EU  	2005	5	3	CA050222005      	1	20050222	G	2916		RESERVOIR       			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYD SYS	LOW             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYD GREEN RESERVOIR LOW LEVEL QTY ZERO.  GREEN RESERVOIR SERVICED IAW AMM 12-12-29-611-001.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005041200024	20050412	00024	EU  	2005	4	12	CA050222006      	1	20050222	G	3260		SENSOR          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NLG DOOR	OPEN            	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) LOWERED THE GEAR HANDLE AND GEAR SHOWED IN TRANSIT, THEN E-CAM FOR GEAR NOT DOWN AND LOCKED.  RECYCLED THE HANDLE 	AND GEAR CAME DOWN, LANDED WITHOUT INCIDENT.  POST FLT REPORT FLAGS RT NLG DOOR OPEN SENSOR 38GA. INTERCHANGED WITH C1 C	ARGO PROX SWITCH.  LGCIU TESTED ON SYSTEM 1 AND 2 WITH NO FAULTS. SERV.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005051000001	20050510	00001	NE  	2005	5	10	CA050222007      	2	20050215	G	7200		ENGINE          								PWA   	PT6   	PT6A60A     	52043	NE  						DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								95687			(CAN) AS A RESULT OF PROP STRIKE ENG SUFFERED SOME TIP RUBS IN COMPRESSOR, PT & SCORING DAMAGE IN A PROPSHAFT BOLT HOLE.	 FULL O/H LEVEL INSP OF RGB COMPONENTS FOUND ONLY NORMAL OPS DAMAGE WITH NO ADDITIONAL DAMAGES. ENG FOUND TO HAVE 14 OF 	47 1ST STAGE PT BLADES CRACKED IN FIRTREE ROOT.  IT IS POSSIBLE THAT THESE CRACKS ARE RESULT OF FATIGUE.   PROP STRIKE C	AUSED A DEFORMATION BENDING OF ONE OF THE PROP MOUNT BOLTS.  RUB DAMAGE FOUND IN COMPRESSOR IS ALSO CONSIDERED TO BE MIN	OR & IS ALSO SIMILAR TO THAT OF THE SISTER ENG. THIS TYPE OF DAMAGE IS NOT UNCOMMON FOR AN ENGINE WITH 3700 HOURS OF OPS	 BUT THE SIMILARITY TO THE SISTER ENG IT MAY ALSO BE WHOLLY OR PARTIALLY A RESULT OF THE SUDDEN STOPPAGE/PROP STRIKE.						4	T			E4EA				 
2005050300172	20050503	00172	EA  	2005	5	3	CA050222008      	1	20050219	G	2424	720846D	GCU             			CNDAIR	CL601 	CL6012A12   	1900303	EA  										GENERATOR	INOPERATIVE     	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) A FEW MINUTES AFTER TAKE-OFF FROM AIRPORT WHILE SHUTTING DOWN THE APU, THE FLIGHT CREW HAD A SEVERE ELECTRICAL SME	LL IN THE COCKPIT, BUT NO SMOKE APPEARS. THE FLIGHT CREW DECLARED AN EMERGENCY LANDING AT THE SAME AIRPORT.  BACK TO THE	 MAINTENANCE FACILITY,  TECH TROUBLESHOOT THE AIRCRAFT AND FOUND B2XE CIRCUIT BREAKER POPPED ON THE JB-1 PANEL, AFTER IN	VERTIGATION THE APU GCU OVER VOLTAGE CARD FOUND BURNED.  TECHS DID A COMPLETE CIRCUITY CHECK AND REPLACED THE APU GCU IT	SELF.  GROUND RUN WAS SUCCESSFULLY COMPLETED, THE AIRCRAFT RETURN TO SERVICE WITHOUT ANY FURTHER INCIDENT.		2	L	7	2 	4F			RT	A21AE   					 
2005050300171	20050503	00171	EA  	2005	5	3	CA050222009      	2	20050221	G	7414	D6LN3200	MAGNETO         			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE WOULD NOT START.  THE PROBLEM WAS TRACED TO THE MAG. THIS OVERHAULED MAGNETO HAD BEEN IN SERVICE FOR 34 HRS	.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005050300170	20050503	00170	EA  	2005	5	3	CA050222010      	2	20050221	G	8530	LW12427	CYLINDER        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	NR 2	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L2915936A			(CAN) AIRCRAFT WAS IN A CRUISE CONFIGURATION WHEN THE PILOT NOTICED A VIBRATION FROM THE ENGINE.  REDUCED POWER AND CAME	 BACK TO LAND AT THE DEPARTING AIRPORT WITHOUT INCIDENT.  AIRCRAFT WAS BROUGHT INTO THE HANGER AND THE COWLINGS WERE REM	OVED.  IT WAS DISCOVERED THAT THE NR 2 CYLINDER HAD CRACKED FROM THE UPPER SPARK PLUG HOLE TO THE LOWER SPARK PLUG HOLE.	 NEW CYLINDER WAS ORDERED FROM MFG.			1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2005050300169	20050503	00169	NE  	2005	5	3	CA050222011      	2	20050222	G	8540	272225	BOLT            								PWA   	R2800 	R2800*      	52026	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P27467			(CAN) UPON INSPECTION OF THE ENGINE DURING A SCHEDULED B-CHECK, ONE OF THE BOLTS HOLDING THE POWERCASE AND REAR ACCESSOR	Y CASE TOGETHER WAS FOUND MIGRATING OUT OF THE POWERCASE BETWEEN CYLINDER NR4 AND NR5.  ENGINE WAS REMOVED FOR REPAIR BY	 OVERHAUL SHOP.									4	R			5E8				 
2005042500164	20050425	00164	SW  	2005	4	25	CA050223001      	1	20050216	G	2820		FILTER          			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					FUEL SYSTEM	OPEN            	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) ENGINE FLAME OUT ON LANDING, 200 POUNDS ON BOARD.  SENT AME ON SITE CHECK FUEL SYSTEM. IN-LINE FUEL FILTER STUCK O	PEN.  CLEAN ALL FUEL SYSTEMS AND GROUND RUN IAW MM PROCEDURE.  FLEW THE A/C BACK TO THE HANGAR AND CLEANED FUEL SYSTEMS 	AGAIN.  CHECK FOR LOW LEVEL FUEL LIGHT SYSTEMS, FOUND OK.  RESULT OF INVESTIGATION WAS IN LINE FUEL FILTER VERY DIRTY, C	HECK VALVE STUCK OPEN, FUEL MAY HAVE BEEN TRANSFERING AS IT SUPPOSE TO AND A/C RAN OUT OF FUEL.			1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005050300168	20050503	00168	CE  	2005	5	3	CA050223004      	1	20050223	G	1430	MS1782612	NUT             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	WING	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12439								(CAN) DURING CPCP AND SID INSPECTION, THE WING LOWER ATTACH STRUT BOLT AND NUT WERE REMOVED FOR INSPECTION AND THE NUT W	AS FOUND FRACTURED THROUGH. THE COTTER KEY WILL HOLD THE NUT/BOLT IN PLACE. THE FRACTURE WAS LOCATED THRU THE MFG IDENTI	FICATION STAMPS ON THE OUTER SURFACE AND WAS COMPLETELY THROUGH.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005050300167	20050503	00167	SO  	2005	5	3	CA050223005      	1	20050222	G	2121	4878621CH214	SWITCH          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT LDG SAFETY	DEFECTIVE       	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) HEATER GROUND FAN NOT WORKING AFTER LANDING, HEATER SYSTEM CHECK AND FOUND DEFECTIVE WIRE (OPEN) FROM LT LANDING G	ROUND SWITCH.  THE OTHER SYSTEM WASN'T AFFECTED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005090600006	20050906	00006	EA  	2005	9	6	CA050223006      	2	20050211	G	7310	310050401	CONNECTOR       								PWA   	PT6T  	PT6T3       	52045	EA  					FUEL	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								63165			(CAN) DURING ENGINE VISUAL INSPECTION AT MFG, 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 F	OR REVIEW, AFTER WHICH THEY WILL BE DESTROYED.  NOTE: THIS IS THE 4TH OCCURRENCE RECENTLY.								4	U			E22EA				 
2005090600007	20050906	00007	EA  	2005	9	6	CA050223007      	2	20050222	G	7310	310050401	CONNECTOR       								PWA   	PT6T  	PT6T3       	52045	EA  					FUEL	IMPROPER PART   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								TH0554			(CAN) DURING ENGINE VISUAL INSPECTION AT MFG, 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 REVIEW, AFTER WHICH THEY WILL BE DESTROYED. NOTE: THIS IS THE 5TH OCCURENCE RECENTLY.								4	U			E22EA				 
2005050300165	20050503	00165	EA  	2005	5	3	CA050223008      	1	20050210	G	7921	V6007DV5	OIL COOLER      			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT NOTICED DECREASING OIL PRESSURE APPROX 8 MINUTES FROM DESTINATION.  UNEVENTFUL LANDING WAS CARRIED OUT. OIL 	PRESSURE DID NOT DROP BELOW 60 PSI, BUT OIL LEVEL IN TANK WAS BELOW BOTTOM OF DIPSTICK. APPROXIMATELY 3 TO 3.5 GALLONS O	F OIL LOST IN UNDER 10 MINUTES.  UNIT WAS RETURNED TO SUPPLIER FOR INSPECTION AND REPORT.  UNIT WAS EXCHANGED UNDER WARR	ANTY DUE TO ONLY 108.0 HOURS TIS SINCE OVERHAUL.			1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005050300164	20050503	00164	GL  	2005	5	3	CA050223009      	1	20050217	G	2710	182G	SLEEVE          			AMTR  	VANS  	RV8         	       	GL  	ROTAX 	      	ROTAX*      		EU  					CONTROL CABLE	CRIMPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON ASSY OF NEW .0937 INCH STAINLESS STEEL CONTROL CABLES.  IT WAS DISCOVERED THAT THE NICOPRESS SLEEVES WERE NOT	 CRIMPED SUFFICIENTLY. SOME CABLES PULL TESTED ACTUALLY PULLED APART. THE NICOPRESS TOOL WAS CALIBRATED USING THE TOOL G	O/NO-GO GAUGE.  IT APPEARS THE WALL THICKNESS OF THE NICOPRESS IS TOO THIN AND DOES NOT ALLOW ENOUGH MATERIAL TO PROPERL	Y CRIMP.  A COMMERCIAL NICOPRESS SLEEVE HAS A THICKER WALL AND CRIMPS BETTER.			1	L	7	1 	3O	3	I	NT	EXPA1L71	EXPE3I				 
2005050300161	20050503	00161	EA  	2005	5	3	CA050223010      	2	20050210	G	8520	LW16512LW16812	LIFTER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CAMSHAFT	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL208976T			(CAN)  INSPECTION OF OIL SUMP SCREEN FOUND LARGE METALLIC FERROUS PARTICLES. ENG TTSN 1738.0.  IT WAS FOUND THAT LIFTERS	 WERE BADLY SPALLED (CYL NR1, INTAKE SPALLED, CYL NR2 BOTH GOOD, CYL NR3, INT AND EX SPALLED, CYL NR4, INTAKE SPALLED) A	LONG WITH SPALLED AND WORN CAM LOBES.  MFG MSB SPECIFY THAT  EXHAUST VALVE CLEARANCES BE CHECKED, ALONG WITH INSPECTION 	OF EXHAUST LIFTERS, FOR ENGINES AT 1000 HRS.  ENGINE HAS BEEN REMOVED AND SENT OUT FOR REPAIR. NO INDICATION IN ENG PERF	ORMANCE TO INDICATE PROBLEMS. SEB WAS LAST DONE ON OCT3/03 AT 994.3 HRS ENG TIME.  CYL NR4 EXHAUST LIFTER WAS CHANGED OU	T AT THAT TIME.  20W50XC OIL, ALONG WITH LW16702 OIL ADDITIVE IS USED AND CHANGED EVERY 50 HRS. ENGINE-REMANUFACTURED.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005041200020	20050412	00020	EA  	2005	4	12	CA050223011      	2	20050222	G	8520	LW16512LW16812	LIFTER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CAMSHAFT	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL208976T			(CAN) DURING PROGRESSIVE CARE OPERATION NR2 ON INSPECTION OF OIL SUMP SCREEN FOUND LARGE METALLIC FERROUS PARTICLES. ENG	INE ON FURTHER INVESTIGATION, IT WAS FOUND THAT ALL LIFTERS (INTAKE AND EXHAUST) WERE BADLY SPALLED, ALONG WITH SPALLED 	AND WORN CAM LOBES. MFG SPECIFY THAT THE EXHAUST VALVE CLEARANCES BE CHECKED, ALONG WITH AN INSPECTION OF THE EXHAUST LI	FTERS, FOR THE 76T MODEL ENGINES AT 1000 HRS. THERE WAS NO INDICATION IN ENGINE PERFORMANCE TO INDICATE PROBLEMS.  20W50	XC OIL, ALONG WITH LW16702 OIL ADDITIVE IS USED AND CHANGED EVERY 50 HRS. ENGINE-REMANUFACTURED, PURCHASED FROM LYCOMING	. LYCOMING HAS BEEN CONTACTED ON THIS SITUATION.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005050300160	20050503	00160	CE  	2005	5	3	CA050223012      	1	20050220	G	5341	501200742	FITTING         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WING TO BODY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23322								(CAN) DURING AD-81-25 THIS FITTING WAS FOUND CRACKED AND IT WAS REPLACED IAW THE SIRM.						1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005050300158	20050503	00158	EA  	2005	5	3	CA050223013      	1	20050223	G	2497	D1822A	BUSS            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					AC UTILITY	DAMAGED         	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE, EICAS MESSAGES AC BUSS 1 AND AC UTILITY BUSS 1 APPEARED SIMULTANEOUSLY WITH A CHATTERING NOISE WHICH CO	ULD BE IDENTIFIED.  THE AIRCRAFT LANDED AS SCHEDULED.  INSPECTION BY MAINTENANCE REVEALED THAT: C/BS J4 CBP-1 AND 2 (AC 	UTIL CONT) AND C/B A2 CBP-1 WERE POPPED OUT.   THE AC UTILITY BUSS 1 CONTACTOR 1K4XD WAS ALMOST COMPLETELY MELTED.  THE 	PANEL ASSY, THE OTHER 3 RELAYS (K1XC, K2DB, K3DB) AS WELL AS SOME WIRES INCLUDING THE FEEDERS HAVE BEEN DAMAGED BY HEAT.	  ALL DAMGED PART WILL BE REPLACED.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300154	20050503	00154	EU  	2005	5	3	CA050224001      	1	20050218	G	3242	9595601511	BRAKE ASSY      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RT MLG	FROZEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON LANDING AND DECELERATION, THE AIRCRAFT DRIFTED RT OF CENTERLINE DUE TO A FROZEN BRAKE ON THE RT SIDE.  THIS R	ESULTED IN THE TIRE BEING FLATTENED AND THE AIRCRAFT UNABLE TO BE MOVED UNDER ENGINE POWER.  THE AIRCRAFT WAS TOWED CLEA	R AND THE WHEEL AND TIRE ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT.  PRIOR TO TAKE-OFF, THE AIRCRAFT WAS PARKED WITH	 A RT QUARTERING HEADWIND.  ALTHOUGH LITTLE PRECIPITATION WAS FALLING, MODERATE BLOWING SNOW WAS OCCURRING.  IT IS SUSPE	CTED THAT THE UPWIND BRAKE ASSEMBLY BECAME CONTAMINATED, RESULTING IN A FROZEN BRAKE AND FLAT TIRE DURING THE SUBSEQUENT	 LANDING.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005050300153	20050503	00153	NM  	2005	5	3	CA050224003      	1	20050224	G	3260	S258	SENSOR          			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LT MLG	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) ON TOUCHDOWN, MASTER WARNING CONFIG LIGHT GEAR NOT DOWN CAUTION, LT SIDE BRACE LIGHT AND LT GEAR GREEN LIGHT EXTIN	GUISHED.  AIRCRAFT STOPPED, GEAR PINS INSTALLED AND TAXIED IN.  FOUND TOP OF SENSOR S258 SHEARED OFF. REPLACED SENSOR. S	258 AND S236 ADJUSTED IAW MM 32-61-02. CHECKS OK.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005050300152	20050503	00152	CE  	2005	5	3	CA050224005      	1	20050215	G	2710	08615201	CLAMP           			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	AUTOPILOT	OBSTRUCTED      	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN THE AILERON CONTROL WAS MOVED TO THE EXTREME LT, THE CONTROL WOULD OCCASIONALLY CATCH MOMENTARILY AND THEN RE	LEASE. UPON FURTHER EXAMINATION OF THE AILERON CONTROL SYSTEM, THE AUTOPILOT CLAMP ON THE LT AILERON CABLE WAS FOUND TO 	BE CATCHING ON THE DE-ICE BOOT LINE TO THE TAIL, WHEN THE CONTROL WAS MOVED FULL LT.  THE DE-ICE LINE WAS REPOSITIONED A	ND SECURED TO THE BELLY PANEL TO ALLOW MORE CLEARANCE WITH THE AILERON CABLE AND NO FURTHER PROBLEMS HAVE OCCURRED.			1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
2005050300149	20050503	00149	CE  	2005	5	3	CA050224006      	1	20050222	G	5514	4555301480003	TORQUE LINK     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HORIZONTAL STAB	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPLIANCE OF SB 45-27-13, REPLACEMENT OF HORIZONTAL STAB. UPPER AND LOWER TORQUE LINK ASSYS, THE LOWER TOR	QUE LINK WAS FOUND INSTALLED UPSIDE DOWN AND WAS MAKING CONTACT WITH THE UPPER TORQUE LINK WHEN HORIZONTAL STAB. TRAVELS	 TO FULL DOWN POSITION 10.4 DEG.  (AIRCRAFT NOSE UP).  NEW TORQUE LINKS WERE INSTALLED AND FOUND THEY MAKE NO DIFFERENCE	 IN TRAVELS.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005042500165	20050425	00165	EA  	2005	4	25	CA050224007      	1	20050224	G	2740	C6TPM10215	HINGE BRACKET   	DHAV        		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			30444			244					(CAN) CORROSION FOUND UNDER BLOCK.  WHILE INSPECTING CENTER HINGE BRACKET IAW SB 6/512.  CORROSION VISIBLE ON SURFACE SU	RROUNDING BLOCK.  BLOCKS REMOVED FOR FURTHER INSPECTION AND EXFOLIATION/CORROSION FOUND UNDER BOTH SIDES.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005050300148	20050503	00148	NE  	2005	5	3	CA050224008      	2	20050224	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						SHUTDOWN        	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								DD0012			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN IN CRUISE.  SUBSEQUENT RELIGHT ATTEMPTS WERE UNSUCCESSFUL.  THE CRE	W DECLARED AN EMERGENCY AND THE FLIGHT DIVERTED.  MFG WILL INVESTIGATE THE EVENT AND SUPPLEMENT THIS REPORT TO REFLECT R	OOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005050300146	20050503	00146	NE  	2005	5	3	CA050224009      	2	20050218	G	7200		ENGINE          								PWA   	PT6   	PT6A34AG    	52053	NE  						POWER LOSS      	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CA								56561			(CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER SHORTLY AFTER DEPARTING THE RUNWAY.  THE AIRCRAFT SUBSEQUENTLY IMPACTED	 THE GROUND.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL SUPPLEMENT THIS REPORT TO REFLECT ROOT CAUSE, ONCE	 DETERMINED.									4	T			E4EA				 
2005050300145	20050503	00145	NE  	2005	5	3	CA050224010      	2	20050219	G	7200	PW530A	ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA								DA0423			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN IN DESCENT.  MFG WILL INVESTIGATE THE INCIDENT AND WILL SUPPLEMENT 	THIS REPORT TO REFLECT ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005050300144	20050503	00144	NE  	2005	5	3	CA050224011      	2	20050216	G	7200		ENGINE          			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  		MALFUNCTIONED   	W				K				NONE                    				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		IN	INSP/MAINT     	1			CA								92630			(CAN) THE ENGINE WAS SHUTDOWN IN FLIGHT DUE TO DECREASING ENGINE OIL PRESSURE ACCOMPANIED BY OIL ODOR IN CABIN AND INCRE	ASING OIL AND TURBINE TEMPERATURES.  MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL SUPPLEMENT THIS REPORT TO 	PROVIDE ROOT CAUSE ONCE ESTALISHED.				1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2005041200019	20050412	00019	NE  	2005	4	12	CA050224012      	2	20050217	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						FAILED          	W				C				ABORTED TAKEOFF         				M	J		OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			CA								127102			(CAN) ON TAKEOFF ROLL THE AIRCRAFT EXPERIENCED A YAW ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN ENGINE TORQUE AND TUBINE	 OVER TEMPERATURE AND LOW OIL PRESSURE WARNING ANNUNCIATIONS.  TAKEOFF WAS ABORTED.  MFG WILL INVESTIGATE THE INCIDENT A	ND WILL SUPPLIMENT THIS REPORT TO REFLECT ROOT CAUSE AS AND WHEN ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2005050300143	20050503	00143		2005	5	3	CA050224013      	4	20050224	G	3420	066031252500	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EHSI	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT'S EHSI WENT INTERMITENTTLY FUZZY.  INFORMATION STILL READABLE. DISPLAY UNIT REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005050300142	20050503	00142	EU  	2005	5	3	CA050225001      	1	20050221	G	7500	EU15969	GASKET          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					BLEED DUCT LINE	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW OBSERVED NR1 ANTI-ICE INDICATION FOLLOWED BY A BLEED DUCT FAULT.  THE AIRCRAFT MADE AN UNSC	HEDULED LANDING WITHOUT INCIDENT.  THE ORIGINAL SNAG WAS CLEARED WITH NO FAULT FOUND.  THE AIRCRAFT WAS RELEASED FOR SER	VICE WITH THE SNAG RETURNING.  THE SITUATION RETURNED TWICE BEFORE THE AIRCRAFT WAS GROUNDED FOR EXTENSIVE TROUBLESHOOTI	NG.  FURTHER INVESTIGATION FOUND THE 3 INCH METAL GASKET ON THE BLEED LINE HAD BROKEN IN 2 PIECES.  THE AIRCRAFT IS AOG 	FOR PARTS AND WILL ARRIVE 25 FEBRUARY, 2005.		2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005050300141	20050503	00141	GL  	2005	5	3	CA050225002      	2	20050221	G	7250	6870832G	COUPLING        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE802228BA			(CAN) PITTING ON CIRCUMFERENCE OF COUPLING.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005050300140	20050503	00140	CE  	2005	5	3	CA050225003      	1	20050221	G	5514	07321014	REINFORCEMENT   	CESSNA      		CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	STAB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1851087					(CAN) BOTH STABILIZER HINGE REINFORCEMENT FOUND CRACKED WHILE PERFORMING ANNUAL INSPECTION. REPLACEMENT PARTS ORDERED FR	OM MFG. THIS IS NOT UNCOMMON TO FIND CRACKS IN THIS AREA.  PROBABLE GROUND HANDLING LOADS OR MISFIT ON INSTALLATION.  NO	TE THAT STABILIZER HAS BEEN REBUILT IN 1996 AFTER AIRCRAFT GROUND LOOP.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2005050300139	20050503	00139		2005	5	3	CA050225004      	4	20050223	G	3425	6226190204	AHRS            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					NR 2	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) AHRS NR 2 FAILED ON TAKEOFF, CAUSING THE AUTOPILOT AND YAW DAMPENER TO FAIL.   AHRS WAS RECENTLY OVERHAULED.  ATTI	TUDE AND HEADING REFERENCE SYSTEM (AHRS).					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005050300136	20050503	00136	GL  	2005	5	3	CA050225005      	1	20050204	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											(CAN) DURING ROUTINE 100 HR INSPECTION THE SPLINE SEAL ON THE FLAP ACTUATOR WAS FOUND TO BE LOOSE. REPLACED FLAP ACTUATO	R ASSY WITH NEW UNIT. SEAL HAD BEEN GLUED 105.7 HRS EARLIER. FLAP UNIT WAS REPLACED ONCE BEFORE, MARCH 1/04.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2005050300133	20050503	00133	NM  	2005	5	3	CA050225006      	1	20050224	G	5532	220000033	DOUBLER         			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE ACCOMPLISHING AD 80-19-14 STABILIZER FITTING INSPECTION, 2 CRACKS WERE NOTICED ON THE BOTTOM RIB P/N 220000-	033 OF THE VERTICAL FIN. CRACKS ARE LOCATED INTHE REAR 90 DEGREE BEND OF THE RIB, RADIATING INWARDS FROM THE RADIUS CUT 	OUT.  CRACKS WERE BOTH ABOUT 1 INCH LONG.  VERTICAL FIN REMOVED TO FACILITATE RIB P/N 220000-033 REPLACEMENT. ONCE FIN W	AS REMOVED, ANOTHER RIB WAS FOUND CRACKED.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2005052300130	20050523	00130	NM  	2005	5	23	CA050225007      	1	20050224	G	5531	220000021	RIB             			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL RIB WAS REMOVED FOR RIB REPLACEMENT.  ONCE FIN WAS REMOVED, FORWARD RIB WAS FOUND TO HAVE 2 CRACKS IN THE	 REAR 90 DEGREE BEND. CRACKS ORIGINATE FROM LT AND RT RADIUS CUTS AND GO ALONG THE BEND RADIUS. LT CRACK IS A HALF AN IN	CH LONG AND THE RT CRACK IS A HALF AN INCH LONG, STOP DRILLED AND ANOTHER ONE .1250 INCH PAST THE STOP DRILL HOLE. AS TH	IS WAS DONE BEFORE WE BOUGHT THE AIRCRAFT, WHO AND WHEN THIS STOP DRILLING WAS DONE IS UNKNOWN. PART IS BEING REPLACED.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2005050300131	20050503	00131		2005	5	3	CA050226001      	4	20050216	G	8300	6014T81G27	GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR 2 ENGINE SELF SHUTDOWN AT 11,000 FEET. DECLARED AN EMERGENCY AND LANDED WITH ONE ENGINE.  NO OTHER PROBLEMS NOT	ED.  MAINTENANCE FOUND THE GEARBOX TO BE AT FAULT.  REPLACED THE GEARBOX AND RETURNED THE AIRCRAFT TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300128	20050503	00128	SO  	2005	5	3	CA050227001      	1	20050227	G	5521	437430001	RIB             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE AME FOUND THE TIP RIB ON THE RT ELEVATOR CRACKED. THE CRACK WAS LOCATED IN THE BEND 	WHERE THE RIB TRANSITIONS INTO THE FLANGE AT RIVET NR7 FROM THE TRAILING EDGE.  UPON REMOVAL IT WAS DISCOVERED THAT THES	AME CRACK COULD BE FOUND ON TOP AND BOTTOM SIDES OF THE RIB.   IN ADDITION THE FLANGE WAS CRACKED AT 90 DEGREES TO THE B	END, CREATING A CRACK IN THE SHAPE OF THE LETTER.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005050300126	20050503	00126	EA  	2005	5	3	CA050228001      	2	20050225	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2	FLUCTUATES      	W				E	B			ENGINE SHUTDOWN         	EMER. DESCENT           			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0151			(CAN) IN-FLIGHT SHUTDOWN OF NR 2 ENGINE DUE TO OIL PRESSURE FLUCTUATION. AIRCRAFT WAS ENROUTE WHEN THE EVENT OCCURRED, A	T WHICH AN EMERGENCY WAS DECLARED AND THE AIRCRAFT HAD TO COMPLETE AN UNSCHEDULED LANDING.  AFTER LANDING INSPECTION, AI	R CREW REPORTED AN EXCESSIVE AMOUNT OF OIL AROUND LOWER AFT NACELLE AREA, INDICATING A POSSIBLE OIL LEAK AROUND THE OIL 	COOLER AREA. BORESCOPE INSPECTION SHOWED DAMAGED HP IMPELLER . ENGINE MUST BE REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005050300124	20050503	00124	NE  	2005	5	3	CA050228003      	2	20050226	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 1	FOD             	W				C				ABORTED TAKEOFF         				C	J		F.O.D.                    	WARNING INDICATION        		TO	TAKEOFF        	1			CA								P728014			(CAN) DURING TAKE-OFF, NR 1 ENGINE STALL SURGE AND 2 AUDIBLE STALLS HEARD.  N1 REACHED 107 PERCENT FOR 3 TO 4 SECONDS.  	REJECTED TAKE-OFF INITIATED WITHOUT INCIDENT AND AIRCRAFT RETURNED TO THE GATE.  SUSPECT FOD DUE TO ICE.  ENGINE CHANGE 	IN PROCESS.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005041200018	20050412	00018	WP  	2005	4	12	CA050228004      	1	20050226	G	3241	406256	TRANSDUCER      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					WHEEL SPEED	INOPERATIVE     	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF, WHEEL NOT TURNING LIGHT ILLUMINATED AT 80 KNOTS.  REJECTED TAKE-OFF CARRIED OUT WITHOUT INCIDENT.	  WHEEL NOT TURNING LIGHT EXTINGUISHED.  SUSPECTED DE-ICING FLUID AND WET RUNWAY WAS THE CAUSE.  CREW REQUESTED SECOND T	AKE-OFF ATTEMPTED.  UNABLE TO TAKE-OFF DUE TO SAME SNAG.  REJECTED TAKE-OFF CARRIED OUT SERVICEABLE.  MAINTENANCE REPLAC	ED THE WHEEL SPEED TRANSDUCER IAW MM 32-40-00 AND CHECKED SERVICEABLE.  NO FURTHER FAULT DURING SUBSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005042500166	20050425	00166	EA  	2005	4	25	CA050228005      	1	20050218	G	3246	58S923	STRUT           	EDOXXXXXXXXX		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	RT FLOAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION AND FLOAT REMOVAL, THE FWD RT FLOAT STRUT WAS FOUND TO HAVE LEVEL 2-3 CORROSION ON THE IN	SIDE OF THE STRUT.  DUE TO THE FACT THAT ALL OTHER STRUTS WERE IN EXCELLENT CONDITION LEADS US TO BELIEVE THAT THIS STRU	T WAS INSTALLED WITHOUT ANY CORROSION PROOFING BEING APPLIED.  TIME IN SERVICE 1352.8 HRS.  AIRCRAFT OPERATED IN A CORRO	SIVE ENVIRONMENT.			1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005050300123	20050503	00123	CE  	2005	5	3	CA050228006      	1	20050224	G	3230	571302	MOTOR           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) DURING LANDING THE CREW ATTEMPTED TO EXTEND THE GEAR BUT THE GEAR WOULD NOT RESPOND.  MANUAL EXTENSION OF THE GEAR	 WAS COMPLETED.  MAINTENANCE FOUND THE HYD PACK MOTOR SHORTED AND INOPERATIVE. THE MOTOR WAS REPLACED AND THE AIRCRAFT R	ELEASED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005050300122	20050503	00122	CE  	2005	5	3	CA050228007      	1	20050227	G	3297	MS24171D1	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	BURNED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) DURING APPROACH, CREW ATTEMPTED TO EXTEND THE GEAR BUT REQUIRED MANUAL EXTENSION.  MAINTENANCE FOUND THE LANDING G	EAR MOTOR RELAY TO BE BURNED IN THE CONTACT AREA.   THE RELAY WAS REPLACED AND THE AIRCRAFT RELEASED. THIS OPERATOR HAS 	HARD TIMED THE RELAYS TO 3000 HOURS.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005050300121	20050503	00121	CE  	2005	5	3	CA050228008      	1	20050228	G	2730		CONTROL CABLE   			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	ELEVATOR TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  (.0625) ELEVATOR TRIM CABLE WAS FOUND WITH WIRES BROKEN IN A CRITICAL FATIGUE AREA,  (.2500) LENGTH FROM AFT END,	 THROUGH THE IDLER PULLY AND CAPSTAN OF BENDIX FCS 810 AUTOPILOT TRIM SERVO.   SEC 7 PART B: FOUND DURING AUTOPILOT REPL	ACEMENT. SEC 7 PART C: REPLACED CABLE DURING AUTOPILOT REPLACEMENT.  DEFECTIVE PART AVAILABLE UPON REQUEST.  REFERENCE A	C43.13-1B R1 CHAPTER 7, PARAGRAPH 7-149END.			1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
2005050300119	20050503	00119	EA  	2005	5	3	CA050228009      	2	20050228	G	8520	11F20022D3	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L165968A			(CAN) SUSPECT CRACK IN THE VICINITY OF CYLINDER NR 2.  ENGINE REMOVED FOR FURTHER INSPECTION.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005050300114	20050503	00114	EA  	2005	5	3	CA050228013      	2	20050224	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						UNKNOWN         	W				R				AUTOROTATION            				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA											(CAN) A/F 18258 HOURS. HELI SKIING OPERATION.  PILOT WAS DESCENDING DOWN A HILL AND SETTING UP HIS APPROACH TO LAND HELI	COPTER. THE PILOT PULLED IN POWER TO CONTROL HIS DESCENT RATE AND NOTICED THAT THE ENGINES REMAINED IN FLIGHT IDLE. HE C	HECKED HIS THROTTLE GRIPS AND FOUND THAT BOTH THROTTLES WERE ON MAX STOP. HE SET UP HIS AUTOROTATION AND LANDED HARD IN 	POWDER SNOW. HELICOPTER DAMAGED. NTSB HAS BEEN NOTIFIED OF THIS INCIDENT AND WILL BE INVESTIGATING IN THE NEAR FUTURE. T	HE PILOT WAS THE ONLY ONE ON BOARD.		1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005050300099	20050503	00099	EU  	2005	5	3	CA050301001      	1	20050225	G	3150	20662155	TUBE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					DISPLAY UNIT	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			39220	15281		2213					(CAN) DURING PRE-DEPARTURE CHECK, ON THE GROUND, BURN SMELL WAS NOTICED FROM RT ECAM SYSTEM.  DISPLAY UNIT WAS REMOVED A	ND INSPECTED. NO FAULT WAS FOUND AND SYSTEM WAS DEACTIVATED UNDER MEL.  UNIT WAS REPLACED AT THE NEXT STATION. UNIT WAS 	SENT TO THE OEM FOR INVESTIGATION.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2005050300097	20050503	00097	GL  	2005	5	3	CA050301002      	1	20050301	G	8011	852401	SPRAG CLUTCH    			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	CRANKSHAFT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3300					(CAN) ENG WAS FOUND TO HAVE SEVERAL OIL LEAKS AND HARD STARTING.  DURING INSP IT WAS NOTED THAT CRANKCASE SEALANT WAS NO	T IAW MFG REC.  SEALANT HAD  RUBBERY/SILICONE COMPOSITION AS OPPOSED TO APPEARANCE OF CORRECT SEALANT. DURING COLD START	S, STARTING SPRAG CLUTCH WOULD SLIP. DURING TEARDOWN INSP, DISCOVERED THAT SPRAG CLUTCH HSG WAS ASSEMBLED USING INCORREC	T RETAINING COMPOUND, ALLOWING HSG TO SLIPON CRANKSHAFT.  SPRAG CLUTCH HSG WAS GALLED AND UNSERVICABLE, CRANKSHAFT SUSTA	INED NO DAMAGE.  INCORRECT CRANKCASE SEALANT ALLOWED MOVEMENT BETWEEN CRANKCASE HALVES CAUSING FRET DAMAGE, CASE DAMAGE.	 NOTE:  INCORRECT SEALING COMPOUND AND THREAD LOCKING COMPOUND WAS FOUND TO HAVE BEEN USED THROUGHOUT ENGINE.	1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2005050300094	20050503	00094	EU  	2005	5	3	CA050301003      	1	20050223	G	2730	298G3096	LEVER           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PREFLIGHT INSPECTION, NOTICED DEFORMITY ON LEVER ASSY. PART REPLACED WITH SERVICEABLE UNIT.						2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005041200016	20050412	00016	NE  	2005	4	12	CA050301004      	2	20050221	G	7230	01R3028332	GAS GENERATOR   			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCEPJ0109			(CAN) DURING ENGINE INSPECTION USING A VIDEO BORESCOPE, THE HIGH PRESSURE BLEED VALVE TUBE FROM P3 WAS FOUND CRACKED OFF	 AND A HORIZONTAL CRACK APPROXIMATELY 3 INCHES LONG BELOW BLEED VALVE ATTACH FLANGE WAS NOTED. SOME STAINING INDICATED C	RACK WAS PROBABLY NOT RECENT AND THIS AREA IS NOT READILY VISIBLE WITH THE BLEED VALVE SHROUDS INSTALLED. ALL ENGINE PER	FORMANCE RUNS AND TREND MONITORING DATA WERE WITHIN ALLOWABLE PARAMETERS. GAS GENERATOR WAS REMOVED AND SHIPPED FOR REPA	IR.		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2005050300092	20050503	00092	CE  	2005	5	3	CA050301005      	1	20050224	G	2133	781904	OUTFLOW VALVE   			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  		FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OVERHAULED VALVE PURCHASED JANUARY 23, 2001, GATE VALVE WAS FOUND STUCK IN THE CLOSED POSITION. THE VALVE WOULD NO	T OPEN WHEN THE PRESSURE SELECTOR WAS SWITCHED TO THE OPEN POSITION.					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	5	C	P60GL	 
2005050300091	20050503	00091	EA  	2005	5	3	CA050301006      	1	20050301	G	4920		APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, AIRCRAFT FILLED WITH SMOKE FROM APU OIL.  AIRCRAFT AT THE BASE, FLIGHT DATA RECORDER PULLED SENT TO 	PLAYBACK CENTER FOR READ OUT.   APU COMPT.  INSPECTED NO FAULT FOUND SO FAR EXCEPT GLYCOL.  MORE INFO WILL FOLLOW AS BEC	OMES (AVAILABLE).				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300089	20050503	00089	EU  	2005	5	3	CA050301007      	1	20050225	G	2150		A/C PACK        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 2	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WHILE AT CRUISE, THE CABIN CREW INFORMED THE FLIGHT DECK THERE WAS SMOKE IN THE CABIN.  THE AIRCRAFT MADE AN UNSCH	EDULED LANDING RETURNING TO BASE AND LANDED WITHOUT INCIDENT.  NR 2 PACK WAS TURNED OFF AND SMOKE DISSIPATED.  MAINTENAN	CE OPERATED THE NR 2 PACK WITH NO FAULT FOUND.  MEL 21-51-10 RAISED AND DMI 13736 ISSUED.  AIRCRAFT WAS RELEASED WITH NO	 FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005050300088	20050503	00088	CE  	2005	5	3	CA050301008      	1	20050221	G	5210		BRACKET         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOWER DOOR POST SUPPORT BRACKETS CRACKED BOTH SIDES.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005050300087	20050503	00087	NM  	2005	5	3	CA050301009      	1	20050227	G	7920	MS124776	HOUSING         	PWA         	726042      	BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					OIL FILTER	LOOSE           	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA			58552			72605271					(CAN)  CREW REPORTED, NR 1 ENG OIL PRESSURE WAS BELOW RED AND INDICATION WAS READING ZERO.  ENG WAS SHUTDOWN, AC LANDED 	W/O INCIDENT.  MAINT FOUND NR 1 ENG OIL FILTER CAP WAS DISLODGED DUE TO LWR STUDS OF GB HSG HELICOILS FAILING. ENGINEERI	NG ISSUED A PROD PERMIT B737-72-18790 TO REINSTALL HELICOIL WITH REPEAT INSP OF 50 HOURS.  HISTORY REVIEWED THAT 2 DAYS 	PRIOR, THIS OCCURRENCE WAS A REPORT OF AN OIL LEAK FROM NR 1 ENG WHICH WAS NOT EVIDENT DURING ENG RUN AND WAS RELEASED A	S GROUND CHECKED SERVICEABLE. AS IT APPEARS THAT OVER TIGHTENING OF THE OIL FILTER CAP NUTS MAY CONTRIBUTE TO PROBLEM, R	EMINDER ISSUED TO LINE ENGINEERS THAT TORQUE ON THESE FASTENERS IN 25-30 INCH POUNDS AS STATED IN WORK CARD 1193.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005050300085	20050503	00085	EA  	2005	5	3	CA050301010      	2	20050301	G	7300		LINE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NR 2 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE HARD TO START. REMOVED COWLS AND FOUND PRIMER LINE BROKEN, NR 2 CYLINDER, DUE TO FATIGUE. INSPECTED ALL LIN	ES AND FITTINGS. DETERMINED THAT THEY WERE ALL NEARING FATIGUE LEVELS. ALL WERE REMOVED AND REPLACED BY A COMPLETE SET O	F LINES, FITTINGS AND CLAMPS IAW PARTS MANUAL.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005050300083	20050503	00083	EU  	2005	5	3	CA050301011      	1	20050228	G	5210	350A25127520	PIN             			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					SLIDING DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REMOVED SLIDING DOOR PINS FROM A AS 350 TO CONDUCT AN DYE PENETRANT INSPECTION IAW ALERT TELEX 05.00.47. THE INSPE	CTION WAS CONDUCTED.  DURING THE DYE CHECK A SMALL INDICATION WAS REVEALED BUT WAS NOT VERY APPARENT AND EASILY DISTINQU	ISHED. THE NDT INSPECTOR CONDUCTED A FLOURESCENT MAGNETIC PARTICLE EXAMINATION. THIS REVEALED .0312 REJECTABLE INDICATIO	N ON BOTH SIDES OF THE SPRING ATTACH HOLE B.  IT WAS RECOMMENDED FROM THE NDT INSPECTOR TO NOTIFY MFG AND TRANSPORT TO R	EVISE THE NDT EXAMINATION TO EITHER A FLOURESCENT MAGNETIC PARTICLE OR SPECIFY THAT A METHOD (FLOURESCENT) LEVEL 4 DYE B	E UTILIZED.  ARE NOW REPLACING ALL PINS WITH NEW AND CONDUCTING A MAGNETIC PARTICLE INSPECTION ON USED PINS.	1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005050300082	20050503	00082	EU  	2005	5	3	CA050302001      	1	20050301	G	5610	D205443205	WINDSHIELD      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING ENROUTE, THE CAPTAIN OBSERVED HIS SIDE WINDSHIELD ASSY WAS CRACKED.  THE AIRCRAFT WAS DIVERTED AND LANDED W	ITHOUT INCIDENT.  THE CAPT'S SIDE WINDSHIELD ASSY WAS REPLACED IAW MM 56-11-00.  NO FURTHER INCIDENT DURING SUBSEQUENT F	LIGHT.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2005050300081	20050503	00081	CE  	2005	5	3	CA050302002      	1	20050227	G	3040	10138402521	HEATER          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WINDSHIELD	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ELECT SMELL/SMOKE WAS CAUSED BY FAILED GROUND POINT FOR WINDSHIELD HEAT ON LT WINDSHIELD.  CREW FOLLOWED EMERG CKL	IST, WHICH CALLS FOR TURNING OFF ELEC PWR. THIS AC HAS HYDR LANDING GEAR RETRACT SYS INSTALLED (STC), ELECTRICALLY DRIVE	N HYDR PUMP PROVIDES PRESS TO MAINTAIN HYDR PRESS IN RETRACTION SYS. THIS PUMP WILL NORMALLY CYCLE ONCE EVERY MINUTE. HY	DR PRESS DECAYED WHILE ELEC PWR WAS OFF, L.G. STARTED TO DROPOUT OF WHEEL WELLS.  WHEN ELEC PWR WAS TURNED BACK ON, HIGH	 LOAD REQUIRED TO RETRACT GEAR DUE TO HIGHER THAN NORMAL AIRSPEED CAUSED PUMP CB TO TRIP.  ALTERNATE EXT SYS HAD TO BE U	SED TO EXTEND GEAR.  GEAR EXTENSION SYS HAS BEEN FUNCTION CHECKED AND BLED STC MAINT, FOUND W/O FAULT.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005050300079	20050503	00079	CE  	2005	5	3	CA050302003      	1	20050218	G	5551	12120031	DOUBLER         			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BULKHEAD DOUBLER REINFORCES THE HOLE WHERE THE HORIZONTAL STAB ATTACHES.  DOULBER SPLIT IN TWO THROUGH ANCHOR 	NUT RIVIT HOLE.  RESULTED IN BULKHEAD STA 209.0 P/N 1212402-2 CRACKING. THIS DOUBLER IS FOUND ON EARLY MODEL.  LATER MOD	ELS HAVE TWO DOUBLERS, ONE IN FRONT AND ONE IN BACK.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2005041200015	20050412	00015	CE  	2005	4	12	CA050302004      	1	20050321	G	5551	12120031	DOUBLER         	CESSNA      	12124026    	CESSNA	210   	T210K       	2073447	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BULKHEAD DOUBLER REINFORCES THE HOLE WHERE THE HORIZONTAL STAB ATTCHES.  DOUBLER SPLIT IN TWO THROUGH THE ANCH	OR NUT RIVIT HOLE. THIS DOUBLER IS ONLY FOUND ON EARLY MODELS.					1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P21EA	 
2005050300078	20050503	00078	EA  	2005	5	3	CA050303001      	1	20050228	G	2121	GG670950283	FAN             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					GALLEY	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, CREW REPORTED SMOKE IN THE COCKPIT. DECLARED EMERGENCY AND RETURNED SAFELY TO FIELD.  NO FURTHER IN	CIDENTS REPORTED. ALSO, SMOKE AFT LAV MASTER WARNING ILLUMINATED.  INSPECTED AIRCRAFT AND FOUND ELECTRICAL SMOKE SMELL O	RIGINATING FROM GALLEY/FWD LAV EXHAUST FAN.   RAI GALLEY HEATER/LAV EHAUST FAN IAW CRJ- 700 AMM 21-23-93.  OPS GOOD. GRO	UND RUN AIRCRAFT, NO DEFECTS NOTED.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005050300077	20050503	00077	EA  	2005	5	3	CA050303002      	1	20050228	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGH FL340, THE CAPT DV WINDOW SHATTERED.  DIVERTED. REMOVED AND REPLACED WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005050300075	20050503	00075	EU  	2005	5	3	CA050303004      	1	20050105	G	2750		CONTROL SYSTEM  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF PILOT SELECTED FLAPS TO ZERO DEGREE. FLAPS DID NOT RESPOND AND FLAP WARNING ON CAWS ILLUMINA	TED.  PILOT TRIED RESET BUT NO RESPONSE.  PILOT RETURNED TO AIRPORT WITH 15 DEGREES FLAP.  MAINTENANCE RESET FLAP COMPUT	ER AND LUBRICATED FLAP ACTUATORS.  FUNCTION CHECK CARRIED OUT AND FOUND SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. UNABL	E TO DETERMINE CAUSE OF FAILURE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005061700014	20050617	00014	CE  	2005	6	17	CA050303005      	1	20050125	G	3240	20701700	HOSE            	PARKERHANFIN		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					BRAKE ASSY	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											ON APPROACH,  PILOT APPLIED BRAKE AND HAD NONE.  TRIED REVERSE, BUT DUE TO TAIL WIND WAS INEFFECTIVE.  TRIED TO AVOID FU	EL BOWSER BUT WAS UNABLE AND RAN INTO LADDER AND PUMP OFF  FUEL BOWSER AS HE PUT PROPS IN FEATHER.  AIRCRAFT RT PROP SEV	ERELY DAMAGED, RT ENGINE POWER SECTION DAMAGED,  NOSE GEAR DAMAGED.  CAUSE OF LOSS OF BRAKE WAS HOSE TO THE LT INBOARD B	RAKE UNIT LEAKING.  AFTER CHECKING WITH SEVERAL OPERATORS OF SAME TYPE, HOSE LEAKING IS COMMON PROBLEM.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2008013100012	20080131	00012		2008	1	31	CA050303006      	4	20050301	G	2213	5226703002	COMPUTER        			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					FLIGHT COMPUTER	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA		CGIRE									(CAN) ON OCTOBER 15, 2004 A FLIGHT COMPUTER (FC) WAS REPLACED ON AIRCRAFT.  THE REMOVED FC WAS THEN SENT FOR REPAIR. IT 	WAS DETERMINED THAT THE FC PN WAS NOT RECOGNIZED. IT WAS THEN SENT TO THE MFG FOR FURTHER INVESTIGATION. MFG CONFIRMED T	HAT THE INSTALLED ID PLATE WAS NOT THEIR OWN. THE PART WAS THEREFORE CLASSIFIED AS UNAPPROVED. ONCE NOTIFIED OF THE DISC	REPANCY, SKYSERVICE PROCEEDED IN A TECHNICAL RECORD REVIEW TO DETERMINE THE ORIGIN OF THE SUBJECT PART. THE AIRCRAFT COM	PONENT REPLACEMENT HISTORY HAS BEEN REVIEWED (STARTING BEGINNING OF 2000). NO FC REPLACEMENT HAS BEEN FOUND. (TC NR 2005	0303006)	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005050300074	20050503	00074	EA  	2005	5	3	CA050303007      	1	20050303	G	7500		DUCT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT ENG 14TH STAG	LOOSE           	W				B				EMER. DESCENT           				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, RT DUCT 14TH AND AURAL.  MESSAGE REMAIN ON EVEN AT IDLE.  AFTER 14TH STAGE CLOSED MESSAGE DISAPEARE	D.  NEW CLAMP INSTALLED ON RT 14TH STAGE DUCT, JUST DOWNSTREAM OF S/OFF VLV IAW AMM SUBT 36-12-01-420-001.  RUN APU AND 	ENGINES TO CONFIRM NO LEAK AND OPERATION SERVICABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300073	20050503	00073	EU  	2005	5	3	CA050303008      	1	20050303	G	2913	623977	PUMP            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			CA			28654								(CAN) FAULT: TOTAL LOSS OF ALL GREEN HYD FLUID.  LOST MOST OF THE FLUID ON DEPARTURE AND THE REST ON LANDING.  NR1 EDP R	EPLACED IAW AMM 29-11-51.  ENG RUN FUNCTIONAL CHECK CARRIED OUT SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005051200001	20050512	00001	EA  	2005	5	12	CA050303009      	1	20050303	G	3251		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG STEERING	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) JUST AFTER TOUCHDOWN AT 80 KNOTS NOSE WHEEL STEERING FAILED DRAMATIC YAW TO LT CONTROLLED WITH AERODYNMIC RUDDER A	ND DIFF BRAKES RESET ON TAXIWAY REFAILED ON TAXI IN DURING LT TURN. REPLACED LT RVDT AND NWS HARNESS.  RT RVDT RE-RIGGED	.  OPS CHK SERV.  A/C TAXI CHECK CARRIED OUT, NO FAULTS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300071	20050503	00071	NM  	2005	5	3	CA050303010      	1	20050302	G	3260	841101	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER COMPLETION OF A NORMAL TAKEOFF THE WT ON WHEELS CAUTION LIGHT ILLUMINATED. THE AIRCRAFT LEVELED OUT AND THE 	DECISION WAS MADE TO RETURN BACK TO BASE. THE A/C LANDED SUCCESSFULLY WITH NO FURTHER INCIDENT.  IT WAS NOTED THE THE WT	 ON WHEELS CAUTION LIGHT EXTINGUISHED AT THE MOMENT THE NOSE WHEEL CONTACTED THE GROUND.  IT WAS FOUND THAT THE NOSE GEA	R WOW PROXIMITY SENSORS WERE PHYSICALLY DAMAGED AND THE LT SENSOR WAS CAUSING THE CAUTION LIGHT. THE PROX SENSORS WERE R	EPLACED AND THE A/C WAS RETURNED TO SERVICE. THESE ARE THE OLD STYLE PROXIMITY SENSORS WHICH ARE MADE OF PLASTIC. THE NE	W STYLE PROXIMITY SENSOR ( P/N 8-642-02) ARE MADE OF STEEL.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005050300070	20050503	00070	EA  	2005	5	3	CA050303011      	1	20050303	G	2731	C2T47A	ROD             			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	LT ELEV TRIM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, PILOT EXPERIENCED A SLIGHT THUMP THROUGH ELEVATOR CONTROL SYSTEM, AND A MINOR VIBRATION WHICH STOPPE	D WHEN LEVEL FLIGHT WAS ACHIEVED.  THE FLIGHT WAS CONTINUED TO DESTINATION WHERE MAINTENANCE WAS AVAILABLE.  THE PILOT N	OTED THAT MORE ELEVATOR TRIM WAS NEEDED TO ACHIEVE LEVEL FLIGHT.  AFTER AN UNEVENTFUL LANDING, MAINTENANCE INVESTIGATION	 REVEALED THAT THE LT ELEVATOR TRIM ROD HAD FAILED AT THE AFT END IN THE STEEL THREADED SECTION.  CLOSE EXAMINATION OF T	HE BREAK REVEALED THAT THE ROD HAD BEEN BENT AND COLD STRAIGHTENED AT SOME POINT, INITIATING A CRACK. THE ROD WAS REPLAC	ED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE AIRCRAFT IS OPERATING IN A CORROSIVE ENVIRONMENT.	1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005050300069	20050503	00069	EU  	2005	5	3	CA050303012      	1	20050303	G	5610	9599122104	NOZZLE          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDOW	LOOSE           	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF THE FLIGHT CREW HEARD A LOW PITCH HOWLING NOISE FROM THE COPILOTS SIDE THAT SEEM TO INTENSIFY WITH 	INCREASED POWER SETTINGS. MAINTENANCE CONDUCTED GROUND RUNS AND FOUND THE NOISE TO BE COMING FROM THE COPILOTS FRESH AIR	 VENT.  WHEN THE VENT WAS OPEN THE NOISE DISAPPEARED, WHEN CLOSING THE VENT THE SOUND WOULD REAPPEAR AND INCREASE AS IT 	WAS CLOSED OFF. THE ECS SYSTEM WAS FUNCTIONING NORMAL IN ALL OTHER RESPECTS. THE VENT WAS TO BE LEFT OPEN A SMALL AMOUNT	 AND THE FLIGHT CREW TO REPORT FURTHER.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005050900002	20050509	00002	GL  	2005	5	9	CA050303013      	1	20050224	G	2420	GL45615011	LINKAGE         	HAMSTD      		BOMBDR	BD700 	BD7001A10   	1390006	GL  										RAT DOOR	BENT            	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA						0162					(CAN) AT 41,000' MACH .85 THERE WAS UNCOMMANDED RAT DEPLOYMENT. RAT DID NOT FULLY DEPLOY, LOCK INTO POSITION.  STOPPED A	BOUT 3 INCHES FROM LOCKED POSITION. BECAUSE THE RAT DID NOT FULLY DEPLOY AND LOCK INTO POSITION, BLADES REMAINED LOCKED 	AND DID NOT TURN. THEREFORE NO EMERG ELECT OR HYDR PWR WAS AVILABLE TO AC.  IT WAS FOUND THAT SWIVEL ROD END ON RAT DOOR	 LINKAGE WAS BENT, WHICH PREVENTED RAT FROM FULLY DEPLOYING.  AC GROUND TESTING, WITH BENT DOOR LINKAGE STILL INSTALLED,	 RESULTED IN SAME PARTIAL DEPLOYMENT OF RAT.  AFTER REPLACEMENT OF BENT DOOR LINKAGE, RAT DEPLOYMENTS ON GROUND RESULTED	 IN NORMAL OPER WITH NO SIGNS OF DAMAGE. INVESTIGATIONS ARE UNDERWAY TO DETERMINE CAUSE OF UNCOMMANDED AUTO-DEPLOYMENT.	2	L	7	2 	4F			RT	T00003NY					 
2005050300066	20050503	00066	SW  	2005	5	3	CA050303014      	1	20050303	G	6220	47120252011	GRIP            			BELL  	47    	47G4A       	1181031	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROTOR GRIP WAS SUBMITTED FOR NDT TESTING IAW AD 2001-17-17 AND WAS REJECTED DUE TO CRACKING IN THE ADAPTER NUT THR	EAD AREA.  GRIP WAS NEW AND HAD ONLY ACCUMULATED 196.9 HOURS SINCE NEW.					1	G	7	1 	3O	3	O		2H3     	E304				 
2005041200014	20050412	00014	SW  	2005	4	12	CA050303015      	1	20050303	G	6220	47120252011	GRIP            			BELL  	47    	47G4A       	1181031	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN ROTOR GRIP WAS REMOVED TO COMPLY WITH AD 2001-17-17 AND WAS REJECTED DUE TO CRACKING INDICATIONS IN THE THREA	DS OF THE ADAPTER NUT AREA.					1	G	7	1 	3O	3	O		2H3     	E304				 
2005050300065	20050503	00065		2005	5	3	CA050304001      	4	20050214	G	6122	469153	ROD END         	HARTZL      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP GOVERNOR	BROKEN          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA						02219TJ					(CAN) ON TAKEOFF ROLL RT ENGINE UNDERSPED BY 300 RPM.  TAKEOFF REJECTED AND RETURNED FOR MAINTENANCE.  MAINTENANCE FOUND	 RT PROP GOVERNOR ROD END (JOINT) BROKEN.  PART REPLACED AND GROUND RUN C/W SERVICEABLE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005050300064	20050503	00064	CE  	2005	5	3	CA050304003      	1	20050302	G	5310		DOOR FRAME      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12700								(CAN) WHEN COMPLYING WITH MFG REPETIVE SEB 03-5, A 2 INCH CRACK WAS DISCOVERED IN THE AREA OF THE LT LOWER DOOR HINGE AT	TACH POINT ON THE DOOR POST.  INSTALLED SERVICE KIT SK172-154TO REPAIR THE CRACK.  NO INDICATIONS OF CRACKS ON THE RT SI	DE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005050300063	20050503	00063	SO  	2005	5	3	CA050305001      	2	20050204	G	8520		CRANKCASE       			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) VISUAL INSPECTION DETECTED CRACKED CASE. ONCE ENGINE DISMANTLED, EXCESSIVE CRACK FOUND IN THE FRONT MAIN JOURNAL A	REA.  LARGE SECTION OF JOURNAL COMPLETELY DETACTED FROM CASE.					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
2005050300062	20050503	00062	CE  	2005	5	3	CA050305003      	1	20050304	G	5312	12134121318	BULKHEAD        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10239								(CAN) STN 18.4 BULKHEADS FOUND CRACKED LT AND RT SIDE AT AFT FUELING STEP ATTACHPOINTS.  BULKHEAD REPAIRED LT AND RT SID	E IAW MM SECTION 1 8 PAR 18-64 FIGURE 18-4.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2005050300061	20050503	00061	WP  	2005	5	3	CA050306001      	1	20050225	G	6210	369D21100523	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) MAIN ROTOR BLADE SKIN CRACKED AT DOUBLER LIP ON BOTTOM SIDE OF BLADE CHORDWISE. CRACK LENGTH 2 INCHES.  RUNS UNDER	NEATH SEALANT THAT BOND DOUBLER TO THE BLADE.  FOUND DURING 100 HR INSPECTION M/R TORQUE EVENT INSPECTION.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005050300060	20050503	00060	NE  	2005	5	3	CA050307001      	2	20050224	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					BOTH	UNRESPONSIVE    	W				R				AUTOROTATION            				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA								TX0066			(CAN) ON APPROACH NEITHER ENGINE RESPONDED TO INCREASED COLLECTIVE.  THE AIRCRAFT AUTOROTATED TO A HEAVY LANDING.  MFG W	ILL MONITOR THE INVESTIGATION INTO THIS EVENT AND WILL SUPPLIMENT THIS REPORT TO REFLECT ROOT CAUSE, ONCE ESTABLISHED.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005050300059	20050503	00059	EA  	2005	5	3	CA050307002      	2	20050203	G	7321	32447452	FCU             			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED INCREASE IN TORQUE AND FAILED TO RESPOND TO THROTTLE INPUT.  T	HE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED A FRACTURED FUEL CONTROL COUPLING SHAFT.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005050300058	20050503	00058	NE  	2005	5	3	CA050307003      	2	20050210	G	7320	324485824	HMU             			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, (ENGINE OUT) INDICATION ANNUNCIATED.  THE PILOT SHUT THE ENGINE DOWN IN FLIGHT AND COMPLETED A SI	NGLE-ENGINE LANDING AT POINT OF DESTINATION. SUBSEQUENT INVESTIGATION REVEALED AN UNSERVICEABLE ENGINE HYDRO MECHANICAL 	FUEL CONTROL UNIT.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005050300057	20050503	00057	NE  	2005	5	3	CA050307004      	2	20050218	G	7321	8063162C	FMU             			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY A (FADEC FAILED) ANNUNCIATION.	  THE PILOT ASSUMED MANUAL CONTROL OF THE ENGINE, ABORTED THE FLIGHT AND DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INV	ESTIGATION REVEALED AN UNSERVICEABLE ENGINE FUEL MANAGEMENT MODULE.				1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2005050300056	20050503	00056	NM  	2005	5	3	CA050307005      	1	20050225	G	7312	108790	FUEL HEATER     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE EXPERIENCED A LOSS OF OIL PRESSURE IN FLIGHT.  THE PILOT SHUT THE ENGINE DOWN IN FLIGHT AND DECLARED AN	 EMERGENCY.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE FROM A CRACKED FUEL OIL HEAT EXCHANGER.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005050300055	20050503	00055	NE  	2005	5	3	CA050307006      	2	20050221	G	7230		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PW120 	PW127       	 	NE  						LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								AS0005			(CAN) DURING FLIGHT, THE ENGINE LOST OIL PRESSURE.  THE PILOT SHUT THE ENGINE DOWN AND DIVERTED TO POINT OF DEPARTURE.  	SUBSEQUENT INSPECTION REVEALED A SEIZED HIGH PRESSURE ROTOR.  MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL 	SUPPLEMENT THIS REPORT TO REFLECT ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005041200013	20050412	00013	NE  	2005	4	12	CA050307007      	2	20050225	G	7200		ENGINE          			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								AM0057			(CAN) DURING CLIMB, THE ENGINE EXPERIENCED AN INCREASE IN TURBINE TEMPERATURE ACCOMPANIED BY VIBRATION AND NOISE.  THE C	REW SHUT THE ENGINE DOWN IN FLIGHT AND DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DEBRIS ON THE TUR	BO MACHINERY AND REDUCTION GEARBOX CHIP DETECTORS.  MFG WILL INVESTIGATE THE EVENT AND WILL SUPPLIMENT THIS REPORT TO RE	FLECT ROOT CAUSE ONCE DETERMINED.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005050300054	20050503	00054	NM  	2005	5	3	CA050307008      	1	20050224	G	3240	58570	BRAKE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	EMERGENCY PARK	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE ON ROUTE FROM THE HANGAR THE AIRCRAFT FELT LIKE IT HAD A FLAT TIRE. ADDITIONAL POWER WAS REQUIRED TO CLEAR R	UNWAY AND MANOUVERING AREA. ONCE SAFELY CLEAR OF ABOVE MENTIONED AREAS THE AIRCRAFT WAS SHUTDOWN AND INSPECTED.  IT WAS 	NOTE THAT ALL 4 BRAKE ASSEMBLIES WERE GLOWING. ALL 4 BRAKE ASSEMBLIES AND WHEELS WERE REPLACED ALONG WITH THE EMERGENCY 	PARK BRAKE ASSEMBLY.  FUNCTIONAL CHECK CARRIED OUT AND NO FURTHER FAULTS FOUND.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005050300053	20050503	00053	NE  	2005	5	3	CA050307009      	2	20050228	G	7320	324485318	FCU             			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER.  THE CREW SHUT THE ENGINE DOWN IN FLIGHT A	ND DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INVESTIGATION REVEALED AN UNSERVICEABLE ENGINE MECHANICAL FUEL CONTROL UN	IT(FCU).				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005050300052	20050503	00052	SW  	2005	5	3	CA050307010      	1	20050224	G	6220	NAS10222A8	NUT             			BELL  	412   	412         	1182202	SW  										ROTOR HUB	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) CAD PLATED NUT NAS1022AX8 INSTALLED INSTEAD OF DRY FILM LUBED NAS10222A8. THE NAS1022AX8 NUT FAILED DURING TORQUE 	UP, PART CRACKED.					1	G	7	2 	4U				H4SW    					 
2005050300051	20050503	00051	EU  	2005	5	3	CA050307011      	1	20050304	G	2497		WIRE            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  		OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA											(CAN) OVERHEATED WIRES ON TB-10 WERE REPAIRED THIS WAS DUE TO LOOSE NUT ON MAIN POWER FEED.						1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
2005050300050	20050503	00050	CE  	2005	5	3	CA050307012      	1	20050303	G	2750	SM50D7	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	TE FLAP CONTROL	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) CREW REPORTED FLAP MOVEMENT AS INTERMITTENT.  MAINTENANCE REPLACED THE FLAP CONTROL RELAY AND THE AIRCRAFT WAS REL	EASED.  FURTHER INVESTIGATION INTO THE RELAYS IDENTIFIED A KNOWN MANUFACTURER PROBLEM WITH RELAYS PRIOR TO DATE CODE 044	4.  THE CODE IDENTIFIES YEAR 2004-WEEK 44. POST 0444 RELAYS HAVE BEEN MODIFIED TO CORRECT THE INTERMITTENT ISSUE WITH TH	E RELAYS THROUGH A MODIFICATION TO PREVENT STICKING AND INTERMITTENT ACTUATION.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005050300049	20050503	00049		2005	5	3	CA050307013      	4	20050303	G	8300	8679225	PLANETARY GEAR  			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54202			(CAN) DURING ROUTINE MAINTENANCE, THE OIL PRESSURE TREND WAS NOTICED TO HAVE DROPPED ABOUT 12 PSI IN RECENT DAYS. THIS T	OGETHER WITH A BAD OIL SAMPLE INDICATED A PLANETARY CARRIER PROBLEM AS EXPERIENCED IN THE PAST BY THIS OPERATOR. THE ENG	INE GEARBOX WAS DISASSEMBLED AND THE PLANETARY GEAR CARRIER WAS FOUND CRACKED. THE CRACKS ORIGINATED FROM THE OIL GALLER	Y PASSAGES.  THE ENGINE WAS REMOVED FOR REPAIR.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2005050300048	20050503	00048	EA  	2005	5	3	CA050308001      	1	20050303	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) WE HAVE RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT.  RT SIDE WINDOW CRACKED DURING DESCENT AT ABOUT 400	0 FEET.  COPILOT'S SIDE WINDOW REPLACED IAW AMM AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005050300047	20050503	00047	WP  	2005	5	3	CA050308002      	1	20050306	G	7920	7938314501	LINE            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					OIL PRESSURE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						P728034					(CAN) FLIGHT DIVERTED, DUE TO THE NR 1 ENGINE PROBLEM. THE NR 1 ENGINE LOST OIL QTY TO 0, ASSOCIATED WITH LOW PRESSURE L	IGHT AND PRESSURE INDICATION AT 22 PSI. THE ENGINE WAS SHUT DOWN IN FLIGHT. ON GROUND, MAINTENANCE FOUND ONE OIL LINE LE	AKING.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005050300046	20050503	00046	EU  	2005	5	3	CA050308003      	1	20050104	G	3260		SWITCH          			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AC DEPARTED IN HEAVY RAIN, LANDED IN FREEZING CONDITIONS. ON TAKEOFF LANDING GEAR WAS SELECTED UP, LANDING GEAR DO	ORS OPENED, LANDING GEAR RETRACTED, BUT DOORS WOULD NOT CLOSE. LANDING GEAR WAS SELECTED DOWN, LANDED SAFELY.  MAINT FOU	ND MOISTURE IN LANDING GEAR CONNECTOR PLUGS.  CONNECTOR PLUGS WERE CLEANED, GEAR SWING WAS COMPLETED TO VERIFY CORRECT O	PS, AC WAS RELEASED FOR SERVICE, FLEW SAFELY FOR 2 NIGHTS, THEN SAME SCENARIO REPEATED ITSELF. INVEST REVEALED THAT RT D	OOR ACTUATOR MICROSWITCH HAD HEAVY GREASE INSIDE SWITCH. SWITCH WAS CLEANED AND A GEAR SWING COMPLETED. AC RETURNED TO S	ERVICE. IMPLEMENTED AN INSP OF ALL 9 MICROSWITCHES AND CONNECTOR PLUGS (6 WEEK INTERVAL) TO PREVENT RECURRENCE.	2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2005050300045	20050503	00045	CE  	2005	5	3	CA050308004      	1	20050110	G	5511	043200146	RIB             	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											(CAN) LEADING EDGE, LT IB RIB WAS FOUND CRACKED AT THE TOP REAR CORNER (RADIUS).						1	H	7	1 	3O	3	O		3A19    	E223	5	N	P50GL	 
2005052300128	20050523	00128	CE  	2005	5	23	CA050308005      	1	20050113	G	5511	04320016	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13332								(CAN) RT LEADING EDGE IB RIB WAS FOUND CRACKED AT REAR LOWER CORNER (RADIUS).						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005052300127	20050523	00127	CE  	2005	5	23	CA050308006      	1	20050113	G	5511	043200146	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13332								(CAN) LT LEADING EDGE IB RIB WAS FOUND CRACKED AT REAR TOP CORNER (RADIUS).						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005050300044	20050503	00044	CE  	2005	5	3	CA050308007      	1	20050113	G	2720	105740X2F0250	BUSHING         	BEECH       		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RUDDER PEDAL	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BOLT, P/N 130909B172, ATTACHING RUDDER PEDAL TO RUDDER PEDAL ARM WILL NOT FIT PROPERLY THROUGH BUSHING. THE RUDDER	 PEDAL MUST THEN TURN ON THE BOLT AND THE BUSHING MUST TURN WITHIN THE RUDDER PEDAL ARM CAUSING PREMATURE WEAR AND/OR PO	SSIBLE FAILURE.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	STC	 
2005050300043	20050503	00043	NM  	2005	5	3	CA050308008      	1	20050305	G	1430	BACC30BK5	COLLAR          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	RT WING FASTENER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			34826								(CAN) 8 COLLARS WERE FOUND CRACKED ON THE RT WING FORWARD SPAR AT EXTENSION SPLICE YW 490.00, ANOTHER 2 OF THE SAME COLL	ARS WERE ALSO CRACKED ON THE SAME LOCATION ON THE AFT SIDE.  INSPECTION OF THE LT WING IN THE SAME YW 490.00 LOCATION RE	VEALED FURTHER TWO FASTERNERS WITH THE SAME P/N COLLARS CRACKED ON THE FRONT SPAR AND FOUR OTHER CRACKED ON THE AFT SIDE	.  ALL OF THE ABOVE DEFECTS WERE NOTED DURING A C-CHECK INSPECTION.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005041200012	20050412	00012	GL  	2005	4	12	CA050308009      	2	20050228	G	7230	230397911	ADAPTER         	ALLSN       	250C20B     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAC36542					(CAN) COMPONENT DID NOT MAKE IT THROUGH ITS LIFE EXPECTANCY.  FRETTING WEAR FOUND OVER PILOT OUTSIDE DIAMETER.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005050300042	20050503	00042	WP  	2005	5	3	CA050308010      	2	20050304	G	7310	B99193	SHAFT           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		CL	CLIMB          	1			CA								P54093			(CAN) UPON CLIMB OUT, RT ENGINE BEGAN TO SURGE WITH NO RESPONSE FROM PWR LEVER INPUTS.  FLIGHT CREW ELECTED TO SHUTDOWN 	ENG AS A PRECAUTION AND CARRIED OUT AN UNEVENTFUL LANDING. UPON INSP OF ENG, IT WAS FOUND THAT ENG CNTRL CENTER SHAFT OR	 CHRISTMAS TREE DISCONNECTED FROM PROP GOV. IT WAS DETERMINED THAT SET SCREW WHICH SECURES ARM BETWEEN CENTER SHAFT AND 	PROP GOV WAS BACKED OUT WHICH ALLOWED ARM TO DISCONNECT FROM SHAFT.  INSP OF SET SCREW REVEALED A FLAT SPOT ON IT WHERE 	SHAFT HAD BEEN WEARING INTO SCREW DUE TO FACT IT WAS LOOSE.  LINKAGES WERE RE-INSTALLED AND ENG RUNUP CARRIED OUT, SERVI	CEABLE.  FLIGHT TO BASE REVEALED A FUEL LIMITED CONDITION WITH ENG, FCU WAS REPLACED AS A PRECAUTION.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2005050300041	20050503	00041	NE  	2005	5	3	CA050308011      	2	20050304	G	7200		ENGINE          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 1	FAILED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								718043			(CAN) DURING TAKE-OFF THE CREW HEARD A LOUD BANG FOLLOWED BY A DROP IN N1 FROM 80 PERCENT TO 19 PERCENT ON THE NR 1 ENGI	NE.  AT 70 KNOTS FORWARD SPEED A REJECTED TAKE-OFF WAS INITIATED WITHOUT INCIDENT.  ON RETURN TO THE GATE, OIL PRESSURE 	DROPPED TO ZERO.  NR 1 ENGINE WAS REPLACED IAW TASK CARD 80UN-014 AND ENGINE RUN CARRIED OUT SERVICEABLE IAW TASK CARD 8	0EC-001AR1. AIRCRAFT WAS DISPATCHED AND NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.  ENGINE WILL BE SHIPPED TO THE O/H 	FACILITY FOR TEARDOWN AND REPORT ISSUED.		2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005050300040	20050503	00040	EU  	2005	5	3	CA050308012      	1	20050224	G	5754	1372030B57	BRACKET         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FLP/SLT SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14051								(CAN) FLAP SLAT BRACKET FOUND CRACKED DURING MAINTENANCE, CHECK THE CRACKS IN THOSE 3 BRACKETS ARE 1 INCH LONG LOCATED I	N THE FORWARD RADIUS OF THE BENDS.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2005050900001	20050509	00001	CE  	2005	5	9	CA050308013      	1	20050307	G	2432	X610007	CONTACTOR       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALTERNATOR	FAILED          	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) ALT CHARGING SYS WOULDN`T COME ONLINE. TROUBLESHOOTING SHOWED EVERYTHING SHOULD BE WORKING.  ALL VOLTS ( IAW MM) A	PPEARED TO BE NORMAL, CHARGING SYS SHOWING A DISCHARGE. ALT CONTACTOR IS IN SERIES WITH MAIN BUSS & BATTERY. CURRENT NOT	 FLOWING THROUGH CONTACTOR, ALT FAILED TESTS.  HIGH RIPPLE VOLTS DETECTED & FAILURE OF ALT OCCURED. INSTALLED NEW ALT & 	CONTACTOR VOLTAGE, NO CURRENT.  SHUTDOWN SYS. VOLT CHKD AT OUTPUT SIDE OF ALT CONTACTOR & FOUND NORMAL. NO CURRENT FLOW.	  REPLACED ALT CONTACTOR & SYS BEGAN TO OPS CHK OK. 2ND CONTACTOR FAILURE, TOOK 1ST FAILURE, SPLIT OPEN CONTACTOR. CONTA	CT POINTS DISCOLOURED & CONTACT POINTS BLACK (CARBON BUILD UP) POSSIBLE CURRENT LOAD THROUGH CONTACTOR TOO HIGH.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005050300039	20050503	00039	EU  	2005	5	3	CA050308014      	1	20050125	G	6520	350A33020005	GEARBOX         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON A PREFLIGHT IT WAS NOTED THAT ALL OIL HAD EXITED THE TAIL ROTOR GEARBOX. THE INPUT SEAL WAS THE AREA WHERE TH	E OIL EXITED. THE GEARBOX WAS REPLACED AS A PRECAUTION.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005071200025	20050712	00025	SW  	2005	7	12	CA050308017      	1	20050228	G	3222		STRUT           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	INCORRECT       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED AND GEAR WAS SELECTED UP YET THE GEAR WOULD NOT STAY UP AND LOCKED.  AIRCRAFT RETURNED AND MAINT	ENANCE FOUND THAT THE LOWER NOSE STRUT WAS NOTFULLY EXTENDED.  THE OLEO HAD BEEN SERVICED WITH THE PISTON NOT IN THE PRO	PER POSITION WHICH LIMITED THE OLEO LENGTH. THE OLEO WAS SERVICED AND GEAR SWINGS CHECKED SERVICIBLE.AMM PROCEDURE WAS C	ORRECT YET WAS SUBJECT TO INTERPETATION.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005050300037	20050503	00037	SW  	2005	5	3	CA050308018      	1	20050228	G	2910	278100322040	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) LINE CHAFED WHERE LINE COMES THROGH THE COOLING TURBINE MODULATING VALVE.  NEW LINE FABRICATED AND INSTALLED WITH 	ADDITIONAL CLAMPS TO PREVENT FUTURE CHAFING. W.S. 39.1 IPC FIG 29-10-50 FIG 2 ITEM 2					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005050300036	20050503	00036	SO  	2005	5	3	CA050308019      	1	20050307	G	2436	PA31T	REGULATOR       	PIPER       	PA31T       	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DC SYSTEM	WORN            	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA			19726			31T790045					(CAN) DURING CLIMB OUT, THE RT GENERATOR FAILED AND THE AIRCRAFT RETURNED TO THE AIRPORT. A RUN UP WAS CARRIED OUT AND I	T WAS DISCOVERED THAT THE LT GENERATOR ALSO DROPPED (OFFLINE) WHEN THE RT VOLTAGE REGULATOR CIRCUIT BREAKER IS PULLED AN	D RESET. THE SOCKETS IN THE VOLTAGE REGULATOR CONNECTOR PLUGS WERE FOUND TO BE SLIGHTLY WORN.  SOCKETS WERE REPLACED, SA	TISFACTORY RUN UP AND A TEST FLIGHT WAS CARRIED OUT.			1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2005050300035	20050503	00035	EA  	2005	5	3	CA050308020      	1	20050304	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE CO-PILOT'S WINDOW CRACKED.  WINDOW REPLACED IAW AMM AND THE AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005041200011	20050412	00011	SW  	2005	4	12	CA050309001      	1	20050301	G	2910	214001023101	TUBE            	BELL        		BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT72A       	30030	NE  					HYD SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE, THE SUBJECT TUBE WAS FOUND WITH A (0.375 INCH X 0.187 INCH) HOLE THAT ORIGINATED FROM 	CHAFING WITH A HYDRAULIC OIL LINE.  THE HOLE WAS LOCATED APPROXIMATELY IN THE CENTER OF THE TUBE.  THE TOTAL CHAFING DAM	AGE IN THIS AREA, COVERED APPROXIMATELY TWENTY PERCENT OF THE TUBE CIRCUMFERENCE.  IN ADDITION, THERE WERE TWO OTHER ARE	AS DISPLAYING SIGNIFICANT CHAFING DAMAGE NEAR THE TOP END OF THE TUBE, ORIGINATING FROM CONTACT WITH ANOTHER OIL LINE.  	IT WAS EVIDENT THAT INCORRECT ROUTING OF THE OIL LINES WAS THE CAUSE OF THE DISCREPANCY.  THERE WAS NO DAMAGE TO THE OIL	 LINES AS THEY WERE COVERED WITH PLASTIC SPIRAL WRAP.	2	G	7	2 	4U	4	U		H10SW   	E8NE				 
2005050300034	20050503	00034	SW  	2005	5	3	CA050309002      	1	20050228	G	6520	406340105101	SEAL            	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					T/R GEARBOX	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						AFS2825					(CAN) T/R GEARBOX OUTPUT SEAL LEAKING, SENT FOR SEAL REPLACEMENT.  THE SPRING INSIDE THE SEAL WAS AT THE SEAL LIP AND MA	RKED THE SLEEVE .					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005050300033	20050503	00033	SW  	2005	5	3	CA050309003      	1	20050308	G	6520	406340105101	SPRING          	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					GEARBOX SEAL	MISMANUFACTURED 	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA						AMM01698					(CAN) OIL LEAK FROM T/R GEARBOX OUT PUT.  THE SPRING INSIDE THE SEAL WHEN TO THE SEAL LIP AND MARK THE SLEEVE.   THIS IS	 THE SECOND TIME IN 2 WEEKS, THE SPRING IS TO TIGHT AND PUSHES TO MUCH ON THE SEAL LIP .					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005050300032	20050503	00032	CE  	2005	5	3	CA050309004      	1	20050307	G	3530	OB30	BOOSTER         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	OXYGEN SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SHOP TOOL FOR FILLING O2 SYSTEMS. THE OXYGEN BOOSTER DESCRIBED ABOVE WAS BEING USED TO FILL MEDICAL OXYGEN IN TO T	HE AIRCRAFT LIFEPORT MEDICAL SLED ON BOARD THE AIRCRAFT, WHEN THE UNIT EXPLODED WITH NO WARNING SENDING A TORCHING FLAME	 WITH HOT SHRAPNEL APPROXIMATELY 45 FEET ACROSS THE HANGER, HITTING A WALL AND STARTING A SMALL FIRE. LUCKILY THE OPERAT	OR ESCAPED WITH MINOR BURNS, DUE TO HIS CLOSE PROXIMITY, AND MINOR DAMAGE TO THE HANGAR AREA.  QUICK THINKING ON THE PIL	OTS PART HELPED TO LIMIT THE DAMAGE, BUT IF THIS WAS TO HAPPEN AGAIN, IT COULD CAUSE A LOSS OF LIFE AND OR THE DESTRUCTI	ON OF THE BUILDING AND AIRCRAFT.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005050300031	20050503	00031	NM  	2005	5	3	CA050309005      	1	20050307	G	3320	BV033000220	SUPPORT         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LIGHT	MELTED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE FLIGHT ATTENDANT NOTED A STRONG ELECTRICAL ODOR IN THE CABIN IN THE AREA ADJACENT TO THE PSU PANE	L AT SEAT 8A. THERE WAS NO EVIDENCE OF SMOKE OR HEAT IN THE AREA. THE FLIGHT CREW BRIEFED THE PASSENGERS, NOTIFIED THE T	OWER AND LANDED UNEVENTFUL. UPON INSPECTION ON THE GROUND, THE CREW WAS UNABLE TO PIN-POINT THE SOURCE OF THE ODOR, BUT 	BELIEVED IT TO BE IN OR AROUND THE PSU PANEL.  MX WAS DISPATCHED FOR INVESTIGATION AND REPAIR.  THE CAUSE OF THE INCIDEN	T WAS DETERMINED TO BE A MELTED END SUPPORT FOR THE LIGHTING TUBE ADJACENT TO ROW 8A. THE PN OF THE END SUPPORT IS BV033	00-02-20. BOTH END SUPPORTS AND LAMP WERE REPLACED AND THE WIRING AND CONNECTIONS INSPECTED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005050300030	20050503	00030	EU  	2005	5	3	CA050309006      	1	20050305	G	5540	A5547150002200	RUDDER          			AIRBUS	310   	A310        	       	EU  										EMPENNAGE	SEPARATED       	W				A				UNSCHED LANDING         				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			49202								(CAN) AFTER DEPARTURE IN CRUISE AT 35000 FT, THE CREW REPORTED THAT A LOUD BANG WAS HEARD. THE PILOT TOOK MANUAL CONTROL	 AND RETURNED TO LAND SAFELY AT THE DEPARTING AIRPORT.  VISUAL INSPECTION AFTER LANDING REVEALED THAT A LARGE PORTION OF	 THE RUDDER SURFACE WAS MISSING.  A PORTION OF THE RUDDER STRUCTURE REMAINED ATTACHED BETWEEN LOWER HINGE AND THE 3 SERV	O-CONTROL ATTACHMENT POINTS.  THE EVENT IS SUBJECT TO A FORMAL INVESTIGATION. MFG HAS SENT A TEAM OF SPECIALISTS TO ASSI	ST THE AUTHORITIES WITH THEIR INVESTIGATION.		2	L	7	2 	4F			RT	A35EU   					 
2005050300029	20050503	00029	EU  	2005	5	3	CA050309007      	2	20050308	G	7314	GB3173CE	PUMP            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 1 ENG FUEL	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) THE NR 1 ENGINE FUEL PUMP FAILED ON TAKEOFF POWER APPLICATION. THE AIRCRAFT RETURNED TO THE COMPANY RAMP WHERE IT 	WAS DETERMINED THE FUEL PUMP HAD FAILED.  THE PUMP WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER GROUND TE	STING SERVICEABLE.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005052300126	20050523	00126	CE  	2005	5	23	CA050309008      	1	20050302	G	3242	1013800157	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	BRAKES	LEAKING         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING LANDING, AC PULLED TO RT, FULL LT BRAKING, REVERSE AND RUDDER WERE UNABLE TO KEEP AC ON RUNWAY.  AC CAME TO	 A STOP RT OF LANDING DIRECTION, WITH RT MAIN AND NOSE GEAR OFF OF RUNWAY.  DETERMINED THAT RT SIDE BRAKES WERE FROZEN C	AUSING WHEELS TO LOCK UP.  OTHER THAN 2 RT MAIN TIRES BEING SQUARED OFF, NO DAMAGE TO AC.  BRAKE DE-ICE SYS WAS VISUALLY	 INSPECTED, NO DAMAGE WAS FOUND.  LEAK CHECK WAS COMPLETED, CAUSE OF BRAKES FREEZING WAS A LEAKING RT BRAKE DE-ICE HOSE.	  HOSE VISUALLY APPEARED SERVICEABLE BUT A LEAK WAS FOUND 8 INCHES FROM LOWER END OF HOSE BENEATH UNDAMAGED OUTER PROTEC	TIVE SHEATH. THIS IS LOWER HOSE THAT CONNECTS TO THE MANIFOLD. THE HOSE, WHEELS WERE REPLACED, AC RETURNED TO SERVICE.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005050300028	20050503	00028	EA  	2005	5	3	CA050309009      	1	20050304	G	5610	601R3303317	WINDSCREEN      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) A/C , WAS ENROUTE AT FL 360 WHEN THE CREW ADVISED ATC THAT THEIR WINDSCREEN SHATTERED AND REQUESTED DESCENT.  A SH	ORT TIME LATER, THE CREW REQUESTED DIVERSION .  THE FLIGHT LANDED SAFELY AT 2313Z.  NO EMERGENCY WAS DECLARED BUT AFF RE	SPONDED.  A/C WAS FERRIED TO HAVE WINDSCREEN REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300027	20050503	00027	SW  	2005	5	3	CA050309011      	1	20050307	G	6240	2060763731	TACH GENERATOR  			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE WORN SPLINES WERE FOUND.  NOTE: THESE SPLINES DRIVE THE HYDRAULIC PUMP. TACH GENERATOR 	WAS REMOVED AND SENT FOR OVERHAUL. PART WAS RETURNED 2 MONTHS LATER WITH NEW PAINT AND THE SAME WORN OUT SPLINES. OLD GR	EASE WAS STILL IN THE WORN SPLINES.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005050300026	20050503	00026	EA  	2005	5	3	CA050309012      	1	20050306	G	7810	311178001	DUCT            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	EXHAUST PORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RB0138			(CAN) AT EXHAUST PORT, THE FLANGE THAT PROTRUDES OUT OF THE CASE TO PREVENT EXHAUST GASES FROM EXITING THROUGH THE FLANG	E WHERE THE EXHAUST STACK BOLTS ON, WAS CRACKED ABOUT 320 DEGREES AROUND THE CIRCUMFERENCE. THE OPPOSITE PORT WAS DETERM	INED TO BE CRACKED TO A LESSOR AMOUNT.  THE EXHAUST FLANGE ON THE EXHAUST DUCT ITSELF WAS SERVICEABLE.				1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
2005041200010	20050412	00010	EA  	2005	4	12	CA050309013      	1	20050306	G	6120	210574AB	CSU             			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) ON RUNUP AFTER INSTALLATION, IT WAS FOUND THAT THE OVERHAULED PROPELLER CONTROL UNIT WOULD NOT FUNCTION PROPERLY. 	 THE PROPELLER REMAINED IN THE BETA MODE AND THERE WAS NO CONTROL OTHER THAN FEATHER/UNFEATHER.  ANY ADDITION OF POWER R	ESULTED IN THE PROPELLER MOVING INTO THE REVERSE RANGE.  THE UNIT WAS AN EXCHANGE.				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005052300125	20050523	00125	SO  	2005	5	23	CA050310001      	1	20050220	G	3242	0690200	BOLT            	CLEVELAND   		GRUMAN	G73   	G73T        	3951902	SO  	LYC   	O320  	O320D1D     	41508	EA  	HARTZL	HCF2Y	HCF2Y*      	GL  	LT BRAKE ASSY	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) PILOT REPORTED NORMAL LANDING, WITH NORMAL BRAKE USE, ON LANDING ROLL OUT BRAKES WERE APPLIED, THERE WAS NO LT BRA	KE, BRAKE CHECK AND FOUND TO HAVE DEPARTED FROM AIRCRAFT. PILOT FOUND IT ON THE RUNWAY.  NOTE: ONE ANCHOR NUT SHOWED SIG	NS OF BEING PARTLY CRACKED ON SHAFT.				1	H	7	2 	3R	3	O		A783    	E274	5	C	P27EA	 
2005050300025	20050503	00025	EU  	2005	5	3	CA050310002      	1	20050309	G	2750	527521214	DRIVE ASSY      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT IB FLAP DRIVE ARM BENT AND CRACKED LENGTHWISE.  CAUSE OF FAULT IS FLAP INTERCONNECT CABLE FREEZING AND WHEN THE	 FLAPS ARE EXTENDED IT BENT AND CRACKED DRIVE ARM.  NOTE FROM QA, SYSTEM WAS STILL FUNCTIONING PROPERLY AT THE TIME OF F	INDING THE CRACKED ARM.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005050300024	20050503	00024	CE  	2005	5	3	CA050310003      	1	20050310	G	3340	4522	LAMP            			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LANDING LIGHT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) STATIC WAS NOTED IN THE HEADPHONES WHEN LANDING LIGHT WAS TURNED ON. LIGHT WAS NOTED INOPERABLE AFTER LANDING, AND	 UPON VISUAL INSPECTION IT COULD BE SEEN THAT ONE OF THE FILAMENT MOUNTING WIRES HAD SEPARATED AT ITS SPOT-WELD AND WAS 	VIBRATING AGAINST THE TERMINAL INSIDE THE BULB WHILE THE ENGINE WAS RUNNING, CREATING THE STATIC. THE LIGHT IS MOUNTED I	N THE ENGINE COWLING.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005052300124	20050523	00124	EU  	2005	5	23	CA050310004      	1	20050304	G	5210	350A25127520	PIN             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PIN P/N 350A25-1275-20 WAS REMOVED FOR NDT IAW THE REQUIREMENTS OF AD F-2005-032 AND ALERT TELEX 05.00.47.  A VISU	AL INSPECTION OF THE PIN REVEALED A CRACK ON BOTH SIDES OF THE HOLE THAT IS DRILLED TO FIT UPON INSTALLATION. THE PIN WA	S REPLACED.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005050300023	20050503	00023	EA  	2005	5	3	CA050310005      	1	20050113	G	2824	T99B38601	EJECTOR         			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					FUEL SYSTEM	STUCK           	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHILE PARKED IN BREST, THE CREW NOTICED AND UNCOMMAND FUEL TRANSFERED INTO THE CENTER TANK DURING THE NIGHT.  THE 	NEXT REVENUE FLIGHT WAS CANCELED FOR TROUBLESHOOTING.  TROUBLESHOOTING (JAN. 13, 2005) REVEALED A LEAK ON THE LT TRANSFE	R EJECTOR PUMP.  THE UNIT WAS REPLACED. IT WAS NOTED THAT THE TRANSFER EJECTOR CHECK VALVE WAS STUCK (OPEN) THE FUEL QUA	NTITY GAUGE COMPUTER (FQGC) WAS ASLO REPLACED BY PRECAUTIONARY MEASURES.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005050300022	20050503	00022	NE  	2005	5	3	CA050311001      	2	20050309	G	8530	399353A1	CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT AT 1200 ASL, THE PILOT REPORTED A MISS IN THE ENGINE ACCOMPANIED WITH A REDUCTION IN CRUISE S	PEED. CARB HEAT WAS SELECTED AND ENGINE CHECKS COMPLETED.  SHORTLY THEREAFTER, THE ENGINE BACKFIRED 3 TIMES BUT CONTINUE	DTO RUN NORMALLY BUT ROUGHLY.  A PRECAUTIONARY LANDING WAS COMPLETED.  MAINTENANCE INVESTIGATION REVEALED THAT THE NR7 C	YLINDER HEAD HAD SEPARATED FROM THE BARREL.			1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005050300021	20050503	00021	EA  	2005	5	3	CA050311002      	2	20050123	G	8530		ENGINE          			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  		FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			CA								L1152240			(CAN) ENG FOUND TO HAVE DROP IN OIL PRESS.  INSP, PUNCTURE HOLE WAS FOUND IN TOP OF RT CRANKCASE HALF.  METAL WAS FOUND 	IN OIL SCREEN.  CYL 2, 4, AND 6 WERE REMOVED FOR INSP.  4 OF 12 LIFTER BODY CONTACT FACES WERE BROKEN.  BROKEN MATERIAL 	FROM LIFTER BODIES INTRODUCED TO ENGINE, RESULTING, COMPLETE DESTRUCTION OF ENG INTERNAL.  EXACT CAUSE OF LIFTER BODY CO	NTACT FACES BREAKING COULD NOT BE DETERMINED, SUSPECTED THAT EXCESS CORROSION ON LIFTER FACE COULD HAVE BEEN TO BLAME. D	ETERMINED BY RETRIEVAL OF BROKEN PIECES IN ENGINES OIL SUMP AND OIL SCREEN AND EXAMINING THEM. CORROSION WAS EVIDENT ON 	2 OF  LIFTER FACES.  ENG DOES NOT REACH HIGH ENOUGH OPERATING TEMP TO BURN OFF MOISTURE CREATED BY ENG OPERATION.	1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
2005052300123	20050523	00123	CE  	2005	5	23	CA050311003      	1	20050309	G	3230		SPLINE          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	INTERNAL	LACK OF LUBE    	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA						472M					(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN AND THE NOSE GEAR DID NOT FULLY EXTEND.  AN EMERGENCY EXTENSION PRO	CEDURE WAS CARRIED OUT AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THAT THE SPLINE COUPLING CONN	ECTING THE HYDRAULIC POWER PACK MOTOR TO THE PUMP HAD FAILED DUE TO WEAR FROM LACK OF LUBRICATION AND CORROSION.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2005050300020	20050503	00020	NE  	2005	5	3	CA050311005      	2	20050311	G	7200	PT6D114	ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  		UNKNOWN         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								PCE17232			(CAN) DURING TAKEOFF AND CLIMB OUT PILOT REPORTED A CHANGE IN THE SOUND OF THE ENGINE.  AIRCRAFT RETURNED. PILOT REPORTE	D ENGINE INDICATION NORMAL, NO ENGINE PERFORMANCE ABNORMALITIES. MAINTENANCE INSPECTED THE ENGINE OIL FILTER, NO FINDING	S, ENGINE WAS RUN WITH NO FAULTS FOUND. SUSPECT THE ENGINE INERTIAL SEPARATOR NOT STOWED CORRECTLY CAUSING INTAKE AIR DI	STURBANCE. AIRCRAFT HAS BEEN RETURNED TO SERVICE.			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005050300019	20050503	00019	EA  	2005	5	3	CA050312001      	1	20050309	G	4920	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU BAY	DAMAGED         	W				F				ACTIVATE FIRE EXT.      				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA			17205								(CAN) AFTER APU SHUTDOWN, FIRE AND SMOKE OUT OF EXHAUST, FOUND OIL-SYSTEM EMPTY AND OIL BURNING AT APU EXHAUST: APU EXTI	NGUISHED WITH FIRE X BOTTLE. FIRE DAMAGE INSPECTION APU EXHAUST HEATSHIELD, LOWER TRANSLATING, COWL AND ACCESS PANEL NR 	422DB,422BB, 422CB, 422EB,444BB REMOVED. WIRES AND CABLES IN AREAS MENTIONED ABOVE INSPECTED, NO SIGNS OF HEAT DAMAGE FO	UND AREA AND STRUCTURE INSIDE RT PYLON INSPECTED, NO SIGNS OF HEAT DAMAGE FOUND APU ENCLOSURE AND AFT EQUIPMENT BAY INSP	ECTED, NO SIGNS OF HEAT DAMAGE FOUND.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300018	20050503	00018		2005	5	3	CA050312002      	4	20050226	G	8300	6890914	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE GEARBOX	WORN            	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ENGINE CHIP LITE REPORTED BY PILOT ON ENGINE STARTUP.  CHIP PLUGS CHECKED AND METAL FOUND, MAINTENANCE FOUND WORN 	2.5 BEARING AND WORN INNER RACE ON SPUR ADAPTER SHAFT.  BOTH ITEMS CHANGED AND A/C RETURNED TO SERVICE WITH OUT ANY FURT	HER PROBLEMS.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005052300122	20050523	00122	EU  	2005	5	23	CA050312003      	1	20050223	G	6520	770441	MAGNETIC SEAL   	AEROSP      		SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					T/R GEARBOX	DISLODGED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA						M909					(CAN) AFTER LANDING, OIL WAS FOUND ALL OVER TAIL GEARBOX AREA, MAINTENANCE WAS CALLED AND T/R G/B WAS REPLACED WITH A RE	NTAL AND NO FURTHER PROBLEM WAS FOUND.  UPON INSPECTION AT MAIN BASE THE VENT HOLE ON THE INPUT WAS FOUND PLUGGED UP , T	HIS WE FEEL WAS THE CAUSE OF THE MAG SEAL TO BECOME DISLODGED AND BEGIN LEAKING.  THIS GEARBOX WAS CLOSE TO O/H SO IT WA	S SENT IN EARLY AND NEW SEAL WAS INSTALLED.			1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2005050300017	20050503	00017	EA  	2005	5	3	CA050312004      	1	20050310	G	5610	NP1393211	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			20183								(CAN) LT WINDSHIELD CRACKED DURING LEVEL FLIGHT.  DIVERTED FLIGHT.  LT WINDSHIELD WAS REPLACED IAW AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005050300016	20050503	00016	NM  	2005	5	3	CA050314001      	1	20050311	G	7170	DSC1975	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE DRAIN	BLOCKED         	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			J	A		WARNING INDICATION        	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING A MAINTENANCE GROUND RUN, THE RT ENGINE DEVELOPED A TAIL PIPE FIRE AFTER THE ENGINE START WAS INITIATED. TH	IS WAS CONFIRMED BOTH BY FIRE WARNING IN THE COCKPIT AND BY GROUND PERSONNEL. THE ENGINE WAS SHUT DOWN AND THE ENGINE FI	RE BOTTLES WERE ACTIVATED.  INVESTIGATION SHOWED THAT THE GAS GENERATOR CASE DRAIN FLEXIBLE FLUID LINE WAS PLUGGED WITH 	DEBRIS.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005050300015	20050503	00015	CE  	2005	5	3	CA050314003      	1	20050307	G	2820	652635537	LINE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL BOOST	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11253								(CAN) DURING THE ACCOMPLISHMENT OF MFG SB 550-28-14 WING FUEL BOOST PUMP WIRING IMPROVEMENT, LINE ASSEMBLY P/N 6526355-3	7 FOUND DAMAGED, WHICH THE ELECTRIC FUEL PUMP HARNESS CUT THROUGH THE WALL OF TUBING. NO DAMAGED FOUND ON ELECTRICAL HAR	NESS.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005041200009	20050412	00009	GL  	2005	4	12	CA050314004      	2	20050309	G	7250		TURBINE         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	STIFF           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) AFTER A SCHEDULED INSP, WERE GOING TO DO A COMPRESSOR WASH, SINCE THE BLEED VALVE AREA WAS DIRTY.  WHEN THE COMPRE	SSOR WAS NOTED AS BEING STIFF TO TURN, FURTHER INVESTIGATION WAS NEEDED.  AFTER REMOVAL OF THE TURBINE ASSY, THE COMPRES	SOR AND GEARBOX MOVED FREELY. THE 6 AND 7 BEARING AREA WAS CLEANED AND A HEAVY CARBON DEPOSIT NOTED.  THE OIL FLOW AFTER	 CLEANING WAS GOOD AND SAW NO INDICATION OF MECHANICAL PROBLEM.  THE TURBINE WAS INSTALLED AND TEST FLOWN SATISFACTORY. 	AFTER DISSCUSSION WITH A ENGINE REPAIR FACILITY THE OLD COOL DOWN PROCEDURE WAS NOTED AS BEING THE CULPRIT.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005052300121	20050523	00121	EU  	2005	5	23	CA050314005      	1	20050305	G	6730	SC5084	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					HYDRAULIC SYS	RATCHETING      	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) WHILE IN FLIGHT THE PILOT NOTICED A RATCHETY FORE AND AFT CYCLIC MOVEMENT WHILE MOVING THE CYCLIC FORE AND AFT.  S	ERVO SENT TO MFG FOR EVALUATION.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005052300120	20050523	00120	CE  	2005	5	23	CA050315001      	1	20050311	G	5540	MS289135	BEARING         			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RUDDER HINGE	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 800 HR INSP OF AC, TAIL SEC WAS BEING INSPECTED IAW CHECK SHEETS. LIGHT RUB AND WEAR WAS NOTICED ON RUDDER 	HINGE POINTS STRUCTURE.  IT WAS ALSO, THAT RUDDER APPEARED TO BE SITTING LOWER THAN NML ON ITS HINGE POINTS.  INSP OF RU	DDER AND ITS STRUCTURE WAS CARRIED OUT WHICH REVEALED LOWER HINGE POINT BEARING P/N MS28913-5 HAD COMPLETELY DISINTEGRAT	ED ALLOWING RUDDER TO DROP DOWN. PARTS OF BEARING WERE FOUND IN TAIL CONE AND ONLY THING REMAINING IN HINGE WAS BEARING 	RACE.  LIGHT CORROSION WAS EVIDENT ONCE BEARING RACE WAS REMOVED. HINGE POINT DAMAGE WAS CLEANED, INSPECTED, PRIMED, PAI	NTED AND BEARING WAS REPLACED.  ITS WORTH NOTING THAT THERE IS NO LUB OR CORROSION CONTROL REQUIRED IN THIS AREA IAW MM.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005050300014	20050503	00014	EU  	2005	5	3	CA050315002      	2	20050314	G	7310		FITTING         			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	FUEL LINE	BROKEN          	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT PROCEEDED TO TAKEOFF WET POWER.   WET TORQUE WAS NOT ACHIEVED ON RT ENGINE AND TAKEOFF WAS ABORTED.  UPON	 INVESTIGATION, MAINTENANCE FOUND THE FLEXIBLE FUEL FEED LINE TO THE NR5 COMBUSTION CAN BROKEN AT THE ONE END (STEEL POR	TION OF LINE) FUEL LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005050300013	20050503	00013	NE  	2005	5	3	CA050315003      	2	20050309	G	7250	304574101	BLADE           								PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PC0592			(CAN) AFTER ENGINE SPLIT, ENGINE SUFFERED A CT BLADE FAILURE. 1 CT BLADE HAD LOST APPROX HALF OF ITS AIRFOIL, & OTHER BL	ADES HAD MATERIAL MISSING MOSTLY IN THE AIRFOIL UPPER PORTION APPARENTLY AS A RESULT OF IMPACT DAMAGE. MATERIAL FROM CT 	BLADES ALSO DAMAGED HOT SECTION DOWNSTREAM OF CT VANE.  GG CASE DIFFUSER DUCTS HAD UNUSUAL & UNIFORM CRACKING DAMAGE. FR	ACTURE OF BLADE AT MID SPAN IS SUGGESTIVE OF A FATIGUE FAILURE DUE TO BLADE VIBRATION. CT BLADES WERE INSPECTED AT THE L	AST O/H IAW O/H MANUAL. 12 BLADES FOUND TO HAVE UNACCEPTABLE COATING LOSS & REPLACED NEW & BALANCE OF SET INSPECTED AS S	ERVICEABLE & WERE RE-INSTALLED.  THE CT BLADE FAILURE INVESTIGATION.						3	T			E4EA				 
2005050300012	20050503	00012	EA  	2005	5	3	CA050315004      	2	20050309	G	7210		SUN GEAR        								PWA   	PT6   	PT6A28      	 	EA  					ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14967	12388				50439			(CAN) THE SOURCE OF THE METAL CONTAMINATION WAS THE SUN GEAR FROM THE 1ST STAGE REDUCTION GEAR.  THE SUN GEAR HAD LOST A	 CONSIDERABLE AMOUNT OF MATERIAL FROM THE GEAR TEETH FACES.  DAMAGE IS THOUGHT TO HAVE STARTED AS A GEARTOOTH SPALLING W	HICH PROGRESSED, GRADUALLY LOOSING SMALL PARTICLES FROM THE TEETH SURFACES AND CONTAMINATING THE OIL SYSTEM.  PRESENCE O	F SCORING IN THE RGB SCAVENGE PUMP AND MAIN PRESSURE PUMP HOUSINGS WAS  DIRECT RESULT OF PUMPING CONTAMINATED OIL.  THER	E WAS NO SIGN THAT CONTAMINATED OIL BYPASSED THE OIL FILTER AND IT IS NOT FELT THAT THERE WAS ANY CONTAMINATION OF THE P	RESSURE SIDE OF THE ENGINE LUBRICATING SYSTEM.  THE CAUSE OF SUN GEAR SPALLING IS NOT APPARENT.						4	T			E4EA				 
2005050300011	20050503	00011	NE  	2005	5	3	CA050315005      	2	20050130	G	7310	0301007220	LINE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE FUEL SYS	CRACKED         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT SHOWED SIGNS OF IRREGULAR STARTS.  WHILE WATCHING A START, THE ENGINEER NOTICED WHISPS OF SMOKE COMIN	G FROM THE RT SIDE OF THE ENGINE.  TUBE WAS REMOVED AND INSPECTED AND FOUND CRACK ON FLARED END UNDER FERRULE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005052300118	20050523	00118	CE  	2005	5	23	CA050315008      	1	20050111	G	2750	66720	SOLENOID VALVE  			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					TE FLAPS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLAP HYDRAULIC SOLENOID VALVE WEEPING FLUID EXTERNALLY, UNABLE TO LOCATE LOCATION OF LEAK.  THE BOTTOM OF THE VALV	E IS WET AFTER FLIGHT.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005052300117	20050523	00117		2005	5	23	CA050315009      	4	20050225	G	3422	402057723	GYRO            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERY SLOW TO SLAVE WHEN COLD SOAKED OVERNIGHT AT -20 DEGREES C.  TOOK APPROXIMATELY 15 MINUTES TO ALIGN.  AFTER EN	GINE START, OPERATED OK DURING FOLLOWING FLIGHTS, UNTIL COLD SOAKED OVERNIGHT AGAIN WHEN VERY SLOW TO SLAVE.  REPLACED D	IRECTIONAL GYRO, GROUND CHECKED OK.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005052300116	20050523	00116	CE  	2005	5	23	CA050315010      	1	20050311	G	2720	1015240381	ARM             			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	TORQUE TUBE	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION OF THE RUDDER SYSTEM ON A 4TH PHASE 800 HOUR INSPECTION THE BLIND RIVETS WHICH ATTACH THE CON	TROL ARM QUADRANT P/N 101-524038-1, TO THE RUDDER TORQUE SHAFT P/N 101-524012-11, WERE FOUND TO BE LOOSE. THE COMPLETE A	SSEMBLY WAS REMOVED FROM THE AIRCRAFT AND THE LOOSE RIVETS REMOVED AND REPLACED WITH SERVICEABLE UNITS IAW THE SRM. THE 	ASSEMBLY WAS REINSTALLED AND CHECKED SERVICEABLE.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005050300010	20050503	00010	EU  	2005	5	3	CA050315011      	1	20050314	G	5522		SKIN            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN APPROX. 4 INCH CRACK WAS FOUND ON THE RT SIDE, UPPER REAR PORTION OF VERTICAL STAB.  THE AREA IS JUST BELOW THE	 AFT LOWER FAIRING.  THE AIRFRAME STRUCTURAL MANUAL CONTAINS A REPAIR SCHEME SPECIFIC TO THIS CRACKING. REF CHAP 55-00-0	0. REPAIRS ARE IN PROGRESS IAW SRM DRAWINGS. THE LOWER AFT FAIRING SHEAR FITTING AND PLATE ARE ALSO BEING REPLACED WITH 	NEW.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005052300115	20050523	00115	EA  	2005	5	23	CA050315012      	1	20050310	G	2810	234PS4691	VENT            			BOEING	234   	234         	1385049	EA  	LYC   	AL5512	AL5512      	41581	NE  					FUEL TANK	FAILED          	W				E	H			ENGINE SHUTDOWN         	DEACTIVATE SYST/CIRCUITS			K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) DURING REFUELING, A LOUD BANG WAS HEARD FROM CABIN OF AIRCRAFT. FUEL WAS THEN SEEN LEAKING RAPIDLY FROM AIRCRAFT. 	 PILOTS NOTED FUEL INSIDE CABIN SECTION BUT NOT IN COCKPIT. ENGINES WERE SHUT DOWN, ELECTRICAL SYSTEMS TURNED OFF AND PI	LOTS EXITED AIRCRAFT THROUGH THEIR EMERGENCY EXITS. COCKPIT DOOR WAS CLOSED WHICH KEPT FUEL FROM SPRAYING INTO COCKPIT. 	 BREAKAWAY VENT FOR NR1 FUEL TANK HAD FAILED, CAUSING THE TANK TO OVER PRESSURIZE DURING REFUELING.  TANK STRUCTURE FAIL	ED AT 90 PERCENT CAPACITY RELEASING FUEL INTO CABIN. THERE ARE NO WARNING SYS TO ALERT CREW OF FAILURE. REFUELING SEEMED	 TO BE TAKING LONGER THEN USUAL BUT CREW WAS USING A NEW PUMP AND DID NOT ASSOCIATE FLOW RATE WITH A VENT FAILURE.	2	G	7	2 	4U	4	U		H9EA    	E4NE				 
2005050300009	20050503	00009	GL  	2005	5	3	CA050316001      	3	20050314	G	6112	4E11887	BOOT            													HARTZL	HCB4T	HCB4TN5     	GL  	PROP BLADE	MISLOCATED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									CDA3380M2		(CAN) PROPELLER HC-B4TN-5GL, SERIAL NR CDA3380M2, WORK ORDER NR T65300 BLADE DE-ICER PART NR 4E1188-7. WHEN RECEIVED, FO	UND THAT THE DEICE BOOTS HAD BEEN INSTALLED TOO FAR OUT ON THE BLADE.  THEY WERE .6875 TO 1.2500 INCHES FROM THE OUTSIDE	 EDGE OF THE BLADE CLAMP.  IN MANUAL 202, AND IN DRAWING 7E1338 SPECIFY FOR THIS AIRCRAFT INSTALLATION THAT THE DE-ICERS	 SHOULD BE INSTALLED, 1 INCH FROM THE OUTSIDE EDGE OF THE BLADE CLAMP.  BUT IN PROPELLER DE-ICING SYSTEMS REPLACEMENT PA	RTS LIST FOR REFERENCE KIT 65-165, SPECIFIES 1.2500 INCH.  THE MANUFACTURER WAS ADVISED OF THE DE-ICER DISTANCE, AND THE	Y STATED.											6	C	P40EA	 
2005050300008	20050503	00008	GL  	2005	5	3	CA050316002      	3	20050311	G	6110		CYLINDER        	HARTZL      												HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER	LEAKING         	W				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CA						CDA3380M2			CDA3380M2		(CAN) PROP WAS IN FOR BETA LIGHT FLICKERING, TORQUE FLUC, OIL PRESS FLUC. PROP HAD A SLOW PITCH CHANGE, OIL LEAK BETWEEN	 BASE OF CYL & HUB, GREASE LEAKAGE FROM ALL FOUR BLADE CLAMPS.  FOUND NR 4 BLADE OUT 0.6 DEG IN ANGLE.  LATCH ANGLES OUT	 ABOUT 0.7 DEGREES.  PROP BEING DISASSEMBLED, FOUND PISTON NUT, INSIDE, OUTSIDE BLADE CLAMP BOLTS WERE NOT TO REQUIRED T	ORQUE.  OUTER CLAMP BOLTS FOUND AT 40 TO 50 FT-LBS TORQUE, WHEN 65 FT-LBS IS SPEC.  IT WAS FOUND THAT OD OF BLADE SHANK 	HAD ALSO BEEN PAINTED.  NO ALIGNMENT TAPE FOUND ON BLADE SHANKS AND CLAMPS TO DETERMINE IF BLADES HAD SLIPPED IN CLAMPS.	  COULD HAVE BEEN CAUSE FOR BLADE ANGLES TO BE OUT OF SPECS.  JOINT BETWEEN  CYL AND HUB WAS FOUND TO BE LEAKING OIL.											6	C	P40EA	 
2005050300007	20050503	00007	NM  	2005	5	3	CA050316003      	1	20050314	G	5754		ARM             			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					SLAT	PUNCTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND HANDLING, MAINTENANCE DISCOVERED A SIGNIFICANT FUEL LEAK ON THE RT WING.  FUEL WAS RUNNING DOWN THE 	OB FLAP CANOE AND DRIPPING ONTO GROUND. AIRCRAFT WAS REMOVED FROM SERVICE AND PLACED INTO HANGAR FOR FURTHER INSPECTION 	AND FUEL DRAINING. AFTER OPENING THE WING TO LOCATE THE SOURCE OF THE LEAK, IT WAS DISCOVERED THAT THERE WAS A PUNCTURE 	HOLE IN THE HOUSING/BOX THAT THE SUPPORT ARMS FOR THE LEADING EDGE SLAT RUN INTO WHEN THE SLATS ARE RETRACTED. THIS HOLE	 ALLOWED FUEL TO EXIT THE FUEL TANK AND RUN UNDER THE WING. THIS IS CURRENTLY UNDER INVESTIGATION AND AN UPDATE WILL BE 	PROVIDED LATER.	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005041200007	20050412	00007	GL  	2005	4	12	CA050316004      	3	20050314	G	6111	S90AT2	BLADE           	MCAULY      		CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			668  			743155			743155		(CAN)  PROPELLER, W/O T 64571, RECEIVED FOR 10 YEAR OVERHAUL.  LAST OVERHAUL MAY 1996.  NOW 667.9 HOUR SINCE OVERHAUL. F	OUND BLADE S-90AT-2, SN B34101YS, CRACKED IN BLADE THREADS, FOUND WITH EDDY CURRENT.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
2005050300006	20050503	00006	GL  	2005	5	3	CA050316005      	3	20050314	G	6114	D4715	HUB             	MCAULY      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						767673			767673		(CAN) MCCAULEY PROPELLER D2A34C58, WORK ORDER NR T 65243 C-XX PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.  LAST OVERHAUL MA	R 1989. 5 YEAR CORROSION INSPECTION JUNE 1994, 259.9 HOURS SINCE OVERHAUL.  NOW 889.2 HOUR SINCE OVERHAUL.  FOUND HUB CR	ACKED IN ONE BLADE SOCKET THREAD ROOT, USING LPI FOUND BLADE RETENTION NUT PN C4902 CRACKED IN THREADS, USING LPI.  FOUN	D BLADE S-90AT-4, SN K98954YS, CRACKED IN BLADE THREADS, USING LPI, CONFIRMED WITH EDDY CURRENT.			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2005050300005	20050503	00005	CE  	2005	5	3	CA050316006      	1	20050315	G	3244	178K235	TIRE            	GOODYEAR    		LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					SIDEWALL	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						SEP871568					(CAN) LEAKS FOUND ON TIRE ON SIDEWALL. UNUSUAL CUT IN THE SHAPE OF AN (X). REMOVED AND REPLACED M/W ASSY.						2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005052300114	20050523	00114		2005	5	23	CA050316007      	1	20050310	G	2140	A23D04	CONTROL VALVE   	JANITROL    																HEATER REGULATOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AD 2004-25-16, HEATER REGULATOR/CONTROL VALVE, P/N A23D04, WEEPING FUEL. ACTION TAKEN- DISABLED AT PRESENT, PARTS 	ON ORDER.																		 
2005052300113	20050523	00113	EA  	2005	5	23	CA050317001      	2	20050314	G	7532	310082903	DIAPHRAGM       			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BLEED VALVE	RUPTURED        	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA								PCE24839			(CAN) ENGINE UNABLE TO ACHIEVE TAKEOFF POWER/TORQUE DUE TO BLEED VALVE NOT CLOSING FULLY.  COMPRESSOR BLEED VALVE DIAPHR	AM FOUND RUPTURED.					1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
2005050300004	20050503	00004	NM  	2005	5	3	CA050317002      	1	20050315	G	3230	485023	RELEASE CABLE   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A MLG AREA INSPECTION, EMERGENCY RELEASE CABLE P/N 48502-3 INSTALLED IN THE LT NACELLE WAS FOUND CHAFED.  I	NSPECTION OF THE CABLE IN THE RT NACELLE WAS COMPLETED WITHOUT ANY FINDINGS.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005050300003	20050503	00003	NE  	2005	5	3	CA050317003      	2	20050315	G	7230	3020159	RETAINING RING  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COMPRESSOR	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE19412			(CAN) A REVIEW OF AIRCRAFT RECORDS SHOWED THE ENGINE WAS ASSEMBLED USING SHROUD SEGMENTS WITH A RETAINING RING. THE ENGI	NE WAS BORESCOPE INSPECTED IAW SB 1631.   2 SEGMENTS WERE FOUND TO BE AXIALLY DISPLACED WITH COMPRESSOR TURBINE BLADE TI	P RUB ON ONE SEGMENT.   HOT SECTION COMPONENTS WERE REMOVED TO EMBODY SB 1627 AND SB 1628.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005052300112	20050523	00112	WP  	2005	5	23	CA050317004      	2	20050314	G	7321	8978017	FCU             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			CA								P54093			(CAN) CREW WAS UNABLE TO REDUCE PWR ON RT ENG ON DESCENT. SPEED LEVERS HIGH, POWER LEVERS AT FLIGHT IDLE, ENG REMAINED A	T 54 PERCENT TORQUE, CREW COULD NOT CONTROL ENG PWR, ELECTED TO SHUTDOWN ENG AS A PRECAUTION.  FCU WAS REPLACED, NORMAL 	ENG OPS WERE RESTORED.  REVIEW OF RECORDS FOR THIS ENG AND FCU REVEALED THAT THIS FCU HAD BEEN INSTALLED PRIOR TO FAILUR	E, FOLLOWING A REPAIR FOR SAME PROBLEM. THIS FCU WAS O/H MAY, 2004, REMOVED FOR REPAIR JANUARY, 2005, RE-INSTALLED ON AF	FECTED AC MARCH, 2005, FAILED MARCH, 2005. TEARDOWN REPORTS RECEIVED, INDICATED THAT FAULTS COULD NOT BE DUPLICATED AND 	WARRANTY WAS REFUSED.  (3) FAILURES IN 603 HRS ON THIS FCU, 2 OF WHICH RESULTED IN UNCONTROLLABILITY OF AFFECTED ENG.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2005050300002	20050503	00002	GL  	2005	5	3	CA050317005      	3	20050309	G	6114		HUB             			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									770963		(CAN) PROPELLER DISMANTLED FOR 10 YEAR O/H.   1-S90AT-4 BLADE, 1 C58 HUB AND 2-A3054 FERRULES U/S DUE TO SEVERE CORROSIO	N.  PROPELLER HAS EXCEEDED THE MANUFACTURERS RECOMENDED CALENDAR TBO BY 4 YRS.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2005050300001	20050503	00001	CE  	2005	5	3	CA050317006      	1	20050311	G	3240	195183	SHUTTLE VALVE   	BFGOODRICH  		CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					RT BRAKE ASSY	UNSERVICEABLE   	W				O				OTHER                   				P			NO WARNING INDICATION     			TX	TAXI/GRND HDL  	1			CA						2792					(CAN) UPON ROUTINE BRAKING DURING TAXI FROM RAMP TO RUNWAY, AC VEERED TO THE LT ON TAXIWAY. HARD PEDDLE(S) WHERE NOTED D	URING THE ATTEMPT TO STOP.  IN ORDER TO ENSURE DIRECTIONAL CONTROL AND BRING THE AC TO A COMPLETE STOP REVERSE THRUST WA	S UTILIZED.  THE AIRCRAFT WAS TOWED TO THE HANGAR FACILITY.   INSPECTED BRAKE SYSTEM INCLUDING TRANSDUCERS AND BRAKE ASS	EMBLIES. ATTEMPTED TO BLEED BRAKES AND FOUND EXTREMELY SMALL AMOUNTS OF FLUID COMING FROM RT BRAKE BLEED BLOCK (HARD RT 	PEDAL EVEN WHEN POWER BRAKE SYSTEM SHUT OFF).  REMOVED RT BRAKE SHUTTLE VALVE ASSEMBLY P/N 195-183 AND INSTALLED SERVICE	ABLE UNIT. BRAKE SYSTEM BLED. GROUND AND TAXI CHECKED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2005042700330	20050427	00330		2005	4	27	CA050317007      	4	20050316	G	2330	5401100003	VIDEO DISPLAY   			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) 7F SCREEN SMOKING, SYSTEM INOPERATIVE THE SEB AND VDU WERE REPLACED. THE OPERATOR IS FOLLOWING UP WITH THE OEM TO 	GET TSN /TSO AND TEARDOWN INFORMATION. NOTE: MFGR IS LIVE TV.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005052300111	20050523	00111	WP  	2005	5	23	CA050318001      	1	20050127	G	6320	C0061	SPLINE          	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					M/R GEARBOX	DAMAGED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA						0382					(CAN) VIBRATIONS AND A NOISE WAS DETECTED BY AN ENGINEER DURING SHUT DOWN. FURTHER INVESTIGATION REVEALED THE INPUT YOKE	 RETAINING NUT WAS LOOSE. THIS IN TURN DAMAGED THE INPUT SPLINES BEYOND LIMITS AND THE GEAR BOX WAS REPLACED. THE INPUT 	SEAL P /N C996-3 HAD BEEN REPLACED PRIOR AT 1082.8 TSO. WE HAVE CONCLUDED THE TORQUE OFTHE NUT WAS NOT CORRECT. TRAINING	 HAS SINCE BEEN CONDUCTED.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2005052300110	20050523	00110	EA  	2005	5	23	CA050318002      	1	20050127	G	5510	V201	STRUCTURE       			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	HORIZONTAL STAB	DEPARTED        	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN)  AC HAD ITS RT FINLET DEPART.  AC CONDUCTING REPEAT LATERAL STABILITY TESTING.  DEPARTURE WAS BOTH HEARD AND FELT 	BY PILOT AND TECH OBSERVER.  AC RETURNED TO ITS POINT OF DEPARTURE WITH NO ADVERSE STABILITY ISSUES.  UPON DETAILED INSP	, IT WAS DETERMINED THAT FWD FINLET ATTACHMENT BRACKET HAD FAILED.  A DESIGN IMPROVEMENT THAT ALLOWS AN INCREASE IN OVER	ALL STRENGTH OF ATTACHMENT POINTS.  THOUGHT THAT STRESSES IMPOSED ON FINLETS DURING REPEATED LATERAL STABILITY TESTING U	NDER FLIGHT PERMIT CONTRIBUTED TO FAILURE AND THAT DURING REGULAR OPERATING CONDITIONS THIS WOULD NOT OCCUR.  AN INCREAS	ED INSP SCHEDULE IS BEING INCLUDED IN THE GENERAL MAINT REQUIREMENTS OF AIRCRAFT EQUIPPED WITH FLOATS/FINLETS.	1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA	 
2005042700329	20050427	00329	NM  	2005	4	27	CA050318003      	1	20050314	G	3213	69186803	BOLT            	BOEING      		BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					RT MLG STRUT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2339					(CAN) DURING THE WALK-AROUND FOR A SERVICE CHECK, THE MECHANIC DISCOVERED THE HEAD OF THE BOLT BROKEN OFF AND MISSING FR	OM THE RT MAIN LANDING GEAR SIDE STRUT.  THIS BOLT ATTACHES THE SIDE STRUT UPPER AND LOWER SEGMENTS AT THE PIVOT.  THE B	OLT WAS REMOVED AND REPLACED.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005042700328	20050427	00328	SO  	2005	4	27	CA050318004      	2	20050317	G	8530	TIST712ACA	CYLINDER HEAD   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								291018R			(CAN) DURING A 100 HR INSPECTION, CYLINDER NR 4 WAS FOUND TO HAVE A LARGE CRACK FROM THE EXHAUST VALVE TO THE UPPER SPAR	K PLUG HOLE.  CYLINDER ASSY REMOVED AND REPLACED WITH NEW ECI CYLINDER ASSY OF SAME PART NR.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2005052300109	20050523	00109	CE  	2005	5	23	CA050320001      	1	20050312	G	5320	071349564	BRACKET         			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION SHEARED RIVETS WERE FOUND. THE RIVETS WERE REPLACED AND THE BRACKET WAS LPID IAW THE SRM. THE AI	RCRAFT WAS FLOWN TO A REPAIR FACILITY ON A FERRY FLIGHT PERMIT.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2005042700327	20050427	00327	NM  	2005	4	27	CA050321001      	1	20050313	G	3251	89891	LINK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG STEERING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ARRIVAL CREW REPORTED A SHIMMY IN THE NOSE WHEEL DURING LANDING. MAINTENANCE INSPECTED THE NOSE WHEELS AND TIRE	S WITH NO DEFECTS. INSPECTION OF THE NOSE GEAR STEERING SYSTEM FOUND A BROKEN NOSE WHEEL STEERING LINK. THERE WAS NO OTH	ER DAMAGE OR EVIDENCE OF WORN PARTS. THE LINK ASSEMBLY WAS REPLACED AND STEERING TESTED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005052300108	20050523	00108	EU  	2005	5	23	CA050321003      	1	20050310	G	5210	350A25003138	SUPPORT         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					REAR DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN AME WAS PERFORMING AN INSPECTION ON A DOOR PIN IAW AD F-2005-032 AND NOTICED THAT THE LT REAR SUPPORT BRACKET H	AD A CRACK FROM THE EDGE OF THE PART TO THE RADIUS NEAR THE RT UPPER ATTACHMENT HOLE. THE PART WAS REPLACED.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005042700326	20050427	00326	NE  	2005	4	27	CA050321004      	2	20050318	G	7230		COMPRESSOR      			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					NR 2 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								V0347			(CAN) THE CAPTAIN REPORTED HEARING A LOUD BANG FROM ENG NR 2 WITH INCREASED EGT, 2 RESTARTS WERE ATTEMPTED WITH NO SUCCE	SS AND THE FIRE HANDLE WAS PULLED (BOTTLES WERE NOT DISCHARGED). DAMAGE TO THE 3RD AND 4TH STAGE HIGH PRESSURE COMPRESSO	R WAS CONFIRMED.				2	L	7	2 	4F	4	F	RT	A28NM   	E311NE				 
2005052300107	20050523	00107	SW  	2005	5	23	CA050321005      	1	20050318	G	6320	206040156101	MAGNETIC SEAL   	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TRANSMISSION	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						BMC00337					(CAN) DURING CRUISE FLIGHT, FLUID WAS SEEN ON THE WINDOW BY THE LT REAR PASSENGER. THE PILOT REPORTED THE AIRCRAFT LOCAT	ION TO OUR RADIO OPERATOR AND LANDED TO SEE WHERE THE FLUID WAS COMING FROM. UPON INSPECTION, IT APPEARED THAT THE OIL W	AS COMING FROM THE REAR OF THE TRANSMISSION. AN AME WAS DISPATCHED WITH ANOTHER HELICOPTER AND CONFIRMED THE MAGNETIC SE	AL WAS LEAKING. THE SEAL AND O-RINGS WERE REPLACED AND THE HELICOPTER RETURNED TO SERVICE. NO OIL WAS SEEN DURING THE PR	EVIOUS PRE-FLIGHT INSPECTIONS TO INDICATE THE SEAL WAS STARTING TO LEAK. (TRANSMISSION OIL PRESSURE INDICATIONS WERE NOR	MAL DURING THE FLIGHT)	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005041200006	20050412	00006	WP  	2005	4	12	CA050321006      	2	20050304	G	7240	8939735	PLENUM          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P27081			(CAN) WHILE CONDUCTING AN ENGINE INSPECTION, A 2 INCH CRACK WAS DISCOVERED ON THE PLENUM NEAR THE BLEED AIR OUTLET.  THE	 ENGINE WAS REMOVED AND THE CRACKED PART REPLACED.  A FLEET WIDE ENGINE INSPECTION OF THE SAME DEFECT WAS CARRIED OUT.  	NO OTHER DEFECTS FOUND.				1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005041200043	20050412	00043	NE  	2005	4	12	CA050321007      	2	20050314	G	7200		ENGINE          			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					NR 2	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								113106			(CAN) AFTER TAKEOFF, CREW NOTICED NR2 ENG CHIP DETECTOR WARNING LITE ON, FOLLOWED SHORTLY BY NR 2 ENGINE OIL FILTER LITE	 (WARNING).  PILOT REDUCED THRUST ON NR2 ENGINE AND RETURNED TO AIRPORT.  MAINTENANCE INSPECTION DISCOVERED METAL ON CHI	P DETECTOR AND IN FILTER. ENGINE REPLACED. DAMAGED ENGINE SENT FOR REPAIR. STRIP REPORT TO FOLLOW .				2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2005041200042	20050412	00042	NE  	2005	4	12	CA050321008      	2	20050311	G	7320	252444993	FUEL CONTROL    			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA								PCE92604			(CAN) ENGINE POWER REDUCED TO IDLE ON TAKEOFF.  MAINTENANCE INSPECTION REVEALED FUEL CONTROL UNIT FAILURE.  REPLACED ENG	INE DRIVEN PUMP TO FUEL CONTROL COUPLING AND FUEL CONTROL UNIT.  GROUND RUN SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2005042700325	20050427	00325	EA  	2005	4	27	CA050321009      	2	20050319	G	7240	310926302	COMBUSTION LINER			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 3 INCH BURN THROUGH INNER LINER IN COMBUSTION AREA. ONE SMALL PINHOLE THROUGH PRIMARY SHROUD OR CAP.  THE CAP ON T	HE AFT FACE OF THE UNIT HAD CRACKED ABOUT 120 DEGREES AROUND THE CIRCUMFERENCE.  THE BURN THROUGH WAS VISIBLE WITH THE B	OROSCOPE INSPECTION HOWEVER THE CRACK ON THE AFT FACE WAS ONLY VISIBLE WITH THE LED REMOVED.  SUSPECT THAT A BAD FUEL NO	ZZLE WAS THE CAUSE OF THE BURN THROUGH.  HOT GASES ENTERING THE VOID BETWEEN THE PRIMARY SHROUD/CAP THROUGH THE BURN HOL	E IN THE INNER LINER MAY HAVE BEEN RESPONSIBLE FOR THE CRACKING.		1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
2005052300106	20050523	00106	SW  	2005	5	23	CA050322001      	1	20050321	G	7714	SL76121	SHAFT           			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	TACHOMETER	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TACHOMETER CABLE DRIVE SEPARATED FROM OUTER SHAFT HOUSING, AND TURNING BELOW TRUE ENGINE RPM WHICH IN TURN GAVE FA	LSE INDICATION.					1	L	7	1 	3O	3	O		2A3     	E286	5	C	P25EA	 
2005042700324	20050427	00324	EU  	2005	4	27	CA050322002      	1	20050321	G	2822	TPZA10063T251V	SEAL            	TMECA       		SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					BOOST PUMP	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						919B					(CAN) WHILE PERFORMING POST FLIGHT DAILY INSPECTION , TURNED ON BOOSTER PUMP AND NOTICED FUEL LEAKING FROM ENGINE DRAIN.	  FOLLOWED LEAK TO SEAL DRAIN OF HIGH PRESSURE ENGINE FUEL PUMP.  WHEN BOOST PUMP TURNED (OFF) LEAK STOPPED.  LEAK WAS P	RODUCING 6 ML PER MINUTE.   DID NOT SUSPECT HP PUMP WAS LEAKING FUEL IN FLIGHT AS NO FUEL DISCOVERED ON TARMAC AFTER AIR	CRAFT LANDED AND NO FUEL RESIDUE ON SIDE OF FUSELAGE OR TAILBOOM.  PUMP SEAL WILL BE REPLACED ONCE PARTS ARE RECEIVED.			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005052300105	20050523	00105	CE  	2005	5	23	CA050322003      	1	20050318	G	5510	04320049	BRACKET         	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10278								(CAN) DURING INSP WHEN PRESSURE WAS APPLIED TO THE HORIZONTAL STAB TIP AN UNUSUAL SOUND WAS HEARD.  INVESTIGATION REVEAL	ED THE CRACKED BRACKET.  REINFORCEMENT P/N 0432001-15 AND SPAR P/N 0432001-56 WERE ALSO FOUND CRACKED.  CESSNA SEB03-06 	REFERS.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005042700323	20050427	00323	NE  	2005	4	27	CA050322004      	2	20050312	G	7510	601970977	ANTI-ICE VALVE  		601970977   	CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	CLOSED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE ENGINE ANTI-ICE WAS SELECTED ON THE NR 2 ENGINE BUT VALVE WOULD NOT OPEN.  UPON RETURNING TO BASE VALVE 	WAS REPLACED AND TESTED FUNCTIONAL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005052300104	20050523	00104	CE  	2005	5	23	CA050322005      	1	20050321	G	5270	1013644662	SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	PAX DOOR	FALSE ACTIVATION	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI TO DEPART, THE MAIN CABIN DOOR WARNING LIGHT ILLUMINATED. THE DOOR WAS CHECKED VISUALLY AND CONFIRMED 	CLOSED BUT THE DOOR ANNUNCIATOR WOULD NOT EXTINGUISH.  DUE UN-MEL-ABLE, THE AIRCRAFT WAS FERRIED TO MAINTENANCE FACILITY	 AND THE SWITCH WAS REPLACED FOR PRECAUTIONARY REASONS.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005052300103	20050523	00103		2005	5	23	CA050322006      	4	20050322	G	2562	PS400010	ELT             																	CABIN	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ELT RECERTIFICATION THE G SWITCH FUNCTION FAILED THE REQUIRED G FORCE TEST.  WE HAVE SINCE FOUND SEVERAL	 G SWITCH FAILURES. THE ELT'S WERE SENT BACK TO THE MFG FOR REPAIR.																		 
2005052300102	20050523	00102	SW  	2005	5	23	CA050322007      	1	20050321	G	3250		STEERING SYS    			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NOSE WHEEL	WARNING LIGHT   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL THE PILOT DISCONNECTED THE NOSE WHEEL STEERING.  THE NOSE WHEEL STEERING FAIL LIGHT CAME ON YE	T DID NOT FADE OUT LIKE IT SHOULD.  THE TAKEOFF WAS ABORTED AND THE AIRCRAFT TAXIED BACK TO THE TERMINAL.  ON THE WAY BA	CK TOTHE TERMINAL THE LIGHT WENT OUT.  THE AIRCRAFT WAS INSPECTED AND MAINTENANCE COULD NOT DUPLICATE THE DEFECT.  NO FU	RTHER INCIDENTS HAVE BEEN ENCOUNTERED.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005042700322	20050427	00322	NM  	2005	4	27	CA050322008      	1	20050318	G	5610		WIRE            			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					L2 WINDOW	ARCED           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CAPT L2 SLIDING WINDOW POWER CORD ARCING AND FILLING THE COCKPIT WITH SMOKE.  WINDOW HEAT SELECTED OFF AND BREAKER	 PULLED. POWER CORD DISCONNECTED FROM RECEPTICLE. REMOVED AND REPLACED THE CAPT L2 SLIDING WINDOW, SYSTEM TESTED SERVICE	ABLE, AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005052300101	20050523	00101	NE  	2005	5	23	CA050322009      	2	20050321	G	7324	39439611	FLOW DIVIDER    			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					ENGINE FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND RUN, FUEL WAS OBSERVED TO BE LEAKING FROM THE RT AFT ENGINE AREA. THE PROBLEM WAS FOUND TO BE A LEAK	ING FUEL FLOW DIVIDER. THE PART WAS REPLACED, A SATISFACTORY GROUND RUN AND LEAK CHECK WAS CARRIED OUT AND THE AIRCRAFT 	WAS RETURNED TO SERVICE.				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005052300100	20050523	00100	NE  	2005	5	23	CA050323001      	1	20050307	G	7931	7645001078120	TRANSDUCER      			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					PRESSURE	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) PRESSURE TRANSDUCER FAILED, GIVING A HIGH READING ON INDICATOR.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005042700321	20050427	00321	NE  	2005	4	27	CA050323002      	2	20050317	G	7200		ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  						OUT OF LIMITS   	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA								9322			(CAN) THE ENGINE HAS BEEN INSTALLED AFTER OVERHAUL, AND ON GROUND RUN HIGH VIBRATION ON THE FORWARD POINT WITHIN LIMIT B	UT ABNORMALLY HIGH. AFTER CONTACTING THE OVERHAUL FACILITIES, WE DID SOME TESTS FOR RESULT. THE VIBRATION WENT UP CLOSER	 TO THE LIMIT.  AFTER THE VISIT BY A OVERHAUL FACILITIES TECH, IT WAS DETERMINED THAT THE ENGINE WAS OUT OF LIMIT AND WA	S REMOVED AND SENT BACK TO THE OVERHAUL SHOP.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005042700320	20050427	00320	EA  	2005	4	27	CA050323003      	2	20050314	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			23502					86034			(CAN) FOUND BETA CNTRL SYS WAS JAMMED.  BETA CNTRL SLEEVE HAD WORN AGAINST PROPSHAFT DIA. RGB WAS REBUILT, IDENTICAL FAI	LURE IN TEST CELL.  RGB WAS REBUILT, TESTED, RETURNED. NOT INSTALLED BUT RETURNED BECAUSE OF LOOSE MOUNT RING ON RGB. CO	RRECTED, ENG TESTED OK IN TEST CELL BEFORE BEING RETURNED TO OPER. OPER USED ENG FOR SHORT PERIOD UNTIL METAL WAS FOUND 	ON RGB CHIP DETECTOR AND IN OIL FILTER.  ENG LOST ALL ITS OIL FROM IMPROPERLY SECURED FILTER BOWL, WAS EXPOSED TO PERIOD	 OF WINDMILLING OPERATION WITHOUT OIL.  ENG HAS BEEN RETURNED TO O/H FACILITY. SOURCE OF METAL IN OIL WAS DETERMINED TO 	BE FROM ABRASIVE CONTACT WEAR BETWEEN BETA CNTRL SLEEVE, PROP SHAFT. NO EFFECTS NOTED FROM WINDMILLING WITH LIMITED OIL.						4	T			E4EA				 
2005052300099	20050523	00099	NE  	2005	5	23	CA050323004      	2	20050303	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  		MAKING METAL    	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								19196			(CAN) IN CRUISE THE ENGINE EXPERIENCED A POWER LOSS ACCOMPANIED BY A GEARBOX CHIP DETECTOR INDICATION. THE PILOT CARRIED	 OUT AN EMERGENCY LANDING ON A ROAD-WAY WHICH RESULTED IN DAMAGE TO THE AIRCRAFT.   MFG WILL MONITOR THE INVESTIGATION O	F THIS INCIDENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005052300098	20050523	00098	NE  	2005	5	23	CA050323005      	2	20050307	G	7310	31B186501	LINE            			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305B      	52128	NE  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FUEL WAS FOUND LEAKING FROM A CRACKED HMU-TO-FUEL FLOW TRANSMITTER LINE.  THE ENGINE HAD PREVIOU	SLY EXPERIENCED AN AIRFRAME STARTER-GENERATOR FAILURE.					2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2005052300097	20050523	00097	NE  	2005	5	23	CA050323006      	2	20050228	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		AP	APPROACH       	1			CA								121170			(CAN) ON APPROACH THE ENGINE EXPERIENCED AN UNCOMMANDED POWER (TORQUE) REDUCTION ACCOMPANIED BY A LOUD NOISE AND LOSS OF	 ENGINE OIL PRESSURE.  THE CREW SECURED THE ENGINE IN FLIGHT AND ACCOMPLISHED A SINGLE-ENGINE LANDING.  SUBSEQUENT INSPE	CTION REVEALED DAMAGE TO THE TURBO MACHINE.  MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CA	USE ONCE DETERMINED.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005052300096	20050523	00096	EA  	2005	5	23	CA050323007      	2	20050214	G	7200		ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  						FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA								51754			(CAN) ON TAKE-OFF ROLL, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY HIGH/INCREASING TURBINE TEM	PERATURE.  THE PILOT ABORTED TAKE-OFF AND SECURED THE ENGINE.  SUBSEQUENT INSPECTION REVEALLED HOT SECTION DISTRESS.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005052300095	20050523	00095	GL  	2005	5	23	CA050323008      	3	20050314	G	6110	1A103TCM695	PROPELLER       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PROPELLER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER INCORRECTLY INSTALLED IAW AD2003-12-05 / SB 221C.  BOLTS INCORRECT AND SPACER MISSING.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005052300094	20050523	00094	NE  	2005	5	23	CA050323009      	2	20050322	G	7322	NAR9B	CARBURETOR      			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE FLIGHT CREW REPORTED THAT THE ENGINE WAS RUNNING ROUGH AT HIGH POWER SETTINGS AND RETURNED TO POINT OF ORIGIN.	  THE CARBURETOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  THERE WAS NO EVIDENCE OF FUEL CONTAMINATION IN 	THE FUEL TANKS, FUEL FILTER, FINGER SCREEN OR CARBURETOR BOWL.  A TEARDOWN REPORT HAS BEEN REQUESTED.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005042700319	20050427	00319	EA  	2005	4	27	CA050323010      	1	20050321	G	5540	C6CF10221	BRACKET         			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	CORRODED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING THE FIVE YEAR CORROSION CHECK, BOTH RUDDER TORQUE TUBE ATTACH BRACKETS WERE FOUND TO BE HEAVILY RUSTED FROM	 THE INSIDE. THERE WAS NO EVIDENCE OF CORROSION PROOFING HAVING BEEN INSTALLED ON THE INSIDE OF THE BRACKETS.  AIRCRAFT 	IS OPERATED IN A CORROSIVE ENVIRONMENT.				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005052300093	20050523	00093	EU  	2005	5	23	CA050323011      	1	20050323	G	2913	POLYV597K4	DRIVE BELT      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A DAILY INSPECTION AME DISCOVERED A CRACK IN THE HYDRAULIC PUMP DRIVE BELT.  THE CRACK APPROXIMATELY 1-1.5 	INCH LONG WAS LOCATED BETWEEN THE V-GROOVE SEGMENTS.  (THE CRACK SEPARATES ALMOST COMPLETELY WHEN BELT IS PINCHED BY HAN	D IN A FOLDING MANNER  WHITISH DISCOLORATION WAS ALSO NOTICED ON EITHER SIDE OF THE DAMAGED AREA (SIGN OF FATIGUE).  THE	 BELT OPERATED FOR 325.4 HRS WITH BELT TENSION ORIGINALLY SPECIFIED BY MFG, AND THEN FURTHER 347 HRS AFTER THE BELT TENS	ION WAS REDUCED IAW ASB 63.00.14.		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005052300092	20050523	00092	CE  	2005	5	23	CA050323012      	1	20050303	G	5740	501200734	FITTING         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20655								(CAN) CRACK DISCOVERED IN OB FITTING RADIUS.						1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005052300091	20050523	00091	EU  	2005	5	23	CA050324001      	1	20050322	G	2780		CONTROL SYSTEM  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LE FLAPS	INOPERATIVE     	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, THE FLAPS WERE SELECTED UP, (FLAPS) CAUTION ILLUMINATED, AND FLAP OPERATION STOPPED. AIRCRAFT RE	TURNED FOR LANDING, FLAP SYSTEM INSPECTED FOR OBVIOUS DAMAGE, AND FLAPS MEASURED FOR POSSIBLE ASYMMETRY AND FOUND SATISF	ACTORY.  FLAP GROUND RESET PERFORMED AND NO FURTHER PROBLEMS NOTED.  AFTER RETURNING TO BASE, FLAP CODES SHOWED E210 (FL	AP ASYMMETRY CENTER/CENTER).  FLAP ASYMMETRY AGAIN MEASURED SATISFACTORY, AND AIRCRAFT RETURNED TO SERVICE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005052300090	20050523	00090	EA  	2005	5	23	CA050324002      	1	20050102	G	3260	831605	SENSOR          			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30015	NE  					MLG	INOPERATIVE     	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) ON JANUARY 02, 2005, AFTER TAKE OFF THE LANDING GEAR WERE SELECTED UP (RETRACT). LANDING GEAR REMAINED ON EXTENDED	 POSITION. AIRCRAFT RETURNED TO DEPARTURE AND LANDED SAFELY WITH NO INCIDENCE. POST FLIGHT INSPECTION REVEALED NO MECHAN	ICAL DAMAGE. LT AND RT PROXIMITY SENSORS WERE FOUND DEFECTIVE. NLG PROX SENSORS AND LANDING GEAR CONTROL UNIT WERE ALSO 	REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005052300089	20050523	00089	CE  	2005	5	23	CA050324004      	1	20050323	G	7921	9919330726361	TUBE            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					OIL COOLER	CHAFED          	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) AFTER CREW REPORTED A LOW OIL PRESSURE ON LT ENGINE. THE MAINTENANCE PERSONNEL FOUND AFTER INVESTIGATION THAT THE 	OIL COOLER TUBE ASSEMBLY WAS PUNCTURED/CHAFED.  ONE OF THE HOLDING CLAMP`S PROTECTIVE MATERIAL WAS COMPLETELY CHAFED (IN	SIDE PORTION) AND WITH TIME, CHAFED THROUGH THE TUBE. THE TUBE ASSEMBLY WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVIC	E.			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005041200003	20050412	00003	SO  	2005	4	12	CA050324006      	2	20050315	G	8520	639196	COUNTERWEIGHT   	CONT        		CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	CRANKSHAFT	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA						H25921N					(CAN) ROLLER RETAINER AND SNAP RING CAME OUT OF CLUT, RELEASING ROLLER IN 5TH ORDER CWT. (NO DAMAGE TO PARTS, POSSIBILIT	Y WAS NOT INSTALLED CORRECTLY.) ROLLER MIGRATED TO REAR OF ENGINE AND JAMMED BETWEEN 6TH ORDER CWT AND ENGINE CASE STOPP	ING ENGINE.  CRANKSHAFT NRPLE AT NR2 ,AOM KPIRMA, FRP, SUDDEN STOPPAGE.				1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2005042700318	20050427	00318	SO  	2005	4	27	CA050324008      	2	20050316	G	8520	654853B	PISTON          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300C       	17022	SO  					ENGINE	ERODED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) TOP LAND OF PISTON ERODED AWAY AND HOLE BURNED THROUGH PISTON BELOW 3RD RING FROM HEAD OR TOP OF PISTON.  PISTON E	XPANDED FROM EXCESSIVE HEAT AND SCUFFED AGAINST CYLINDER BARREL, SMEARING SKIRT AND SCORING BARREL. CAUSE APPEARS TO BE 	DETONATION. PARTS CORRECT FOR APPLICATION, TIMING SET CORRECT, MAGNETOS INSPECTED. NO MECHANICAL DISCREPANCIES FOUND. FU	EL WAS 100CC BUT SAMPLE TAKEN FROM CARB HAS A			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005052300085	20050523	00085	EA  	2005	5	23	CA050324010      	1	20050324	G	5551	215231096	FITTING         			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	HORIZONTAL STAB	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SUSPECTED CRACK FOUND ON VISUAL INSPECTION OF THE STAB ATTACHEMENT FITTING.  DEFECT INDICATIONS HAS BEEN CONFIRMED	 BY EDDY CURRENT INSPECTION. FITTING REPLACED AND AIRCRAFT RETURN TO SERVICE.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2005052300084	20050523	00084	EU  	2005	5	23	CA050324011      	1	20050320	G	5210	80155104901	CABLE           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	DOOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							1057				(CAN) THE CABIN LOWER DOOR'S CABLE ASSEMBLIES WERE FOUND WORN AND THEY WERE REPLACED.						1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
2005052300083	20050523	00083	SW  	2005	5	23	CA050328001      	1	20050310	G	6210	407015001135	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) M/R BLADE EXHIBITS CRACKS IN THE NICKEL PLATING ON THE LEADING EDGES (EROSION STRIP).						1	G	7	1 	3U			O	H2SW    					 
2005052300082	20050523	00082	GL  	2005	5	23	CA050328002      	2	20050323	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								CAT44268			(CAN) COMBUSTION LINER FOUND CRACKED WHEN REMOVED DURING UNRELATED SCHEDULED MAINTENANCE. NO CRACKS ALLOWED IN SUBJECT A	REA. THIS IS AN ON GOING PROBLEM WITH THIS PART.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005042700317	20050427	00317	EA  	2005	4	27	CA050328003      	1	20050323	G	2797	CSP1352	FAIRLEAD        			DHAV  	DHC6  	DHC6300     	2802606	EA  										RT WING ROOT	CHAFED          	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PRESUMED THAT RH AILERON CABLE BROKE DUE TO CHAFFING ON A THE FAIRLEAD. MORE DETAILS WILL FOLLOW ON REVISION 1 OF 	THE INCIDENT REPORT FILED BY AIR GUYANE SP WITH THEIR LOCAL AVIATION AUTHORITY.					1	H	7	2 	3T			RT	A9EA    					 
2005052300081	20050523	00081	GL  	2005	5	23	CA050329001      	1	20050310	G	2750	1952642	UNIVERSAL JOINT 			AMTR  	2     	2           	       	GL  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	12D	12D40       	NE  	RT FLAP	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE 2 UNIVERSAL JOINTS CONNECTING CENTER SECTION FLAP TO RT FLAP WORN.  THE WORN JOINTS CAUSED THE 2 SETS OF FLAP 	ROLLERS BOTH IB AND OB OF THE UNIVERSALS TO ALSO BE AFFECTED.  ALL ABOVE ITEMS WERE REPLACED WITH NEW PARTS.					1	L	7	1 	3O	3	R		EXPA1L71	5E2	5	C	P257	 
2005041200065	20050412	00065	NM  	2005	4	12	CA050329002      	1	20050328	G	5610	58935733	WINDOW          			BOEING	737   	737522      	138449F	NM  	GE    	CFM56 	CFM56*      	13802	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE PILOTS NR 4 WINDSHIELD (EYEBROW) APPEARED TO SHATTER.  THERE WAS NO LOSS OF PRESSURIZATION.  THE 	LANDING WAS CONTINUED WITHOUT PROBLEM.  ON INVESTIGATION, THE GLASS LAYER SEEMS TO HAVE FAILED.  THE OUTER LAYERS WERE I	NTACT BUT THE INNER LAYER APPEARS TO HAVE SHATTERED.  THE PILOTS DID NOT SEE ANY IMPACT NOR WAS THERE EVIDENCE OF A BIRD	 STRIKE.  THE WINDOW WAS REPLACED WITH A SERVICEABLE UNIT.			2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005041200002	20050412	00002	NM  	2005	4	12	CA050329003      	1	20050327	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			63228								(CAN) DURING ROUTINE MAINTENANCE A CRACK WAS FOUND IN THE FUSELAGE AT STATION 759.5 BELOW STRINGER 18L.  HFEC WAS CARRIE	D OUT TO VERIFY THE CRACK AND DETERMINE THE EXTENT.  IT WAS DETERMINED THAT THE CRACK WAS APPROX 1.4 INCHES LONG.  THE C	RACK WAS REPAIRED IAW SRM 53-30-3 PAGE 284 FIG. 48 SHEET 32 DETAIL X.				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005052300080	20050523	00080	NE  	2005	5	23	CA050329004      	2	20050201	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								123083			(CAN) DURING CRUISE, ENGINE TORQUE INCREASED UNCOMMANDED, ACCOMPANIED BY A LOW OIL PRESSURE WARNING ANNUNCIATION WITH OI	L PRESSURE DECREASING TO ZERO.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND SUBSEQUENTLY REMOVED FOR INVESTIGATION.  MFG WILL 	INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005052300078	20050523	00078	NE  	2005	5	23	CA050329005      	2	20050314	G	7200		ENGINE          								PWA   	PT6   	PT6A36      	52043	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA								38169			(CAN) DURING DESCENT THE ENGINE WAS REPORTED AS NOT RESPONDING TO THROTTLE INPUT.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  T	HE ENGINE WAS INSPECTED AND INSTALLED ON A SECOND AIRCRAFT.  DURING A SUBSEQUENT FLIGHT, THE PROBLEM RE-OCCURRED WITH TH	E ENGINE AGAIN BEING SHUTDOWN IN FLIGHT.  MFG WILL MONITOR THE INVESTIGATION OF THESE EVENTS AND WILL ADVISE OF ROOT CAU	SE ONCE ESTABLISHED.								4	T			E4EA				 
2005052300079	20050523	00079	SO  	2005	5	23	CA050329006      	1	20050114	G	5711	6207007	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON ANNUAL INSPECTION, A SKIN DEFORMITY WAS FOUND ON UPPER SPAR OB OF FUEL CELL.  RIVETS ATTACHING SKIN TO SPAR W	ERE DRILLED OUT EXPOSING SEVERE CORROSION OF SPAR CAP.  IT WAS DETERMINED FROM THE EXTENT OF CORROSION THE SPAR WAS UNSE	RVICEABLE.  SUSPECTED THAT THE ROAD SALT CONTAMINATE FROM THE NEAR BY HIGHWAY WAS A FACTOR IN THE CAUSE OF THIS CORROSIO	N.			1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2005052300076	20050523	00076	EA  	2005	5	23	CA050329007      	2	20050313	G	7314		DRIVE ASSY      			PILATS	PC6   	PC6         	7090102	EU  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL PUMP	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FRENCH AUTHORITIES HAVE REPORTED AN INFLT SHUTDOWN WITH INDICATIONS OF A FUEL PUMP DRIVE MALFUNCTION.						1	H	7	1 	3O	4	T		7A15    	E4EA	6	C	P15EA	 
2005052300077	20050523	00077	NE  	2005	5	23	CA050329008      	2	20050317	G	7200		ENGINE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       	 	NE  						MALFUNCTIONED   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								115283			(CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER IN CRUISE. DURING TAKE-OFF ROLL ON A PREVIOUS FLIGHT, THE ENGINE DID NO	T REPOND TO THROTTLE INPUT.  MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLIS	HED.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2005052300073	20050523	00073	NE  	2005	5	23	CA050329009      	2	20050316	G	7200		ENGINE          			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								AM0039			(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN.  THE FUEL CONTROL (MFC) AND FUEL PUMP WERE REMOVED F	OR INVESTIGATION.  MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005052300074	20050523	00074	EA  	2005	5	23	CA050329010      	2	20050321	G	7323	101250003	EGU             			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6B36      	52043	EA  					ENGINE	OSCILLATES      	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) DURING AIRCRAFT DELIVERY FLIGHT, THE CREW REPORTED ROTOR OSCILLATION.  THE ENGINE'S GOVERNING UNIT (EGU) WAS SUBSE	QUENTLY REPLACED.  MFG WILL MONITOR INVESTIGATION OF THE SUSPECT EGU AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	G	7	2 	3U	4	U		H7EU    	E4EA				 
2005052300075	20050523	00075	GL  	2005	5	23	CA050329011      	1	20050309	G	2710	5252315	ROD             			AMTR  	2     	2           	       	GL  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	12D	12D40       	NE  	LT AILERON	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) LT AILERON PUSH PULL ROD REMOVED TO CLEAN CORROSION FROM STEEL ENDS, AFTER CLEANING INSPECTION REVEALED A CRACK PR	OGRESSING FROM THE INNER RIVET.  SUSPECT CRACK FROM AGE HARDENING OF COMPONENT, APPROXIMATELY 61 YEARS OF AGE.					1	L	7	1 	3O	3	R		EXPA1L71	5E2	5	C	P257	 
2005052300071	20050523	00071	CE  	2005	5	23	CA050329012      	1	20050305	G	2432	CB2411	BATTERY         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	MASTER	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B	H	J	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF FROM AIRPORT THE PILOT SMELLED THE BATTERY OVERCHARGING, HE NOTICED THE ALTERNATOR AMPMETER CHARGING	 AT APPROXIMATELY 60 AMPS.  THE PILOT TURNED OFF THE ALTERNATOR AND MASTER SWITCHES AND PROCEEDED INTO THE AIRPORT USING	 HIS CELL PHONE AS COMMUNICATION WITH THE TOWER. THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND FOUND TO HAVE A INTERNAL 	DEAD SHORT WHEN PLACED ON A CHARGER.			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2005052300072	20050523	00072	SO  	2005	5	23	CA050329013      	1	20050328	G	3231	46357000001	BRACKET         			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT MAIN LANDING GEAR IB GEAR DOOR FORWARD AND AFT UPPER BRACKETS WERE FOUND CRACKED.  BOTH BRACKETS REPLACED.						1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2005052300069	20050523	00069	WP  	2005	5	23	CA050329014      	1	20050222	G	5610	34031103078	WINDOW          			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60117    	NE  	COCKPIT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			D	C	J	INFLIGHT SEPARATION       	F.O.D.                    	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) THE OPERATOR HAS FILED AN INCIDENT REPORT WITH THE FAA. WINDOWPANE FAILURE AT CRUISE ALTITUDE OF 21,000 FT, WHICH 	CAUSED FOD DAMAGE TO THE RT ENGINE.  THE WINDOW WAS LAST INSPECTED FEB 14 2005.  REASON: COMPLETE FAILURE OF THE VINYL L	INER AT THE EDGE OF THE METAL INSERT.  INSPECTION OF THE WINDOWPANE REMAINS, INDICATES THE WINDOW WAS P/N 340-3110307-8.	 THE WINDOW HAS BEEN SUPERSEDED BY A10.			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2005052300070	20050523	00070	GL  	2005	5	23	CA050329015      	2	20050322	G	7200	250954106	SAFETY VALVE    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AERONAUTICAL ACCESSORIES PC SAFETY VALVE KIT, STC SE327AT, STA SE93-4.  UPON REMOVAL FOR OVERHAUL THE ACTUATING KN	OB WAS FOUND SHEARED AND HELD IN PLACE BY THE RETAINING CLIP. THE KNOB WOULD NOT HAVE FALLEN HOWEVER THE VALVE ITSELF WA	S NO LONGER HELD IN PLACE OTHER THAN BY FRICTION. THE VALVE COULD HAVE FALLEN OUT CAUSING A SUBSTANTIAL AIR LEAK.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005052300067	20050523	00067	NE  	2005	5	23	CA050330001      	3	20050328	G	6110	31028851	BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROP SHAFT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENG WAS REMOVED FROM AC DUE TO EXCESS RADIAL PLAY FOUND AT PROP SHAFT.  OIL LEAK WAS EVIDENT FROM PROP SHAFT SEAL 	AREA.  MOUNTED DIAL IND ON ENG,  MEASURED APPROX, 0.010 TO 0.018 INCH PROP SHAFT RADIAL PLAY.  THIS WAS SECOND SEAL INST	ALLED, ENG STILL LEAKING. EXCESS RADIAL PLAY AT BRG WAS LIKELY WEARING OUT SEALS AT ACCELERATED RATE CAUSING OIL LEAKAGE	 SEEN FROM PROP SHAFT AREA. INSTALLED DIAL IND TO MEASURE SIDE TO SIDE RADIAL PLAY.   BRG MEASURED AT 0.012 IN, 2 OTHER 	BEARINGS WERE INSTALLED, CKD USING SAME DIAL IND. BOTH BRGS MEASURED APPROX, 0.006 IN RADIAL PLAY. THIS CONFIRMED HIGHER	 THAN NML RADIAL PLAY WAS FOUND WITH PROP SHAFT BRG. REMOVED PROP SHAFT BRG, SENT FOR ENGINEERING EVALUATION.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005052300068	20050523	00068	NE  	2005	5	23	CA050330002      	2	20050308	G	8520	16475	CRANKCASE       			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								JP206356			(CAN) ENGINE HAD OIL LEAK WHICH WAS DETERMINED TO BE COMING FROM CRACK ON THE FRONT CRANKCASE BETWEEN NR 3 AND 4 CYLINDE	R BASE AREA. THIS CRACK WAS ABOUT 3.5 INCHES LONG ORGINATING FROM CRANKCASE THROUGH BOLT UP TOWARDS THE CYLINDER BASES.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206	 
2005041200064	20050412	00064		2005	4	12	CA050330003      	4	20050320	G	3460	7003974730	COMPUTER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	FLT MANAGE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40034								(CAN) FLIGHT GUIDANCE COMPUTER FAILED DUE TO HARDWARE INTERNAL FAILURE. WHEN AIRCRAFT POWER WAS ATTACHED AND SELECTED ON	: TO TROUBLE SHOOT YAW/DAMPER FAIL SNAG, MECHANICS NOTICED RED GLOW FROM INSIDE BOX AND FAINT SMOKE/MICARTA SMELL INDICA	TING OVERHEAT CONDITION - FLIGHT GUIDANCE COMPUTER REPLACED WITH NO FURTHER INCIDENT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005052300066	20050523	00066	EU  	2005	5	23	CA050331001      	1	20050317	G	2140	350A72072102	HOSE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HEATER	COLLAPSED       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) HOSE COLLAPSED IN FLIGHT FILLING CABIN WITH INSULATION PARTICLES AND DUST.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005052300064	20050523	00064	GL  	2005	5	23	CA050331002      	3	20050328	G	6111		BLADE           			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						812065			812065		(CAN) EXCESSIVE LT/RT MOVEMENT ON ONE PROP BLADE DUE TO WORN BUSHINGS ON LINK BETWEEN BLADE AND PITCH CONTROL.  LINK WAS	 REPLACED.					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	5	C	P60GL	 
2005052300063	20050523	00063	NM  	2005	5	23	CA050401001      	1	20050331	G	2720	85710012006	SUPPORT         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RUDDER PEDALS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE, A CHAFE WAS FOUND ON THE F/O'S AND CAPTAINS RT RUDDER SUPPORT TUBE (P/N85710012-006) R	EF IPC 27-20-00, FIG 10, ITEM 230.  DAMAGE CAUSED FROM CONTACT WITH SCREW IN TRIM PANEL REFERENCE IPC 27-20-00 FIG. 55 I	TEM 90 (TOP SCREW).  DAMAGE MEASURED TO .005. DEFECT NOTED WHEN CARRYING OUT TRAVELCHECKS FOR RII.  CONTACT WILL ONLY OC	CUR WHEN PEDALS ADJUSTED TO FULL AFT POSITION ND FULL LT INPUT TO RUDDER.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005052300060	20050523	00060	EU  	2005	5	23	CA050401002      	1	20050401	G	3230		LANDING GEAR    			AIRBUS	A321  	A321211     	3930370	EU  	CFMINT	CFM56 	CFM565B5    	 	NE  					MAINS	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) LANDING GEAR WOULD NOT EXTEND ON FIRST ATTEMPT.  GEAR HANDLE RECYCLED, NO FIX ALTERNATE GEAR EXTENTION OPERATE NOR	MALLY. BITE TEST ALL CHECKED OK. LG CIU 1 AND 2 INTERCHANGED NO FIX.  MTCE ADVISED AND TROUBLESHOT THE SNAG, ACFT ON JAC	KS.				2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2005052300061	20050523	00061	GL  	2005	5	23	CA050401003      	1	20050401	G	2560		INERTIA REEL    			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	SHOULDER BELT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION IT WAS FOUND, WHILE CHECKING THE SHOULDER HARNESS OPERATION, THAT THE REEL MECHANISM IN 	THE LT SHOULDER HARNESS ASSY WAS DEFECTIVE AND WAS NOT ALLOWING THE BELT TO RETRACT.  AFTER REMOVAL, THE BELT WAS FINALL	Y RETRACTED AFTER SHAKING THE LOOSE NYLON PIECES THAT HAD BROKEN INSIDE THE REEL.  IT WAS THEN NOTED THAT THE BELT WOULD	 GO IN AND OUT AS IT NORMALLY DOES BUT THE INERTIA REEL WAS NO LONGER LOCKING. BELT ASSY. WAS REPLACED WITH NEW UNIT AND	 RETURNED FOR WARRANTY.		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2005052300058	20050523	00058		2005	5	23	CA050401004      	4	20050331	G	3460	27375001107	DISPLAY         			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					COCKPIT	INOPERATIVE     	W				B	H			EMER. DESCENT           	DEACTIVATE SYST/CIRCUITS			H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, TESTSCREEN NR1 (TOP SCREEN) OF IIDS DISPLAY UNIT WAS LOST. THE PILOT SELECTED BOTTOMED DISPLAY TO C	OMPOSITE MODE. WITHIN SECONDS , SMOKE STARTED TO APPEAR FROM UNDER BOTTOM OF IIDS DISPLAY UNIT.  NO BREAKER POPOUT.  PIL	OT STARTED EMERGENCY DESCENT AND TRANSMITTED INTENTIONS TO GROUND PERSONNEL. NR1 IIDS DISPLAY UNIT SCREEN BREAKER WAS PU	LLED OUT. SMOKE STOPPED AND AIRCRAFT LANDED SAFELY.  PART REMOVED AND REPLACED.			1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2005052300059	20050523	00059	NE  	2005	5	23	CA050401005      	2	20050329	G	7200		ENGINE          								PWA   	PT6   	PT6A25      	52043	NE  						MAKING METAL    	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								26284			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER FOLLOWING TAKE-OFF.  THE FLIGHT DIVERTED TO POINT OF ORIG	IN.  DURING SUBSEQUENT TROUBLESHOOTING, THE CHIP DETECTOR WARNING ANNUNCIATED AND METAL PARTICLES WERE FOUND ON THE DETE	CTOR.  MFG WILL MONITOR THE INVESTIGATION OF THIS INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.									3	T			E4EA				 
2005052300057	20050523	00057	EA  	2005	5	23	CA050401006      	1	20050323	G	3246	C2US335	WASHER          			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	AXLE	MISSING         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) WASHER WAS NOT INSTALLED ON AXLE UPON INSTALLATION OF SKIS. THIS CAUSED SKI TO SLIDE OFF AXLE ON LANDING, RESULTIN	G IN AN OVERSHOOT. THE SKI DANGLED FROM THE CABLES AND BEAT AGAINST THE FUSELAGE CAUSING FURTHER DAMAGE BEFORE BREAKING 	FREE.  THE PILOT THEN CALLED AN EMERGENCY AND HAD EMERGENCY RESPONSE COME IN.  THE AIRCRAFT WAS THEN LANDED WITHOUT FURT	HER INCIDENT.			1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206	 
2005052300054	20050523	00054	CE  	2005	5	23	CA050401007      	1	20050324	G	5320	P01012	TEE FITTING     			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	LOOSE           	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) TEE FITTING SUPPLYING TORQUE PRESSURE READING TO AIRCRAFT INSTRUMENTS WAS LOOSE, CAUSING AN OIL LEAK. THE TEE FITT	ING WAS WITNESSED (WIRED) AND APPROX  HALF TURN WAS NEEDED TO TIGHTEN.  AIRCRAFT ENGINE WAS SHUTDOWN IN FLIGHT AND AIRCR	AFT LANDED SAFELY.  OIL PRESSURE WAS RECORDED AT 45 PSIG PRIOR TO SHUTDOWN. THIS FITTING IS PART AN STC'D INSTALLATION O	F THE ALTAIR TWIN-K031-3 ENGINE HIGH PRECISION TORQUE KIT.  NOTICE 651-77-12-016 WAS CREATED TO CHECK FOR SIMILAR CONDIT	IONS ON COMPANY FLEET AIRCRAFT. IT WAS FOUND THAT MANIPULATING THE TEE FITTING BY HAND COULD CAUSE LOOSENING.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2005052300055	20050523	00055	SO  	2005	5	23	CA050401008      	1	20050324	G	2410	ALX9425B	ALTERNATOR      			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	ENGINE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				L	O		NO TEST                   	OTHER                     		CR	CRUISE         	1			CA											(CAN) ALTERNATOR FAILURE, SEPARATION OF DRIVE GEAR DUE TO SHEARED ROTOR SHAFT. METAL CONTAMINATION OF ENGINE.						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
2005052300056	20050523	00056	CE  	2005	5	23	CA050401009      	1	20050310	G	2435	6608458010	STARTER GEN     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					STARTER GEN	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT, JUST PRIOR TO DESCENT FOR LANDING, THE CREW NOTICED A VIBRATION FROM REAR OF AC.  THE AIRCRAFT L	ANDED UNEVENTFULLY. POST FLIGHT INSPECTION FOUND EXCESSIVE AMOUNTS OF BLACK STAIN (CARBON) ON BOTTOM OF LT ENGINE COWLIN	G AFT OF STARTER/GENERATOR COOLING VENT. THE LT STARTER/GENERATOR WAS REPLACED AND SUBSEQUENT ENGINE RUNS FOUND THIS CUR	ED THE VIBRATION.  THIS IS THE THIRD STARTER/GENERATOR FAILURE ON THIS AIRCRAFT AND THIS UNIT WAS TO THE LATEST MODIFICA	TION STATUS.  WE HAVE NOT HAD A STARTER/GENERATOR ON THIS AIRCRAFT MAKE IT TO ITS FULL RATED LIFE OF 1200 HOURS.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005052300052	20050523	00052	SW  	2005	5	23	CA050401010      	1	20050112	G	6210	427015001125	BLADE           			BELL  	427   	427         	1182207	SW  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND M/R BLADE WITH A CRACK IN THE L/E EROSION STRIP.  CRACK IS 3.250 INCH IN LENGTH CHORDWISE AND 107.5 INCH IB 	FROM THE BLADE TIP (BLADE STATION 114.5).					1	G	7	1 	3U				R00001RC					 
2005052300053	20050523	00053	SW  	2005	5	23	CA050401011      	1	20050401	G	2520		TABLE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MFG 5 MAN SEAT POSITION IS SHOWN AT FS 119. SEAT HAS 2 IN THICK BACK CUSHION AT TRANSMISSION BULKHEAD STA. MM PUTS	 5 MAN TROOP SEAT AT FS 117.  MIDDLE PASSENGER FOR THAT SEAT CONFIGURATION HAS ITS BACK DIRECTLY AGAINST THE TRANSMISSIO	N BULKHEAD. IT SEEMS ODD THAT THE MFG PASSENGER STATION WOULD BE 2 INCHES AFT OF THE TROOP PASSENGER SEAT. THE MFG AIRLI	NE PASSENGER SEATING ARRANGEMENT IS VERY SIMILAR TO THE MFG SEATS AND SHOWS THE 5 MAN SEAT POSITION AT FS 114.7.  THERE 	IS ALSO A SLIGHT DIFFERENCE IN THE 4 MAN SEAT, WHICH SHOULD BE CHECKED ALSO. THERE IS A NEED FOR CLARIFICATION. HAVE THE	 SAME KIT INSTALLED IN THREE OTHER HELICOPTERS. PLEASE FIND ATTACHED APPLICABLE SUPPLEMENTS.	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005052300050	20050523	00050	NM  	2005	5	23	CA050401012      	1	20050325	G	7830	PNLJ75153	TORQUE RING     			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					THRUST REVERSER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT ARRIVED WITH DAMAGE TO THE NR 2 ENG FORWARD THRUST REVERSER TORQUE BOX ON THE OB SIDE.  CLOSER INSPECTION	 REVEALED THAT THE BLADE STRAP (PART OF THE ACTUATOR LOCKOUT MECHANISM) AFT ATTACHMENT POINT CAME LOOSE AND WHEN THE THR	UST REVERSER STOWED THE STRAP FOLDED FORWARD AND CAUSED THE DAMAGE.  IT WAS NOTICED THAT THE BLADE STRAP BRACKET ON THE 	TORQUE RING HAD BEEN BADLY WORN CAUSING DAMAGE TO THE TORQUE RING AND CASCADE VANE. THE OTHER SIDE SHOWED SIMILAR WEAR M	ARKS. THE FWD FITTING FOR THE BLADE STRAP WAS FOUND TO BE CRACKED AS WELL.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005052300051	20050523	00051	CE  	2005	5	23	CA050401013      	1	20050327	G	3260	444EN496	SAFETY SWITCH   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR WAS SELECTED UP BUT THE GEAR DID NOT RETRACT.  AIRCRAFT RETURNED TO AIRPORT SAFELY.  D	URING TROUBLESHOOTING MAINTENANCE FOUND THAT THE RT GEAR SAFETY SWITCH WAS FAULTY.  SAFETY SWITCH WAS REPLACED WITH NO F	URTHER PROBLEMS.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061700013	20050617	00013	CE  	2005	6	17	CA050401014      	1	20050309	G	3222		FORK            			BEECH 	100   	B100        	1152919	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE PERFORMING  NDT INSP CALL UP IN AD 2004-23-02, NOSE GEAR FORK FOUND TO BE CRACKED.  NOSE GEAR FORK REPLACED WITH N	EW STYLE FORK ASSY IN BEECH 101-8030-1S SERVICE KIT.					1	L	7	2 	4T				A14CE   					 
2005052300049	20050523	00049	CE  	2005	5	23	CA050404001      	1	20050401	G	3241	40911	TRANSDUCER      			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					WHEEL SPEED	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CHANGING NR3 BRAKE, MAINTENANCE PERSONNEL NOTICED A HAIRLINE CRACK ON THE FACE ON THE TRANSDUCER.  AFTER REM	OVING THE TRANSDUCER, THE TECHNICIAN SAW THAT THE CRACK WAS EXTENDING ALL THE WAY THROUGH THE TRANSDUCER HOUSING. THE TR	ANSDUCER WAS REPLACED AND SYSTEM WAS TESTED SERVICEABLE.  NOTE: IN THE PAST COUPLE OF WEEKS WE HAVE HAD A INTERMITTENT S	NAG, THE ANTI SKID LIGHT WOULD COME ON.			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005052300047	20050523	00047	GL  	2005	5	23	CA050404002      	3	20050401	G	6110	A251378	BOLT            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									R771121		(CAN) AD 2003-12-05 (MFG SB 221C) REQUIRES MAGNETIC PARTICLE INSP. OF PROP MOUNTING BOLTS. DURING INSP 1 OF THE 6 PROP M	OUNTING BOLTS WAS NOTED AS CRACKED IN THE GRIP APPROX .25 BELOW THE BOLT HEAD.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005052300048	20050523	00048	SO  	2005	5	23	CA050404003      	2	20050402	G	7414	105136037	MAGNETO         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING, ENGINE BECAME NOTICEABLY ROUGH.  AFTER LANDING A MAGNETO CHECK WAS ACCOMPLISHED.  THE MAG CHECK REVEAL	ED THAT THE RT MAGNETO WAS NOT FIRING. UPON INSPECTION OF SAME IT WAS DISCOVERED THAT THE INTERNAL NYLON GEAR HAD FAILED	 (TEETH STRIPPED).  MAGNETO WAS REMOVED AND A NEWLY OVERHAULED MAGNETO WAS INSTALLED.				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2005052300045	20050523	00045	CE  	2005	5	23	CA050404004      	1	20050321	G	8011		DRIVE ASSY      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L3657127A			(CAN) THE PROBLEM WAS DISCOVERED WHEN THE STARTER DID NOT ENGAGE TO START THE ENGINE.  THE STARTER BENDIX GEAR WAS FOUND	 TO BE IN PIECES.  THIS HAS BEEN THE THIRD TIME FOR THIS PROBLEM TO OCCUR.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005052300046	20050523	00046	EA  	2005	5	23	CA050404005      	1	20050302	G	2923	332574	PLATE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PISTON RETAINER	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			42469	42469							(CAN) NR 1 STANDBY POWER UNIT INDICATED, 'NO PRESSURE OUTPUT'.  DEFECT 435468, SPU REMOVED AND SENT TO SHOP.  APRIL 4TH 	JAZZ HYD SHOP WO NR 174735 REPORTED, 'PISTON SHOE FAILURE CAUSED PISTON BEARING PLATE TO BE GOUGED.  PISTON RETAINER PLA	TE, PISTON RETAINER PLATE RETAINER AND CYLINDER BARREL DAMAGED BY FOD.  PUMP TESTED AND RETURNED TO SERVICE.'				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005052300044	20050523	00044	SW  	2005	5	23	CA050404006      	1	20050317	G	6210	407015011117	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK IN THE LEADING EDGE EROSION STRIP WAS DISCOVERED WHILE TRYING TO WORK THE MAIN ROTOR WITH THE RADS.  ON INIT	IAL INSPECTION THE CRACK APPEARED TO BE A MASKED EDGE FROM THE NICKEL ABRASION COATING BUT AFTER THE BLADE WAS FLEXED, I	T OPENED UP TO REVEAL A CRACK.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005052300043	20050523	00043	CE  	2005	5	23	CA050404007      	1	20050404	G	3230	504501025	TORQUE TUBE     			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING AN INSPECTION, RECOMMENDED BY THE MANUFACTURER, RT MAIN LANDING GEAR EXTENSION/RETRACTION TORQUE TUBE FO	UND CRACKED IN TWO PLACES, AT THE FORK BOLT ATTACHMENT AND THE ARM CLOSE TO IT.					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2005052300042	20050523	00042	EU  	2005	5	23	CA050404008      	1	20050404	G	5610	NP1653113	WINDSCREEN      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CAPTAIN WINDSCREEN CRACKED IN FLT 36000 FT EMERGENCY DESCENT CARRIED OUT.  CRACK SPARKED ELECTRICALLY WHILE CRACKI	NG TIME OF CRACK IS FULL LENGTH 3 FT. WINDOW REPLACED AS PER AMM 56-11-11, WINDOW CONTROLLER CHANGED AND TESTED AS PER A	MM 30-42-34 PB 40.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005052300041	20050523	00041	SO  	2005	5	23	CA050404009      	2	20050404	G	8520		CRANKCASE       			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE INITIAL PROBLEM WAS AN OIL LEAK FOUND DURING INSPECTION, AFTER SEVERAL ENGINE GROUND RUN-UPS, CRACK OF 2 INCHE	S FOUND FWD OF CYLINDER NR 5 ON CRANKCASE UPPER SECTION, ENGINE REMOVED AND SEND TO REPAIR SHOP.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2005052300040	20050523	00040	NE  	2005	5	23	CA050405001      	2	20050401	G	7261		CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) BOMBARDIER AEROSPACE REGIONAL AIRCRAFT HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT.  CLIMBING THROUG	H FL310, LEFT ENGINE OIL PRESSURE WARNING MESSAGE WITH PRESSURE AT 25-35 PSI., EVENTUALLY STABILIZED AT 25 PSI.  PRECAUT	IONARY ENGINE SHUTDOWN PERFORMED.  REMOVED AND REPLACED CARBON SEALS ATF AXIS, D AXIS, AND BB AXIS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071200010	20050712	00010	CE  	2005	7	12	CA050405002      	1	20050316	G	2435	30539423	SPEED SWITCH    			BEECH 	100   	B100        	1152919	CE  										LT STARTER GEN	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) LT STARTER GENERATOR SYSTEM SPEED SWITCH MALFUNCTIONED. NO IGNITION WAS INITIALED AT THE PRESCRIBED PERCENTAGE N2.	 SWITCH REPLACED.					1	L	7	2 	4T				A14CE   					 
2005052300039	20050523	00039	CE  	2005	5	23	CA050405003      	1	20050321	G	3252	04425121	SHIMMY DAMPENER 			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					NLG	FAILED          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) SHIMMY DAMPNER FAILED AT TAKEOFF CAUSING A VIBRATION.  AIRCRAFT CAME TO REST WITH ONLY MINIMAL DAMAGE.  SHIMMY DAM	PNER REPLACED.					1	H	7	1 	3O	3	O		3A19    	E252				 
2005052300038	20050523	00038		2005	5	23	CA050405005      	4	20050316	G	3425	7014300901	DISPLAY         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					EFIS	FAILED          	W				O				OTHER                   				C			F.O.D.                    			AP	APPROACH       	1			CA											(CAN) DISPLAY SCREEN COLORS CHANGED AFTER LIGHTNING STRIKE, FUNCTION NORMAL.  UNIT GROUND TESTED NORMAL, EXCEPT FOR COLO	R CHANGE.  REPLACED UNIT WITH EXCHANGE UNIT.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005052300202	20050523	00202		2005	5	23	CA050405006      	4	20050316	G	3425	7012100825	RMU             			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					COCKPIT	FAILED          	W				O				OTHER                   				C			F.O.D.                    			AP	APPROACH       	1			CA											(CAN) DISPLAY SCREEN COLORS CHANGED AFTER LIGHTNING STRIKE, FUNCTION NORMAL. UNIT GROUND TESTED NORMAL EXCEPT FOR COLOUR	 CHANGE.  REPLACED UNIT WITH EXCHANGE UNIT.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005052300200	20050523	00200		2005	5	23	CA050405007      	4	20050326	G	3460	7012100825	RMU             			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					FUSELAGE	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DISPLAY COLORS CHANGED, FUNCTION NORMAL UNIT GROUND TESTED NORMAL. REPLACED WITH EXCHANGE UNIT.  THIS WAS APPROXIM	ATELY 14 HOURS AFTER LIGHTNING STRIKE.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005052300037	20050523	00037		2005	5	23	CA050405008      	4	20050326	G	3425	7014300901	DISPLAY         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					EFIS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DISPLAY COLORS CHANGED, FUNCTION NORMAL UNIT GROUND TESTED.  NORMAL. REPLACED WITH REPAIRED EXCHANGE UNIT.  THIS W	AS APPROXIMATELY 14 HOURS AFTER LIGHTNING STRIKE.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005052300036	20050523	00036	SW  	2005	5	23	CA050405009      	1	20050330	G	2435		BEARING         	LEARSIEGLER 		BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3505					(CAN) AFT BEARING FAILURE, REMOVED STARTER GENERATOR.  INSTALLED SERVICEABLE STARTER GENERATOR.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005052300035	20050523	00035	NM  	2005	5	23	CA050405010      	1	20050330	G	2782	1U109592	ACTUATOR        			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					NR 1 SLAT	FAILED          	W				J	A			DUMP FUEL               	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB PHASE, SLATS RETRACTED, NR 1 SLAT, HOWEVER DID NOT SHOW RETRACTED.  FLIGHT CREW CONFIRMED THAT AIRCRA	FT DID NOT HAVE ANY UNCOMMANDED ROLL IN THE FLIGHT CHARACTERISTICS.  THIS INDICATED AN INDICATION FAULT ONLY.  CREW RETU	RNED TO POINT OF DEPARTURE AFTER DUMPING 7300 LBS OF FUEL WITHOUT FURTHER INCIDENT.  MAINTENANCE CONFIRMED SLATS FUNCTIO	NAL AND ONLY INDICATION AT FAULT.  ACTUATOR WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005052300034	20050523	00034	SO  	2005	5	23	CA050405011      	1	20050320	G	2710	MS21251B5S	TURNBUCKLE      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					AILERON CABLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON CHANGING THE RIGHT HAND AILERON CABLE AT WING STATION 70, THE CONNECTING TURNBUCKLE WAS FOUND CRACKED PN MS2125	1-B5S.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005052300033	20050523	00033	SW  	2005	5	23	CA050405012      	1	20050331	G	2913	PV34426	PUMP            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  LOSS OF HYDRAULICS, FLT WAS CONTINUED, UNEVENTFUL FLAPLESS LANDING COMPLETED. INSP OF AC, NOTED, ALL OF FLUID LEA	KED OVERBOARD FROM LT ENG HYD PUMP. INSP OF PUMP REVEALED EXTRUDED O-RING SEAL FROM PUMP HSG SPLIT LINE. BOLTS HOLDING 2	 PUMP HSG HALVES TOGETHER WERE FOUND LOOSE, ALLOWING O-RING TO BE PUSHED OUT DURING NML PUMP OPS. NML FIELD MAINT OF ENG	 DRIVEN HYD PUMPS DO NOT REQUIRE DISTURBING OR REMOVING ANY OF HYD PUMP BOLTS NOR WAS ANY EVIDENCE AS SUCH. PUMP WAS REP	LACED, AC HYD SYS INSPECTED, TESTED. 3 HYD SYS CHK VALVES WERE FOUND UNSERVICEABLE, 1 FOR EA PUMP, HYD SYS PRESS RELIEF 	CHECK VALVE. APPEARS FAILURE OF THIS PUMP DAMAGED ENG DRIVE SPLINES TO DEGREE THAT ENG HAD TO BE REMOVED FOR REPAIR.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2005052300032	20050523	00032	NM  	2005	5	23	CA050405013      	1	20050328	G	3250		CABLE           			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					STEERING TILLER	MALFUNCTIONED   	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED THAT THE STEERING TILLER AND THE RUDDER PEDALS DO NOT CENTER WHEN RELEASED, AND THE TILLER STICKS O	N HARD TURNS.  MAINTENANCE FOUND THE STEERING CABLE TURN BARREL ID TAG HAD SLIPPED FROM THE TURN BARREL, THEREBY RESTRIC	TING FREE MOVEMENT OF THE CABLE ASSEMBLY.  THE TAG WAS REMOVED AND STEERING SYSTEM WAS CHECKED FOR FREE AND FULL MOVEMEN	T.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005052300031	20050523	00031	WP  	2005	5	23	CA050406001      	2	20050331	G	7310	8G12561	PRESSURE SWITCH 			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 2 ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHILE FLIGHT CREW WAS PREPARING FOR NEXT FLIGHT, THE FLIGHT ATTENDANT NOTICED FUEL DRIPPING FROM THE BOTTOM OF NR 	2 ENGINE COWL.  UPON FURTHER INSPECTION, FUEL WAS LEAKING OUT OF VENT HOLE OF THE NR 2 LOW FUEL PRESSURE SWITCH.  SWITCH	 WAS REPLACED WITH NEW.  THIS IS THE SECOND SWITCH FOR THIS AIRCRAFT, FIRST ONE WAS ON THE NR 1 ENGINE 270 HOURS AGO.  A	S A CAUTIONARY MEASURE, THE NR 3 ENGINE LOW FUEL PRESSURE WILL BE REPLACED WHEN AIRCRAFT RETURNS TO HOME BASE. THE MANUF	ACTURER HAS BEEN INFORMED.		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2005052300030	20050523	00030	WP  	2005	5	23	CA050406002      	1	20050404	G	7810	9063571	SUPPORT         			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					TAIL PIPE	SHEARED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) DURING ENGINE RUN, A VIBRATION WAS NOTED ON THE LT ENGINE.  UPON INVESTIGATION MAINTENANCE CREW NOTED THAT THE TAI	L PIPE SUPPORT WAS SHEARED.  THE SUPPORT WAS REPLACED.  THE ENGINE WAS GROUND RUN AND THE VIBRATION WAS STILL PRESENT.  	THE ENGINE WILL BE REMOVED AND REPLACED WITH A SERVICEABLE UNIT.  IT IS BELEIVED THAT THE ENGINE VIBRATION WAS THE CAUSE	 OF THE SHEARED TAIL PIPE SUPPORT.			2	L	7	2 	4R	4	T		6A6     	E282				 
2005052300029	20050523	00029	NM  	2005	5	23	CA050406003      	1	20050324	G	3246	29685	BEARING         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG WHEEL	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING LANDING, THE OUTBOARD ANTI-SKID CAUTION LIGHT ILLUMINATION.  INSPECTION BY TECHNICIANS REVEALED THE FOLLOWI	NG: RT WHEEL AND BRAKE ASSY OVERHEATED, INBOARD BEARING BROKEN/OVERHEATED ON RT OUTBOARD MAIN WHEEL, ANTI-SKID WIRING WI	THIN WHEEL AXLE BURNED (CAUSE OF ANTISKID C/L).				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005052300028	20050523	00028	CE  	2005	5	23	CA050406004      	1	20050404	G	7160	NH300038010	DUCT            			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					RAM AIR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING OTHER MAINTENANCE ON AIRCRAFT, NOTICED RAM AIR DUCT IN REAR EQUIPMENT BAY CRACKED.  UPON CLOSER INSPECTION 	OF RAM AIR DUCT, NOTICED SEVERE CHAFFING BETWEEN RAM AIR DUCT AND RT ENGINE BLEED AIR LINE JUST PRIOR TO BLEED AIR CHECK	 VALVE.  RAM AIR DUCT WAS CHAFED 99 PERCENT THROUGH, AND BLEED AIR TUBE IS BEYOND REPAIR LIMITS.  THIS IS AN AREA THAT I	S NOT EASILY VISUALLY ACCESSABLE.  NEW DUCT AND NEW BLEED TUBE NEED TO BE INSTALLED.			1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005052300027	20050523	00027	EA  	2005	5	23	CA050406005      	1	20050406	G	3233	6008500237	ACTUATOR        			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					NLG	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) NOSE LANDING GEAR ACTUATOR LEAKING AT ROD END PISTON.  LIFE LIMITED PART AT 19480 CYCLES.  A/C RETURN TO BASE ON S	PECIAL FLIGHT PERMIT WITH GEAR DOWN.					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2005052300026	20050523	00026	SW  	2005	5	23	CA050406007      	1	20050317	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLESHOOTING MAIN ROTOR SYSTEM FOR CAUSE OF DIFFICULTY WITH M/R TRACK AND BALANCE A HAIRLINE CRACK WAS DI	SCOVERED IN THE DISCREPANT BLADE LEADING EDGE ABRASION STRIP APPROXIMATELY 77 INCHES FROM THE BLADE TIP.  THE BLADE AS P	LACED ON A WORK STAND AND GENTLY FLEXED UP AND DOWN INDICATING THAT THE CRACK OPENED AND CLOSED WHEN FLEXED.  THE CRACK 	WAS SO FINE IT HAD TO BE VERIFIED WITH A 10X MAGNIFYING GLASS AND THE BLADE FLEXED TO BE SURE IT WAS NOT JUST A SURFACE 	SCRATCH.  THE BLADE WAS REMOVED FROM SERVICE AND REPLACED WITH A RECONDITIONED UNIT SUPPLIED BY BELL.  MALFUNCTION REPOR	T ALSO SUBMITTED TO BELL HELICOPTER.	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005052300025	20050523	00025		2005	5	23	CA050407001      	4	20050405	G	6122	0210659	GOVERNOR        			BNORM 	BN2   	BN2A21      	1520221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					PROPELLER	SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								L1224548			(CAN) THE AIRCRAFT DEPARTED FOR DESTINATION WITH ONE PILOT ABOARD.  SHORTLY AFTER TAKEOFF, THE RIGHT ENGINE S/N L12245-4	8 RPM BEGAN TO DETERIORATE.  THE PILOT SHUT THE ENGINE DOWN AND RETURNED FOR A NORMAL LANDING AT THE DEPARTURE AIRFIELD.	  INSPECTION REVEALED THAT THE PROPELLER GOVERNOR ON THAT ENGINE HAD SEIZED AND BROKEN THE DRIVE SPLINE.  THE GOVERNOR W	AS REPLACED, THE ENGINE GROUND RUN OK, AND THE AIRCRAFT RETURNED TO SERVICE.  ENGINE TTSO/H 1653.9 HRS.  GOVERNOR TTSO/H	 1652.3 HRS.		1	H	7	2 	3O	3	O		A17EU   	1E4				 
2005071300046	20050713	00046	CE  	2005	7	13	CA050407002      	1	20050404	G	2913	99140751	PUMP            			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF, THE LT HYDRAULIC PRESSURE LOW ANNUNCIATION ILLUMINATED IN CLIMB. AIRCRAFT RETURN TO MAINTENANCE BA	SE. LT ENGINE HYDRAULIC DRIVEN PUMP REPLACED.					2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2005052300024	20050523	00024	CE  	2005	5	23	CA050407003      	1	20050319	G	3230	402	BRUSHES         	ELECTROMECH 		BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  					MLG MOTOR	SHORTED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			LD	LANDING        	1			CA						1562					(CAN) A/C SUSTAINED GEAR COLLAPSE AFTER ERRONEOUS GEAR INDICATIONS.  MOTOR CURRENT LIMITER FOUND 'BLOWN', MOTOR WOULD NO	T RUN UNDER 'LOAD'.  CASB CURRENTLY INVESTIGATING INCIDENT.  NOTE, BRUSH INSP LIMIT 2500 CYCLES BRUSH INSP TOTAL CYCLES 	2374.  COULD NOT DUPLICATE ERRONEOUS GEAR INDICATIONS AT THIS TIME NOTE L/G MOTOR REPAIR REPORT TO FOLLOW.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005052300023	20050523	00023	EU  	2005	5	23	CA050407004      	1	20050320	G	2742	1291110002	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					PITCH TRIM	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) INTERMITTENT FAILURE.  AIRCRAFT DID NOT ARRIVE AT THE STATED POSITION. THE AUTOPILOT COMPENSATOR INDICATED FUNCTIO	NED NORMALLY, BUT THERE WAS NO MOVEMENT FROM THE HORIZONTAL STABILIZER WHICH CAUSED AN AUTO DISCONNECT OF THE AUTOPILOT 	SYSTEM.  THE TWO MOTORS ARE INSTALLED ON THE SAME TRANSMISSION, IT BECOMES IMPOSSIBLE IN THE EVENT OF BREAKING MECHANICA	LS TO ACTUATE THE COMPENSATOR.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2005052300022	20050523	00022	CE  	2005	5	23	CA050407005      	1	20050331	G	7921	1143890005	OIL COOLER      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) RT ENGINE OIL PRESSURE LOW LIGHT CAME ON IN FLIGHT.  ENGINE WAS SECURED AND EMERGENCY LANDING CARRIED OUT.  OIL CO	OLER WAS TESTED UNDER PRESSURE AND WAS FOUND TO BE LEAKING AND WAS REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005052300021	20050523	00021	CE  	2005	5	23	CA050407006      	1	20050401	G	5610	1013840252	WINDSHIELD      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDSHIELD INNER PANE SHATTERED IN CRUISE.  CREW CARRIED OUT ABNORMAL PROCEDURES FOR CRACKED WINDSHIELD AND LAN	DED THE AIRCRAFT.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005052300020	20050523	00020	EA  	2005	5	23	CA050407007      	1	20050405	G	2701	C3CF39519	CONTROL COLUMN  			DHAV  	DHC6  	DHC6        	2802606	EA  										COCKPIT	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LOWER CONTROL COLUMN IS MIS-MANUFACTURED AT THE BOTTOM TORQUE TUBE.  THE STOP BOLT INSERTS AND CABLE QUADRANT 	SUPPORTS WERE MIS-LOCATED DURING MANUFACTURE OF THE ASSEMBLY.  FINAL ASSEMBLY PROBLEMS WILL OCCUR.					1	H	7	2 	3T			RT	A9EA    					 
2005052300019	20050523	00019	CE  	2005	5	23	CA050407008      	1	20050406	G	8011		BRUSHES         	LAMAR       		CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	STARTER	LOOSE           	W				O				OTHER                   				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA						85029912					(CAN) STARTER FAILED.  BRUSHES WERE LOOSE UPON EXAMINATION AND WINDINGS BURNT.  SUSPECT THE BRUSHES WERE LOOSE TO START 	WITH.					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2005052300018	20050523	00018	CE  	2005	5	23	CA050407009      	1	20050331	G	2435	03600918	BEARING         	LEARSIEGLER 		BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					STARTER GEN	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						Y20014					(CAN) GENERATOR FAIL LIGHT CAME ON IN FLIGHT.  MAINTENANCE FOUND THAT THE FRONT BALL BEARING HAD FAILED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005052300017	20050523	00017	EU  	2005	5	23	CA050408001      	1	20050406	G	2434	10200311	GCU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					NR 2	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) SHORTLY AFTER DEPARTING YZF, NR 2 DC GENERATOR WENT OFF LINE.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WHERE M	AINTENANCE RERACKED THE NR 2 GCU AND GROUND RAN THE AIRCRAFT WITH NO FAULT FOUND.  RETURNING TO YZF LATER SAME DAY THE N	R 2 DC GENERATOR WENT OFFLINE AGAIN.  UPON ARRIVAL IN YZF THE NR 2 GCU WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE	.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005052300016	20050523	00016	NE  	2005	5	23	CA050408002      	1	20050406	G	2420		SHAFT           	LUCAS       		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					AC GENERATOR	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						1109					(CAN) AC GENERATOR SHAFT SHEARED.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005052300015	20050523	00015	EA  	2005	5	23	CA050408003      	1	20050405	G	3250	7116111	COLLAR          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					NLG STEERING	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ON AIRCRAFT ARRIVAL AT YZF, THE CREW REPORTED LOSS OF NOSE WHEEL STEERING.  INVESTIGATION BY MAINTENANCE STAFF REV	EALED THAT THE NWS COLLAR P/N 71-161-11 WAS SHEARED OFF.  THE ENTIRE NOSE GEAR ASSEMBLY WAS REPLACED AND THE SURROUNDING	 AREA WAS INSPECTED FOR SECONDARY DAMAGE.  NO FURTHER FINDINGS WERE NOTED.  THE FACILITY THAT O/H THE GEAR ASSY WAS CONT	ACTED AND NOTIFIED.  THE O/H FACILITY ADVISED THAT FRACTURES OF THIS NATURE WERE PRESUMABLY CAUSED BY REPETITIVE EXCESSI	VE STRESS IMPOSED ON THE ALUMINUM STEERING COLLAR AT THE PIVOT POINT DUE TO SHARP TURNING INPUTS.  THE AIRCRAFT WAS RETU	RNED TO SERVICE FOLLOWING THE GEAR REPLACEMENT.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005052300014	20050523	00014	EU  	2005	5	23	CA050408004      	1	20050408	G	2560	504339401	SHOULDER BELT   			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COCKPIT	FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE SEAT BELT SHOULDER STRAP CHAFED ON A RETAINING BRACKET FOR THE SEAT BACK COVER ON THE PILOTS SEAT.  THE CHAFIN	G OCCURRED DURING RETRACTION AND EXTENSION OF THE INERTIA REEL OVER A PERIOD OF TWO MONTHS AND SEVERAL FLIGHTS.  THE BRA	CKET IN QUESTION HAD SHARP EDGES WHICH IS NOT THE NORM FOR THIS PART.  IT ALSO HAS A LARGER RADIUS ON ONE OF THE TWO BRA	CKETS USED FOR HOLDING THE PILOT'S SEAT BACK COVER IN POSITION.  REPLACED THE INERTIA REEL ASSEMBLY WITH A NEW UNIT AND 	SMOOTHED OUT THE EDGES OF THE SUSPECT BRACKET WHICH CUT INTO THE SHOULDER BELT.  THE SYSTEM HAS BEEN TESTED, HQ NOTIFIED	, AND WE SHALL BE KEEPING A REGULAR WATCH ON THIS AREA AS IS OUR NORM .	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2005052300013	20050523	00013	CE  	2005	5	23	CA050408005      	1	20050406	G	2897	92746205	RELAY           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					FUEL PUMP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PHASE INSPECTION, BOTH FUEL PUMP RELAYS (JT AND KT) WERE FOUND WITH CORRODED TERMINAL BLOCKS.  ONE WIRE FRO	M THE RELAY WAS DAMAGED AND ARCHED ON THE CASE OF THE RELAY.  THE RELAYS ARE LOCATED UNDER THE WING TO FUSE BELLY FAIRIN	G.  THIS AREA IS SUBJECTED TO MOISTURE DUE TO THE MEANS THAT THE PANELS ARE SEALED (PERFORMED SEAL)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005052000012	20050520	00012		2005	5	20	CA050408009      	4	20050408	G	3444		CASE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RADAR ALTIMITER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING AVIONICS UPGRADE PROCEDURES IT WAS FOUND THAT THE PILOTS RADAR ALTITUDE INDICATOR P/N 622-4160-018 WOULD CH	AFE ON THE WINDSHIELD CENTER POST STRUCTURAL DOUBLER P/N 50-420066-281.  THE CHAFFING WAS SERIOUS ENOUGH TO DAMAGE THE D	OUBLER BEYOND ACCEPTABLE LIMITS AS WELL AS THE INDICATOR CASE REAR RIGHT HAND CORNER BEING WORN THROUGH.  THE STRUCTURAL	 DAMAGE WAS SUBSEQUENTLY REPAIRED AND DAMAGED INDICATOR REPLACED.  IT IS WORTH NOTING THAT THE AVIONICS UPGRADE PROGRAM 	HAS RELOCATED PANEL EQUIPMENT SUCH THAT THIS IS NO LONGER A INTERFERENCE PROBLEM.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005052000011	20050520	00011	GL  	2005	5	20	CA050408010      	1	20050407	G	6120	14392102	CONTROL ROD     			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					PROPELLER	STIFF           	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) ENGINE POWER LEVER FOUND JAMMED DURING PREFLIGHT, DISCONNECTED THROTTLE AND PROPELLER CONTROL ROD END AT ENGINE AN	D FOUND PROPELLER CONTROL CABLE IS NOT MOVING.  NO EXTERNAL SIGN OF DAMAGE TO CABLE TO CAUSE JAMMING.  CABLE ASSEMBLY RE	PLACED.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2005052000010	20050520	00010	EA  	2005	5	20	CA050408011      	2	20050403	G	7414	103492901	MAGNETO         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	BURNED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								L406161A			(CAN) RT ENGINE PARTIAL FAILURE ON CLIMB-OUT.  RPM, MP, FF, FP EXCESSIVE DROPS.  TROUBLE SHOOTING FOUND THAT LT MAGNETO 	FAILED.  NEW MAGNETO INSTALLED.  A/C TEST FLOWN, SATISFACTORY TEST FLIGHT.  U/S MAGNETO SENT OUT FOR O/H.  TEAR DOWN FOU	ND POINTS BURNT.  DISTRIBUTOR CAP ARCING INSIDE.  TEST FOUND ONLY FIRING ON HALF OF CYLINDERS.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005052000009	20050520	00009	EA  	2005	5	20	CA050408012      	1	20050407	G	3220	713099	WASHER          	HEROUX      		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					NLG FORK	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						H715					(CAN) SERVICING THE NOSE OLEO, THE ENGINEER NOTICED THAT THE FORK WAS LOOSE ON THE STRUT.  REMOVAL OF THE STRUT REVEALED	 THAT IT WAS ASSEMBLED INCORRECTLY.  THE WASHER P/N 71-309-9 WAS MISSING AND THAT EXTRA PEEL ABLE SHIMS HAD BEEN ADDED. 	 THE SHIMS ARE A SMALLER DIAMETER THAN THE WASHER AND LEFT A SPACE BETWEEN THEM AND THE STRUT.  OVERTIME THE SHIMS DEFOR	MED AND MOVED INTO THE SPACE ALLOWING THE FORK TO BECOME LOOSE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005052000008	20050520	00008	EA  	2005	5	20	CA050409001      	1	20050324	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WINDSHIELD	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) RT WINDSHIELD CRACKED ON APPROACH.  RT WINDSHIELD REPLACED AND TESTED ACCORDING AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005052000007	20050520	00007	EU  	2005	5	20	CA050411001      	1	20050409	G	3320	8ES00463200	POWER UNIT      			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2*    	 	GL  					CABIN LIGHTS	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) 45 MINUTES AFTER TAKEOFF, BURNING ODOR WAS REPORTED IN THE PASSENGER CABIN AT ROW 17-18.  ODOR DISAPPEARED AFTER 1	0 MINUTES.  DURING INVESTIGATION FOUND LIGHT TRANSFORMER ON POWER UNIT 18 BURNED AND FUSE BLOWN.  SUSPECT PROBLEM BEING 	CAUSED BY LIGHT SOCKET PINS, FOUND FUSED COMPLETE POWER UNIT.  REPLACED AND SYSTEM TESTED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2005052300129	20050523	00129	CE  	2005	5	23	CA050411002      	1	20050410	G	2750	1013800006	FLEX DRIVE      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			20087	20087							(CAN) ON APPROACH FLAPS WERE SELECTED TO 17 DEG, FLAPS STARTED TO MOVE THEN STOPPED, AIRCRAFT LANDED SAFELY.  INSPECTION	 OF THE FLAP SYSTEM SHOWED THAT THE RT FLAPS WERE IN A SPLIT FLAP CONDITION BETWEEN 0 DEG AND 17 DEG.  FURTHER INVESTIGA	TION REVEALED THE RT OB FLEX DRIVE WAS PHYSICALLY SHEARED IN HALF.  THE CABLE WAS BROKEN 86 INCHES FROM THE FLAP ACTUATO	R, THE FLEX DRIVE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005052000006	20050520	00006	CE  	2005	5	20	CA050411003      	1	20050410	G	3231	4532103045002	BELLCRANK       	HEROUX      		LEAR  	45    	45LEAR      	5170805	CE  										RT MLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1015					(CAN) DURING A ROUTINE INSPECTION, THE RT MLG OUTBOARD DOOR BELLCRANK WAS FOUND WITH A SLIGHT BEND.  THE TECHNICIAN GRAB	BED THE BELLCRANK AND ONE ARM BROKE OFF.  THE AREA WAS INSPECTED FOR ANY SIGN OF ADDITIONAL DAMAGE AND NONE COULD BE FOU	ND.  THE LT GEAR WAS INSPECTED BY NDT AND NO DAMAGE WAS FOUND.  THERE WAS NO RECORD OF MAINTENANCE BEING PERFORMED ON TH	IS SYSTEM.  A NEW BELLCRANK WAS INSTALLED AND GEARSWINGS CARRIED OUT WITH NO FAULTS.			2	L	7	2 	4F			RT	T00008WI					 
2005052000005	20050520	00005	GL  	2005	5	20	CA050411004      	2	20050410	G	7230	6890550	COMPRESSOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA			16608								(CAN) CREW WAS PREPARING TO LIFT OFF AND HEARD A LOUD BANG AND FELT A TWITCH.  MAINTENANCE REMOVED THE COMPRESSOR AND RE	PLACED IT WITH A SERVICABLE UNIT.  AIRCRAFT TEST FLOWN AND RETURN TO SERVICE.  AT MAINTENANCE FACILITY THE CASE WAS SPLI	T AND THE SIXTH STAGE STATORS HAD BEEN DAMAGED, HOWEVER NO EVIDENCE WAS FOUND INDICATING FOD FROM THE INTAKE.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005052000004	20050520	00004	NM  	2005	5	20	CA050412001      	1	20050409	G	2421	11522184	GENERATOR       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 1 ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) NR 1 ENG OIL PRESS WARNING LIGHT CAME ON DURING FLT.  OIL PRESSURE INDICATION GRADUALLY DECREASED TO 30 PSI THEN F	LUX 30-35 PSI.  NR 1 ENGINE IN FLIGHT SHUT DOWN CARRIED OUT.  MAINTENANCE DETERMINED THE OIL LEAK WAS CAUSED THREE STATO	R SCREWS MISSING FROM THE AC GENERATOR.  ENGINE HAD OPERATED 56 SECONDS AT 22.0 PSI OIL PRESSURE (OVER LIMIT).  ENGINE R	EPLACED.  AC GENERATOR SENT BACK TO MANUFACTURER FOR INVESTIGATION.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005052000003	20050520	00003		2005	5	20	CA050412002      	4	20050325	G	2200	993642461	CONTROL BOX     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					TRIM	FAILED          	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) NO AURAL WARNING TONE OF THE TRIM IN MOTION FROM THE CONTROL BOX.  BOX FAILURE.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005052000002	20050520	00002	CE  	2005	5	20	CA050412003      	1	20050411	G	2400	70HF10	DIODE           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					SUBPANEL BUSS	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) NO POWER ON RT SUBPANEL BUSS DUE TO BOTH FEEDER DIODES NOT PASSING CURRENT.  DIODES REPLACED, SERVICABLE.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005052000001	20050520	00001	NM  	2005	5	20	CA050413001      	1	20050413	G	2120	213T21095	DUCT            			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LT ENGINE	RUPTURED        	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FAULT: AFTER TAKEOFF, LEFT ENGINE DUCT LEAK TEMPERATURE CONTINUED TO CLIMB IN ALL CABIN.  RETURNED TO CANCUN.  FOU	ND DUCT ASSY 213T2109-5 RUPTURED.  DUCT ASSY CHANGED, OPERATION CHECK CARRIED OUT, FOUND OK CONS SERVICEABLE AS PER AMM 	36-11-01.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005052300198	20050523	00198	SO  	2005	5	23	CA050413002      	1	20050412	G	3230		DRAG ANGLE      			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ENROUTE YZF FROM HIGH LAKE(FLT 702) CLIMBING THROUGH FL230, THE CREW HEARD A BANG IN THE CARGO AREA.  THE L/M THE 	F/E WENT AFT AND OBSERVED A CRACK IN THE LT SIDE DRAG ANGLE.  THE CREW DEPRESSURIZED THE AIRCRAFT AND CONTINUED TO DESTI	NATION LANDING WITHOUT FURTHER INCIDENT.  MAINTENANCE OBSERVED A CRACK APPROXIMATELY 20 INCHES LONG CENTERED AT STA 577.				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2005051900249	20050519	00249		2005	5	19	CA050413003      	4	20050413	G	2210	1600980003	ELEMENT         			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					AUTO THROTTLE	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED 1200-HOUR CHECK, A FUNCTIONAL TEST OF THE RIGHT THRUST REVERSER AUTO THROTTLE RETARDER WAS CARR	IED OUT. THE RIGHT THROTTLE FAILED TO RETURN TO IDLE POSITION WITH THE THRUST REVERSERMANUAL DEPLOYMENT. UPON INVESTIGAT	ION IT WAS DISCOVERED THAT THE AUTO DEPLOYMENT RETARDER CABLE WAS BROKEN AT THE INNERSLEEVE WHERE IT ATTACHES TO THE THR	EADED ADJUSTER.			2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2005051900248	20050519	00248	CE  	2005	5	19	CA050413004      	1	20050408	G	2410	DOFF10300J	ALTERNATOR      			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	UNSERVICEABLE   	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) UPON CLIMB-OUT AFTER DEPARTURE NOTICED WHITE SMOKE COMING FROM THE LT SIDE OF THE AIRCRAFT AND THE SMELL OF BURNIN	G IN THE COCKPIT.  NOTIFIED THE TOWER OF THE EVIDENCE OF SMOKE AND RETURNED TO LAND UNEVENTFULLY.  UPON INVESTIGATION IT	 WAS REVEALED THE ALTERNATOR FAILED INTERNALLY WITH THE FIELD BRUSH DEPARTING ITS HOLDER SENDING POSITIVE VOLTAGE OUT TH	E GROUND WIRE BREAKING IT FREEOF ITS AMP CONNECTOR AND SHORTING ON THE FIREWALL MOUNTED NOISE FILTER.  THE NOISE FILTER 	AND ALTERNATOR ARE BEING REPLACED NEW AND THE GROUND WIRE REPAIRED.		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
2005061700012	20050617	00012	WP  	2005	6	17	CA050414002      	1	20050401	G	6320	369D2512311	GEAR            	DOUG        		HUGHES	369   	369D        	4470706	WP  										M/R GEARBOX	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA						U0561					MAIN ROTOR TRANSIMISSION SENT IN FOR REPAIR DUE TO REPORTED CHIPS ON DETECTOR.  TRANSIMISSION OPENED AND APPROXIMATELY 2	/3 OF TOOTH (CENTER PORTION) FOUND MISSING FROM INPUT GEAR.  PIECE LOCATED INSIDE TRANSIMISSION CASE.  NO FURTHER DAMAGE	 NOTED.				1	G	7	1 	3U				H3WE    					 
2005061700011	20050617	00011	WP  	2005	6	17	CA050414003      	1	20050401	G	6320	369D2512311	GEAR            	DOUG        		HUGHES	369   	369D        	4470706	WP  										M/R GEARBOX	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA						U0561					MAIN ROTOR TRANSMISSION SENT IN FOR REPAIR DUE TO REPORTED CHIPS ON DETECTOR.  TRANSMISSION OPENED AND APPR NR 2/3 OF TO	OTH (CENTER PORTION) FOUND MISSING FROM INPUT GEAR.  PIECE LOCATED INSIDE TRANSMISSION CASE.  NO FURTHER DAMAGE NOTED.					1	G	7	1 	3U				H3WE    					 
2005051900247	20050519	00247	WP  	2005	5	19	CA050414004      	2	20050412	G	7230	30721631	FAN BLADE       			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AT ROTATION, A POPPING NOISE WAS HEARD BUT NO ABNORMAL INSTRUMENT INDICATIONS WERE OBSERVED.  CLIMB AND CRUISE WER	E NORMAL AS WERE ALL TREND MONITOR RESULTS.  ABNORMAL VIBRATION WAS APPARENT ON DESCENT WITH LOWER POWER SETTINGS.  POST	 FLIGHT INSPECTION FOUND SIGNIFICANT DAMAGE TO THE RIGHT ENGINE FAN ASSEMBLY AND DISCOVERY OF FAN BLADE FAILURE.  INSPEC	TION AND REPAIR SERVICES WILL ATTEMPT TO DETERMINE CAUSE OF FAILURE.			2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2005051900246	20050519	00246	EU  	2005	5	19	CA050414005      	1	20050322	G	5610	1379628C402	WINDSHIELD      			BAG   	JETSTM	JETSTM4112  	       	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  					COCKPIT	FRACTURED       	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											40 MINUTES IN FLIGHT AT FL220, SUDDEN POP AND RT WINDSHIELD FRACTURED.  PRESSURIZATON WAS RAPIDLY REDUCE, DESCENT TO 800	0 FT WAS CARRIED OUT, AFTER VERIFING THE WINDOW WAS STILL INTACT FLIGHT CONTINUEDTO DESTINATION UNEVENTFUL.					1	L	7	2 	4T	4	T	RT	A196    	E4WE				 
2005051900245	20050519	00245	NE  	2005	5	19	CA050414006      	2	20050405	G	7261	7578679	OIL FILTER      			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					ENGINE	CONTAMINATED    	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								696564			(CAN) DURING T/O ROLL OUT AT 70 KTS NR 3 ENG OIL BYPASS LIGHT ILLUMINATED.  REJECTED T/O INITIATED, A/C SLOWED, LIGHT WE	NT OUT.  RETURNED TO GATE FOR MX TO INVESTIGATE. MX INSPECTED ENG & CARRIED OUT ENG RUN WITH NO FAULT FOUND. A/C RETURNE	D TO SERVICE. A/C DEPARTED WITH NO FURTHER PROBLEMS. DURING NEXT T/O OUT, NR 3 OIL BYPASS LIGHT AGAIN ILLUMINATED & AGAI	N WHEN A/C SLOWED, LIGHT WENT OUT. ALL OTHER ENG INDICATIONS NORMAL & ELECTED TO ATTEMPT ANOTHER T/O. DURING SECOND T/O,	 BYPASS LIGHT CAME ON. RETURNED TO BLOCKS.  MX INSPECTED ENG INCLUDING OIL FILTER & FOUND FILTER CONTAMINATED. FILTER RE	PLACED & ENG RUN CARRIED OUT WITHOUT FAULT.  ACFT RETURNED TO SERVICE WITH NO FURTHER PROBLEMS DURING REMAINING FLTS.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005061700010	20050617	00010	EU  	2005	6	17	CA050414007      	1	20050413	G	2460	MS2452423	MASTER SWITCH   			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											SHORTLY AFTER BATTERY MASTER SWITCH  SELECTED "ON",  ALL POWER TO COCKPIT INSTRUMENTS AND LIGHTING SHUTDOWN COMPLETELY. 	 RESELECTION OF BATTERY MASTER' 'OFF' THEN "ON", ALL POWER RETURNED.  CYCLING SWITCH SEVERAL TIMES CAUSED NO ADVERSE EFF	ECTS.  ALL FUNCTIONS NORMAL FOR REMAINDER OF FLIGHTS.  CONTINUITY TESTING OF BATTERY MASTER SWITCH REVEALED HIGHER THAN 	NORMAL RESISTANCE.  NEW SWITCH INSTALLED.			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005051900244	20050519	00244	WP  	2005	5	19	CA050414008      	2	20050308	G	7310	31033941	LINE            			BAG   	JETSTM	JETSTM4112  	       	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) IT WAS NOTICED AFTER A FUEL NOZZLE CHANGE THAT THERE WAS FUEL LEAKING.  FUEL LEAK WAS CAUSED BY CHAFING BY THE ADE	L CLAMP THAT WAS ATTACHED TO THE TUBE ASSY.  TUBE ASSY REPLACED.  NO FURTHER PROBLEMS.					1	L	7	2 	4T	4	T	RT	A196    	E4WE				 
2005051900243	20050519	00243	GL  	2005	5	19	CA050414009      	3	20050414	G	6114	D220118	BEARING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	PROP HUB	CHIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									AN5012		(CAN) HUB P/N D2201-18, CHIPPED IN TWO PLACES AND TOOL MARK ALL IN A 1 INCH AREA ON INSTALLATION SEAL LIP. FORK P/N WORN	 BEYOND MAXIMUN/M LIMITS T/2 BEARINGS P/N DENTED BEYOND SERVICABLE LIMITS.  THESE US PARTS RETURNED TO CUSTOMER.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
2005051900242	20050519	00242		2005	5	19	CA050414010      	1	20050414	G	6120	B24914S	ROD BEARING     													HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									DJ8034		(CAN) P/N B2491-4S PC ROD GOUGED ON SPRING AREA BEYOND LIMITS, P/N A2202.  BEARING DENTED BEYOND SERVICABLE LIMITS P/N S	PRING END OF SPRING DAMAGED LEAVING A SHARP EDGE TO GOUGE PC ROD SCRAP PARTS RETURNEDTO CUSTOMER.															5	C	P33EA	 
2005051900241	20050519	00241	EU  	2005	5	19	CA050414011      	1	20050408	G	3020	SM600BA100N1	CIRCUIT BREAKER 			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					RT INTAKE HEAT	FAILED          	W				O				OTHER                   				B	H	M	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	OVER TEMP                 	TX	TAXI/GRND HDL  	1			CA											REMOTE C/B FOR INLET HEAT STAYED IN CLOSED POSITION AND WOULD NOT OPEN.  ALLOWING THE RT ENGINE INTAKE HEAT TO OPERATE W	HEN AIRCRAFT POWER WAS TURNED ON AND CAUSED AN OVERHEAT SITUATION AT THE INTAKE ITSELF.  PARTS WERE REPLACED WITH NEW AN	D AIRCRAFT WAS RELEASED WITHOUT FURTHER INCIDENT.				2	H	7	2 	4T	4	T		A41EU   	E4EA				 
2005061600227	20050616	00227	SW  	2005	6	16	CA050414012      	1	20050414	G	5531	310025	FRAME           			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											SMALL CRACKS AND LOOSE RIVETS FOUND IN FRAME AS PER SB 218 TWIN COMMANDER KIT CK175-1 INSTALLED.						1	H	7	2 	3T	4	T		2A4     	E2WE				 
2005051900240	20050519	00240	NM  	2005	5	19	CA050415001      	1	20050414	G	4940		STARTER         			BOEING	737   	737500*     	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					APU	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOGBOOK SNAG STATED THAT THE APU WOULD NOT START.  UPON INVESTIGATION IT WAS NOTED THAT THE APU STARTER HAD OVERHE	ATED AT BOTH TERMINAL CONNECTIONS.  TERMINAL ENDS AND CABLE PROTECTION HEAT DAMAGED.  NO INDICATION OF FIRE WARNING OCCU	RRED.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005051900239	20050519	00239	CE  	2005	5	19	CA050416001      	1	20050415	G	5511	053200198	SPAR            			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FRONT SPAR CRACKED CENTER SECTION AT LIGHTNING HOLE.						1	H	7	1 	3O	3	O		3A17    	E1CE				 
2005051900238	20050519	00238	EA  	2005	5	19	CA050417001      	1	20050412	G	2820	T99A38603	EJECTOR         			CNDAIR	CL600 	CL6002C10   	1390015	EA  										FUEL SYSTEM	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FUEL QUANTITY ON THE CENTER TANK INCREASES (SUSPECT FUEL LEAKAGE FROM LEFT MAINTANK).  MX FOUND LEFT PRIMARY EJECT	OR TO BE CRACKED.  REMOVED AND REPLACED LEFT AND RIGHT EJECTORS IAW CRJ AMM 28020-01 AND S/B 670BA-28-027.  PERFORMED OP	S CHECK OF LEFT AND RIGHT EJECTORS, OPS GOOD.  P/N 'ON' T99A38-606, P/N 'OFF' P/N T99A38-603, S/N 'ON' B84172, S/N 'OFF'	 B56188.			2	L	7	2 	4F			RT	A21EA   					 
2005051900237	20050519	00237	EA  	2005	5	19	CA050417002      	1	20050412	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) RIGHT WINDOW REPLACED ACCORDING AMM PROCEDURE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005051900236	20050519	00236	EA  	2005	5	19	CA050417003      	1	20050412	G	5610	NP1393222	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) F/O'S WINDOW CRACKED.  CALLED OUT TO INSPECT PER SL 56-005 REV A.  A/C FERRY FOR WINDOW CHANGE.						2	L	7	2 	4F			RT	A21EA   					 
2005051900235	20050519	00235	EA  	2005	5	19	CA050417004      	1	20050403	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) LEFT WINDOW REPLACED ACCORDING AMM PROCEDURE.						2	L	7	2 	4F			RT	A21EA   					 
2005051900234	20050519	00234	NE  	2005	5	19	CA050417005      	2	20050413	G	7421	CH34745	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CENTER CERAMIC LOOSE, PLUG REPLACED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005051900233	20050519	00233	NE  	2005	5	19	CA050417006      	2	20050414	G	7421	CH34745	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CENTER CERAMIC MISSING, BOROSCOPE OF ENGINE FOUND NO DAMAGE, IGNITER REPLACED.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005051900232	20050519	00232	EA  	2005	5	19	CA050418001      	1	20050331	G	5210	1327971	HANDLE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN CREW ARRIVED AT AIRCRAFT, THEY WERE NOT ABLE TO OPEN THE MAIN CABIN DOOR. TROUBLESHOOTING BY MAINTENANCE DISC	OVERED THE HANDLE CRACKED IN TWO LOCATIONS ON THE SHAFT.  THE ONE CRACK WAS ALMOST COMPLETELY AROUND THE CIRCUMFERANCE O	F THE SHAFT. IPC REF 52-11-03 FIG.4 ITEM 140.  THE DOOR HANDLE ASSEMBLY P/N H3414-33 WAS REPLACED.  THIS EVENT APPEARS R	ELATED TO SDR 20050215008 FOR SEIZED MAIN CABIN DOOR PIVOT FITTINGS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061600226	20050616	00226	CE  	2005	6	16	CA050418002      	1	20050409	G	5311		BULKHEAD        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25839	25839							AFT PRESSURE BULKHEAD FOUND CRACKED AT INTERSECTION OF FRAME 50-440014-595.  PATCH MADE AND INSTALLED.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005051900231	20050519	00231	SO  	2005	5	19	CA050418003      	2	20050408	G	7314		GASKET          			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					FUEL PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								174695R			(CAN) FUEL PUMP LEAKING FROM REAR GASKET.  NOTICED ON 50 HOUR INSPECTION.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005071300045	20050713	00045	CE  	2005	7	13	CA050418004      	1	20050411	G	2820	050011874	LINE            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 200 HOURS INSPECTION, FUEL LINE ASSEMBLY FROM UNION TO FUEL STRAINER FOUND WORN (DAMAGED) BY NOSE STEERING 	PUSH/PULL ROD ASSY. NOTE: SAME DAMAGED FOUND PREVIOUSLY WHICH SDR WAS PRODUCED IN FEBRUARY 11, 2005.  NEW FUEL LINE ASSY	 SUPPLY BY MFG SEEM TO HAVE A BETTER CLEARANCE FT BETWEEN PARTS.  SUSPECT NOSE STEERING TUBE ASSEMBLY WHEN BALL JOINT AT	TACHMENT BECOME WORN/EXCESSIVE PLAY. RUB AGAINST FUEL LINE.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005061600224	20050616	00224	CE  	2005	6	16	CA050418005      	1	20050413	G	3260	6070843004	INDICATOR       			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  					MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			AP	APPROACH       	1			CA											TEST FUNCTION OF LIGHT ASSY STUCK IN TEST MODE, CAUSING FALSE COCKPIT GEAR DOWN  INDICATION, DURING AN ABNORMAL GEAR EXT	ENSION FROM A GEAR MOTOR FAILURE.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005051900230	20050519	00230	SW  	2005	5	19	CA050418006      	1	20050404	G	6420	204010775003	HOUSING         	BELL        		BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					T/R CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DIFS43					(CAN) DURING INSPECTION THE TAIL ROTOR CONTROL WAS REMOVED AND INSPECTED FOR WEAR.  WEAR WAS FOUND BEYOND LIMITS IN THE 	HOUSING. THIS ITEM IS A 1000 HOUR OVERHAUL INTERVAL.					1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2005061600023	20050616	00023	SW  	2005	6	16	CA050418007      	1	20050411	G	2430	AN30251	RELAY           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					RCR	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											ON SHUTDOWN ENGINE CONTINUED TO MOTOR OVER SLOWLY.  CONTACTS STUCK. RCR REPLACED AND PROBLEM SOLVED.						1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2005061600022	20050616	00022	SW  	2005	6	16	CA050418008      	1	20050408	G	7600		NUT             	GLOBE       		BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					LINEAR ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						9366					UPON INSP NOTICED CRACKED JAN NUT ON LINEAR ACTUATOR.						1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2005061600021	20050616	00021	EU  	2005	6	16	CA050418009      	1	20050413	G	2822	P94B12203	PUMP            			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					FUEL BOOST	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											BOOST PUMP INOPERATIVE.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005051900229	20050519	00229	CE  	2005	5	19	CA050418010      	1	20050407	G	7603	718256	THROTTLE CABLE  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											LEFT THROTTLE WOULD NOT STAY IN DETENT WAS REPORTED BY FLIGHT CREW. THROTTLE FORCE CHECK FAILED AND AFT CONTROL CABLE WA	S DETERMINED FAULTY.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005051900228	20050519	00228	CE  	2005	5	19	CA050418011      	1	20050417	G	7603	718256	THROTTLE CABLE  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	DAMAGED         	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											PILOTS REPORTED LT THRUST LEVER SPLIT (AFT) IN T/O DETENT.  FOUND AFT THROTTLE CABLE EXTREMLY STIFF.  THIS WAS SECOND OC	CURENCE TO THE COMPANY IN A WEEK FIRST SUBMISSION ON SDR NUMBER 20050418010					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061600222	20050616	00222	SO  	2005	6	16	CA050418013      	1	20050415	G	5524	110321001	ANGLE           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						MC110310					INSP REVEALED CRACK ON LT ELEVATOR TRIM TAB ACTUATOR SUPPORT BRACKET ATTACH POINT REINFORCING ANGLE.  CRACK  FOUND AT UP	PER LT SUPPORT BRACKET BOLT HOLE AND PROPAGATED TO RIVETS DIRECTLY ADJACENT TO HOLE ON BOTH LT AND RT SIDES.  UPON FURTH	ER INVESTIGATION  SMALL CRACK  FOUND ON  ELEVATOR FRONT SPAR AT SAME BRACKET ATTACH BOLT HOLE.  NEW ANGLE  INSTALLED AND	 SPAR  REPAIRED IAW  APPLICABLE SRM.  NOTE:   EMBRAER  ISSUED S.B. 110-055-0026 WHICH INTRODUCES THICKER REINFORCING ANG	LES IN THIS AREA TO PREVENT THESE CRACKS FROM OCCURRING.  THESE THICKER ANGLES WERE PREVIOUSLY INSTALLED BUT CRACKED REG	ARDLESS.	1	L	7	2 	4T	4	T		A21SO   	E4EA				 
2005051900227	20050519	00227		2005	5	19	CA050418014      	4	20050418	G	6122	6505458	ROTARY ACTUATOR 	ALLSN       		LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  					PROPELLOR	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	J		INADEQUATE Q C            	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AT EIGHT THOUSAND FEET WHILE SLOWING THROUGH 160 KTS, ON THE TC CHECK RIDE, NR 3 PROP OVERSPEED TO 14,550 ERPM.  T	HE ENGINE WAS SHUT DOWN AND PROP FEATHERED.  THE A/C RETURNED TO CYQF AND LANDED WITHOUT INCIDENTS.  MAINTENANCE FOUND R	OTARY ACTUATOR DRIVEN PAST LIMITS.  UNIT REPLACED, ALL GROUND RUNS PERFORMED AND NO FAULTS FOUND.				2	L	7	4 	4T	4	T		4A22    	E282				 
2005061500146	20050615	00146	SW  	2005	6	15	CA050418015      	1	20050412	G	6210	212015501115	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR	DAMAGED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											ON DESCENT, HEARD SOUND SIMILAR TO WHISTLE & HEARD SOUNDS DURING RT BANK ON APPR.  A/C SHUTDOWN,  INSP M/R BLADES & STAB	 BAR FOR CAUSE OF NOISE.  SUSPECT BLADE TAPE ON STAB BAR LOOSE.  NO DEFECTS FOUND.  NO FURTHER NOISE APPARENT. APPROX 1-	2 MINS INTO NEXT FLT, A/C RETURNED,  VIBE LEVEL INCREASED WITH FEEDBACK THROUGH CONTROLS & AIRFRAME OF VERT.   DIFFERENT	 NOISE WITH INCREASED VOLUME HEARD DURING APPR.  A/C LANDED, SHUTDOWN,  REPORTED INCREASE VERT VIBE LEVEL IN A/C WITH VI	BE IN CONTROLS DECIDED TO RETURN & SHUTDOWN.  INSP REVEALED UPPER SKIN NEAR OUTBOARD TIP HAD LIFTED AFT ABRASION STRIP. 	 AREA AFFECTED APPROX 4 INCHES BY 2 INCHES.  ADHESIVE SEPARATED CLEANLY.  NO VISIBLE CORROSION OR AUDIBLE DELAMINATION.	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005061500136	20050615	00136	EA  	2005	6	15	CA050418016      	2	20050417	G	7414	4371T	MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L4242927A			(CAN) AIRCRAFT EXPERIENCED A ROUGH RUNNING ENGINE.  RT MAGNETO FOUND TO BE UNSERVICABLE.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005051900226	20050519	00226	NE  	2005	5	19	CA050419001      	2	20050404	G	7320	312064401	HYDROMECH UNIT  			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ENGINE	INOPERATIVE     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE CREW SHUT THE ENGINE DOWN IN FLIGHT.  TH	E HYDROMECHANICAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005051900224	20050519	00224	EA  	2005	5	19	CA050419003      	2	20050329	G	7314		DRIVE ASSY      			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  					FUEL PUMP	INOPERATIVE     	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN.  TROUBLESHOOTING REVEALED A WORN FUEL PUMP DRI	VE.  THE FUEL PUMP WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3T	3	T		3A20    	E4EA				 
2005061500135	20050615	00135	CE  	2005	6	15	CA050419004      	1	20050406	G	5610	5042006935	WINDSHIELD      			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DELAMINATION OCCURRING ON UPPER RIGHT HAND CORNER OF WINDSHIELD.  HAD NO EFFECT ON PILOT VISION OR STRUCTURE OF WI	NDSHIELD.  REMOVED DUE TO UNKNOWN ADVANCE OF FURTHER DELAMINATION.  WINDSHIELD WAS JUST UNDER 5 YEARS IN SERVICE.  BEECH	CAFT AND PPG SHOULD DESIGN A MORE RELIABLE WINDSHIELD.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005051900223	20050519	00223	NE  	2005	5	19	CA050419005      	2	20050408	G	7321	304589603	FUEL CONTROL    			AGUSTA	A109  	A109E       	0260119	EU  	PWC   	PW206C	PW206C      		NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION TO IDLE SPEED.  THE FUEL CONTROL UNIT (FMM) 	WAS SUBSEQUENTLY REPLACED.					1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
2005051900222	20050519	00222	NE  	2005	5	19	CA050419006      	2	20050412	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PC0549			(CAN) DURING CRUISE, THE ENGINE EXHIBITED A LOUD NOISE ACCOMPANIED BY A LOSS OF POWER.  THE AIRCRAFT DIVERTED AND A DEAD	-STICK LANDING WAS ACCOMPLISHED.   INITIAL INVESTIGATION REVEALED A FRACTURED REDUCTION GEARBOX HOUSING AND POWER TURBIN	E BLADES WITH LOSS OF CONTINUITY BETWEEN PROPELLER AND POWER TURBINE.  MFG WILL INVESTIGATE THE INCIDENT AND WILL ADVISE	 OF ROOT CAUSE, ONCE DETERMNED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005051900221	20050519	00221	NE  	2005	5	19	CA050419007      	2	20050402	G	7200		ENGINE          								PWA   	PT6   	PT6A25      	52043	NE  						MALFUNCTIONED   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								26323			(CAN) DURING A MAINTENANCE FLIGHT, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE PILOT WAS UNABLE TO MODUL	ATE POWER AND SUBSEQUENTLY SUCCESSFULLY EJECTED FROM THE AIRCRAFT.  MFG WILL MONITOR THE INVESTIGATION OF THIS INCIDENT 	AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED.									3	T			E4EA				 
2005051900220	20050519	00220	NE  	2005	5	19	CA050419008      	2	20050416	G	7261		CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	FAILED          	W				F	G	A		ACTIVATE FIRE EXT.      	O2 MASK DEPLOYED        	UNSCHED LANDING         		K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA								GEE950240			(CAN) ON ROTATION F/A REPORTED SMOKE IN THE CABIN.  THIS WAS FOLLOWED BY TOILET SMOKE MESSAGE.  CREW THEN NOTICED SMOKE 	IN THE COCKPIT.  CREW DONNED MASKS, AND DUMPED PRESSURIZATION.  THEN RECEIVED A CARGO SMOKE MESSAGE, AND BLEW CARGO FIRE	 BOTTLES.  AFTER LANDING, A/C PERFORMED A RAPID PASSENGER DEPLANEMENT.  MX DISCOVERED SEVERE OIL LEAK AND OIL SEAL RETAI	NING SPRING SHOWING ON NR 2 ENGINE.  FURTHER INVESTIGATION DISCOVERED THAT THE CARBON SEAL OF THE NR 1 BEARING SEAL S /N	 STA6270B HAD FAILED.  BEARING SEAL WAS REPLACED.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500134	20050615	00134	EU  	2005	6	15	CA050419009      	1	20050418	G	7603	MS202194	PULLEY          			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE331*     	01514	WP  					POWER LEVER	BINDING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) ACFT DEPARTED & RETURNED WITH PRECAUTIONARY ENGINE SHUTDOWN DUE TO JAMMED POWER LEVER.  MX ABLE TO DUPLICATE SYMPT	OMS. POWER LEVER CIRCUIT INSPECTED & IN RT SIDEWALL AT PULLEY ASSY, A SMALL SCREW NR 4 DIAMETER .375 INCH LONG FOUND IN 	IMMEDIATE VICINITY. SCREW MOVED TO PULLEY & SYMPTOMS WERE DUPLICATED.  INSPECTION OF AREA & CONDITION OF SCREW SHOW THAT	 SCREW NOT PART OF CURRENT AIRFRAME.   AS A PRECAUTION LT POWER CIRCUIT INSPECTED FOR FOREIGN OBJECTS AROUND THE PULLEY 	CLUSTER NONE WAS FOUND.  INDEPENDENT CONTROL CHECK WAS CARRIED OUT, AND THE AIRCRAFT WAS RELEASED FOR TEST FLIGHT WITH N	O FURTHER OCCURRENCE.  PICTURES OF SCREW AVAILABLE UPON REQUEST.	2	H	7	2 	4T	3	T	RT	A16EU   	E2WE				 
2005061500133	20050615	00133	EA  	2005	6	15	CA050419010      	1	20050415	G	2420		GROUND STUD     			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					TRU	CORRODED        	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) AT 15000 FT, AN ELECTRICAL AND/OR DATA INTERRUPTION OCCURRED WHICH RESULTED IN A SIMULTANEOUS LOSS OF FLAPS & PILO	T PFD & MFD TO FLICKER.  FLAPLESS LANDING COMPLETED WITHOUT FURTHER INCIDENT.  TROUBLESHOOTING REVEALED CORROSION ON GRO	UND STUD LOCATED IN TRU BAY, ON RADOME BULKHEAD.  DURING INVESTIGATION DISCOVERED GROUND STUD BONDING SURFACE & TORQUE V	ALVE HAS BEEN MODIFIED & TORQUE CHANGES WERE NOT IMPLEMENTED.  INADEQUATE BONDING SURFACE & IMPROPER TORQUE VALVE OF GRO	UND STUDS CONTRIBUTED TO CREATE CORROSION.  BONDING SURFACE OF TRU GROUND STUDS MAIN BATTERY GROUND STUD HAS BEEN ENLARG	ED AND THE TORQUE VALVE OF THE ABOVE MENTIONED GROUND STUDS INCREASED.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005061500132	20050615	00132	SW  	2005	6	15	CA050419011      	1	20050419	G	5751	250000167166	SPAR            			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING SB-238 CRACKS WERE FOUND AROUND THE ANCHOR NUTS, ON THE SPAR CENTER HINGE ATTACH.  BOTH LEFT AND RIGHT	 HAND AILERONS, TWIN COMMANDER KITS SB238-503 AND -504 WERE INSTALLED.					1	H	7	2 	3T	4	T		2A4     	E2WE				 
2005061500131	20050615	00131	SW  	2005	6	15	CA050419012      	1	20050419	G	5751	250000167166	SPAR            			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING S.B. 238 CRACKS WERE FOUND AROUND THE ANCHOR NUTS, ON THE SPAR CENTER HINGE ATTACH.  BOTH LEFT AND RIG	HT HAND AILERONS, TWIN COMMANDER KITS SB238-503 AND -504 WERE INSTALLED.					1	H	7	2 	3T	4	T		2A4     	E2WE				 
2005051900219	20050519	00219		2005	5	19	CA050420001      	4	20050419	G	2330	BACC18AC5	CIRCUIT BREAKER 			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					LIVE TV SYSTEM	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) CIRCUIT BREAKER, RT ZONE FEED (P6-4 A10) FOR LIVE TV HAD 2 OCCURANCES OF (FOUND POPPED).   MAINTENANCE INVESTIGATI	ON FOUND EVIDENCE THAT SCREWS ON LINE FEED TERMINALS HAD CONTACTED ADJACENT STRUCTURE.  THE CB WAS REPLACED AND SHORTER 	SCREWS WERE INSTALLED.   Q.C. INITIATED A FLEET CAMPAIGN TO REPLACE ALL -7 SCREWS (AS PROVIDED BY MFG) WITH -5 SCREWS , 	RECORD ANY DEFECTS FOUND AND RECOMMEND FURTHER ACTION IF NESSESSARY.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005061500130	20050615	00130	CE  	2005	6	15	CA050420002      	1	20050420	G	5743	12410141	SUPPORT         			CESSNA	210   	210         	2073402	CE  	CONT  	O470  	IO470E      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OUTBOARD AFT WEB OF LEFT OUTBOARD LANDING GEAR SUPPORT FOUND CRACKED WHILE REPLACING LANDING GEAR PIVOT ASSEMBLY.						1	H	7	1 	3O	3	O	RT	3A21    	3E1	5	C	P3EA	 
2005061500129	20050615	00129	SO  	2005	6	15	CA050420003      	1	20050418	G	5540	4A3441	HINGE BRACKET   			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE MAINTENANCE INSPECTION, A CRACK WAS FOUND ON THE RUDDER UPPER HINGE BRACKET.  THIS BRACKET IS ATT	ACHED TO THE RUDDER FRONT SPAR AND ATTACHED TO THIS ARE TWO FLANGES FOR THE RUDDER UPPER HINGE BOLT.  THE CRACK ON THE B	RACKET EXTENDS FROM A DRAIN HOLE ON THE UPPER LEFT SIDE OF THE BRACKET THROUGH TWO RIVET HOLES, RIVETS WHICH RETAIN THE 	UPPER HINGE FLANGE, TOWARDS A DRAIN HOLE ON THE RIGHT SIDE OF THE BRACKET.  A NEW BRACKET WILL BE INSTALLED.  ATTACHED A	RE PICTURES WHERE THE CRACKS CAN BE SEEN.		1	L	7	2 	4T	4	T		A21SO   	E4EA				 
2005051900218	20050519	00218	NE  	2005	5	19	CA050420004      	2	20050417	G	7200		ENGINE          			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 1	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGH APPROX 17,000' AT 320 KIAS, WITHOUT WARNING, A BANG WHICH CAUSED ACFT TO SHUDDER FOLLOWED BY VIBR	ATION & A HOWLING NOISE NR 2 ENG VIBRATION INDICATOR READING IN EXCESS OF 2 UNITS, EGT & OIL TEMP STARTED TO RISE, & ALS	O A DROP IN EPR.  ACFT LEVELED OFF & THRUST REDUCED ON BOTH ENGINES. CARRIED OUT ENG SEVERE DAMAGE QRC. ADVISED ATC  OF 	PROBLEM WITH AN ENG & THAT IT HAD BEEN SHUTDOWN & REQUESTED CLEARANCE BACK TO BASE.   ASKED EMPLOYEE ABOARD TO LOOK OUT 	WINDOW AT ENGINE.  THE QRC REFERENCE ITEMS CARRIED OUT.  DECLARED AN EMERGENCY. NR 1 ENGINE INOPERATIVE LANDING CHECKLIS	T CARRIED OUT.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005061500128	20050615	00128	EA  	2005	6	15	CA050420005      	1	20050415	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ON CO-PILOT'S WINDOW, 2 CRACKS ON THE INNER LAYER FROM LOWER TO UPPER SIDE OF WINDOW, A 3RD CRACK APPEARED LATER. 	 THE WINDOW WAS REMOVED AND REPLACED IN ACCORDANCE WITH THE AMM.  THE WINDOW WAS AN OLDER CONFIGURATION.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005051900217	20050519	00217	NM  	2005	5	19	CA050421001      	1	20050418	G	3220	82103	LINK            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) AN OPERATOR HAS SUFFERED DAMAGE THEIR AIRCRAFT AS A RESULT OF AN NLG-UP LANDING.  THE PRELIMINARY INVESTIGATION HA	S REVEALED THAT LINK HAS FAILED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005061500127	20050615	00127	SW  	2005	6	15	CA050421002      	1	20050420	G	3234	790231509	SELECTOR VALVE  			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					MLG	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING ACCOMPLISHMENT OF THE FLIGHT IDLE CHARACTERISTIC CHECK ON THE AIRCRAFT, THE CREW WAS UNABLE TO MOVE THE LAN	DING GEAR SELECTOR TO THE DOWN POSITION.  AFTER SEVERAL UNSUCCESSFUL ATTEMPTS TO MOVE THE SELECTOR THE SIDE PEDESTAL COV	ER WAS REMOVED TO ACCESS THE GEAR SELECTOR VALVE. WITH PRESSURE DOWN ON THE GEAR SELECTOR AND THE VALVE ARM TOGETHER, TH	E VALVE MOVED FROM GEAR UP TO GEAR DOWN POSITION AND THE LANDING GEAR EXTENDED.  THE LANDING GEAR WAS LEFT IN THE DOWN P	OSITION AND THE AIRCRAFT RETURNED TO THE AIRPORT AND LANDED. THE VALVE HAD BEEN REPLACED DURING THE ANNUAL INSPECTION AN	D A GEAR SWING WAS COMPLETED AND THE LANDING GEAR FUNCTION CHECKED NORMALLY. WITH SYSTEM HYDRAULIC PRESSURE ON THE VALVE	1	H	7	2 	3T	4	T		2A4     	E2WE				 
2005051900216	20050519	00216		2005	5	19	CA050421003      	1	20050417	G	3246	MS2000526	BOLT            																	MLG	FRACTURED       	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TIE BOLT FOUND BROKEN IN HALF IN IB RIM.  TIE BOLT CAUSED DAMAGE TO BOLT HOLE IN RIM.  RIM HALF WAS REJECTED FOR S	ERVICE ALONG WITH TIE BOLT.  ALL OTHER 5 BOLTS WERE TIGHT IN THE RIM HALFS.  TIME UNKNOWN ON BOLTS AS THEY ARE MPI EVERY	 REMOVAL.																	 
2005061500126	20050615	00126	CE  	2005	6	15	CA050421004      	1	20050421	G	5751	1185210245	YOKE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15146								(CAN) DURING STRUCTURAL INSPECTIONS, THE AILERON YOKE INSPECTION REPEATING AT 3000 HOURS WAS ACCOMPLISHED AND IT WAS FOU	ND THAT BOTH THE LEFT AND RIGHT AILERON YOKE ASSEMBLIES WERE CRACKED.  THE CRACKS EXTEND FROM THE BORE FOR SPIGOT INSERT	ION THROUGH THE OUTER CASING.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005051900215	20050519	00215	NE  	2005	5	19	CA050421005      	3	20050418	G	6110		NUT             			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									16012		(CAN) PROPELLOR DEPARTED FROM ENGINE.  BOTH MECHANICS THAT INSTALLED PROPELLOR AND TORQUED NUT, CLAIMED 720 FT LBS CALCU	LATED WITH THEIR BODY WEIGHTS ON A LEVER ARM TO THE SPLINED WRENCH AND WITNESSED THE LOCK IN PLACE.  MORE TO FOLLOW WHEN	 NUT HAS BEEN INDEPENDENTLY TESTED. BLADES WERE DESTROYED IN THIS INCIDENT AND BENT THE PILOT TUBE AS WELL.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736	 
2005051900214	20050519	00214	NE  	2005	5	19	CA050422001      	2	20050408	G	7200		ENGINE          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAYMK6118   	 	NE  					RIGHT	FAILED          	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			A			FLAME/FIRE                			CL	CLIMB          	1			CA								16012			(CAN) AFTER TAKEOFF ON CLIMB OUT THE CREW HEARD A LOUD BANG AND THE RT TGT ROSE QUICKLY. THE TOWER REPORTED FIRE FROM TH	E TAIL OF THE AIRCRAFT.  THE CREW EXECUTED THE ENGINE FIRE CHECKLIST AND RETURNED TO THE AIRPORT AND PERFORMED A SINGLE 	ENGINE LANDING.  ENGINE FAN DOES NOT ROTATE. THERE IS NO SIGN OF EXTERNAL FIRE. THE RT FIRE BOTTLE IS SHOT.  ENGINE WILL	 BE INDUCTED AT MFG ON APRIL 23RD FOR INVESTIGATION. MFG WILL BE ON SITE NEXT WEEK FOR THE INVESTIGATION.			2	L	7	2 	4F	4	F	RT	A12EA   	A25NE				 
2005061500124	20050615	00124	EU  	2005	6	15	CA050422002      	1	20050421	G	2432	501171202	POWER SUPPLY    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EMERGENCY SYS	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) PRIOR TO FLIGHT, THE PILOT IN COMMAND PLACED THE EMERGENCY PWR SUPPLY SWITCH IN THE TEST POSITION AND NOTED NO TES	T.  AFTER TROUBLE SHOOTING THE EMERGENCY SUPPLY COULD NOT BE CHARGED TO CONDUCT THE FLIGHT.  THE PC 12 USES THIS TO POWE	R THE NR 1 NAV COMM AND A STANDBY HORIZON IN THE EVENT OF AN ELECTRICAL FAILURE.  THERE IS AN ANNUAL CAPACITANCE TEST IN	 PLACE AND THIS FUNCTION WAS CONDUCTED ON AUG 9 04.  THE PWR SUPPLY WAS REPLACED WITH A CHECKED UNIT AND TESTED SERVICAB	LE.  CLOSE MONITORING IN FUTURE MAY PREVENT A LIKE FAILURE.  THESE BATTERIES ARE SEALED LEAD ACID AND POSSIBLY SHOULD HA	VE A CYCLE AND CALENDAR LIFE	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005051900213	20050519	00213	EU  	2005	5	19	CA050422003      	1	20050420	G	2897		WIRE            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					SWITCH	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  SWITCH MONITORS FUEL TEMP AT ENGINE FUEL PUMP & IS FITTED TO TFE731-3 ENGINES INSTALLED ON HAWKER 700 ACFT. ON TH	IS INSTALL SWITCH WIRES CONNECT TO AIRFRAME SUPPLIED ENGINE HARNESS THROUGH IN-LINE CONNECTORS. THESE CONNECTORS ARE NOR	MALLY ONLY DISTURBED AT ENGINE, PUMP OR SWITCH REPLACEMENT. THERE ARE NO SCHEDULED INSP, TESTS OR CALIBRATION ON THE SWI	TCH IN QUESTION, OTHER THAN VISUAL INSPECTIONS PERFORMED AS PART OF ACFT OR ENGINE ROUTINE INSP.THE WIRES CONNECTED TO S	WITCH ARE THIN & EASILY KINKED. IN THIS CASE A WIRE FOUND BROKEN AT IN-LINE CONNECTOR UNDER INSULATING CONNECTOR SHEATH.	 THIS WOULD PREVENT A COCKPIT INDICATION IN THE EVENT OF A FUEL HOT CONDITION. A NEW CONNECTOR WAS INSTALLED ON THE WIRE	2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2005061500125	20050615	00125	CE  	2005	6	15	CA050422004      	1	20050420	G	5330	2411001	SKIN            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FUSELAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			11998								(CAN) THE LOWER FORWARD SKIN SRM REF 53-28-00, FIG 4, ITEM 2, WAS FOUND WITH A 3 INCH LONG CRACK UNDER A FACTORY INSTALL	ED ADF ANTENNA THAT WAS REMOVED DURING AN AVIONICS UPGRADE.  THERE IS NO SCHEDULED REQUIREMENT TO INSPECT UNDER THE ANTE	NNA, ALTHOUGH LEARJET IS APPARENTLY PLANNING TO AMEND THE INSPECTION SCHEDULE TO REQUIRE STRUCTURAL INSPECTION UNDER SUC	H ANTENNA. THE DAMAGE WAS REMOVED AND REPAIRED WITH AN EXTERNAL DOUBLER IAW THE LEARJET STRUCTURAL REPAIR MANUAL (SRM) A	ND SPECIFIC GUIDANCE INSTRUCTIONS FROM LEARJET ENGINEERING. THE ANTENNA HAD AT SOME TIME PREVIOUSLY BEEN INCORRECTLY SHI	MMED TO THE FUSELAGE PROFILE. A SECOND ADF ANTENNA FURTHER AFT ON THE BELLY WAS REMOVED AND THE SKIN INSPECTED WITH NO D	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005061700038	20050617	00038		2005	6	17	CA050422005      	1	20050422	G	3020	P307	HINGE PIN       	FOUND       																HINGE HALF	MIGRATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING ANNUAL INSP, OPERATOR REPORTED HINGE PIN (PART NR P307) FOR  ALTERNATE AIR INTAKE DOOR MIGRATED ALLOWING HINGE PI	N, SPRING AND LOWER DOOR/HINGE HALF TO BECOME DETACHED FROM  INTAKE BOX.  PARTS  RECOVERED AND REASSEMBLED WITH BOTH END	S CRIMPED TO AVOID ANY MIGRATION.  HINGE PIN IS 0.250 SHORTER THAN  HINGE HALVES AND CRIMPED DURING MANUFACTURE TO PREVE	NT MIGRATION.  UNCLEAR WHY HINGE PIN ABLE TO MIGRATE.  POSSIBLE THAT LOOSE SPRING INGESTED INTO ENGINE OR LOOSE HINGE HA	LF MAY CREATE AIR INTAKE BLOCKAGE. OPERATORS CONTACTED, APPRISED OF INCIDENT, AND REQUESTED TO INSP AREA BEFORE NEXT FLI	GHT.  AIRCRAFT CANADA INC ENGINEERING REVIEWING. SB FORTHCOMING FOR FOLLOW UP INSP AND POSSIBLE CORRECTIVE ACTIONS.														 
2005061700037	20050617	00037	EA  	2005	6	17	CA050422006      	1	20050420	G	2820	21564087191	LINE            			CNDAIR	CL215 	CL2151A10   	1900320	EA  										FUEL SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											DURING FUELING,  FUEL BEGAN LEAKING ALMOST IMMEDIATELY, APPROX 300 LITRES IN TANK. UPON INVESTIGATION BY MAINTENANCE CRE	W, 2 INCH CRACK  DISCOVERED IN FUEL INTECONNECT AT WELDED SEAM.  NO SIGNS OF CORROSION.  MAY HAVE BEEN CAUSED BY TRAPPED	 WATER, HOWEVER NO TRACES OF MOISTURE.  MAY HAVE BEEN A WEAK WELD JOINT.  OTHER AIRCRAFT INSP BUT NO FURTHER DAMAGE NOTE	D.			2	H	7	2 	4R			RT	A14EA   					 
2005051900212	20050519	00212	GL  	2005	5	19	CA050425001      	2	20050419	G	7200		TURBINE BLADES  			EMB   	145   	EMB145ER    	3260211	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				D	Y	J	INFLIGHT SEPARATION       	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA			14145					CAE310006			(CAN) FOLLOWING A LOUD BANG, UNCOMMANDED IN FLIGHT SHUTDOWN, ENGINE FOR INVESTIGATION.  STRIP REVEALED THAT ONE HPT BLAD	ES HAS FAILED AT ROOT.  REQUESTED FOR FAILED MATERIAL TO BE RETURNED FOR FAILURE ANALYSIS.					2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2005051900211	20050519	00211	NE  	2005	5	19	CA050425002      	2	20050424	G	7260		ENGINE          			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  						LEAKING         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA								654717			(CAN) AFTER T/O, SMOKE ACCUMULATED IN THE CABIN.  THE FWD AND AFT SMOKE DETECTORS LOCATED IN THE LAVS ACTIVATED.  SUCCES	SFULLY RETURNED TO AIRPORT.  MX CARRIED OUT ENG GROUND RUNS & COULD NOT DUPLICATE DEFECT ON GROUND. A TEST FLT ORDERED &	 AND IN FLT SMOKE PRESENTED IT SELF AGAIN.  THROUGH T/S IN AIR IT DETERMINED THAT BY TURNING OFF THE A/C PACK ON 1 SIDE 	THAT SMOKE STOPPED ACCUMULATING.  ACRFT RETURNED TO AIRPORT FOR FURTHER TROUBLESHOOTING.  MX FOUND OIL IN AIR CON COALES	OR BAG WITH AFFECTED A/C PACK INOP.  ACFT FLOWN TO A NEARBY AIRPORT FOR FURTHER MX.  AN INTERNAL OIL LEAK FOUND IN ENG 6	54717 AROUND THE C1 AND C2 BEARING. THIS OIL MADE ITS WAY TO THE BLEED AIR SYSTEM AND INTO A/C PACK.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005051900210	20050519	00210	NE  	2005	5	19	CA050425003      	2	20050419	G	7497	310737101	LEAD            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					IGNITER	MISLOCATED      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) PILOTS REPORTED THAT THE RT ENGINE TAKEOFF POWER WAS LOW.  TECHNICIANS DISCOVERED THAT THE 5 O'CLOCK POSITION IGNI	TER LEAD WAS INTERFERING WITH THE FUEL FLOW DIVIDER LINKAGE.  THE IGNITER LEAD WAS REPOSITIONED AND FUNCTION CHECK OF TH	E POWER LEVERS PERFORMED.  WHEN THE IGNITER WAS CHANGED, THE INSTALLATION WAS INSPECTED AND APPEARED TO HAVE PROPER CLEA	RANCE. THE MAINTENANCE MANUAL DOES NOT HAVE ANY INSTRUCTIONS AS TO THE ORIENTATION OF THE IGNITER LEAD OR TO THE FACT TH	AT THE LEAD MAY INTERFERE WITH THE POWER LEVERS IN THE FULL POWER SETTING.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005061700036	20050617	00036	NE  	2005	6	17	CA050425004      	2	20050105	G	8530		LINK ROD        			GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985AN14B   	52008	NE  					CYLINDER	BROKEN          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											AIRCRAFT ABORTED TAKEOFF DUE TO ENGINE POWER LOSS.  ENGINE SENT FOR REPAIR AND LINK ROD FOR NR 1 CYLINDER DISCOVERED BRO	KEN AT LINK PIN END.  DAMAGE ALSO OBSERVED AT CYLINDER SKIRT.  STRIP REPORT SUGGESTS  LOSE BUSHING STARTING TO FAIL IN  	LINKROD WAS CONTRIBUTING FACTOR.				1	H	7	2 	3R	3	R		TC654   	5E1				 
2005061700035	20050617	00035	CE  	2005	6	17	CA050425005      	1	20050404	G	3233		SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA						497B					DURING APPROACH, CREW SELECTED GEAR DOWN AND NOTED THAT NOSE GEAR DID NOT INDICATE DOWN AND LOCKED.  CREW USED EMERGENCY	 LANDING GEAR EXTENSION SYSTEM AND FLEW BY  TOWER FOR GEAR POSITION CONFIRMATION.  GPWS SOUNDED A CONTINUOUS WARNING BEL	OW 1500 FEET UNTIL LANDING.  AIRCRAFT LANDED SUCCESSFULLY WITHOUT FURTHER INCIDENT.  MAINTENANCE CREWS DETERMINED THAT N	OSE GEAR ACTUATOR INTEGRAL MICROSWITCH HAD FAILED AND UNIT WAS REMOVED.  A SERVICEABLE NOSE GEAR ACTUATOR WAS INSTALLED 	AND AIRCRAFT WAS RETURNED TO SERVICE.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005061700034	20050617	00034	CE  	2005	6	17	CA050425006      	1	20050406	G	3233	99121202	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NLG ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA						519					FOLLOWING TAKEOFF AND AFTER SELECTING GEAR UP, GEAR FAILED TO LOCK UP.  CREW SELECTED GEAR DOWN AND RETURNED TO LAND WIT	HOUT INCIDENT.   AIRCRAFT FERRIED WITH GEAR DOWN.  MAINTENANCE DETERMINED  NLG ACTUATOR HAD FAILED.  A SERVICEABLE ACTUA	TOR WAS INSTALLED AND AIRCRAFT RETURNED TO SERVICE. THIS IS  SECOND FAILURE OF THIS SAME ACTUATOR SINCE AUGUST 2002.  TH	E FIRST FAILURE OCCURRED AT 8375 TCSN, AND 375 TCSO.  SECOND FAILURE OCCURRED AT 9060 TCSN AND 685 TCSO.   ACTUATOR IS B	EING RETURNED  FOR INSP.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005061700033	20050617	00033	EA  	2005	6	17	CA050425007      	1	20050425	G	2150	78279015	ACM             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											WHEN RT PACK SELECTED MANUAL TO INCREASE HT IN CABIN AT FL350 RT PACK TEMP RUN AWAY.  DASH LINES DISPLAYED ON PACK 2 ON 	ECS PAGE.  F/A ADVISES CABIN GETTING SMOKE.  RT PACK SELECTED TO AUTO FULL COLD.  A/C DESCENDED TO FL240.  RT PACK RECYC	LED.  SMOKE DISSIPATED.  RT ACM REPLACED PER AMM 21-51-10 OPERATION CHECKED OK.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005051900209	20050519	00209	GL  	2005	5	19	CA050425008      	3	20050421	G	6112	4E16013	BOOT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP DE-ICE	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									DJ9291A		(CAN) RT PROPELLER MISSING A DE-ICE BOOT. DISCOVERED DURING ROUTINE CHECK. NEW DE-ICE BOOT INSTALLED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005051900208	20050519	00208	EU  	2005	5	19	CA050425009      	1	20050424	G	7603	4261212A	PUSH-PULL CABLE 			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					THROTTLE	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE AT 340, AFTER 2.5 HRS IN FLIGHT, NR 2 ENGINE THROTTLE JAMMED.  QRH APPLIED WING ANTI-ICE SELECTED.	   AFTER CRUISING AT 260, THROTTLE CONTROL RECOVERED AND NORMAL OPERATION UP TO FL 360 AND THE REMAINING OF THE FLIGHT. 	 THROTTLE CONTROL VERIFICATION CARRIED OUT ON ARRIVAL AND FOUND THROTTLE OPERATION NORMAL, FREE AND NO BINDING.  NR 2 EN	GINE THROTTLE PUSH-PULL CABLE ASSY REPLACED AS PRECAUTIONARY DUE FOUND MOISTURE BETWEEN PROTECTIVE SHIELDS.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2005051900207	20050519	00207	NE  	2005	5	19	CA050425010      	2	20050404	G	8530		CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								18796			(CAN) HEAD SEPARATED FROM BARREL CAUSING SOME ENGINE POWER LOSS AND ROUGHNESS. PILOT LANDED PLANE ALONG ROUTE. CYLINDER 	ASSY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005051900206	20050519	00206	NE  	2005	5	19	CA050425011      	2	20050425	G	8530		CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								14452			(CAN) DURING ROUTINE INSPECTION, NR 9 CYLINDER HEAD WAS FOUND CRACKED. CRACK WAS LOCATED ON VERY TOP OF HEAD ON A LINE T	HAT WOULD CONNECT FRONT AND BACK SPARK PLUGS.  CYLINDER WAS REPLACED AND AIRCRAFT INSPECTION COMPLETED AND AIRCRAFT RETU	RNED TO SERVICE.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005061700032	20050617	00032	SW  	2005	6	17	CA050426001      	1	20050425	G	6730	206075606210	ACTUATOR        			BELL  	407   	407         	1182206	SW  										SERVO	FAULTY          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						HR705					PILOT VALVE WOULD ONLY MOVE IN ONE DIRECTION.  LIFTED UP (DUST CAP) BOOT TO LOOK AT PILOT VALVE ROD AND FOUND LOCKING ME	CHANISM LOOSE AND ABLE TO ROTATE.  SERVO PISTON WOULD NOT MOVE IN ANY DIRECTION.					1	G	7	1 	3U			O	H2SW    					 
2005051900205	20050519	00205	EU  	2005	5	19	CA050426002      	1	20050411	G	2434	10300311	SENSOR          	AUXILEC     		AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					NR 2 DC GEN	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA						2286					(CAN) AFTER DEPARTING YZF, THE NR 2 DC GENERATR WENT OFF LINE AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  MAINTENA	CE DETERMINED THE NR 2 HALL EFFECT SENSOR HAD FAILED.  THE UNIT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE AF	TER SATISFACTORY FUNCTION TEST.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005051900204	20050519	00204	NM  	2005	5	19	CA050426003      	1	20050420	G	3050	10607921	VALVE           			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 2 ENGINE	FOULED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER DEPARTING, THE CREW OBSERVED AN INDICATION OF ANTI-ICE SELECT FAILURE ON NR1 ENGINE. THE CREW RETURNED TO DE	PARTURE, WHERE MAINTENANCE FOUND INTERNAL PARTS FROM THE THERMOSTATIC VALVE FOR THE NR1 LT NOSE COWL ANTI-ICE HAD FOULED	 THE ANTI-ICE VALVE. THE CONTAMINATION WAS REMOVED, THE THERMOSTATIC VALVE, AND THE ANTI-ICE VALVE WERE REPLACED BEFORE 	THE AIRCRAFT WAS RELEASED FOR RETURN TO SERVICE.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005061700031	20050617	00031	CE  	2005	6	17	CA050426004      	1	20050326	G	2450	665GC02Y07	CONTROL PANEL   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RT AFT POWER DIS	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											RT GENERATOR WOULD NOT GO ON-LINE AFTER START-UP.  RT AFT POWER DISTRIBUTION PANEL REPLACED WITH REPAIRED UNIT.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061700030	20050617	00030	CE  	2005	6	17	CA050426005      	1	20050406	G	2731	6627401000007	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZ STAB TRIM	DEFECTIVE       	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											PRIMARY TRIM FAIL CAS MESSAGE APPEARS WHEN SECONDARY TRIM ACTUATED DURING PREFLIGHT CHECK.  REPLACED HORIZ STAB ACTUATOR	 WITH REPAIRED UNIT.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061700029	20050617	00029		2005	6	17	CA050426006      	4	20050313	G	3120	600591999	ACCELEROMETER   			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					LEFT	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE, STALL FAIL CAS MESSAGE APPEARED MOMENTARILY.  TROUBLESHOOTING OF THE SYSTEM LEAD TO LT ACCELEROMETER INTE	RMITTENTLY FAILING AFTER BEING POWERED FROM 30 MINUTES TO 3.5 HOURS.  LT ACCELEROMETER REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005051900203	20050519	00203	WP  	2005	5	19	CA050426007      	2	20050421	G	7321	8978017	FUEL CONTROL    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	UNRESPONSIVE    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			CA								P54019			(CAN) DURING DESCENT, FLIGHT CREW ATTEMPTED TO REDUCE POWER WITH LITTLE TO NO RESPONSE. POWER LEVER HAD TO BE BROUGHT BA	CK ALMOST TO FLIGHT IDLE BEFORE ENGINE RESPONSE WAS OBTAINED, RESPONSE WAS SUDDEN AND ABRUPT.  AC LANDED WITHOUT INCIDEN	T. UPON INSPECTION ALOT OF FREE PLAY WAS NOTED IN POWER LEVER AND INSPECTION OF FUEL CONTROL MANUAL FUEL VALVE. ABNORMAL	 MOVEMENT OF CONTROL SHAFT WAS NOTED ON MANUAL FUEL VALVE WHEN IT WAS TURNED TO A LOW POWER/FUEL SETTING. INSTEAD OF BEI	NG A SMOOTH CONSTANT MOVEMENT, FUEL CONTROL WOULD (SNAP) TO A LOW POWER/FUEL CONDITION. THIS WAS DETERMINED TO BE AN INT	ERNAL PROBLEM WITH THE FCU.  THE FCU WAS CHANGED, DEFECT HAS NOT RETURNED. FCU SENT TO MFG FOR REPAIR.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2005061700028	20050617	00028	EA  	2005	6	17	CA050426008      	1	20050425	G	5610	NP139321002	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											DURING CRUISE IN ICING CONDITIONS, COPILOT'S WINDSHIELD DEVELOPED SPIDER WEB TYPE CRACK ON OUTER PLY.  WINDSHIELD REPLAC	ED,  AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005061700027	20050617	00027	EA  	2005	6	17	CA050426009      	1	20050422	G	5610	601R3303312	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											COPILOT'S SIDE WINDOW CRACKED DURING DESCENT.  WINDOW REPLACED.  AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005061700026	20050617	00026	EA  	2005	6	17	CA050426010      	1	20050421	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											COPILOT'S SIDE WINDOW CRACKED IN CRUISE.  WINDOW REPLACED.  AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061700025	20050617	00025	EA  	2005	6	17	CA050427001      	1	20050420	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											WHILE IN CRUISE,  COPILOT WINDSHIELD CRACKED.  WHILE REPLACING WINDSHIELD, NOTICED  CAPTAIN WINDSHIELD ALSO CRACKED. REP	LACED BOTH WINDSHIELDS. AIRCRAFT RETURNED TO SERVICE.  COPILOT WINDSHIELD: P/N NP139321-10, S/N 01046H1005.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061700024	20050617	00024	EA  	2005	6	17	CA050427002      	1	20050420	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											COPILOT'S WINDOW FOUND CRACKED.  WINDOW REPLACED,  AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2005061700023	20050617	00023	NE  	2005	6	17	CA050427003      	2	20050415	G	7261	6087T04P06	SCAVENGE PUMP   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											RT ENGINE OIL PRESSURE WARNING MESSAGE CAME ON AT FL360.  PRESSURE NEVER STABILIZED REGARDLESS OF ALTITUDE.  OIL PRESSUR	E FLUCTUATED BETWEEN 28 AND 37 PSI.  FLUCTUATION DECREASED WITH ENGINE AT IDLE. CREW SHUTDOWN  RT ENGINE INTENTIONALLY. 	 LUBE AND SCAVENGE PUMP ASSY REPLACED,  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061700022	20050617	00022		2005	6	17	CA050427004      	4	20050420	G	2215	8220259001	SERVO           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					SERVO MOUNT	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AILERON CONTROL FELT JAMMED.  AFTER ADDING PRESSURE TO AILERON CONTROL,  JAM BROKE FREE AND SEEMED NORMAL,  OCCURRED ON 	CAPT AND F/O SIDE.  COULD NOT DUPLICATE BUT AS A PRECAUTION  REPLACED AILERON SERVO AND SERVO MOUNT.  SERVO MOUNT, P/N 8	22-0259-001, S/N 404X SERVO, P/N 622-4404-101, S/N 3XGG.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005051900202	20050519	00202	EU  	2005	5	19	CA050427005      	1	20050422	G	5497		WIRE HARNESS    			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2 NACELLE	ARCED           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER DEPARTING, THE NR 2 AC GENERATOR WENT OFF LINE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REP	LACED THE GCU WHICH DID NOT RECTIFY THE PROBLEM. FURTHER INVESTIGATION REVEALED THAT ARCHING BETWEEN THE AC HARNESS AND 	THE ENGINE CASE AT THE (D) FLANGE HAD OCCURRED.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2005061700021	20050617	00021	EU  	2005	6	17	CA050427006      	1	20050403	G	2720	BN45991	ROD             			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					RUDDER BAR DRIVE	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											DURING TAXI NOTICED RUDDER PEDALS SLOPPY,  UPON INSP DISCOVERED  RUDDER BAR DRIVE ROD BROKEN.						1	H	7	2 	3O	3	O		A17EU   	E295				 
2005051900201	20050519	00201	EA  	2005	5	19	CA050427007      	2	20050405	G	7314		FITTING         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	FUEL PUMP	LOOSE           	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA						2104					(CAN) ENGINE LOST POWER, SUBSEQUENT INSPECTION REVEALED A LOOSE FITTING ON THE INLET SIDE OF MECHANICAL FUEL PUMP CAUSIN	G THE PUMP TO SUCK AIR, THUS DEPLETING THE FUEL TO THE CARBURETOR. THE FITTING WAS RETIGHTENED AND 'LOCK TIGHT' WAS USED	 ON THE JAM NUT, NOT THE FITTING.				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2005061700020	20050617	00020	SW  	2005	6	17	CA050427008      	1	20050401	G	6210	2040112501	BLADE           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					MAIN ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											VOID, CHORDWISE STATION 155 TO 157, HALF INCH WIDE THREE INCHES LONG.  BELL HELICOPTER VERDICT THAT BLADE STILL SERVICEA	BLE.  BHT ALLOWS VOID IN THIS AREA.  6 INCHES SPANWISE BY THE FULL CHORDWISE WIDTH OF CORE.  BLADE RETURNED TO SERVICE. 	 WILL CONTINUE TO MONITOR.				1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2005061700019	20050617	00019	EA  	2005	6	17	CA050427009      	2	20050408	G	7414	ES10382585	POINTS          	BENDIX      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ROUTINE INSP REVEALED MAGNETO TO ENGINE TIMING WAS OFF BY ABOUT 4 OR 5 DEGREES. MAGNETO REMOVED TO CHECK POINTS.  POINTS	  JUST BARELY OPENING,  NORMAL POINT GAP 0.016'.   PLASTIC/NYLON HEEL THAT RIDES ON  MAGNETO CAM  WORN DOWN.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005061700018	20050617	00018	EU  	2005	6	17	CA050427010      	1	20050422	G	5246	F50B281943200	DOOR            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					LAV SERVICE	MISSING         	W				O				OTHER                   				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		NR	NOT REPORTED   	1			CA											IN LEVEL FLIGHT, CREW REPORTED HEARING A RUMBLE LASTING 20 SECONDS.  UPON LANDING, CREW NOTICED  AFT LAVATORY SERVICE DO	OR AND  FORWARD 1/3 OF SURROUNDING BELLY PANEL MISSING. FURTHER INSP REVEALED SCORING ON SURROUNDING FAIRINGS AND  DAMAG	ED ANTENNAS.  ROOT CAUSE DETERMINED TO BE FOD THROWN FROM  NOSE WHEEL ON TAKEOFF WHICH DEFORMED PANEL ALLOWING AIR LOADS	 TO OPEN SERVICE DOOR.			2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2005051900200	20050519	00200	CE  	2005	5	19	CA050427011      	1	20050416	G	2720		RIVET           			BEECH 	18    	C18S        	1150902	CE  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	RUDDER CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT 100 HOUR INSPECTION, MOVEMENT (LINEAR) WAS NOTED ON ACTUATING LINK BUT NO MOVEMENT AT ATTACH POINTS. FURTHER IN	VESTIGATIION REVEALED UNDER SPRING LOOSE RIVETS THAT SECURE THE TWO ENDS TOGETHER VIA A RIVETED SLEEVE WERE FOUND TO BE 	LOOSE.  THIS IS HARD TO DETECT. THE FAILURE WOULD RENDER THE RUDDER TO BE DISCONNECTED.				1	L	7	2 	3R	3	R		A757    	5E1	5	C	P28EA	 
2005061700017	20050617	00017	SW  	2005	6	17	CA050427012      	1	20050410	G	3230	AN174C21A	BOLT            	ALCO        		GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	UPLOCK CYLINDER	BENT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA						8056					LT MLG FAILED TO UNLOCK.  AIRCRAFT RECEIVED DAMAGETO LT PROP AND UNDERSIDE OF FUSELAGE.						1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2005061700016	20050617	00016	CE  	2005	6	17	CA050427013      	1	20050426	G	2750	S19061	SWITCH          			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	FLAP SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											SWITCH CONTROLLING FLAP RETRACTION FAILED DURING FLAP RETRACTION AFTER LANDING.  FLAPS WERE STUCK AT APPROX 10 DEGREES. 	FAILURE INSIDE SWITCH AND APPEARS TO INVOLVE BROKEN INTERNAL MECHANISM.					1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2005061500123	20050615	00123	CE  	2005	6	15	CA050428002      	1	20050427	G	5514	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15115								WHILE PERFORMING THE INSPECTION REQUIREMENTS OF SEB 03-06, THE BRACKET WAS FOUND TO BE CRACKED.  ALL OTHER PARTS OF INTE	REST WHILE PERFORMING THIS SB WERE SERVICEABLE.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005061500122	20050615	00122	NE  	2005	6	15	CA050428003      	2	20050317	G	7421	9530175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								4408			ENGINE WOULD NOT START.  IGNITORS FOUND UNSERVICEABLE.  ORIGINALLY INSTALLED APRIL 4, 2003.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005061500121	20050615	00121	EA  	2005	6	15	CA050428004      	1	20050428	G	2434	2CM70D6A	GENERATOR       			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					DC SYSTEM	FIRE            	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA											MAINTENANCE WAS DOING A GROUND RUN, NR 2 ENGINE WAS STARTED FIRST THEN NR 1, AFTER BOTH ENGINES WERE WARMED UP A SMALL L	OAD WAS PUT ON THE GENERATORS.  FLAMES WERE NOTICED COMING FROM THE NR 2 ENGINE GENERATOR EXHAUST COOLING VENT.  THE ENG	INE WAS SHUT DOWN AND THE FIRE BOTTLES WERE SET OFF, THE FIRE WAS OUT.  THE ONLY DAMAGE AT THIS TIME IS TO THE DUCT WORK	 AND THE GENERATOR.  THE GENERATOR IS BEING SENT TO AN OVERHAUL SHOP FOR ASSESSMENT.			2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
2005061500120	20050615	00120	GL  	2005	6	15	CA050429001      	2	20050428	G	7261	23066681	BOWL            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					OIL FILTER	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											THE CEFA OIL FILTER BYPASS INDICATOR POPPED OUT.  INVESTIGATION REVEALED THE IMPENDING BYPASS INDICATOR ON THE CEFA OIL 	FILTER BOWL FELL APART.  A RETAINING CLIP BROKE AND PARTS OF IT WERE FOUND IN THE OIL SYSTEM.  SPRING, PRESSURE PLATES A	ND POPPET WERE ALSO RECOVERED.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005061500119	20050615	00119	EA  	2005	6	15	CA050429002      	2	20050413	G	8530		CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					NR 3	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											LOSS OF RIGHT ENGINE POWER IN-FLIGHT.  UNSCHEDULED LANDING, NR 3 CYLINDER SEPARATED.  THE 58 STUDS BROKE.  ENGINE REPLAC	ED BY LYCOMING TIO540A2B, S/N R11946-61, DUAL INSPECTION OF CONTROLS DONE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005061500118	20050615	00118	CE  	2005	6	15	CA050429003      	1	20050428	G	7500	1295500631	DUCT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT WING	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			12908								THE CREW HAD A BLEED AIR FAIL INDICATION IN FLIGHT, FOLLOWED PROCEDURES AND SHUT THE LT BLEED AIR VALVE OFF AND CONTINUE	D FLIGHT.  UPON INSPECTION AT A MX BASE ,IT WAS FOUND THAT THE EVA TUBING IN THE AREA OF THE DUCT HAD MELTED.  THE EVA T	UBING WAS REPLACED AND INVESTIGATION INTO WHY THE EVA TUBING MELTED RESULTED IN FINDING THE CRACKED DUCT ASSEMBLY.  THE 	MOUNTING PAD ON THE DUCT AT THE AREA OF THE CRACK IS FOR THE DUCT OVERTEMPERATURE SENSOR MOUNTING.  THE OVERTEMP SENSOR 	WEIGHS A COUPLE OF OUNCES.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061500117	20050615	00117	NE  	2005	6	15	CA050429004      	2	20050415	G	7320		EEC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	LOOSE           	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								CA0273			DURING CLIMB, AN EEC AMBER WARNING LIGHT ANNUNCIATED ACCOMPANIED BY A POPPING NOISE AND AN UNCOMMANDED ENGINE SHUTDOWN. 	 THE CREW SUCCESSFULLY RE-STARTED THE ENGINE IN FLIGHT AND PROCEEDED TO DESTINATION.  SUBSEQUENT INSPECTION REVEALED A L	OOSE ELECTRONIC ENGINE CONTROL (EEC) HARNESS CONNECTOR.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005061500116	20050615	00116	NE  	2005	6	15	CA050429006      	2	20050414	G	7200		ENGINE          								PWA   	PT6   	PT6A25      	52043	NE  						SHUTDOWN        	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								26013			DURING CRUISE, THE PILOT NOTICED OIL SMELL IN THE CABIN ACCOMPANIED BY DECREASING ENGINE OIL PRESSURE.  THE PILOT DECLAR	ED AN EMERGENCY AND COMPLETED AN UNSCHEDULED LANDING.  FOLLOWING LANDING POWER COULD NOT BE MODULATED AND THE ENGINE WAS	 SHUT DOWN.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE AIR CONDITIONER DRIVE PAD AND OUTPUT GEARSHAFT.									3	T			E4EA				 
2005061500115	20050615	00115	NE  	2005	6	15	CA050429007      	2	20050428	G	7200		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  						SHUTDOWN        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								124142			DURING CRUISE, THE ENGINE OIL PRESSURE DECREASED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT.  THE FLIGHT DIVERTED TO P	OINT OF ORIGIN.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL FILTER AND MAIN CHIP DETECTOR.  P&WC WILL INVES	TIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005061500114	20050615	00114	SO  	2005	6	15	CA050429008      	1	20050428	G	7900		WARNING LIGHT   			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	ENGINE OIL	ILLUMINATED     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								115622			DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED ACCOMPANIED BY A ROLL BACK IN ALL ENGINE PARAMETERS.  THE	 PILOT SECURED THE ENGINE AND THE FLIGHT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LE	AKAGE AND A TURBOMACHINE CHIP DETECTOR INDICATION.  P&WC WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF 	ROOT CAUSE, ONCE DETERMINED.			2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2005061500113	20050615	00113	CE  	2005	6	15	CA050430001      	1	20050428	G	2497	762720200301	FAIRLEAD        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RUDDER	ARCED           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											DURING PREFLIGHT, FOUND EVIDENCE OF MELTED FAIRLEAD.  FURTHER INVESTIGATION FOUND BOTH UPPER AFT RUDDER CABLES (P/N 7627	202003-001 AND 7627202004-001) CHAFING IN TO WIRE NR SAH0001-2AT FS 575 CAUSING ARCING BETWEEN WIRE AND CABLES WHICH IN 	TURN MELTED FAIRLEAD AT FS 581.  WIRE NR SAH0001-2 GOES FROM T3 ON LT AFT POWER DISTRIBUTION PANEL TO LT ESSENTIAL BUSES	.  TEMPORARY REPAIR OF WIRE INSULATION IAW MANUFACTURER ENGINEERING DISPOSITION WAS ACCOMPLISHED.  DAMAGE TO RUDDER CABL	ES FOUND TO BE FUNCTIONALLY AND STRUCTURALLY ACCEPTABLE FOR THE FERRY FLIGHT BY MANUFACTURER ENGINEERING DISPOSITION.  A	IRCRAFT WILL BE FERRIED TO MANUFACTURER REPAIR FACILITY.	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061500112	20050615	00112	EA  	2005	6	15	CA050501001      	1	20050429	G	2897		WIRE HARNESS    			CNDAIR	CL604 	CL604       	1900301	EA  										FUEL TRANSMITTER	SHORTED         	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											FUEL QTY IND FOR RT WING TANK INTERMITTENTLY FLICKERED, CHANGED QTY DISPLAYED & OCCASIONALLY ROLLED DOWN TO ZERO POUNDS 	OF FUEL INDICATED.    NO TRUE CONDITION OF FUEL IMBALANCE APPARENT.  INVESTIGATION REVEALED THE RED WIRE FOR NR 1 FUEL Q	TY TRANSMITTER FOR RT WING TANK HAD FRETTED ON A VENT PIPE.  INSULATION ON WIRE WORN THROUGH TO CORE WIRE STRANDS, NONE 	WERE BROKEN, AT APPROX 16 INCHES FROM TERMINAL ENDS OF WIRE HARNESS AT TRANSMITTER.  FUEL SHIFTED IN FLT, WIRE WOULD INT	ERMITTENTLY MAKE HARD CONTACT WITH PIPE, & QTY SIGNAL WOULD SHORT TO GROUND, RESULTING IN ERRONEOUS INDICATIONS.  A/C PE	RMITTED A TEMPORARY REPAIR UNTIL A REPLACEMENT WIRE HARNESS IS MADE AVAILABLE.	2	L	7	2 	4F			RT	A21EA   					 
2005061500111	20050615	00111	WP  	2005	6	15	CA050501002      	1	20050429	G	6310	C1883	SPRAG CLUTCH    			ROBSIN	R44   	R44RAVENII  	7640122	WP  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING DISASSEMBLY OF CLUTCH ASSY DUE TO LEAKAGE, IT WAS EVIDENT A EAR BROKE OFF 1 OF THE PEANUTS.  HUB TO SLEEVE FOUND 	TO BE FRETTING.  PAST HISTORY OF THE SPRAG HAS SHOWN DAMAGE TO THE CAGE AND THE PEANUTS. THE CAGE HAS BEEN UPGRADED AND 	NO FURTHER DAMAGE HAS BEEN FOUND.   WITH THE UPDATED CAGE, THE PEANUTS ARE NOW SHOWING SIGNS OF BEING THE WEAK LINK.  PI	CTURES SHOW THE BROKEN PEANUT.  SUBMITTED A REPORT TO ROBINSON HELICOPTERS.  THE CLUTCH ASSY HAS BEEN REPAIRED, NEW PART	S INSTALLED AND RETURNED BACK TO SERVICE.  THE COMPONENT SHOPMANAGER HAS IDENTIFED SMALL PITTING IN THE NON CONTACT POIN	TS OF THE PEANUT.  AS FOR THE REASON OF THE CRACKED PEANUT, FURTHER INVESTIGATION ON BEHALF OF ROBINS ON IS REQUIRED.	1	G	7	1 	3O				H11NM   					 
2005061500110	20050615	00110	NM  	2005	6	15	CA050502001      	1	20050429	G	2497		WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						SHORTED         	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											LOW SPEED CUE MESSAGE INDICATION ON TAKEOFF, THE T/O WAS ABORTED.  UPON LANDING THE CUE MESSAGE REAPPEARED ALONG WITH FA	DEC 2/DU MESSAGE.  THIS TIME THE REMAINED DISPLAYED.  MAINTENANCE REMOVED THE MFDS AND ED AND IT WAS FOUND THAT THE ED W	IRING HARNESS AT THE BASE OF CONNECTOR 7740-P2-A1 WAS CHAFED AND SHORED.  WIRING REPAIRED PER STANDARD PRACTICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005061500109	20050615	00109	EU  	2005	6	15	CA050502002      	1	20050425	G	5610	NP1752011	WINDSHIELD      			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			24828								DURING CRUISE, AT FL 380, CAPTAIN WINDSHIELD CRACKED.  QRH PERFORMED AND AIRCRAFT LANDED AT NEXT SUITABLE AIRPORT.  WIND	SHIELD INSPECTED AS PER AMM AND FOUND OUTER PANE SHATTERED.  WINDSHIELD REPLACED.					1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2005071200023	20050712	00023	EA  	2005	7	12	CA050502003      	1	20050502	G	4930		LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU FUEL FEED	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) INVESTIGATION OF FUEL LEAK FROM SHROUD DRAIN REVEALED APU FUEL LINE BROKEN AT THE CROSS ADAPTOR FUEL SHROUD, LOCAT	ED BENEATH THE CARGO FLOOR AT FS 574. CROSS ADAPTOR SHROUD REMOVED FOR APU FUEL LINE REPLACEMENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500108	20050615	00108	NM  	2005	6	15	CA050502004      	1	20050518	G	5610	NP15790213	WINDOW          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ROUTINE WALK AROUND BY MAINTENANCE PERSONAL NOTICED LT SIDE WINDOW HAD DELAMINATION.  CLOSER INSPECTION FOUND THAT THE I	NTERNAL HEATING ELEMENT HAD SHORTED CAUSING THE WINDOW TO DELAMINATE.  WINDOW REPLACED WITH SERVICEABLE IAW M/M GROUND R	UNS AND PRESSURIZATION CHECKS CARRIED OUT AND FOUND TO BE SERVICEABLE, AIRCRAFT RETURN TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005061500107	20050615	00107	NM  	2005	6	15	CA050502005      	1	20050426	G	2910	654476117	CONTROL UNIT    			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			16644								A/C 743 WAS IN CRUISE WHEN 'B' SYSTEM LOW QUANTITY LIGHT CAME ON FOLLOWED BY GAUGE GOING TO ZERO.  'B' SYSTEM LOW PRESSU	RE LIGHTS ILLUMINATED, BOTH 'B' PUMPS SELECTED OFF.  OVERHEAT LIGHTS DID NOT ILLUMINATE.  A/C WAS EN ROUTE TO YEG, ATC W	S ADVISED AND EMERGENCY VEHICLES WERE REQUESTED TO BE ON STAND BY.  THE LANDING WAS UNEVENTFUL AND THE A/C TAXIED TO THE	 GATE.  MAINTENANCE CONFIRMED THE SOURCE OF THE LEAK WAS THE 'B' SYSTEM PCU.  THE PCU WAS REPLACED AND THE AIRCRAFT RETU	RNED TO SERVICE WITH NO FURTHER DEFECTS RELATED TO THE HYDRAULIC SYSTEMS TO DATE.		2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005061500106	20050615	00106		2005	6	15	CA050502006      	4	20050502	G	2562	0010009REVC	BATTERY         	NARCO       																ELT	DISCHARGED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						13918					AT THE ANNUAL INSPECTION OF THE ELT FOUND THE BATTERY VOLTAGE AT (ZERO) 0 VDC.  BY TAPPING ON THE LOWER PORTION OF THE B	ATTERY THE VOLTAGE WOULD JUMP UP TO 14.5 VDC.  ABLE TO CONCLUDE THAT THERE WAS AN INTERMITTENT CONNECTION INTERNAL TO TH	E BATTERY.  ATTERY WAS HALF WAY THROUGH ITS TIME CYCLE.  BATTERY REPLACED WITH NEW.																	 
2005061600070	20050616	00070	CE  	2005	6	16	CA050503001      	1	20050419	G	5541	130630000607	SPAR            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15645								RUDDER TORQUE TUBE P/N 101-630010-9 LOWER ATTACH BOLTS (3) FOUND LOOSE, HOLES IN TORQUE TUBE ELONGATED.  RUDDER CONTROL 	HORN P/N 101-524059-1 DAMAGED AT CENTER ATTACH HOLE DUE BENT ATTACH BOLT, BEARING P/N MS28913-5C DAMAGED FROM BOLT.  ALL	 ABOVE PARTS REPLACED WITH NEW, BOLT P/N AN175-17A.  RUDDER SPAR CRACKED ON RT SIDE AT CENTER HINGE CLEVIS AREA - SPAR R	EPAIRED PER APPROVED BEECH FIELD REPAIR.BEECH TECH.  SUPPORT INDICATED THEY HAD FOUR OTHER 1900D AIRCRAFT THAT WERE REPA	IRED WITH THE SAME FIELD REPAIR.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061500105	20050615	00105	EA  	2005	6	15	CA050503002      	2	20050420	G	8530	LW12416	CYLINDER HEAD   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FOUND CRACKED CYLINDER WHERE CYLINDER HEAD AND CYLINDER BARREL MATE TOGETHER, CRACK WAS 4 INCHES LONG, AND LEAKING EXHAU	ST GAS ON THE NR 1 CYLINDER.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005061500104	20050615	00104	SW  	2005	6	15	CA050503003      	1	20050423	G	3213	206052111007	SADDLE          	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					RT SKID TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											2 PIECE SADDLE, CRACKED ACROSS BOLT HOLE, .250 TO EDGE AND .750 TO BEND STEP RADIUS.  FORWARD SIDE, 3RD BOLT HOLE DOWN F	ROM TOP.  PART REPLACED WITH 1 PIECE SADDLE.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005061500103	20050615	00103	GL  	2005	6	15	CA050503004      	2	20050423	G	7230	6898607	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					COMPRESSOR	SPALLED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAC43336			(CAN) ENGINE CHIP DETECTOR WARNING IN FLIGHT. 2ND WARNING LIGHT IN 6 HOURS. FINE FERROUS METAL ON PLUG. SMALL BRASS PART	ICLES IN OIL FILTER. TROUBLE SHOOTING INDICATED NR 1 BEARING.  NR 1 BEARING REMOVED, INNERRACE SPALLED 360 DEGREES, BEAR	ING SEPARATOR (BRASS) COMPLETELY DISINTEGATED IN 9 LARGE PIECES AND SEVERAL SMALL ONES. (CHIP DETECTOR ON 1ST WARNING SH	OWED 2 SMALL PARTICLES. CHIP PLUG CLEANED, AIRCRA FT HOVERED 30 MINUTES, NO WARNING LIGHT AND FUZZ FOUND ON CHIP DETECTO	R.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071200009	20050712	00009	CE  	2005	7	12	CA050503005      	1	20050502	G	3230	1013880083	SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			15069	15069							(CAN) ACFT DEPARTED TERRACE AND WHEN GEAR WAS SELECTED UP IT DID NOT OPERATE.  IT WAS CYCLED ONCE MORE WITH NO EFFECT. T	HE GEAR INDICATION SHOWED DOWN AND LOCKED SO THE CREW ELECTED TO LAND WHERE MAINTENANCE MAINTENANCE WAS AVAILABLE.  LAND	ED UNEVENTFULLY AND DURING INSPECTION BY MAINTENANCE, NO POWER WAS PRESENT AND THE GEAR MOTOR RELAY. SUBSEQUENT TROUBLES	HOOTING REVEALED A DEFECTIVE WITCH IN THE GROUND SERVICE VALVE. IT WAS REPLACED AND THE GEAR SWUNG NUMEROUS TIMES WITHOU	T FAILURE. THE AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061500102	20050615	00102	CE  	2005	6	15	CA050503006      	1	20050502	G	2820	244224151	LINE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					LT WHEEL WELL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PREFLIGHT CHECK, NOTICED FUEL SEEPING FROM LT FLEXIBLE FUEL TRANSFER HOSE LOCATED IN LT WHEEL WELL AREA.  S	EEPAGE APPEARS TO BE FROM HOSE MATERIAL AND NOT THE FITTING.  HOSE ASSY WILL BE SENT TO MFG FOR INSPECTION.  NEW HOSE WA	S INSTALLED AND LEAK CHECK OK.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061500101	20050615	00101	SW  	2005	6	15	CA050503007      	1	20050219	G	2432	G641	BATTERY         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MASTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BATTERY SPECIFIC GRAVITY CHECK AFTER CHARGING AND AFTER REMOVAL FROM AIRCRAFT NOT SERVICEABLE.  BATTERY ONLY HAS 9	.6 HOURS WILL NOT START AIRCRAFT.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005061500100	20050615	00100	CE  	2005	6	15	CA050503008      	1	20050502	G	5753		SUPPORT BRACKET 	CESSNA      		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FLAP ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  ACCOMPLISHMENT INSTRUCTIONS, FOUND FLAP ACTUATOR SUPPORT BRACKET CRACKED. SERVICE KIT SK208-158 ORDERED AOG,  WIL	L BE INSTALLED UPON RECEIPT.					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005061500099	20050615	00099	EA  	2005	6	15	CA050503009      	2	20050322	G	7313	R5A5AD1	NOZZLE          			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	FUEL INJECTOR	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT AFTER TAKEOFF, A HIGH FUEL PRESSURE READING ON THE LT ENGINE WAS NOTICED (NEEDLE TO THE REDLINE).  RE	DUCED POWER/CALLED ATC/RETURNED FOR LANDING. (SUSPECT CLOGGED FUEL INJECTOR NOZZLE.)					1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
2005061500098	20050615	00098	CE  	2005	6	15	CA050503012      	1	20050429	G	3220	NAS336CA17	BOLT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	NLG	SHEARED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											AFTER T/O & GEAR UP SELECTED, CREW HEARD A LOUD THUD IN NOSE AREA.  GEAR IND SHOWED AN UNSAFE CONDITION, GEAR SELECTED D	OWN & 3 GREENS WERE OBTAINED FOR DOWN & LOCKED.  DURING FLYBY, OBSERVED NLG TO BE PERPENDICULAR TO STRAIGHT.  DECIDED TO	 FLY TO MAIN BASE.    IT APPEARS THAT THE N/G CENTERING BOLT BROKE AT THE HEAD AND CAUSED THE CENTERING ROLLER TO BECOME	 JAMMED IN THE CENTERING CAM, NOT ALLOWING THE SPRING STRUT TO CENTER THE NOSE GEAR.  ALL OF THE DAMAGED PARTS WERE REPL	ACED, INCLUDING THE CENTERING SPRING STRUT AND GEAR SWINGS ACCOMP TO ENSURE SERVICEABILITY.  THE REMAINING 2 A/C IN THE 	FLEET WERE ALSO CHECKED AND FOUND WITH NO FAULTS.  RAYTHEON A/C HAS BEEN CONSULTED ON THE BOLT BREAKAGE ISSUE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061500097	20050615	00097	EA  	2005	6	15	CA050503014      	1	20050503	G	2710		AILERON         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					AILERON SYSTEM	DIRTY           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER T/O, RAIN CONDITIONS, CLIMBING INTO BELOW FREEZING TEMP, AILERONS BECAME STIFF. QRH CHECKS COMPLETED, FLIGHT	 CONTINUED.  REMOVED WING PANELS, INSPECTED CABLE CONDITION FOR DRYNESS, WHITE POWDER.  IF FOUND, REMOVED POWDER AND LUB	RICATE IN FULL..  INSPECT EXT AILERON PULLIES,  ATTENTION AT BOTH BPSU, AILERON PCU POSITIONS. REPLACE PULLIES IF REQUIR	ED.  EXTERIOR PULLIES INSP, NO FAULTS FOUND, PULLIES LUBRICATED. DEBRIS FOUND ON PULLIES IN RT/ LT WHEEL/WELL AREAS.  CA	BLES/PULLIES CLEANED/LUBRICATED. RESISTANCE AND FUNCTIONAL CHECK CARRIED OUT AMM 27-11-00.  RESISTANCE RESULTS WITHIN LI	MITS BREAKOUT FORCE RT AND LT (4LBS). 60 DEGREE PULL TEST RT 11 LBS- LT 10 LBS 60 DEGREE HOLD TEST RT  7 LBS- LT 7 LBS.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500096	20050615	00096	WP  	2005	6	15	CA050503015      	1	20050502	G	6210	369D21100523	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) CRACK FOUND DURING M/R BLADE TORQUE EVENT INSP. CRACK IS APPROX. 11 INCHES OUT FROM BLADE GRIP ON LOWER SURFACE OF	 BLADE. CRACK RUNS CORDWISE AND IS APPROX. 3.5INCHES LONG.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005061500095	20050615	00095	CE  	2005	6	15	CA050503016      	1	20050528	G	3222	04425051A	TORQUE LINK     			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND CRACKED ON INSPECTION, ABOUT 1 INCH FROM THE FRONT OF THE SCISSOR ON THE BOTTOM CURVE ON BOTH SIDES. CRACK W	AS ABOUT .1250 OF AN INCH LONG.					1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P47GL	 
2005061500094	20050615	00094	CE  	2005	6	15	CA050503017      	1	20050426	G	3222	04425051A	TORQUE LINK     			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND CRACKED ON INSPECTION ABOUT 1 INCH FROM THE FRONT OF THE SCISSOR ON THE BOTTOM CURVE. CRACK WAS ABOUT .1250 	OF AN INCH LONG.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2005061500093	20050615	00093	EA  	2005	6	15	CA050504001      	1	20050409	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT LT WINDSHIELD CRACKED AT 22000 FT.  CRACK TYPE IS SPIDER WEB.  ELECTRICAL SPARK OCCURRED FROM LT BO	TTOM OF THE WINDSHIELD BEFORE CRACK OCCURRED.  WINDSHIELD HEAT MSG DID NOT APPEAR.  AIRCRAFT LANDED WITHOUT INCIDENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500092	20050615	00092	EA  	2005	6	15	CA050504002      	1	20050412	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER BECOMING AIRBORNE AT 500 FT, LT WINDOW HEAT MSG APPEARED.  THERE WERE SIGNS OF SHORT CIRCUIT AT TOP OF WINDS	HIELD.  THEN WINDSHIELD CRACKING WITH SPIDERS WEB.  AIRCRAFT LANDED WITH OUT INCIDENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500091	20050615	00091	EA  	2005	6	15	CA050504003      	1	20050502	G	2740	C13045BA03	CONTROL UNIT    			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					HORIZONTAL STAB	INOPERATIVE     	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, STABILIZER TRIM AND MACH TRIM CAUTION MESSAGES GOT POSTED, COULD NOT RE-ENGAGED EITHER HORIZONTAL 	STABILIZER CHANNELS.  LANDING SUCCESSFULLY WITH FLAPS AT 20.  AIRCRAFT RELEASED BY REFERRING TO AOM254.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005061500090	20050615	00090		2005	6	15	CA050504004      	4	20050424	G	2340		INTERPHONE      			BBAVIA	7     	7DC         	2110116	SW  	CONT  	C90   	C9012F      	17009	SO  	MCAULY	1B90	1B90CM      	GL  	COCKPIT	INTERMITTENT    	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) RADIO WAS INTERMITTENT.  A 2 PLACE PORTABLE INTERCOM WAS BEING USED. PILOTS RT KNEE WAS RESTING AND PULLING ON THE	 POWER CABLE. THE POWER CABLE IS EQUIPPED WITH A LIGHTER PLUG ADAPTER. THE PULL ON THE CABLE WOULD CAUSE THE LIGHTER PLU	G TO COME LOOSE, WHEN THE PILOT MOVED HIS LEG THE INTERCOM, AND THUS THE RADIO, WOULD WORK OR NOT WORK.   THE CABLE WAS 	RE-ROUTED TO AN AREA WHERE THERE WOULD BE NO PULL ON THE CABLE. THE SYSTEM NOW WORKS FINE.			1	H	7	1 	3O	3	O		A759    	E252	5	N	P842	 
2005061500089	20050615	00089	CE  	2005	6	15	CA050504005      	1	20050419	G	7120	075100125	MOUNT           			CESSNA	180   	180D        	2072610	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK, APPROXIMATELY 1 INCH LONG, WAS DISCOVERED AT A CLUSTER WELD LOCATED UNDER THE RT REAR MOUNTING PAD. THE W	ELD THAT FAILED WAS ON THE LOWER REAR TUBING THAT RUNS LT TO RT ON THE AIRCRAFT, AND JOINS INTO THE MAIN FRAME OF THE MO	UNT (WHICH RUNS FORE AND AFT).				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P880	 
2005061500088	20050615	00088	NM  	2005	6	15	CA050504006      	1	20050503	G	2131	7638101	CONTROLLER      			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CABIN PRESSURE	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, A/C WAS CLIMBING THROUGH FL210 WHEN THE CREW NOTICED THE CABIN DIFFERENTIAL WAS AT MAXIMUM AND THE C	ABIN RATE OF CLIMB WAS EXCEEDING 3000 FPM (UP).  THEY IMMEDIATELY INITIATED A RAPID DESCENT AND STABILIZED THE CABIN ALT	ITUDE AT AN A/C ALTITUDE OF 17,000 FT.  THE A/C RETURNED AND PERFORMED A NORMAL LANDING. MAINTENANCE CARRIED OUT T/S AND	 REPLACEMENT OFTHE PRESSURE CONTROLLER.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005061500087	20050615	00087	WP  	2005	6	15	CA050504007      	2	20050427	G	7230	31028471	DIFFUSER        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P44725C			DURING ENG TEARDOWN, 1ST STAGE DIFFUSER CRACKED & BROKEN AT INTERSTAGE SEAL BORE / WALL. IT APPEARS THE WALL SECTION WAS	 MACHINED UNDERSIZE IN THIS AREA CAUSING FATIGUE CRACKS TO DEVELOP & A LARGE PORTION OF PART BROKE OFF. BROKEN PIECE FEL	L INTO REAR FACE OF 1ST STAGE IMPELLER CAUSING A LOUD INTERNAL RUBBING NOISE. ENG REMOVED FOR REPAIR. 1ST STAGE DIFFUSER	 INSTALLED IN OVERHAULED CONDITION & HAD 3625.6 HOURS TSO AT TIME OF FAILURE.  NO OTHER WORK DONE IN COMPRESSOR AREA OF 	ENGINE SINCE THE TIME OF INSTALLATION.   PIECES & SHRAPNEL FROM FAILED PART ENTERED PRIMARY GAS PATH CAUSING IMPACT DAMA	GE & RUB DAMAGE TO DOWN STREAM COMPONENTS. MAJOR RUB DAMAGE FOUND ON 1ST STAGE IMPELLER & 2ND STAGE COMPRESSOR HOUSING.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005061500086	20050615	00086	EU  	2005	6	15	CA050505001      	1	20050505	G	5753	25WF4402	HINGE           			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11805								(CAN) DURING A SCHEDULED INSPECTION, A CRACK WAS DETECTED VISUALLY, IN THE AFT, INNER MACHINED RADIUS OF THE RT FLAP OUT	ER HINGE, P.N: 25WF4402.  MPI NDT DETECTED A SECOND CRACK IN THE OPPOSITE, FORWARD RADIUS.  BOTH CRACKS RUN APPROXIMATEL	Y 5.5 INCHES IN LENGTH, AND ARE IN EXCESS OF 0.040 INCHES IN DEPTH.  PART REPLACED WITH NEW.  MANUFACTURER FIELD SERVICE	 REPRESENTATIVE NOTIFIED.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2005061500085	20050615	00085	CE  	2005	6	15	CA050505002      	1	20050416	G	5510	07326015	ATTACH BRACKET  	CESSNA      		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13459	13459							(CAN) DURING INSPECTION THE RT FORWARD STABILIZER ATTACH BRACKET WAS FOUND BROKEN JUST BELOW THE ATTACH BOLT.  STABILIZE	R REMOVED FROM AIRCRAFT BOTH FORWARD ATTACH BRACKETS REPLACED WITH NEW PARTS.  STABILIZER RE-INSTALLED.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2005061500084	20050615	00084	SO  	2005	6	15	CA050505003      	1	20050425	G	3246	16193B	WHEEL           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	MLG	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) ON LANDING PILOT REPORTED A NOISE FROM THE LT MAIN LANDING GEAR. INSPECTION FOUND THE INNER WHEEL HALF CRACKED AT 	THE BASE OF THE WHEEL FLANGE FOR APPROX 4 INCHES AND THE WHEEL FLANGE BOWED OUTWARD AND INTERFERING WITH THE BRAKE CALIP	ER. THE WHEEL ASSY WAS REMOVED AND REPLACED WITH NEW WHEEL ASSY P/N 40-120C, THE TIRE WAS ALSO DAMAGED IN THE SIDEWALL A	ND WAS REPLACED WITH A NEW TIRE. THE OTHER MAIN WHEEL ASSY AND NOSE WHEEL ASSY WHERE REMOVED DISSASEMBLED AND INSPECTED,	 NO DEFECTS WHERE NOTED AND THE WHEEL ASSY'S WHERE REASSEMBLED AND REINSTALLED.		1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P25EA	 
2005061500083	20050615	00083	CE  	2005	6	15	CA050505005      	1	20050504	G	3245	302039402	TUBE            			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TIRE	TORN            	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) UPON LANDING CREW NOTICED VIBRATION CONSISTENT WITH FLAT TIRE.  CONFIRMED AFTER SHUT-DOWN. MAINT WAS DISPATCHED TO	 REPLACE FLAT TIRE.  WHEN FLAT TIRE WAS DISASSEMBLE, NOTICED THAT INNER TUBE WAS TORN APART.  NO SIGNS OF PINCHING OR UN	USUAL WEAR WERE NOTICED.  5TH TIRE OF SAME MFG AND SIZE TO HAVE CAUSED UNSCHEDULED TIRE CHANGES. MAINT HAS BEEN INTERVIE	WED TO DETERMINE WHETHER THERE HAS BEEN A CHANGE IN MAINT PRACTICES OR IF ANYONE HAS OBSERVED ANYTHING THAT MIGHT EXPLAI	N EXPERIENCING AN INCREASE IN THE FAILURE RATE OF THESE INNER TUBES. NO CAUSES FOUND. OPERATOR HAS BROUGHT ISSUE TO ATTE	NTION OF SUPPLIER WITH A REQUEST TO NOTIFY MFG OF RETURN OF ALL REMAINING INNER TUBES FOR REPLACEMENT WITH ANOTHER.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2005061500082	20050615	00082		2005	6	15	CA050505006      	4	20050505	G	3418	0861HB	VANE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ANGLE OF ATTACK	MALFUNCTIONED   	W				B				EMER. DESCENT           				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE THE CREW HAD AN AIRSPEED INDICATOR PROBLEM AND LATER DETERMINED THE AIRSPEED WAS CORRECT, BUT THE 	BARBER POLE INDICATOR SHOWED AND THE STICK SHAKER  BECAME ACTIVE.  THE FLIGHT DECLARED AN EMERGENCY AND RETURNED TO LAND	.   THE EMERGENCY VEHICLES WERE STANDING BY FOR THE ARRIVAL.  MDC SPC CH NR 1 LBL 350 BIT 12 AND 13 SPC CH NR 2 LBL 350 	BIT 12.  LT AND RT AOA VANE CHGD IAW AMM 27-35-05-400-801, LT MACH TX CHGD IAW AMM 27-35-25-400-801.   OPERATIONAL TEST 	OF AOA LT AND RT DONE IAW AMM 27-35-05-710-801,LT MACH TX FUNCT TEST DONE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500081	20050615	00081	SO  	2005	6	15	CA050505007      	2	20050505	G	8530	AEC631397ST712A	CYLINDER HEAD   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								291018R			(CAN) ENGINE EQUIPPED WITH NEW STEEL ENGINE COPONENTS IN (ECI)CYLINDER ASSY'S P/N AEC631397ST71.2A, 606.4 HR TOTAL TIME.	  CYLINDER NR 4 WAS FOUND CRACKED IN THE CYLINDER HEAD JUST BELOW TOP SPARK PLUG HOLE. (SDR WAS ISSUED) AT 706.0 HRS CYL	INDER 2 AND 6 WERE ALSO FOUND TO BE CRACKED IN THE SAME LOCATION. ALL CYLINDERS WERE CHECKED AGAINST S/N TO COMFIRM THAT	 THEY WERE NOT AFFECTED BY ECI SB 04-1 (AD 2004-08-10) AND ALL WERE FOUND TO BE NOT APPLICABLE BY THEIR SERIAL NUMBERS. 	 AS A RESULT OF THE DISCOVERY OF THESE CRACKED CYLINDERS AND THAT ALL CYLINDERS WERE INSTALLED NEW AT ENGINE OVERHAUL.  	ALL 5 ORIGINAL INSTALLATION CYLINDERS WILL BE REPLACED WITH NEW CYLINDER ASSY.	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2005061500080	20050615	00080	CE  	2005	6	15	CA050506001      	1	20050503	G	5610	10138402516	WINDSHIELD      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) COPILOT INNER WINDOW PANE SHATTERED (LOUD BANG) DURING CRUISE AT 24,000 FT. IAS WAS 175 KNOTS , O.A.T. -32C. WINDS	HIELD ANTI-ICE SELECTED OFF.  NO LOSS OF PRESSURIZATION, CREW FOLLOWED CHECKLIST PROCEDURES FOR UNEVENTFUL LANDING.  WIN	DOW HAD DELAMINATION OCCURRING BUT WITHIN LIMITS IAW MM 56-10-00 PAGE 205.  WINDSHIELD IS BEING REPLACED.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2005061500079	20050615	00079	CE  	2005	6	15	CA050506002      	1	20050504	G	2621	516002	FIRE BOTTLE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					APU	DISCHARGED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON AIRCRAFT ARRIVAL, THE APU FIRE EXTINGUISHER BOTTLE WAS FOUND READING (0) PSI.  NEW BOTTLE ORDERED.  UPON INVE	STIGATION INTO WHY THE BOTTLE DISCHARGED, CALLED MFG AND WAS INFORMED THAT THIS IS A KNOWN ISSUE WITH THIS MODEL. THE AP	U FIRE BOTTLE HAS BEEN KNOWN TO DISCHARGE IF THE FIRE WARNING TEST BUTTON IS DOUBLE TAPPED OR HELD TO LONG.  UPON REMOVA	L OF THE APU BOTTLE IT WAS DISCOVERED THAT THE BOTTLE HAD BECOME SEPARATED FROM DISCHARGE NOZZLE.  MFG WAS INFORMED AND 	PICTURES SENT.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061500078	20050615	00078	NM  	2005	6	15	CA050506004      	1	20050416	G	3600	577957	DUCT            			BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MANIFOLD	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DUCT ASSEMBLY (13TH STAGE BLEED AIR) SEPARATED FROM FLANGE.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005061500077	20050615	00077	SO  	2005	6	15	CA050506005      	1	20050422	G	3230		PUSH-PULL CABLE 			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  	HARTZL	HCA2V	HCA2VK2     	GL  	MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AFTER EMERGENCY GEAR EXTENSION IN FLIGHT AND UNEVENTFUL LANDINGS. UNDER CARRIAGE COLLAPSED ON SUBSEQUENT TAXI. GEA	R WAS EXTENDED, PUT ON JACKS LT MAIN UNDER CARRIAGE WAS INOPERATIVE. UPON INVESTIGATION GEAR PUSH PULL CABLE WAS FOUND B	ROKEN.				1	L	7	1 	3O	3	O		1A15    	E295	5	C	P24EA	 
2005071200008	20050712	00008	EU  	2005	7	12	CA050506006      	1	20050505	G	6310	350A35105901	COUPLING        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TRANSMISSION	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STAKED WASHER ON FLECTOR WAS FOUND TO BE SEPERATED/BROKEN. THE BRAKE WAS ON OPPOSITE SIDE WHICH HAD BEEN STAKED. T	HIS WAS DISCOVERED DURING MAINTENANCE OF THE TRANSISSION INPUT RE-TORQUE. REPLACEMENT PART AND HARDWARE INSTALLED.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005061500076	20050615	00076	WP  	2005	6	15	CA050506007      	1	20050420	G	5220		DOOR            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	HAMSTD	54H	54H60       	NE  	EMERGENCY EXIT	OUT OF RIG      	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			W	D		INADEQUATE Q C            	INFLIGHT SEPARATION       		CR	CRUISE         	1			CA											(CAN) AFTER IN-FLIGHT FAILURE OF EDC AND SUSEQUENT LOSS OF PRESSURIZATION, THE RT OVER-WING EMERGENCY EXIT DOOR FELL INT	O CABIN AREA. AIRCRAFT DESCENDED TO 3000 ASL. AIRCRAFT LANDED WITH NO FURTHER INCIDENT, EDC WAS REPAIRED, EMERGENCY EXIT	 DOOR WAS INSPECTED AND FOUND OUT OF RIG. THE DOOR WAS RE-RIGGED, FUNCTION CHECKED ANDTHE AIRCRAFT WAS RETURNED TO SERVI	CE.			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2005061500075	20050615	00075	EA  	2005	6	15	CA050506008      	2	20050503	G	8520	SL13885	MAIN BEARING    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L147768A			(CAN) METAL FLAKES FOUND IN OIL SCREEN AND FILTER. AT ENGINE TEARDOWN, FOUND SL13885 FRONT MAIN BEARING DELAMINATED APPR	OX. 1 SQUARE INCH OF SURFACE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005061500074	20050615	00074	WP  	2005	6	15	CA050506009      	2	20050414	G	7314	5909242	RELIEF VALVE    	SUNDSTRANDAI		LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FUEL PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						0387					(CAN) DURING GROUND RUN WITH THE LOWER ENGINE COWLING REMOVED, THE ABOVE MENTIONED RELIEF VALVE WAS FOUND LEAKING FUEL. 	THIS WAS NOT NOTICEABLE WHEN THE COWLING WAS INSTALLED. THIS RELIEF VALVE HAD BEEN INSPECTED FOR S/B 73-5125 AT 1084.7 H	OURS WHICH SPECIFIED REPLACEMENT IF IT HAD LESS THAN 1000 HOURS BUT WAS NOT REPLACED.  INSTALLED NEW VALVE P/N 5912983 I	AW THE ABOVE S/B 73-5125.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061500073	20050615	00073	SW  	2005	6	15	CA050506010      	1	20050429	G	2497	Q2A18N	GROUND WIRE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ELECTRICAL	DISCONNECTED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF HELICOPTER FOR COMPLIANCE OF AD CF-2005-10 AND ASB206-05-103. (FUEL DISTRIBUTION SYSTEM INSPE	CTION) FOUND DISCONNECTED GROUND WIRE Q2A18N, THE WIRE WAS MOST LIKELY LEFT OFF DURING A PREVIOUS SHEET METAL REPAIR TO 	THE LANDING GEAR SUPPORT AREA. REINSTALLED GROUND WIRE TO GROUND IAW BULLETIN.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005061500072	20050615	00072	WP  	2005	6	15	CA050506011      	2	20050401	G	7230		CASE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GAS GENERATOR	CRACKED         	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) RT ENGINE FAILED TO MEET TAKEOFF TORQUE SETTING. EX ONLY GOT 90 PERCENT TORQUE ON A +7C, 1900 ASL (TRUE) DAY. SHOU	LD BE 104.5.  ON INSPECTION, IT WAS FOUND THAT THE GAS GENERATOR CASE WAS CRACKED AT THE AIRFRAME SERVICE FLANGE. ENGINE	 REMOVED AND LOANER ENGINE INSTALLED.				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2005061500071	20050615	00071	CE  	2005	6	15	CA050506012      	1	20050505	G	2621	516201	VALVE           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					APU FIRE EXTING	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						0211					(CAN) DURING TROUBLESHOOTING AN APU FAULT , IT WAS DISCOVERED THAT THE APU FIRE BOTTLE HAD DISCHARGED . WHEN THE BOTTLE 	DISCHARGED THE OUTLET VALVE'S FLANGE NUT BROKE INTO 3 PIECES AND THE FIRE BOTTLE SUPPORT BRACKET WAS BENT, WHICH CAUSED 	THE FIRE BOTTLE TO SEPARATE FROM THE OUTLET VALVE. THE FIRE BOTTLE ASSY WAS REMOVED AND NEW ASSY INSTALLED.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005061500070	20050615	00070	CE  	2005	6	15	CA050506013      	1	20050504	G	5220	551124914	THRESHOLD       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					DOOR FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSP ON AIRFRAME, THRESHOLD INSP REVEALED DAMAGE TO PAINT, FILLER WHERE MN CABIN DOOR SEAL INFLATES AGAINST.  ONCE	 STAIR BRACKETS WERE REMOVED, DEFECT NOTED AS 1 INCH CRACK FROM MAIN FASTENER HOLE ON AFT STAIR BRACKET HOLE. DEFECT WAS	 CAUSED BY IMPROPER INSTALLATION OF STAIR BRACKETS, AS THEY WERE INSTALLED WITH AFT BRACKET INSTALLED IN FWD POSITION, F	WD BRACKET INSTALLED IN AFT POSITION. DUE TO CURVED PORTION OF SKIN WHERE BRACKETS SIT, BRACKETS CONFORM TO THIS CURVATU	RE. WITH BACKWARDS INSTALLATION, INSTEAD OF LOAD BEING THROUGH A .5 INCH LAND, IT ALL CARRIED THROUGH A SHARP CORNER, WO	RKING AGAINST SKIN CREATING STRESS RISER. CURRENTLY INNER AND OUTER THRESHOLD ARE BEING REMOVED AND INSPECTED.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005061500069	20050615	00069	GL  	2005	6	15	CA050506014      	1	20050406	G	3240	MS28775218	CALIPER         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	BRAKE	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) LOSS OF BRAKE FLUID DUE TO FAILED BRAKE CALIPER.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2005071200028	20050712	00028	CE  	2005	7	12	CA050506015      	1	20050505	G	2621		NOZZLE          			LEAR  	45    	45LEAR      	5170805	CE  										EXTINGUISHER	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						0233					(CAN) UPON RECEIPT OF THE NEW FIRE BOTTLE IT WAS DISCOVERED THAT THE DISCHARGE NOZZLE WAS NOT SECURELY ATTACHED TO THE B	OTTLE AND LOCK WIRE WAS NOT PRESENT. THERE ARE NO INSTRUCTIONS IN THE MM FOR THE NUT TO BE TORQUED OR LOCK WIRE TO BE IN	STALLED. LEAR JET WAS CONTACTED AND A NEW BOTTLE IS BEING SHIPPED. THEIRSURVEY OF STOCK INDICATED THAT THERE WAS SEVERAL	 BOTTLES IN THIS CONDITION.			2	L	7	2 	4F			RT	T00008WI					 
2005061500068	20050615	00068	NM  	2005	6	15	CA050509001      	1	20050506	G	2530		OVEN            			BOEING	737   	737248C     	1384415	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					GALLEY	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DEPARTING, DURING CLIMB, SMOKE/HAZE WAS OBSERVED EMINATING FROM THE AFT CABIN AREA. THE AIRCRAFT DECLARED AN EMERG	ENCY AND RETURNED TO POINT OF DEPARTURE, LANDING WITH NO FURTHER INCIDENT.  THE SOURCE OF THE SMOKE WAS DETERMINED TO BE	 THE CONTENTS OF A GALLEY OVEN.  THE AFT SLIDES WERE DEPLOYED AND ENGINE FIRE BOTTLES WERE DISCHARGED.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2005061500067	20050615	00067	EA  	2005	6	15	CA050509003      	1	20050509	G	2820		LINE            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					TAIL TANK	CRACKED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED (TAIL TANK AUTO INHIBIT LIGHT ON) BEFORE DEPARTURE.  UPON INVESTIGATION, A CRACK ON THE TAIL TANK P	RESSURE FUEL LINE WAS FOUND.  IPC 28-13-22 ITEM 115.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500066	20050615	00066	EU  	2005	6	15	CA050509004      	1	20050509	G	3320	8ES00469210	LIGHT           			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					R1 DOOR	BURNED          	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN)  APPRO 15 AFTER TAKEOFF,  PURSER REPORTED SMOKE IN R1 GALLEY AREA, SMOKE INCREASED.  GALLEY C/B'S PULLED, ELECT SM	OKE, CARRIED OUT AND FLIGHT RETURNED TO DEPARTURE. OVERWEIGHT LANDING CARRIED OUT.  FOUND R1 DOOR F/A READING LT ASSY BU	RNED.  INSPECTION CARRIED OUT, OK OTHER DR'S CHECKED FOUND L1 DR FWD NR 1 READING LT CONNECTOR ACRING.  DEFERRED FOR WIR	ING REPL POSN L1 5046VE7 AND R1 5046VS4 WIRING REMOVED FROM BLOCK. P/P ISSUED A340-33-19640.			2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2005061500065	20050615	00065	EA  	2005	6	15	CA050509005      	1	20050506	G	3246		PLATE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SKI HARNESS	TORN            	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) UPON ENTERING CRUISE FLIGHT, THE PILOT HEARD A LOUD BANG AND FELT THE AIRCRAFT SHUTTER. HE NOTICED THAT THE RT SKI	 HARNESS HAD COME UNATTACHED TO THE UPPER WING ATTACH FITTING, LETTING THE RT SKI ROTATE UPWARD AGAINST THE WING STRUT. 	 THE PILOT TOOK MEASURES TO LAND THE AIRCRAFT AT HIS ORIGINAL DEPARTURE LOCATION.  UPON LANDING THE RT SKI DEPARTED FROM	 THE AIRCRAFT AND DAMAGE WAS SUSTAINED TO THE RT LANDING GEAR AND WING STRUT ASSEMBLY.  FURTHER INVESTIGATION IS CONTINU	ING FOR CAUSE OF SKI HARNESS ASSEMBLY DETACHMENT.		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005061500064	20050615	00064	CE  	2005	6	15	CA050509006      	1	20050509	G	5514	04310093	FITTING         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						79520					(CAN) FITTING CRACKED 90 PERCENT THROUGH, IN RADIUS BETWEEN OUTER HORIZONTAL AND VERTICAL SECTIONS.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005061500063	20050615	00063	CE  	2005	6	15	CA050509007      	1	20050509	G	2430	DOFF10300J	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING RUNUP A DISCHARGE WAS NOTICED ON AMMETER.  FURTHER INSPECTION BY AN ENGINEER CONCLUDED THAT THE ALTERNATOR 	HAD FAILED INTERNALLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005061500062	20050615	00062	EA  	2005	6	15	CA050510001      	1	20050502	G	5610	NP1393212	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			26934								(CAN) THE RT WINDSHIELD HAD THE OUTER LAYER CRACKED WHILE IN APPROACH. THE WINDSHIELD WAS REPLACED IAW AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500061	20050615	00061	NM  	2005	6	15	CA050510002      	1	20050510	G	2597	146T51451	WIRE            			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					CHILLER	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FAULT: REF L1523271 AFT CHILLER POPS CB, FOUND UPPER CHILLER WIRING BURNED AND ARCED TO BOTTOM OF FLOORBEAM .  FLO	ORBEAM AT STN 1540 , 26 INCHES RT OF CENTER LINE.  HAS HOLE BURNED THROUGH LOWER CHORD APROX .8750 INCHES WIDE , .5 INCH	 ACROSS LOWER CHORD, .2500 INCH UP FWD FLANGE. ACTION: FLOORBEAM AT STN 1562 REPAIRED IAW PP B767-53-19570.  TEMP REPAIR	 ANGLE TO BE REPLACED WITH NEW REPAIR ANGLE IAW SRM 51-70-12 FI G 1 OR FIG 2 AT NEXTM-CHECK.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005071200007	20050712	00007	CE  	2005	7	12	CA050510003      	1	20050504	G	2750	995240257	MOTOR           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					TE FLAPS	OVERHEATED      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA											(CAN) FLAP MOTOR OVERHEATNG, BURNING ODOR IN CABIN. FLAP MOTOR/GEARBOX ASSY REPLACED WITH OVERHAULED UNIT. VOLTAGE TO MO	TOR CHKD & GROUND WIRE CHKD OKAY. CHKD FLAP SYS FOR BINDING, ACTUATORS, CABLES & FLAPS OPERATED WITHOUT BINDING. SYS CHK	D FLAP MOTOR/GEARBOX ASSY, NO FAULTS NOTED. RIGGING CHKD OKAY. CONDUCTED A TEST FLT WITH FLAP MOTOR OBSERVED, FLAPS EXTE	NDED, & MOTOR RUNNING-ON, MOTOR HAD BURNING ODOR. DETERMINED IN FLT, WHEN FLAPS EXTENDED, DOWN LIMIT SWITCH ROLLER WENT 	OFF LIMIT SWITCH CAM PREVENTING FLAPS FROM STOPPING, FLAPS WENT TO END OF TRACKS & LOADED UP MOTOR. FLAP DOWN LIMIT SWIT	CH ADJUSTED. TEST FLT FAULT FREE.  PREVIOUS MOTOR REPLACED, MOTOR HAD 94.2 HOURS SINCE OVERHAUL.	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005061500060	20050615	00060	NM  	2005	6	15	CA050510004      	1	20050508	G	5600	58935733	WINDOW          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) NR 4 WINDOW CRACKED AT ALTITUDE. WINDOW REPLACED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071200006	20050712	00006	CE  	2005	7	12	CA050510005      	1	20050426	G	5753	10116001415	BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAP	TORN            	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		AP	APPROACH       	1			CA											(CAN) ON TUESDAY, APRIL 26, 2005 THIS AIRCRAFT SUFFERED A RIGHT HAND OUTBOARD FLAP FAILURE WHILE APPROACHING CYWG. THE C	REW WERE ABLE TO MAINTAIN CONTROL OF THE AIRCRAFT AND LANDED WITHOUT FURTHER INCIDENT.ON EXIT FROM THE AIRCRAFT, THE CRE	W OBSERVED NR 1, 2 AND 3 FLAPS IN THE FULL DOWN POSITION. NR 4 (RT OUTBOARD) FLAP WAS IN THE FULL UP POSITION, AND ANGLE	D OUT FROM THE WING. INVESTIGATION REVEALED TH E INBOARD GUIDE ROLLER, BOUT, WASHER AND NUT HAD BEEN TORN OUT OF BRACKET	. TO THIS DATE THE ROOT CAUSE OF THIS INCIDENT HAS NOT BEEN ESTABLISHED. FURTHER INVESTIGATION IS BEING CARRIED OUT.		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005061500059	20050615	00059	NM  	2005	6	15	CA050510006      	1	20050509	G	2432	10612243	GCU             			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 ENGINE	SHORTED         	W				H	D			DEACTIVATE SYST/CIRCUITS	RETURN TO BLOCK         			B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER STARTING THE NR 1 ENGINE, THE CREW TURNED ON POWER FROM THE NR 1 ENGINE. THEY IMMEDIATELY NOTICED SMOKE COMI	NG FROM THE GCU. THEY TURNED THE POWER OFF AND RETURNED TO GATE FOR MAINTENANCE.  MAINTENANCE SWAPPED THE NR 1 GCU WITH 	THE APU GCU AND CARRIED OUT EXTENSIVE TROUBLESHOOTING AND FUNCTION TESTS. THE GCU WAS FOUND TO BE AT FAULT.  SUSPECT INT	ERNAL SHORT CIRCUIT. THE APU GCU WAS PLACED ON MEL 24-2 AND THE AIRCRAFT RETURNED TO SERVICE. THE INOPERATIVE GCU WAS LA	TER REPLACED.  INFORMATION TO FOLLOW AFTER COMPLETION OF THE TEARDOWN INSPECTION AND REPORT FROM SHOP.		2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005061500058	20050615	00058	EU  	2005	6	15	CA050510007      	1	20050508	G	3242	200146652	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	LT BRAKE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) AFTER LANDING, THE CREW OBSERVED THE NR 1 IB BRAKE UNIT LINE LEAKING.  MAINTENANCE WAS DISPATCHED. THE LINE WAS RE	PLACED AND THE SYSTEM BLED.  THE AIRCRAFT GROUND RUN SERVICEABLE BEFORE BEING RETURNED TO SERVICE.					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005061500057	20050615	00057	NM  	2005	6	15	CA050510008      	1	20050510	G	7603		THROTTLE CABLE  			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					LEFT	MISALIGNED      	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THRU FL 130 EICAS (L PRV) QRH COMPLETED - THRU FL 200 LT THROTTLE VERY HARD TO ADVANCE OR MOVE TO IDL	E. A/T ARM OFF NO IMPROVEMENT. RETURN TO LHR. NO LT REVERSE ON LANDING.  FOR T/S AND INFO ON PRV REFER TO L1425969. LT E	NG PUSH PULL CABLE REMOVED, INSPD AND CLEANED, UPPER END OF DOVE TAIL BELOW STRUT FOUND SLIGHTLY MIS-ALIGNED, CABLE RUN 	RE-ASSBLD AND FUNC CHK SERV IAW 76-11-00-765-100-400, AUTO THROT SYST CHK SERV.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005061500056	20050615	00056	SW  	2005	6	15	CA050510009      	1	20050509	G	3230	246006	SOLENOID VALVE  	AIRIGHT     		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD POWERPACK	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA						761					(CAN) ON APPROACH THE GEAR WOULD NOT EXTEND NORMALLY.  MANUAL EMERGENCY EXTENSION WORKED AND AIRCRAFT LANDED WITHOUT INC	IDENT.  MAINTENANCE INSPECTED SYSTEM AND FOUND GEAR SOLINOID VALVE TO BE NON OPERATIONAL.  THIS VALVE ALSO CONTROLS HYD 	PRESSURE FOR THE NOSE STEERING, WITH THIS VALVE NON OPERATIONAL THE GEAR WILL NOT EXTEND AND THERE IS NO NOSE STEERING. 	 VALVE REPLACED, GEAR SWINGS AND NOSE STEERING CHECKED WITHIN MANUFACTURES SPECIFICATIONS.  AIRCRAFT RELEASED TO SERVICE	.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005061500055	20050615	00055	NM  	2005	6	15	CA050510010      	1	20050507	G	3246	296852629	BEARING         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG WHEEL	DETACHED        	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI OUT FOR TAKE OFF, THE FLIGHT ATTENDANT NOTIFIED THE CREW OF SMOKE OFF OF THE NR 1 WHEEL ASSY.  WHEN MA	INTENANCE ARRIVED THEY FOUND THE INSIDE BEARING OF THE NR 1 WHEEL ASSY DESTROYED.  INVESTIGATING THE EVENT.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005061500054	20050615	00054	EU  	2005	6	15	CA050510011      	1	20050321	G	2510	541010501	PAN             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TIME ON THIS PART IS NOT TRACKED.  CRACKED HAVE BEEN NOTICED ON CREW SEAT PANS IN A LOCATION THAT HAS NOT BEEN NOT	ED IN THE PAST.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005061500053	20050615	00053	EU  	2005	6	15	CA050510012      	1	20050324	G	3411	524111255	BRACKET         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITOT HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS NOTED DURING INSPECTIONS AT LEADING AND TRAILING EDGES OF PITOT HEAD MOUNTING BRACKETS.  MANUFACTURER SHOUL	D BEGIN CURVING THE MOUNTING PLATE TO MATCH THE UNDER SIDE OF WING.  FEEL THIS WOULD STOP THE STRESS CRACKING.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005061500052	20050615	00052	EU  	2005	6	15	CA050510013      	1	20050218	G	5540		BUSHING         			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											PLAY WAS NOTED IN THE RUDDER UPPER ATTACHMENT EVEN WITH PILATUS ECE-TM-02-327 INCORPORATED.  THE BUSHING AND BEARING BON	DING MATERIAL WAS STILL HOLDING.  THE BOLT P/N NAS1161-3-17, BEARING P/N 940.83.28.506 AND BUSHING P/N 941.20.31.550 ALL	 HAD TO BE REPLACED DUE TO WEAR.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005061500036	20050615	00036	EU  	2005	6	15	CA050510014      	1	20050223	G	5210	5521012100	HINGE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX DOOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12950								THE DOOR SEAL WAS MAKING NOISE IN FLT AND THE DOOR WAS DIFFICULT TO CLOSE.  INSPECTION NOTED THE HINGE WORN.  THE FIRST 	NOTE OF A DOOR HINGE PROBLEM WOULD BE THE PAINT IS WEARING OFF BETWEEN THE HALVES.  CLOSING THE DOOR 3/4 OF THE WAY AND 	MOVING THE DOOR FOR AND AFT WILL ALOW YOU TO SEE THE PLAY.  IF YOU DO NOT ADDRESS THE WORN HINGE YOU MAY MISS FORM YOUR 	DOOR SEAL, OR IF THE DOOR IS STIFF THE PILOTS ME BRAKE THE INSIDE HANDLE.  NAC HAS NOW REPLACE 4 OUT OF 5 OF THERE PC12/	45DOOR HALVES OF THE HINGE. THE AIRFRAME HALF DOES NOT SEEM TO BE WEARING.  ALL OF THESE HINGES HAVE BEEN REPLACED IN AN	D AROUND THE 11,000 HOUR AND 13,000 CYCLE AREA.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005061500035	20050615	00035	EU  	2005	6	15	CA050510015      	1	20050328	G	2932	9738114304	PRESSURE SWITCH 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	FAILED          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											THE HYDRAULIC LOW PRESSURE SWITCHED ON THERE PC12/45 FLEET LEAKING EXTERNALLY.  HYDRAULIC FLUID SEAMS TO BE LEAKING OUT 	OF THE WELDED SEAM.  THIS HAS BEEN PRESENTING ITSELF AS, HYDRAULIC LIGHT COMING ON AFTER LANDING, OR A SLUGGISH HYDRAULI	C SYSTEM.  THE LEAK IS NOT ENOUGH TO CAUSE A HYDRAULIC FAILURE.  THE PROBLEM SEEMS TO BE TIED TO BELLOW -30 DEGREES C.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005061500034	20050615	00034	NE  	2005	6	15	CA050510016      	2	20050509	G	7310	512983	LINE            			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67      	52043	NE  					FUEL DISTRI	TWISTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							802A0198				DURING MAINTENANCE IT WAS DISCOVERED THAT THE FUEL LINE WAS TWISTED, THUS RESTRICTING FLOW.  IT WAS ALSO NOTED THAT THE 	WATER RUDDER RETRACT CABLE PULLEY WAS CHAFING ON THE FUEL LINE.  THE LINE WAS INSPECTED AND REPOSITIONED.					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2005071200005	20050712	00005	SW  	2005	7	12	CA050511001      	1	20050506	G	2497	Q23A22N	GROUND WIRE     			BELL  	206   	206B        	1181511	SW  										FUSELAGE	MISLOCATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16469								(CAN) DURING INSPECTION OF BELL 206 HELICOPTER FOR COMPLIANCE OF AD CF-2005-10 AND ASB206-05-103. (FUEL DISTRIBUTION SYS	TEM INSPECTION) NOTE: FOUND GROUND WIRE Q23A22N, GROUNDED TO A DIFFERENT LOCATION. REROUTED GROUND AND GROUNDED AS PER A	SB				1	G	7	1 	3U				H2SW    					 
2005061500033	20050615	00033	EA  	2005	6	15	CA050511002      	2	20050421	G	8530	72877	LIFTER          			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	DESTROYED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L2520236A			A/C SUFFERED A PWR LOSS IN FLT DUE TO THE COLLAPSE/FRACTURE OF NR 2 CYLINDER EXHAUST VALVE HYD LIFTER BODY P/N 72877.  T	HE PILOT WAS ABLE TO MAINTAIN CONTROL OF THE A/C AND CONTINUE THE FLT TO THE CLOSEST AIRPORT (SWAN HILLS, ALBERTA 'CEM5'	).  LANDED W/O FURTHER INCIDENT.  INSPECTION REVEALED INTERNAL DAMAGE TO THE ENGINE RESULTING FROM THE BREAK-UP OF THE V	ALVE LIFTER BODY, AND PIECES OF IT BEING PROJECTED AGAINST THE CRANKCASE, AS A RESULT. THE ENG IS A TOTAL WRITE OFF THE 	ENGINE WAS CHANGED AND THE A/C WAS RETURNED TO SERVICE. THIS ENGINE OPERATED ON A TRANSPORT CANADA APPROVED 'ON CONDITIO	N' MX PROGRAM.  FLIGHT TECH AVIATION AS THE MX ARM OF ALTA FLIGHTS (CHARTERS) INC HAVE DECIDED TO REDUCE THIS ENG MAKE/M	1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2005071200004	20050712	00004	SO  	2005	7	12	CA050511003      	1	20050506	G	3230		WIRE            	PIPER       		PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					SQUAT SWITCH	SHORTED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF GEAR SELECTOR HANDLE STUCK IN UP POSITION. PILOT MADE AN UNSHEDULED LANDING. FOUND LEFT GEAR SQUAT 	SWITCH WIRE SHORTING ON SCISSOR BOLT CETTER PIN.REPAIRED WIRING AND COMPLETED FIVE FAULT FREE GEAR CYCLES.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005061500032	20050615	00032	SW  	2005	6	15	CA050511004      	1	20050419	G	2435	230321301	FAN             	LUCAS       		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					STARTER GEN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						14046					THE COOLING FAN IN THE STARTER GEN DEVELOPED A CRACK IN THE FAN BLADE PART (4 BLADES ARE STAMPED FROM ONE ALUMINUM PIECE	, AND SWAGED ON A STEEL HUB) AT THE NOTCH BETWEEN TWO BLADES.  UNDER CENTRIFUGAL FORCE AT 12,000 RPM, THE BLADES SPLIT I	N TWO AND CAME OFF THE HUB.  NO FOD RESULTED.  VISUAL PREFLIGHT INSPECTION FOUND THE DEFECT.  THIS FAN IS AN OLD DESIGN,	 AND HAS NOW BEEN REPLACED BY A SUPERSEDING PART THAT IS A ONE-PIECE CAST ALUMINUM FAN.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005061500031	20050615	00031	NM  	2005	6	15	CA050512001      	1	20050427	G	2730	82760113005	SPRING          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											AS A RESULT OF 'C CHECK' RECTIFICATIONS, THE A/C'S ELEV GUST LOCK SYS REQUIRED RE-RIGGING. DURING THE RE-RIGGING TASK AN	 UNUSUAL NOISE WAS NOTICED COMING FROM THE ELEV SYSTEM WHEN THE ELEVATORS WERE MOVED THROUGH THEIR OP RANGE. FURTHER INV	ESTIGATION WAS CARRIED OUT ON THE ELEV CONTROL SYS AND THE ELEV SPRING TAB CONTROL SYSTEM. THE NOISE INVESTIGATION REVEA	LEDTWO INCORRECTLY INSTALLED NON-SECURED BOLTS SECURING THE SPRING SHAFT TO THE ANCHOR.  ATTACH BOLTS WERE REMOVED INSPE	CTED AND INSTALLED CORRECTLY.  AS THIS IS THE A/C'S FIRST C CHECK SINCE MANUF IT IS BELIEVED THAT THE INCORRECT INSTALLA	TION OF THE BOLTS WAS CARRIED OUT AT A/C MANUF. A QUALITY INVESTIGATION IS BEING CARRIED OUT BY BOMBARDIER AEROSPACE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005061500030	20050615	00030	EA  	2005	6	15	CA050512002      	1	20050505	G	2910	601R7528637	TUBE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HYD SYSTEM	CHAFED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											CREW REPORTED A HYDRAULIC PROBLEM, 'HYD 1 LO PRESS' LOSS OF QUANITY - '0'. FLIGHT CONTINUED AND LANDED ON RUNWAY WITH NO	 FURTHER INCIDENT.  MAINTENANCE FOUND THE NR 1 SYSTEM SUCTION TUBE ASSEMBLY CHAFFED AT A POINT 18 FT FROM THE FORWARD EN	D.  P/ N 601R75286-37, REF IPC 29-11-00 FIG 4 ITEM 120.  TUBE HAD CHAFFED ON THE NR 1 HYDRAULIC SYSTEM STAINLESS STEEL P	RESSURE LINE.  P/N601R75286-61, REF IPC 29-11-00 FIG 4 ITEM 5.  SEGMENT OF NEW LINE WAS PERMASWAGED IN POSITION, ENSURIN	G PROPER SEPARATION BETWEEN LINES.  PRESSURE LINE WAS INSPECTED SERVICEABLE, AND NR 1 ENGINE DRIVEN PUMP WAS ALSO REPLAC	ED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500029	20050615	00029	CE  	2005	6	15	CA050512003      	1	20050510	G	2821	1J1810	BOWL            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL FILTER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											DURING DAILY INSPECTION IT WAS NOTICED THAT THE MAIN FUEL FILTER BOWL WAS WEAPING FUEL. MAINTENANCE INSPECTED THE ASSEMB	LY AND DETERMINED THAT THE FUEL BOWL FILTER ASSEMBLY CASTING WAS CRACKED.  THE AREA IN QUESTION WAS BETWEEN THE HANGER B	RACKET AND CASTING.  ALL FLIGHTS CANCELLED UNTIL NEW FUEL FILTER BOWL ASSEMBLY REPLACED.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005061500028	20050615	00028	NM  	2005	6	15	CA050512004      	1	20050505	G	2131	106120917	CONTROLLER      			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					CABIN PRESSURE	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			J			WARNING INDICATION        			DE	DESCENT        	1			CA											DURING DESCENT FROM FL290 TO FL270, THE 'OFF SCHEDULE' DESCENT LIGHT ILLUMINATED.  CABIN ALTITUDE WAS QUICKLY INCREASING	 WITH CABIN DIFFERENTIAL QUICKLY DECREASING.  CREW SWITCHED TO STANDBY, MANUAL DC AND MANUAL AC BUT CABIN CONTINUED TO D	E-PRESSURIZE.  ATC WAS ADVISED AND AN EMERGENCY DESCENT WAS INITIATED.  AT APPROX 14,000 FT CABIN DIFFERENTIAL WAS ZERO 	AND CABIN ALTITUDE WAS AT 14,000 FT. DESCENT WAS SLOWED AT THIS POINT AND CONTINUED TO CLEARED ALTITUDE OF 8,000 FT. DES	CENT AND LANDING AT DESTINATION AIRFIELD COMPLETED W/O FURTHER INCIDENT. MX WAS ABLE TO CONFIRM FAULT IN THE CONTROLLER.	 THE CONTROLLER WAS REPLACED AND TESTED SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE.	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005061500027	20050615	00027	EA  	2005	6	15	CA050512006      	2	20050419	G	7314	R99080J4A	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					FUEL SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											FUEL PUMP ERRATIC, LOSING PRESSURE.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005061500026	20050615	00026		2005	6	15	CA050512007      	4	20050420	G	2330	50401100003	DISPLAY         			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											THE VDU AT ROW 22C WAS REPORTED AS BEING HOT AND HAVING AN ASSOCIATED BURNING SMELL.  THIS PART WILL BE RETURNED TO THE 	OEM FOR TEARDOWN.  THIS UNIT WAS PREVIOUSLY REPORTED ON SDR 20050317007.  TO MAKE THIS ITEM MORE VISIBLE FOR TRACKING AN	D TO ADHERE WITH COMPANY POLICY A SEPARATE SDR FILE IS BEING SUBMITTED AT THIS TIME.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005061500025	20050615	00025		2005	6	15	CA050512008      	4	20050429	G	2330	50401100003	DISPLAY         			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											VDU AT ROW 5D HAD GONE BLACK AND THERE WAS A BURNING SMELL PRESENT.  THE PART WILL BE RETURNED TO THE OEM FOR TEARDOWN. 	 THIS UNIT WAS PREVIOUSLY REPORTED ON SDR20050317007.  TO MAKE THIS ITEM MORE VISIBLE FOR TRACKING AND TO ADHERE TO COMP	ANY POLICY A SEPARATE SDR FILE IS BEING SUBMITTED AT THIS TIME.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005061500024	20050615	00024	SO  	2005	6	15	CA050512009      	2	20050512	G	7314	631683	COUPLING        	CONT        		BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					EDP	WORN            	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA						E129812BR					AIRCRAFT IN CRUISE, ENGINE SPUTTERED AND DIED.  BOOST PUMP ACTIVATED AND ENGINE RESTARTED.  PART IS AN ON-CONDITION ITEM	.  THE SQUARE DRIVE ROUNDED OFF UNTIL IT WOULD NO LONGER ENGAGE THE DRIVE GEAR P/N 631684.  THIS CAUSED THE FUEL PUMP TO	 STOP ROTATING RESULTING IN ENGINE STOPPAGE.  THESE PUMPS ARE DELIVERED WITH OVERHAULED ENGINES.  THIS PARTICULAR PUMP W	AS REMOVED PRIOR TO OVERHAUL AND RE-INSTALLED ON ANOTHER ENGINE RESULTING IN THE 2600+ HOURS INSTEAD OF BEING OVERHAULED	 AT ENGINE TBO OF 1700 HOURS.		1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2005061500023	20050615	00023	EA  	2005	6	15	CA050513001      	1	20050509	G	5730		SKIN            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15729								DURING INSTALLATION OF A REPAIR DOUBLER INBOARD OF THE RT NACELLE AS PER RD6-57-618 IT WAS FOUND THAT 3 AREAS OF DISBOND	 HAD OCCURRED BETWEEN THE UPPER WING SKIN AND THE CORRUGATION . AS PER INSTRUCTIONS IN THE REPAIR DEFINITION THE MANUFAC	TURE WAS CONTACTED AND A REPAIR TO THE DISBOND IS BEING DEVELOPED.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005071200003	20050712	00003	EU  	2005	7	12	CA050513002      	1	20050419	G	6410	355A12004008	SPAR            	AEROSP      		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					T/R BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						8286					(CAN) NOISE HEARD ON PITOT DAILY INSPECTION AS PART OF EUROCOPTERS CRITERIA. DISASSEMBLED BY ENGINEER AND FOUND CRACKED.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005071200002	20050712	00002	SO  	2005	7	12	CA050513003      	1	20050414	G	3234	487155	PIN             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG	BENT            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)  PILOT COULD NOT MOVE MLG HANDLE TO RETRACT MLG. TRIED SELECTING GEAR DOWN & WIGGLING HANDLE BUT STILL UNABLE TO R	ETRACT. PILOT REQUESTED RETURN TO BASE & AFTER AN UNEVENTFUL LANDING NOTICED MLG HORN SOUNDING CONTINUOUSLY, AIRCRAFT BR	OUGHT TO A STOP ON RUNWAY & MX NOTIFIED TO TOW ACFT FROM RUNWAY. MX PROCEEDED TO RUNWAY, COMPLETED A MLG INSPECTION TO E	NSURE ALL 3 GEAR IN A SAFE & LOCKED POSITION THEN TOWED ACFT TO HANGAR. UPON FURTHER INSPECTION MLG ANTI-RETRACTION SOLE	NOID PLUNGER PIN FOUND BENT & RESTRICTING ITS RETRACTION HINDERING THE SELECTION OF GEAR UP WITH HANDLE. SOLENOID WAS RE	PLACED WITH A SERVICEABLE SOLENBOID AND F/C. THE AIRCRAFT WAS RETURNED TO SERVICE.	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005061500022	20050615	00022	EU  	2005	6	15	CA050513004      	1	20050504	G	3040	9728132202	CONTROLLER      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSHIELD HEAT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TROUBLESHOOTING RT WINDSHIELD HEAT PROBLEM ON LIGHT SETTING.  RT HEAT CONTROLLER SWITCHED WITH LT CONTROLLER.  DID NOT N	OT ICE AT THAT TIME. WIRES TO CIRCUIT BREAKERS FOR RT HEAT CONTROLLER DAMAGED.  WHEN 2 CONTROLLERS WERE SWITCHED & SYS T	ESTED, WIRE & SPLICE TO WIRE ON PIN -A-  SMOKED.  SYS TURNED OFF & WIRE & SPLICE REPAIRED.  SYS TESTED & WORKED NORMALLY	.  RT HEAT ON LIGHT SETTING FAILED. INSP OF WIRES SHOWED HEAT CONTROLLER MOVED TO THE LT POSITION DAMAGED WIRES.  WIRES 	REPAIRED & HEAT CONTROLLER MOVED TO RT POSITION REINSTALLED IN LT POSITION. NOTICED TERMINAL ENDS OF CIRCUIT BREAKERS LO	OSE. REPLACED WITH NEW AS WELL AS CIRCUIT BREAKERS.  A NEW HEAT CONTROLLER INSTALLED ON RT.  SYS TESTED & OPS NORMAL.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005071200001	20050712	00001	SW  	2005	7	12	CA050513005      	1	20050511	G	5311	110061	FRAME           			AIRTRC	AT802 	AT802A      	0390308	SW  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FUSELAGE LOWER LOGITUDINAL TUBE FRAME LT,  A CRACK WAS FOUND. CRACK ESTIMATED TO BE APPROXIMATEL	Y 1/4 TO 1/2 INCHES LENGTH. CRACK EMINATED FROM THE LT AFT FLOAT MOUNT PLATES THAT ARE ATTACHED TO THE FRAMES.  PLATES A	RE WELDED TO TUBES AS WELLAS REAR SPAR CROSS TUBE ASSY. THE AIRCRAFT WILL BE DISMANTLED ADEQU ATELY TO FURTHER EVALUATE 	THE DAMAGE AND COMPLETE THE REQUIRED REPAIRS AS DETERMINED BY THE OEM. FURTHER INFORMATION WILL BE FORWARDED AS IT BECOM	ES AVAILABLE. THE OTHER FLOAT EQUIPPED AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO DAMAGE NOTED.		1	L	7	1 	3T			NC	A19SW   					 
2005071100242	20050711	00242	EU  	2005	7	11	CA050513006      	1	20050512	G	6410	355A12004008	TRIM TAB        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						7125					(CAN) THE PILOT WAS DOING A PRE FLIGHT ON THE HELICOPTER AND NOTICED A CRACK IN THE PAINT ON THE T/R TRIM TAB. THE T/R A	SSEMBLY WAS REMOVED FOR FURTHER INVESTIGATION.AFTER REMOVING THE T/R ASSY AND REMOVED SOME PAINT IT APPEARED TO BE STILL	 CRAC KED ON THE TRIM TAB SPAN WISE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005061500021	20050615	00021	NM  	2005	6	15	CA050516001      	1	20050516	G	3244	468K292	TIRE            			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					MAIN GEAR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FOUND NR 1 MAIN WHEEL RECAP, 3/4 THICK, MISSING.  TIRE PRESS STILL 220PSI.  NR 1 MAIN WHEEL CHANGED AS PER MM32-45-01.						2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2005061500020	20050615	00020	EU  	2005	6	15	CA050516002      	1	20050516	G	3244	542K694	TIRE            			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					MAIN WHEEL TIRE	DEFLATED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											PREMATURE FAILURE OF NR 5 TIRE OF A/C 934, ON LANDING IN LHR MAY 02,2005 FROM FLIGHT 850 FROM YYC.  NR 5 WHEEL WAS FOUND	 DEFLATED.  NR 5 MAIN WHEEL REPLACED ON A/C 934 AS PER AMM 32-45-01.					1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2005061500019	20050615	00019	EU  	2005	6	15	CA050516003      	1	20050516	G	3244		TIRE            			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					MAIN WHEEL	DEFLATED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											PREMATURE FAILURE OF NR 2 TIRE OF A/C 902 ON LANDING IN YVR MAY 01,2005 FROM FLIGHT 850 FROM HKG.  NR 2 TIRE WAS FOUND D	EFLATED.  MAIN WHEEL REPLACED ON A/C 902 IAW 32-41-11-400.					2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2005061500018	20050615	00018	NE  	2005	6	15	CA050516004      	2	20050511	G	7310		WARNING LIGHT   			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					FUEL PRESSURE	ILLUMINATED     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCEBF0006			(CAN) AT 2500 FEET ASL DURING A 120 KNOTS CRUISE FLIGHT AT APPROXIMATELY 70 PERCENT TOTAL TORQUE, THE ENG FUEL PRESS WAR	NING LIGHT ILLUMINATED. APPROXIMATELY 10 SECONDS LATER THE ENG FAIL WARNING LIGHT ILLUMINATED.  FLIGHT WAS CONTINUED OEI	 WITH A RUN ON LANDING AT HELIPORT.				1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2005061500017	20050615	00017	SO  	2005	6	15	CA050516005      	2	20050513	G	7310		LINE            			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	ENGINE FUEL DIST	MISINSTALLED    	W				A				UNSCHED LANDING         				W	K	B	INADEQUATE Q C            	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	CL	CLIMB          	1			CA											(CAN) AN ALTERNATOR BELT HAD FAILED ON THE PREVIOUS FLIGHT AND HAD BEEN REPLACED. THIS REQUIRED THE REMOVAL OF THE ENGIN	E DRIVEN FUEL PUMP PRESSURE RETURN LINE. THE LINE HAD BEEN LEFT OFF OF THE FUEL PUMP WHICH RESULTED IN FUEL LEAKING INTO	 THE ENGINE COMPARTMENT. THIS RESULTED IN THE SMOKE. THE DESIGN OF THE ENGINE IS SUCH THAT THIS LINE MUST BE REMOVED TO 	REPLACE THE ALTERNATOR BELT WHICH CREATS AN OPPORTUNITY FOR THIS TYPE OF ERROR.			1	L	7	2 	3O	3	O		A34CE   	E8CE	5	C	P57GL	 
2005061500016	20050615	00016	SO  	2005	6	15	CA050516006      	1	20050515	G	8120		SEAL            	LYC         		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	TURBOCHARGER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						BIO27978					(CAN) DURING ENGINE RUN-UP AND SUBSEQUENT CHECK FOR FUEL AND OIL LEAKS, AFTER A ROUTINE ENGINE CHANGE, AN OIL LEAK WAS F	OUND IN THE VICINITY OF THE TURBOCHARGER. FURTHER INVESTIGATION REVEALED THAT THE OIL WAS COMING THRU ONE OF THE SEALS O	N THE EXHAUST SIDE OF THE TURBOCHARGER. THE LEAKING TURBO WAS EXCHANGED AND IS BEING SENT BACK FOR WARRANTY CONSIDERATIO	NS AND REPAIR/OVERHAUL. NO REASON FOR THE LEAKING SEAL COULD BE FOUND IN THE FIELD. THIS TURBO CAME WITH 0.0 HRS TSO WIT	H THE NEWLY OVERHAULED ENGINE. FAILURE OF THE TURBOCHARGER COULD LEAD TO LOSS OF POWER AND THIS IS WHY A DECISION WAS MA	DE TO FILE THIS SDR.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2005071100241	20050711	00241	EA  	2005	7	11	CA050516007      	1	20050510	G	2820	S613063005315	TUBE            			CARSON	S61   	S61LSKRSKY  	       	EA  	GE    	CT58  	CT581401    	30011	NE  					FUEL SYSTEM	LEAKING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			LD	LANDING        	1			CA								295067			(CAN) WHILE LANDING,ONE OF THE PASSENGERS IN THE CABIN NOTICED FLUID RUNNING DOWN THE RIGHT HAND SIDE OF THE AIRCRAFT. A	FTER AIRCRAFT SHUT DOWN THE ENGINEER INSPECTEDTHE RIGHT HAND ENGINE AND FOUND A TUBE ASSY FROM THE MAIN FUEL SUPPLY LINE	 HADLOOSENED, CAUSING A FUEL LEAK. THE LINE WAS TIGHTENED AND A LEAK CHECK CARRIED OUT. THE AIRCRAFT RETURNED TO BASE WI	THOUT FURTHER INCIDENT.			2	G	7	2 	4U	4	U		H8EA    	1E3				 
2005061500015	20050615	00015	EU  	2005	6	15	CA050516008      	1	20050426	G	2422	358401001	INVERTER        			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					AC SYSTEM	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING FLIGHT DECK PREPARATION WITH EXTERNAL POWER OFF AND BATTERIES POWER ON, SMOKE ODOR WAS NOTICED IN FLIGHT DE	CK. DURING INVESTIGATION FOUND STATIC INVERTER AT FAULT WITH THE SUPPLIED FUSE BLOWN.  BOTH UNITS WERE REPLACED. ALSO TH	IS POWER PROBLEM DISABLED THE FUEL QUANTITY INDICATION COMPUTER AND THE FLIGHT WARNING COMPUTER. BOTH UNITS WERE ALSO RE	PLACED.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2005071100240	20050711	00240	SO  	2005	7	11	CA050516009      	1	20050514	G	2910	1776692	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											DURING THE LANDING APPROACH, THE GEAR WOULD NOT COME DOWN AND LOCK.  AN EMERGENCY EXTENSION WAS CARRIED OUT USING THE HA	NDPUMP.  AFTER LANDING AN INSPECTION OF THE NOSE GEAR AREA SHOWED A LOT OF HYDRAULIC FLUID LEAKING.  THIS WAS TRACED TO 	THE NOSE GEAR ACTUATOR UP LINE.  A SMALL PINHOLE WAS FOUND IN THE HOSE.  THE HOSE WAS MANUFACTURED IN 1992.  PIPER CALLS	 FOR A PRESSURE TEST OF THE HOSES EVERY TEN YEARS WITH NO REPLACEMENT GUIDE.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005071100239	20050711	00239	SW  	2005	7	11	CA050516010      	1	20050513	G	2820	10001212S	FITTING         			AIRTRC	AT802 	AT802A      	0390308	SW  										FIREWALL	MISMANUFACTURED 	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, A FUEL LEAK WAS DISCOVERED AT THE FWD ENGINE FIREWALL FITTINGDURING A LEAK/PRESSURE CHECK. UPON	 INVESTIGATION IT WAS DISCOVERED THAT THE FIREWALL FITTING HAD A FACTORY MANUFACTUINGDEFECT (SCORE MARK) THAT EXTENDED F	ROM THE HEX NUT PORTION OF THE FITTING THROUGH THE FWD CONE SEALING SURFACE. THE FITTING WAS REPLACED AND THE SYSTEM WAS	 LEAK AND PRESSURE CHECKED SERVICEABLE.			1	L	7	1 	3T			NC	A19SW   					 
2005061500014	20050615	00014	NM  	2005	6	15	CA050517001      	1	20050517	G	5250		LOCK            			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					COCKPIT DOOR	MELTED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) FAULT: ELECTRICAL BURNING SMELL NOTED AROUND VCR IN FORWARD GALLEY, LAVATORY AND OVERHEAD AREA.  RETURNED.  ACTION	: BURNED ELEC SMELL LOCATED AS COMING FROM COCKPIT DOOR LOCK SOLENOID. SOLENOID AND HARDWARE REMOVED AND PLACED IN PLAST	IC BAG IN OPB. AREA DEODORIZED AND A/C CHECKED (S) FOR FLT. COCKPIT DOOR CAN BE LOCKED WITH DEAD BOLT IAW MEL.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2005061500013	20050615	00013	NM  	2005	6	15	CA050517002      	1	20050517	G	3320		LIGHT           			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					FWD GALLEY	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) ON FINAL TO 24R, IN CHARGE F/A REPORTED SMOKE FROM UTILITY LIGHT FWD GALLEY AFTER COMPLETING QRH AND CUTTING UTILI	TY BUSSES SMOKE SUBSIDED. TRANSFORMER REPLACED AND OPS TESTED OK.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005061500012	20050615	00012	EU  	2005	6	15	CA050517003      	1	20050513	G	2121	68C6122	COOLING FAN     			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					NR 2 RADIO	OVERHEATED      	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											EN ROUTE, CREW NOTICED AN ELECTRICAL BURNING ODOR & SMOKE IN COCKPIT.  FLT TERMINATED & AN UNEVENTFULL LANDING MADE.  MX	 INVESTIGATION REVEALED THE NR 2 RADIO CRATE COOLING FAN SMOKE BLACKENED & DIFFICULT TO TURN BY HAND.  FAN REMOVED & BEN	CH TESTED. DURING BENCH TEST FAN ROTATED VERY SLOWLY & OVERHEATED.  NOTED DURING TEST THE CURRENT DRAW BY FAN LESS THAT 	15 AMPS, WHICH WOULD EXPLAIN WHY ASSOCIATED ACFT 15 AMP C/B DID NOT TRIP.   FAN REPLACED.  ASSOCIATED WIRING HARNESSES &	 C/BS INSPECTED & TESTED.  COOLING FAN INSTALLATION FUNCTION TESTED ON THE AIRCRAFT AND SHOWED NO EVIDENCE OF DEFECTS.  	THE AIRCRAFT RELEASED TO SERVICE.	2	L	7	2 	3T	4	T		A24EU   	A196				 
2005061500011	20050615	00011	CE  	2005	6	15	CA050517004      	1	20050510	G	2435	115167CXX16070	HOSE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	FUEL SYSTEM	CHAFED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING A TRAINING FLIGHT, THE CREW NOTICED THE LT ENGINE WAS SLOW TO RESPOND TO POWER INPUTS AND THEY WERE SOMEWHA	T TORQUE LIMITED. THE AIRCRAFT RESUMED ONTO THE MAINTENANCE BASE AND LANDED IN NORMAL CONFIGURATION.  MAINTENANCE WAS IN	FORMED AND INSPECTED THE LT ENGINE. THE INSPECTION REVEALED THAT THE STARTER GENERATOR COOLING HOSE P/N: 116167CXX-070 H	AD CHAFED THROUGH A FCU FUEL LINE P/N: 3032791 . THE FUEL LINE WAS REPLACED, THE COOLING TUBE WAS ROUTED AWAY FROM THE F	UEL TUBE AND THE AIRCRAFT RUN AND PERFORMANCE CHECKED. THE REST OF THE ENGINES THAT COULD BE AFFECTED WERE INSPECTED FOR	 PROPER ROUTING.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005061500010	20050615	00010	NM  	2005	6	15	CA050517005      	1	20050517	G	2910	1U10851	VALVE           			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, AFTER GEAR EXTENSION (A) SYSTEM HYDRAULIC FLUID WAS FOUND DROPPING. A NORMAL LANDING WAS ACCOMPLISHED	 BUT THE AIRCRAFT HAD TO BE TOWED OFF THE TAXI WAY DUE TO HYDRAULIC LOSS CAUSING THE STEERING SYSTEM TO BE INOP. AT THE 	RAMP MAINTENANCE TROUBLE SHOT THE SYSTEM AND FOUND A PIN HOLE IN THE LT MAIN LANDING GEAR LOCK OPERATED SEQUENCE VALVE B	ODY. AIRCRAFT IS DOWN UNTIL NEW VALVE CAN BE INSTALLED AND GEAR SWING ACCOMPLISHED.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005061500009	20050615	00009	NM  	2005	6	15	CA050517006      	1	20050516	G	7120	BLT5249	BOLT            	BOEING      	FW18694     	BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					ENGINE MOUNT	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						EEAQ1837					(CAN) DURING C CHECK, IT WAS FOUND THAT THE FRONT MOUNT ASSEMBLY HAD A KEEPER BOLT MISSING FROM THE AFT PICKUP BEARING B	USHING. THE BEARING BUSHING HAD SHIFTED TRANSFERING ALL WEIGHT TO ONE LUG OF THE BRACKET. COMPLETE MOUNT WAS REPLACED AS	 A PRECAUTION.  APPROVAL OBTAINED FROM MFG.  IT COULD NOT BE CONFIRMED THAT THE BOLT WAS EVER INSTALLED OR THAT IT WAS N	OT PROPERLY SAFETIED AND FELL OUT AT A LATER DATE.  NO HARDWARE WAS FOUND IN THE COWLING SUGGESTING IT WAS NOT INSTALLED	 AT BUILDUP. AIRCRAFT FLEW 1298 HOURS AND 361 CYCLES BETWEEN TIME THE ENGINE WAS INSTALLED UNTIL THE BOLT WAS NOTICED MI	SSING.	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005061500008	20050615	00008	CE  	2005	6	15	CA050517007      	1	20050427	G	7603	509440763	ARM             			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT ENGINE	WORN            	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											AFTER AN UNEVENTFUL FLT, CREW UNABLE TO GET THE RT ENGINE TO DROP BELOW 78 PERCENT NG AND IT HAD INSUFFICIENT REVERSE.  	MAINTENANCE INVESTIGATED AND FOUND THAT THE PIVOT ARM (50-944076-3) ON THE CAM CLUSTER HAD WORN ALLOWING IT TO SLIP ON T	HE CAM, CHANGING THE RELATIONSHIP BETWEEN THE POWER LEVER AND THE FUEL CONTROL UNIT.  THIS CAUSED THE LOSS OF THE REVERS	E CAPABILITY AND THE 78 PERCENT NG WITH THE POWER LEVER SET AT IDLE.  THE BOLT SECURING THE PIVOT ARM WAS TIGHTEN TO STO	P THE SLIPPING BUT THE SLOT IN THE PIVOT ARM BOTTOMED OUT BEFORE IT WAS TIGHT ENOUGH TO BE SECURE.  THE PIVOT ARM WAS RE	PLACED AND THE AIRCRAFT RETURNED TO SERVICE.  SEE ATTACHED PICTURES.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005071100238	20050711	00238	CE  	2005	7	11	CA050517008      	1	20050502	G	3310	CM39570	POTENTIOMETER   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT LIGHT	FAILED          	W				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) DURING LANDING PHASE OF FLT, MLG SELECTED DOWN & 3 GREEN LIGHTS DID NOT APPEAR TO BE ON. AFTER ALL PROPER PROCEDUR	ES, ACFT LANDED WITHOUT FURTHER INCIDENT. ONCE GENERATORS SELECTED OFF LINE, GREEN LIGHT ILLUMINATED. BEING A LATER S/N 	AIRCRAFT THESE LIGHTS ARE EQUIPPED WITH AN AUTOMATIC DIMMING SYS, MLG INDICATION LIGHT WILL AUTOMATICALLY DIM IF ALL THE	 RIGHT CONDITIONS ARE MET, GENERATORS ONLINE, COCKPIT OVERHEAD LIGHT ON, AMBIENT DAYLIGHT SENSOR SENSING LOW LIGHT, ETC 	IN THIS INSTANCE ALL BUT ONE OF THE CONDITIONS WERE MET, AMBIENT DAYLIGHT SENSOR SHOULD HAVE STOPPED LIGHT FROM GOING TO	 DIM MODE. AFTER TROUBLE SHOUTING IT WAS DISCOVERED THAT COCKPIT LIGHT POTENTIOMETER WAS MALFUNCTIONING CAUSING THE LIGH	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005071100237	20050711	00237	CE  	2005	7	11	CA050517009      	1	20050515	G	3260	10136457813	PCB             			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	INTERMITTENT    	W				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) ALL 3 GREEN GEAR INDICATIONS BLANKED OUT DURING FINAL APPROACH. AFTER CYCLING GEAR , LIGHTS RETURNED. PROBLEM FOUN	D WITH A125 PCB WHICH PROVIDES A COMMON GROUND FOR ALL 3 LIGHTS.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061500007	20050615	00007	EA  	2005	6	15	CA050518001      	1	20050505	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			10080								LEFT WINDSHIELD CRACKED DURING CLIMB AT FL180.  DIVERTED FLIGHT BACK TO DEPARTURE AIRPORT.  LEFT WINDSHIELD REPLACED AND	 TESTED ACCORDING TO AMM PROCEDURE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500006	20050615	00006	EA  	2005	6	15	CA050518002      	1	20050502	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											INBOUND THE CAPTAINS SIDE WINDOW CRACKED.  REPLACED WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061500005	20050615	00005	EA  	2005	6	15	CA050518003      	1	20050515	G	2440	EP361	MONITOR         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CABIN	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											THE AIRCRAFT WAS IN THE PROCESS OF RETURNING BACK TO THE AIRPORT DUE TO AN ADG DROP.  TURNED AROUND TO FACE THE CUSTOMER	S AND SAW SPARKS OUT OF THE CORNER OF MY EYE AND SMOKE BEGAN TO LIGHTLY COME OUT FROM THE AREA OF THE FLIGHT ATTENDANT P	ANEL/PHONE AND GO TOWARDS THE FLIGHT DECK.  PRELIMINARY FINDINGS HAS ATTRIBUTED THE SMOKE WAS CAUSED BY THE EXTERNAL POW	ER MONITOR (PN EP361) (DESIGNATOR A2XB).  CONNECTOR FOUND BURNED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071100232	20050711	00232	EU  	2005	7	11	CA050518005      	1	20050421	G	6220	350A310033K1T7	SPRING          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ANTI-VIBRATION	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN DI CONDUCTED BY A ENGINEER, A BROKEN SPRING WAS DISCOVERED UNDER THE CHINESE HAT.THE SPRING WAS REPLACED	 WITH NEW. THE OTHER SPRINGS WERE INSPECTED AND NO DEFECTS WERE FOUND. THE SPRING WHICH WAS BROKEN, SHOWED SIGNS OF A CR	ACK WHICH FINALLY COMPLETELY BROKE OVER TIME. THE TOTAL TIME OF THE SPRING CAN NOT BE DETERMINED AT THIS TIME.				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005071300033	20050713	00033	CE  	2005	7	13	CA050518006      	1	20050516	G	2612		FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LEFT	WILL NOT TEST   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING START, CREW WAS RUNNING PREFLIGHT CHECKS AND FOUND LT FIRE LOOP WOULD NOT TEST.  MAINTENANCE FOUND THE FWD 	FIREWALL CONNECTION WAS POOR AND WAS CORRECTED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071300031	20050713	00031	CE  	2005	7	13	CA050518007      	1	20050517	G	2997		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PRESSURE SWITCH	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, THE LANDING GEAR REPORTED AS (FAILED TO OPERATE RELIABLY) REQUIRING MULITIPLE EXTENSION ATTEMPTS.	  TROUBLESHOOTING FOUND CHAFED WIRED AT THE HYD PACK PRESSURE SWITCH THAT WERE REPAIRED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071500137	20050715	00137	EA  	2005	7	15	CA050518009      	2	20050511	G	7310	FT60	TRANSDUCER      			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	FUEL FLOW	LEAKING         	W				F	D			ACTIVATE FIRE EXT.      	RETURN TO BLOCK         			A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) A NEW FP5-L FUEL FLOW WAS INSTALLED AND LEAK TESTED ON FIRST FLIGHT. APPROX 20 MINUTES AND AIRCRAFT WAS LANDED AND	 PILOT REALIZED HE HAD AN ENGINE FIRE. AIRCRAFT IS TURBO CHARGED.  FUEL FLOW TRANSDUCER LOCATION APPROX. 10 INCHES FROM 	COMPRESSOR SIDE OF TURBO.  TRANSDUCER AND LINES COVERED WITH FIRE SLEEVE. IT IS BELIEVED FIRE IGNITED ON TOUCHDOWN. FUEL	 FLOW TRANSDUCER WAS BROUGHT BACK TO HANGAR AND TESTED FOR LEAKS. LEAK OCCURS THROUGH ELECTRONIC COMPARTMENT COVER.			1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P9EA	 
2005061500004	20050615	00004	CE  	2005	6	15	CA050518010      	1	20050510	G	3260	65430087	UPLOCK SWITCH   			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					RT MLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											PILOT NOTED THAT THE GEAR WOULD NOT RETRACT AFTER TAKEOFF.   IT MADE A REPETATIVE CLUNKING SOUND AND THE RED GEAR INDICA	TION LIGHT FLASHED ON AND OFF.  CYCLED THE GEAR BACK DOWN NORMALLY AND LANDED.  THE RT MLG UPLOCK SWITCH WAS REPLACED.  	PERFORMED GEAR EXTENSION AND RETRACTION AND CHECKED OK.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005061500003	20050615	00003	EU  	2005	6	15	CA050518011      	1	20050221	G	3240	LWB9227H24	BOLT            	DUNLOP      		BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BRAKE ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11487			KQ258					BRAKE UNIT ON WING FOUND WORN TO LIMITS, UNIT REMOVED FOR OVERHAUL, THE ASSEMBLY SENT TO THE WHEEL AND BRAKE SHOP FOR TE	AR DOWN, INSPECTION TASK 32420-RAI-10000-2 AS PER IN HOUSE FORM SSF030 WAS DONE, THE ENGINEER FOUND THE HEAD OF A BOLT S	HEARED OFF OF ONE OF THE BOLTS BETWEEN THE TORQ PLATE AND TORQ TUBE ASSY.  THE BOLT HEAD HELD IN PLACE BY THE LOCK WIRE 	THE SHANK IS A CLOSE TOLORANCE BOLT SO IT WAS STILL IN PLACE.  CMM REFERENCE 32-44-44 FIG #1 ITEM 860.  ALT PART# DSR429	1-1411.		2	H	7	4 	4F	4	F		A49EU   	E6NE				 
2005061500002	20050615	00002	EU  	2005	6	15	CA050518015      	1	20050506	G	3246	95443331	EMBELLISHER     			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					RT WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											EMBELLISHER ON RIGHT WHEEL IS CRACKED.  RT EMBELLISHER REPLACED WITH NEW UNIT.						2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005061500001	20050615	00001	NE  	2005	6	15	CA050518016      	3	20050518	G	6111	SFA13M1R0AD	BLADE           													HAMSTD	14SF	14SF5       	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									910615		DURING FLUORESCENT PENETRANT INSPECTION, FOUND THE FILLET RADIUS WITH CRACK INDICATIONS RADIALLY IN THREE PLACES ABOUT 1	/8 INCH FROM THE OUTSIDE DIAMETER.  THE LONGEST IS ABOUT 1/2 INCH LONG.  THERE IS ALSO A CRACK INDICATION ON THE OUTSIDE	 DIAMETER ABOUT 1/8 INCH FROM THE EDGE OF THE FILLET RADIUS, ABOUT 1/2 INCH LONG .  THE INDICATIONS WERE CHECKED WITH ED	DY CURRENT AND CONFIRMED THAT THEY ARE NOT SURFACE SCRATCHING.  THERE ARE NO CRACKS ALLOWED IN BLADE SHANK, INCLUDING TH	E FILLET AREA.												6	C	P7NE	 
2005061400148	20050614	00148	WP  	2005	6	14	CA050518017      	2	20050517	G	7200	8679225	CARRIER ASSY    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					GEARBOX	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			26132					P50004			FLIGHT CREW OBSERVED THE ENGINE OIL PRESSURE TREND TO BE STEADILY DECREASING OVER A SHORT PERIOD OF TIME.  AS AN EXPERIE	NCED OPERATOR OF THIS ENGINE, THIS TREND INDICATED A CRACKING PROBLEM WITH THE PLANETARY GEAR CARRIER IN THE ENGINE GEAR	BOX.  THE ENGINE WAS REMOVED FOR INSPECTION AND AS SUSPECTED THE PLANETARY GEAR CARRIER ASSY HAD MULTIPLE CRACKS AND NEA	RING COMPLETE FAILURE.  TO DATE OUR COMPANY HAS ISSUED SEVERAL SDR'S ON THIS SAME ISSUE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005071400091	20050714	00091	CE  	2005	7	14	CA050518018      	1	20050430	G	2731	556544054	CHAIN           	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TRIM CONTROL	MISINSTALLED    	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA						14453					(CAN) DURING MAJOR INSP, TRIM ACTUATOR WAS REMOVED AND REINSTALLED. WHEN ENGINEER MOUNTED TRIM CONTROL CABLE CHAIN ONTO 	ACTUATOR SPROCKET, INSTALLED OPPOSITE TO WAY IT WAS REMOVED. THIS CAUSED ELEV TRIM CONTROL SYS TO WORK BACKWARDS. MM DOE	S NOT FULLY DESCRIBE INSTALLATION OF CHAIN ON SPROCKET AND IT IS EASY TO INSTALL IT INCORRECTLY. PERSONS DOING DUAL INSP	ECTION OF THE SYS FAILED TO RECOGNIZE ERROR BECAUSE OF HUMAN FACTORS. ERROR WAS NOT CAUGHT UNTIL AIRCRAFT WAS TEST FLOWN	 WHEN HEAVIER THAN NORMAL CONTROL FORCES WERE REQUIRED TO CONTROL PITCH.  RATHER THAN TROUBLESHOOT PROBLEM CREW ELECTED 	TO RETURN IMMEDIATELY AND LANDED WITHOUT FURTHER INCIDENT.  BECAUSE OF NATURE OF THE DIFFICULTY DECLARED AN EMERGENCY.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005071400090	20050714	00090	CE  	2005	7	14	CA050519001      	1	20050517	G	3210	07416011	LEG ASSY        	CESSNA      		CESSNA	182   	182J        	2072722	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						318002					(CAN) DUE TO A BROKEN MLG LEG ON ONE OF OUR AIRCRAFT LAST SEASON IT WAS DECIDED TO HAVE ALL MLG LEGS MAGNAFLUXED TO DETE	RMINE IF ANY OTHERS IN THE FLEET WERE CRACKED.  EACH INSPECTION SINCE THEN, NDTD LEGS HAVE BEEN INSTALLED AND THE LEGS R	EMOVED FROM SERVICE HAVE BEEN TESTED. WHEN LEGS WERE TESTED THE LT LEG WAS FOUND TO HAVE A CRACK IMMEDIATELY OB THE MLG 	SUPPORT BRACKET IN THE SAME PLACE WHERE THE MLG LEG BROKE ON LAST SEASON.			1	H	7	1 	3O	3	O	NT	3A13    	3E1	5	C	P3EA	 
2005071400112	20050714	00112	NM  	2005	7	14	CA050519003      	1	20050121	G	3240	266230	HOUSING         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	BRAKE ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22152			0264					(CAN) PILOT REPORTED GETTING A VIBRATION WHEN APPLIED BRAKE PRESSURE WHILE SLOWING DOWN AFTER LANDING AND EVEN WHILE TAX	ING. ENGINEERS INSPECTED THE BRAKES AND FOUND THE NR 4 POSITION BRAKE WORN TO LIMITS.  BRAKE WAS REPLACED AND SENT TO TH	E BRAKE SHOP.  THE UNIT WAS OVERHAULED AND PRESSURE TESTED, THAT IS WHEN DISCOVERED THAT A PISTON HOUSING WAS LEAKING.  	THE UNIT WAS DISASSEMBLED AND SENT FOR NDT INSPECTION WHERE THEY FOUND A CRACK IN THE SIDEWALL OF A PISTON HOUSING IT WA	S DETERMINED TO BE BEYOND LIMITS SO THE ASSEMBLY WAS SCRAPPED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071400089	20050714	00089	SO  	2005	7	14	CA050519004      	1	20050510	G	5523	110321632	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) UPON GROUND INSPECTION, THE ELEV TRIM TAB ACTUATOR BRACKET WAS FOUND BROKEN. THE BRACKET WAS REPLACED WITH A NEW A	ND THE TRIM TAB REINSTALLED AND RIGGED IAW M/M.					1	L	7	2 	4T	4	T	RT	A21SO   	E4EA	6	C	P15EA	 
2005071100225	20050711	00225	CE  	2005	7	11	CA050519005      	1	20050513	G	3230		CLEVIS          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					MLG ACTUATOR	OUT OF RIG      	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON INITIAL GEAR EXTENSION DURING APPROACH RT MLG DOWNLOCK LIGHT DID NOT ILLUMINATE. THE PILOTS OPERATED THE EMERGE	NCY GEAR EXTENSION SYSTEM HOWEVER LIGHT STILL NOT ILLUMINATE. ONLY ONCE AIR SPEED WAS REDUCED JUST PRIOR TO TOUCHDOWN DI	D LIGHT ILLUMINATE INDICATING A DOWN & LOCKED CONDITION.  NUMEROUS MLG CYCLES WITH ACFT ON JACKS WERE CARRIED OUT HOWEVE	R GEAR APPEARED TO OPERATE NORMALLY. ONLY ONCE DRAG LEG SLIGHTLY LOADED IN AFT DIRECTION AT ITS CENTRE HINGE POINT, DID 	GEAR FAIL TO LOCK. FURTHER INVEST REVEALED THAT ALTHOUGH SPRING LOADED LOCK HOOK WOULD ENGAGE WITH NO LOAD ON DRAG LEG, 	ACTUATOR CLEVIS NOT ADJUSTED PER MM, LONG ENOUGH TO POSITIVELY PUSH DRAG LEG TO AN OVER CENTRE LOCKED CONDITION.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005071500135	20050715	00135	EA  	2005	7	15	CA050519007      	1	20050412	G	1420	770231	CONNECTOR       	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PSU	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			31028								(CAN) AC WAS IN FOR FMS INSTALLATION, CONNECTOR FWD OF FIRST LT PSU WAS DISCOVERED BURNED UP, ALONG WITH WIRE SPLICES IN	 SYS. THIS CONNECTOR IS MAIN PWR FEED FOR ALL OF PSU ON THAT SIDE OF AC, WASN'T JUST ONE PSU AT FAULT.  CONNECTOR WAS RE	PLACED, RETERMINATED WIRES IAW SB.  SYSTEM FUNCTION,  OPS TEST WERE CARRIED OUT, SYS WAS DEEMED SERVICEABLE. THESE CONNE	CTORS ARE PART OF THE MOD8/2924 AND WAS CARRIED AS AD.  MFG WAS CONTACTED, THEY ARE AWARE OF SITUATION AS IT HAD BEEN PR	EVIOUSLY REPORTED.  THIS CONNECTOR HAD ONE OF ITS LOCKING CLIPS BROKEN OFF, SUSPECT THAT THIS MAY HAVE BEEN CONTRIBUTING	 FACTOR IN THIS INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005061400147	20050614	00147	GL  	2005	6	14	CA050519008      	2	20050514	G	7200		ENGINE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) THE AIRCRAFT WAS IN A HOVER WITH A 125 FOOT LONG LINE. THE PILOT DROPPED OFF A BATTERY AND HAD DESCENDED ABOUT 5 F	T, THEN NOTICED A RAPID DESCENT AND THE RPM WAS DELAYED. ENTERED INTO AUTOROTION AND LANDED. THE PILOT ADJUSTED THE THRO	TTLETO IDLE AND SHUT THE ENGINE DOWN THE ENGINE WITH THE FUEL SHUT OFF. SOURCE OF THIS DECELL IS UNKNOWN.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005061400146	20050614	00146	CE  	2005	6	14	CA050520001      	1	20050519	G	2731	505244761	BUSHING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	MIGRATED        	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) ON A ROUTINE FLT THE PILOTS COULD HEAR A NOISE IN THE CONTROL COLUMN WHEN MOVING IT BACKWARDS AND FORWARDS.  WHEN 	THE AIRCRAFT RETURNED MAINTENANCE FOUND THE LEFT ELEVATOR TAB BINDING AT THE CONTROL ROD TO TAB HORN ATTACHMENT.  THE BU	SHING HAD MIGRATED SUCH THAT IT WAS BINDING WHEN THE ELEVATOR WAS MOVED CAUSING OIL-CANNING IN THE SKIN.  A NEW BUSHING,	 NUT, BOLT AND COTTER PIN WERE INSTALLED AND RIGGED.  THE SYSTEM WAS CHECKED SERVICEABLE AND THE AIRCRAFT RETURNED TO SE	RVICE.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005071100207	20050711	00207	EU  	2005	7	11	CA050520003      	1	20050516	G	6710	12TW13	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COLLECTIVE STICK	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A GROUND RUN AND HYDRAULIC CHECKS THE HYDRAULIC WARNING HORN WOULD NOT SOUND WHEN OPERATING COLLECTIVE HYDR	UALIC SWITCH. HORN WOULD NOT SOUND WHEN OPERATING COLLECTIVE HYDR. SWITCH. HYDRAULICS WOULD TURN ON AND OFF, HORN WOULD 	NOT TURN ON. COLLECTIVE HYDRAULIC SWITCH P/N 12TTW1-3 WAS REPLACED AND HORN FUNCTIONEDPROPERLY ON AND OFF. AIRCRAFT WAS 	RETURNED TO SERVICE.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005061400145	20050614	00145	EA  	2005	6	14	CA050523001      	1	20050517	G	3230	2603070001	HANDLE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					EMER MLG EXTEND	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER LIFT OFF 'GEAR DISAGREE' MESSAGE APPEARED.  THE NOSE WHEEL WOULD NOT RETRACT AND NOSE DOORS DID NOT CLOSE.  AIRCRA	FT RETURNED TO POINT OF DEPARTURE.  WHEN DOING THE EMERGENCY EXTEND THE HANDLE BROKE OFF.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061400144	20050614	00144		2005	6	14	CA050524001      	1	20050518	G	2622	A81360021	EXTINGUISHER    																	ENGINE BAY	LEAKING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											ENGINE FIRE EXTINGUISHER RECEIVED EMPTY FROM CUSTOMER FOR INVESTIGATION AS TO CAUSE OF DEPLETION. INSPECTION OF THE BOTT	LE CONFIRMED THAT UNIT EMPTY BUT HAD NOT BEEN ACTIVATED.  FOUND EXTINGUISHER LEAKING THROUGH THE TCPS VENT HOLE.  EXTING	UISHER MANUFACTURED IN 1985, AND HAD BEEN HYDROSTATICALLY TESTED TWICE SINCE.																	 
2005071100206	20050711	00206	EU  	2005	7	11	CA050524002      	1	20050510	G	6420	704A33651190	BEARING         	AEROSP      		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R SPIDER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M2178					(CAN) 1) BEARING ROUGH. 2) REPLACED SPIDER.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005061400143	20050614	00143	EA  	2005	6	14	CA050524003      	1	20050524	G	3020		CONNECTING ROD  			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					INTAKE DEFLECTOR	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING OVERHAUL AND FUNCTION TESTING, THE INTAKE DEFLECTOR ACTUATOR WAS FOUND TO BE BINDING DURING OPERATION.  THE CONNE	CTING ROD HAD BEEN ASSEMBLED AND RIGGED IAW THE CMM CH 71-60-01, FIGURE 1, PAGE 5, WITH THE ROD ENDS AT 90 DEGREES TO EA	CH OTHER.  IT WAS FOUND DURING OPERATION THAT THE ROD END WOULD REACH THE LIMIT OF ITS SIDEWAYS TRAVEL BEFORE THE PISTON	 REACHED FULL TRAVEL, CAUSING IT TO BIND.  WHEN THE ROD END WERE RIGGED IN THE SAME PLANE, THE PISTON DID NOT BIND AND T	HE SYSTEM OPERATED NORMALLY.  THE SUBMITTER REPORTS THAT HE HAS DONE THIS TO OTHER CONNECTING RODS IN THE PAST.		1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2005071400088	20050714	00088	CE  	2005	7	14	CA050524004      	1	20050524	G	5544	05310186	HINGE BRACKET   	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CRACK IN CORNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18771								(CAN) DURING AN INSPECTION A CRACK WAS FOUND IN THE CORNER OF A TOP RUDDER HINGE BRACKET.  THE AMO HAS BEEN MONITORING T	HE WEAR ON THESE BRACKETS IN OUR HIGH TIME AIR FRAMES.  SUBSEQUENTLY 5 HIGH TIME AIRFRAME SHAVE HAD THEIR RUDDER HINGE B	RACKETS REPLACED. NO MORE CRACKS WERE FOUND BUT THE BRACKETS DID SHOW SIGNIFICANT WEAR.  HAVE INCLUDED THIS INSPECTION A	ND REPAIR IN OUR AGING AIRCRAFT INSPECTIONS AND ARE MONITORING THE REST OF OUR FLEET.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005071100205	20050711	00205	SW  	2005	7	11	CA050524005      	1	20050520	G	6410	4270160010	BLADE           			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					TAIL ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 427 TAIL ROTOR BLADE SKIN SEPARATION. AFT OF LEADING EDGE NEAR THE TIP OF THE BLADE ON APPROX. 2 SQ. IN. OUTBOARD 	SIDE.					1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2005071200022	20050712	00022	SW  	2005	7	12	CA050525001      	1	20050401	G	6730		SEAL            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						2534					(CAN)  OIL LEAK REAR SEAL.  OIL LEAK REPAIRED, RETURN TO SERVICE..						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071200039	20050712	00039	NE  	2005	7	12	CA050526001      	2	20050520	G	7261	M832481042	O-RING          			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE	MISSING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								LE45228CAEF			(CAN) ON RECEIPT OF THE ENGINE AFTER INTERNAL REPAIRS CARRIED OUT BY HONEYWELL GREER, NUMEROUS MINOR OIL LEAKS WERE DETE	CTED AND REPAIRED BEFORE REINSTALLING THE ENGINE INTO THE AIRFRAME. HOWEVER, ON REMOVAL OF THE TORQUE METER COVER TO REP	AIR AN OIL LEAK, IT WAS DISCOVERED THAT O-RING, HAD BEEN OMITTED ON REASSEMBLY HENCE THE OIL LEAK.				1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2005071200021	20050712	00021	EU  	2005	7	12	CA050526002      	1	20050524	G	6410	10531810	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BO105 BASED IN THE WEST HAS IN THE PAST EXPERIENCED PROBLEMS WITH PAINT EROSION ON THE TAIL ROTOR BLADES. NEW 	STYLE BLADES WERE INSTALLED IN THE BELIEF THAT THIS WOULD SOLVE THE PROBLEM WE WERE EXPERIENCING WITH PAINT EROSION. 50 	HOURS AFTER INSTALLATION & FLT THROUGH MINOR AMOUNTS OF RAIN. MX ENGINEER NOTICED EROSION OF PAINT FROM LEADING EDGE NEA	R THE TIP OF THE BLADE. MANUFACTURER REQUESTED THESE BLADES FOR ANALYSIS TO DETERMINE WHY THE PAINT WAS NOT ADHEREING TO	 THE SURFACE.  IN THE MEANTIME WE WERE DIRECTED BY TH E MANUFACTURER TO LIGHTLY SAND & FEATHER THE AFFECTED AREA.  THIS 	WAS DONE AND BLADES REMAINED INSERVICE FOR AN ADDITIONAL 50 HOURS PRIOR TO ARRIVAL OF REPLACEMENT BLADES.	1	G	7	2 	3U				H3EU    					 
2005071200020	20050712	00020	CE  	2005	7	12	CA050526003      	1	20050523	G	5753	501600036	BRACKET         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION A CRACK WAS NOTICED ON THE LT INBOARD FLAP ACTUATOR ATTACHMENT BRACKET, BRACKET WAS RE	MOVED AND A TOTAL OF 4 CRACKS WERE FOUND ON THE BRACKET SURROUNDING THE UPPER BOLTHOLE. THE FLAP WAS ALSO CRACKED UNDER 	THE FORWARD END OF THE BRACKET. THE FLAP WAS REPAIRED, THE BRACKET REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005061400142	20050614	00142	NE  	2005	6	14	CA050526004      	2	20050525	G	7322	NAR9B19	CARBURETOR      			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				O				OTHER                   				W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		LD	LANDING        	1			CA											AFTER RETURNING FROM A FLIGHT, THE CREW REPORTED THAT THE ENGINE WOULD NOT IDLE BELOW 1000 RPM, AND WAS ROUGH AT INTERME	DIATE SPEEDS.  IDLE MIXTURE ADJUSTMENT HAD NO EFFECT.  THE CARBURETOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERV	ICE.  UNIT WAS OVERHAULED BY L.A. AERO ENGINES.				1	H	7	1 	3R	3	R		A806    	5E1				 
2005071400078	20050714	00078	CE  	2005	7	14	CA050526005      	1	20050526	G	2510	LC6010000B	LOCK            	CESSNA      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ADULT MALE WAS ADJUSTING HIMSELF IN THE FRONT RT SEAT WHEN THE SEAT COLLAPSED REARWARD. PASSENGER WAS QUITE LARGE,	 250 LBS PLUS.  PART FAILED AT THE FORWARD ATTACH CRIMP.  WHERE IT CRIMPS ON TO THE SPLINE.					1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P47GL	 
2005071200019	20050712	00019	SW  	2005	7	12	CA050526006      	1	20050516	G	2910	70012H000Y136	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYD SYSTEM	FAILED          	W				H	E			DEACTIVATE SYST/CIRCUITS	ENGINE SHUTDOWN         			K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) RAPID LOSS OF HYDRAULIC PRESSURE ON GROUND RUN-UP.  FOUND TO BE BLOWN FLEX LINE AT BOTTOM FITTING CRIMP RESULTING 	IN LOSS OF NR 2 HYDRAULIC PRESSURE & FLUID. PROBABLE CAUSE COMBINATION OF TWISTED LINE & TRANSMISSION MOVEMENT CAUSED LI	NE TO FATIQUE & RUPTURE.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005061400141	20050614	00141	NM  	2005	6	14	CA050527001      	1	20050525	G	2721	682015	SWITCH          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RUDDER TRIM	BURNED          	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											FLIGHT CREW REPORTED DURING THE APPROACH PHASE OF FEELING UNWELL, IT WAS THEN NOTED THE RUDDER TRIM SWITCH WAS HOT AND U	NABLE TO FULLY OPERATE. THE C/B FOR RUDDER TRIM ACTUATOR WAS THEN NOTED AS TRIPPED.  MAINTENANCE FOUND RUDDER TRIM SWITC	H BURNT.  THE SWITCH HAD BEEN REPLACED ON THE				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005061400140	20050614	00140	NM  	2005	6	14	CA050527002      	1	20050519	G	2721	652183121	ACTUATOR        			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					RUDDER TRIM	LACK OF LUBE    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											DURING CRUISE, A/C BEGINNING TO PITCH UP & DOWN SLIGHTLY WITH AUTOPILOT ENGAGED.  DISENGAGED AUTOPILOT IN ORDER TO RE-TR	IM A/C.  DURING PROCEDURE RUDDER TRIM FOUND IMMOBILE.  ATTEMPTED SMALL RUDDER DEFLECTION WITH RUDDER PEDALS & FOUND THEM	 TO BE IMMOBILE.  DECLARED AN EMERGENCY AND DIVERTED TO CYWG.  DURING DESCENT AT APPROX 9000 FT, RUDDER BEGAN TO FREE IT	SELF & FUNCTION CORRECTLY.  A/C CONTINUED ITS APPROACH & LANDED AT CYWG W/O FURTHER INCIDENT.  MX INVEST WITH ASSISTANCE	 OF BOEING SERVICE LETTER 727-SL-27-24 INDICATED RUDDER TRIM ACTUATOR TO BE LACKING SUFFICIENT LUBE RESULTING IN HIGHER 	THAN NORMAL INPUT FORCE.  RUDDER TRIM ACTUATOR & RELATED PARTS LUBED IAW SERVICE LETTER & MM. A/C RETURNED TO SERVICE.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005061400139	20050614	00139	EA  	2005	6	14	CA050527004      	1	20050525	G	2710	TBC6CWM104327	PIN             			DHAV  	DHC6  	DHC6300     	2802606	EA  										AILERON CONTROL	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											PDA PART ROD SECURING PIN DEHAVILLAND P/N C6CWM1043-27 INCORRECTLY MANUFACTURED.  PIN OUTSIDE DIAMETER TOO LARGE TO FIT 	INTO 'H' BEAM HOLE.  REFERENCE DHC-6-300 IPC CHAPTER 27-10-00 FIGURE 4 ITEM 560. 'H' BEAM ATTACHMENT HOLE EDGE DISTANCE 	MAY BE TOO SMALL IF HOLE OPENED UP TO ACCEPT OVERSIZED PIN.  THIS COULD COMPROMISE AILERON CONTROL ROD STRENGTH.				1	H	7	2 	3T			RT	A9EA    					 
2005061400138	20050614	00138	EA  	2005	6	14	CA050527006      	2	20050421	G	7314		COUPLING        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUEL PUMP	FRACTURED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED TORQUE AND TEMPERATURE INCREASE.  THE ENGINE WAS SHUT DOWN IN FLIGH	T.  SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL PUMP COUPLING SHAFT.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005061400137	20050614	00137	WP  	2005	6	14	CA050527007      	1	20050526	G	3260	MS250112	SWITCH          			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					MLG	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											ON FINAL APPROACH TO MONTREAL, THE RT MAIN LANDING GEAR DOWN ANNUNCIATION LIGHT FAIL TO INDICATE.  AFTER INVESTIGATION, 	THE DOWN MICROSWITCH WAS FOUND INOPERATIVE, UNIT REPLACED AND ADJUSTED IAW MAINTENANCE MANUAL.  GEAR SWING C/O SERVICEAB	LE, AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4R	4	T		6A6     	E282				 
2005061400136	20050614	00136	NE  	2005	6	14	CA050527008      	2	20050502	G	7320	82370002	HMU             			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											IN DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN.  A RELIGHT ATTEMPT WAS UNSUCCESSFUL.  THE HYDROMECHANICAL FU	EL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005061400135	20050614	00135	EA  	2005	6	14	CA050527009      	2	20050518	G	7322		VENTURI         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CARBURETTOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											REPLACEMENT OF VENTURI, A GRANULAR (CRYSTALIZED) TYPE MATERIAL WAS FOUND IN THE VENTURI INLET AND IN THE REGULATOR AREA 	ACCESSED VIA THE BRASS HEX PLUG.  WHEN THIS AREA WAS ACCESSED, THIS GRANULAR (POWDER LIKE) MATERIAL WAS THOUGHT TO BE CO	RROSION (RESULT OF).  INJECTION SERVO REMOVED, SENT TO REPAIR AGENCY (LEAVENS AVIATION), AND THEY DETERMINED THAT THIS M	ATERIAL WAS NOT CORROSION RELATED.  INJECTION SERVO CLEANED, FLUSHED, TESTED, AND RE-INSTALLED ON AIRCRAFT.  GRANULAR/PO	WER LIKE MATERIAL TO BE SENT TO LAB FOR ANALYSIS.		1	G	7	1 	3O	3	O		H11NM   	E295				 
2005061400134	20050614	00134	EA  	2005	6	14	CA050527010      	2	20050316	G	7200		ENGINE          			DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  						FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			TX	TAXI/GRND HDL  	1			CA											THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED GRINDING NOISES FROM THE POWER	 SECTION.  THE ENGINE WAS REMOVED FOR REPAIR.					2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
2005061400133	20050614	00133	NE  	2005	6	14	CA050527011      	2	20050406	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								PC0966			DURING TAKEOFF ROLL, THE ENGINE CHIP DETECTOR ANNUNCIATED.  THE TAKEOFF WAS ABORTED AND THE ENGINE WAS SHUT DOWN.  SUBSE	QUENT INSPECTION REVEALED HOT SECTION DAMAGE INCLUDING DISTRESSED COMPRESSOR TURBINE AND POWER TURBINE BLADES					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005061400132	20050614	00132	NE  	2005	6	14	CA050527013      	2	20050401	G	7261		CAP             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					OIL TANK	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											DURING SERVICING, EXTERNAL OIL LEAKAGE WAS FOUND BECAUSE OF A LOSS OF THE OIL TANK CAP RETENTION.  THIS WAS DEEMED AS RE	SULTING FROM A LOSS OF TORQUE OF THE CAP ASSEMBLY NUT.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005061400131	20050614	00131	EA  	2005	6	14	CA050527014      	2	20050117	G	7321	3244753191	FUEL CONTROL    			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											IN DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  THE FUEL CONTRO	L UNIT WAS SUBSEQUENTLY REPLACED.					2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2005061400130	20050614	00130	EU  	2005	6	14	CA050527015      	1	20050501	G	7920		TUBE            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					OIL TRANSFER	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											DURING CLIMB, THE ENGINE EXHIBITED A TORQUE SPLIT ACCOMPANIED BY A LOW OIL PRESSURE WARNING AND A SUBSEQUENT FIRE WARNIN	G.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED 	A FRACTURED NR 6/7 BEARING OIL TRANSFER TUBE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005061400129	20050614	00129	NE  	2005	6	14	CA050527016      	2	20050526	G	8520	261280	CRANKSHAFT      			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								JP208016			THE ENGINE WAS RETURNED TO CANADA FROM THE USA FOLLOWING REPAIR AND INSTALLED ONDHC-2 MK 1 AIRCRAFT.  WHEN THE ENGINE WA	S STARTED EXCESSIVE OIL LEAK WAS OBSERVED FROM THE AREA NEAR THE REAR OF THE PROPELLER HUB AND THE NOSE CASE OF THE ENGI	NE.  THE PROPELLER AND REAR CONE WERE REMOVED AND THE CRANKSHAFT WAS FOUND TO BE CRACKED.  THE CRACK WAS VISIBLE TO THE 	NAKED EYE AND WAS LOCATED ON THE SHAFT WHERE THE REAR CONE SITS.  THE CRACK MEASURES APPROX 2.5 INCHES IN LENGTH AROUND 	THE CIRCUMFERANCE OF THE SHAFT.  THE ENGINE WAS REMOVED.		1	H	7	1 	3R	3	R		A806    	5E1				 
2005061400128	20050614	00128		2005	6	14	CA050527017      	4	20050428	G	8300		LOCKWASHER      			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	GEARBOX DRIVE	FRACTURED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INVES	TIGATION REVEALED THE THE ACCESSORY GEARBOX TOWERSHAFT LOCKWASHER TO BE FRACTURED AND THE TOWERSHAFT RETAINING NUT DISLO	DGED.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2005061400127	20050614	00127	NE  	2005	6	14	CA050527018      	2	20050427	G	7314	5009982D	PUMP            			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					FUEL SYS	UNSERVICEABLE   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											THE ENGINE EXPERIENCED AN UNCOMMANDED IN-FLIGHT SHUT-DOWN SHORTLY AFTER TAKEOFF.  THE AIRCRAFT DIVERTED TO POINT OF DEPA	RTURE. THE ENGINE FUEL CONTROL UNIT ANDFUEL PUMP WERE SUBSEQUENTLY REPLACED.					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005061400126	20050614	00126	NE  	2005	6	14	CA050527019      	2	20050502	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								DA0555			DURING GROUND HANDLING OPERATIONS, THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION.  THE ENGINE DID NOT RESPOND TO TH	ROTTLE OR SHUTOFF LEVER INPUT.  THE CREW SECURED THE ENGINE VIA AIRFRAME FIREWALLSHUT-OFF.  PWC WILL INVESTIGATE THE EVE	NT AND ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.				1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005061400125	20050614	00125	NE  	2005	6	14	CA050527020      	2	20050416	G	7310	8210410	CSD             			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			DE	DESCENT        	1			CA											DURING DESCENT, THE ENGINE EXPERIENCED SURGING AND THE PILOT ELECTED TO SHUT THE ENGINE DOWN IN FLIGHT.  THE CONSTANT SP	EED UNIT AND FUEL CONTROL UNIT WERE SUBSEQUENTLY REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005061400124	20050614	00124	NE  	2005	6	14	CA050527021      	2	20050503	G	7260		SHAFT           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       	 	NE  					AGB	FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT-DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FRACTURED ACCESSORY GEARBOX	 TOWERSHAFT.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2005061400123	20050614	00123	EA  	2005	6	14	CA050527022      	2	20050511	G	7261		ENGINE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  						LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								41635			DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT.  THE AIRCRA	FT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE FROM THE NR 3 BEARING SEAL AREA.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005061400122	20050614	00122	NE  	2005	6	14	CA050527023      	2	20050516	G	7200		WARNING LIGHT   			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	FALSE INDICATION	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA								EB0145			DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT.  A SUBSEQUE	NT INSPECTION WAS UNABLE TO IDENTIFY CAUSE AND THE ENGINE WAS REMOVED FOR INVESTIGATION.  THE ENGINE HAD EXPERIENCED A S	IMILAR LOW OIL PRESSURE INDICATION AND PILOT-COMMANDED IN-FLIGHT SHUT-DOWN TWO WEEKS PRIOR.  P&WC WILL MONITOR INVESTIGA	TION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005061400121	20050614	00121	NE  	2005	6	14	CA050527024      	2	20050514	G	7200		ENGINE          			PILATS	PC7   	PC7         	7090401	EU  	PWA   	PT6   	PT6A25A     	52043	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				M	J		OVER TEMP                 	WARNING INDICATION        		DE	DESCENT        	1			CA											DURING DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED DECREASE IN TORQUE, ACCOMPANIED BY AN INCREASE IN TURBINE TEMPERAT	URE.  THE ENGINE DID NOT RESPOND TO THROTTLE INPUT AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT.  THE ENGINE WAS SUBSEQU	ENTLY RELIT IN FLIGHT BUT REMAINED UNRESPONSIVE TO THROTTLE INPUT.  THE ENGINE WAS AGAIN SHUT DOWN AND AN EMERGENCY (WHE	ELS-UP) LANDING CARRIED OUT.  P&WC WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETE	RMINED. TWO SEATER, SINGLE ENGINE, FULLY AEROBATIC, TURBO-TRAINER AIRCRAFT.		1	L	7	1 	3T	3	T	RT	A50EU   	E4EA				 
2005061400120	20050614	00120	SW  	2005	6	14	CA050527025      	1	20050511	G	7330		WARNING LIGHT   			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					ENGINE FUEL	ILLUMINATED     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								BF0006			DURING CRUISE, THE ENGINE FUEL PRESSURE WARNING ANNUNCIATED FOLLOWED BY AN ENGINE FAIL WARNING ANNUNCIATION.  THE FLIGHT	 CONTINUED ON OEI RATING.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.					1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2005061400119	20050614	00119	NE  	2005	6	14	CA050527026      	2	20050518	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA								CA0410			DURING DESCENT, THE ENGINE EMITTED TWO LOUD BANGS AND SUBSEQUENTLY FLAMED OUT.  AN AIR-RESTART WAS SUCCESSFULLY ACCOMPLI	SHED BUT THE ENGINE AGAIN EMITTED A LOUD BANG AND FLAMED OUT IN RESPONSE TO THROTTLE INPUT. THE AIRCRAFT DIVERTED FOR AN	 UNSCHEDULED LANDING.  P&WC WILL INVESTIGATE THIS EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005061400118	20050614	00118	EA  	2005	6	14	CA050527027      	2	20050518	G	7261		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		AP	APPROACH       	1			CA								FA0184			ON APPROACH, SMOKE BECAME EVIDENT IN THE CABIN AND ON THE FLIGHT DECK.  THE CREW DECLARED AN EMERGENCY AND OPENED THE FO	RWARD OUTFLOW AND DUMP VALVE.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE AND THE ENGINE WAS REMOVED FOR INVEST	IGATION.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005061400117	20050614	00117	NE  	2005	6	14	CA050527028      	2	20050517	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						SHUTDOWN        	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								CA0273			DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT-DOWN.  AN IN-FLIGHT RELIGHT WAS SUCCESSFULLY ACCOMPLISHED.  THE	 ENGINE WAS SUBSEQUENTLY REMOVED FOR INVESTIGATION.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE, ONCE ESTA	BLISHED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005061400116	20050614	00116	NE  	2005	6	14	CA050527029      	2	20050523	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						SHUTDOWN        	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA								305128			ON DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT-DOWN.  AN IN-FLIGHT RELIGHT WAS SUBSEQUENTLY ACCOMPLISHED.  P&WC 	WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE, ONCE DETERMINED.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005061400115	20050614	00115	EA  	2005	6	14	CA050527030      	2	20050511	G	7230		COMPRESSOR      			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								TH0263			DURING CRUISE, ENGINE TURBINE TEMPERATURE STEADILY INCREASED ACCOMPANIED BY A DECEASE IN COMPRESSOR SPEED.  THE CREW SHU	T THE ENGINE DOWN IN-FLIGHT AND THE AIRCRAFT WAS DIVERTED.  SUBSEQUENT INSPECTION EVIDENCED COMPRESSOR SEIZURE.  P&WC WI	LL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2005061400114	20050614	00114	NE  	2005	6	14	CA050527031      	2	20050524	G	7200		ENGINE          			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  						SHUTDOWN        	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								120613			ON TRANSITION BETWEEN CLIMB AND CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT-DOWN.  THE AIRCRAFT DIVERTED TO POINT	 OF DEPARTURE.  PWC WILL MONITOR THE INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005061400113	20050614	00113	NE  	2005	6	14	CA050527032      	2	20050525	G	7200		ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  						SHUTDOWN        	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								JC0589			DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT-DOWN COINCIDENT WITH THROTTLE INPUT FOR POWER REDUCTION.  THE A	IRCRAFT DIVERTED TO POINT OF DEPARTURE.  PWC WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE O	NCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2005071200018	20050712	00018	SW  	2005	7	12	CA050527033      	1	20050516	G	6220	204011116001	NUT             	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					M/R HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						HEL301292					(CAN) THE M/R HUB WAS IN FOR OVERHAUL, AS PART OF THE OVERHAUL THE ACORN NUTS HAD TOBE NDT. ONE NUT PASSED AND THE OTHER	 REJECTED. TO CONFIRM THE NDT OF THE ACORN NUT WE SENT IT TO ANOTHER NDT AMO. STRIKE TWO THIS ACORN NUT WAS REJECTED DUE	 TO A CRACK. THE CRACKING WAS AROUND THE RADIUS.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005071300030	20050713	00030	EA  	2005	7	13	CA050528001      	1	20050526	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDSHIELD CRACKED WHILE IN CRUISE. THE WINDSHIELD IS POST SB.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005061400112	20050614	00112	EU  	2005	6	14	CA050530001      	1	20050510	G	6320	70BMO55020	GEARBOX         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			12598					4193			ENGINE CHIP LIGHT, ENGINE REPLACED MO5 SENT FOR REPAIR, TRIPLEX WAS FOUND TO BE THE CAUSE OF THE METAL CONTAMINATION.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005071200045	20050712	00045	CE  	2005	7	12	CA050530002      	1	20050527	G	3211	501202011	SUPPORT         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG DRAG LEG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24255								(CAN) DURING SCHEDULED MAIN LANDING GEAR REPLACEMENT, UPPER DRAG LINK ATTACH FITTING AT MAIN SPAR WAS DISCOVERED CRACKED	 AT THE RADIUS OF THE ATTACH LUG. REFERENCE BEECH KING AIR 100 IPC CHAPTER 32-10-01 FIGURE 10-01 ITEM 54. THE BEECH 100 	IPC DOES NOT LIST THE SPECIFIC BRACKET IN QUESTION. THE PART NUMBER WAS LOCATED THROUGH BEECH TECH SUPPORT. THIS BRACKET	 IS COMMON TO BEECH 99 AND SUPER KING AIR 200 MODELS.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005071200044	20050712	00044	NE  	2005	7	12	CA050530003      	1	20050303	G	6320	S613520600046	SUPPORT         	SKRSKY      		SKRSKY	S61   	S61N        	8142104	NE  										M/R GEARBOX	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A141016					(CAN) M/R GB TEARDOWN REVEALED HEAVY FRETTING & ELONGATED BOLT HOLES ON LOWER SURFACE OF RING GEAR & UPPER MATING SURFAC	E OF BEARING SUPPORT. HEAVY FRETTING TO LOWER HOUSING & STUD DAMAGE. DAMAGED BACKLASH SHIM. WEAR & DAMAGE IS CONSISTENT 	WITH LACK OF TORQUE TO NUTS & STUDS THAT CLAMP RING GEAR & BEARING SUPPORT TO LOWER HOUSING. LACK OF TORQUE ALLOWS RING 	GEAR TO MOVE & FRET SURFACE OF BEARING SUPPORT. MOVEMENT OF RING GEAR AGAINST STUDS WORKS LOOSE & RESULTS IN PULLING OUT	 OF THREADS IN LOWER HOUSING.  ALL HOLES IN RING GEAR & BEARING SUPPORT ARE DAMAGED & ELONGATED.  WORST AREA WHERE CRACK	 PASSES THROUGH SUPPORT & STUD TO INNER SURFACE.  MX CHECK EVERY 150 HOURS,	2	G	7	2 	4U				1H15    					 
2005061400111	20050614	00111	NM  	2005	6	14	CA050530004      	1	20050525	G	2752	C1535361	SHAFT           			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					FLAP XMSN	SHEARED         	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4090 			107					AFTER SELECTION, NOTICED NO MOVEMENT OF FLAPS,  CREW RESET FLAP CONTROL CB L7  WITH NO SUCCESS. OVERSHOOT C/OUT, FLAPLES	S LANDING C/OUT WITH NO DIFFICULTY. AFTER INSP, RT INBD FLAP, OTBD (RT NR 4) XMISSION SHAFT FOUND SHEARED AT JOINT & CAU	SE A FLAP POWER CAUTION LIGHT DURING APPRO. NOTE: ALSO ASYMMETRY MESSAGE IN CDS. SHAFT IN QUESTION IS ORIGINAL TO A/C, N	EVER REPLACED SINCE A/C ENTERED IN SERVICE. NO SPECIFIC MX PERFORMED ON PART OTHER THAN GENERAL INSPS & FUNCT CHKS OF SY	S. BOMBARDIER ADVISED SAME DAY & DAMAGED PART SHIPPED FOR INVEST. GENERAL VISUAL INSP OF ALL XMISSION SHAFTS (ALL FLAP T	RANSMISSION SHAFT AND TORSION BARS REMOVED FOR INSPECTION) FOR INTEGRITY C/OUT, LUBE ALL FLAP BALL-SCREW ACT C/OUT.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005071200041	20050712	00041	EU  	2005	7	12	CA050530005      	1	20050523	G	5410		PIN             			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COWL LATCH	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AD INSPECTION, THE RT AFT ENGINE COWLING LATCH WAS FOUND WITH A BROKEN HINGE PIN.  A NEW PART WAS	 ORDERED, INSTALLED AND ADJUSTED.					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005061400110	20050614	00110	EA  	2005	6	14	CA050530006      	1	20050511	G	3250	711599	LEVER           			DHAV  	DHC6  	DHC6300     	2802606	EA  										NLG STEERING ACT	FRACTURED       	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) NO RESPONSE TO NWS AFTER LANDING. LEVER ARM FRACTURED AT RADIUS WHERE CONNECTS TO ACTUATOR HOUSING BOSS. SEE MFG A	MM FIGURE 201.RDIMS LETTER NR 1199637 SENT - CAA IN RESPONSE TO TO HIS LETTER TO TC. REFERENCE ATTACHMENT.					1	H	7	2 	3T			RT	A9EA    					 
2005061400109	20050614	00109	GL  	2005	6	14	CA050530007      	2	20050527	G	7321		MOUNT           			LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  					NR 1 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) ON LANDING ROLL OUT THE NR 1 ENGINE FIREBELL WENT OFF, THE CREW HANDLED THE ENGINE AND THE FIRE BELL WENT OUT.  MA	INTENANCE FOUND THE AFT SECTION OF THE REAR BEARING SUPPORT AND SWIRL STRAIGHTENER IN THE EXHAUST BELL HOUSING PIPE.  TH	ERE WAS SOME COWL DAMAGE. THE A/C DID A 3 ENGINE FERRY, WHERE THE ENGINE WAS REPLACED AND THE A/C RETURNED TO SERVICE.				2	L	7	4 	4T	4	T		4A22    	E282				 
2005071400068	20050714	00068	CE  	2005	7	14	CA050530008      	1	20050517	G	2430	DOFF10300JR	ALTERNATOR      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) ALTERNATOR FAILED IN FLIGHT.  REPLACED UNIT.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P21EA	 
2005061400108	20050614	00108	NM  	2005	6	14	CA050530009      	1	20050426	G	2910	DSC252B40124	HOSE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			34816	34816							(CAN) DURING PREFLIGHT INSPECTION , FOUND NOSE WHEEL WELL AREA LEAKING HYDRAULIC FLUID.  MAINTENANCE INSPECTION FOUND FL	EXABLE HYDRAULIC LINE FOR THE DRAG STRUT ACTUATOR FAILED/LEAKING.  HOSE REPLACED , GEAR SWINGS CARRIED OUT. AIRCRAFT RET	URNED TO SERVICE. THIS PART IS CONSIDERED AN EXPENDABLE AND PART TIMES NOT TRACKED , TIMES PROVIDED ARE TOTAL AIRCRAFT T	IMES SINCE NEW. HOSE DATE CODE PT 7-96.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005061400107	20050614	00107	SO  	2005	6	14	CA050531001      	2	20050525	G	8520	642720	MAIN BEARING    	CONT        		CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	CRANKSHAFT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT CAME IN WITH A REPORT OF LOW OIL PRESSURE. THE OIL FILTER WAS PULLED AND INSPECTED WITH NO FAULTS FOU	ND, THE OIL PRESSURE RELIEF VALVE WAS REMOVED, CLEANED, AND REINSTALLED. THE AIRCRAFT WAS RUN-UP AND FOUND TO BE OPERATI	NG NORMALLY. AT THE 50 HOUR INSPECTION COMPLETED AT 3767.8 HOURS. THE OIL FILTER WAS AGAIN INSPECTED WITH NO FAULTS FOUN	D BUT TWO LARGE PIECES OF FERROUS METAL WHERE FOUND IN THE OIL DRAIN PLUG. THE ENGINE WAS REMOVED FOR INTERNAL INSPECTIO	N AND THE MAIN BEARING AT THE NR 2 CYLINDER WAS FOUND TO HAVE FAILED.  STRIP REPORT AVAILABLE FROM ENGINE SHOP.		1	L	7	2 	3O	3	O		A34CE   	E8CE	5	C	P57GL	 
2005061400106	20050614	00106	SO  	2005	6	14	CA050531002      	1	20050406	G	8120	4066109020	TURBOCHARGER    			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	LEAKING         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ENGINE WAS SEEN TO BE SMOKING AT STARTUP AND LOW POWER. AN INSPECTION OF THE TURBO CHARGER REVEALED THAT OIL WAS G	ETTING BY THE SEALS INTO THE TURBINE SECTION. THE TURBO CHARGER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. T	HIS ENGINE IS ON CONDITION IAW THE MSA W1281.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005061400105	20050614	00105	NE  	2005	6	14	CA050531003      	2	20050528	G	7200		ENGINE          			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			46117					30736			(CAN) DURING ENGINE START, ENGINE FAILED TO ACHIEVE APPROPRIATE RPM. START ABORTED. TROUBLESHOOTING FOUND DEBRIS IN THRE	E CHIP DETECTORS. ENGINE WILL BE CHANGED AND SHIPPED BACK TO OVERHAUL FACILITY FOR INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005071400067	20050714	00067	CE  	2005	7	14	CA050531004      	1	20050518	G	5343	071349561	SUPPORT BRACKET 			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  	HARTZL	HC82V	HC82V*      	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTERGRANULAR CORROSION FOUND ON INSPECTION.						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P23EA	 
2005071300029	20050713	00029		2005	7	13	CA050531005      	4	20050529	G	3421	332D11T	VERTICAL GYRO   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON ROLLOUT FOR TAKEOFF AT APPROX 60 KNTS THE CAPTAINS ATTITUDE INDICATOR FLAGGED OFF AND WENT BLANK. THE T/O WAS R	EJECTED AND THE AIRCRAFT RETURNED TO THE GATE. DURING THE TAXI THE UNIT CAME BACK ONLINE. THE CREW CONTACTED MAINTENANCE	 AND AS THE UNIT WAS OPERATING THEY ELECTED TO GO AGAIN. THE T/O WAS NORMAL BUT DURING THE CRUISE PORTION OF THE FLIGHT 	THE UNIT FAILED AGAIN. THEY SELECTED ALL INFO FROM THE NR 2 SYSTEM AND COMPLETED THE FLIGHT.  THE AIRCRAFT WENT TO MAINT	ENANCE AND THE NR 1 VERTICAL GYRO WAS REPLACED AND TESTED SERVICEABLE.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071300044	20050713	00044		2005	7	13	CA050531006      	1	20050531	G	3244	256K433	TIRE            																	MLG	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE OVERHAULING A MAIN WHEEL ASSEMBLY, A DEFECT WAS FOUND IN THE NEW TIRE DURING INSTALLATION. A 1 INCH CRACK AT	 .2500 DEEP IN SIDE WALL WAS FOUND IN THE NEW TIRE RECEIVED FROM STORES. THE TIRE WAS TAGGED UNSERVICEABLE AND WILL BE R	ETURNED TO THE VENDOR FOR CREDIT CONSIDERATION.																	 
2005071300028	20050713	00028	CE  	2005	7	13	CA050531007      	1	20050517	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA							BB24				(CAN) DURING A/C CLIMB THROUGH 10,000, RT WINDSHIELD OUTERPANE CRACKED ACROSS ENTIRE WINDOW, (WINDSHIELD HEAT ON).   NO 	OTHER PROBLEMS OCCURED (DEPRESSURIZATION ETC)  AIRCRAFT RETURNED TO BASE AND COMPLETED A NORMAL LANDING.  MAINTENANCE CH	ANGED WINDOW AND A/C RETURNED TO SERVICE. MAINTENANCE NOTE THAT SPONGE SEAL STRIP WAS MISSING FROM PREVIOUS INSTALLATION	.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005071500134	20050715	00134	GL  	2005	7	15	CA050531008      	3	20050527	G	6114	NQ007	HUB             			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									EAA1132M3		(CAN) DURING AN AUDIT OF AD'S IT WAS DISCOVERED THAT AN ERROR HAD BEEN MADE BY THE OVERHAULER WHEN INTERPRETING AD96-18-	14 WHICH RESULTED IN AN EXPIRED HUB BEING INSTALLED ON THE PROP. DURING OVERHAUL THE HUB AND BLADES WERE REPLACED. THE H	UB SN HAD AN EXTRA DASH NUMBER ADDED BY MFG (-M3)INDICATING THAT AD95-01-02 HAD BEEN CARRIED OUT ON IT. THIS LED THE OVE	RHAULER TO BELIEVE THAT THIS SERIAL NUMBER WAS NOT AFFECTED BY AD96-18-14 WHICH WOULD HAVE RETIRED THE HUB FROM USE ON T	HIS AIRCRAFT. THE AD DID NOT CLEARLY STATE THAT THE DASH NUMBER WAS NOT A FACTOR. FURTHER CHECKING REVEALED THAT THE SAM	E MISINTERPRETATION HAD OCCURRED ON TWO OTHER PROPS IN THE PAST	1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005061400104	20050614	00104	NE  	2005	6	14	CA050601001      	2	20050601	G	7320	32448714	HYDROMECH UNIT  			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	INOPERATIVE     	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLL, ENGINE TORQUE DROPPED AND THE TAKE-OFF WAS ABORTED.  THE HYRDOMECHANICAL FUEL CONTROL WAS SU	BSEQUENTLY REPLACED.					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2005071300027	20050713	00027	CE  	2005	7	13	CA050601002      	1	20050530	G	5510	04320049	BRACKET         	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11774								(CAN) PART DISCOVERED CRACKED IAW 2 PREVIOUS EXAMPLES.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005071300026	20050713	00026	EA  	2005	7	13	CA050601003      	1	20050526	G	5230	H341531	HOUSING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					DOOR HANDLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11803	11803							(CAN) ON ARRIVAL, GROUND CREW WAS UNABLE TO OPEN CARGO DOOR. INVESTIGATION BY MAINTENANCE FOUND CENTER PART OF THE DOOR 	HANDLE ASSY HOUSING WHERE THE SHAFT PASSES THROUGH WAS COMPLETELY BROKEN AWAY.  CRJ 200 IPC REF 52-31-00 FIG.2 ITEM 20A.	 CARGO DOOR HANDLE ASSY WAS REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071200011	20050712	00011	NM  	2005	7	12	CA050601004      	1	20050530	G	3030		HEATER          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PITOT TUBE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AN OPERATOR HAS EXPERIENCED A SECOND INCIDENT OF PITOT HEAT FAILURE WITH SUBSEQUENTLY LOSS OF AIRSPEED INDICATION 	CAUSED BY A POPPED CB.SIX WEEKS AGO THE SAME OPERATOR LOST BOTH AIRSPEEDS BY POPPED CBS PITOT HTR 1 AND 2 SIMULTANEOUS. 	MOISTURE HAS BEEN FOUND ON PITOT TUBE RECEPTACLES CAUSED BY WEAK SEALANT. BOMBARDIER AEROSPACE IS INVESTIGATING THE EVEN	TS.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071300025	20050713	00025	SO  	2005	7	13	CA050601005      	1	20050525	G	3260		WIRE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG IND SOCKET	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) NO INDICATION OF (NOSE GEAR DOWN).  AFTER INSPECTION, WIRE REPAIRED ON LIGHT SOCKET. CO2 BOTTLE REPLACED, SEVERAL 	RETRACTIONS ACCOMPLISHED.					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2005071200012	20050712	00012	NM  	2005	7	12	CA050601006      	1	20050526	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, AN OPERATOR EXPERIENCED A NR 2 HYDRAULIC SYSTEM FAILURE DUE TO FLUID LOST FROM NR 2 EDP. NR 2 EDP A	ND PTU REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005071800023	20050718	00023	EU  	2005	7	18	CA050601007      	1	20050525	G	7430	9550177760	EXCITER         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA								22360			(CAN) DURING ROUTINE IGNITER TEST ONE OF THE TOWERS FROM THE EXCITER UNIT FAILED TO PROVIDE IGNITION.  THE IGNITER WAS R	EMOVED AND REPLACED WITH NEW, WITH NO IGNITION. THE HARNESS WAS MOVED TO THE OTHER TOWER AND IGNITION WAS SUCCESSFUL . E	XCITER WAS REPLACED, TEST REPEATED, AIRCRAFT RETURNED TO SERVICE.				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005071200017	20050712	00017	NM  	2005	7	12	CA050602001      	1	20050601	G	2752		RING            	ROTOL       		BOEING	727   	72744C      	1384100	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					K-FLAP ACTUATOR	LEAKING         	W				J	A			DUMP FUEL               	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA						2721A					(CAN) AFTER DEPARTING YOW FOR YFB THE CREW OBSERVED AN 'A' HYD. SYSTEM FLUID LOSS CONDITION WITH 2.5 GAL.INDICATED CLIMB	ING THROUGH FL190. THE AIRCRAFT WAS REROUTED TO POINT OF DEPARTURE AND FUEL WAS DUMPEDPRIOR TO THE LANDING AT YOW. POST 	ARRIVAL INVESTIGATION BY MAINTENANCE FOUND A TRUNNION SEAL ON NO.5 KRUEGER FLAP ACTUATOR HAD FAILED. BOTH 'A' SYSTEM PUM	PS WERE REPLACED, THE CASE DRAIN FILTERS CHEC KED AND REPLACED, NO.5 KRUEGER FLAP ACTUATOR REPLACED AND THE AIRRAFT GROU	ND CHECK CARRIED OUT BEFORE THE AIRCRAFT WAS REURNED TO SERVICE.		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005071200016	20050712	00016	NM  	2005	7	12	CA050602002      	1	20050417	G	2730	85520271003	STOP            			DHAV  	DHC8  	DHC8201     	2809001	NM  						HAMSTD	14SF	14SF23      	NE  	ELELVATE	DETERIORATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) ABNORMAL AMOUNT OF ELEVATOR TRAVEL OBSERVED DURING FLIGHT CONTROLS RANGE OF TRAVEL CHECKS.BOTH UPPER ELEVATOR STOP	 BUMPER ASSEMBLIES SPLIT.  NO DAMAGE WAS NOTED TO THE SURROUNDING STRUCTURE.  BUMPERS WERE REPLACED 264 CYCLES EARLIER.E	LEVATOR STOP BUMPER ASSEMBLIES REPLACED IN ACCORDANCE AMM,  AD/CF-2001-08 & AWLTR 2-20.  ELEVATOR RIGGING CHECKED WITH N	O PROBLEMS IDENTIFIED.  INSPECTION PER IOD REDUCED.			2	H	7	2 	4T			RT	A13NM   		6	C	P7NE	 
2005071200015	20050712	00015	NM  	2005	7	12	CA050602003      	1	20050418	G	2730	85520271003	STOP            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR	DETERIORATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) ABNORMAL AMOUNT OF ELEVATOR TRAVEL OBSERVED DURING FLIGHT CONTROLS RANGE OF TRAVEL CHECKS.ONE UPPER ELEVATOR STOP 	BUMPER ASSEMBLY MISSING AND THE OTHER UPPER ELEVATOR STOP BUMPER ASSEMBLY SPLIT.  NO DAMAGE WAS NOTED TO THE SURROUNDING	 STRUCTURE. BUMPERS WERE REPLACED 267 CYCLES EARLIER. ELEVATOR STOP BUMPER ASSEMBLIES REPLACED IN ACCORDANCE AMM,  AD/CF	-2001-08 & AWLTR 2-20.ELEVATOR RIGGING CHECKED WITH NO PROBLEMS IDENTIFIED.  INSPECTION PER IOD REDUCED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071200038	20050712	00038	NE  	2005	7	12	CA050602004      	3	20050531	G	6111	SFA13M1ROA	BLADE           	HAMSTD      	14SF        	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			17089			13157					(CAN) PILOT REPORTED THAT THEY HAD NO INDICATION OR LOAD ON B-PHASE OF NR 2 PROPELLER DEICE SYSTEM. INSPECTION OF NR 2 P	ROPELLER FOUND THAT NR 4 BLADE HAD AN OPEN CIRCUIT IN HEATER MAT. BLADE REPLACED WITH SERVICEABLE GROUND RUNS CARRIED OU	T AND FOUND SERVICEABLE AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071200014	20050712	00014	NM  	2005	7	12	CA050602005      	1	20050419	G	2730	85520271003	STOP            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR	DETERIORATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) ABNORMAL AMOUNT OF ELEVATOR TRAVEL OBSERVED DURING FLIGHT CONTROLS RANGE OF TRAVEL CHECKS.ONE UPPER ELEVATOR STOP 	BUMPER ASSEMBLY MISSING AND THE OTHER UPPER ELEVATOR STOP BUMPER ASSEMBLY SPLIT.  NO DAMAGE WAS NOTED TO THE SURROUNDING	 STRUCTURE. BUMPERS WERE REPLACED 215 CYCLES EARLIER. ELEVATOR STOP BUMPER ASSEMBLIES REPLACED IN ACCORDANCE AMM , AD/CF	-2001-08 & AWLTR 2-20.  ELEVATOR RIGGING CHECKED WITH NO PROBLEMS IDENTIFIED.  INSPECTION PER IOD REDUCED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071200037	20050712	00037	GL  	2005	7	12	CA050602006      	2	20050519	G	7250		BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					SPUR ADAPTER	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) THIS WAS A NEW 2 1/2 BEARING AND NEW SPUR ADAPTER 104.4 HRS AGO , NO WARNING UNTIL STARTING, AT WHICH TIME, MAG PL	UG WAS FOUND FULL. WE BELEIVE THAT THE MATERIAL WAS BAD/SOFT ON THE INNER RACE OF THE SPUR ADAPTER. WE SENT THE SUSPECTE	D PIECES OFF TO OUR ENGINE SUPPLIER FOR FURTHER TESTING AND VERIFICATION. THIS IS THE 2ND TIME WE HAVE HAD THE EXACT SAM	E PROBLEM.  WE EXAMINED OUR INSTALLATION PROCEEDURES WITH THE MANUFACURER AND OUR ENGINE SUPPLIER AND NO PROBLEMS WERE N	OTED. UPON NEW INFORMATION COMING TO LIGHT I WILL UPDATE ACCORDINGLY.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071200013	20050712	00013	NM  	2005	7	12	CA050602007      	1	20050517	G	3250	89881	LINK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG STEERING	WORN            	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			14333			DCL17988					(CAN) ON LANDING PILOTS NOTICED A SHIMMY COMING FROM NOSE AREA OF THE AIRCRAFT.  INSPECTION OF THE NLG FOUND EXESSIVE PL	AY IN THE NLG STEERING LINKS. LINKS REMOVED AND INSPECTED FOUND THE LINK ENDS HAD WEAR AND A CRACK IN ONE OF THE BEARING	 JOURNALS. SERVICEABLE LINKS,  BEARINGS AND PACKINGS INSTALLED IAW CMM, CHECKED SERVICEABLEAIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071800014	20050718	00014	NM  	2005	7	18	CA050602008      	1	20050531	G	2782	10605582	ACTUATOR        			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					KRUGER FLAP	INOPERATIVE     	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, CREW NOTICED THAT THE NR 1 KRUGER FLAP WOULD NOT RETRACT.  THE CREW LEFT THE FLAPS IN THE DOWN POSIT	ION AND RETURNED TO BASE. MAINTENANCE REPLACED THE NR 1 KRUGER FLAP ACTUATOR AND THE A/C WAS RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005071400057	20050714	00057	EA  	2005	7	14	CA050603001      	1	20050528	G	2821		FILTER          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL SYSTEM	CONTAMINATED    	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL, RT FUEL FILTER CAUTION MESSAGE.  AFTER RUN UP, IT OCCURRED AGAIN. EARLIER SAME DAY, LT FUEL F	ILTER CAUTION MESSAGE POSTED. MAINT REPLACED LT ENG FUEL FILTER PRESSURE SWITCH AND FUEL FILTER.  RT ENG FILTER WAS ALSO	 REPLACED AND SENT FOR ANALYSIS. RESULTS OF ANALYSIS, FILTER WAS FOUND GREASY AND WHITE/BROWN IN COLOR. MATERIAL IS CARB	ON, GREASE (VASELINE) IN BIG AMOUNTS. TANK INSP WAS PERFORMED.  APU FUEL FILTER REMOVED AND REPLACED. SAME SUBSTANCE FOU	ND AS WELL. FUEL ANALYSIS WAS NO CONTAMINATION.  HIGH PWR ENG RUN PERFORMED FOR 15 MIN AND APU RUNNING AS WELL. INSPECTE	D BOTH ENG FILTER AND APU FILTERS WITH NO FURTHER FINDINGS.  FILTERS REMOVED AND REPLACED.  AC RELEASED FOR SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071300024	20050713	00024	EA  	2005	7	13	CA050603002      	1	20050531	G	5230	CC670387303	SEAL            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					AFT CARGO DOOR	OUT OF ADJUST   	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) DURING CLIMB, THE CABIN PRESSURE STARTING INCREASING AND THE CREW COULD NOT ADJUST.  EMERGENCY WAS DECLARED AND TH	E AIRCRAFT RETURNED TO BASE.  MAINTENANCE FOUND SMALL LEAKS ABOVE SERVICE DOOR, FILLET SEALANT ADDED.  AFT CARGO DOOR WA	S RE-ADJUSTED, ITS SEAL REPLACED.  PRESSURIZATION CHECKED GOOD.  AIRCRAFT RETURNED TO SERVICE.  SEAL: P/N CC670-38730-3.	VENDOR: INDUSTRIAL VENTILATION (CAGE: 98269) NOT LISTED IN THE DROP DOWN MENU.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005071200036	20050712	00036	GL  	2005	7	12	CA050603003      	2	20050524	G	7230	6890550	COMPRESSOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	SEIZED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA			10372					CAE840769			(CAN) OVERHAULED COMPRESSOR ASSY WAS INSTALLED ON ENGINE AS PER ALLISON 250-C20B MM. SATISFACTORY GROUND RUN/LEAK CHECKS	 WERE CARRIED OUT. SATISFACTORY TEST FLIGHT AND POWER CHECKS WERE CARRIED OUT. THE HELICOPTER WAS PUSHED INTO THE HANGER	 AND LEFT FOR TWO DAYS, FOLLOWING WHICH THE HELICOPTER WAS PUSHED OUTSIDE AND A START ATTEMPTED. THE IGNITOR FUNCTIONED 	BUT THE ENGINE WOULD NOT CRANK. AFTER SOME TROUBLESHOOTING, IT WAS FOUND THAT THE COMPRESSOR WOULD NOT TURN. THE COMPRES	SOR ASSY WAS REMOVED AND SENT BACK TO THE OVERHAUL SHOP FORINSPECTION.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071400066	20050714	00066	EU  	2005	7	14	CA050603004      	1	20050529	G	3251	28784101	SERVO VALVE     			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					NLG STEERING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC LEAK AT NOSE GEAR. HYDRAULIC SERVO VALVE FOUND LEAKING. VALVE REPLACED.						2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005071400065	20050714	00065	EU  	2005	7	14	CA050603005      	1	20050525	G	3241	95427322	VALVE           			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					ANTI-SKID SYSTEM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION, LT ANTI-SKID VALVE FOUND UNSERVICEABLE. LT ANTI-SKID VALVE REPLACED.						2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005071300023	20050713	00023	CE  	2005	7	13	CA050606001      	1	20050601	G	5311	5042002857	FRAME           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16888								(CAN) DURING INSP 3 CRACKS WERE FOUND IN LT FRAME AT FUSELAGE STATION 207.00.  ONE OF CRACKS (CRACK NR 1) MAY HAVE BEEN 	CAUSED BY A SMALL HOLE THAT WAS DRILLED WITHOUT ANY EDGE DISTANCE, CRACK TRAVELED FROM DRILLED HOLE, AROUND CORNER TO LO	WEST LIGHTING HOLE IN FRAME. DRILLED HOLE WAS NOT USED, IT WAS PROBABLY USED AT SOME TIME IN PAST TO HOLD PART OF INTERI	OR IN PLACE. THIS HOLE WAS ALSO DRILLED THROUGH HEATING DUCT MOUNTED TO FRAME. SECOND CRACK APPEARS TO HAVE STARTED FROM	 LOWEST STRINGER CUTOUT, MOVED IB TO SECOND LIGHTNING HOLE FROM BOTTOM.  THIRD CRACK STARTED FROM SAME STRINGER CUTOUT S	TARTED IT WAY DOWN TO SAME LIGHTNING HOLE AS FIRST CRACK, CRACK HAD ONLY TRAVELED ABOUT INCH.  FRAME IS BEING REPLACED.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2005071300022	20050713	00022	EU  	2005	7	13	CA050606002      	1	20050601	G	7920	174222701	INDICATOR       			SNIAS 	350   	AS350D      	8680803	EU  										ENG OIL BY-PASS	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING OIL BYPASS INDICATOR CHECK, THE RED INDICATOR BUTTON FAILED TO POP, TWO TESTS WERE TRIED WITH BOT	H FAILING. THE A/F ENGINE OIL FILTER INDICATOR ASSY WAS REPLACED (P/N 1742227-01), ANOTHER OIL BYPASS INDICATOR CHECK WA	S PERFORMED WITH THE CORRECT RESULTS.				1	G	7	1 	3U				H9EU    					 
2005071300021	20050713	00021	WP  	2005	7	13	CA050606003      	1	20050606	G	2910		FITTING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O54O  	IO540AE2A   	 	EA  					HYDRAULIC PUMP	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) ACFT GROUNDED DURING A PRE-FLIGHT CHK WHEN HYD OIL FOUND LEAKING ON RT FWD SERVO TEE-FITTING. LINES CHECKED FOR TI	GHTNESS. FITTINGS FOUND LOOSE. FITTINGS TIGHTEN & SYSTEM CHKD WITH HYD POWER PACK. NO LEAKS FOUND.					1	G	7	1 	3O	3	0		H11NM   	1E4				 
2005071300020	20050713	00020	CE  	2005	7	13	CA050606004      	1	20050601	G	3230	MC815AS1	CONTROLLER      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, L G WAS SELECTED UP AND GEAR TRAVELED MOST OF WAY UP, STOPPED WITH GEAR IN TRANSIT LIGHT STILL ILLU	MINATED.  MANUAL EXTEN WAS COMPLETED, AC LANDED W/O FURTHER INCIDENT. DURING INSP, DAMAGE WAS DISCOVERED ON SKIN OF LT I	B GEAR DOOR, LT IB CAM ASSY, LT IB CAM SUPPT BRACKET, LT IB GEAR CAM ROLLER.  PREVIOUS, FLT CONTROLLER MALFUNCTION CAUSI	NG GEAR TO OVER TRAVEL UP DIRECTION DAMAGING /CHANGING ALIGNMENT OF CAM ASSY ON LT IB GEAR DOOR. WHEN GEAR WAS SELECTED 	UP, CAM NO LONGER PROPERLY LINK UP WITH ROLLER AND GEAR BENT CAM OVER INSTEAD ENGAGING IT, CLOSING DOOR, CAUSING GEAR MO	TOR TO BE OVER WORKED WHICH POPPED BREAKER. CONTROLLER, MOTOR, CAM ASSY WERE REPLACED.  AC RETURNED TO SERVICE.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2005071800006	20050718	00006	CE  	2005	7	18	CA050606005      	1	20050527	G	7500	SD028226	COUPLING        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					BLEED AIR SYS	MISALIGNED      	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT AFTER TAKEOFF, THE LT PYLON BLEED AIR LEAK LIGHT CAME ON.  REDUCED POWER ON LT ENGINE, LIGHT WENT	 OUT AFTER ABOUT 1 MINUTE, RETURNED TO AIRPORT.  INSPECTION FOUND IB END OF OZONE CONVERTER IN LOW PRESSURE BLEED AIR SY	STEM,  MISALIGNED AND HAD BLOWN THE COUPLING SEAL P/N SD028-226.  REPLACED SEAL AND REALIGNED COUPLING. GROUND RUN FUNCT	ION CHECK SERVICEABLE.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005071300019	20050713	00019	SW  	2005	7	13	CA050607001      	1	20050606	G	3213	D2571	SADDLE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					SKID TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT OUTER SADDLE CRACKED AT THE AFT SPLIT LINE AT THE RIDGE LINE FOLLOWING THE CONTOUR OF THE SKID TUBE AND CRO	SS TUBE. THE CRACK TURNS 90 DEGREES FROM THE TOP OF THE SADDLE TO THE REAR. THE PART WAS SENT TO HEADQUARTERS FOR INSPEC	TION.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005071300018	20050713	00018	CE  	2005	7	13	CA050607002      	1	20050603	G	3243	4500SA1	CONTROL VALVE   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	BRAKE CONTROL	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AC LANDED AT INTENDED AIRSTRIP.  PARKING BRAKE WAS SET AND ENGINES SHUTDOWN.  WHEN AC WENT TO DEPART THE PARKING B	RAKE WAS RELEASED BUT THE BRAKES STAYED ON.  IT WAS FOUND THAT THE BRAKE CONTROL VALVE FAILED INTERNALLY, THE PLUNGER AC	UTATOR SHAFT SHEARED TRAPPING THE BRAKE FLUID IN THE LINES TO THE BRAKES.  A MAINTENANCE CREW WAS SENT TO REPLACE THE CO	NTROL VALVE AND THE AIRCRAFT CONTINUED ON ITS WAY.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071300017	20050713	00017	CE  	2005	7	13	CA050607003      	1	20050602	G	5610	10138402522	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 FLIGHT ,THE RT WINDSHIELD CRACKED. THE FLIGHT WAS COMPLETED AND THE OUTER PLY WAS FOUND TO BE CRACKE	D. THE DEFECT WAS WITHIN LIMITS SET OUT IN AFM, MM AND GMEL. IT WAS DEFERRED IAW GMEL AND SUBSEQUENT FLIGHTS COMPLETED I	AW RESTRICTIONS UNTIL WINDSHIELD WAS REPLACED. WINDSHIELD WAS INSTALLED SEPT 18, 2004 AND HAD BEEN REPAIRED MAY 2004.  S	OMETHING OF NOTE WAS THAT AS THIS AIRCRAFT WAS CALLING IN, ANOTHER CMA AIRCRAFT HAD THE SAME DEFECT WITHIN MINUTES.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071300016	20050713	00016	CE  	2005	7	13	CA050607004      	1	20050602	G	5610	10138402522	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 FLIGHT ,THE RT WINDSHIELD CRACKED. THE FLIGHT WAS CONTINUED AND UPON LANDING THE OUTER PLY WAS FOUND	 CRACKED. THE DEFECT WAS FOUND TO BE WITHIN AIRWORTHINESS LIMITS FOR CONTINUED FLIGHT UNDER GMEL RESTRICTIONS. THE WINDS	HIELD HAD BEEN INSTALLED OCT 8, 2004 AND REPAIRED MAY 2004. ANOTHER CMA AIRCRAFT HAD THE SAME DEFECT WITHIN MINUTES. A S	DR HAS BEEN SUBMITTED FOR BOTH.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071400064	20050714	00064	CE  	2005	7	14	CA050607005      	1	20050607	G	5521	043200121	SPAR            	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HINGE BRACKET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12594								(CAN) WAS REPLACING RT ELEVATOR SKIN DUE TO HINGE WEAR (OB HINGE POINT IS PART OF SKIN). CRACKS WERE FOUND ON THE SPAR P	/N 0432001-21 UNDER IB HINGE BRACKET P/N 0432001-72. THESE CRACKS COULD NOT BE SEEN THRU VISUAL INSPECTION ON THE FORWAR	D SIDE OF THE SPAR. MFG HAS UPDATED THE SPAR ASSY WHICH COMES WITH A NEW, MORE SUPPORTED BRACKET INSTALLED TO REDUCE THI	S ISSUE. IF THIS HINGE (ON THE OLDER STYLE SPAR) IS AT ALL WORN THIS AREA SHOULD BE INSPECTED WITH GREAT DETAIL. CODE DE	TAIL 7B) ELEVATOR WAS FOUND HAVING AN ABNORMAL AMOUNT OF PLAY DURING A PHASE INSPECTION. DURING REPAIR FOR THIS PLAY THE	 SPAR WAS FOUND CRACKED.  NO ACTION WAS TAKEN BY FLIGHT CREW.	1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005071300015	20050713	00015	CE  	2005	7	13	CA050607006      	1	20050602	G	5610	10134802522	WINDSHIELD      			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL260 THE INNER PANE OF THE RT WINDSHIELD SHATTERED WITH A LOUD BANG, STARTLING THE CREW AND PASS	ENGERS. THERE IS NO APPARENT REASON FOR THE FAILURE. THE LT WINDSHIELD INNER PANE SHATTERED AND WAS REPLACED IN SEPTEMBE	R OF 2004 AT 1879.7 HOURS, 1835 CYCLES.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005071200035	20050712	00035	CE  	2005	7	12	CA050607007      	1	20050515	G	7810	3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE80591			(CAN) WHILE CONDUCTING A PHASE 4 INSPECTION, THE EXHAUST STACKS WERE REMOVED FROM THE RT ENGINE. A VISUAL INSPECTION HAD	 INDICATED A CRACKED EXHAUST DUCT. POWER SECTION WAS REMOVED FOR INVESTIGATION AND REPAIRS. THE EXHAUST DUCT HAD CRACKIN	G IN THE AFT END OF THE INNER CONE. THE CRACKSHAD PROPAGATED ALONG THE CONE THROUGH THE EXHAUST DUCT INNER SUPPORT AND T	HROUG H THE INNER SUPPORT WELD BEAD.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005071300014	20050713	00014	CE  	2005	7	13	CA050607008      	1	20050602	G	5753	501600036	BRACKET         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DO TO A CRACK BEING FOUND ON ONE OF OUR AIRCRAFT, A FLEET CAMPAIGN IS BEING COMPLETED TO INSPECT ALL THE FLAP ACTU	ATOR ATTACHMENT BRACKETS. DURING THIS SPECIAL INSPECTION, THE LT IB BRACKET WAS FOUND TO HAVE 4 SMALL CRACKS IN THE AREA	 AROUND THE FWD HOLE OF THE BRACKET.  (BRACKET REPORTED IN SDR 20050526003).  BRACKET REPLACED AND AIRCRAFT WAS RETURNED	 TO SERVICE.			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2005071400111	20050714	00111	NM  	2005	7	14	CA050608001      	1	20050513	G	3246	300620	WHEEL           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			22372								(CAN) WHILE TAXING IN AFTER LANDING THE CREW HEARD A LOUD BANG ONCE AT THE GATE THE CREW INSPECTED THE AIRCRAFT AND FOUN	D THE LT OB TIRE WAS FLAT.  MAINT FOUND A 18 INCH SECTION OF THE IB WHEEL HALF OF THE LT OB TIRE WAS MISSING.  IT WAS FO	UND ON THE TAXIWAY.  MAINTENANCE ALSO FOUND THAT THE BRAKE UNIT INSTALLED ON AIRCRAFT WAS DAMAGED AND REQUIRED REPLACEME	NT.  AC WAS INSPECTED FOR FURTHER DAMAGE, NONE WAS NOTED.  BOTH MAIN WHEELS AND NR 1 BRAKE ASSEMBLIES WERE REPLACED, ALL	 SYS FUNCTIONED.  AC WAS RETURNED TO SERVICE.  MAIN WHEEL ASSY HAD BEEN INSTALLED ON THE AC FOR 58 DAYS.  WHEEL ASSY HAS	 BEEN SENT BACK TO THE MFG FOR ANALYSIS.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071500132	20050715	00132	CE  	2005	7	15	CA050608003      	1	20050531	G	5347	04101342	SEAT TRACK      			CESSNA	150   	150K        	2071822	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT FWD END OF SEAT TRACKS, 2 SCREWS BEYOND END OF TRACK.  SCREWS ATTACH TO ANGLE UNDER FLOOR SKIN. CRACKS ORIGINAT	E FROM UNDER SCREW HEADS, FWD OF TRACK. TRACK, PILOT'S IB, DOES NOT HAVE UNDER FLOOR ANGLE. THERE WERE NO CRACKS THIS LO	CATION. OTHER 3 WERE CRACKED. ONE CRACK ON OB TRACK WAS 3 INCHES LONG.  FLOOR AND SEAT RAIL FLEXING UP AND DOWN, ANGLE T	HAT ATTACHES TO LWR DOOR FRAME AND FLOOR, ALSO FLEXED UP AND DOWN. THIS CHAFED HOLE IN FUEL LINE THAT PASSES UNDER IT, W	HICH WAS ORIGINAL PROBLEM.  CARPETING IN THIS AREA IS GLUED TO FLOOR, MAKING IT IMPOSSIBLE TO SEE. WHEN FUEL LEAK BECAME	 AN ISSUE, CARPET HAD TO BE PEELED UP TO GAIN ACCESS TO FUEL LINE ON PILOT'S SIDE. THEN FIRST CRACKS BECAME KNOWN.	1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2005071800022	20050718	00022	CE  	2005	7	18	CA050608004      	1	20050526	G	2750	12602443	ROD END         			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	FLAP SYNC ROD	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROD END ON FLAP SYNCHRONIZING ROD FOUND BENT FROM CONTACT WITH FLAP BELLCRANK DUE TO RIGGING OF FLAP SYSTEM FROM M	ANUFACTURE.  NEW ROD INSTALLED AND SYSTEM RIGGED SO IT WOULD NOT CONTACT THE BELLCRANK.					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P58GL	 
2005071400063	20050714	00063	CE  	2005	7	14	CA050608005      	1	20050524	G	2120	66150405	DUCT            			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ACM	LOOSE           	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA						49187					(CAN) DEPARTURE AFTER MAINTENANCE, AT FL 22,000 CLIMBING, CREW HEARD A LOUD BANG, THEN THE CABIN ALTITUDE BEGAN TO RISE 	( DELTA PRESSURE DROPPED). THE CREW STOPPED CLIMB AND DESCENDED BELOW 10,000 FEET AND ELECTED TO RETURN TO POINT OF DEPA	RTURE.  MAINTENANCE CREW FOUND THE AIR CYCLING MACHINE (ACM) DUCT (P/N 6615040-5) GOING TO THE WATER SEPARATOR TO BE LOO	SE FROM RUBBER MATING DUCT.  THE GROUND CREW REATTACHED THE DUCT ASSEMBLY AND TIGHTENED ALL CLAMPS (P/N S1891-64).  PRES	SURE CHECK AND LEAK DUCT CHECKED.		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005071400110	20050714	00110	EA  	2005	7	14	CA050608006      	1	20050603	G	2720	C6CFM144328	LEVER           	DHAV        		DHAV  	DHC6  	DHC6        	2802606	EA  										RUDDER PEDAL	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A NEW PART WAS PURCHASED (FROM OTHER THAN THE OEM).  TO REPLACE AN UNSERVICEABLE COMPONENT.  THE NEW PART ARRIVED 	AND WAS FOUND TO BE IMPROPERLY MANUFACTURED. THE CENTER HOLE WAS NOT DRILLED INTO THE PART AT THE PROPER SIZE, ONLY A PI	LOT HOLE WAS PRESENT.				1	H	7	2 	3T			RT	A9EA    					 
2005071500133	20050715	00133	EA  	2005	7	15	CA050608007      	1	20050604	G	2913	66EAL300	PUMP            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	LT HYD SYSTEM	SEPARATED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE AIRCRAFT WAS ON APPROACH WHEN THE LANDING GEAR WAS SELECTED AND IT DID NOT EXTEND. HYDRAULIC PRESSURE WENT TO 	0 AND THE CREW INITIATED AN EMERGENCY LOWERING. THE GEAR EXTENDED AND A SUCCESSFUL LANDING WAS MADE WITHOUT INCIDENT. AN	 INVESTIGATION REVEALED THAT THE LT HYDRAULIC PUMP HEAD HAD SEPARATED SLIGHTLY WHICH CAUSED AN EXTREME LEAK AND DEPLETED	 ALL THE FLUID FROM THE RESERVOIR. EVEN THOUGH THE BOLTS FOR THE HEAD WERE LOCK WIRED THEY WERE FOUND TO BE LOOSE. ALSO,	 AN OUTPUT LINE WAS ALSO LEAKING AROUND ONE OF THE FLARED ENDS. THE PUMP AND LINE WAS REPLACED AND THE ENGINE AREA CLEAN	ED. THE RESERVOIR WAS REPLENISHED AND THE AIRCRAFT WAS RETURNED TO SERVICE.	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2005071400109	20050714	00109	SW  	2005	7	14	CA050608008      	1	20050608	G	6210	206010200033	BLADE           			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											BLADE WAS DECLARED BEYOND SALVAGE (SCRAP) ON 12-09-04 AND FOUND WITH SERVICEABLE TAG ON 04-17-05.						1	G	7	1 	3U				H2SW    					 
2005071300013	20050713	00013	CE  	2005	7	13	CA050608009      	1	20050606	G	3230	1225P363	PRESSURE SWITCH 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT MLG	INTERMITTENT    	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA							BB710				(CAN) ON APPROACH, CREW SELECTED GEAR DOWN AND BOTH MAIN GEAR REMAINED IN WHEEL WELLS.  CREW NOTED THAT GEAR DOORS WERE 	MOVING SLIGHTLY ON DOWN SELECTION. TWO MORE GEAR UP/GEAR DOWN SELECTIONS WERE REQUIRED BEFORE GEAR FINALLY EXTENDED AND 	LOCKED INTO THE DOWN POSITION. FERRY PERMIT WAS ISSUED AND AIRCRAFT RETURNED TO BASE WITH GEAR DOWN. MAINTENANCE FOUND T	HE PRESSURE SWITCH WHICH CONTROLS THE HYDRAULIC LANDING GEAR SYSTEM PUMP,  WHICH MAINTAINS SYSTEM PRESSURE,  WAS INTERMI	TTENT. PRESSURE SWITCH WAS REPLACED, GEAR SWINGS COMPLETED AND AIRCRAFT RETURNED TO SERVICE.		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005071200034	20050712	00034	NE  	2005	7	12	CA050608010      	2	20050325	G	7261	30756691	SEPARATOR       			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					AIR/OIL	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P73210			(CAN) DURING OIL CHANGE, METAL FOUND IN OIL AND FILTER. SOURCE OF METAL FOUND TO BE AIR/OIL SEPARATOR ALUMINUM LIGAMENTS	. PART CHANGED AS PER SB TFE731-72-3696 TO NEWPART NUMBER 3075781-1.					2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2005071400062	20050714	00062	SO  	2005	7	14	CA050608011      	1	20050526	G	2910	1776602	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT HYD SYSTEM	PUNCTURED       	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) GEAR HANDLE DID NOT RETURN TO NEUTRAL. GEAR LIGHTS INDICATED 3 GREEN. HAD TO PUMP GEAR DOWN IN ORDER TO MAKE SURE 	GEAR WAS DOWN. SMELL OF HYDRAULIC FLUID IN COCKPIT.  HAD TO WAIT UNTIL JUNE 01, 2005 FOR FAA REPAIR STATION TO TROUBLESH	OOT.  FOUND GEAR EXTENSION RETURN LINE WITH HOLE. REMOVED AND REPLACED HOSE, CUSTOMER SUPPLIED PART. GEAR HANDLE FUNCTIO	NS NORMALLY WHEN TESTED WITH RT ENG.  HOSE WAS INSPECTED AND FOUND TO BE 1973 VINTAGE. INSPECTION CALLS FOR PRESSURE CHE	CK ALL FLUID HOSES IN WING AREA AFTER 10 YEARS TIME-IN-SERVICE. VISUALLY CHECK FOR LEAKS. HOSES THAT PASS INSPECTION MAY	 REMAIN IN SERVICE AND CHECKED THERE AFTER EACH FIVE YEARS TIME-IN-SERVICE.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005071200033	20050712	00033	NE  	2005	7	12	CA050609002      	2	20050315	G	7314	430137701	PUMP            			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								LE43443CE			(CAN) DURING GROUND RUNUP, FUEL WAS LEAKING FROM FUEL PUMP, WHERE THE FUEL PUMP ATTACHES TO THE GEARBOX.  FUEL PUMP RECE	IVED AFTER INTERNAL SPLINE AD INSPECTION WHICH REQUIRES REMOVAL OF FRONT SEAL HOUSING TO ENABLE REMOVAL OF SHAFT. THIS S	EEMS TO BE THE AREA OF THE FUEL LEAK.				1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2005071200032	20050712	00032	NE  	2005	7	12	CA050609003      	2	20050318	G	7323	430123507	LIMIT SWITCH    			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ENGINE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING OVER SPEED LIMITER TEST, ENGINE NG OSCILLATING 10 PERCENT, FOLLOWED BY TOT AND ITT REPLACED OVER SPEED LIMI	TER - PROBLEM CORRECTED.					1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2005071300012	20050713	00012	CE  	2005	7	13	CA050609005      	1	20050608	G	3297	70HF10	DIODE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	FAULTY          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE NR 1 INVERTER WARNING LIGHT ILLUMINATED AND THE NR 1 DUAL FEED BUSS CB TRIPPED. AS GEAR WAS BEING 	EXTENDED AT THE TIME, GEAR DOWN SHOWED 3 GREEN BUT GEAR INTRANSIT LIGHT ALSO ILLUMINATED. PILOT OVERSHOT RUNWAY AND PERF	ORMED EMERGENCY GEAR EXTENSION PROCEDURE, THIS CONFIRMED GEAR DOWN AND LOCKED.  TROUBLESHOT SYSTEM AFTER LANDING AND FOU	ND A FAULTY DIODE, THIS DISABLED A BUSS FEEDER TO NR 1 BUSS WITH THE AIRCRAFT IN THE APPROACH AT NIGHT, THERE WAS MORE T	HAN A 50 AMP DRAW FROM THE NR 1 BUSS SO THE REMAINING CB TRIPPED. THIS ALSO HAD THE EFFECT OF SHOWING A WARNING FOR GEAR	 INTRANSIT AND TOOK ALL THE NR 1 BUSS FEED SYSTEMS OFF LINE.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005071200031	20050712	00031	CE  	2005	7	12	CA050609006      	1	20050418	G	8011	MMU4001	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	BURNED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER WOULD NOT ENGAGE, REMOVED UNIT FOUND ARC/BURNED MARK AT REAR COVER BY BRUSHES.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005071200030	20050712	00030	CE  	2005	7	12	CA050609007      	1	20050512	G	8011	PM2403	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FOD             	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER WOULD NOT OPERATE. STARTER REMOVED,  FOREIGN OBJECT AT REAR CASE OF STARTER. MOTOR RETURNED FOR WARRANTY.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005071200029	20050712	00029	CE  	2005	7	12	CA050609008      	1	20050601	G	8011	PM2403	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER WOULD NOT OPERATE. STARTER REMOVED, RATTLING SOUND IN MOTOR END BY BRUSHES.  STARTER RETURNED TO SUPPLIER.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005071300011	20050713	00011	EU  	2005	7	13	CA050609009      	1	20050516	G	6220	350A31187320	SCREW           	AEROSP      		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					M/R HEAD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION NOTED ON YELLOW BLADE (MAIN ROTOR HEAD) PITCH LINK UPPER BOLT WHERE IT ATTACHES TO BLADE HORN.  REMOVED 	BOLT FOUND WEAR SPOT ON BOLT SHANK FROM PITCH LINK SPHERICAL BEARING.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005071300042	20050713	00042	SO  	2005	7	13	CA050609010      	2	20050523	G	8520	AEC654729	PISTON          	CONT        		CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	NR 1 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						OA13979					(CAN) DURING FLIGHT, MOMENTARY DROP IN OIL PRESSURE WAS NOTED.  DURING NEXT OIL CHANGE, SIGNIFICANT AMOUNTS OF METAL AND	 CARBON WERE NOTED IN OIL SCREEN.  DUE TO HIGH LEVELS OF CARBON, IT WAS SUSPECTED THAT AN EXHAUST VALVE HAS FAILED.  NR 	1 CYLINDER WAS SUSPECT.  WHEN THAT CYLINDER WAS REMOVED, MARKS WERE NOTED IN PISTON.  IT WAS OBVIOUS THAT SOMETHING WAS 	BEING BANGED AROUND INSIDE ENGINE.  A CLOSE LOOK INSIDE ENGINE REVEALED THAT NR 2 PISTON WAS MISSING HALF OF ITS PISTON 	SKIRT.  ENGINE WAS REMOVED FOR OVERHAUL. MANY OF BROKEN PIECES OF PISTON WERE LOCATED IN OIL SUMP.  MOST PIECES ARE TOO 	LARGE TO BE REMOVED FROM DRAIN HOLE.  PISTON ASSY WILL BE SENT  FOR FURTHER EVALUATION.	1	H	7	1 	3O	3	O		5A5     	E269	5	N	P874	 
2005071400061	20050714	00061	CE  	2005	7	14	CA050609012      	1	20050608	G	2821	121640719	RESERVOIR       			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUEL SYSTEM	CRACKED         	S				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED DURING WALKAROUND, FUEL DRAIN ON LT BELLY WOULD NOT STOP DRIPPING.  CLOSER INSPECTION REVEALED THAT	 FAULT WAS IN DRAIN VALVE BUT THE RESEVOIR ITSELF AND FOUND THAT WELD WAS CRACKED ADJACENT TO MOUNTING TAB TO AIRCRAFT S	TRUCTURE.  RESEVOIR REMOVED, REPAIRED AND REINSTALLED.  THIS IS THE SECOND REMOVAL OF THIS RESEVOIR.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2005071300041	20050713	00041	NE  	2005	7	13	CA050609013      	2	20050527	G	7200		ENGINE          								PWA   	PW120 	PW127       	 	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								127184			(CAN) OPERATORS REPORT OF FOD TO LP IMPELLER. INSPECTION REVEALED THAT REMAINING COMPONENTS IN COLD AND HOT SECTION SUFF	ERED MINIMAL DAMAGE WITH EXCEPTION OF ONE LP TURBINE BLADE. MOST FOREIGN MATERIAL HAD HIT LP IMPELLER EXITED BACK OUT TH	ROUGH INTAKE. A MINIMAL AMOUNT MADE IT PAST LP IMPELLER RESULTING IN MINOR DAMAGE TO HP IMPELLER, DIFFUSER ENTRY AREAS I	N ICC AND GGC.  DISASSEMBLY OF ENGINE REVEALED OTHER HEAVY DAMAGE.  TM HAD HEAVY METAL CONTAMINATION OF OIL SYSTEM DUE T	O AN UPPER TOWER SHAFT BEARING FAILURE.  IT IS OBVIOUS THAT FOD INCIDENT OCCURRED FIRST DUE TO FACT THAT ENGINE WOULD NO	T BE ABLE TO RUN AFTER BEARING FAILURE.  HEAVY SURFACE CORROSION WAS ALSO NOTED IN COLD SECTION OF TURBOMACHINE.						4	T			E20NE				 
2005071300010	20050713	00010	CE  	2005	7	13	CA050609014      	1	20050602	G	3230	1018100423	LINK            			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	GEAR EXTENSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION THE EMERGENCY GEAR EXTENSION LINK WAS DISCOVERED CRACKED. THE ONLY INSPECTION METHOD WAS TO R	EMOVE THE PILOT'S FLOORBOARD. THE PROBLEM WITH THIS DEFICIENCY IS THAT THE MECHANICAL PUMP WILL WORK AS A SINGLE ACTION 	PUMP INSTEAD OF DOUBLE ACTING, THUS LOWERING THE GEAR IN AN EMERGENCY SITUATION SLOWLY. THE GEAR WOULD TAKE TWICE AS LON	G TO EXTEND. THE PART WAS REPLACED.			1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005071400108	20050714	00108	NE  	2005	7	14	CA050609015      	2	20050609	G	7210	3036180	REDUCTION GB    			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 2 ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29392								(CAN) DURING ROUTINE MAINTENANCE INSPECTION  , NR 2 ENGINE RGB CHIP DETECTOR FOUND FLAGGED. WHEN REMOVING CHIP DETECTOR 	FOR INSPECTION , AUTO SHUTOFF DID NOT ACTIVATE AS LARGE METAL CHIP FOUND HOLDING CHIP DETECTOR BASE VALVE OPEN. CHIP POS	SIBLY GEAR MATERIAL. CHIP LARGE ENOUGH TO STRADDLE BOTH PINS OF CHIP DETECTOR. ENTIRE ENGINE ASSEMBLY REMOVED, TO BE FOR	WARDED TO REPAIR FACILITY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071300009	20050713	00009	NE  	2005	7	13	CA050609016      	2	20050406	G	7320	0164248850	FUEL CONTROL    			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					ENGINE	MISRIGGED       	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) FCU INSTALLED. PILOT DID THE FIRST START AND THE T4 INDICATED 865C AT THE HIGHEST POINT BEFORE HE SHUT IT DOWN.  F	CU CHECKED AND FOUND THROTTLE RIGGING WAS DONE INCORRECTLY.  AT SHUTDOWN THE THROTTLE LEVER WAS LOCATED IN THE GREEN AT 	15 DEGREES. THE PILOT IS UNSURE OF THE LENGTH OF TIME THE T4 WAS AT THE RED LINE SO A T4 HOT INSPECTION WILL BE CARRIED 	OUT.  BOROSCOPE CARRIED OUT SATISFACTORY.			1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2005071300008	20050713	00008	EU  	2005	7	13	CA050609017      	1	20050505	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PULLEY SPLINES FOUND TO BE WORN BEYOND 2/3 DURING A 100 HR INSPECTION.  COUPLING S40 REPLACED 336.4 HOURS PREVIOUS	LY FOR THE SAME REASON. HYDRAULIC PUMP SPLINES FOUND 2/3 WORN. A NEW PUMP HAD BEEN INSTALLED 336.4 HOURS PREVIOUSLY FOR 	THE SAME REASON.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005071300007	20050713	00007	EU  	2005	7	13	CA050609018      	1	20050505	G	2620	RTA600	NOZZLE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					EXTINGUISHER	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						P001541					(CAN) FIRE EXTINGUISHER TRIGER AND NOZZLE HEAD DISLODGED AND SEPARATED FORM THE MAIN BODY.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005071300006	20050713	00006	SW  	2005	7	13	CA050609019      	1	20050415	G	6510	206040323003	HANGER ASSY     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R DRIVESHAFT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNUSUAL NOISE HEARD ON SHUTDOWN.  NR 1 T/R DRIVESHAFT HANGER SUPPORT 206-030-433-007 FOUND TO HAVE ELONGATED HOLES	 FOR HANGER ASSY ATTACH SCREWS 206-040-323-003. THESE SCREWS WERE WORN .333 THROUGH.  NEW HANGER MOUNT, HANGER ASSY, BEA	RING COLLAR, DRIVESHAFT SEGMENT AND RELATED HARDWARE INSTALLED.  A/C GROUND RUN - NO VIBRATION NOTED. NO ROUGHNESS NOTED	 IN THE REMOVED BEARING.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071300005	20050713	00005	CE  	2005	7	13	CA050609020      	1	20050607	G	5610	10138402522	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			CA											(CAN) DURING CRUISE AT FL 240 THE RT WINDSHIELD CRACKED ALONG THE CENTER POST.  THE FLIGHT CREW REDUCED ALTITUDE AND CAB	IN PRESSURIZATION IAW THE AFM, AND RETURNED TO BASE.  MAINTENANCE CREWS REPLACED THE WINDSHIELD.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005071500167	20050715	00167	EU  	2005	7	15	CA050610001      	1	20050602	G	2530	67254M	OVEN            			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					GALLEY	SPARKS          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CABIN CREW NOTICED SPARKS COMING FROM RT OVEN.  OVEN WAS DEACTIVATED AND REPLACED AT THE NEXT MAINTENANCE STATION.	 OVEN ROUTED TO REPAIR SHOP FOR INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2005071300004	20050713	00004	SO  	2005	7	13	CA050610002      	1	20050609	G	3213	45504006	FORK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13183								(CAN) DURING A WALKAROUND THE PILOT NOTICED THE BRAKE DISC WAS RUBBING AGAINST THE SIDE OF THE GEAR FORK.  AFTER THE WHE	EL ASSEMBLY WAS REMOVED A CRACK WAS FOUND ON THE AXLE AT THE INNER MOST BEARING RIDE LOCATION.  THE CRACK WAS MORE THAN 	A THIRD OF THE WAY AROUND THE AXLE. THE CRACK HAD STARTED ON THE BOTTOM AREA OF THE AXLE WHICH IS HARD TO SEE UNLESS A M	IRROR IS USED DURING NORMAL INSPECTION.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005071200040	20050712	00040	EU  	2005	7	12	CA050610003      	1	20050609	G	6520	4619002003	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION A SMALL BUT SIGNIFICANT QUANTITY OF FUZZ WITH SOME SMALL FLAKES WAS FOUND ON THE MAGNETIC CHIP DETEC	TOR. THE SAME HAD BEEN NOTICED ON THE PREVIOUS100 HOUR INSPECTION. NO CHIP LIGHT HAD BEEN REPORTED. THE OIL WAS DRAINED 	ON THE PREVIOUS INSPECTION AND NO METAL WAS FOUND. ON THIS OCCURRENCE THE OIL WAS DRAINED AND ONE SMALL FLAKE WAS FOUND.				1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2005071300003	20050713	00003	EU  	2005	7	13	CA050610004      	1	20050609	G	6510	11213152112	PIN             			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					T/R DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN REMOVING THE REAR FLANGE ON THE LONG TAIL ROTOR DRIVE SHAFT FOR REPLACEMENT OF THE BEARING SLEEVES, TWO OF TH	E THREE SILVER PLATED SPRING PINS WERE FOUND CRACKED. ONE WAS CRACKED ALONG IT S FULL LENGTH, THE OTHER EXTENDED FROM TH	E BEVELED END OF THE PIN ABOUT 80 PERCENT OF IT S LENGTH. BOTH CRACKS WERE LOCATED OPPOSITE THE SPRING PIN OPENING.				1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2005071300040	20050713	00040	NE  	2005	7	13	CA050610005      	2	20050609	G	7261		WARNING LIGHT   			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 1 ENG OIL	ILLUMINATED     	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								702985			(CAN) A/C WAS IN CRUISE WHEN THE NR 1 ENGINE OIL FILTER BYPASS LIGHT ILLUMINATED.  CHECKLIST WAS ACCOMPLISHED, POWER LEV	ER RETARDED, AND OIL PRESSURE DECREASED WITH POWER DECREASE. LOW OIL PRESSURE LIGHT CAME ON AND ENGINE WAS SHUTDOWN.  A/	C CONTINUED TO DESTINATION AND HAD AN UNEVENTFUL LANDING.  TROUBLESHOOTING AND MAINTENANCE CURRENTLY BEING ACCOMPLISHED,	 ENGINE IS BEING CHANGED.  A FULL TEARDOWN REPORT AND FOLLOW UP  WILL TAKE PLACE AS INFORMATION IS RECEIVED.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005071500154	20050715	00154	SW  	2005	7	15	CA050610006      	1	20050610	G	2435	230322844	DRIVE SHAFT     	LEARSIEGLER 		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STARTER GEN	SHEARED         	W				E				ENGINE SHUTDOWN         				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA						23497					(CAN) ON LANDING GENERATOR FAIL LIGHT ILLUMINATED.  AC SHUTDOWN, STARTER CHECKED AND SHAFT WAS FOUND TO BE SHEARED.  STA	RTER REMOVED AND REPLACED WITH SERVICABLE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071300002	20050713	00002	CE  	2005	7	13	CA050610007      	1	20050524	G	5610	1013840252	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CO-PILOTS WINDSHIELD SHATTERED IN CRUISE FLIGHT AT ALTITTUDE.  BOTH INNER AND OUTER PANES WERE AFFECTED.  AIRCRAFT	 RETURNED TO BASE.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005071300001	20050713	00001	SO  	2005	7	13	CA050610008      	1	20050607	G	2912	AN62341	HOUSING         	FACET       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD FILTER	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE LANDING GEAR FAILED TO EXTEND WHEN SELECTED. EMERGENCY EXTENSION CARRIED OUT.  LANDED SAFELY.  IN	VESTIGATION FOUND THE CANISTER OF THE HYDRAULIC FILTER ON THE LT ENGINE FIREWALL HAD CRACKED IN THE THREADS ALLOWING FLU	ID TO BE PUMPED OVERBOARD.  CANISTER REPLACED, FLUID REPLENISHED, GEAR SWINGS AND GROUND RUN CARRIED OUT.  OPERATION NOR	MAL.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005071800005	20050718	00005	EA  	2005	7	18	CA050613001      	1	20050612	G	2620	14034011	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FIRE EXTING	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING CRJ SERVICE CHECK ON ROUTINE MAINTENANCE. THE MECHANIC WAS UNABLE TO PUSH-IN EITHER LT OR RT (FIRE EXT PUSH	-OFF) SWITCHES/PBA.  BOTH PBA  ASSEMBLIES FOUND CONTAMINATED (CORROSION) WITH A WHITE POWDER DEPOSIT. REPLACED BOTH PBA 	ASSEMBLIES.  AIRCRAFT FUNCTION CHECKED AND RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071300039	20050713	00039	NE  	2005	7	13	CA050613002      	2	20050609	G	7261	AE7010101K0306	HOSE            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	OIL SUPPLY	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) OIL PRESSURE DROPPED PASSED 40 PSI IN FLIGHT.  SHUTDOWN LT ENGINE. FOUND OIL SUPPLY HOSE FROM OIL COOLER TO TOP OF	 ENGINE LEAKING. REPLACED WITH NEW. INSPECTED OIL CHIP DETECTOR, FOUND NO FAULTS. ADDED ENGINE OIL TO ENGINE. PERFORMED 	SATISFACTORY ENGINE RUNS AND LEAK CHECK.				1	L	7	2 	3T	4	T	RT	A8EA    	E4EA	6	C	P15EA	 
2005071200046	20050712	00046		2005	7	12	CA050613003      	4	20050610	G	6122	6506715	GOVERNOR        			LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  					PROPELLER	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			DE	DESCENT        	1			CA											(CAN) ON DESCEND TO A BOMBING RUN RPM AND FUEL FLOW WERE HIGH ON NR 4 ENGINE. THE ENGINE WAS SHUT DOWN AND FEATHERED, TH	E A/C RETURNED WITH OUT INCEDENT TO HIGH LEVEL A IRPORT. THE PROP GOVENOR WAS AJUSTED ANDTHE A/C WAS RETURED TO SERVICE.					2	L	7	4 	4T	4	T		4A22    	E282				 
2005080400064	20050804	00064		2005	8	4	CA050613004      	2	20050610	G	7421	URHM38E	SPARK PLUG      																	ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WELD EMBRITTLEMENT BELOW HEX ON SPARK PLUG BODY.  UPON INSTALL 1 SPARK PLUG SEPARATED FROM THREADED SECTION LEAVIN	G THAT PART STILL INSTALLED IN CYLINDER.  VISUALINSPECTION CONFIRMED WELD EMBRITTLEMENT, REMOVED ALL OTHER 23 PLUGS AND 	FOUND 19 WITH SIMILAR DEFECT, BLACK OVERHEATED WELD, AND CRACK AROUND THE AREA.  IF NOT DETECTED PRIOR TO FLIGHT COULD S	EPARATE INFLIGHT AND CAUSE LOSS OF ENGINE POWER.  SPARK PLUGS PURCHASED FROM AVIALL DATED FEB 14, 2005 WITH A LOT NUMBER	 OF 105173207. THIS PROBLEM MAY NOT BE LIMITED TO THIS SPECIFIC SPARK PLUG.  RECOMMEND A VISUAL INSPECTION FOR A BLACK R	ING BETWEEN HEX AND THREADED SECTION OF SPARK PLUG.														 
2005071500153	20050715	00153	NM  	2005	7	15	CA050613005      	1	20050607	G	7931		ENGINE          			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RIGHT	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								PCEFA0015			(CAN) AC, FLIGHT TESTING FOR A MODIFICATION TO AIRTANKER (FIREFIGHTING) ROLE. DURING PUSHOVER BOTH ENGINES LOST OIL PRES	S ACTIVATED MASTER CAUTION WARNING LIGHTS AND LOW OIL PRESS LIGHTS.  OIL PRESS LOSS LASTED LESS THAN 12 SECONDS FOR BOTH	 ENG BEFORE RECOVERING TO NORMAL LEVELS.  LT ENG DID NOT EXHIBIT ANY ANOMOLIES DURING OIL PRESS LOSS EVENT.  RT ENG PROP	 RPM DROPPED INITIATING UNDERSPEED PROTECTION.  SYS WORKED NORMALLY, HELD  PROP RPM AT 1060 ON OVERSPEED GOV.  CREW FEAT	HERED ENG AS PRECAUTIONARY MEASURE, RETURNED.  AN INVESTIGATION IAW AMM SHOWED NO ANOMOLIES AS A RESULT OF OIL PRESS LOS	S. SYS  ON RT ENG FUNCTIONED NORMALLY FOR THE PROP UNDERSPEED.  ROOT CAUSE OF LOSS OF OIL PRESS IS UNDER INVESTIGATION.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071300038	20050713	00038	EU  	2005	7	13	CA050613006      	1	20050602	G	3246	AHM7389	WHEEL           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN WHEEL NR 2 POSITION 15 PERCENT OF WHEEL RIM BROKEN OFF WHEEL (TIRE REMAINED PARTIALLY INFLATED).  WHEEL/TIRE 	ASSEMBLIES REPLACED.					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005071400060	20050714	00060	EU  	2005	7	14	CA050613007      	1	20050601	G	2910	L38710SA	SWIVEL FITTING  			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	RT HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			35645								(CAN) DURING DEPARTURE, LT MAIN WHEEL AND NOSE GEAR RETRACTED NORMALLY BUT RT MAIN GEAR WOULD NOT RETRACT.  CREW OBSERVE	D HYDR FLUID LEVEL AND OPERATING PRESSURE INDICATED LOW.  EMERGENCY GEAR EXTENSION AND AFTER ORBITING TO REDUCE FUEL LOA	D, RETURN FOR A LANDING.  INSP FOUND THAT A (SWIVEL FITTING) IN MAIN HYD RETRACTION/EXTENSION SYS OF RT MLG HAD (DEVELOP	ED A LEAK).  INSPECTION OF SWIVEL FITTING HAD BROKEN/FAILED INTERNALLY, CAUSING LOSS OF HYD SYS PRESSURE AND FLUID CONTE	NT.  NEW SWIVEL FITTING WAS INSTALLED ON RAMP.  AC WAS FLOWN FOR RESTORATION/REPLACEMENT OF EXPLOSIVE BOLTS, GEAR SWINGS	 AND FUNCTION CHECKS PRIOR TO GOING BACK INTO SCHEDULED SERVICE. FAILED SWIVEL FITTING HAS BEEN RETAINED FOR EVALUATION.	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2005071500152	20050715	00152	EU  	2005	7	15	CA050613008      	1	20050611	G	2435	524031	DRIVE SHAFT     	AUXILEC     		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER GEN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1890					(CAN) DURING A START FOR THE FIRST FLIGHT OF THE DAY, THE AIRCRAFT FAILED TO START. INVESTIGATION BY MAINTENANCE REVEALE	D A SHEARED DRIVE. THIS IS THE FIRST TIME WE HAVE EVER SEEN THIS HAPPEN. WE HAVE NOT SENT THE STARTER GEN OUT FOR REASON	 FOR THE BROKEN SHAFT. IF THERE IS FURTHER INFORMATION TO SUPPLEMENT, WE WILL SUBMIT THAT INFORMATION.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005071500151	20050715	00151		2005	7	15	CA050613009      	4	20050609	G	2562	DURACELL	BATTERY         	KING        		CESSNA	188   	A188B       	2073005	CE  	CONT  	O550  	IO550D      	17042	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ELT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						457222					(CAN) THE DURACELL BATTERIES WERE FOUND TO BE LEAKING AND CORRODED.						1	L	7	1 	3O	3	O		A9CE    	E3SO	5	C	P25EA	 
2005071400107	20050714	00107	EU  	2005	7	14	CA050614001      	1	20050614	G	2530	4110001137	COFFEEMAKER     			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					AFT GALLEY	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											MID COFFEEMAKER IN AFT GALLEY U/S A SPARK CAME FROM IT AND IT WAS TURNED OFF BY F/A GALLEY POWER OFF.ACTION: C/M REPLACE	D. POS 505 AND 506 BREW CYCLE OPS CHECKED (SERV).					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005071400106	20050714	00106	NM  	2005	7	14	CA050614002      	1	20050614	G	3234	257T110314	CONTROL LEVER   			BOEING	767   	767209      	1385127	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					MLG	FAILED          	W				B				EMER. DESCENT           				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) FAULT: EICAS MESSAGE (LDG GEAR MONITOR) LANDING GEAR IND 3 GREEN.  ALSO RECEIVED A GRN PROX (TOO LOW GEAR) RECYCLE	D THE GEAR. LANDED WITH NORMAL INDICATIONS.  REPLACED LDG GEAR CONTROL LEVER MODULE IAW AMM 32-31-01 PG 1-5. AND CABLE T	ENTION ADJUSTED IAW AMM 32-31-00.  OPS CHECK CARRIED OUT, ALL INDICATIONS NORMAL.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005071300037	20050713	00037	CE  	2005	7	13	CA050614003      	1	20050607	G	8011	PM2403	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) STARTER WOULD NOT OPERATE.  STARTER REMOVED.  CALLED MFG DIRECT TO OBTAIN PERMISSION TO OPEN STARTER FOR EXAMINATI	ON.  NOTE: STARTER FAILED AT LESS THAN 1 HOUR TIME SINCE OVERHAUL.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005071400105	20050714	00105	EU  	2005	7	14	CA050614004      	1	20050609	G	5310	S2551032900000	SUPPORT         			AEROSP	ATR72 	ATR72212    	8680945	EU  										REAR CARGO	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RUDDER CONTROL CABLE WAS RIDING ON CROSSMEMBER AND SEVERED CROSSMEMBER COMPLETELY IN HALF.  IMPROPER INSTALLATION 	OF CROSSMEMBER POSITIONED WITH CABLE ABOVE MEMBER. CABLE SHOULD PASS BELOW MEMBER.					2	H	7	2 	4T			RT	A53EU   					 
2005071300036	20050713	00036	EU  	2005	7	13	CA050614005      	1	20050527	G	6730	105456611	HOUSING         			BOLKMS	105   	BO105CBS    	5626008	EU  										ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14953			2934					(CAN) THIS UNIT WAS RECEIVED FROM THE USA FOR ROUTINE SERVICING/MAINTENACE.  DURING DISASSEMBLY A CRACK WAS DISCOVERED B	ETWEEN THE LEE PLUG AND THE OPENING OF THE PISTON GUIDE.					1	G	7	2 	3U			NC	H3EU    					 
2005080400065	20050804	00065	SW  	2005	8	4	CA050614006      	1	20050610	G	6210	206010200033	BLADE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BLADE WAS DECLARED BEYOND SALVAGE 'SCRAP' ON 12-09-04 AND FOUND WITH SERVICEABLE TAG ON 04-17-05.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071800021	20050718	00021	EA  	2005	7	18	CA050614007      	2	20050612	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								L2608240A			(CAN) WHILE CONDUCTING A 50 HR INSPECTION, THE OIL FILTER SHOWED EVIDENCE OF METAL CONTAMINATION.  THERE HAVE BEEN NO CO	MPLAINTS FROM PILOTS IN REGARDS TO ENGINE OPERATION OR PARAMETERS. THE PARTICLES EVIDENT ARE ALUMINUM AND FEW METALLIC. 	THE ENGINE HAS BEEN REMOVED FROM THE AIRCRAFT FOR OVERHAUL AND FURTHER INVESTIGATION. ONCE THAT REPORT HAS BEEN ISSUED W	E WILL SUBMIT THE FURTHER FINDINGS.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2005071400059	20050714	00059	SW  	2005	7	14	CA050614008      	1	20050518	G	2720	304201	TORQUE TUBE     			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION, RUDDER TUBE ASSY WAS FOUND TO BE UNAIRWORTHY DUE TO CRACKS.						1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL	 
2005071400096	20050714	00096	SO  	2005	7	14	CA050614009      	2	20050524	G	8520	649134	CRANKSHAFT      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	NR 2 MAIN	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								816628R			(CAN) CRANKSHAFT FRACTURED AT NR 2 MAIN BEARING JOURNAL FILLET NEXT TO NR 3 CHEEK.  FAILURE IS IN LINE WITH NR 2 CONNECT	ING ROD JOURNAL IN AREA WHERE CRANKSHAFT IS INSPECTED FOR SUB-SURFACE CRACKS BY UT.  MAIN BEARINGS WERE POUNDED TO VERY 	THIN METAL PIECES. NR 1, NR 2 MAIN BEARING SADDLES IN CRANKCASE WERE DAMAGED FOLLOWING FAILURE OF CRANKSHAFT, NR 2 MAIN 	BEARINGS.  DUE TO AMOUNT OF DAMAGE, CAUSE OF FAILURE COULD NOT BE DETERMINED WITH INSPECTION EQUIPMENT AVAILABLE. CRANKS	HAFT WAS MFG BY VAR PROCESS. AIRCRAFT WAS IN AN INCIDENT.  CRANKSHAFT, CRANKCASE, MAIN BEARINGS, CONNECTING RODS, CYLIND	ERS AND PISTONS HAVE BEEN TAKEN BY NTSB.	1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2005071500150	20050715	00150	NE  	2005	7	15	CA050614010      	2	20050610	G	7200		ENGINE          			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											DURING CLIMB AND AFTER DEPARTURE, NR 2 ENGINE HIGH OIL TEMP WAS EXPERIENCED.  HIGH OIL TEMP SUP PROCEDURES ACCOMPLISHED,	 FOLLOWED BY THE ENGINE FAILURE/SHUTDOWN CHECKLIST.  A/C RETURNED TO BASE. MAINTENANCE TROUBLESHOOTING FOUND 2 SNAGS. FU	EL ANT-ICE VALVE P/N 320115 FOUND TO WORK INTERMITTENTLY AND REPLACED.  20 BALL JOINT AT 8TH STAGE DUCT LEAKING HOT AIR 	ON TO OIL TANK.  BALL JOINT RESEALED,  AS A PRECAUTION OIL SYSTEM FLUSHED AND FILTER REPLACED.  A/C GROUND RUN WITH NO F	AULTS AND A/C RETURNED TO SERVICE.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005071400095	20050714	00095	SW  	2005	7	14	CA050615001      	1	20050614	G	5302	212030158001	FITTING         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					T/BOOM BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FITTING FOUND CRACKED AT ATTACHMENT BOLT HOLE. DEFECT FOUND BY NDT TECHNICIAN USING EDDY CURRENT INSPECTION METHOD	.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005080400066	20050804	00066	WP  	2005	8	4	CA050615002      	1	20050610	G	2435	BC3151002	STARTER GEN     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING AN PRE INSPECTION RUN UP, THE STARTER WOULD ENGAGE AND WAS INTERMITTENT.  THE STARTER WAS REMOVED	 AND NO FURTHER PROBLEMS WERE FOUND.  THE BENDIX IS SUSPECT AND RETURNED FOR REPAIR.					1	G	7	1 	3O	3	O		H11NM   	E295				 
2005080400067	20050804	00067	WP  	2005	8	4	CA050615003      	1	20050612	G	2435	BC3151002	STARTER GEN     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS STARTER HAS BEEN SNAGGED AS INTERMITTENT ON ONE OTHER OCCASION.  THE STARTER HAD 118.1 HRS TSO WHEN ORIGINAL 	PROBLEM EXISTED.  THE STARTER HAS 299.3 TSO AND THE SAME PROBLEM HAS OCCURRED.  DURING THE TIMES THE STARTER HAD PROBLEM	S, THE RING GEAR SOMETIMES HAD SUSTAINED DAMAGE AND THE RING HAD TO BE CHANGED.  THE BENDIX IS SUSPECTED AND WAS RETURNE	D FOR FURTHER INVESTIGATION.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2005071800004	20050718	00004	EU  	2005	7	18	CA050615004      	1	20050614	G	2710	33412TX080041XA	BOLT            			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					AILERON	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						78SE251					(CAN) WHEN REINSTALLING THE LT AILERON AFTER MAINTENANCE, THE ENGINEER NOTICED THAT THE AILERON BOLTS WERE INSTALLED INC	ORRECTLY AT BEARING NR 1 AND NR 3 ATTACH POINTS.  THE RT AILERON BOLTS WERE ALSO CHECKED AND FOUND TO BE INSTALLED INCOR	RECTLY.  BOLTS WERE THEN REMOVED, INSPECTED AND REINSTALLED IAW  MM 57-511 REF. FIGURE 1C DETAIL A.  NOTE: BOLTS WERE FO	UND OPPOSITE OF DETAIL A.			2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2005071300049	20050713	00049	SO  	2005	7	13	CA050615005      	1	20050612	G	5552	110321001	ANGLE           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE MAINTENANCE INSPECTION 2 SMALL CRACKS WERE FOUND IN THE LT ELEVATOR TRIM TAB ACTUATOR SUPPORT BRA	CKET ATTACH POINT AREA. THE CRACKS WERE FOUND IN THE AREA AROUND THE 2 LOWER SUPPORT BRACKET BOLT HOLES. UPON FURTHER IN	VESTIGATION BOTH THE REINFORCING ANGLE AND THE SPAR WERE FOUND TO BE CRACKED. THE AREA WAS REPAIRED AND REINFORCED IAW T	HE APPLICABLE SRM.			1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2005071400058	20050714	00058	EU  	2005	7	14	CA050615006      	1	20050613	G	2913	350A35020172	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD SYSTEM	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) PILOT NOTICED STRANGE NOISE IN FLIGHT.  UPON LANDING, CONDUCTED AN INVESTIGATION OF NOISE WHILE AC REMAINED RUNNIN	G.  NOISE DETERMINED TO BE COMING FROM HYD DRIVE AREA.  AC WAS SHUTDOWN, PART REMOVED.  DRIVEN PULLEY OF HYD SYS WAS FOU	ND TO HAVE ITS BEARING INNER RACE SPINNING ON PULLEY SHAFT. CAUSED SIGNIFICANT WEAR ON SHAFT, WHICH IN TURN CAUSED BEARI	NG TO BE LOOSE ON SHAFT, RESULTING IN NOISE DURING OPERATION.  HAD THIS CONDITION PERSISTED, HYD SYS FAILURE WOULD HAVE 	OCCURRED FORCING EMERGENCY LANDING.  BEARING CONDITION WAS NORMAL, WITH NO ROUGHNESS OR BINDING FELT.  SUSPECT UNDERSIZE	 BEARING INNER RACE OR PULLEY SHAFT, ALLOWING RACE TO SPIN ON SHAFT.  PART REMOVED AND REPLACED, AC BACK IN SERVICE.	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005071400094	20050714	00094	EU  	2005	7	14	CA050615007      	1	20050614	G	6730	AC67246	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ROTOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TROUBLESHOOTING THE DEFECT, FOR HELICOPTER COMPANY.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005090600008	20050906	00008	CE  	2005	9	6	CA050615008      	1	20050604	G	5524	115610010191	TORQUE TUBE     			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF AIRCRAFT TAILCONE FOR OTHER MAINTENANCE, LT ELEVATOR TORQUE TUBE WAS DISCOVERED CRACKED. CRACK PRO	PAGATED FROM UNDER  ELEVATOR MOUNTING FLANGE FITTING, EMANATING FROM TAPER PIN HOLE. WITH TAPER PINS REMOVED AND FITTING	 SLID BACK, ONLY THEN COULD FULL EXTENT OF DAMAGE BE VIEWED. CRACK STARTED AT IB OF 2 TAPER PINS, SPIRALED BOTH DIRECTIO	NS COMPLETELY ENCIRCLING TORQUE TUBE. BOTH CRACKS ENDED ABOUT 2 INCHES APART BUT ADJACENT TO EACH OTHER. SMALLER CRACKS 	WERE ALSO STARTING TO EMANATE FROM TAPER PIN HOLES FOR HORN FLANGE. SB HAD NOT YET BEEN COMPLETED ON THIS ASSY AS IT HAD	 JUST 364.7 HRS SINCE NEW . THIS DAMAGE MAY HAVE BEEN CAUSED BY SEVERE GUST LOADS OR JET BLAST.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2005071400093	20050714	00093	SO  	2005	7	14	CA050615009      	2	20050612	G	8530	AEC631397	CYLINDER HEAD   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	NR 2	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS PROPELLER WAS ROTATED, AIR WAS HEARD ESCAPING FROM NR 2 CYLINDER. A CYLINDER LEAKAGE CHECK WAS CARRIED OUT TO C	ONFIRM LEAKAGE, AND A SOAP/WATER SOLUTION USED TO LOCATE THE CRACK.  CRACK WAS LOCATED IN CYLINDER HEAD ABOVE EXHAUST VA	LVE AREA.  CYLINDER ASSY WAS REMOVED FROM SERVICE. THIS IS THE 6TH CYLINDER ASSY FOUND IN THIS CONDITION IN THE PAST TWO	 MONTHS. ALL CYLINDERS WHERE SAME MFG CYLINDER'S WITH APPROXIMATELY THE SAME 3 OF HOURS.			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2005071400100	20050714	00100	EU  	2005	7	14	CA050616001      	1	20050616	G	3260	D3221402200060	UPLOCK          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NLG DOOR	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											WHEN GEAR WAS RETRACTED IMMEDIATELY AFTER T/O, HEARD A LOUD BANG AND GEAR DID NOT RETRACT. ECAM DIRECTED TO CYCLE GEAR. 	WHEN GEAR LOWERED HAD A GEAR DOORS NOT CLSD ECAML FLT DX AND MOC ADVISED A RETURN TO AIRPORT.  TRANSCRIBED FROML1470135.	 NLG DOOR UPLOCK ASSY REPLACED IAW MM 32-31-14. DOOR OPERATION CHECKS SERVICEABLE.  REQS 2 BOLTS CHGD IAW P/P NR A320-32	-20089.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005071800003	20050718	00003	CE  	2005	7	18	CA050616002      	1	20050513	G	7921	639171	OIL COOLER      			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE OIL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OIL WAS NOTICED TO BE LEAKING, THE SOURCE OF WHICH WAS DETERMINED TO BE THE OIL COOLER AS THERE 	WAS A CRACK ON THE WELD ALONG THE UPPER OUTER CORNER OF THE OIL COOLER.  THE OIL COOLER WAS REPLACED WITH AN OVERHAULED 	UNIT.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
2005071400099	20050714	00099	EA  	2005	7	14	CA050616003      	1	20050530	G	5310	C3FS5250	WINDOW POST     			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13305				97				(CAN) DURING AN UNSCHEDULED WINDSHIELD REPLACEMENT IT WAS NOTICED THE RT POST WAS CORRODED TO THE EXTENT THAT THE POST N	O LONGER PROVIDED THE INTENDED SUPPORT.					1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2005071800024	20050718	00024	NM  	2005	7	18	CA050616004      	1	20050614	G	3350		SIGN            			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					EMERGENCY EXIT	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS IN CRUISE WHEN A PASSENGER SEATED AT 12F, RT EMERGENCY EXIT CALLED FLIGHT ATTENDANT TO ADVISE THAT EM	ERGENCY EXIT LIGHT HAD FLASHED ON AND A PUFF OF SMOKE CAME OUT OF SIGN.  THIS OCCURRED A SECOND TIME AND PASSENGER WAS R	ELOCATED, A F/A WAS STATIONED IN THE ROW WITH A FIRE EXTINGUISHER.  THE A/C THEN DIVERTED WITH AN UNEVENTFUL LANDING. AF	TER REACHING THE GATE ALL POWER WAS REMOVED FROM THE AC AND THE PASSENGERS WERE DEPLANED WITHOUT INCIDENT.  AN INVESTIGA	TION IS CURRENTLY ON GOING AND THIS FILE WILL BE UPDATED AS INFORMATION IS AVAILABLE.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005090600009	20050906	00009	SW  	2005	9	6	CA050616005      	1	20050308	G	2840	206063613003	SWITCH          	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					LOW FUEL SWITCH	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1361					(CAN) SYSTEM TEST CARRIED OUT AS PART OF THE ANNUAL FUEL SYSTEM INSPECTION. FOUND THAT THE LOW FUEL LIGHT WOULD NOT COME	 ON UNTIL 25 LBS INDICATED (SHOULD BE 70 LBS). LOW FUEL SWITCH REPLACED AND A/C RETURNED TO SERVICE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005090600012	20050906	00012	SW  	2005	9	6	CA050616009      	1	20050516	G	2435	23032018	STARTER GEN     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOISE IN HEADSET REPORTED BY PILOT, THAT WAS GETTING WORSE. PILOT TURNED OFF GENERATOR AND NOISE WAS ELIMINATED.  	STARTER THEN FAILED TO ROTATE WHEN STARTER ATTEMPTED.  START/GEN REPLACED AND A/C RETURNED TO SERVICE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071500155	20050715	00155	EA  	2005	7	15	CA050616010      	2	20050609	G	7323	210598	GOVERNOR        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	OVERSPEED	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) RT ENGINE DID NOT ACHIEVE MAX NP RPM.  RT ENGINE OVERSPEED GOVERNOR REPLACED WITH OVERHAULED UNIT. GROUND RUN SUCC	ESSFULLY REACHED MAX PROP RPM.					1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2005071800007	20050718	00007	EA  	2005	7	18	CA050617001      	1	20050612	G	3220		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NOSE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) A/C LANDED NOSE GEAR UP, CREW UNABLE TO EXTEND NLG BY NORMAL OR MANUAL. THE NLG IS THE ORIGINAL INSTALLATION FROM 	PRODUCTION.  STILL UNDER INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071500138	20050715	00138	NM  	2005	7	15	CA050617002      	1	20050616	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 HYD	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, AN OPERATOR EXPERIENCED A NR 2 HYDRAULIC SYSTEM FAILURE DUE TO A FAILED NR 2 HYDRAULIC PUMP (EDP). 	  NR 2 EDP REPLACED, FULL HYDRAULIC SYSTEM FLUSHED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071500157	20050715	00157	EU  	2005	7	15	CA050617003      	1	20050609	G	2910	438Q2277	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											DURING TAKEOFF, THE CREW SAW THE HYDRAULIC FLOW WARNING LIGHTS ILLUMINATE. THE FLIGHT WAS TERMINATED AND THE AIRCRAFT RE	TURNED WHERE AN UNEVENTFUL LANDING WAS MADE.  MAINTENANCE INVESTIGATION REVEALED THAT THE TOP CONNECTION UNION ON HP HYD	RAULIC PIPE WAS LEAKING. THE PIPE WAS REMOVED AND INSPECTED WITH NO DEFECTS FOUND. THE CONNECTION ADAPTOR WAS INSPECTED 	WITH NO DEFECTS FOUND. THE PIPE WAS REINSTALLED AND HYDRAULIC SYSTEM BLED. FULL SYSTEM FUNCTION TESTS WERE CARRIED OUT, 	AND AN ENGINE RUN AND TAXI TEST WERE COMPLETED. NO EVIDENCE OF FURTHER LEAKAGE WAS FOUND.		2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005090700007	20050907	00007	SW  	2005	9	7	CA050617004      	1	20050527	G	6310	206340104101	SEAL            			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					FREEWHEEL UNIT	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) REPLACED SEAL DUE TO LEAKING OIL. (FREEWHEEL)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071500161	20050715	00161	NM  	2005	7	15	CA050617005      	1	20050611	G	7312	320115	VALVE           			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUEL HEAT	STUCK           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, THE CREW NOTICED THAT NR 2 ENGINE OIL TEMPERATURE WAS INCREASING. TEMP CONTINUED TO INCREASE DUR	ING CLIMB AND ENGINE WAS SHUT DOWN.  AIRCRAFT RETURNED TO BASE. INVESTIGATION FOUND THAT THE NR 2 ENGINE FUEL HEAT VALVE	 WAS STUCK IN THE OPEN POSITION. THE VALVE WAS REPLACED. ALSO THE 8TH STAGE AIR DUCT JOINT WAS BLOWING HOT AIR DIRECTLY 	ON TO THE OIL TEMP SENSOR. LEAK WAS RECTIFIED. ENGINE RUN WAS CARRIED OUT NO FURTHER FAULTS FOUND, AIRCRAFT RETURNED TO 	SERVICE.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005071500160	20050715	00160	EA  	2005	7	15	CA050617006      	1	20050530	G	7120	C3EM215	MOUNT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								11509			FOUND CRACK IN UPPER LT ARM, WHERE THE TUBE JOINS THE CIRCULAR MOUNT.						1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2005090700008	20050907	00008	CE  	2005	9	7	CA050617007      	1	20050615	G	5711	5840083S	DOUBLER         			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					FRONT WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE LPI INSPECTION OF THE FRONT WING SPAR CARRY THRU STRUCTURE AND REPAIR DOUBLERS IN ACCORDANCE WITH A	D90-08-14, THE LT FWD REPAIR DOUBLER WAS FOUNDCRACKED IN THE LOWER BEND RADIUS IN THE SAME SPOT AS THE ACTUAL WING SPAR 	WHICH THE DOUBLER WAS USED TO REPAIR. THE FAA WAS CONTACTED FOR A REPAIR PROCEDURE AN D ADVISED US THAT REPLACEMENT OF T	HE DOUBLER WAS AN ACCEPTABLE REPAIR TO RESTORETHE STRUCTURAL INTEGRITY. THE ORIGINAL REPAIR DOUBLER WAS INSTALLED AUGUST	 14,1990 AND HAS SINCE ACUMULATED 7486.0 HOURS SINCE IT'S INSTALLATION.		1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2005071800015	20050718	00015	NE  	2005	7	18	CA050617008      	2	20050608	G	7200		ENGINE          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								950230			(CAN) RT ENGINE ROLLED BACK, FLAMED OUT DURING CRUISE, AT FL380. NO ABNORMAL INDICATIONS SHOWN. CREW DECLARED EMERGENCY,	 DESCENDED TO FL210 AND RESTARTED ENGINE USING CROSS BLEED. UNEVENTFUL LANDING AT DIVERSION AIRPORT. NO LEAKS FOUND DURI	NG GROUND RUNS. FUEL SAMPLE TAKEN. FUEL TANKS WERE DRAINED AND INSPECTED.  BORESCOPE INSPECTION OF ENGINE PERFORMED NO A	BNORMALITIES FOUND. ALL FILTERS AND SCREENS INSPECTED. SYSTEM CHECKED FOR LEAKS. OPERATIONAL TESTS OF LOW PRESSURE WARNI	NG SYS CHECKED. FUEL SYS CHECKED WITH NO FAULTS FOUND.  COMPLETE TROUBLESHOOTING OF ENGINE SYS CHECKED WITH NO FAULT FOU	ND .  MFC REPLACED AND SENT FOR INVESTIGATION AS A PRECAUTION.  AC RETURNED TO SERVICE FOLLOWING TEST FLIGHT .	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071500159	20050715	00159	EA  	2005	7	15	CA050617009      	2	20050615	G	7260		GEARSHAFT       			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LT ENGINE	WORN            	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT THE LT ENGINE LOST POWER AND SPOOLED DOWN WITHOUT PRIOR WARNING. THE FLIGHT CREW REPORTED SEEING THE	 FUEL PRESSURE AND ENGINE WARNING LIGHTS ILLUMINATE. THE FLIGHT CREW PERFORMED THE SHUTDOWN PROCEDURE AND PROP FEATHER P	ROCEDURE. THE PROPELLER DID NOT RESPOND TO CONDITION LEVER INPUT AND THE CREW HAD TO USE THE ALTERNATE FEATHER SYSTEM TO	 FEATHER THE PROPELLER.  AFTER ENGINE REMOVAL THE ACCESSORY GEARBOX ANGLE DRIVE GEARBOX COVER WAS REMOVED. THE GEARSHAFT	 WAS FOUND TO HAVE EXCESSIVE MOVEMENT AND WAS NOT ENGAGING THE HP ROTOR PROPERLY. PART NUMBERS AND TIMES TO FOLLOW.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071800008	20050718	00008	EA  	2005	7	18	CA050617010      	1	20050607	G	5610	NM1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) RT WINDSHIELD INNER PLY BROKE DURING THE APPROACH.  WINDSHIELD REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005071500158	20050715	00158	EA  	2005	7	15	CA050620001      	2	20050617	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA								PCEFA0178			(CAN) AN AIRCRAFT EXPERIENCED AN ODOR AND WHITE SMOKE IN THE CABIN APPROXIMATELY 3 MINUTES AFTER TAKE OFF.  THE CAPTAIN 	DECLARED AN EMERGENCY AND REQUESTED AN IMMEDIATE RETURN TO BASE.  ON GROUND, THE ODOR AND SMOKE WAS CONFIRMED TO BE COMI	NG FROM THE NR 2 ENGINE, THIS WAS PROVEN THROUGH ENGINE RUNS.   ALSO FAULT CODE NR 938 (TURBO MACHINERY CHIP DETECTOR) W	AS FLAGGED, THE P2.2 AND P3 DUCTS WERE CHECKED AND FOUND DRY, THE P2.7 VALVE AND DUCTING WAS FOUND WET WITH OIL. AN OIL 	LEVEL CHECK AFTER THE ENGINE RUN CONFIRMS THAT THE 2 ENGINE HAS LOST 3 QTS OF ENGINE OIL SINCE THIS MORNING.  NR 2 ENGIN	E REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071500168	20050715	00168	NM  	2005	7	15	CA050620002      	1	20050531	G	3260	NAS13038	BOLT            			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG SENSOR	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF, LANDING GEAR WOULD NOT RETRACT.  MAINTENANCE FOUND AIR/GND PROX TARGET LEVER BOLT LOOSE.  BOLT/NUT-  P	/N NAS 1303-8/BACN10JC3.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005071500149	20050715	00149	NM  	2005	7	15	CA050620003      	1	20050609	G	8011		STARTER         			BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	SEPARATED       	S				E				ENGINE SHUTDOWN         				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA								702698			(CAN) CREW REPORTED NR 2 ENGINE HEAVY VIBRATION, GAUGES FLUCTUATING, ENGINE SHUT DOWN. LANDED WITHOUT INCIDENT.  UPON AR	RIVAL, INSPECTION OF ENGINE FOUND THE STARTER WAS SEPARATED AT SPLIT LINE, CSO OFF PRESSURE FILTER POPPED. CSD QUAD RING	 BOLT LOOSE, OIL IN TAIL PIPE. SUSPECT INTERNAL BEARING FAILURE. FURTHER INVESTIGATION IN PROGRESS.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005080400068	20050804	00068	CE  	2005	8	4	CA050620004      	1	20050615	G	2430	TD805W	RELAY           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					OVERVOLTAGE	INTERMITTENT    	W				C				ABORTED TAKEOFF         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			CA							U92				(CAN) THE BEECH 99 WAS ON ITS TAKEOFF ROLL WHEN FIRST ONE THEN THE SECOND GENERATOR FAILED.  THE LIGHTS IN THE COCKPIT B	RIGHTENED SUDDENLY JUST BEFORE THE GENERATORS FAILED.  WHEN MAINTENANCE TROUBLESHOT THE PROBLEM THEY INITIALLY COULD NOT	 FIND ANY THING WRONG WITH THE SYSTEM.  THE GENERATORS WERE WORKING AS PER SPECIFICATIONS.  THE ENGINEERS SIMULATED VIBR	ATIONS ON THE ELECTRICAL COMPONENTS IN THE BELLY BY TAPPING THEM WITH A SCREWDRIVER.  WHEN THE RAH OVER VOLTAGE RELAY WA	S TAPPED THE GENERATORS WENT OFFLINE.  REPLACEMENT OF THE OVER VOLTAGE RELAY ON THE RIGHT SIDE CURED THE PROBLEM.  SUBSE	QUENT FLIGHTS SHOWED NO PROBLEMS WITH THE GENERATOR ORS.	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005080400163	20050804	00163	WP  	2005	8	4	CA050621001      	1	20050610	G	2435	BC3151002	STARTER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING THE FIRST START OF THE DAY THE STARTER FAILED TO ENGAGE.  THE STARTER WAS FOUND TO BE INTERMITTENT AND THE BENDIX	 IS SUSPECT.  THE STARTER WAS REMOVED FOR FURTHER INVESTIGATION.  AIRCRAFT WAS RETURNED TO SERVICE AND FLIGHT COMMENCED.					1	G	7	1 	3O	3	O		H11NM   	E295				 
2005080400167	20050804	00167	WP  	2005	8	4	CA050621002      	1	20050617	G	5302	C0231	SLEEVE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAIL BOOM	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING AN 100 HR INSPECTION, THE TAIL BOOM REQUIRES A VISUAL INSPECTION.  UPON INSPECTION THERE WAS EVIDENCE OF SMOKING 	AROUND THE FORWARD NYLON SLEEVE WHERE THE PITCH CHANGE CONTROL TUBE TRAVEL THROUGH.  FURTHER INVESTIGATION REVEALED INDE	ED THE NYLON SLEEVE HAD ERODED THE BULKHEAD MATERIAL ENLARGING THE HOLE HOLDING THE SLEEVE IN PLACE.  ROBINSON HAS BEEN 	NOTIFIED.  THE TAIL BOOM WAS REPLACED WITH A NEW BOOM AND AIRCRAFT RETURNED TO SERVICE.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2005071500148	20050715	00148	NE  	2005	7	15	CA050621003      	2	20050522	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  		FAILED          	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								PS0198			(CAN) DURING CRUISE SMOKE BECAME EVIDENT IN THE CABIN ACCOMPANIED BY HIGH ENGINE OIL TEMPERATURE AND LOW OIL PRESSURE IN	DICATIONS.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION FOUND OIL LEAKING FROM THE ENGINE INLET AREA.  MF	G WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005071500147	20050715	00147	NE  	2005	7	15	CA050621004      	2	20050524	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  						FAILED          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		TO	TAKEOFF        	1			CA								121218			(CAN) BEFORE ACHIEVING TAKE-OFF POWER, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOW OIL PRESSURE WARNING ANNUNCI	ATION.  THE CREW ABORTED TAKE-OFF AND SHUT THE ENGINE DOWN.  SUBSEQUENT INSPECTION REVEALED SEIZURE OF THE LOW PRESSURE 	ROTOR.  MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005071500146	20050715	00146	NE  	2005	7	15	CA050621006      	2	20050207	G	7200		ENGINE          			AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A34AG    	52053	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A	J		FLAME/FIRE                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											DURING FLIGHT, ENGINE OIL PRESSURE AND TURBINE TEMPERATURES WERE REPORTED TO RISE, FOLLOWED BY AN OIL PRESSURE REDUCTION	 AND FLAMES EMANATING FROM THE EXHAUST. THE PILOT SHUT THE ENGINE DOWN IN FLIGHT AND COMPLETED A DEAD-STICK LANDING.  MF	G WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	3T	4	T	NC	A17SW   	E4EA				 
2005080400168	20050804	00168	CE  	2005	8	4	CA050621007      	1	20050615	G	5551	07326004	ATTACH FITTING  			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470*       	17026	SO  					STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											STABILIZER SPAR P/N 0732602-22, SPAR REINFORCEMENT P/N 0732602-1, SPAR REINFORCEMENT P/N 0732603-1 AFT, ATTACH REINFORCE	MENT P/N 0732106 5), ATTACH REINFORCEMENT P/N 0732106-1, HINGE REINFORCEMENT P/N 0732101-4, DURING INSPECTION/REPAIR OF 	STABILIZER THESE PARTS WERE FOUND CRACKED AT ATTACH POINT TO AIRFRAME.  SUSPECT USE OF EXTERNAL HANDS CAUSING CRACKING.				1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2005071500145	20050715	00145	EA  	2005	7	15	CA050621008      	2	20050607	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  		FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								FA0015			DURING AN STC FLIGHT TEST, THE AIRCRAFT WAS FLOWN TO A 45 DEGREE ANGLE FOLLOWED BY A PUSH-OVER RESULTING IN A ZERO GRAVI	TY CONDITION. THE LOW ENGINE OIL PRSSURE WARNING ANNUNCIATED AND BOTH PROPELLERS FEATHERED.  ENGINE POWER WAS REDUCED AN	D OIL PRESSURE STABILIZED. WHILE THE SISTER ENGINE/PROPELLER RECOVERED, PROPELLER WENT TO OVERSPEED GOVERNING.  THE CREW	 ELECTED TO SHUT THE ENGINE DOWN INFLIGHT.   MFG WILL INVESTIGATE THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMIN	ED.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071500144	20050715	00144	NE  	2005	7	15	CA050621009      	2	20050613	G	7200		ENGINE          			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN TORQUE, ACCOMPANIED BY A SLIGHT BURNING ODOR.  SUB	SEQUENTLY, ENGINE OIL PRESSURE REDUCED AND A FIRE WARNING ANNUNCIATED.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCR	AFT DIVERTED TO POINT-OF-DEPARTURE.  MFG WILL INVESTIGATE THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005071500173	20050715	00173	NE  	2005	7	15	CA050621010      	2	20050611	G	7250		BLADE           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					TURBINE SECTION	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED CHANGE IN POWER ACCOMPANIED BY VIBRATIONS.  THE ENGINE WAS SH	UTDOWN IN FLIGHT AND A SINGLE ENGINE LANDING WAS ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE B	LADES.				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2005071500143	20050715	00143	EA  	2005	7	15	CA050621011      	2	20050612	G	7322	32447452	HYDROMECH UNIT  		32447452    	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER CHANGE WITH NO SUBSEQUENT RESPONSE TO THROTTLE  LEVEL I	NPUT.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT-OF-DEPATURE.  SUBSEQUENT INSPECTION REVEALE	D A DAMAGED HYDROMECHANICAL FUEL CONTROL/FUEL PUMP ASSEMBLY.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2005071500142	20050715	00142	NE  	2005	7	15	CA050621012      	2	20050616	G	7200		ENGINE          			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  						FLAMED OUT      	W				O				OTHER                   				D	X		INFLIGHT SEPARATION       	ENGINE FLAMEOUT           		DE	DESCENT        	1			CA								JA0391			(CAN) ON DESCENT, THE ENGINE WAS REPORTED TO HAVE EMITTED A NOISE AND SUBSEQUENTLY FLAMED OUT.  THE ENGINE WAS SUCCESSFU	LLY RE-STARTED IN FLIGHT AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVI	SE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2005071500141	20050715	00141	EA  	2005	7	15	CA050621013      	2	20050615	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  		SHUTDOWN        	W				E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0015			(CAN) DURING LEVEL FLIGHT, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN.  THE CREW SECURED THE ENGINE AND FEATHERED TH	E PROPELLER.  SUBSEQUENT INSPECTION REVEALED METALLIC PARTICLES ON THE TURBO MACHINE CHIP DETECTOR AND IN THE ENGINE OIL	 FILTER.  THE ENGINE HAD RECENTLY EXPERIENCED AN INCIDENT INVOLVING LOSS OF MAIN OIL PRESSURE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071500166	20050715	00166	EU  	2005	7	15	CA050621014      	1	20050602	G	3060		BOOT            			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					PROPELLER	DETACHED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) DURING CLIMB A PROPELLER DE-ICING BOOT DETACHED WITH RESULTANT DAMAGE/BEAKAGE OF A FUSELAGE WINDOW.						2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005071500165	20050715	00165	NE  	2005	7	15	CA050621015      	2	20050619	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						SHUTDOWN        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								114292			(CAN) DURING CRUISE, ENGINE OIL PRESSURE WAS OBSERVED TO FLUCTUATE AND SUBSEQUENTLY DECREASE.  THE ENGINE WAS SHUTDOWN I	N FLIGHT.  SUBSEQUENT INSPECTION REVEALED INTERNAL OIL LEAKAGE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CA	USE, ONCE ESTABLISHED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005071500164	20050715	00164	NE  	2005	7	15	CA050621016      	2	20050614	G	7200	PW126A	ENGINE          			BAG   	ATP   	ATP         	       	EU  	PWA   	PW120 	PW126A      	 	NE  						SHUTDOWN        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								124044			(CAN) THE ENGINE EXPERIENCED AN IN-FLIGHT SHUTDOWN UNDER UNKNOWN CIRCUMSTANCES.  MFG WILL MONITOR THE INCIDENT AND ADVIS	E OF ROOT CAUSE, ONCE DETERMINED.					2	L	7	2 	4T	4	T	RT	A27NM   	E2ONE				 
2005071500163	20050715	00163	EA  	2005	7	15	CA050621017      	2	20050617	G	7200	PW150A	ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  		LEAKING         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA								FA0178			(CAN) DURING TAKEOFF CLIMB, SMOKE WAS OBSERVED IN THE CABIN AND FLIGHTDECK.  THE CREW DECLARED AN EMERGENCY AND RETURNED	 TO POINT-OF-DEPARTURE WITH ENGINE BLEEDS SELECTED (OFF).  SUBSEQUENT INSPECTION REVEALED ENGINE INTERNAL OIL LEAKAGE.  	MFG WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005071500140	20050715	00140	CE  	2005	7	15	CA050621018      	1	20050618	G	5610	10138402517	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											CRACKED WINDSHIELD.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005071500139	20050715	00139	CE  	2005	7	15	CA050621019      	1	20050615	G	5610	10138402517	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DELAMINATION AT WINDSHIELD.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005080400169	20050804	00169	NE  	2005	8	4	CA050621020      	1	20050618	G	6320	SB3317101	BEARING         	SKRSKY      		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					M/R GEARBOX	SPALLED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						A08100332					SPALLED BEARING RACE.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005071500172	20050715	00172	EA  	2005	7	15	CA050622001      	2	20050617	G	7414	1068291013	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT SIDE	FAILED          	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA								L629161A			(CAN) SHORTLY AFTER TAKEOFF THE LT ENGINE BEGAN TO SURGE.  THE AIRCRAFT RETURNED FOR LANDING WITH NO PROBLEMS.  A MAG CH	ECK CARRIED OUT ON THE GROUND REVEALED THE LT ENGINE, RT MAGNETO WAS DEAD. THE POINTS THAT CONTROL THAT SIDE OF THE DUAL	 MAG WERE BURNED.  THE MAG HAD BEEN REPLACED THE DAY BEFORE FOR THE SAME REASON, POINTS WERE WORN.  HOWEVER THE CAPACITO	RS WERE NOT CHANGED AT THAT TIME.  FOLLOWING THIS PROBLEM THE POINTS AND CAPACITORS WERE CHANGED AND NO FURTHER PROBLEMS	 OCCURRED.  IT IS THE OPERATORS PLAN TO MAKE THE REPLACEMENT OF THE CAPACITORS MANDATORY WHENEVER A MAGNETO IS CHANGED.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005080400170	20050804	00170	EU  	2005	8	4	CA050622002      	1	20050520	G	5313	A240084A176	STRINGER        			DORNER	DO228 	DO228202    	2992030	EU  										TAIL	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			13461								DURING PRE-BUY INSPECTION, THE PURCHASER VISUALLY NOTED THE PRESENCE OF CORROSION ON THE TOP SURFACE OF THIS STRINGER.  	UPON FURTHER AND LATER INSPECTION, IT WAS DETERMINED TO REQUIRE REPLACEMENT OF THIS STRINGER.					2	H	7	2 	4T			RT	A16EU   					 
2005071800002	20050718	00002	NE  	2005	7	18	CA050622003      	2	20050606	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DETACHED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE IGNITER WAS FOUND TO HAVE A LOOSE CENTER ELECTRODE.  PART WAS REMOVED FROM SERVICE A	ND REPLACED WITH NEW PART.  PART WAS REMOVED FROM SERVICE DUE TO PREVIOUS INSTANCES OF IGNITER CENTER ELECTRODES DETACHI	NG AND FODDING THE TURBINE, RESULTING IN EXPENSIVE REPAIR (RE: TURBOMECA SERVICE LETTER).				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005071800020	20050718	00020	SW  	2005	7	18	CA050623001      	1	20050613	G	5302	206031004023	SKIN            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BCJN07389					(CAN) APPROXIMATELY 2, PLATE CRACKED						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400171	20050804	00171	CE  	2005	8	4	CA050623002      	1	20050622	G	5522	115610010167	SKIN            	BEECH       		BEECH 	100   	B100        	1152919	CE  										ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BE131					THE ELEVATOR WAS REMOVED TO REPLACE THE TRAILING EDGE SPLINE AND REPAIR CRACKS IN THE LE SKIN NEAR THE OUTBOARD HINGE PO	INT.  THE HORN AREA WAS DISMANTLED TO INSPECT THE INNER STRUCTURE.  A TOTAL OF TWENTY CRACKS WERE FOUND IN THE VARIOUS P	ARTS OF THE STRUCTURE OUTBOARD OF THE HINGE POINT, INCLUDING SKINS, RIBS, AND CLIPS. A SEARCH OF BEECH SERVICE INFORMATI	ON REVEALED THAT SB 0799-133 AND AD76-22-03MAY ADDRESS THIS PROBLEM BUT DO NOT PERTAIN TO THIS AIRCRAFT SERIAL NUMBER.			1	L	7	2 	4T				A14CE   					 
2005071500162	20050715	00162	EA  	2005	7	15	CA050623003      	1	20050621	G	3040	XW200672075	FLEX DRIVE      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WINDSHIELD WIPER	SEIZED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) A FEW MINUTES AFTER DEPARTURE, THE FLIGHT CREW NOTICED A BURNING ODOR FOLLOWED BY SMOKE EMITTING FROM THE GLARESHI	ELD. ON INVESTIGATION BY MAINTENANCE, THE FLEX DRIVE BETWEEN THE WIPER MOTOR AND PILOT CONVERTER WAS FOUND TO BE OVERHEA	TING AND MELTED A PORTION OF THE WINDSHIELD DEFROST DUCTING. WHEN THE FLEX DRIVE WAS REMOVED, IT WAS SEIZED. THE FLEX DR	IVE WAS REPLACED, THE WINDSHIELD DEFROST DUCTING REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005080400172	20050804	00172	SW  	2005	8	4	CA050623004      	1	20050621	G	2740	2744026007	TORQUE TUBE     			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ELEVATOR HORN	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			21421	21421							DURING AN INSPECTION, IT WAS DISCOVERED THAT THE RIGHT ELEVATOR TORQUE TUBE HORN WAS CHAFFED.  THE CAUSE OF THE CHAFF WA	S A SCREW, WHICH ATTACHES A CLOSING PANEL ON THE VERTICAL STAB.  THE TORQUE TUBE WAS REPLACED AND A SHORTER SCREW INSTAL	LED.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005080400173	20050804	00173	EA  	2005	8	4	CA050623006      	1	20050613	G	3246	58C015	ATTACH FITTING  			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10800								UPON REMOVAL OF THE SPREADER BAR FROM THE FLOAT, A CRACK WAS NOTED ALONG THE CASTING SEAM OF THE RT FRONT FLOAT STRUT FI	TTING.  THE ONLY TIME THIS AREA IS EXPOSED IS DURING HEAVY MAINTENANCE, WHERE THE AIRCRAFT IS REMOVED FROM FLOATS AND TH	E FLOATS ARE DISMANTLED.				1	H	7	1 	3R	3	R		A806    	5E1				 
2005071800001	20050718	00001	NE  	2005	7	18	CA050623007      	2	20050604	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ROUTINE INSPECTION BOTH ENGINE START IGNITERS WERE FOUND TO HAVE LOOSE CENTER ELECTRODES.   REMOVED AND REPLACE	D WITH NEW IGNITERS.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005071500171	20050715	00171	GL  	2005	7	15	CA050624001      	2	20050531	G	7250	6898731	SUPPORT         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAT33124			(CAN) TURBINE ASSY DISMANTLED TO INSPECT AND REPAIR AS NECESSARY FOR A LOW POWER CONDITION, SUMP COVER  P/N 6888547, 9-1	2 SEAL BORE EXCESSIVELY WORN, FOREIGN PARTICULATE FOUND IN 9-12 SEALBORE AREA.  PT SUPPORT, 25-28 SERRATED SEAL PULLED (	BROKE 3 TACKWELDS) ON DISASSEMBLY, 19-24 SEALBORE EXCESSIVELY WORN, FOREIGN PARTICULATE FOUND IN SUMP COVER BOSS, 3 O'CL	OCK SUPPORT STRUT AND 19-24 SEALBORE AREAS, PARTICULATE ANALYZED AND FOUND TO BE GLASS BEADS MATERIAL.  NOTE: MATERIAL A	NALYSIS REPORT NO.05-213:  IT IS CONCLUDED THAT PARTICULATE FOUND IN AIR PASSAGES CONTRIBUTED TO LOW PWR CONDITION BY ER	OSION OF SEALBORE MATERIAL INCREASING, LEAKAGE RATE OUT OF THRUST BALANCE CHAMBER ON FRONT SIDE OF 2ND STAGE WHEEL.	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400174	20050804	00174	CE  	2005	8	4	CA050624002      	1	20050611	G	3246	16131	WHEEL           			CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300C       	17022	SO  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											AS AIRCRAFT TAXIED FROM TIE-DOWN, NOSE WHEEL FAILED ABRUPTLY, APPROXIMATELY 15 FEET FROM TIE-DOWN, TUBE, TIRE AND NOSE W	HEEL REMAINED IN YOKE, WITH NO DAMAGE TO TIRE OR YOKE.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2005071500170	20050715	00170	EA  	2005	7	15	CA050624003      	2	20050605	G	8520	SL134441	PISTON PIN      			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	NR 4 CYLINDER	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) 4 CYLINDER PISTON PIN PLUG FAILED (BROKEN OFF) CAUSING HIGH AMOUNT OF ALUMINUM IN OIL FILTER, CAUSING LOSS OF OIL 	PRESSURE DURING CRUISE.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2005080400197	20050804	00197	EU  	2005	8	4	CA050624005      	1	20050607	G	2731	Z4244120000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ELEVATOR TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DUE TO PREVIOUS TRIM CABLE FAILURES A 3000 HR REPLACEMENT INTERVAL WAS INTRODUCED.  THIS CABLE WAS BEING REMOVED FOR REP	LACEMENT WHEN IT WAS FOUND TO BE FRAYED AT THE CONTROL STOP.  THE 3000 HR REPLACEMENT INTERVAL WILL CONTINUE.					1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2005080400198	20050804	00198	EU  	2005	8	4	CA050624006      	1	20050616	G	2731	Z4244120000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ELEVATOR TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DUE TO PREVIOUS ELEVATOR TRIM CABLE FAILURES A 3000 HR REPLACEMENT INTERVAL WAS PUT INTO PLACE.  THIS CABLE WAS BEING RE	MOVED FOR REPLACEMENT WHEN THE DEFECTS WERE FOUND.  THE 3000HR INTERVAL WILL CONTINUE.					1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2005080400199	20050804	00199		2005	8	4	CA050624007      	1	20050622	G	2432	AD40787	BATTERY         																	MASTER	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											DURING A SCHEDULED CHECK, THE BATTERY WAS OBSERVED TO HAVE 1 INCH DIAMETER HOLE IN THE TOP OF THE CASE AS WELL AS EVIDEN	CE OF ERROSION ON THE SIDE OF THE CASE BELOW THE HOLE.  THREE CELLS IN THE AREA OF THE HOLE EXHIBIT EVIDENCE OF OVERHEAT	ING AND THERMAL DAMAGE.  INVESTIGATION INTO THE CAUSE IS ON GOING.  THE BATTERY HAS 6 MONTHS TIME IN SERVICE SINCE NEW A	ND 226.1 HOURS SINCE IT'S LAST SERVICE.																 
2005071800013	20050718	00013	GL  	2005	7	18	CA050624008      	1	20050623	G	7602		CONTROL CABLE   			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	MIXTURE CONTROL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MIXTURE CONTROL WAS FOUND STIFF TO OPERATE.  INSPECTION FOUND CABLE OUTER SLEEVE IS SEIZED ONTO THE INNER CABLE JU	ST BEHIND THE CONTROL ROD END LOCATED IN THE ENGINE COMPARTMENT.  CABLE IS ONLY 7 MONTHS OLD WITHOUT ANY SIGN OF EXTERNA	L DAMAGE.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2005071800019	20050718	00019	EA  	2005	7	18	CA050625001      	1	20050620	G	3010	14463108	PICCOLO TUBE    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ANTI-ICE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT INSPECTION IAW S/B 601R-30-029, MAINTENANCE FOUND 2 CRACKS IN THE OB PICCOLO TUBE ASSY.  BOTH C	RACKS ARE APPROX 1INCH IN LENGTH, THE FIRST CRACK IS 77.5 INCH FROM THE OB END, THE SECOND CRACK IS 83 INCH FROM OB END.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005080400200	20050804	00200	EA  	2005	8	4	CA050627001      	1	20050622	G	3320	18994	INVERTER        			CNDAIR	CL600 	CL600*      	       	EA  										LIGHTING	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA											WHEN THE CABIN LIGHT SWITCH WAS TURNED ON IN FLIGHT, MANY COCKPIT SYSTEMS OPERATED ERRATICALLY.  MAIN AND AUXILIARY FUEL	 TOTAL INDICATORS OPERATED ERRATICALLY, COCKPIT FLIGHT DIRECTOR BARS INDICATED SHALLOW LEFT TURN, RUDDER PULSED SEVERAL 	TIMES, AUDIO SYSTEM STATIC, STALL PROTECTION SYSTEM LIGHTS FLICKERED, AND THE BATTERY TEMPERATURE INDICATOR WAS IN YELLO	W BAND.  SWITCHING OFF THE CABIN LIGHTS RECTIFIED THE PROBLEMS.  THE LOWER AFT CABIN LIGHTING POWER SUPPLY IN THE AVIONI	CS BAY WAS FOUND FAILED AND EMITTING SUFFICIENT EMI TO AFFECT NEARBY SYSTEMS.  THE POWER SUPPLY WAS REPLACED AND ALL AFF	ECTED SYSTEMS WERE GROUND CHECKED SERVICEABLE.	2	L	7	2 	4F			RT	A21EA   					 
2005071500176	20050715	00176	NM  	2005	7	15	CA050627002      	1	20050624	G	2750	5906989101	DRIVE ASSY      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15588								(CAN) ON ROUTINE INSPECTION FOUND THAT SECONDARY FLAP DRIVE CORE HAD BROKEN STRANDS AND BLISTERING, CORE REPLACED WITH S	ERVICEABLE.  FUNCTION CARRIED OUT IAW MAINTENANCE MANUAL, AIRCRAFT RETURNED TO SERVICE					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005071500174	20050715	00174	NM  	2005	7	15	CA050627003      	1	20050623	G	3260	82400033011	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	UNSERVICEABLE   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			33452								(CAN) IN CRUISE, PILOTS REPORTED WEIGHT ON WHEELS CAUTION LIGHT WAS INTERMITTENTLY COMING ON.  MAINTENANCE PERSONNEL DID	 PSEU BITE CHECK AND FOUND THAT THE LT MLG NR1 PROXIMITY SENSOR CODE CAME UP.   RESISTANCE CHECK OF SENSOR FOUND THAT IT	 HAD VERY HIGH RESISTANCE.  SENSOR REPLACED WITH SERVICEABLE UNIT, FUNCTION CHECKS CARRIED OUT AND FOUND TO BE SERVICEAB	LE. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080400201	20050804	00201	GL  	2005	8	4	CA050627004      	2	20050601	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											TOT INDICATOR CHECKED FOR CALIBRATION WITH BARFIELD TESTER, NO DEFECT NOTED.  ON GROUND RUN OF AIRCRAFT, FOUND THE BLEED	 VALVE WAS NOT MOVING AS THE ENGINE WAS ACCELERATED.  BLEED VALVE REPLACED WITH SERVICEABLE UNIT, ENGINE POWER CHECK C/O	 AND PASSED.  AIRCRAFT RETURNED TO SERVICE				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005071800012	20050718	00012	GL  	2005	7	18	CA050628001      	2	20050616	G	7200		TURBINE         			EMB   	145   	EMB145LR    	3260212	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					NR 1 ENGINE	SHUTDOWN        	W				A				UNSCHED LANDING         				Y	M	J	ENGINE STOPPAGE           	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			CA								CAE312086			A/C EXPERIENCED AN UNCOMMANDED SHUTDOWN OF THE NR 1 ENGINE AT FL 120 AFTER TAKEOFF.   ITT WENT TO 900 DEGREES C AND THE 	CREW REDUCED THE THROTTLE AFTER WHICH THE ENGINE SHUTDOWN, UNCOMMANDED.  THE AIRCRAFT RETURNED AND LANDED SAFELY WITH NO	 INJURIES REPORTED.  DEBRIS WAS FOUND IN THE TAILPIPE WITH NO DAMAGE TO THE LPT3 BLADES NOTED.  THE FAN COULD BE ROTATED	 SMOOTHLY BY HAND AND BORESCOPE OF THE HP COMPRESSOR REVEALED NO DAMAGE. ENGINE IN FOR INVESTIGATION, STRIP REPORT WILL 	BE SUBMITTED AT A LATER DATE.		2	L	7	2 	4T	4	F	RT	T00011AT	TE6CH				 
2005071800011	20050718	00011	EA  	2005	7	18	CA050628002      	2	20050624	G	7200		ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		SHUTDOWN        	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCE40252			(CAN) A LOSS OF OIL PRESSURE WAS NOTED BY THE FLIGHT CREW WHO ELECTED TO SHUT THE ENGINE DOWN ONCE THE OIL PRESSURE APPR	OACHED LOWER LIMITS.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE DISCOVERED FINE BLACK PARTICLES, CARBON IN THE 	OIL AND DETERMINED THAT THEY WERE AFFECTING THE OIL PRESSURE REGULATOR.  NO OIL LEAKS WERE NOTED AT THAT TIME.  THE ENGI	NE WAS REMOVED FOR FURTHER INVESTIGATION.  ONCE THE FINAL INVESTIGATION HAS BEEN ACCOMPLISHED MORE DETAILS WILL BE ADDED	.		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2005071800018	20050718	00018	SO  	2005	7	18	CA050628003      	2	20050626	G	8530	AEC631397SN	CYLINDER HEAD   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)  CYLINDER HEAD CRACKED.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2005071800010	20050718	00010	EU  	2005	7	18	CA050629001      	1	20050620	G	2910	NAS1602916	O-RING          			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					GREEN HYD SYS	DEFORMED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											THREE HOURS INTO FLIGHT, AIRCRAFT EXPERIENCED LOSS OF GREEN SYSTEM HYDRAULIC FLUID.  GREEN SYSTEM ENGINE DRIVEN PUMPS SE	LECTED OFF FOR THE REMAINDER OF FLIGHT.  LANDING GEAR GRAVITY EXTENSION CARRIED OUT AND AIRCRAFT LANDED WITHOUT INCIDENT	.  LEAK IDENTIFIED AS O-RING BETWEEN HYDRAULIC RESTRICTOR AND CHECK VALVE OF GREEN SYSTEM PRESSURE IN NR 2 ENGINE PYLON 	AREA.  O-RING REPLACED AND SYSTEM TESTS SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2005071800009	20050718	00009	NM  	2005	7	18	CA050629002      	1	20050629	G	2913	62337	PUMP            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP (EDP) LOW PRESSURE LIGHT ILLUMINATED.  THE  A-SYSTEM HYDRAULIC Q	UANTITY WAS ALSO LOW AT 22 PERCENT.  THE AIRCRAFT CONTINUED TO THE DESTINATION WITHOUT ANY INCIDENT. MAINTENANCE INSPECT	ION REVEALED A DAMAGED O-RING ON THE EDP INLET ELBOW. THE LEAK THAT OCCURRED CAUSED THE FLUID LEVEL TO DEPLETE ENOUGH TO	 CAUSE THE EDP TO CAVITATE. THIS CAUSED FAILURE OF THE PUMP AND CREATED THE LOW PRESSURE SITUATION. MAINTENANCE REPLACED	 THE EDP, O-RINGS, FILTERS AND SERVICED THE HYDRAULIC FLUID. THE AIRCRAFT WAS RETURNED TO SERVICE AFTER SUCCESSFUL LEAK 	TESTS WERE CONDUCTED.	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071800017	20050718	00017	GL  	2005	7	18	CA050629003      	2	20050628	G	7323	23070101	GOVERNOR        			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					PT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								CAE890625S			PT GOVERNOR, HIGH SIDE FAILURE.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005080500001	20050805	00001	NM  	2005	8	5	CA050629004      	1	20050503	G	4920	PW901A	APU             			BOEING	747   	747400      	       	NM  										APU BAY	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THE APU SUFFERED DAMAGE TO THE HIGH PRESSURE TURBINE BLADES AND SHEARING OF THE POWER TURBINE SHAFT AND CASING FLANGE BO	LTS.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONE DETERMINED.					2	L	7	4 	4F			RT	A20WE   					 
2005080500002	20050805	00002	NE  	2005	8	5	CA050629005      	2	20050623	G	7200		ENGINE          								PWA   	PT6   	PT6A68      	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								RA0326			DURING TAKEOFF AN UNCOMMANDED PROPELLER FEATHER OCCURRED.  NORMAL POWER WAS RESTORED AFTER PULLING THE PROPELLER SYSTEM 	CIRCUIT BREAKER AND THE AIRCRAFT DIVERTED TO AN AUXILIARY AIRFIELD.  THE ENGINE CHIP DETECTOR WARNING SUBSEQUENTLY ANNUN	CIATED FOLLOWED BY UNCOMMANDED TORQUE FLUCTUATIONS.  THE ENGINE WAS SHUT DOWN IN FLIGHT ON FINAL APPROACH.  P&WC WILL IN	VESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.								4	T			E26NE				 
2005080900079	20050809	00079	NE  	2005	8	9	CA050629006      	2	20050624	G	7200		ENGINE          	PWA         	PW125B      	FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA						125062		125062			(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED TORQUE REDUCTION.  THE AIRCRAFT CONTINUED TO DESTINATION WHERE	 GROUND INSPECTION REVEALED DEBRIS ON BOTH ENGINE CHIP DETECTORS.  A SUBSEQUENT START ATTEMPT PRODUCED UNUSUAL ENGINE NO	ISES.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE, ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005071800016	20050718	00016	CE  	2005	7	18	CA050630001      	1	20050613	G	8011	630680	BEARING         	CONT        		CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1A175	1A175SFC    	GL  	STARTER ADAPTER	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STARTER ADAPTER DISASSEMBLED FOR OVERHAUL. SHAFT GEAR REMOVED FROM BEARING WHEN NEEDLES FELL OUT, SUSPECT POSSIBLE	 UNAPPROVED PART.  ENGINE HAD JUST BEEN INSPECTED. QUALITY AND WORKMANSHIP MADE ENGINE NON-AIRWORTHY IAW FINDING.					1	H	7	1 	3O	3	O		3A12    	E253	5	N	P857	 
2005080900082	20050809	00082	GL  	2005	8	9	CA050630002      	2	20050615	G	7250	23005200	TURBINE         	ALLSN       	C28         	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					1ST STG NOZZLE	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA						CAE860657					(CAN) FAILED POWER CHECK. TURBINE REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005080900083	20050809	00083	CE  	2005	8	9	CA050630003      	1	20050613	G	3230	0024100381	SHAFT           			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	CAM TRACK	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NLG DOOR RETRACT SHAFT ASSEMBLY PREMATURE WEAR (160 CYCLES) NEW AIRCRAFT (2005).  INSTALLED PRODUCT IMPROVEMENT KI	T NR 36-8005-3 SUGGEST KIT BE INCORPORATED AT PRODUCTION (KIT REPLACES PIN THAT TRACKS INCAM WITH A ROLLER).					1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P36EA	 
2005080900084	20050809	00084	CE  	2005	8	9	CA050630004      	1	20050606	G	2432		BATTERY CABLE   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	BATTERY CABLE	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) BATTERY DISCHARGE - ELECTRICAL SYSTEM TURNED OFF. NORMAL LANDING. BATTERY REMOVED/CHARGED/REPLACED.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2005080900085	20050809	00085	GL  	2005	8	9	CA050630005      	3	20050609	G	6111	HCC2YR1BFF84	BLADE           			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	PROP BLADE	BROKEN          	W				O	A			OTHER                   	UNSCHED LANDING         			D	E	Y	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	ENGINE STOPPAGE           	CR	CRUISE         	1			CA											(CAN) AC WAS IN CRUISE AT 3500 FEET. PILOT HEARD A LOUD BANG, AC STARTED TO SHAKE VIOLENTLY.  PILOT WAS ABLE TO MAINTAIN	 ALTITUDE AND TURNBACK.  EMERGENCY CALL WAS MADE.  ENGINE STARTED TO SURGE ON SHORT FINAL, OIL LIGHT CAME ON, ENGINE QUI	T.  MADE A SAFE LANDING ON RUNWAY WITH NO FURTHER INCIDENT.  INSP REVEALED, 9 INCHES OF ONE PROP BLADE HAD BROKEN OFF.  	VIBRATION HAD CAUSED MANY COMPONENTS TO BREAK OR FALL OFF.  STARTER SOLENOID FELL OFF, SEVERAL EXHAUST PIPES BROKE OFF M	ELTING A HOLE IN COWLING. FUEL SERVO HAD BROKEN. INITIAL INSP REVEALED NO CRACKS IN MOUNT STRUCTURE. PROP IS IN FOR LAB 	ANALYSIS.  AMO HAS IMPLEMENTED MORE DETAILED NDT AND PREFLIGHT PROCEDURES FOR AIRCRAFT RUNNING ON GRAVEL STRIPS.	1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2005080800103	20050808	00103	SW  	2005	8	8	CA050630006      	1	20050623	G	2432	MS24171D1	RELAY           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					BATTERY	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											RELAY NOT ACTIVATING.  REPLACED RELAY.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080800104	20050808	00104	EU  	2005	8	8	CA050630007      	1	20050629	G	3210	107A703056A	LANDING GEAR    			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	NOSE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER T/O FROM YXH FOR YQL, CREWS ATTEMPTED TO RETRACT L/G.  GEAR WOULD NOT RETRACT SO THE CREW SELECTED OVERRIDE.  THE 	GEAR RETRACTED BUT NLG DID NOT FULLY RETRACT INTO NOSE GEAR BAY.  CREWS THEN SELECTED GEAR EXTENSION AND RETURNED BACK T	O BASE WITH NO FURTHER PROBLEMS.  MX FOUND THAT L/G GEAR SAFETY SWITCH WAS NOT BEING MADE DUE TO L/G BEING IMPROPERLY SE	RVICED NIGHT BEFORE.  IT HAS BEEN NOTED BEFORE THAT N/G INTERNAL FLOATING PISTON ON OCCASION (ALL JETSTREAM NOSE GEAR AS	SY`S ) WILL HANG UP AND STICK DURING SERVICE GIVING AME A FALSE INDICATION OF PROPER SERVICE.  AFTER REVIEW FOUND ALTERN	ATE METHOD IN MM.  THAT WILL RECTIFY THIS PROBLEM.  ALL OF OUR MX TO BE NOTIFIED.  GEAR RESERVICED AND NO FURTHER FAULTS	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2005080800105	20050808	00105	GL  	2005	8	8	CA050630008      	2	20050629	G	7250	6898663	TURBINE WHEEL   			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					THIRD STAGE	FAILED          	W				E				ENGINE SHUTDOWN         				X	T	E	ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   	VIBRATION/BUFFET          	LD	LANDING        	1			CA								CAT90167			DURING SCHEDULED LANDING, WHILE THE WEIGHT OF THE A/C WAS ALREADY ON WHEELS, PILOT HEARD A LOUD BANG FOLLOWED BY NUMBER 	2 ENGINE N2 DECELERATION AND ENGINE CHIPLIGHT INDICATIONS.  PRELIMINARY INVESTIGATION REVEALED FAILURE OF THE THIRD STAG	E TURBINE WHEEL (SEE ATTACHED PHOTO OF SECTIONS OF THE WHEEL'S OUTER SHROUD).  FULL INVESTIGATION IS TO FOLLOW AT STANDA	RD AERO.			1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005080800106	20050808	00106	CE  	2005	8	8	CA050630009      	1	20050629	G	5520	11561001065	RIB             	BEECH       	1156100163  	BEECH 	100   	B100        	1152919	CE  										ELEVATOR	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA						BE114A					WHILE REPAIRING OTHER CRACKS IN THE AREA OF THE RIB, CRACKS WERE FOUND IN THE RIB AT THE POINT WHERE THE BALANCE WEIGHT 	ATTACHMENT ANCHOR NUTS ARE RIVETED ON .					1	L	7	2 	4T				A14CE   					 
2005080800107	20050808	00107	NM  	2005	8	8	CA050630010      	1	20050626	G	2910	DSC252B40124	LINE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYD	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											AFTER TAKEOFF AND GEAR RETRACTION, CREW NOTICED LOSS OF HYDRAULIC FLUID IN THE NR 2 SYSTEM.  AIRCRAFT RETURNED FOR NORMA	L LANDING.  MAINTENANCE INSPECTION FOUND THE HYDRAULIC FLEX LINE TO THE NOSE GEAR DRAG STRUT ACTUATOR LEAKING.  LINES RE	PLACED.  FLUID TOPPED UP AND SYSTEM BLED.  GROUND CHECKED SERVICEABLE, AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080400001	20050804	00001	NE  	2005	8	4	CA050701001      	2	20050626	G	7322	3616991	CARBURETOR      			CVAC  	PBY5  	PBY5A       	2421208	WP  	PWA   	R1830 	R183092     	52020	NE  					LT ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA								25007			(CAN) LT ENGINE OF AIRCRAFT STARTED TO BACK FIRE AND DEVELOP LOW POWER DURING POWER REDUCTION AFTER TAKEOFF.  PILOT'S EL	ECTED TO 'CAGE' ENGINE AND RETURN TO THE DEPARTURE AIRPORT.  DIAGNOSIS FOUND A CARBURETOR THAT DID NOT FUNCTION CORRECTL	Y FORMED RANGE POWER SETTINGS, ALTHOUGH IDLE AND FULL POWER WERE FINE.  CARB REPLACED WITH OVERHAULED EXCHANGE UNIT AND 	PROBLEMS WERE RESOLVED.  DURING CARB EXCHANGE, SIGNIFICANT LEVELS OF CORROSION PRODUCTS WERE FOUND FLOATING OUT OF FITTI	NGS ETC.		2	H	7	2 	4R	4	R		2548    	5E4				 
2005080400014	20050804	00014	NE  	2005	8	4	CA050704003      	2	20050614	G	7261	4074T58PXX	O-RING          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 ENGINE	FLAT            	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, ENG NR 1 OIL PRESS WAS FLUCTUATING THEN 'ENG 1 OIL PRESS' WARNING MESSAGE WAS RECEIVED ON ED1.  THE E	NGINE NR 1 WAS SHUT DOWN.  AIRCRAFT LANDED IN VALENCIA.  5 QUARTS WERE ADDED TO ENGINE NR 1 AND FOUR C-SUMP O-RINGS WERE	 REPLACED.  THE PART NUMBERS OF THE O-RINGS ARE: 4074T58P02, P07, P14, P15.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005080400015	20050804	00015	CE  	2005	8	4	CA050704004      	1	20050629	G	2434		HOUSING         			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					ALTERNATOR	LOOSE           	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED HEARING A NOISE AND THEN NOTICED HIS ALTERNATOR WAS OFF LINE.  AIRCRAFT LANDED WITHOUT FURTHER INCI	DENT.  MAINTENANCE FOUND THAT THE HOUSING HALVES ON THE ALTERNATOR WERE QUITE LOOSE.  REPLACE ALTERNATOR STILL NO CHARGE	.  FURTHER REPLACED VOLTAGE REGULATOR AND TEST RUN.  FOUND CHARGING SYSTEM OPERATIONAL. THE ALTERNATOR HAS REGULAR 500 H	OUR BRUSH INSPECTIONS. THE LAST BRUSH INSPECTION WAS 470 HOUR PRIOR TO THIS OCCURRENCE. TSOH 1393.1.			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005080400016	20050804	00016	NE  	2005	8	4	CA050704007      	2	20050702	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  						DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA								124610			(CAN) ON LEVELING FROM CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND T	HE AIRCAFT DIVERTED.  POST-FLIGHT INSPECTION REVEALED THE ENGINE OIL FILTER TO BE BLOCKED BY CARBON PARTICLES.  PWC WILL	 MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2005080400017	20050804	00017	NE  	2005	8	4	CA050704008      	2	20050626	G	7260		DRIVE ASSY      			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ACCESSORY G/R	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE ENGINE LOST POWER AND FLAMED OUT.  THE AIRCRAFT COMPLETED A SINGLE-ENGINE LANDING AT DESTINATION.	  POST-FLIGHT INSPECTION REVEALED A DAMAGED ACCESSORY GEARBOX DRIVE TOWERSHAFT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080400018	20050804	00018	NE  	2005	8	4	CA050704009      	2	20050629	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								DB0083			(CAN) DURING CLIMB, THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT TO REDUCE POWER.  THIS WAS ACCOMPANIED BY AN ELECTRON	IC ENGINE CONTROL (EEC) REVERSION.  THE FLIGHT WAS DIVERTED AND THE ENGINE WAS SHUT DOWN ON FINAL APPROACH.  P&WC WILL I	NVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005080400069	20050804	00069	SO  	2005	8	4	CA050705002      	1	20050630	G	3220		BUSHING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NLG	MISSING         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON LANDING AND TAXI IN, RIGHT HAND GEAR COLLAPSED, NO PROP STRIKE OCCURRED.  DRAG STRUT CENTER BOLT BROKE IN HAL	F, THUS THE GEAR FAIL.  UPON INVESTIGATION FOUND ONE BUSHING MISSING, TWO ARE REQUIRED.  COULD NOT FIND BUSHING IN THE T	AXI AREA, DON'T KNOW WHERE OR WHEN IT WENT MISSING.  BOLT SUBMITTED TO TSB IN WINNIPEG.  NO PASSENGERS ONBOARD AND A NOR	MAL LANDING.			1	L	7	2 	3O	3	O		1A10    	1E4				 
2005080400070	20050804	00070	NE  	2005	8	4	CA050705003      	2	20050630	G	8520		CRANKCASE       			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A MAINTENANCE INSPECTION TO TROUBLESHOOT AIRCRAFT, OIL LEAK, MAINTENANCE DISCOVERED A CRACK IN THE CRANKCAS	E.  AERO-ENGINES INC OUT OF LOS ANGLES REBUILT THIS ENGINE, BUT I WAS UNABLE TO FIND THEM FROM THE MANUFACTURER DROP-DOW	N LIST.  THE NUMBER OF ENGINE CYCLES IS UNKNOWN.				1	H	7	1 	3R	3	R		A806    	5E1				 
2005080400071	20050804	00071	NE  	2005	8	4	CA050705004      	2	20050524	G	7200	3032208	BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA			13452								(CAN) ENGINE ORIGINALLY OVERHAULED IN 2002, FIRST RUN. AT THAT TIME, A PROCESS TO CLEAN OIL JET NOZZLE 3 AND 4 WAS UTILI	ZED AS PER OEM MANUAL. OTHER OPERATORS HAD EXPERIENCED DIFFICULTY WITH THE 3/4 OIL NOZZLE AND IT WAS FOUND THAT PROPER A	ND THOROUGH CLEANING OF THE NOZZLE WAS NOT ASSURED AT THE OVERHAUL LEVEL. IT WOULD APPEAR THAT THE 3/4 NOZZLE PLUGGED UP	 AND STARVED THE NR 3 BEARING TO THE POINT OF FAILURE. OVERHAULS WHERE MANDATED WITH A MANDATORY REPLACEMENT OF THE 3/4 	NOZZLE FOR ALL OUR ENGINES. HAVE SEVERAL THAT AS A PRECAUTION, GOING BACK IN, TO SIMPLY REPLACE 3/4 NOZZLE AS A RESULT O	F FAILURE. THIS IS THE 1ST FAILURE.  FLEET EXPERIENCED FAILURES IN THE NR 2 BEARING CAVITY.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005080400072	20050804	00072	NM  	2005	8	4	CA050706001      	1	20050629	G	2130	56697	VALVE           			BOEING	737   	737500*     	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FLOW CONTROL	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, A/C WOULD NOT PRESSURIZE.  SUSPECTING AN OPEN DOOR OR POSSIBLE DAMAGE, ELECTED TO RETURN.  IAW AMM M	X PERSONNEL INSPECTED A/C AND FOUND NO DEFECTS WITH PRESSURE VESSEL AND ALL DOORS CLOSED TIGHT WITH NO DAMAGED SEALS.  T	/S OF PRESS SYS REVEALED OUTFLOW VALVES WERE WORKING CORRECTLY.  SUSPECTING A FAULTY CONTROLLER, A/C RETURNED TO SERVICE	 USING MEL RELIEF FOR THE PRESS SYSTEM.  THE NEXT DAY A/C RETURNED TO ITS PRIMARY MX BASE, FURTHER T/S REVEALED A SEIZED	 AUTOMATIC FLOW CONTROL VALVE LOCATED IN THE EE BAY WAS THE CAUSE.  THE VALVE WAS REPLACED AND A/C PRESSURIZED CORRECTLY	.  TO FURTHER ENSURE THE DEFECT WAS CORRECTED, A TEST FLT WAS ISSUED.  A/C PRESSURIZED AS REQUIRED DURING TEST FLT.	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005080400073	20050804	00073	NE  	2005	8	4	CA050706002      	2	20050705	G	7250		SEAL            			BOEING	767   	767300      	1385204	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					GEARBOX	MIGRATED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											LOW OIL QUANTITY INDICATIONS AND HIGHER THAN NORMAL TEMPERATURE AT CRUISE RESULTANT FROM FRAGMENTS OF A DISBONDED INLET 	GEARBOX GEARSHAFT TEFLON (PTFE) SEAL DISCOVERED WHICH HAD MIGRATED INTO THE TGB SCAVENGE LINE AND INLET SCREEN.  ENGINE 	MANUFACTURER HAS PRIOR KNOWLEDGE OF SEAL FAILURE.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005080400074	20050804	00074	WP  	2005	8	4	CA050706003      	1	20050630	G	6240		GOVERNOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ROTOR	OVERSPEED       	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			HO	HOVERING       	1			CA											WHILE MOVING HELICOPTER IN A HOVER, PILOT NOTICED A POWER ON OVERSPEED AT APROX 114 PERCENT ROTOR AND ENGINE.  GOVERNOR 	WAS CONFIRMED TO BE ON BY THE PILOT.  GOVERNOR SWITCH RESET BETWEEN OFF AND ON POSITION WITHOUT A CHANGE.  IMMEDIATE LAN	DING CARRIED OUT.  SUBSEQUENT TEST HAS BEEN MADE ON THE GOVERNOR WHICH SEEMED TO WORK FINE.  CONDITIONAL OVERSPEED INSPE	CTION CARRIED OUT PER R44 MM 2.540 AND ENGINE SB 369 J.  NO MAJOR PROBLEM FOUND.  BLADE BOLTS REPLACED AS A PRECAUTIONAR	Y MEASURE.  GOVERNOR ISSUE WILL BE DISCUSSED WITH RHC CIE.		1	G	7	1 	3O	3	O		H11NM   	E295				 
2005080400075	20050804	00075	NM  	2005	8	4	CA050706004      	1	20050706	G	5610		WINDOW          			BOEING	767   	767209      	1385127	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					COCKPIT	ARCED           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											BURNING SMELL DETECTED IN COCKPIT.  ACFT DIVERTED.  OVERWEIGHT LANDING BY 10,600 KL AND SMOOTH LANDING.  FOUND CAUSE OF 	BURNING SMELL AT GROUND CONN OF RT NR 3 WINDOW.  DE-ACT RT NR 3 AS PROCEDURES C/B P36-H7 PULLED AND COLLARED NR3 RT WIND	OW HEAT INOP.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005080400076	20050804	00076	SW  	2005	8	4	CA050706005      	1	20050706	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  					TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											RT FLAP CABLE FRAYED AT WING ROOT PULLEY.  THIS CABLE WAS A GALVANIZED CABLE.						1	H	7	1 	3O	3	O		A21CE   	E286				 
2005080400077	20050804	00077	CE  	2005	8	4	CA050706006      	1	20050702	G	2434	DOFF10300BR	ALTERNATOR      			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	BATTERY STUD	ARCED           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA								27338R			(CAN) DURING APPROACH INTO YYC, THE PILOT NOTED A SHORT, MODERATE BUZZING NOISE IN HEADSET.  THERE WAS NO SIGN OF SMOKE 	BUT THE AMMETER INDICATED ZERO AMPS.  THE PILOT LANDED WITH NO OTHER INDICATIONS.  THE SYSTEM WAS INSPECTED AND FOUND TH	AT THE BATTERY STUD ON THE ALTERNATOR HAD ARCED ON THE ALTERNATOR CASE.  THE CASING ON THE ALTERNATOR AND THE STUD WERE 	BOTH MELTED.  THE WIRING TO CONDENSER WAS ALSO DAMAGED.  THE TORQUE ON THE STUD AND NUT WAS NOT EXCESSIVE WHEN THE BATTE	RY CABLE WAS REMOVED.  THIS LEADS US TO SUSPECT THE INSULATOR MAY HAVE FAILED.		1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2005080400136	20050804	00136	CE  	2005	8	4	CA050706007      	1	20050629	G	4900	99101135	BLOWER          			CESSNA	650   	650         	2076802	CE  										APU COOLING FAN	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHEN APU ON AND APU STARTER/GEN PUT ONLINE (GENERATOR ON). THE APU STARTER/GENERATOR WOULD COME OFFLINE AFTER ABOU	T 3 SECONDS AND APU WOULD SHUT DOWN.  DURING INVESTIGATION, THE MECHANIC FOUND THE APU COOLING FAN BLADES MISSING, ALL T	HE BLADES WERE BROKEN OR MISSING.  IT WAS FOUND THAT IF NO AIRFLOW WAS SENSED WITHIN 3 SECONDS OF GENERATOR ON, THE GENE	RATOR AND APU WOULD SHUTDOWN.			2	L	7	2 	4F				A9NM    					 
2005080400139	20050804	00139	NM  	2005	8	4	CA050706008      	1	20050705	G	2910	B432E0562C	LINE            			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											LOSS OF A SYSTEM HYDRAULICS.  RECTIFICATION INVESTIGATION FOUND THE NUMBER 2 ENGINE THRUST REVERSER HYDRAULIC RETURN LIN	E HAD FAILED CAUSING THE LOSS OF A SYSTEM FLUID, PART NUMBER B432E0562C.  UPON DELIBERATION WITH FLIGHT OPERATIONS, IT W	AS DECIDED TO DISPATCH THE AIRCRAFT UNDER A FERRY PERMIT AUTHORITY, WHICH INCLUDED ISOLATING THE NUMBER 2 THRUST REVERSE	R IN ACCORDANCE WITH MEL 78-01-01.  REPLENISHING THE HYDRAULIC FLUID AND CHECKING FOR ADDITIONAL LEAKS. UPON ARRIVAL INT	O YEG, THE REFERENCED HYDRAULIC LINE WAS REPLACED.		2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005080400140	20050804	00140	SW  	2005	8	4	CA050706009      	1	20050627	G	2822	2C271	CARTRIDGE       	AIRBORNE    		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					BOOST PUMP	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						7AF260					(CAN) FUEL BOOST PUMP MAKING NOISES.  PUMP CHANGED.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005080400141	20050804	00141	NM  	2005	8	4	CA050706010      	1	20050705	G	5753	144N25311	ATTACH FITTING  			BOEING	757   	757256      	1384925	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			49904								DURING ROUTINE C2 INSPECTION OF AIRCRAFT, BOTH LOWER FLAP MECHANISM ATTACH FITTINGS WERE FOUND TO BE CORRODED.  DATA WAS	 PASSED TO COMPANY ENGINEERING DEPARTMENT WHO CONTACTED BOEING ENGINEERING.  BOEING SENT AN APPROVED TIME LIMITED REPAIR	 WHICH WAS CARRIED OUT TO THEIR INSTRUCTIONS.  THIS REPAIR IS SATISFACTORY FOR 24 MONTHS, NOT TO EXCEED 3000 CYCLES.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005080400142	20050804	00142	SW  	2005	8	4	CA050706011      	1	20050610	G	6210	212015501115	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR	DEBONDED        	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											BOTTOM SKIN OF BLADE DEBONDED FROM TIP ALONG STAINLESS LEADING EDGE FOR 28 INCHES AND APPROX 3 INCHES PEELED BACK, CAUSI	NG SEVERE VERTICAL VIBRATION.  PILOT DECLARED A MAYDAY AND CARRIED OUT PRE-CAUTIONARY LANDING.  BLADE WAS REMOVED AND SE	NT TO CTI AS IT WAS REPAIRED AT CTI ONLY 3 HOUR BEFORE THE FAILURE, BLADE WAS INSPECTED BY TSB.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005080400143	20050804	00143	EU  	2005	8	4	CA050707001      	1	20050608	G	3246	C20206150	WHEEL           			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680A      	30025	NE  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING TRANSIT CHECK ONE OF THE MAIN WHEEL TIRE WAS FOUND WITH LOW PRESSURE.  MAIN WHEEL ASSEMBLY WAS REMOVED AND SENT T	O THE REPAIR SHOP FOR INVESTIGATION.  DURING INSPECTION, THE OUTBOARD WHEEL HALVE WAS FOUND CRACKED APPROX ONE INCH LONG	 ON LOWER WHEEL WEB BETWEEN THE TIE BOLT FLANGE AND THE TIRE BEAD FLANGE.  THE WHEEL HUB WAS SCRAPPED AND AIRBUS INDUSTR	IES WAS ADVISED.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2005080400144	20050804	00144		2005	8	4	CA050707002      	4	20050707	G	3417	7000700637	ADC             			DHAV  	DHC7  	DHC71       	2802702	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING ROUTINE MAINTENANCE AND RECERTIFICATION OF THE AIRCRAFT AIR DATA COMPUTERS AND FLIGHT MANAGEMENT SYSTEM THE TECHN	ICIANS NOTED THAT THE ADC S SYSTEM HAD BEEN MODIFIED TO USE P/N 7000700-637 ADC S IN PLACE OF THE DEHAVILLAND INSTALLED 	P/N 7000700-920 UNITS.  THERE IS CURRENTLY NO APPROVAL IN PLACE TO USE THE 637 UNITS IN THE DASH 7.  A SEARCH OF THE AIR	CRAFT MAINTENANCE RECORDS HAS FAILED TO PROVIDE ANY APPROVAL OF THE ADC SYSTEM MODIFICATION OR APPROPRIATE ENGINEERING D	OCUMENTS AND CERTIFICATION.		2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2005080400145	20050804	00145	NE  	2005	8	4	CA050707003      	2	20050627	G	8530	R1340	CYLINDER HEAD   								PWA   	R1340 	S3H1        	52016	NE  					ENGINE	CRACKED         	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) CYLINDER HEAD CRACKED FROM REAR SPARK PLUG HOLE AROUND TO FRONT PLUG HOLE.											3	R			E143				 
2005080400146	20050804	00146	NE  	2005	8	4	CA050707004      	2	20050625	G	8530	R1340	CYLINDER HEAD   								PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	SEPARATED       	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) CYLINDER HEAD SEPARATED FROM BARREL JUST BELOW SPARK PLUG HOLES.											3	R			5E2				 
2005080400147	20050804	00147	SW  	2005	8	4	CA050707005      	1	20050624	G	6220	K913001003	HUB             			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING LAG PIN REPLACEMENT BLADE WAS REMOVED.  UPON REMOVAL OF BLADE HUB WAS INSPECTED AND THE PROBLEM WAS FOUND. 	 THE UPPER SURFACE OF THE LOWER HUB HALF KRON BEARING SURFACE WAS WORN THROUGH TO METAL IN APPROXIMATELY 1/5 OF ITS CIRC	UMFERENCE.  NO INSPECTION CRITERIA WAS FOUND IN THE MM FOR THIS PARTICULAR INSTANCE SO HUB WAS RETIRED.				1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
2005080400164	20050804	00164	SW  	2005	8	4	CA050707006      	1	20050706	G	5210	2724150475	DOOR            			SWRNGN	SA227 	SA227*      	       	SW  										PAX	OUT OF ADJUST   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											AIRCRAFT DEPARTED AND THE PRESSURIZATION WAS MAKING A LOUD SQUALLING SOUND.  AIRCRAFT RETURNED TO BASE AND DOOR ECCENTRI	CS WERE ADJUSTED FOR A BETTER FIT.  AIRCRAFT RELEASED TO SERVICE AFTER SUCCESSFUL TEST FLIGHT.					2	L	7	2 	4T			RT	A5SW    					 
2005080400175	20050804	00175	WP  	2005	8	4	CA050707007      	2	20050630	G	7230	31037081	BEARING         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBIX	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											PILOT REPORTED, WHEN TURNING THE LT ENGINE PROPELLER AFTER SHUTDOWN, NOTICED A GRINDING NOISE COMING FROM THE ENGINE.  A	FTER INVESTIGATION, THE ENGINE GEARBOX WAS OPENED AND THE FWD COMPRESSOR BEARING WAS FOUND DAMAGED AND TO BE THE CAUSE O	F THE NOISE AND FRICTION.  BEARING WAS REPLACED.  NOTE THAT THERE IS A LIFE LIMIT TO THIS BEARING AND THAT THE BEARING I	N CAUSE HAD NOT REACHED ITS LIFE LIMIT.			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2005080400176	20050804	00176	EA  	2005	8	4	CA050707009      	2	20050705	G	7250	3032208	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NR 3	CHATTERING      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCERC0093			WHILE ROTATING THE RIGHT PROPELLER TO DRESS PROPELLER BLADES AN UNUSUAL NOISE WAS HEARD.  A STANDARD AERO TECHNICIAN WAS	 CALLED IN.  THE RIGHT HAND ENGINE POWER SECTION WAS REMOVED AND DISMANTELED.  FOUND ROTOR BALANCING ASSEMBLY.  NR 3 BEA	RING P/N:3032208 TO HAVE CHATTER MARKS ON THE OUTER RACE.  NR 3 BEARING REPLACED WITH NEW UNIT P/N:3032208 S/N:BB0042763	.  ENGINE REASSEMBLED, ENGINE GROUND RUNS COMPLETED SATISFACTORY, AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005080400177	20050804	00177	EA  	2005	8	4	CA050707010      	2	20050705	G	7250	311269603	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NR 4	BRINELLED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCERC0093			WHILE ROTATING THE RIGHT PROPELLER TO DRESS PROPELLER BLADES AN UNUSUAL NOISE WAS HEARD.  A STANDARD AERO TECHNICIAN WAS	 CALLED IN.  THE RIGHT HAND ENGINE POWER SECTION WAS REMOVED AND DISMANTELED.  FOUND ROTOR BALANCING ASSEMBLY.  NR 4 BEA	RING P/N:3112696-03 TO HAVE BRINELLING ON THE OUTER RACE.  NR 4 BEARING REPLACED WITH NEW UNIT P/N:3112696-03 S/N:FC1526	96. ENGINE REASSEMBLED, ENGINE GROUND RUNS COMPLETED SATISFACTORY, AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005080400178	20050804	00178	NM  	2005	8	4	CA050708001      	1	20050707	G	7160		NOSE COWL       			BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								SBRR4099			DURING ROUTINE C-CHECK INSPECTION OF AIRCRAFT, SEVERAL CRACKS WERE FOUND ON THE NR 1 ENGINE INTAKE COWL.  THE FORWARD DI	APHRAGM HAD MULTIPLE CRACKS ALL AROUND THE CIRCUMFERENCE, INCLUDING A 27 INCH CRACK AT THE LOWER SIDE.  THE REAR DIAPHRA	GM HAD 2 CRACKS.  THE COWL WILL BE REPLACED BEFORE FLIGHT.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005080400179	20050804	00179	WP  	2005	8	4	CA050708002      	2	20050707	G	7250		ENGINE          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								P44722C			AIRCRAFT WAS EN ROUTE WHEN THE CREW EXPERIENCED PROBLEMS WITH POWER.  THE CREW SHUT DOWN THE LT ENGINE AND LANDED WITHOU	T INCIDENT.  UPON INVESTIGATION IT WAS DISCOVERED THAT MOST OF THE OIL HAD LEFT THE ENGINE OUT THE BACK BY THE SCAVENGE 	PUMP.  MAINTENANCE REPLACED THE ENGINE.  ONCE THE ENGINE HAS BEEN DISMANTLED THE EXACT CAUSE WILL BE KNOWN ALTHOUGH IT H	AS THE APPEARANCE OF A FAILED SCAVENGE PUMP, SCAVENGE PUMP SEAL OR REAR TURBINE BEARING.  MORE INFO ONCE ENGINE HAS BEEN	 DISMANTLED.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2005080400180	20050804	00180	NM  	2005	8	4	CA050708003      	1	20050708	G	1430	BACC30BK5	COLLAR          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT WING SPAR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING HEAVY MAINTENANCE IT WAS DISCOVERED ON THE LHS WING FWD SPAR AT WS 490.0 SPLICE JOINT. 4 CRACKED LOCKBOLT COLLARS	 PN BACC30BK5 WERE FOUND.  REQUEST HAS BEEN SENT TO BOMBARDIER TO REPLACE LOCKBOLTS AND COLLARS WITH HILOCK SUBSTITUTES.	  DETAILED VISUAL INSPECTION CARRIED OUT ON ALL THERE COLLARS WITH NO FAULTS FOUND,				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080400181	20050804	00181	EA  	2005	8	4	CA050708004      	1	20050702	G	2822	1D217	PUMP            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING EMMA CHECK, THE NR 1 FUEL SYSTEM STRAINER WAS FOUND TO BE HEAVILY CONTAMINATED WITH A FINE, GRITTY SUBSTANCE THAT	 STAYED SUSPENDED IN THE FUEL.  FUEL TANKS AND DRAINS WERE FOUND TO BE CLEAR.  FURTHER INVESTIGATION REVEALED THAT THE O	UT PUT FROM THE NR 1 BOOST PUMP WAS SIGNIFICANTLY LOWER THAN NR 2 PUMP.  WHEN A MAGNET WAS INTRODUCED TO THE CONTAMINATE	D FUEL, THE CONTAMINANT ATTACHED ITSELF TO THE MAGNET.  THE BOOST PUMP WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SER	VICE WITH NO RECURRENCE OF THE CONTAMINATION IN THE FUEL STRAINER.		1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2005080500003	20050805	00003	SW  	2005	8	5	CA050708005      	1	20050705	G	3260	3A07005178	PROXIMITY SWITCH			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  					NLG	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											DURING CRUISE, THE PILOT NOTED A GEAR UNSAFE LIGHT FOR THE NLG.  THE AIRCRAFT DID A LOW PASS AT THE AIRPORT.  IT WAS DET	ERMINED THAT THE GEAR WAS DOWN AND IT APPEARED TO BE AN INDICATION PROBLEM.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  DURI	NG INVESTIGATION BY MAINTENANCE CREW, THE AIRCRAFT WAS JACKED AND THE PROXIMITY SWITCH WAS READJUSTED AND SECURED.  A GE	AR SWING WAS ACCOMPLISHED TO VERIFY CORRECT OPERATION.  THE OTHER AIRCRAFT IN THE FLEET WERE INSPECTED AND 2 OTHER SWITC	HES WERE FOUND LOOSE, WERE RESECURED.  THE AIRCRAFT WERE RETURNED TO SERVICE.		1	L	7	1 	3T	4	T	NC	A19SW   	E4EA				 
2005080500004	20050805	00004	EA  	2005	8	5	CA050708006      	2	20050708	G	7414		POINTS          	BENDIX      							WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						06873					DURING GROUND RUN, LT ENGINE WOULD NOT RUN WITH THE LT MAG SELECTED.  MAINTENANCE CREW FOUND THE BREAKER POINT ARM BROKE	N OFF DURING INVESTIGATION.  THE MAGNETO WAS REPLACED WITH A SERVICEABLE UNIT, AND THE AIRCRAFT WAS RETURNED TO SERVICE,	 MAGNETO TSO 425.0.									4	R			E259	6	C	P8879	 
2005080500005	20050805	00005	CE  	2005	8	5	CA050709001      	1	20050707	G	2731	12600741	ACTUATOR        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ELE TRIM TAB	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			AP	APPROACH       	1			CA			13885								ELEVATOR TRIM STICKING INSPECTED AND FOUND ELEVATOR TRIM ACTUATOR TO BE AT FAULT.  GROOVE PIN LOOSE IN ACTUATOR SPROCKET	 ASSY PIN HOOKING IN GUIDE BLOCK.  ACTUATOR ASSY REPLACED.  CURRENTLY INSPECTING THE REST OF THE FLEET 152/172'S FOR LOO	SE GROOVE PINS IN SPROCKET OF ACTUATOR.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005080500006	20050805	00006	CE  	2005	8	5	CA050711001      	1	20050708	G	2460	1N1199A	DIODE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ZONE 600	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19761								AIRCRAFT STILL POWERED UP AFTER BATTERY IS SELECTED OFF.  BATTERY BUSS TIE CONTROL T/S.  FOUND THAT BATTERY RELAY WELDED	 CLOSED.  REPLACED BATTERY RELAY.  BATTERY BUSS TIE RELAY INSPECTED AND FOUND CONTACTS BADLY PITTED.  REPLACED BATTERY B	USS TIE RELAY.  OPS CHECK CARRIED OUT AND FAULT STILL RE-OCCURRED.  METERED OUT SYSTEM AND FOUND THAT BATTERY FEEDER DIO	DES SHORTED.  REPLACED DIODES AND SYSTEM CHECKED OK.  BUS CONFORMITY CHECK AND TRIPLE FED BUS SYSTEM CHECK CARRIES OUT. 	 CHECKING SERVICEABLE. WOULD SUGGEST THAT AT A REGULAR INTERVAL THAT THE RELAYS AND DIODES BE METERED OUT.  RESISTANCE V	ALUES WOULD DETERMINE IF THE RELAYS ARE GETTING WEAK AND WOULD ALSO TELL YOU IF THE DIODES ARE STILL WORKING.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005080500007	20050805	00007	CE  	2005	8	5	CA050711002      	1	20050708	G	7500	1149700401	TUBE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					BLEED AIR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											RIGHT HAND ENGINE BLEED AIR FAILURE ANNUNCIATOR ON IN CRUISE.  RIGHT HAND BLEED AIR ISOLATED AS PER SOP.  BLEED AIR TUBE	 FOUND TO HAVE FAILED AT B NUT IN RIGHT HAND WING.  EVA TUBING HAD MELTED CAUSING ANNUNCIATOR TO LIGHT.  TUBE WAS REPLAC	ED.  EVA TUBING REPAIRED AND GROUND RUN C/O WITH NO FURTHER DEFECTS.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005080500008	20050805	00008	NE  	2005	8	5	CA050711003      	2	20050706	G	7250		ENGINE          			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		DE	DESCENT        	1			CA											A/C INVOLVED IN AERIAL GRAPPLE LOGGING OPS ON DOWN WIND APPROACH TO LOG LANDING WITH A 15,000 LB SINGLE LOG LOAD.  PILOT	 REDUCED POWER TO 30% TQ. UPON ACTION CREW HEARD SOUND OF ENG SPOOLING DOWN FOLLOWED BY LOW RPM AUDIO WARNING HORN & ILL	UM OF  WARNING LIGHT.  ONCE PILOT ABLE TO SAFELY RELEASE LOAD, CONFIRMED WHAT CO-PILOT HAD IDENTIFIED AS CORRECT ENG. PU	LLED NR 2 ENG THROTTLE BACK TO CUT-OFF & ENGAGED STARTER TO COOL DOWN T5 TEMP.  ENG COOLED DOWN, MADE A SINGLE ENG LANDI	NG.  AFTER SHUTDOWN A CHECK OF T5 RECORDING SYS IND AN ENG TEMP OF 767 DEGREES C WAS REACHED FOR 3 SEC. ENG REMOVED & RE	TURNED TO OPERATOR FOR HOT SECTION INSP.  AFTER COMPLETE GROUND CHECK OUT A/C RELEASED FOR RETURN TO SERVICE.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005080500009	20050805	00009	EA  	2005	8	5	CA050711004      	2	20050702	G	7421	URHM38E	SPARK PLUG      			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LIO360A1G6  	41515	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING ROUTINE SCHEDULED 100 HR, 1 SPARK PLUG APPEARED BENT WHILE INSTALLED IN CYLINDER. UPON REMOVAL, CONFIRMED BY INSP	ECTION THAT SPARK PLUG BODY HAD SEPARATED AT NECKED DOWN AREA OF METAL BODY OF PLUG ON IGNITION LEAD SIDE OF GASKET SEAL	ING SURFACE.  AFFECTED AREA APPEARED TO HAVE OVERHEATED AND METAL WAS DISCOLOURED, METAL OVERHEATING RESULTED IN CRACK. 	 ALL PWGS INSPECTED, ONE OTHER FOUND WITH OVERHEATING BUT NOT CRACKED, BOTH REPLACED.  OVERHEATING NOT CAUSED BY ENG CON	DITION, SUGGEST MANUFACTURER DEFECT. SLOWLY PHASING OUT THE USE OF AUTOLITE SPARK PLUGS TO AVOID SIMILAR SITUATIONS, PLU	GS ARE BEING INSPECTED FLEETWIDE FOR THIS CONDITION DURING SCHEDULED MX AND SWITCHING TO CHAMPION BRAND.	1	L	7	2 	3O	3	O		A29CE   	1E10				 
2005080500010	20050805	00010	CE  	2005	8	5	CA050711005      	1	20050706	G	7602	S17771	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MIXTURE	BROKEN          	W				O				OTHER                   				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA											WHEN SHUTTING DOWN, THE ENGINE ON THE RAMP AFTER FLIGHT PILOT PULLED THE MIXTURE CONTROL TO LEAN AND THE CABLE BROKE.  E	NGINE SHUT DOWN BUT MIXTURE CABLE HAD TO BE REPLACED BEFORE NEXT FLIGHT.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005080500011	20050805	00011	CE  	2005	8	5	CA050711006      	1	20050705	G	2421		GENERATOR       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	AC SYSTEM	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING FLIGHT, PILOT NOTICED THAT THE ALTERNATOR FAILED.  WHILE THE A/C WAS STILL IN FLIGHT THE BATTERY WENT DEAD AND CO	MMUNICATION WAS LOST.  PILOT USED HANDHELD RADIO TO COMMUNICATE.  AIRCRAFT LANDED SAFELY.  ALTERNATOR WAS REMOVED AND A 	BROKEN WIRE FOUND AT THE POSITIVE TERMINAL.  TERMINAL END REPLACED.  BATTERY RECHARGED AND AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005090700009	20050907	00009	EA  	2005	9	7	CA050711007      	1	20050708	G	3213	C6UF101527	STRUT           			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WALKAROUND, THE FLIGHT CREW OBSERVED A RIVET HEAD MISSING FROM THE OUTSIDE OF THE LOWER LUG OF THE LT FORWA	RD FLOAT STRUT.  THE AIRCRAFT WAS FERRIED TO MAINTENANCE WHERE THE STRUT WAS REMOVED AND INSPECTED.  THE RIVET STEM SHOW	ED SIGNS OF INTERNAL CORROSION.  ALL OTHER RIVETS ON THE STRUT WERE INSPECTED SERVICEABLE. THE ONE RIVET WAS REPLACED AN	D THE AREA REPROTECTED.  THE STRUTS ARE NOT TRACKED SO NO TIME IN SERVICE IS AVAILABLE.			1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2005080900080	20050809	00080	CE  	2005	8	9	CA050711008      	1	20050705	G	2710	636000189	CABLE           		636000189   	CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					AILERON CABLE	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FOUND FWD AILERON CABLE TENSION AT ZERO. CROSSOVER CABLES FOUND TO BE LOOSE. REMOVED AILERON CROSSOVER CABLES FROM	 CNTRL COLUMNS WITHOUT DISTURBING HUMBUCKLE LOCKING. INSPECTED CABLES, CHAINS, SWAGES AND HUMBUCKLE.  DETERMINED ONE OF 	CROSSOVER CABLE CHAINS (FWD) WAS LIKELY INSTALLED INCORRECTLY ON DRUM SPROCKET. TEMPORARILY INSTALLING ONE OF CHAINS (BU	NCHED-UP) ON SPROCKET ONE LINK OVER FROM ITS CORRECT POSITION YIELDED APPROX CORRECT CABLE TENSION (9 LBS) AND CORRECT Y	OKE POSITION. INSTALLED CHAINS PROPERLY AND RIGGED IAW MM CH 27-10-01(4B) AND TENSION ADJUSTED IAW FIG.204. REMAINDER OF	 AILERON CNTRL SYS RIGGING CHECKED.  NO OTHER DEFECTS NOTED. INDEPENDENT CHECK COMPLETED ON ALL DISTURBED FLIGHT CONTROL	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2005080800108	20050808	00108	CE  	2005	8	8	CA050712002      	1	20050707	G	2701	B55	BEARING         			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	CONTROL COLUMN	UNSERVICEABLE   	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											WHILE FUNCTION CHECKING THE AILERON CONTROL SYSTEM PRIOR TO FLIGHT THEY BECAME HARD TO OPERATE.  THE CO-PILOT'S CONTROL 	COLUMN BEARING ON OUTER SURFACE OF FIREWALL WAS FOUND TO BE UNSERVICEABLE.  THE NEEDLE BEARINGS HAD DEPARTED THE CAGE.  	THE BEARING WAS REPLACED NEW AND THE AILERON SYSTEM WAS FUNCTION CHECKED SERVICEABLE.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
2005080800109	20050808	00109	NM  	2005	8	8	CA050712003      	1	20050701	G	2910	DSC252C6020	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											THE GEAR WOULD NOT COME UP ON DEPARTURE.  THERE WERE PROBLEMS WITH THE NR 2 HYDRAULIC SYSTEM.  THE FLIGHT RETURNED FOR M	AINTENANCE TO INVESTIGATE.  AN EMERGENCY WAS DECLARED.  DEFECT 437568 NR 2 HYD ISO VALVE LIGHT ILLUMINATED, LOSS OF SYST	EM 2 FLUID NLG RETRACTION ACTUATOR LINE (FLEX) .  REPLACED PN DSC252C6-0200, SYS PRESSURIZED BLED, NO FURTHER LEAKS NOTE	D			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080800110	20050808	00110	NE  	2005	8	8	CA050712004      	2	20050621	G	8530		EXHAUST VALVE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	NR 1 CYLINDER	BROKEN          	W				B				EMER. DESCENT           				E	O	P	VIBRATION/BUFFET          	OTHER                     	NO WARNING INDICATION     	TO	TAKEOFF        	1			CA											EXHAUST VALVE BROKE ON NR 1 CYLINDER AND FOUND IN EXHAUST STACK.						1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2005080800111	20050808	00111	CE  	2005	8	8	CA050712006      	1	20050706	G	3246	55S013	STRUT           			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					FLOAT	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											MAIN GEAR LEG BOLTS TO FLOATS FOUND LOOSE (FRONT LEG) NAS1021A5 NUTS FOUND LOOSE.  REPLACED NUTS AND RETORQUED.						1	L	7	2 	3R	3	R		A765    	5E1				 
2005080800112	20050808	00112	EA  	2005	8	8	CA050712007      	1	20050613	G	2820	NA	LINE            		C2TP211     	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL PICK UP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10786			348					DURING INSPECTION OF THE LT WING TIP FUEL TANK THE INTERNAL FUEL DELIVERY LINE WAS FOUND TO BE BROKEN AT THE INBOARD BUL	KHEAD ATTACH POINT (TACKWELD).  THIS CONDITION IF RETURNED TO SERVICE WOULD NOT ALLOW THE FULL CONTENTS OF THE WING TANK	 TO BE TRANSFERED TO THE MAIN FUEL SYSTEM, APPROXIMATELY 1/2 OF THE TIP TANKS FUEL CONTENTS WOULD REMAIN IN THE FUEL CEL	L.			1	H	7	1 	3R	3	R		A806    	5E1				 
2005080800113	20050808	00113	EA  	2005	8	8	CA050712008      	1	20050630	G	2731	C2CF1049	BELLCRANK       		C2CF1009A   	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CABLE ATTACH LUG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22753								THE ELEVATOR CONTROL BELLCRANK LOCATED IN THE FUEL SELECTOR BAY WAS FOUND TO BE CORRODED AT THE INBOARD CABLE ATTACH POI	NT, SPECIFICALLY AT THE POINT WERE THE CABLE LINK PN NR C2CF347ND ATTACHES TO THE BELLCRANK.					1	H	7	1 	3R	3	R		A806    	5E1				 
2005080400002	20050804	00002	CE  	2005	8	4	CA050712009      	1	20050601	G	3240		LINE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	BRAKE ASSY	PINCHED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON PERFORMING A GEAR SWING ON THE AIRCRAFT, IT WAS NOTED THAT, ON BOTH LT AND RT SIDES, THE BRAKE LINES WERE BEI	NG PINCHED IN THE GEAR DOORS WHEN CLOSED.  THE BRAKE LINES WERE REPLACED WITH NEW AND THE CLAMPS WERE REPOSITIONED TO PR	EVENT THE BRAKE LINES FROM BEING CAUGHT IN THE DOORS.				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE	 
2005080400019	20050804	00019	EA  	2005	8	4	CA050712010      	1	20050518	G	7120	MB100888	BOLT            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE ENGINE MOUNT BOLT NDT INSPECTION, A CRACK WAS NOTED ON THE ENGINE SIDE OF THE ATTACH BOLT AT THE 	RADIUS WHERE THE TIE BAR PN NR MB100877 ATTACHES.					1	H	7	1 	3R	3	R		A806    	5E1				 
2005080400020	20050804	00020	WP  	2005	8	4	CA050712011      	2	20050429	G	7497		WIRE HARNESS    			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	SHORTED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								77130			(CAN) ENGINE START PROBLEM INTERMITTENT.  EXPERT TROUBLESHOOTING FOUND 2 WIRES THAT CROSSED AND HAD CHAFED TOGETHER.  ON	LY A FAINT BLACK DUST AT THE CONNECTION REVEALED POTENTIAL SHORTING OF WIRES.  CORRECTED AND ENGINE START CORRECTED.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2005080400021	20050804	00021	NE  	2005	8	4	CA050712012      	2	20050711	G	7314		SHAFT           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					FUEL PUMP	SHEARED         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA						TF476734					(CAN) LEFT HAND ENGINE DRIVEN FUEL PUMP FAILED IN FLIGHT.  CREW SELECTED BOOST PUMP TO RESTORE FUEL PRESSURE.  2 MINUTES	 LATER FUEL BOOST PUMP (P/N 215-61620-3, S/N 113, TSO 113.8 HOURS) FAILED.  CREW FEATHERED ENGINE AND LANDED THE AIRCRAF	T WITH NO FURTHER INCIDENT.				2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
2005080400022	20050804	00022	WP  	2005	8	4	CA050712015      	1	20050711	G	2510		ANCHOR          	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					SEAT BELT	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE PREPARING TO START THE HELICOPTER PILOT REACHED TO LOCK HIS SEATBELT INTO THE BUCKLE.  THE BUCKLE WAS LYING 	BETWEEN THE SEATS NEXT TO THE COLLECTIVE.  UPON FURTHER INSPECTION IT WAS NOTED THAT THE ANCHOR TAB HAD BROKEN AWAY FROM	 THE C348-5 ANCHOR ASSEMBLY.  PART WAS CHANGED OUT THE OPERATORS OTHER R44 ANCHOR ASSEMBLIES WERE INSPECTED WITH NO OTHE	R DEFECTS NOTED.  THE ANCHOR HAS BEEN SENT TO ROBINSON FOR FURTHER INSPECTION.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2005080400023	20050804	00023	SO  	2005	8	4	CA050713001      	1	20050712	G	5280		HINGE           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					MLG DOOR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) RIGHT INBOARD GEAR DOOR DROOPING.  RED GEAR LIGHT ON DURING FLIGHT.  RIGHT INBOARD GEAR DOOR HINGE FOUND BROKEN.  	HINGE REPLACED WITH STEEL TYPE.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2005080400024	20050804	00024	SO  	2005	8	4	CA050713002      	1	20050712	G	3232	WTC21141	ACTUATOR        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					MLG DOOR	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIGHT GEAR DOOR ACTUATOR FOUND BENT AS A RESULT OF THE HINGE BREAKING.  ACTUATOR REPLACED WITH OVERHAULED UNIT.  S	YSTEM TESTED SERVICEABLE.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2005080400025	20050804	00025	SW  	2005	8	4	CA050713003      	1	20050713	G	6220	206010101129	YOKE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AJM0163					(CAN) CRACK FOUND DURING OVERHAUL 1 INCH LONG CRACK INDICATION LOCATED ON THE BOTTOM SECTION OF THE FILLET RADIUS.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400050	20050804	00050	NM  	2005	8	4	CA050713004      	1	20050713	G	5230	D20703	ACTUATOR        			BOEING	767   	767209      	1385127	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					CARGO DOOR	MALFUNCTIONED   	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FWD CARGO DOOR LIGHT CAME ON.  QRH FOLLOWED WITH A DESCENT AND DIVERSON TO YHZ.  NO FLUCTUATION IN P	RESSURIZATION.  NO BUFFET. FWD CARGO LATCH/HOOK ACTUATOR REPLACED AS PER AMM52-33-0.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2005080400078	20050804	00078	NM  	2005	8	4	CA050713005      	1	20050706	G	3233	65264351	FORGING         			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING SCHEDULED MLG REPLACEMENT, THE RETRACTION ACTUATOR END CAP FORGING WAS FOUND CRACKED, AND BROKE APART ON REMOVAL 	OF THE ACTUATOR. PRIOR TO THE GEAR CHANGE THERE WAS NO INDICATIONS OF ANY RETRACTION OR EXTENSION PROBLEMS.  THE NATURE 	OF THE INSTALLATION IS SUCH THAT THE WEIGHT OF THE GEAR AND HYDRAULIC PRESSURE WOULD KEEP THE ACTUATOR HELD IN PLACE EVE	N IF THE ATTACHMENT LUG HAD FAILED.  THE DAMAGED PARTS ARE BEING RETURNED FROM THE MRO IN MIAMI TO MISSISSAUGA FOR FOLLO	WUP.		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005080400079	20050804	00079	EA  	2005	8	4	CA050713006      	1	20050617	G	3246	MS2125005018	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NLG WHEEL	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											NOTICED BY MAINTENANCE THAT THE NR 2 NOSE WHEEL ASSEMBLY WAS MISSING ONE TIE BOLT.  NOSE WHEEL WAS REPLACED.  A SECOND O	CCURANCE A FEW DAYS LATER ON ANOTHER AIRCRAFT WAS REPORTED AFTER THE CREW NOTED THAT THE NOSE WHEEL SEEMED TO BE SPINNIN	G LONGER THAN USUAL.  MAINTENANCE FOUND A TIE BOLT MISSING AND TIRE WORN OUT OF ROUND ON NR 1 NOSE WHEEL ASSEMBLY.  PART	 CYCLES 127 TSO 169:33HRS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005080400080	20050804	00080	CE  	2005	8	4	CA050714001      	1	20050706	G	5754	99143446	RETAINER        			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					RT WING SLAT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A VISUAL INSPECTION, IT WAS FOUND THAT THE RT FLAP FLEXSHAFT RETAINER WAS MISSING (BROKEN OFF).  NEW R	ETAINER WAS INSTALLED.					2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2005080400081	20050804	00081	EU  	2005	8	4	CA050714002      	1	20050711	G	5610	NP1653118	WINDSHIELD      			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					COCKPIT	CRACKED         	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											F/O WINDSHIELD OUTER LAYER CRACKED DURING CRUISE GENERATING A WARNING MESSAGE 'ANTI-ICE R WINDSHIELD'.  NO FLAMES OR SPA	RKS WERE NOTICED.					2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2005080400124	20050804	00124	EA  	2005	8	4	CA050714003      	2	20050709	G	7250	3020745	COVER           			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PS22359			ON ENGINE SHUTDOWN, THE CAPTAIN HEARD A RUBBING SOUND EMANATING FROM THE NR 1 ENGINE.  TURNING THE PROPELLER BY HAND REP	RODUCED THE RUBBING SOUND.  THE POWER SECTION WAS REMOVED FOR INVESTIGATION.  REMOVAL OF THE PT WHEEL REVEALED THAT THE 	NR 3 BEARING COVER ITEM NR 130 B SECTION 72-50-04 FIG 2, HAD SHIFTED AND WAS RUBBING AGAINST THE PT WHEEL.  MAINTENANCE 	REPLACED THE POWER SECTION AND RETURNED THE AIRCRA FT TO SERVICE.  LAST ENGINE OVERHAUL WAS BY PRATT AND WHITNEY IN 2000	.		1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2005080400125	20050804	00125	CE  	2005	8	4	CA050714004      	1	20050711	G	3246	1388920629	BEARING         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NLG WHEEL	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING NR 5 PHASE INSPECTION, NOSE WHEEL WAS ROTATED BY HAND WHICH REVEALED A DEEP RUMBLING NOISE.  WHEN DISASSEMBLED BE	ARING WAS FOUND TO BE DRY AND BADLY WORN.  BEARING CUP WAS ALSO DAMAGED DUE TO LACK OF LUBRICATION.  DISOVERY FOLLOWED C	OMPLAINTS BY CREW OF A VIBRATION DURING CLIMB-OUT WHICH HAS SINCE STOPPED NOW BEARINGS AND CUPS HAVE BEEN REPLACED.  SUS	PECTED GREASE WAS THROWN PAST WORN GREASE SEALS WHICH HAVE ALSO BEEN REPLACED.  THERE IS NO INSPECTION REQUIREMENT BETWE	EN WHEEL CHANGES OF THE NOSE WHEEL BEARING WHICH COULD BE ON THE A/C FOR UP TO 3 YEARS.  HAVE INITIATED AN INSPECTION OF	 THE NOSE WHEEL BEARING EVERY 600 HOURS TO COINCIDE WITH THE 5TH AND 2ND PHASE INSPECTIONS.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005080400126	20050804	00126	NM  	2005	8	4	CA050715001      	1	20050625	G	2910	115503008	HOSE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LT MLG	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											NR 2 HYD SYS FLUID LOSS DURING APPROACH.  GO-AROUND CARRIED OUT L/G WAS LEFT IN DOWN POSITION.  DIVERTED A/C TO EXT.  IN	SPECTION CARRIED OUT AND FLUID LOSS FOUND DUE TO A LEAK FROM LEFT MLG STABILIZER STRUT DOWN LOCK JACK, LOWER FLEXIBLE HO	SE P/N 115503-008.  HOSE SUBSEQUENTLY REPLACED IAW AMM 32-11-16-400-801. INSPECTION OF NR 2 SYSTEM EDP CASE DRAIN CARRIE	D OUT FOR DEBRIS IAW AMM 29-11-34.  FILTER ELEMENT REPLACED, NO CONTAMINATION EVIDENT.  NR 2 HYD EDP REPLACED AS A PRECA	UTION IAW AMM 29-11-01.  NR 2 HYD SYS BLED IAW AMM 29-10-00-870-802.  NR 2 HYD SYSSERVICED IAW AMM 12-10-29-611-801.  LE	AK CHECK CARRIED OUT ON REPLACED HOSE ON LT MLG DOWN LOCK AND STARBOARD EDP, NIL LEAKS EVIDENT.  UNDERCARRIAGE FUNCTIONS	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005080400127	20050804	00127	SW  	2005	8	4	CA050715002      	1	20050710	G	6420	0301245	TURNBUCKLE      			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					TAIL ROTOR HEAD	UNSECURE        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											LOCKWIRE LEFT UNLOCKWIRED RESULTING IN TURNBARREL BECOMING UNDONE RESULTING IN TAILROTOR PITCH CHANGE FAILURE.  SPEED RI	GS WERE LOCK WIRED ON THE ONE END BUT THE ENGINEER DIDN'T RECOGNIZE THE OTHER END REQUIRED LOCKWIRE.					1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2005080400128	20050804	00128	CE  	2005	8	4	CA050715003      	1	20050627	G	3233	11238002219	ACTUATOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	NLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											AIRCRAFT WAS ON APPROACH ,WHEN SELECTED GEAR DOWN DID NOT GET NOSE GEAR INDICATION ALTHOUGH THE HANDLE WAS NO LONGER RED	.  DUE TO THE NO AVAILABILITY OF MAINTENANCE ELECTED TO RETURN TO BASE.  THE LIGHT OPERATED NORMALLY BUT THEY STILL ELEC	TED TO HAVE EMERGENCY VEHICLES STAND BY.  THE LANDING WAS UNEVENTFUL AND MAINTENANCE FOUND THAT THE INTERNAL MICRO SWITC	H IN THE NLG ACTUATOR WAS AT FAULT.  THE ACTUATOR WAS REPLACED AND TESTED SERVICEABLE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005080400137	20050804	00137	NM  	2005	8	4	CA050718001      	1	20050718	G	2910	82970009363	LINE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYDRAULIC SYS	BROKEN          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											OPERATOR EXPERIENCED A LOSS OF HYD SYSTEM NR 1 AFTER TAKEOFF.  FLIGHT CREW MADE AN UNSCHEDULED LANDING.  EDP NR 1 PRESS 	LINE FOUND BROKEN IN LT NACELLE.  HYD LINE AND EDP NR 1 REPLACED.  PURGED SYSTEM.  AIRCRAFT RTS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080400148	20050804	00148	CE  	2005	8	4	CA050718002      	1	20050716	G	2435	23085001	STARTER GEN     			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											AFTER THE LEFT ENGINE START, THE GENERATOR WOULD NOT COME ON LINE.  DURING THE SUBSEQUENT ENGINE START BY MAINTENANCE A 	LOUD GRINDING NOISE WAS HEARD FROM THE LEFT ENGINE.  THE START WAS ABORTED AND THE COWLINGS REMOVED.  THE STARTER GENERA	TOR WAS VERY HOT AND HAD AN EXCESSIVE AMOUNT OF CARBON DUST ON IT AND THE ADJACENT ENGINE AREA.  WHEN REMOVED FROM THE E	NGINE, THE STARTER GENERATOR COULD NOT BE ROTATED EVEN WITH A WRENCH ON THE DRIVE.  THE DRIVE HAD A LOT OF SIDE TO SIDE 	MOVEMENT WHICH SUGGESTS A BEARING FAILURE.  THE STARTER GENERATOR STILL HAD 71.4 HOURS LEFT UNTIL OVERHAUL.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005080400149	20050804	00149	NM  	2005	8	4	CA050718004      	1	20050712	G	3320	9506747	CIRCUIT BOARD   			DHAV  	DHC8  	DHC8301     	1386003	NM  						HAMSTD	14SF	14SF23      	NE  	X312.35	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											OVERNIGHT MX, F/A STATED A NUMBER OF PAX CALL BUTTON LIGHTS COULD NOT BE RESET.  DURING CHECK DISCOVERED ALL OF PAX SERV	ICE UNITS CONTROL CIRCUIT BOARDS HAD BEEN HEAT DAMAGED.  INVESTIGATION REVEALED WIRE ON OUTLET SIDE OF ALL OF PSU CONTRO	L CIRCUIT BOARDS HAD CHAFED INSULATION ALLOWING SHORT CIRCUIT TO GROUND AT STN X312.35.  UNCONTROLLED SHORT CIRCUIT RESU	LTED IN OUTLET TRANSISTOR TO BURN OUT ON ALL PSU CONTROL CIRCUIT BOARDS.  ALL CABIN PSU'S WERE REPLACED AND A/C RETURNED	 TO SERVICE.		2	H	7	2 	4T			RT	A13NM   		6	C	P7NE	 
2005080400150	20050804	00150	NE  	2005	8	4	CA050718005      	2	20050704	G	8510	519513	CASE            			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	NR 2 ENGINE	DETERIORATED    	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA								P33489			AIRCRAFT DEPARTED AND DURING CRUISE, THE FLIGHT CREW NOTICED THAT ENGINE NR 2 WAS COVERED IN OIL.  THE PROP WAS FEATHERE	D AND THE ENGINE WAS SHUT DOWN.  THE AIRCRAFT LANDED.  DURING INVESTIGATION, THE MAINTENANCE CREW DISCOVERED THAT THE TH	READS IN THE NOSE CASE FOR THE OIL TRANSFER PLUG WERE DETERIORATED ALLOWING THE TRANSFER PLUG TO LEAK.  THE NOSE CASE AS	SEMBLY WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	4 	4R	4	R		6A4     	E264	6	C	P871	 
2005080400151	20050804	00151	WP  	2005	8	4	CA050718006      	2	20050712	G	7230	30601293	PLANETARY GEAR  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FAN GEARBOX	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								P111175			(CAN) RT ENGINE CHIP CAS MESSAGE ILLUMINATED ON TAKEOFF.  THE TAKEOFF WAS ABORTED WITHOUT INCIDENT.  INVESTIGATION REVEA	LED THE METAL PICKED UP BY THE CHIP DETECTOR WAS COMING FROM THE FAN GEARBOX ASS'Y.  WHILE DISASSEMBLING THE PLANETARY G	EAR ONE OF THE GEARSHAFT WAS FOUND SHEARED OFF AS PER REASON IN SERVICE BULLETIN TFE 731-72-5181.  THE SERVICE BULLETIN 	WAS COMPLIED WITH THE INSTALLATION OF A NEW SET OF PLANETARY GEAR P/N 3060129-7.  THE ENGINE GROUND RUN AND VIBRATION SU	RVEY WERE COMPLETED SUCCESSFULLY AND THE AIRCRAFT WAS RETURN TO SERVICE.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005080400152	20050804	00152	SW  	2005	8	4	CA050718007      	1	20050707	G	6330	206040532101	MOUNT           			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TRANSMISSION	UNSERVICEABLE   	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											PILOT REPORTED OF AN UNUSUAL VIBRATION THROUGH THE AIRFRAME AFTER SHUTDOWN.  A/C INSPECTED AND FOUND ONE SPHERICAL BEARI	NG HAD LOST ITS STAKING AND WAS FREE TO MOVE.  RESTRAINT REPLACED AND A/C RETURNED TO SERVICE					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400153	20050804	00153	NM  	2005	8	4	CA050718008      	1	20050712	G	2612	894120	FIRE LOOP       			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CL	CLIMB          	1			CA											DURING CLIMB AT FL120, NR 3 ENGINE FIRE WARNING LIGHT ILLUMINATED AND ASSOCIATED WARNING HORN SOUNDED INTERMITTENTLY.  C	REW FOLLOWED ENGINE FIRE EMERGENCY CHECKLIST SECURED ENGINE AND FIRE EXTINGUISHER BOTTLES WERE ACTIVATED.  ENGINE FIRE I	NDICATION REMAINED, CREW DECLARED AN EMERGENCY RETURNING TO DEPARTURE STATION YWG.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2005080400154	20050804	00154	SW  	2005	8	4	CA050718009      	1	20050711	G	5302	206031329103	INTERCOSTAL     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING INSPECTION, INTERCOSTAL FOUND CRACKED ON BOTH LEGS.  TAILBOOM REMOVED.  AFT BULKHEAD FRAME FOUND CRACKED ABOVE BO	LT HOLE.  DAMAGE AT UPPER LEFT FITTING OF TAILBOOM ATTACH BOLTS.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400165	20050804	00165	SO  	2005	8	4	CA050718010      	1	20050705	G	2121	475213	MOTOR           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					E/E BAY FAN	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			10764								(CAN) DURING THE CLIMB, POWER WAS REDUCED AND AN ODOR WAS DETECTED RESEMBLING BURNING ELECTRICAL COMPONENTS.  ALL ELECTR	ICAL WAS SHUT OFF AND ODOR DISAPPEARED, THE PILOT IMMEDIATELY RETURNED TO THE RUNWAY.  THE WEATHER WAS DAY VFR.  NO AD'S	 OR SERVICE BULLETINS WERE APPLICABLE TO THIS COMPONENT.  THE ONLY WAY TO AVOID THIS RE-OCCURRENCE IS TO PLACE A LIFE LI	MIT ON THIS COMPONENT.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2005080400182	20050804	00182	CE  	2005	8	4	CA050718011      	1	20050701	G	5610	1013840252	WINDSCREEN      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											CAPTAIN'S WINDSCREEN CRACKED WHILE AT CRUISE AT 19,000 FT, THE AIRCRAFT CHECK LIST WAS FOLLOWED AND CABIN PRESSURIZATION	 WAS REDUCED.  THE AIRCRAFT WAS RETURNED TO THE BASE WITHOUT FURTHER INCIDENT. THE SUSPECT WINDSCREEN WAS REPLACED AND A	IRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005080400183	20050804	00183	SW  	2005	8	4	CA050718012      	1	20050709	G	7603	C807382	THROTTLE CABLE  			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	BROKEN          	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA											ON START UP AT THE BASE, THE N1 WENT DIRECTLY TO MAXIMUM RPM.  THE PILOT ATTEMPTED TO SHUT THE ENGINE WITH THE THROTTLE 	CONTROL AND DID NOT GET ANY EFFECT ON THE ENGINE.  THE PILOT CALLED AN AME THAT COULD SHUT THE ENGINE BY ACTIVATING THE 	GAS PRODUCER LINKAGE IN THE ENGINE COMPARTMENT. AFTER INVESTIGATION THE THROTTLE CABLE WAS FOUND BROKEN INSIDE ITS SHELL	.  EXCEPT FOR A SMALL FLATTENING, THE OUTSIDE SHELL DID NOT SHOW ANY DAMAGE AT THE POINT OF RUPTURE OF THE CABLE.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400184	20050804	00184	NE  	2005	8	4	CA050718013      	2	20050712	G	7260		CAGE            			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					NR 4 BEARING	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											THE ENGINE WAS REMOVED FROM THE A/C AFTER TWO CHIP LIGHT EVENTS.  WHILE DISSASSEMBLING, THE ENGINE GEARBOX, A BEARING RO	LLER FELL OUT ON TO THE WORK BENCH.  FURTHER EXAMINATION REVEALED THAT THE CAGE INSIDE THE NR 4 BEARING HAD COMPLETELY S	PLIT IN HALF.				1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2005080400185	20050804	00185	GL  	2005	8	4	CA050719001      	2	20050715	G	7210	6894171	GEARBOX         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			15565					CAG27029			THE PILOT OBSERVED LOW/ERRATIC OIL PRESSURE AND TORQUE INDICATIONS AND EXECUTED A PRECAUTIONARY LANDING.  A LARGE OIL LE	AK WAS FOUND FROM THE EXHAUST STACK (GEARBOX VENT) AND COMPRESSOR VENT ORIFICE.  THE ENGINE GEARBOX WAS FOUND TO HAVE MO	RE OIL THAN NORMAL IN IT.  A PROBLEM WITH THE GEARBOX SCAVENGE OIL SYSTEM WAS SUSPECTED AND THE GEARBOX WAS REPLACED AND	 SENT FOR REPAIR.  NO FURTHER PROBLEMS.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005080400186	20050804	00186	NE  	2005	8	4	CA050719002      	2	20050716	G	7260	3022376	SEAL            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ACC GEARBOX	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											STARTER GENERATOR GEARSHAFT OIL SEAL REPLACED DUE TO EXCESSIVE OIL BLOWN OUT THROUGH GENERATOR COOLING EXHAUST DUCT.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005090700010	20050907	00010	EU  	2005	9	7	CA050719003      	1	20050702	G	6220	332A67145620	BRACKET         		332A31000106	SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					M/R HEAD DEICE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M250					(CAN) THE DEICE EQUIPMENT WAS BEING REMOVED FOR THE SUMMER SEASON,WHEN THIS CRACK WAS DISCOVERED. NO PREVIOUS EVIDENCE W	AS DISCOVERED CONCERNING THIS PART.THIS CRACK WAS DISCOVERED VISUALLY DURING THE REMOVAL.					2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2005080400187	20050804	00187	EA  	2005	8	4	CA050719004      	1	20050425	G	5312	C3FS1241	BULKHEAD        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19178								REAR BULKHEAD AT STN 427 FOUND BADLY CRACKED.						1	H	7	1 	3R	3	R		A815    	E142				 
2005080400188	20050804	00188	NE  	2005	8	4	CA050719005      	2	20050623	G	8530	126743	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											AFTER THE PILOT NOTICED A VIBRATION IN FLIGHT, REDUCED ENGINE RPM AND LANDED.  DISCOVERED THAT THE EXHAUST CASE ROCKER I	N NR 1 CYLINDER WAS COMPLETELY BROKEN.  THE CYLINDER ASSEMBLY WAS REPLACED.					1	H	7	1 	3R	3	R		A815    	E142				 
2005080400189	20050804	00189	SO  	2005	8	4	CA050719006      	1	20050308	G	2410	757391	PULLEY          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					LT ALTERNATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											LT ENGINE ALTERNATOR PULLEY FOUND PARTIALLY BROKEN ON ROUTINE INSPECTION.  PULLEY REPLACED WITH NEW BELT.  AIRCRAFT RETU	RN TO SERVICE.					1	L	7	2 	3O	3	O		A19S0   	E286				 
2005080400190	20050804	00190	NE  	2005	8	4	CA050719007      	1	20050714	G	5310	7620202003126	POST            			SKRSKY	S76   	S76C        	8143008	NE  											CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CENTERLINE POST CRACKED, EMANATING FROM RIVET OUTWARDS.  CENTERLINE POST IS LOCATED IN THE BAGGAGE COMPARTMENT.  IT IS A	 KNOWN AREA FOR CRACKING AND IS ON A SCHEDULED 300 HOUR INSPECTION.					1	G	7	2 	3U			NC	H1NE    					 
2005080500012	20050805	00012		2005	8	5	CA050720001      	4	20050705	G	3410	6226197001	DISPLAY         			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											AFTER DEPARTURE AT ABOUT 30NM, CLIMBING THROUGH FL240 THE CO-PILOT EHSI STARTED FLASHING WITH NUMEROUS FLAGS.  REQUESTED	 A RETURN TO BASE AND LANDED NORMALLY.  MAINTENANCE REPLACED U/S EHSI AND RESUMED TRIP.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2005080500013	20050805	00013	CE  	2005	8	5	CA050720002      	1	20050711	G	7921		MOUNT FLANGE    			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  					OIL COOLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A SCHEDULED MAINTENANCE INSPECTION, THE TECHNICIAN DISCOVERED A CRACK IN THE OIL COOLER ASSEMBLY AT THE WELD WHER	E THE COOLER BODY MEETS THE MOUNTING FLANGE.					1	H	7	1 	3O	3	O		3A21    	E5CE				 
2005080500014	20050805	00014	NE  	2005	8	5	CA050720003      	2	20050704	G	8520		STUD            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE CASE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING AIRCRAFT 100HR INSPECTION, A SMALL CRACK WAS FOUND RUNNING FROM THRU BOLT TO A CYLINDER HOLD DOWN STUD ON REAR HA	LF OF POWER SECTION CASE BETWEEN NR 3 AND NR 4 CYLINDERS.  ENGINE REMOVED FROM SERVICE FOR REPAIRS.					1	H	7	1 	3R	3	R		A806    	5E1				 
2005080500015	20050805	00015	SW  	2005	8	5	CA050720005      	1	20050706	G	6410	206016201131	BLADE           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAIL ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AFTER DISCUSSION WITH A FSR FROM BHTC, LEARNED THAT THE TAIL ROTOR ON THIS AIRCRAFT HAD BEEN DAMAGED IN 2004.  THE TECHN	ICAL LOG OF THE AIRCRAFT DID NOT DEMONSTRATE THAT THE PROPER INSPECTION WAS CARRIED OUT AS PER MM CHAP 5-28.  BHTC CONFI	RMED THAT THE PREVIOUS BLADE DAMAGE WAS CAUSED BY SUDDEN STOPPAGE AND THEY HAD ALSO RECOMMENDED THAT THE TAIL ROTOR BLAD	E, HUB AND BONDED SHAFT BE DESTROYED.  ONLY ONE BLADE WAS REPLACED IN 2004.  GROUNDED THE AIRCRAFT AND FINALIZED THE INS	PECTION AS PER BELL MM CHAP 5-28 AND REPLACED THE BLADE, HUB AND BONDED SHAFT.  THE FREE WHEEL ASSEMBLY WAS OVERHAULED I	N JANUARY 2005.  AIRCRAFT WILL BE RETURNED TO SERVICE AS SOON AS THE PARTS ARE RECEIVED.	1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2005080500016	20050805	00016	NM  	2005	8	5	CA050721001      	1	20050720	G	2432	018550000	BATTERY         			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					MAIN	OVERHEATED      	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) EICAS MSG 'MAIN BATT DISCH' OBSERVED DURING DAILY ROUTINE CHECK. BATTERY FOUND EXTREMELY HOT TO TOUCH.  LIFE TIME 	REMAINING OF THIS COMPONENT UNTIL NEXT SCHEDULED REPLACEMENT WAS 142:47 HOURS.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005090700011	20050907	00011	EU  	2005	9	7	CA050722002      	1	20050623	G	5551		FITTING         			AEROSP	SA316 	SA315B      	8680615	EU  	TMECA 	ARTST3	ARTOUSTE3B  	60003	EU  					HORIZONTAL STAB	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) COMPOSITE HORIZONTAL STABILIZER INSTALLED IN ACCORDANCE WITH STC SR00124LA-D. THE R/H REAR ATTACHMENT LUG WAS FOUN	D TO BE BROKEN COMPLETELY OFF AT THE SPAR ON THE STABILIZER.  IT WAS FOUND WHILE A DAILY INSPECTION WAS BEING PERFORMED 	ON THEAIRCRAFT. WE HAVE INFORMED THE MANUFACTURER WHO HAS ISSUED A SERVICE BULLETIN  05-01.				1	G	7	1 	4U	3	U		H1IN    	E11N				 
2005080500017	20050805	00017	GL  	2005	8	5	CA050722003      	2	20050716	G	7397	NSA931322100	CIRCUIT BREAKER 			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					FUEL PUMP	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											FLIGHT CREW REPORTED, RT OUTER TANK FUEL PUMP NR 1, LOW PRESSURE FAULT.  DURING TROUBLESHOOTING, FOUND CIRCUIT BREAKER F	IN 4QA TRIPPED AND EMITTING BURNT SMELL. CIRCUIT BREAKER WAS REPLACED AND SYSTEM OPS CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2005080900077	20050809	00077	GL  	2005	8	9	CA050722004      	1	20050710	G	7100	30387273	OIL FILTER      			BOMBDR	BD700 	BD7001A10   	1390006	GL  										ENGINE	OUT OF ADJUST   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL AT APROX 60 KTS, THE AMBER ICAS (RT ENG OIL PRESS HIGH) POSTED. THE CREW ABORTED THE TAKEOFF. THE 	RT OIL PRESSURE SWITCH WAS ADJUSTED, OPERATIONAL CHECK  AND LEAK TESTS WERE DONE.  ACFT RTS					2	L	7	2 	4F			RT	T00003NY					 
2005080900081	20050809	00081	EU  	2005	8	9	CA050722005      	1	20050719	G	5101		RADIO           	KING        	069102434   	STBROS	SC7   	SC7SERIES3  	8100512	EU  	GARRTT	TPE331	TPE3312201A 	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NAV/COM	INOPERATIVE     	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						86036					(CAN) RETURNED TO BASE WITH NO WORKING RADIOS. IT WAS RETURNING FROM WERE IT HAD BEEN RAINING HEAVILY WHILE THEY WERE ON	 THE GROUND. IT WAS FOUND THAT SOME MOISTURE HAD MADE ITS WAY FROM AN UNKNOWN LOCATION ABOVE THE RADIOS AND WORKED ITS W	AY DOWN DURING FLIGHT. THE SOUCE OF THE LEAK IS BEING INVESTIGATED AT PRESENT.				1	H	7	2 	3T	4	T	NT	A15EU   	E3WE	6	C	P15EA	 
2005080800114	20050808	00114	CE  	2005	8	8	CA050722006      	1	20050527	G	5720		RUDDER PEDAL    			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											PILOT REPORTED THAT RT PARK BRAKE DOES NOT HOLD WHEN SET.  UPON MAINTENANCE INSPECTION IT WAS DISCOVERED THAT CAPTAINS O	B RUDDER PEDAL INTERCOSTAL MOUNT AT STATION 110.00 WAS CRACKED.  IT WAS REPAIRED AS PER CESSNA SRM SECTION 16-38 FIGURE 	16-25.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005080800115	20050808	00115	NM  	2005	8	8	CA050722007      	1	20050722	G	7920	454422	TUBE            			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					OIL PRESSURE	CHAFED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			30596								AIRCRAFT WAS 20 MINITES OUT WHEN THE NUMBER 3 ENGINE OIL LEVEL STARTED TO DROP.  THE ENGINE OIL LEVEL WAS MONITORED BY T	HE F/E AND THE ENGINE WAS NOT SHUT DOWN.  THE AIRCRAFT LANDED SAFELY WITH NO PROBLEMS AND THE ENGINE WAS SHUT DOWN AFTER	 LANDING. MAINTENANCE INSPECTED THE ENGINE AND FOUND THAT THE OIL PRESSURE LINE HAD CHAFFED THROUGH AND OIL WAS ESCAPING	 FROM A HOLE IN THE LINE. THE LINE APPEARED TO HAVE CHAFFED ON THE ENGINE STARTER DUCT.(65-22446-11). THE AIRCRAFT IS GR	OUNDED UNTIL THE LINE CAN BE REPLACED.		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005080800116	20050808	00116	NM  	2005	8	8	CA050722008      	1	20050719	G	3231	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LT MLG DOOR	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											AFTER TAKEOFF, CREW WAS NOT ABLE TO CLOSE LT MLG DOOR.  LDG RECYCLED, NOT ABLE TO EXTEND LT MLG.  ALTERNATE GEAR EXTENSI	ON PERFORMED.  ACFT RETURN TO BASE.  LT MLG DOOR SEQUENCE VALVE REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005080800117	20050808	00117	NE  	2005	8	8	CA050722009      	2	20050722	G	7250	311074102	SHROUD          	PWA         							PWA   	PT6   	PT6A114A    	52043	NE  					CT SHROUD	DISTORTED       	W				E				ENGINE SHUTDOWN         				D	E	W	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	INADEQUATE Q C            	CR	CRUISE         	1			CA						A00049H3					THE HOT SECTION KIT OF A PT6A-114A ENGINE WAS RECEIVED FOR INVESTIGATION/REPAIR DUE TO SHIFTING OF CT SHROUD SEGMENTS.  	THE CT SHROUD SEGMENT-RETAINING RING WAS OF POST SB 1627 CONFIGURATION AND THE CTSHROUD SEGMENTS (P/N 3053094CL5) PRE SB	1628. QTY. 5 RUB SPOTS WERE NOTED ON THE CT SHROUD SEGMENTS WITH MINOR RUB ON CT BLADES.  THE CT SHROUD SEGMENT RETAININ	G RING WAS FOUND DISTORTED AND DISENGAGED FROM THE RETAINING GROOVE OF CT SHROUD HOUSING.  NO OVER HEATING/BURNING OF HO	TSECTION PARTS NOTED.  THE CMM INSPECTION OF THE CT SHROUD HOUSING WAS DONE AND ROUNDNESS NOTED WITHIN O/H MANUAL LIMIT.	  THIS IS 1ST CASE WHERE POST SB 1627 CT SHROUD SEGMENT RETAINING RING WAS FOUND DISTORTED AND DISENGAGED FROM THE RETAI						3	T			E4EA				 
2005080900086	20050809	00086	WP  	2005	8	9	CA050722010      	2	20050721	G	7260	358272	BEARING         	HONEYWELL   	TPE33111U   	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					GEARBOX	DISINTEGRATED   	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			3376 			P44720C		P44720C			ENG WAS FOUND WITH FAILED HYD GEAR SHAFT BEARING. ENG REMOVED DUE TO AN OIL SAMPLE WEAR CHECK INDICATED MAJOR CARBON STE	EL FINES, ALTHOUGH THIS WAS STILL CONSIDERED A NORMAL SAMPLE.  FOUND FWD HYD PUMP GEAR SHAFT BEARING, HAD EXTREME, EXCES	SIVE RADIAL PLAY.  FORWARD END OF HYD GEAR SHAFT FLOPPING AROUND DUE TO FAILED BEARING.  OUTER RACEWAY APPEARED TO HAVE 	MAJOR SPALLING AND SEVERE GALLING ON RACEWAY SURFACE AROUND ENTIRE DIAMETER.  THE BEARING CAGE HAD CONTACTED RACEWAY AND	 WAS RUBBED.  BEARING WAS INSTALLED NEW AT LAST ENG O/H.  BEARING AND GEARBOX HAVE NOT BEEN OPENED SINCE THAT TIME AS TH	ERE HAS BEEN NO REQUIREMENT TO DO SO UNTIL NOW.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005090700012	20050907	00012	SO  	2005	9	7	CA050722011      	1	20050721	G	5220	40979	DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	EMERGENCY EXIT	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) AT APPROXIMATELY 0022Z ON JULY 21, 2005 THE AIRCRAFT WAS ON DESCENT FROM 8,500 THROUGH 7,500 FEET, WHEN THE EMERGE	NCY EXIT DISENGAGED AND FLEW OFF THE AIRCRAFT.AIRSPEED WAS BETWEEN 175 AND 185 KTS. THERE WAS APPARENTLY NO SOUND PRIOR 	TO TH E DISENGAGEMENT OR AFTER THE DISENGAGEMENT TO INDICATE FUSELAGE OR CONTROL SURFACE IMPACT. THE AIRCRAFT FLEW A STA	BILIZED APPROACH TO RUNWAY 29 AND LANDED UNEVENTFULLY. THERE WAS ONE PASSENGER ON BOARD AT THE TIME. THE EMERGENCY EXIT 	CAME OFF OVER A DENSELY WOODED AREA AND HAS NOT BEEN RETRIEVED. THE AIRCRAFT WAS INSPECTED FOR OTHER INCIDENTAL DAMAGE A	ND NONE WAS FOUND. THE LATCHING MECHANISM WAS INSPECTED AND FOUND TO CONFORM TO CORRECT OPERATION AND RIGGING IAW MANUFA	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	 	 
2005080900087	20050809	00087	EA  	2005	8	9	CA050724001      	2	20050708	G	8520	13E17679	CRANKSHAFT      	LYC         	IO540E1B5   	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					CRANKSHAFT	SHEARED         	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA						L505248C					CRANKSHAFT SPLIT NEXT TO THE NR 3 MAIN BEARING JOURNAL.  FAILURE NEXT TO THE NR 4 CONNECTING ROD.  CRANKSHAFT THEN BROKE	 INTO 3 PIECES AND PUNCTURED THE CRANKCASE ABOVE THE SUMP.  ENGINE TEARDOWN RESULTS: A SCRAP CRANKCASE AND NR 3 CYLINDER	 ALSO SCRAP DUE TO DAMAGE. CAMSHAFT ALSO DAMAGED IN THE FAILURE.				1	H	7	2 	3O	3	O		6A1     	1E4				 
2005080900088	20050809	00088	SO  	2005	8	9	CA050724002      	2	20050722	G	8520	640433	CRANKCASE       	CONT        	IO360G1A    	CESSNA	337   	337B        	2075706	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C301  	GL  	FWD END	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						352103		352103			AFTER LANDING FROM A ROUTINE COMPANY FLIGHT, THE MAINTENANCE ENGINEER NOTED MORE THAN NORMAL OIL ON THE LT REAR COWLING.	  UPON FURTHER INVESTIGATION, A 3 INCH CRACK WAS DETECTED ON THE CRANKCASE HALF STARTING FROM THE ENGINE DRIVEN FUEL PUM	P BOSS TO THE CRANKCASE THRU BOLT.  THE ENGINE IS BEING REMOVED AND SENT TO AUTHORIZED REPAIR SHOP FOR REPAIR.				1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2005080900089	20050809	00089	EA  	2005	8	9	CA050725001      	2	20050723	G	7414	106006163	MAGNETO         	LYC         	O540F1B5    	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			IN	INSP/MAINT     	1			CA						L2531940A		L2531940A			AFTER DOING A NORMAL START AND MAGNETO DROP CHECK, THE A/C WAS IN A 20 FT HOVER PREPARING TO TAKEOFF FROM A REMOTE OIL P	LANT SITE, WHEN A CHANGE IN ENGINE NOISE AND AN INCREASE IN MANIFOLD PRESSURE WAS NOTICED.  THERE WAS NOT ENOUGH ENGINE 	POWER TO SUSTAIN A HOVER AND THE PILOT WAS FORCED TO LAND THE A/C.  DURING GROUND RUN CHECKS, IT WAS NOTICED THAT THE EN	GINE WOULD STALL WHEN THE RT MAG WAS SELECTED.  BOTH MAGS WERE REPLACED AND THE A/C RETURNED TO SERVICE.  THE SUSPECT MA	GS ARE BEING SENT FOR OVERHAUL.		1	G	7	1 	3O	3	O		H11NM   	E295				 
2005090700013	20050907	00013	SW  	2005	9	7	CA050725002      	1	20050724	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN ROTOR BLADES P/N 206-010-200-133 S/N A6716 AND A6778 WILL NOT FLY LOWEST IPS WAS 1.7 WITH MAXIMUM TABING. THE	SE ARE NEW BLADES WITH AN APPARENT MANUFACTURING DEFECT.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005090700014	20050907	00014	WP  	2005	9	7	CA050725003      	2	20050720	G	7210	8679225	CARRIER ASSY    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					PLANETARY GEAR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			24694					P54117			(CAN) DURING ENGINE TREND RECORDING BY THE FLIGHT CREW IT WAS NOTICED THAT THE LH ENGINE OIL PRESSURE INDICTION HAD DECR	EASED 15 PSI WITHIN A WEEK OF OPERATION. UPON ARRIVAL MAINTENACE WAS ADVISED AND ELECTED TO REMOVE THE ENGINE FOR INSPEC	TION. UPON INSPECTION OF THE PLANETARY CARRIER ASSY IT WAS OBVIOUSLY FRACTURED AND PIECES OF THE OIL DISTRIBUTION GALLER	IES MISSING. EXCESSIVE WEAR ON THE PLANETARY GEARS WAS ALSO EVIDENT. THE ENGINE WAS REPLACED. THIS CARRIER HAD 381 HRS S	INCE OVERHAUL AND WAS INSPECTED USING LPI PRIOR TO INSTALLATION ONTO THE ENGINE, NO CRACKS WERE DETECTED. THIS IS THE SI	XTH PLANETARY CARRIER FAILURE SUFFERED BY THIS OPERATOR.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005080400003	20050804	00003	EA  	2005	8	4	CA050725004      	2	20050719	G	7321	324475518	FUEL CONTROL    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA								PCE80590			(CAN) ON A VFR FLIGHT, THE FLIGHT CREW ATTEMPTED TO REDUCE POWER FOR THE APPROACH INTO AIRFIELD.  THERE WAS NO ENGINE RE	SPONSE WITH REDUCTION IN POWER SETTINGS.  THE CREW THEN TRIED TO CAREFULLY INCREASE POWER SETTING FROM CRUISE POWER (180	0 LBS) TO 1900 LBS.  THIS SETTING CHANGE WAS SUCCESSFUL BUT THE FOLLOWING REDUCTION IN POWER WAS UNSUCCESSFUL.  THE CREW	 THEN DECIDED TO SHUT DOWN THE AFFECTED ENGINE AND LANDED THE AIRCRAFT SAFELY.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005080400026	20050804	00026	NE  	2005	8	4	CA050725005      	2	20050701	G	7200		ENGINE          			AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A34AG    	52053	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								14025			(CAN) THE ENGINE REPORTEDLY LOST POWER DURING TAKEOFF WITH SUBSEQUENT DAMAGE TO THE AIRCRAFT.  THE ENGINE HAD BEEN CONVE	RTED FROM A PT6A-15AG TO A PT6A-34AG UNDER AIRFORCE TURBINE SERVICES STC SE7677SW.  P&WC WILL MONITOR INVESTIGATION OF T	HE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	L	7	1 	3T	4	T	NC	A17SW   	E4EA				 
2005080400027	20050804	00027	NE  	2005	8	4	CA050725006      	2	20050620	G	7210		HOUSING         			AEROSP	ATR72 	ATR72202    	8680940	EU  	PWA   	PW120 	PW124B      	 	NE  					REDUCTION G/B	CORRODED        	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								AH0011			(CAN) DURING CRUISE, ENGINE OIL PRESSURE DECREASED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEAL	ED CORROSION OF THE REDUCTION GEARBOX HOUSING AT THE PCU TRANSFER TUBE LOCATION.					2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2005090200111	20050902	00111	WP  	2005	9	2	CA050725007      	2	20050721	G	7321	89356117	FCU             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					LT ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) UPON LANDING AND SHUTDOWN OF THE LT ENGINE IT WAS NOTICED THAT THE OVERBOARD ENGINE DRAIN FOR THE FUEL CONTROL UNI	T WAS LEAKING FUEL. THE FUEL CONTROL WAS REPLACED. THE LAST TIME THIS FCU WAS REPAIRED IT WAS FOR THE SAME FUEL LEAK PRO	BLEM IN MARCH OF 2001.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005080400028	20050804	00028	NE  	2005	8	4	CA050725008      	2	20050705	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW120 	PW127       	 	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								AM0019			(CAN) DURING CRUISE IN SEVERE RAIN STORMS, THE ENGINE FLAMED OUT.  THE AUTOMATIC RE-LIGHT SYSTEM SUCCESSFULLY RESTARTED 	THE ENGINE WITHIN 12 SECONDS.  POST FLIGHT GROUND CHECKS FOUND NO ANOMALIES AND THE AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005080400029	20050804	00029	NE  	2005	8	4	CA050725009      	2	20050705	G	7200		ENGINE          			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								RD0006			(CAN) DURING FIRE-FIGHTING OPERATIONS, THE AIRCRAFT FLEW THROUGH A COLUMN OF SMOKE AND THE ENGINE REPORTEDLY LOST POWER.	  THE AIRCRAFT MADE AN EMERGENCY LANDING AND WAS SUBSEQUENTLY CONSUMED BY FIRE.  PWC WILL MONITOR THE INVESTIGATION AND 	ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2005080400030	20050804	00030	NE  	2005	8	4	CA050725010      	2	20050705	G	7250		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PS0041			(CAN) ON TAKEOFF, THE ENGINE EMITTED A LOUD BANG AND LOST POWER.  THE TAKEOFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEAL	ED TURBINE DISTRESS.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005080400031	20050804	00031	NE  	2005	8	4	CA050725011      	2	20050607	G	7230		TURBINE BLADES  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			C	J		F.O.D.                    	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE SUFFERED AN IN-FLIGHT SHUT-DOWN RESULTING IN A FORCED LANDING.  SUBSEQUENT INSPECTION FOUND BIRD REMAIN	S IN THE ENGINE INLET AND HIGH PRESSURE COMPRESSOR.  FURTHER INSPECTION REVEALED A FRACTURED COMPRESSOR TURBINE BLADE.  	P&WC WILL INVESTIGATE THE BLADE FRACTURE AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005080400032	20050804	00032	EU  	2005	8	4	CA050725012      	1	20050630	G	6123	30048000018	AUTOFEATHER SYS 			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  					PROPELLER	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE AIRCRAFT YAWED, ACCOMPANIED BY AN ENGINE TORQUE INDICTION OF ZERO.  THE CREW SHUT THE ENGINE DOW	N IN FLIGHT.  THE ENGINE WAS THEN SUCCESSFULLY RE-STARTED.  THE AUTOFEATHER UNIT WAS SUBSEQUENTLY REPLACED AND AIRCRAFT 	RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005080400033	20050804	00033	NE  	2005	8	4	CA050725013      	2	20050706	G	7310		MANIFOLD        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					FUEL SYSTEM	PUNCTURED       	W				A				UNSCHED LANDING         				K	A	J	FLUID LOSS                	FLAME/FIRE                	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ENGINE FIRE WARNING ANNUNCIATED.  ENGINE THRUST WAS SELECTED TO IDLE, AN EMERGENCY DECLARED AND 	AN UNSCHEDULED LANDING PERFORMED AT POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A PUNCTURED ENGINE FUEL MANIFOLD	, EVIDENCE OF AN ENGINE FIRE AND A RESULTANT HOLE IN THE NACELLE.  P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF	 ROOT CAUSE ONCE DETERMINED.			2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005080400034	20050804	00034	NE  	2005	8	4	CA050725014      	2	20050709	G	7200		ENGINE          			AGUSTA	A109  	A109E       	0260119	EU  	PWC   	PW206C	PW206C      		NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								BC0429			(CAN) THE ENGINE WAS REPORTED TO EMIT A NOISE ACCOMPANIED BY A CHIP DETECTOR INDICATION.  THE ENGINE WAS SHUT DOWN IN FL	IGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED MAGNETIC DEBRIS IN THE ENGINE.  P&	WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
2005080400051	20050804	00051	NE  	2005	8	4	CA050725015      	2	20050708	G	7321	81850010	FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE ENGINE FLAMED OUT.  SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL UNIT FUEL PUMP DRIVE 	SHAFT.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005080400129	20050804	00129	NE  	2005	8	4	CA050725016      	2	20050703	G	7200		ENGINE          			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  						VIBRATION       	W				A				UNSCHED LANDING         				E	A		VIBRATION/BUFFET          	FLAME/FIRE                		NR	NOT REPORTED   	1			CA								106036			THE ENGINE WAS REPORTED TO EMIT FLAMES ACCOMPANIED BY VIBRATION AND LOUD NOISES.  AN EMERGENCY LANDING WAS PERFORMED ON 	A DIRT ROAD.  P&WC WILL INVESTIGATE THE EVENT TO ESTABLISH ROOT CAUSE.					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2005080400130	20050804	00130	EA  	2005	8	4	CA050725017      	1	20050715	G	2913	661903	PUMP            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											SHORTLY AFTER TAKEOFF, THE CREW REPORTED HAVING HYD NR 1 LOW PRESS CAUTION MESSAGE.  QUANTITY OF THE HYDRAULIC RESERVOIR	 WAS DROPPING FAST.  CREW COMPLIED WITH THE QRH AND RETURNED TO THE BASE.  FOUND HYDRAULIC LEAKING FROM THE HYD EDP AT T	HE PORT CAP.  EDP WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005080400131	20050804	00131	NE  	2005	8	4	CA050725018      	2	20050708	G	7200		ENGINE          			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  						FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											THE ENGINE LOST TORQUE AND OIL PRESSURE DURING A SPRAYING RUN (AT 50 FT ALTITUDE).  THE PILOT FEATHERED THE PROPELLER AN	D COMPLETED A FORCED LANDING WITH RESULTANT AIRFRAME AND PROPELLER DAMAGE.  PWC WILL MONITOR INVESTIGATION OF THE INCIDE	NT TO ESTABLISH ROOT CAUSE.				1	L	7	1 	3T	4	T		A3SW    	E4EA				 
2005080400132	20050804	00132	EA  	2005	8	4	CA050725019      	2	20050712	G	7260		SEAL            			DHAV  	DHC7  	DHC7100     	2802404	EA  	PWA   	PT6   	PT6A50      	52043	EA  					ACC GEARBOX	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING CRUISE, OIL PRESSURE FLUCTUATED AND DECREASED.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED.  GR	OUND INSPECTION REVEALED A LEAKING HYDRAULIC PUMP PAD ACCESSORY GEARBOX SEAL.					2	H	7	4 	4T	4	T		A20EA   	E4EA				 
2005080400133	20050804	00133	NE  	2005	8	4	CA050725020      	2	20050718	G	7532		BLEED VALVE     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA								PS0176			DURING A RAPID DESCENT, THE ENGINE SURGED ACCOMPANIED BY TORQUE FLUCTUATIONS.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND TH	E AIRCRAFT PROCEEDED TO DESTINATION.  SUBSEQUENT INVESTIGATION WAS UNABLE TO REPRODUCE THE PROBLEM.  THE ENGINE BLEED VA	LVE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005080400134	20050804	00134	EU  	2005	8	4	CA050726001      	1	20050723	G	3246		BOLT            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					MLG WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						4293					(CAN) DURING TRANSIT CHECK INSPECTION, FOUND NR 2 MAIN WHEEL WITH 2 EA BROKEN TIE BOLTS.  THE MAIN WHEEL ASSEMBLY WAS RE	PLACED.  DURING REPLACEMENT OF THE WHEEL ASSEMBLY, FOUND THE BRAKE DAMAGE BY THE BROKEN TIEBOLTS.  THE BRAKE ASSEMBLY WA	S ALSO REPLACED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2005080900065	20050809	00065	EA  	2005	8	9	CA050726002      	2	20050720	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			13617								(CAN) DAMAGE OCCURRED TO PLATING OF FWD SEALING DIAMETER OF BETA CNTRL OIL TRANSFER SLEEVE. DIAMETER INDICATED BOND OF P	LATING TO PARENT MATERIAL OF SLEEVE WAS STILL GOOD, WAS SCORING FROM FOD.  EXTRUSION OF PLATE FWD FROM DIAMETER, INDICAT	ION PIECES HAD SEPARATED. PROPSHAFT HAD SCORING OF MATING DIAMETER. AXIAL EXTENT OF SCORING COVERS MOVEMENT OF TRANSFER 	SLEEVE ALONG PROPSHAFT.  PIECE OF PLATING HAD BECOME DETACHED FROM EDGE OF SMALL HOLES, EXTRUDING FROM SEALING DIAMETER 	OF BETA CNTRL OIL TRANSFER SLEEVE, HAD CLEARLY BROKEN AWAY.  MAGNETIZATION OF PROP SHAFT WITH DAMAGE TO BETA CNTRL DIAME	TERS IS THOUGHT TO BE RESULT OF FRICTIONAL CONTACT BETWEEN SLEEVE AND SHAFT.  PROPSHAFT COULD HAVE BECOME UNREPAIRABLE.						4	T			E4EA				 
2005080400135	20050804	00135	EA  	2005	8	4	CA050726004      	2	20050724	G	7240	3027408	CASE            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					GAS GENERATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48524					PCE41733			DURING A SCHEDULED HOT SECTION INSPECTION, A CRACK WAS FOUND IN THE CASE WHERE THE FUEL NOZZLE SUPPORT IS LOCATED AT THE	 FIVE O`CLOCK POSITION.  THE CRACK WAS RUNNING FROM THE EDGE OF THE NOZZLE DOUBLER PLATE TOWARDS THE RT IGNITER WELD.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005090700015	20050907	00015	GL  	2005	9	7	CA050726005      	3	20050724	G	6114	B3339	BOLT            	HARTZL      		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									FWA3145		(CAN) DURING AN INSPECTION OF THE BOLTS ACCORDING TO AD2005-14-12 ALL OF THE BOLTS FAILED THE TEST TORQUE.THE BOLTS WERE	 ALL OF BATCH NUMBER 56.THIS IS ONE OF THEBATCHES THAT IS REQUIRED TO BE REPLACED BY THE AD.THE BOLTS WERE REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005080400138	20050804	00138	EA  	2005	8	4	CA050726006      	1	20050725	G	2497	601R576401PE	WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 GENERATOR	BURNED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA											DURING CLIMB, IDG NR 2 DROPPED OFF LINE.  MAINTENANCE FOUND THE GENERATOR NR 2 CABLE AND TERMINAL BURNT IN JB1.  THE TER	MINAL ATTACHMENT HARDWARE WAS FOUND LOOSE ON THE TERMINAL BLOCK STUD INSIDE THE JB1.  DAMAGED PARTS, ELECTRICAL HARNESS,	 601R57640-1PE- PHENOLIC INSULATOR,  600-51428-3- BUS BAR,601R51427-3 - STUD, MS25080-4				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005080400155	20050804	00155	EA  	2005	8	4	CA050726007      	1	20050724	G	5410	22850142601	COWL DOOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 ENGINE	MISSING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			NR	NOT REPORTED   	1			CA											AIRCRAFT DIVERTED AFTER DEPARTURE, FOR NR 1 ENGINE OIL PRESSURE INDICATION PROBLEM.  UPON ARRIVAL AT GATE FOUND UPPER HA	LF OF LT CORE COWL MISSING.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005080400156	20050804	00156	NE  	2005	8	4	CA050727001      	2	20050727	G	7200		ENGINE          								GE    	CFM56 	CFM565A     	13802	NE  					NR 2	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											DURING TAKEOFF ROLL, ENG NR 2 FAILED.  TAKEOFF REJECTED.  RAISED, ENGINE CHANGE IN PROGRESS (YOW).											4	F			E29NE				 
2005080400157	20050804	00157	EU  	2005	8	4	CA050727002      	1	20050727	G	2720	PNSC4710	YAW DAMPER      			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					RUDDER	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											IN CRUISE, YELLOW HYD SYSTEM LEAK TURNED OFF ENG GREEN PUMPS 1 & 2.  NO NOSE STEERING ON LANDING.  FOUND HYD LEAK IN THS	 COMPT YAW DAMPER ACTUATOR 19CS1.  REPLACED AS PER J/C 9-227L-01.					2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2005080400158	20050804	00158	WP  	2005	8	4	CA050727004      	1	20050726	G	3234		SELECTOR        			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											ON APPROACH TO AIRPORT, THE THREE (3) MLG DOWN GREEN LIGHT DID NOT ILLUMINATE AFTER GEAR EXTENSION, THE HORN DID NOT SOU	ND AND THE RED GEAR UNSAFE LIGHT EXTINGUISHED.  MAINTENANCE WAS UNABLE TO DUPLICATE THE SNAG ON GROUND, THE (LANDING) GE	AR LEVER SWITCH WAS TESTED AND INSPECTED, PEDESTAL LIGHT INDICATION WAS TESTED AND INSPECTED, SAME FOR THE DIMMING RELAY	 AND THE RESISTORS.  SUSPECT DIMMING SWITCH WAS AT DIM POSITION.  THE LDG DWN LOCK IND C/B WAS REPLACED IN CASE OF INTER	MITTENT CONTINUITY.  AIRCRAFT RETURN TO SERVICE		2	L	7	2 	4R	4	T		6A6     	E282				 
2005080400159	20050804	00159	NM  	2005	8	4	CA050727005      	1	20050723	G	2597		WIRE            			BOEING	757   	757200      	1384950	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					GALLEY	DAMAGED         	W				H				DEACTIVATE SYST/CIRCUITS				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA											(CAN) DURING T/S OF INBOUND DEFECTS (PA INOP, NSSB INTERMITTENT) FOUND C/B`S POPPED.  RESET SAME (ONE WOULD RESET, OTHER	 NOT).  FOUND WIRE LOOM (W3702) FOR UNINSTALLED PSU (9ABC) PINCHED BETWEEN AFT WALL SURFACE OF MID GALLEY AND STRUCTURE 	OF A/C.  GALLEY INSTALLATION PREDATED HMY'S OWNERSHIP OF A/C, HOWEVER, GALLEY WAS REMOVED DURING C4 CHECK PRIOR TO HMY T	AKING DELIVERY OF A/C IN 2002.  MOVEMENT BETWEEN A/C STRUCTURE AND GALLEY BACK WALL CAUSED CHAFING OF WIRE LOOM, AND DEF	ECTS AS NOTED.  DEFECTS CAUSED BY SEVERING OF SEVERAL WIRES, SHORTING TOGETHER AND TO STRUCTURE.  SMOLDER/SMOKE AND ODOR	 OCCURRED DURING T/S. WIRING REPAIRED PER SWPM, GALLEY BACK WALL CUTOUT INCREASED, AND WIRING REPOSITIONED. GALLEY REINS	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005080400160	20050804	00160	EU  	2005	8	4	CA050727006      	2	20050726	G	7314		SHAFT           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					FUEL PUMP	SHEARED         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											DEPARTING DEWAR LAKE(300NM NORTH OF YFB) FOR YFB, THE NR 2 ENGINE SPOOLED DOWN ON TAKEOFF.  THE AIRCRAFT RETURNED TO POI	NT OF DEPARTURE AND LANDED SAFELY. MAINTENANCE DETERMINED THE NR 2 ENGINE DRIVEN FUEL PUMP INPUT SHAFT HAD SHEARED.  THE	 PUMP WAS REPLACED AND THE ENGINE GROUND RUN AND DECLARED SERVICEABLE.				2	L	7	2 	3T	4	T		A24EU   	A196				 
2005090700016	20050907	00016	CE  	2005	9	7	CA050727007      	1	20050726	G	5751	991300009	SKIN            	BEECH       		BEECH 	100   	B100        	1152919	CE  										AILERON	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						LW196					(CAN) CORROSION WAS FOUND ON THE LEFT HAND AILERON UNDER THE STATIC WICKS. THE AILERO N WAS REMOVED AND DISASSEMBLED. AF	TER REMOVING THE UPPER SKIN, IT WAS DISCOVEREDTHAT THE UPPER AND LOWER SKINS WERE CRACKED IN MULTIPLE LOCATIONS, JUST AF	T OFTHE JOINT WHERE THE NOSE SKIN OVER LAPS THE AFT SKIN. RAYTHEON HAS PUBLISHED A S.B. TO INSPECT THE RIGHT HAND AILERO	N FOR CRACKS IN THE SAME LOCATION,BUT NOT FOR THE LT AILERON.			1	L	7	2 	4T				A14CE   					 
2005090700017	20050907	00017	CE  	2005	9	7	CA050727008      	1	20050725	G	5751	991300009	SKIN            	BEECH       		BEECH 	100   	B100        	1152919	CE  										AILERON	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						LW196					(CAN) CORROSION WAS FOUND ON THE LEFT HAND AILERON UNDER THE STATIC WICKS. THE AILERO N WAS REMOVED AND DISASSEMBLED. AF	TER REMOVING THE UPPER SKIN, IT WAS DISCOVEREDTHAT THE UPPER AND LOWER SKINS WERE CRACKED IN MULTIPLE LOCATIONS, JUST AF	T OFTHE JOINT WHERE THE NOSE SKIN OVER LAPS THE AFT SKIN. RAYTHEON HAS PUBLISHED A S.B. (SB57-3148) TO INSPECT THE RIGHT	 HAND AILERON FOR CRACKS IN THE SAME LOCATION,BUT NOT FOR THE LEFT AILERON.			1	L	7	2 	4T				A14CE   					 
2005090700018	20050907	00018	CE  	2005	9	7	CA050727009      	1	20050725	G	5751	991300009	SKIN            	BEECH       		BEECH 	100   	B100        	1152919	CE  										AILERON	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						LW196					(CAN) CORROSION WAS FOUND ON THE LEFT HAND AILERON UNDER THE STATIC WICKS. THE AILERO N WAS REMOVED AND DISASSEMBLED. AF	TER REMOVING THE UPPER SKIN, IT WAS DISCOVEREDTHAT THE UPPER AND LOWER SKINS WERE CRACKED IN MULTIPLE LOCATIONS, JUST AF	T OFTHE JOINT WHERE THE NOSE SKIN OVER LAPS THE AFT SKIN. RAYTHEON HAS PUBLISHED A S.B. (SB57-3148) TO INSPECT THE RIGHT	 HAND AILERON FOR CRACKS IN THE SAME LOCATION,BUT NOT FOR THE LEFT AILERON.			1	L	7	2 	4T				A14CE   					 
2005080400161	20050804	00161	NM  	2005	8	4	CA050728002      	1	20050726	G	3241	42881	CONTROL UNIT    			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ANTI SKID	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											AN AIRCRAFT EXPERIENCE LT MLG NR 1 TIRE BURST ON LANDING, THEN THE LT MLG NR 2 TIRE BURST DURING TAXI. MAINTENANCE REPLA	CED LT MLG WHEELS REPLACED, ASCU AND LT GEAR A/S CONTROL VALVE.  PERFORMED A/S SYSTEM TEST.  AIRCRAFT RTS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005080400162	20050804	00162	EA  	2005	8	4	CA050728003      	1	20050718	G	2435	02560013	FRICTION RING   	LUCAS       		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					STARTER GEN	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						4818					DURING INSPECTION, THE FAN WAS FOUND TO HAVE MOVED AFT CONTACTING THE FAN HOUSING.  BOTH THE FAN AND HOUSING WERE DAMAGE	D.  THE FRICTION RING AT THE FWD END OF THE SHAFT WAS FOUND COMPLETELY WORN OUT.  SUSPECT MIS-ALIGNMENT OF THE GENERATOR	 INSTALLATION CAUSING THE FRICTION RING TO WEAR PREMATURELY AND ALLOWING THE SHAFT TO MOVE AFT AND ALLOW THE FAN TO CONT	ACT THE HOUSING.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005080400166	20050804	00166	NE  	2005	8	4	CA050728004      	2	20050720	G	8530	399353	CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											DURING CRUISE FLIGHT, THE PILOT EXPERIENCED AN ENGINE VIBRATION.SUSPECTING A CYLINDER FAILURE, RETURNED TO BASE.  TEMPS 	AND PRESSURES REMAINED NORMAL THROUGHOUT THE RETURN.  MAINTENANCE INVESTIGATION REVEALED THAT THE NR 1 CYLINDER HEAD HAD	 SEPARATED FROM THE BARREL. THE CYLINDER ASSY WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	1 	3R	3	R		A806    	5E1				 
2005091500109	20050915	00109	EA  	2005	9	15	CA050728005      	1	20050727	G	3246	C2UF2291	MECHANISM       	EDOXXXXXXXXX		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	WIRE PULL	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA						TB304					(CAN) THE AIRCRAFT LANDED IN ROUGH WATER THE UPPER RT WIRE PULL P/N C2UF2291 FAILED.						1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206	 
2005091500110	20050915	00110	EA  	2005	9	15	CA050728006      	1	20050722	G	3246	585926R	FITTING         	EDOXXXXXXXXX	584580      	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTERGRANULAR CORROSION AT FORWARD FLOAT STRUT FITTING P/N 585926R FOUND DURING A 400 HOUR INSPECTION.						1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206	 
2005080400191	20050804	00191		2005	8	4	CA050728007      	4	20050725	G	2330	50401100003	DISPLAY         			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 11A	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											A/C WAS IN CRUISE WHEN THE CREW WERE ADVISED THAT THE VDU AT SEAT 11A HAD QUIT WORKING AND THAT IT SMELLED LIKE BURNING 	WIRE.  THERE WAS NO SMOKE OR ARCING OBSERVED.  THE IFE SYSTEM WAS TURNED OFF AT THIS POINT.  MAINTENANCE REPLACED THE VD	U AND CHECKED THE SYSTEM TO BE SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEAR DOW	N REPORT WILL BE REQUESTED.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005080400192	20050804	00192	EA  	2005	8	4	CA050728008      	1	20050722	G	6120	KX511	SWITCH          			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP CONTROL	FAILED          	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											DURING CLIMB-OUT, THE FLT CREW EXPERIENCED NR 2 ENGINE AND PROP SURGING.  ENG POWER WAS REDUCED, AND PROPS ADJUSTED TO M	IN GOVERNING.  IN THIS CONFIGURATION THE SURGING WAS NOT PRESENT.  FLIGHT CREW DIVERTED TO A MAINTENANCE BASE AND LANDED	 UNEVENTFULLY WITHOUT THE USE OF REVERSE.  WATER TAXI TO THE DOCK AND DOCKING WERE COMPLETED UNEVENTFULLY.  MAINTENANCE 	INVESTIGATION REVEALED THAT THE BETA MICRO-SWITCH HAD AN INTERMITTENT FAILURE WHICH HAD CAUSED THE ENGINE TO SURGE INITI	ALLY. THE SWITCH WAS REPLACED WITH NO FURTHER PROBLEMS. TIME ON THE SWITCH IS NOT AVAILABLE, BUT THESE SWITCHES HAVE BEE	N FOUND TO BE UNRELIABLE IF NOT HANDLED APPROPRIATELY.  (SLIGHT OVERTIGHTENING WILL CAUSE THE SWITCH TO FAIL READILY).	1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005080400193	20050804	00193	EA  	2005	8	4	CA050728009      	1	20050717	G	7603		LEVER           			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	THROTTLE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											AIRCRAFT LANDED, WHILE FOLLOWING MARSHALLER'S HAND SIGNALS ONTO THE FBO RAMP, THE THROTTLE WAS ADVANCED TO COMPLETE TURN	.  WHEN THE THROTTLE WAS ADVANCED IT WAS UNRESPONSIVE ON TWO FULL MOVEMENTS.  THE AIRCRAFT WAS SHUT DOWN WITH THE MIXTUR	E.  A QUALIFIED AME INSPECTED THE POWER QUADRANT AND OBSERVED THAT THROTTLE CABLE WAS DISCONNECTED AT THE QUADRANT.  FUR	THER INSPECTION REVEALED THAT THE NUT WAS NOT SAFETIED.  PICTURES WERE TAKEN AND THE NUT WAS SAFETIED AND WITNESSED BY T	WO AME'S.		1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206	 
2005080400194	20050804	00194	EA  	2005	8	4	CA050728010      	2	20050724	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						SHUTDOWN        	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								60406			THE ENGINE EXPERIENCED A POWER LOSS IN CRUISE.  THE POWER SECTION WAS SHUT DOWN IN FLIGHT.  P&WC WILL INVESTIGATE THE EV	ENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005080400195	20050804	00195	EA  	2005	8	4	CA050728011      	2	20050722	G	7230		ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		POWER LOSS      	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								57152			THE ENGINE WAS REPORTED AS UNABLE TO ACHIEVE REQUIRED TORQUE ON TAKEOFF AND THE TAKEOFF WAS ABORTED.  SUBSEQUENT INVESTI	GATION WAS REPORTED TO REVEAL COMPRESS OR DAMAGE.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE	 ONCE DETERMINED.				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA	6	C	P15EA	 
2005090600017	20050906	00017	CE  	2005	9	6	CA050729001      	1	20050728	G	5510	3565000525	RIB             			BEECH 	35    	N35         	1151528	CE  	CONT  	O470  	IO470N      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT STABILIZER END RIB FOUND TO HAVE INTERGRANULAR CORROSION WHERE IT ATTACHED TO THE FORWARD RIB.  CORROSION IS ON	 THE UPPER INSIDE CORNER OF THE RIB AND ONLY CAN BE VIEWED USING SMALL MIRROR THRU THE LIGHTENING HOLE OF THIS RIB JUST 	IB OF THE RUDDERVATOR BALANCE WEIGHT.				1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
2005090600018	20050906	00018	CE  	2005	9	6	CA050729002      	1	20050728	G	5510	3565000525	RIB             			BEECH 	35    	N35         	1151528	CE  	CONT  	O470  	IO470N      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	STABILIZER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT STABILIZER END RIB FOUND TO HAVE INTERGRANULAR CORROSION WHERE IT ATTACHED TO THE FORWARD RIB.  CORROSION IS ON	 THE UPPER INSIDE CORNER OF THE RIB AND ONLY CAN BE VIEWED USING SMALL MIRROR THRU THE LIGHTENING HOLE OF THIS RIB JUST 	IB OF THE RUDDERVATOR BALANCE WEIGHT.				1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
2005100600072	20051006	00072	SO  	2005	10	6	CA050729003      	2	20050722	G	7314	RG9080	PUMP            			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					FUEL SYSTEM	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											DURING INSPECTION RUN-UP, THE FUEL PRESSURE DROPPED TO 3 PSI AT IDLE (NORMAL PRESSURE IS 12 PSI). THE ENGINE HAD DIFFICU	LTY RUNNING.  THE PART WAS REMOVED AND RETURNED TO THE OVERHAUL FACILITY FOR WARRANTY WORK.					1	H	7	1 	3O	3	O		5A5     	E269				 
2005080400196	20050804	00196	EA  	2005	8	4	CA050801001      	1	20050707	G	7500	C6VE10081	DUCT            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BLEED AIR	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											WHEN TROUBLESHOOTING A HIGH ENGINE TEMPERATURE PROBLEM, IT WAS DISCOVERED THAT THE BLEED AIR DUCT COMING OFF THAT ENGINE	 WAS LEAKING THROUGH A CRACK IN THE FLEXIBLE BELLOWS SECTION OF THE DUCT, WHICH IS NOT VISIBLE UNDER THE DUCT'S SHIELD. 	 THE CRACK WAS DETECTABLE ONLY BY BLANKING OFF THE SYSTEM AND PRESSURIZING THE DUCT.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005090600019	20050906	00019	CE  	2005	9	6	CA050802001      	1	20050530	G	7120	12991004713	TRUSS           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MULTIPLE CRACKS WERE FOUND EMITTING FROM TOOLING HOLES AND RIVETS IN BRACKETS A (220-050) AND B (220-051), IAW DRA	WING NR 129-910047-13.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005090600020	20050906	00020	CE  	2005	9	6	CA050802002      	1	20050731	G	3297		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	UPLOCK SWITCH	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA			13967								(CAN) AFTER TAKEOFF ,THE GEAR WAS RETRACTED AND THE RED INTRANSIT LIGHT DID NOT EXTINGUISH.  THE GEAR WAS EXTENDED AND O	PERATED NORMALLY.  THE FLIGHT CONTINUED, THE CREW DID A FLYBY OF TOWER TO CONFIRM GEAR POSITION WHEN UP. THE TOWER THOUG	HT THE NOSE WAS LOWER THAN NORMAL. (THE NOSE GEAR TIRE ON A1900 ALWAYS STICKS OUT OF WHEEL WELL.) THE GEAR WAS EXTENDED 	AND INDICATED SAFELY. THE AIRCRAFT RETURNED TO BASE WHERE MAINTENANCE FOUND A BROKEN WIRE ON THE NOSE GEAR UPLOCK SWITCH	 HARNESS.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005090600021	20050906	00021	EA  	2005	9	6	CA050802003      	2	20050802	G	7322	46F10	VENTURI         	PREAIR      	MA4SPA      	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	CARBURETOR	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						5896					(CAN) INSPECTION PRIOR TO ASSEMBLY REVEALED SERIOUS CASTING FLAW IN PART.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2005090600023	20050906	00023	CE  	2005	9	6	CA050803001      	1	20050802	G	2730	NAS428H316	BOLT            			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	STABILIZER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE WALK-AROUND THE PILOT NOTICED THE DOWN ELEVATOR STOP BOLT HEAD HANGING FROM THE LOCKWIRE.  IT HAD BROKE	N FROM THE SHAFT APPROXIMATELY 2MM FROM THE BOLT HEAD. THE BOLT WAS REPLACED NEW AND THE ELEVATOR TRAVELS AND FUNCTION W	ERE CHECKED.				1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2005090600024	20050906	00024	NM  	2005	9	6	CA050803002      	1	20050801	G	3230	54C546349	BOLT            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	SEQUENCE VALVE	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) DURING A LANDING, AN AIRCRAFT EXPERIENCED LOSS OF MOST OF NR 2 HYDRAULIC SYSTEM CONTENTS.  THE DEFECT WAS TRACED T	O FAILURE OF LT DOOR SEQUENCING UNIT PART NR 54C54634-9, WHICH HAD SUFFERED SEVERE HYDRAULIC  FORCED DAMAGE THAT 2 OF TH	E BOLTS SHEARED WITH THE FORCE. THIS UNIT WAS REPLACED AND THE HYDRAULIC SYSTEM SERVICED, FUNCTION FLIGHT CARRIED OUT SY	STEM SATISFACTORY AND AIRCRAFT RELEASED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005090600025	20050906	00025	EA  	2005	9	6	CA050803003      	1	20050728	G	7800	C2EE247AND	SEGMENT         			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3P	HCB3P302    	GL  	EXHAUST ASSY	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) THE PILOT REPORTED AN INTERMITTENT (POPPING) SOUND DURING ALL PHASES OF OPERATION.  MAINTENANCE INVESTIGATION REVE	ALED A CRACK AND BLOWN EXHAUST GASKET ON NR 3 CYLINDER EXHAUST SEGMENT.  THE CRACK EXTENDED AROUND MOST OF THE FLANGE, A	ND WAS CREEPING UP THE STUB APPROXIMATELY 1 INCH.  THE SEGMENT WAS WELD REPAIRED AND REINSTALLED.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P29EA	 
2005090600026	20050906	00026	EA  	2005	9	6	CA050803004      	2	20050729	G	7322	MA45PA	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) THIS OPERATOR HAS EXPERIENCED FOR THE SECOND TIME THE PROBLEM THAT THESE CARBURETORS HAVE WORKED LOOSE BETWEEN TOP	 AND BOTTOM HALVES, EVEN WITH ALL 4 SCREWS AND LOCKING TABS IN PLACE. THIS PROBLEM LEADS TO AIRCRAFT ENGINE RUNNING ROUG	H, ALLOWING AIR TO ENTER BOND AND LET FUEL ESCAPE INTO ENGINE COMPARTMENT. IT APPEARS THAT DUE TO WEIGHT AND STRESS ASSO	CIATED WITH CARBURETOR AIR BOX ATTACHED, THE CASTING OF THE LOWER HALF OF CARBURETOR CANNOT WITHSTAND THE WEIGHT AND THE	 THREADS ARE PULLED FREE THEREBY ALLOWING A SPLIT IN THE UNIT.  VERY SERIOUS PROBLEM EXISTS AS A RESULT, ALLOWING RAW FU	EL TO ENTER ENGINE COMPARTMENT AT CLOSE PROXIMITY TO EXHAUST.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005090600027	20050906	00027	EA  	2005	9	6	CA050803005      	1	20050720	G	2910	82950010271	LINE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CAPTAIN REPORTED A LOSS OF FLUID FROM NR 1 HYDRAULICS.  EVERYTHING SEEMED TO OPERATE NORMALLY, BUT CREW ELECTED TO	 DO THE FLAPLESS LANDING IN CASE OF A GO AROUND.  NR 1 HYDRAULIC SYSTEM DRAINED DOWN TO 1 QUART INFLIGHT.   FOUND IB ROL	L SPOILER PRESSURE CHD LINE WITH A PIN HOLE AT 90 DEGREE BEND ABOUT 3 INCHES FORM ACTUATOR PORT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005091500142	20050915	00142	CE  	2005	9	15	CA050803006      	1	20050802	G	2731		DRIVE SHAFT     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ACTUATOR	SHEARED         	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT, ELEC TRIM WAS OPERATED, IT WOULD ONLY MOVE 1.5 DEG FROM FULL NOSE UP, COULD NOT BE MOVED MANUALLY.  A	C RETURNED TO DEPARTURE AIRPORT.  ELEV TRIM WAS STILL JAMMED ON GROUND ELECTRICALLY AND MANUALLY.  INSP OF ACTUATOR MOTO	R, IN TAIL SECTION, REVEALED THAT DRIVE HAD SHEARED AT END OF ACTUATOR.  ACTUATOR IS CONNECTED TO ANOTHER CABLE DRUM UNI	T WITH UNIVERSAL JOINT.  ACTUATOR ASSY IS CONNECTED TO 1 ELEV TRIM CABLE WITH BRIDAL CABLE, DRUM UNIT IS CONNECTED TO OT	HER ELEV TRIM CABLE WITH A BRIDAL CABLE.  WHEN ACTUATOR DRIVE SHEARED, BRIDAL CABLE OF DRUM UNIT AND UNIVERSAL JOINT JAM	MED ELEVATOR TRIM CABLE, SO THERE WAS VERY LITTLE MOVEMENT OF TRIM SYS. REASON FOR ACTUATOR DRV BREAKING IS UNKNOWN.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005090600028	20050906	00028	NE  	2005	9	6	CA050803007      	2	20050704	G	8520		PUSHROD         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	BROKEN          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA								42113725			(CAN) NR 2 CYL EXHAUST ALUMINUM PUSH ROD BROKEN NEAR THE TOP FITTING.						1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2005090600029	20050906	00029	CE  	2005	9	6	CA050803008      	1	20050707	G	7120	05510171	MOUNT           			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 2 CRACKS FOUND AT LOWER CROSS TUBE SAME CRACKS FOUND ON PREVIOUS MOUNT.  BOTH MOUNTS OVERHAULED, WELDING CRACKS LO	CATED BESIDE WELD AREA SHOULD HAVE GUSSET PLATE WELDED AT THIS AREA TO RE-INFORCE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2005090600030	20050906	00030	SO  	2005	9	6	CA050803009      	2	20050803	G	8530	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) PILOT HEARD UNUSUAL EXHAUST NOISE FROM ENGINE.ON INSPECTION, FOUND NR 5 CYLINDER EXHAUST HEADER HAD SEPARATED .187	5 INCH FROM THE FLANGE JUST BELOW THE WELD.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2005090600031	20050906	00031	SW  	2005	9	6	CA050804001      	1	20050730	G	7810	6896024	NOZZLE          	ALLSN       		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	CRACKED         	W				A				UNSCHED LANDING         				C	D		F.O.D.                    	INFLIGHT SEPARATION       		CL	CLIMB          	1			CA						CAC70116		CAC70116			(CAN) EJECTOR NOZZLE BROKE OFF INTO THE INTAKE PLENUM AND EVENTALLY WERE DRAWN INTO THE COMPRESSOR.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005091500148	20050915	00148	SO  	2005	9	15	CA050804003      	2	20050707	G	8520		LINE            	CONT        							CONT  	O470  	IO470VO     	17026	SO  					CRANKCASE	CLOGGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								1489279V			(CAN) EXCESSIVE AMOUNTS OF AN UNIDENTIFIED SEALANT WAS USED ON THE SPLIT-LINE CAUSING THE SEALANT TO SQUEEZE INTO THE EN	GINE.  A LOSS OF TORQUE WAS FOUND ON THE THRU-BOLTS AND CYLINDER BASE NUTS.  THE OIL PICK-UP WAS CLOGGED WITH THE LOOSE 	SEALANT.									3	O			3E1				 
2005090600033	20050906	00033	SW  	2005	9	6	CA050804004      	1	20050722	G	5302	2060313293	FITTING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK STARTED AT THE TOP OF THE FITTING AND TRAVELED VERTICALLY THROUGH A RIVET HOLE TO APPROXIMATELY .1250 INCH	 BELOW IT.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005090200064	20050902	00064	EU  	2005	9	2	CA050804005      	1	20050623	G	2750	Z4243130000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION THE FLAP CONTROL SYSTEM CENTER CABLE WAS DISCOVERED TO BE FRAYED AT THE AREA OF THE PUL	LEY.  THE CABLE WAS REPLACED NEW.					1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2005090200065	20050902	00065	EU  	2005	9	2	CA050804006      	1	20050623	G	2750	Z4243130000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION THE FLAP CONTROL SYSTEM CENTER CABLE WAS DISCOVERED TO BE FRAYED AT THE AREA OF THE PUL	LEY.  THE CABLE WAS REPLACED NEW.					1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2005090700023	20050907	00023		2005	9	7	CA050804007      	2	20050725	G	7414	107902010	MAGNETO         																	ENGINE	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											MAGNETO SENT TO US TO OFFSET COST OF PARTS ORDERED FROM US.  INSPECTION CARRIED OUT PRIOR TO PUTTING UNIT IN STOCK.  FOU	ND RETAINING RING ON DISTRIBUTOR GEAR SHAFT WAS REUSED.  DISTRIBUTOR GEAR OF OLD DESIGN, SHOULD BE REPLACED AS PER TCM 5	3658.  MAGNETO WAS OVERHAULED.  IMPULSE COUPLING WAS INSPECTED FOR CONDITION/OPERATION.  DOES NOT ENGAGE.  IMPULSE SPRIN	G WOUND BACKWARDS, DISENGAGING FLYWEIGHTS FROM STOP PINS.  STARTING THE ENG WITH THIS MAGNETO MAY CAUSE KICKBACK DUE TO 	THE ENGINE BEING FIRED AT ITS NORMAL ADVANCED TIMING POSITION, NOT THE RETARDED POSITION THE IMPULSE COUPLING PROVIDES. 	 KICKBACK MAY DAMAGE ENGINE AND ACCY COMPONENTS AND CAUSE FAILURE OF THE ENGINE.														 
2005090200066	20050902	00066	EU  	2005	9	2	CA050804008      	1	20050726	G	2750	Z4243130000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION THE CENTER FLAP CABLE WAS FOUND TO BE FRAYED AT THE PULLEY AREA.  THE CABLE WAS REPLACE	D NEW.  THIS IS A COMMON AREA FOR WEAR ON THESE CABLES.					1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2005090200067	20050902	00067	NM  	2005	9	2	CA050804009      	1	20050727	G	2750	694020512	TORQUE TUBE     			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					TE FLAPS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE NR 2 TRANSMISSION TORQUE TUBE, A DEEP 'V' GOUGE .016 INCH DEEP WAS FOUND.  A FLEET C	AMPAIGN WAS INITIATED TO CHECK ALL TRAILING EDGE FLAP TORQUE TUBES.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005090200068	20050902	00068	SW  	2005	9	2	CA050804010      	1	20050802	G	3230	21032031	RELEASE CABLE   			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	EMER MLG RELEASE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN COMPLYING WITH AN UNRELATED INSPECTION UNDER THE COCKPIT FLOOR, MAINTENANCE DISCOVERED THE NOSE LANDING GEAR 	EMERGENCY RELEASE CABLE WAS SHEARED AT THE CLEVIS WHERE IT ATTACHES TO THE HANDLE BELLCRANK.  THIS AIRCAFT HAD RECENTLY 	(WITHIN 50 HOURS) UNDERGONE A PHASE 5 INSPECTION WHERE THE SYSTEM WAS INSPECTED AND TESTED, NO DEFECTS WERE FOUND.  THE 	CABLE WAS REPLACED WITH A SERVICEABLE UNIT, GEAR SWINGS WERE CONDUCTED AND NO FURTHER FAULTS FOUND.  THIS IS THE FIRST F	AILURE OF THIS TYPE THIS OPERATOR HAS EXPERIENCED.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2005090800001	20050908	00001	SO  	2005	9	8	CA050805003      	1	20050803	G	7820		BAFFLE          	LYC         	3241        	PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	MUFFLER	WARPED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						680					(CAN) EXCESSIVE EXHAUST BACK PRESSURE - MUFFLER 2 INCH STACK HOLE IN CAN 1.5 INCH DIAMETER LEFT A HIGH RESTRICTION CAUSI	NG HIGH HEAT PROGRESSIVELY COLLAPSING THE PERFORATED BAFFLE AROUND THE EMERGECY BAIL RESULTING IN A SERIOUS LOSS OF POWE	R.				1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
2005100600073	20051006	00073	EA  	2005	10	6	CA050806001      	2	20050729	G	7310	25766303	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					FUEL SYSTEM	UNSERVICEABLE   	W				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, THE PILOT EXPERIENCED POWER SURGES AND FLUCTUATIONS IN MANIFOLD PRESSURE.  THE SERVO COULD NOT BE 	ADJUSTED EITHER WAY AND BLUE STAINS WERE EVIDENT AT THROAT OF SERVO.  ALSO, THE MANIFOLD PRESSURE WAS 2.5 INCHES HIGHER 	THAN NORMAL AT 100 PERCENT WITH ZERO COLLECTIVE.  MANIFOLD PRESSURE SHOULD BE AROUND 13 TO 13.5' OF MANIFOLD PRESSURE.  	THE SERVO WAS CHANGED AND THE ENGINE NO LONGER SURGED AND MANIFOLD PRESSURE WAS NORMAL.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2005090200015	20050902	00015	EU  	2005	9	2	CA050808001      	1	20050804	G	2400	NAS931323501	CIRCUIT BREAKER 			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  						BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINES GROUND RUN AFTER A ROUTINE INSPECTION VISIT, THE FOLLOWING CIRCUIT BREAKERS WERE FOUND POPPED, FUEL	 LT INNER TANK PUMP NR 1, FUEL RT INNER TANK PUMP NR 2, FUEL CENTER TANK RT PUMP, FUEL LT OUTER TANKPUMP NR 1 AND AFT CA	BIN FAN.  DURING INVESTIGATION FOUND C/B 2XN BURN AND PHASE C MISSING AT 101VUB23 , FOR 202XP BUSS BAR. C/B REPLACED. A 	SPECIAL INSPECTION CAMPAIGN WAS INITIATED TO PERFORM A DETAIL IN SPECTION OF CIRCUIT BREAKERS INSTALLED IN ALL AIRCRAFT 	POWER CENTER 101VU AND REPLACE IN CASE OF FINDINGS.		2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2005090200016	20050902	00016	GL  	2005	9	2	CA050808002      	2	20050807	G	7314		PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE802180BA			(CAN) AIRCRAFT WAS HAVING PROBLEM WITH INITIAL START.  FUEL CHECK VALVE AND FCU HAD BEEN CHANGED FOR TROUBLESHOOTING.  R	EPLACED ENGINE DRIVEN FUEL PUMP, AIRCRAFT RETURNED TO SERVICE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005090200017	20050902	00017	EU  	2005	9	2	CA050808003      	1	20050807	G	2913	9749976	PUMP            			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			24174								(CAN) AIRCRAFT RETURNED TO THE STATION DUE TO NR 1 ENGINE LOW HYDRAULIC PRESSURE AND LOSS OF HYDRAULIC FLUID GREEN SYSTE	M.  DURING INVESTIGATION THE HYDRAULIC PUMP HAD FAILED WITH A HOLE INTO THE HOUSING.  HYDRAULIC PUMP AND FILTER REPLACED	 AND AIRCRAFT WAS RETURN TO SERVICE.  PUMP ROUTED TO REPAIR SHOP FOR INVESTIGATION.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2005090200018	20050902	00018	EA  	2005	9	2	CA050808004      	2	20050801	G	7200		ENGINE          								PWC   	150   	PW150A      	 	EA  						MAKING METAL    	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0098			(CAN) LOSS OF ENGINE OIL PRESSURE OBSERVED IN CRUISE. ENGINE WAS SHUTDOWN AND UNEVENTFUL SINGLE ENGINE LANDING PERFORMED	. GROUND EXAMINATION SHOWED A QUANTITY OF METAL CHIPS ON THE RGB CHIP DETECTOR.  ENGINE IS EN-ROUTE TO MFG FOR TEAR-DOWN	 INVESTIGATION.  MFG WILL KEEP INFORMED AS THE INVESTIGATION PROGRESSES.									4	T			E00062EN				 
2005090200019	20050902	00019	SO  	2005	9	2	CA050808005      	1	20050804	G	3230	1776604	HOSE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE NOSE LANDING GEAR WOULD NOT RETRACT FULLY.  THE CREW THEN SELECTED GEAR DOWN, GEAR WOULD NOT LOC	K DOWN.  LANDING GEAR HAD TO BE MANUALLY PUMPED DOWN IN ORDER TO GET THREE GREEN LIGHTS.  THE NOSE GEAR ACTUATOR RETRACT	 FLEXHOSE WAS FOUND LEAKING.  THE HOSE WAS REPLACED WITH A SERVICEABLE UNIT, AND A SATISFACTORY GEAR SWING WAS CARRIED O	UT.			1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2005090200020	20050902	00020	EU  	2005	9	2	CA050809001      	1	20050804	G	3340	E0062D1S4BJ04	SWITCH          			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					ANTI COLLISION L	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING STATION TURN AROUND, MAINTENANCE NOTICED SMALL SPARK COMING OUT OF THE ANTI-COLLISION CONTROL SWITCH (2LV).	  CIRCUIT BREAKER (5LV) OF THE LOWER BEACON WAS POPPED.  FOUND THE ANTI-COLLISION SWITCH CONTACTS 1B AND 2B SHORTED TOGE	THER, REGARDLESS OF THE SWITCH POSITION AND SHORTED TO GROUND THROUGH THE SWITCH BODY.  SWITCH ASSEMBLY WAS REPLACED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2005091200207	20050912	00207	EU  	2005	9	12	CA050809002      	2	20050728	G	7200		ENGINE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RIGHT	FAILED          	W				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA								13533			(CAN) AC WAS IN CRUISE, RT ENG WAS INDICATING NML, ENG SEEMED TO STUMBLE, COME BACK TO NML, THEN IMMEDIATELY FAILED.  TE	MP GAUGE FOR ENG RAPIDLY EXCEEDED 1000 DEGREES C, RPM DROPPED TOWARDS 0, TORQUE JUMPED THEN DROPPED TOWARDS 0.  CAPT PUL	LED THROTTLE BACK, FEATHERED RT ENG IN ATTEMPT TO CNTRL TEMP.  ENG FAILURE DRILL WAS COMPLETED, SOP AC LANDED WITH 1 ENG	 OPERATIONAL WITHOUT INCIDENT.  REVIEW OF OP LIMITS OF MFG ENGINES, 1000 DEGREES C SURPASSES MAX TEMP ALLOWED.   INFO ST	ANDPOINT PROP WAS PULLED THROUGH WITH NO BINDING OR GRINDING PRESENT, PRESS FILTER WAS INSP, NO DEBRIS NOTED.  BOTH COMP	RESSOR INLET, JET PIPE EXIT INSPECTED NOTHING NOTED.  ENG WAS CHANGED DUE TO TGT EXCEEDENCE, AC WAS RETURNED TO SERVICE.	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005090200021	20050902	00021	CE  	2005	9	2	CA050809003      	1	20050804	G	2120	420C75275M	CLAMP           			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					BYPASS VALVE	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AT 38000 FEET THE LT FUEL COMPUTER WENT OFF LINE. SHORTLY AFTER THE RT COMPUTER WENT OFF LINE. THIS WAS FOLLOWED B	Y EXCESSIVELY HIGH TEMPERATURE BUILDING IN THE CABIN WITH NO CONTROL OF THE ENVIRONMENTAL SYSTEM. THE CREW DECIDED TO LA	ND.  MAINTENANCE TROUBLESHOOTING REVEALED A CONNECTOR CLAMP FOR THE HOT AIR BYPASS VALVE HAD COME LOOSE. FURTHER INVESTI	GATION FOUND 6 OUT OF 8 CLAMPS WERE LOOSE. THE CLAMPS WERE RE-TORQUED AND LEAK CHECKED SERVICEABLE LACK OF LOCK WIRE ON 	THE CLAMPS POSSIBLY CONTRIBUTED TO THIS OCCURRENCE. ALL CLAMPS WERE RE-CHECKED AND LOCK WIRED WHEN THE AIRCRAFT RETURNED	 TO BASE.	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2005090200022	20050902	00022	NM  	2005	9	2	CA050810001      	1	20050810	G	3411		PITOT SYSTEM    			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					PITOT/STATIC SYS	FOD             	W				C				ABORTED TAKEOFF         				C			F.O.D.                    			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL, NO AIRSPEED INDICATION ON THE CAPTAINS SIDE.  DEBRIS FOUND IN CAPTAINS UPPER LT PITOT TUBE. BUG R	EMOVED AND PITOT/STATIC SYSTEM TESTED SERVICEABLE. TIMES: 63714:40  CYCLES: 61165.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005090200023	20050902	00023	CE  	2005	9	2	CA050810002      	1	20050808	G	7312	10585J	HEATER          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	FUEL/OIL	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								PCE94792			(CAN) PILOT REPORTED RT ENGINE HAD NO ACCELERATION RATE AS COMPARED TO LT ENGINE.  THE RT ENGINE DID EVENTUALLY ACCELERA	TE, BUT NOT EQUAL WITH THE LT.  TROUBLESHOT AND FOUND RT OIL-TO-FUEL HEATER THERMOSTAT GONE TO (FULL HOT) AND FUEL TEMP 	WAS SAME AS OIL TEMP, THEREFORE BOILING THE FUEL AND VAPOURIZING IT AND THEREFORE SUBSEQUENT LOSS OFF POWER AND ACCELERA	TION. OIL TO FUEL HEATER CHANGED AND ACCELERATION REGAINED. THE FUEL CONTROL UNIT WAS CHANGED INITIALLY FOR TROUBLESHOOT	ING AS OIL TO FUEL HEATER WAS NOT SUSPECTED AS FAULT.		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2005090200055	20050902	00055	GL  	2005	9	2	CA050810003      	2	20050731	G	7240	6870992	COMBUSTION LINER			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA								CAE840805			(CAN) THE PILOT WAS EXPERIENCING HIGH TOT (WITHIN FLIGHT MANUAL LIMITATION) AND REPORTED THAT THE AIRCRAFT WAS FAILING T	HE POWER CHECK. THE ENGINEER VISUALLY INSPECTED THE ENGINE FOR DISCREPENCIES AND FOUND A 2 INCH CRACK IN THE ARM PIT OF 	THE OUTER COMBUSTION LINER. TSN OF COMBUSTION LINER UNKNOWN. AIRCRAFT HAS ABOUT 12,950 HOURS ON IT BUT THE COMBUSTION LI	NER DOES NOT APPEAR TO BE ORIGINAL.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005090200075	20050902	00075	EA  	2005	9	2	CA050810004      	2	20050728	G	8520	LW11538	CAMSHAFT        								LYC   	O360  	LIO360C1E6  	41515	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L996251AC			(CAN) DURING A ROUTINE INSPECTION, THE OIL FILTER WAS CUT OPEN AND EXAMINED FOR METAL CONTAMINATION IAW MAINTENANCE INST	RUCTIONS. THE FINDINGS WERE TAKEN FOR FURTHER ANALYSIS. IT WAS DETERMINED THAT THE ENGINE WOULD NEED TO COME OFF WITHIN 	50 HRS. 28.8 HRS LATER THE ENGINE WAS REMOVED AND SENT FOR REPAIR. ON WO NR 0508026, REPAIRED THE ENGINE, REPLACING AMON	G OTHER PARTS THE CAMSHAFT.  THE ENGINE WAS THEN REINSTALLED.								3	O			1E10				 
2005100600074	20051006	00074	EA  	2005	10	6	CA050810005      	2	20050805	G	7261	CH481031	OIL FILTER      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION, THE OIL FILTER WAS CUT OPEN AND EXAMINED FOR METAL CONTAMINATION AS PER MAINTENANCE I	NSTRUCTIONS.  IT WAS FOUND THAT THE FILTRATION MEDIUM HAD COLLAPSED.  THE ENGINE WAS EXAMINED FOR POSSIBLE RESTRICTIONS 	OF OIL FLOW AT THE BYPASS VALVE LOCATED IN THE ADAPTER PLATE.  NO SUCH EVIDENCE WAS FOUND.  THE VENDOR HAS BEEN CONTACTE	D WHO IN TURN NOTIFIED THE MANUFACTURER.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005090200076	20050902	00076		2005	9	2	CA050811001      	4	20050809	G	3418		TRANSDUCER      			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	STALL WARNING	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE, THE STICK SHAKER ACTIVATED WITH NO VISIBLE AIRFRAME ICING.  THE AIRCRAFT RETURNED,  WHERE MAINTENANCE R	EPLACED THE NR 2 STALL WARNING TRANSDUCER.  THE AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER PROBLEM.					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005090200077	20050902	00077	SO  	2005	9	2	CA050811002      	1	20050804	G	2810	557003	ADAPTER         	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL TANK COVER	MISSING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT HAD JUST TAKEN OFF WHEN THE PILOTS NOTICED THAT THE LT MAIN FUEL CAP HAD DEPARTED THE AIRCRAFT.  THE 	AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT.  IN ORDER TO PREVENT THE AIRCRAFT FROM BEING ACCIDENTALLY FUELED WITH TURBO 	FUEL, MFG PROVIDES A KIT WITH AN ADAPTER RING TO NARROW THE OPENING TO THE FUEL TANK (SB 797B).  IN THIS CASE THE FUEL C	AP AND THE ADAPTER RING IT LOCKS INTO WERE MISSING.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005090200078	20050902	00078	CE  	2005	9	2	CA050811003      	1	20050808	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA							BB170				(CAN) DURING DESCENT THE PILOTS WINDSHIELD COMPLETELY DELAMINATED.  THE WINDSHIELD STAYED IN PLACE HOWEVER THE VISION FO	RWARD WAS COMPLETELY OBSCURED.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005090200079	20050902	00079	CE  	2005	9	2	CA050812001      	1	20050812	G	2510	50110502	STOP            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPANY CAMPAIGN NOTICE 851-25-26-029 WAS CREATED TO INSPECT FOR PROPPER INSTALLATION OF PASSENGER SEAT STOPS.  DU	RING INSPECTION IT WAS FOUND THAT 4 STOPS WERE MISSING ON THE LT BACK TO BACK SEAT INSTALLATION. PARTS ARE ORDERED AND W	ILL BE INSTALLED PRIOR TO NEXT FLIGHT.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005090200003	20050902	00003	CE  	2005	9	2	CA050812002      	1	20050811	G	2510	50110502	STOP            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT SEATS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPANY CAMPAIGN NOTICE 851-25-26-029 WAS CREATED TO INSPECT FOR PROPPER INSTALLATION OF PASSENGER SEAT STOPS. DUR	ING INSPECTION IT WAS FOUND THAT 4 STOPS WERE MISSING ON THE LT BACK TO BACK SEAT INSTALLATION. PARTS ARE ORDERED AND WI	LL BE INSTALLED PRIOR TO NEXT FLIGHT.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005090200004	20050902	00004	SW  	2005	9	2	CA050812003      	1	20050811	G	5753	21583	MOUNT           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					FLAP HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON THE RT WING IB MOST FLAP MOUNT THERE ARE SEVERAL SMALL CRACKS PROTRUDING OUT OF THE LOWER BOLT HOLE WHICH IS US	ED TO ATTACH THE BRACKET TO THE REAR SPAR OF THE WING.					1	H	7	1 	3O	3	O		A21CE   	E286				 
2005090200005	20050902	00005	SW  	2005	9	2	CA050812004      	1	20050809	G	5753	21583	MOUNT           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FLAP HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON THE LT WING IB MOST FLAP MOUNT THERE ARE SEVERAL SMALL CRACKS AND ONE LARGE CRACK PROTRUDING OUT OF THE LOWER B	OLT HOLE WHICH IS USED TO ATTACH THE BRACKET TO THE REAR SPAR OF THE WING.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005090200006	20050902	00006	CE  	2005	9	2	CA050815001      	1	20050814	G	2121	1013841761	BLOWER          			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	FWD CABIN	FAILED          	W				O				OTHER                   				S			AFFECT SYSTEMS            			AP	APPROACH       	1			CA											(CAN) THE AIRCRAFT WAS ON THE RETURN LEG OF A TRIP WHEN THE FORWARD VENT MOTOR P/N 101-384176-1 MODEL EM640-1 FAILED ON 	SHORT FINAL LANDING. THE TBO ON THIS UNIT IS 1500 HRS IAW COMPONENT OVERHAUL MANUAL. OUR UNIT FAILED PRIOR TO THIS LIMIT	 AND HAVE HAD OTHER OCCURRENCES OF PREMATURE FAILURE.  HAVE DECIDED TO REDUCE THE TBO TIME IN HOUSE TO 1200 HRS AS A PRE	VENTIVE MEASURE. THE REMOVAL AND INSTALLATION OF THIS UNIT IS A TIME CONSUMING TASK ON THIS AIRCRAFT.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005090200069	20050902	00069	CE  	2005	9	2	CA050815002      	1	20050714	G	2820	0500106354	LINE            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2AF34C	D2AF34C*    	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING, FOUND FUEL CROSS-FEED LINE ROUTED THROUGH RT DOOR POST WEEPING FUEL. PORTION OF LINE REMOV	ED AND UPON FURTHER EXAMINATION A PIN-HOLE CAUSED BY CORROSION WAS FOUND UNDER PLASTIC ANTI-CHAFE MATERIAL. SUSPECT COND	ENSATION OVER MANY YEARS CAUSED CORROSION TO FORM UNDER PLASTIC SHEATH. REFERENCE TO FIGURE 99 OF AIRCRAFT IPC.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P5EA	 
2005090600013	20050906	00013	NE  	2005	9	6	CA050815003      	2	20050810	G	7297	601R577921	WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				A	B	J	FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			CA			13944					807022			(CAN) INITIAL INVESTIGATION OF RT FIRE INDICATION LEADS US TO BELIEVE THAT A CHAFED IDG HARNESS ARCED AGAINST MAIN FUEL 	CONTROL. THIS ACTION CAUSED MAIN FUEL CONTROL TO LEAK WHICH LEAD TO THE SMALL CONTAINED OVERHEATING EVENT. THIS CAUSED F	IRE SYSTEM TO ALERT THE CREW.  IAW QRH, FLIGHT CREW ACTUATED THE (ENGINE FIRE PUSH) SWITCH AND SHUTDOWN THE ENGINE. INIT	IAL REPORTS SHOW THAT AFTER THE (ENGINE FIRE PUSH) SWITCH WAS PRESSED THE FIRE MESSAGE WENT OUT.  NO FIRE BOTTLES WHERE 	DISCHARGED AND THE AIRCRAFT LANDED SAFELY. POST INCIDENT INSPECTIONS REVEALED THAT THE CLAMP THAT RESTRAINED THE IDG HAR	NESS AT THE TOP OF THE SERVICE PANEL WAS LOOSE AND ALLOWED THE IDG HARNESS TO MOVE.  ENGINE WAS REMOVED AND REPLACED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005090200070	20050902	00070	NM  	2005	9	2	CA050815004      	1	20050811	G	3010	FSCM79318	ISOLATION VALVE 			DHAV  	DHC8  	DHC8*       	       	NM  										DE ICE SYSTEM	LEAKING         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING THE DE-ICE PRESSURE REGULATOR FUNCTION CHECK THE WING DE-ICE ISOLATION VALVE WAS FOUND TO BE LEAK	ING (NOT CLOSING COMPLETELY) ALLOWING AIR PRESSURE TO BOTH WINGS. TWO OTHER ISOLATION VALVES WERE FUNCTION CHECKED AND W	ERE ALSO FOUND NOT CLOSING COMPLETELY.				2	H	7	2 	4T			RT	A13NM   					 
2005090200071	20050902	00071	NE  	2005	9	2	CA050815005      	2	20050808	G	7230		FAN             			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENGINE	VIBRATION       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			10756	10756							(CAN) NOTICED, FELT VIBRATION ON INITIAL CLIMB OUT BELOW 10000 FT, BROUGHT UP ENG PARAMETERS ON MFD/VIB AT 3.5/ADVSD MTC	. CONTROL/VIB. INCREASED GRADUALLY TO EXCEED 4.0 THROUGH 20000 FEET.  AIRCRAFT RETURNED TO DEPARTURE. ENGINE FAN BLADES 	WERE RE-INSTALLED. ACCORDING TO BLADE SOLUTION DISTRIBUTION.  SPINNER CONE WEIGHTS MORMALIZED AND ENGINE RUN CARRIED OUT	 WITH GOOD RESULTS.  ENGINE VIBES NOW 0.2 NO FURTHER DIFICULTIES RECORDED TO DATE. ISSUE CLOSED.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005090800027	20050908	00027	GL  	2005	9	8	CA050815006      	2	20050810	G	7321	HP3BMA	FUEL CONTROL    			KAMOV 	KA32  	KA32A1      	       	SW  	AMTR  	VK1A  	KLIMOVK1A   		GL  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			AP	APPROACH       	1			CA								087893100098			(CAN) WHILE ON APPROACH FOR LANDING, A HIGH ROTOR SPEED CONDITION OCCURED. THE PILOT IMMEDIATELY NOTICED THE INCREASE IN	 NR AND INCREASED COLLECTIVE TO MAINTAIN THE NR WITHIN NORMAL PARAMETERS.  WITH THE NR STABILIZED, THE DEFECTIVE ENGINE 	WAS IDENTIFIED AND THE THROTTLE CONTROL LEVER WAS RETARDED. THE AIRCRAFT DESCENDED AND CARRIED OUT AN UNEVENTFUL LANDING	. ONCE ON THE GROUND, A SEPARATE ENGINE CHECK IDENTIFIED THE NR 2 ENGINE FCU NF GOVERNOR HAD FAILED. THE FUEL CONTROL UN	IT WAS REPLACED.		1	G	7	2 	4U	4	J	NC	        	EXPE4J				 
2005090200072	20050902	00072	NM  	2005	9	2	CA050816001      	1	20050813	G	5610	1417480150	WINDSHIELD      			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) WHILE IN FLIGHT, THE FLIGHT CREW NOTICED ARCING INSIDE THE FIRST OFFICER WINDSHIELD WHICH RESULTED IN A SEVERELY C	RACKED OUTER PANE.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005121200109	20051212	00109	SW  	2005	12	12	CA050816002      	1	20050725	G	6230	204011426001	PLATE           			BELL  	212   	212         	1181420	SW  										SWASHPLATE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) INK STAMPED NUMBERS ON PART INDICATE THIS IS A BREAKOUT PART ACCORDING TO BELL TEXTRON, MANUFACTURED FOR US ARMY B	Y MORRIS MANUFACTURING.  PURCHASE RECORDS AT BELL HELICOPTERS AS FAR BACK AS 1979 INDICATE THAT MORRIS MANUFACTURING WAS	 NEVER A SUPPLIER FOR BELL.  PART CERTIFICATE THAT CAME WITH THE PART STATES OTHERWISE.  AN FAA FORM 8120-11 WAS RAISED 	THROUGH BELL HELICOPTERS TEXTRON.			1	G	7	1 	4U				H4SW    					 
2005090600014	20050906	00014	EA  	2005	9	6	CA050816003      	2	20050716	G	7260	311663301	DRIVE GEAR      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	A/C PACK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE80394			(CAN) FOLLOWING FLIGHT AND DURING A LAYOVER CHECK, IT WAS NOTED THAT AIR CONDITIONING ACCY DRIVE WAS DE-COUPLED FROM GAS	 GENERATOR AS NOTED DURING ROTATION OF AC COMPRESSOR. REMOVAL OF EXTERNAL DRIVE SPLINE DETERMINED THAT THE FAULT WAS NOT	 EXTERNAL TO ENGINE BUT RATHER ISOLATED TO INTERNALS OF ENGINE ACCY GB. ENGINE WAS REMOVED, SENT TO AN ENGINE SHOP FOR I	NVESTIGATION AND REPAIR. ENGINE TEARDOWN DETERMINED THAT DE-COUPLING WAS RESULT OF BROKEN AGB OPTIONAL GEAR, WHICH DRIVE	S AC COMPRESSOR. ROOT CAUSE OF PROBLEM WAS A RESTRICED OIL JET NOZZLE CAUSING ABNORMAL SHAFT SPLINE WEAR, WHICH RESULTED	 IN ABNORMAL PLAY AND ROTATION OF THE AGB COUPLING SHAFT, RESULTING FATIGUE FAILURE OF THE AGB OPTIONAL GEAR.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005090600015	20050906	00015		2005	9	6	CA050816004      	4	20050721	G	2216	6627401000007	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HORIZONTAL STAB	FAILED          	W				O				OTHER                   				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CL	CLIMB          	1			CA											(CAN) DURING CLIMB-OUT AFTER AUTO-PILOT WAS ENGAGED, THE AMBER PRIMARY PITCH TRIM FAIL EICAS MESSAGE CAME ON.  SECONDARY	 TRIM WAS SELECTED AND USED FOR REMAINDER OF FLIGHT. MAINTENANCE TROUBLESHOOTING FOUND THAT THE AUTO-PILOT TRIM ACTIVATI	ON CAUSED FAILURE OF PRIMARY TRIM SYSTEM.  CHANGED HORIZONTAL STABILIZER TRIM ACTUATOR P/N 6627401000-007.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005090600016	20050906	00016	SW  	2005	9	6	CA050816005      	1	20050812	G	7120	205060105001	MOUNT           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION O	F THE MOUNT IS RIVETED TO ONE LEG AND IT CRACKED FROM ONE OF RIVET HOLES SECURING THE ADJUSTABLE TURN BARREL TO THE MOUN	T LEG.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2005090800039	20050908	00039	SW  	2005	9	8	CA050816006      	1	20050812	G	7120	205060105001	MOUNT           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION O	F THE MOUNT IS RIVETED TO ONE LEG AND IT CRACKED FROM ONE OF RIVET HOLES SECURING THE ADJUSTABLE TURNBARREL TO THE MOUNT	 LEG.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2005090600034	20050906	00034	SW  	2005	9	6	CA050816007      	1	20050814	G	6340	206076373001	DRIVE SHAFT     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					MAIN ROTOR TACH	WORN            	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHILE A/C IN CRUSE FLIGHT LOW ROTOR HORN CAME ON.  ROTOR RPM INDICATED (0).   WHEN PILOT LOWERED COLLECTIVE, HE HA	D NO HYDRAULIC PRESSURE.  A/C LANDED AND MAIN ROTOR CONTACTED TAILBOOM.  ON REMOVAL ROTOR TACH GEN DRIVE SHAFT INTERNAL 	SPLINES WERE FOUND TO BE WORN TO THE POINT OF DISENGAGEMENT.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005090600035	20050906	00035	SW  	2005	9	6	CA050817001      	1	20050628	G	5610	206559258	WINDOW          			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					CABIN	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA						439					(CAN) RETAINER FOR SHOOTING WINDOW FAILED AND VERTICAL SLIDER DEPARTED THE AIRCRAFT.   WINDOW REPLACED, A/C INSPECTED, N	O FURTHER DAMAGE FOUND.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005090800040	20050908	00040		2005	9	8	CA050817002      	4	20050816	G	2330	50401100003	DISPLAY         			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 21D	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON AUGUST 16, 2005 AIRCRAFT WAS IN CRUISE WHEN THE CREW WAS ADVISED THAT THE VDU AT SEAT 21D WAS SMOKING AND THE I	FE SYSTEM WAS TURNED OFF. MAINTENANCE REPLACE D THE VDU AND CHECKED THE SYSTEM TO BE SERVICEABLE.  THIS COMPONENT WILL B	E RETURNED TO THE MANUFACTURER AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE THAT INFO	RMATION IS AVAILABLE.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005090800041	20050908	00041	WP  	2005	9	8	CA050817003      	2	20050814	G	7261	31057463	PRESSURE SWITCH 			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE NOSE CASE	FRACTURED       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL LEAK NOTICED FROM ENGINE COWL AFTER LANDING.  SWITCH WAS BROKEN OFF OF NTS SWITCH HOUSING ON RT SIDE OF NOSE C	ASE.  BROKEN BETWEEN FITTING END AND NUT PART, WHERE THE WRENCH WOULD BE USED TO SECURE IT.  NEW SWITCH INSTALLED AND GR	OUND CHECKED SERVICIBLE AND AIRCRAFT RETURNED TO SERVICE				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005090800042	20050908	00042		2005	9	8	CA050817004      	4	20050626	G	3425	2591411444	INDICATOR       			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	FLT DIRECTOR	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF THE FLIGHT DIRECTOR INDICATOR STARTED TO SMOKE. THE PILOT RETURNED TO THE AIRPORT AND LANDED WITHOUT IN	CIDENT.  THE FLIGHT DIRECTOR INDICATOR WAS REMOVED AND A LOANER UNIT WAS INSTALLED.  THE AIRCRAFT DEPARTED AND COMPLETED	 THE FLIGHT WITHOUT FURTHER INCIDENT.  A FAULTY POWER TRANSFORMER AND BURNED POWER SUPPLY BOARD WERE REPLACED AND THE UN	IT WAS REINSTALLED IN THE AIRCRAFT.			1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005091200222	20050912	00222		2005	9	12	CA050817005      	4	20050815	G	3460	201741211	CDU             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FMS	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN)  1 FMS CDU, DURING CRUISE AT FL210, FMS SCREEN NR 1 FAILED WITH HEAVY SMOKE FROM UNIT, SMOKE CONTINUED FOR ABOUT 1	 MIN OR SO, THEN DISSIPATED.  (P6 NLG STEER CONT) BREAKER WAS ONLY BREAKER THAT WAS POPPED.  RECERTIFICATION DETAILS: 15	 AUG 05, NR 1 FMS CDU REPLACED AND TESTED SERVICEABLE IAW AMM.  P/N 2017-41-211, S/N OFF: 341, S/N ON: 565.  L/S 464094:	  C/B P6 RESET STEERING BY TE TEST COMPLETED, NO FAULT FOUND, TEARDOWN REPORT IS NOT AVAILABLE, SO DETAILS ABOUT THE SPE	CIFIC PART CAUSING DIFFICULTY IS NOT KNOW AT THIS TIME.  UPDATE SDR WHEN INFORMATION IS RECEIVED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005090800043	20050908	00043	SO  	2005	9	8	CA050817006      	1	20050714	G	5330		SKIN            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUSELAGE	DAMAGED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT THE NR 2 COMM ANTENNA DEPARTED THE AIRCRAFT. THE PILOT HEARD THE ANTENNA DEPART AND LANDED 	AT THE NEAREST AIRPORT. A FERRY PERMIT WAS OBTAINED AND FOLLOWING INSPECTION THE AIRCRAFT WAS FERRIED TO FLY WERE IT WAS	 RECENTLY REPAIRED.  THE ATTACH SCREWS WERE FOUND TO HAVE PULLED THROUGH THE SKIN BUT NO APPARENT REASON FOR THIS WAS FO	UND. THE SKIN WAS REPAIRED AND THE ANTENNA DOUBLER WAS REPLACED ALONG WITH THE ANTENNA AND THE AIRCRAFT WAS RETURNED TO 	SERVICE.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005090800044	20050908	00044	EA  	2005	9	8	CA050817007      	1	20050719	G	1410	TA3050052403	BLOCK           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FAIRLEAD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION AME FOUND DAMAGE ON NR 2 HYDRAULIC SUCTION LINE UPSTREAM OF RESERVOIR DAMAGE CAUSED BY WORN F	AIRLEAD BLOCK ALLOWING HYD SUCTION LINE TO CHAFE ON CASE DRAIN LINE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005090800045	20050908	00045	EA  	2005	9	8	CA050817008      	1	20050719	G	1410	601R7528651	BLOCK           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FAIRLEAD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION AME FOUND DAMAGE ON NR 2 HYDRAULIC CASE DRAINLINE UPSTREAM OF RESERVOIR.  DAMAGE CAUSED BY WO	RN FAIRLEAD BLOCK ALLOWING HYDCASE DRAIN LINE AND SUCTION LINE TO CHAFE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005090800046	20050908	00046	WP  	2005	9	8	CA050817009      	1	20050812	G	2697	702054	WIRE            			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	FIRE DETECTOR	SHORTED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHILE AIRCRAFT WAS IN CRUISE, THE FIRE INDICATOR LIGHT FOR THE LT ENGINE ILLUMINATED. THE PILOT RELEASED THE RETAR	DANT LOAD, THROTTLED THE ENGINE BACK AND SHUTDOWN THE ENGINE.  WHEN THE ENGINE WAS SHUTDOWN THE WARNING LIGHT EXTINGUISH	ED. THE AIRCRAFT RETURNED TO BASE. DURING INVESTIGATION BY MAINTENANCE THE FIRE DETECTOR WIRE WAS INDICATING A PARTIAL S	HORT.  THE FIRE DETECTOR WIRE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2005090800047	20050908	00047	WP  	2005	9	8	CA050817010      	1	20050812	G	3242	148144	SEAL            	BENDIX      	147515      	GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	BRAKE SEAL	BLOWN           	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA						C2504					(CAN) AFTER TAKEOFF THE PILOT NOTICED FLUID LEAKING FROM THE LT BRAKE.  UPON LANDING THE PILOT NOTICED THERE WAS NO FEED	 BACK FROM THE LT BRAKE PEDAL. THE AIRCRAFT LANDED UNEVENTFULLY.  DURING INVESTIGATION MAINTENANCE NOTED THAT THE BRAKE 	SEAL HAD BLOWN.  THE BRAKE ASSY WAS REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2005090800048	20050908	00048	EU  	2005	9	8	CA050818003      	1	20050809	G	5312		BULKHEAD        			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	NLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29840								(CAN) CRACK ON FRONT PRESSURE BULKHEAD LT VERTICAL WEB, AT LT NOSE GEAR TRUNNION ATTACHMENT BRACKET TOP CENTER BOLT HOLE	.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2005091200223	20050912	00223	CE  	2005	9	12	CA050818004      	1	20050818	G	1430	NAS14740	BOLT            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORT: NO BRAKE ON RT SIDE OF AIRCRAFT.  BRAKE PEDDLE WAS SOLID, NO TRAVEL.  INSPECTION REVEALED THAT THE O	B MLG CLAMP AFT BOLT HAD SNAPPED ALLOWING THE GEAR TO COME LOOSE.  THE MAIN LANDING GEAR HAD PINCH OFF THE SOLID ALUMINU	M BRAKE LINE.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2005091200224	20050912	00224	NM  	2005	9	12	CA050819001      	1	20050819	G	2910	DSC1896	CHECK VALVE     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 HYD SYSTEM	LEAKING         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) AN OPERATOR EXPERIENCED A LOSS OF HYDRAULIC SYSTEM NR 2, IN FLIGHT, DUE TO A FRACTURED CHECK VALVE.  A VISUAL INSP	ECTION OF THE CHECK VALVE REVEALED A CRACK AROUND THE CIRCUMFERENCE OF THE VALVE BODY.  THE CHECK VALVE IS BEING RETURNE	D TO MFG FOR INVESTIGATION.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005091200225	20050912	00225		2005	9	12	CA050819002      	4	20050818	G	2330	50401100003	DISPLAY         			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 17F	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING AIRCRAFT BOARDING, THE CREW WAS ADVISED THAT THE VDU AT SEAT 17F WAS SMOKING, THE SYSTEM WAS TURNED OFF.   	MAINTENANCE REPLACED THE VDU AND CHECKED THE SYSTEM SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MFG AND A COMPL	ETE TEARDOWN REPORT WILL BE REQUESTED.  THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005090600081	20050906	00081	NM  	2005	9	6	CA050819003      	1	20050816	G	2424	69187094	REGULATOR       			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					AC SYSTEM	UNSERVICEABLE   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			63988								(CAN) AIRCRAFT EXPERIENCED LOSS OF NR 1 GENERATOR SYSTEM ON APPROACH. THE FLAP INDICATION SYSTEM INDICATED A FLAP OUT OF	 ASYMMETRIC CONDITION CA USING THE CREW TO ABORT THE LANDING AND DECLARE AN EMERGENCY. THE AIRCRAFT LANDED SAFELY ON SEC	OND APPROACH AND TAXIED TO THE RAMP.  MAINTENANCE DISCOVERED THAT THE NR 1 GENERATOR SYSTEM VOLTAGE REGULATOR HAD FAILED	. BY THE NR 1 GENERATOR SYSTEM FAILURE, THIS CAUSED A ERRONEOUS FLAP ASYMMETRY FAULT. THE NR 1 VOLTAGE REGULATOR WAS SWA	PPED WITH THE APU VOLTAGE REGULATOR AND THE APU VOLTAGE REGULATOR SYSTEM WAS MEL'D. ALL SYSTEMS CHECKED SERVICEABLE AND 	THE AIRCRAFT WAS RETURNED TO SERVICE.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005090600082	20050906	00082	NE  	2005	9	6	CA050819004      	2	20050819	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSULATION TIP LOOSE.  HASN'T FALLEN OUT YET.  ANOTHER OPERATOR HAS HAD TWO OCCURANCE'S WHERE THE CERAMIC INSULATO	R CAME RIGHT OUT.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005090600083	20050906	00083	NE  	2005	9	6	CA050819005      	2	20050819	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSULATION TIP LOOSE.  HASN'T FALLEN OUT YET.  ANOTHER OPERATOR HAS HAD TWO OCCURANCE'S WERE THE CERAMIC INSULATOR	 CAME RIGHT OUT.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005090600084	20050906	00084	SW  	2005	9	6	CA050819006      	1	20050819	G	3246	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											(CAN) MAIN LEAF SPRING BROKEN AT ALIGNMENT DIMPLE.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005090600085	20050906	00085	SW  	2005	9	6	CA050819007      	1	20050819	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT FLAP WING ROOT CABLE FRAYED AT PULLEY.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005090600086	20050906	00086	SW  	2005	9	6	CA050819008      	1	20050819	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT RUDDER CABLE FRAYED AT CABIN PULLEY.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005090600087	20050906	00087	SW  	2005	9	6	CA050819009      	1	20050819	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT RUDDER CABLE FRAYED AT CABIN PULLEY.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005090600088	20050906	00088	SW  	2005	9	6	CA050819010      	1	20050819	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT RUDDER CABLE FRAYED AT CABIN PULLEY.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005090600089	20050906	00089	SW  	2005	9	6	CA050819011      	1	20050819	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT FLAP CABLE FRAYED AT WING ROOT PULLEY.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005091200226	20050912	00226	SW  	2005	9	12	CA050819012      	1	20050819	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT FLAP CABLES FRAYED AT WING ROOT PULLEYS.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005091200227	20050912	00227	CE  	2005	9	12	CA050822002      	1	20050812	G	8011		DRIVE ASSY      	LAMAR       		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	STARTER	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA						85021709					(CAN) PIC REPORTED A METAL GRINDING NOISE AT SECOND ATTEMPT TO START AIRCRAFT.   FURTHER INVESTIGATION FOUND STARTER TOO	TH MISSING AND TOOTH DRIVE CRACKED AND BROKEN IN SEVERAL SPOTS.  RING GEAR FOUND MISSING TOOTH AND SEVERAL OTHER TEETH W	E  RE CHIPPED.  ALL PARTS (STARTER AND RING GEAR) REPLACED WITH SERVICEABLE PARTS.  AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2005091200228	20050912	00228	WP  	2005	9	12	CA050822003      	2	20050818	G	7200		ENGINE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  		MAKING METAL    	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								P44738			(CAN) UPON TAKEOFF BEFORE ROTATION, CHIP LIGHT STARTED TO FLICKER.  TAKEOFF ABORTED AND RETURNED TO TERMINAL.  MAINTENAN	CE FOUND BRASS COLORED METAL IN OIL.  ENGINE REPLACED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005091200229	20050912	00229	NM  	2005	9	12	CA050822004      	1	20050820	G	7120	AUL39151	STRAP           			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								30637			(CAN) DURING DAILY INSPECTION, FOUND LOW PRESSURE CASE UPPER ACCESSORY MOUNTING STRAP BROKEN.						2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005091900198	20050919	00198	NE  	2005	9	19	CA050822005      	3	20050822	G	6111	SFA13M1R0AD	BLADE           	HAMSTD      	14SF7       	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							366				(CAN) AIRCRAFT, BLADE RECEIVED FOR MAJOR INSP. DURING INSP OF THE BLADE SHANK IAW CMM, WAS FOUND WITH CORROSION PITTING 	AND ETCHING OF THE ALUMINIUM SURFACE.  DURING INSP OF THE TAPERBORE IAW CMM, CORROSION PITTING WAS FOUND.  ZONE 5 IS NOT	 ALLOWED ANY CORROSION DAMAGE, THERE IS PITTING VISIBLE. THE BLADE MUST BE REMOVED FROM SERVICE IAW CMM, NO CORROSION PI	TTING ALLOWED, THE BLADE IS MARKED TO SHOW THAT IS IN COMPLIANCE WITH FAA AD 96-08-02.  CORROSION IN THE TAPER BORE WAS 	PREVIOUSLY ADDRESSED BY CURRENT FAA AD 96-08-02.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005091200230	20050912	00230	WP  	2005	9	12	CA050822006      	1	20050816	G	5210		DOOR            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	HAMSTD	54H	54H60       	NE  	MAIN PAX	OPEN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, ON TAKEOFF ROLL JUST AT THE POINT OF ROTATION THE MAIN ENTRANCE DOOR OPENED. THE CREW IMMEDIATELY RE	TURNED TO THE AIRPORT AND EXECUTED AN UNEVENTFUL LANDING. THE MAINTENANCE CREW INSPECTED THE DOOR AND SURROUNDING STRUCT	URE, AND CHECKED THE RIGGING OF THE DOOR LOCKING SYSTEM.  NO DEFECTS WERE FOUND AND THE AIRCRAFT WAS RETURNED TO SERVICE	.			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2005091200231	20050912	00231	CE  	2005	9	12	CA050822007      	1	20050805	G	2421	ALX9424	ALTERNATOR      			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) THE ALTERNATOR REAR BEARING FAILED ALLOWING THE ROTOR TO TOUCH THE FIXED COIL WHICH GENERATED ENOUGH HEAT TO BURN 	THE PAINT ON THE COIL.  AN ODOR WAS NOTICED IN THE CABIN.					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
2005091200232	20050912	00232	SO  	2005	9	12	CA050823001      	1	20050822	G	5753	1105031412	SUPPORT         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION, MAINTENANCE FOUND A CRACK IN THE RT FLAP ASYMMETRY TELEFLEX CABLE SUPPORT. THIS SUPPO	RT IS LOCATED ON THE RT FLAP IB SUPPORT AND IS ATTACHING POINT FOR ASYMMETRY DETECTOR TELEFLEX ROD END. FURTHER INVESTIG	ATION, A SECOND CRACK WAS ALSO FOUND ON SAME PART. BOTH CRACKS WERE ADJACENT TO SUPPORT ATTACH BOLT HOLES.  FIRST CRACK 	PROPAGATED FROM UPPER PORTION OF SUPPORT AND MEASURED APPROX 1.25 INCHES IN LENGTH.   SECOND CRACK PROPAGATED FROM LOWER	 PORTION OF SUPPORT, MEASURED APPROX  .25 INCHES IN LENGTH.  THE SUPPORT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVI	CE.	1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2005091200233	20050912	00233		2005	9	12	CA050823002      	4	20050822	G	3416		ALTIMETER       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN ANTENNA WAS REMOVED FOR INSPECTION AND CLEANING, IT CAME APART IN 2 PIECES.  CORROSION WAS FOUND INTERNALLY B	ETWEEN BASE PLATE AND COPPER ANTENNA PLATE.  SUSPECTED CAUSE FOR INTERMITTENT GPWS/RAD ALT SNAGS FOR THE PAST MONTH.  ( 	REFERENCE A/C JOURNEY LOG PAGES : 435367,435362 AND 431947 ) NOTE: THIS PART IS TRACKED AS AN EXPANDABLE PART IN OUR SYS	TEM, THUS WE ARE UNABLE TO DETERMINE THE EXACT TSN AND CYCLE ON UNIT.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005091200234	20050912	00234	CE  	2005	9	12	CA050823003      	1	20050608	G	5414	1294300653	SKIN PANEL      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					PYLON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21900								(CAN) SEVER CORROSION FOUND BETWEEN BONDED MEMBERS OF THE SKIN PANEL ASSY STRETCHING THRU THE ENTIRE LENGTH OF THE PANEL	.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005091200235	20050912	00235	CE  	2005	9	12	CA050823004      	1	20050818	G	2497		WIRE            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FEED BUSS	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) SUB PANEL RT NR 1 CB POPPED CAUSING MULTIPLE SYSTEM FAILURES.  INVESTIGATION FOUND DUAL FEED BUSS HAD AN OPEN.  FU	RTHER INVESTIGATION REVEALED MULTIPLE WIRING ABNORMALITIES FROM POOR MAINTENANCE IN THE PAST, AND ELECTRICAL CONNECTIONS	 LOOSE FROM AGE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005091200236	20050912	00236	GL  	2005	9	12	CA050823005      	2	20050819	G	7260	671657	BEARING         			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X	Y		ENGINE FLAMEOUT           	ENGINE STOPPAGE           		DE	DESCENT        	1			CA								501619			(CAN) WITH AN AIRCRAFT MECHANIC AND 2 FLIGHT ATTENDANTS ON BOARD,  NR 1 ENGINE FLAMED OUT IN DESCENT, AIRCRAFT LANDED SA	FELY AT AIRPORT.  AFTER EVALUATION, THE POWER SECTION ACCESSORIES GEARBOX WAS FOUND AT FAULT, TOWER SHAFT BEARING (RR. I	PC 72-60-00 FIG. 3 ITEM 2 P/N 671657) HAD FAILED. GEARBOX WAS REPLACED AND AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2005091200237	20050912	00237	CE  	2005	9	12	CA050823006      	1	20050815	G	5248		DOOR            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					TAILCONE	STIFF           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS PARKED IN HEAVY RAIN WAITING FOR PASSENGERS.  DURING CRUSE THE FLIGHT CREW NOTICED ELEVATOR CONTR	OLS STIFF/ FROZEN.  CONTROLS FREED UP DURING DESCENT AS THEY ENTERED WARMER AIR.  INVESTIGATION ON THE GROUND FOUND LARG	E QUANTITIES OF WATER AND ICE IN THE TAIL NEXT TO THE PRESSURE BULKHEAD.  LOW POINT IN THE CABLE RUN AND IN THE TAIL CON	E.  DETAILED INVESTIGATION FOUND THE DOUBLERS INSTALLED AFTER THE DUAL STRAKE CONVERSION HAD COVERED THE DRAIN HOLES FOR	 THE TAIL AND TAIL CONE, ALLOWING WATER TO POOL.		1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005091200238	20050912	00238	WP  	2005	9	12	CA050823007      	1	20050819	G	5240		HOOK            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	SERVICE DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WITH AN AIRCRAFT MECHANIC AND 2 FLIGHT ATTENDANTS ON BOARD, THE REAR SERVICE DOOR OPEN WARNING LIGHT CAME ON AT 14	,000 FEET.  AIRCRAFT DEPRESSURIZE AND RETURN TO DEPARTURE.  INVESTIGATION REVEALED THAT LOWER REAR HOOK WAS NOT GOING IN	 PLACE PROPERLY, DOOR WAS RE-RIGGED IAW MM FIG. 3.2.103.  AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2005091200239	20050912	00239	WP  	2005	9	12	CA050823008      	1	20050822	G	2410	ALX8421LS	ALTERNATOR      			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO BLADES LET GO ON THE COOLING FAN OF THE ALTERNATOR.  PILOT DISCOVERED THIS DURING HIS DAILY INSPECTION.  ONE O	F THE BLADES WAS LODGED IN THE LOWER ENGINE COWL. THE SECOND BLADE WAS NOT FOUND.  NO DAMAGE WAS FOUND ON ANY OTHER AREA	 OF THE AIRCRAFT.				1	G	7	1 	3O	3	O		H11NM   	E295				 
2005100600075	20051006	00075	NE  	2005	10	6	CA050824001      	2	20050731	G	7200		ENGINE          								PWA   	PW120 	PW123       	 	NE  						FLAMED OUT      	W				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			CA								AF0052			(CAN) ON CLIMB FOLLOWING A WATER DROP, THE ENGINE FLAMED OUT AND THE PROPELLER AUTO-FEATHERED.  THE MECHANICAL FUEL CONT	ROL UNIT AND FUEL PUMP WERE SUBSEQUENTLY REPLACED.  PWC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI	SHED.									4	T			E20NE				 
2005100600076	20051006	00076	EA  	2005	10	6	CA050824002      	2	20050801	G	7261		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								FA0098			(CAN) THE ENGINE WAS SHUT DOWN IN FLIGHT FOLLOWING A LOW ENGINE OIL PRESSURE INDICATION.  SUBSEQUENT INSPECTION REVEALED	 METALLIC DEBRIS ON THE REDUCTION GEARBOX CHIP DETECTOR.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE 	ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005100600077	20051006	00077	NE  	2005	10	6	CA050824003      	2	20050729	G	7261		TUBE            			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					OIL SCAVENGE	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								127109			(CAN) IN CRUISE, THE ENGINE EXHIBITED VERY LOW ITT AND OIL PRESSURE. THIS WAS FOLLOWED BY A FIRE WARNING ANNUNCIATION AN	D THE CREW SHUT THE ENGINE DOWN IN FLIGHT AND DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A FRACTURE	D 6&7 BEARING OIL SCAVENGE TUBE, FRACTURED POWER TURBINE BLADES, EXTERNAL OIL LEAKAGE AND EVIDENCE OF AN EXTERNAL FIRE. 	 P&WC WILL INVESTIGATE THE EVENT AND ADVISE O F ROOT CAUSE ONCE DEFINED.			2	H	7	2 	4T	4	T	RT	        	E20NE				 
2005100600078	20051006	00078	EA  	2005	10	6	CA050824004      	2	20050804	G	7230		STRUT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					COMPRESSOR CASE	CRACKED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								FA0214			(CAN) DURING CRUISE, SMOKE IN THE CABIN AIR BECAME EVIDENT.  THE FLIGHT WAS DIVERTED AND AN EMERGENCY WAS DECLARED CULMI	NATING IN THE EVACUATION OF THE AIRCRAFT ON LANDING.  SUBSEQUENT INSPECTION REVEALED A CRACKED INTER-COMPRESSOR CASE STR	UT AND MATERIAL MISSING FROM THE COMPRESSOR INNER SUPPORT.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONC	E CONFIRMED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005100600079	20051006	00079	NE  	2005	10	6	CA050824005      	2	20050621	G	7322	8197355	FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) IN CRUISE, THE ENGINE EXHIBITED A 2% ROLL-BACK IN N1 SPEED WITH NO RESPONSE TO THROTTLE INPUT.  FOLLOWING A DESCEN	T TO 10,000 FEET, THE ENGINE RECOVERED AND RESPONDED NORMALLY.  THE MECHANICAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLAC	ED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2005100400001	20051004	00001	EU  	2005	10	4	CA050824006      	1	20050803	G	3610		FITTING         			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					PNEUMATIC SYS	LOOSE           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON APPROACH, THE CREW NOTED A VIBRATION/SHUDDER WITH A CORRESPONDING DECREASE IN ENGINE AND MAIN ROTOR SPEEDS AND 	A LOW ROTOR WARNING ANNUNCIATION. THIS CALUMNIATED IN A HARD LANDING.  SUBSEQUENT INSPECTION REVEALED LOOSE PNEUMATIC FI	TTINGS ON THE ENGINE FUEL GOVERNING SYSTEM.  THE ENGINE AND CONTROLS WERE REMOVED FOR FURTHER INVESTIGATION.  PWC WILL I	NVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.			1	G	7	2 	3U	3	T		H7EU    	E2NE				 
2005100400002	20051004	00002	NE  	2005	10	4	CA050824007      	2	20050720	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								17302			(CAN) IN CRUISE, THE ENGINE EXHIBITED AN UNCOMMANDED INCREASE IN ITT.  ENGINE POWER WAS REDUCED TO IDLE AND THE AIRCRAFT	 DIVERTED FOR AN UNSCHEDULED LANDING.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE, ONCE DETERM	INED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005100400003	20051004	00003	EA  	2005	10	4	CA050824008      	2	20050806	G	7230		BLADES          			PILATS	PC6   	PC6         	7090102	EU  	PWA   	PT6   	PT6A20      	52043	EA  					COMPRESSOR	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			C			F.O.D.                    			CL	CLIMB          	1			CA								22072			(CAN) DURING CLIMB, THE ENGINE EXHIBITED A SQUEALING NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WA	S SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED COMPRESSOR AND POW	ER TURBINE BLADE DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	H	7	1 	3O	3	T		7A15    	E4EA				 
2005100400004	20051004	00004	NE  	2005	10	4	CA050824009      	2	20050810	G	7200		TURBINE BLADES  			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					POWER TURBINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								123087			(CAN) FOLLOWING TAKEOFF, THE ENGINE DEVELOPED HIGH VIBRATIONS ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE	 WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER 	TURBINE BLADES.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005091300131	20050913	00131	CE  	2005	9	13	CA050824010      	1	20050815	G	2750	1013800006	DRIVE ASSY      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	TE FLAPS	SHEARED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AC HAD JUST LANDED, SELECTED FLAPS UP, STOPPED BETWEEN APPROACH AND ZERO (FULL UP).  PILOT CALLED MAINT, WAS INSTR	UCTED TO TRY SPLIT FLAP BYPASS SYS, INFORMED MAINT THAT ALL FLAPS WENT UP EXCLUDING THE RT OB.  ASSUMED THAT FLAP DRIVE 	CABLE WAS SHEARED.  AME`S WERE SENT TO INSPECT SYS, CONFIRMED SHEARED CABLE.  RT FLAP WAS SECURED IN FULL UP POSITION, F	LAP SYS DEFERRED AND AC WAS FLOWN BACK TO MAIN MAINT FACILITY.  AFTER CABLE WAS REPLACED ALL NECESSARY CHECKS WERE COMPL	ETED, NO OTHER FAULTS WERE FOUND.  CAUSE OF CABLE FAILURE WAS CORROSION DUE TO TRAPPED MOISTURE.  UPON FURTHER INVESTIGA	TION OF RECORDS IT TURNS OUT THAT CABLE WAS THE NEWEST OF THE 3 CABLES INSTALLED.  MFG HAS BEEN NOTIFIED, PICTURES SENT.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005091500007	20050915	00007	NE  	2005	9	15	CA050824011      	2	20050820	G	7261	575776	LINE            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE OIL	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA								676467			(CAN) AC WAS INVOLVED IN LOGGING OPS.   AS AC WAS APPROACHING LOG LANDING, PILOTS WERE NOTIFIED THAT WHITE SMOKE WAS COM	ING FROM NR 2 ENG.  AC PROCEEDED TO SERVICE LANDING TO HAVE MAINT CREW LOOK AT PROBLEM.  ENROUTE, COPILOT NOTICED WHITE 	SMOKE COMING FROM ENG WAS INCREASING. COMMAND PILOT ELECTED TO CARRY OUT AN INFLIGHT SHUTDOWN OF NR2 ENG AS A PRECAUTION	ARY MEASURE. AC CONTINUED ON TO ITS SERVICE LANDING AND MADE A SINGLE ENGINE LANDING. UPON INSPECTION OF ENG, MAINT CREW	 DISCOVERED THAT OIL TUBE RUNNING FROM ENG OIL PUMP TO OIL COOLER HAD DEVELOPED CRACK AT B-NUT ATTACHMENT END OF TUBE.  	ENGINE HAD NOT BEEN STARVED OF OIL. TUBE WAS REPLACED, OIL RESERVOIR WAS REPLENISHED, AC WAS RETURNED TO SERVICE.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005091300142	20050913	00142	CE  	2005	9	13	CA050824012      	1	20050803	G	2730	115610010325	TORQUE TUBE     			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) WHILE CARRYING OUT A PHASE 2 AND 3 INSPECTION, THE RT ELEVATOR TORQUE TUBE HAD A .5 INCH CRACK. THE CRACK WAS DISC	OVERED BETWEEN THE ELEVATOR AND TORQUE TUBE.  THE TORQUE TUBE WAS REPLACED.					1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005091300143	20050913	00143	EA  	2005	9	13	CA050824013      	2	20050809	G	7261	69675	CONNECTOR       			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C172	1C172TM     	GL  	OIL SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) OIL LEAK DISCOVERED.  UPON LANDING, THE PILOT NOTICED THAT THERE WAS OIL IN THE WHEEL PAN.  THE PILOT CARRIED OUT 	ONE MORE FLIGHT AND THE LEAK WAS REPAIRED AT A FACILITY.  VERIFICATION REVEALED THAT THE CONNECTOR ASSEMBLY TO THE HSG C	OOLER INLET HOSE WAS CRACKED, AND ONCE IT WAS REMOVED, IT EMPTIED ALL ITS OIL.   REPLACED THE CONNECTOR (P/N 69675) AND 	THE ANNULAR GASKET (P/N STD 294).			1	H	7	1 	3O	3	O	NT	A13CE   	E274	5	N	P910	 
2005100400005	20051004	00005	NE  	2005	10	4	CA050824014      	2	20050811	G	7250		TURBINE BLADES  								PWA   	PT6   	PT6A68      	 	NE  					POWER SECTION	DAMAGED         	W				E				ENGINE SHUTDOWN         				B	C	J	SMOKE/FUMES/ODORS/SPARKS  	F.O.D.                    	WARNING INDICATION        	NR	NOT REPORTED   	1			CA								RA0086			(CAN) THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY SPARKS FROM THE EXHAUST.  THE ENGINE WAS SECURED IN FLIGHT AND A DE	AD-STICK LANDING CARRIED OUT.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND SEIZURE OF THE POWER SE	CTION.  P&WC WILL INVESTIGATE THIS EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.									4	T			E26NE				 
2005100400006	20051004	00006	EU  	2005	10	4	CA050824015      	1	20050808	G	2435		PACKING         			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					STARTER	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, A LOW ENGINE OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT I	NSPECTION REVEALED A DAMAGED STARTER, GENERATOR SHAFT O-RING SEAL.					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005100400007	20051004	00007	NE  	2005	10	4	CA050824016      	2	20050820	G	7261		ENGINE          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  						LACK OF LUBE    	W				A				UNSCHED LANDING         				K	X	J	FLUID LOSS                	ENGINE FLAMEOUT           	WARNING INDICATION        	CL	CLIMB          	1			CA								PR0114			(CAN) FOLLOWING TAKEOFF, THE LOW ENGINE OIL PRESSURE WARNING ANNUNCIATED FOLLOWED BY AN UNCOMMANDED REDUCTION IN POWER. 	 FUEL CONTROL MANUAL OVERRIDE WAS ENGAGED AFTER WHICH FLAMES WERE EMITTED FROM THE EXHAUST AND THE ENGINE FLAMED OUT.  S	UBSEQUENT INSPECTION REVEALED NO OIL REMAINING IN THE ENGINE AND SEIZURE OF THE POWER SECTION.  PWC WILL INVESTIGATE THI	S EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2005100400008	20051004	00008	EA  	2005	10	4	CA050824017      	2	20050819	G	7261		ENGINE          			PILATS	PC6   	PC6         	7090102	EU  	PWA   	PT6   	PT6A27      	52043	EA  						LACK OF LUBE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA								51996			(CAN) IN CLIMB, ENGINE TORQUE WAS REPORTED TO FLUCTUATE FOLLOWED BY WHITE SMOKE EMANATING FROM THE EXHAUST.  THE ENGINE 	WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED LOW ENGINE OIL QUALITY AND TORSION DAMAGE OF THE EXHAUST CASE. 	 THE ENGINE HAD BEEN OVERHAULED 12 HOURS PRIOR TO THE INCIDENT.  PWC WILL MONITOR THE INVESTIGATION OF THIS EVENT AND AD	VISE OF ROOT CAUSE ONCE ESTABLISHED.			1	H	7	1 	3O	4	T		7A15    	E4EA				 
2005091300144	20050913	00144	CE  	2005	9	13	CA050824018      	1	20050823	G	2910	661707720	LINE            			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					HYDRAULIC SYS	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING PHASE 5 INSP, 2 HYDRAULIC LINES FOUND CHAFING ON STRUCTURE. P/N 6617077-19 AND 20. REF.   AC MFG PROVIDED E	NG MFG WITH DRAWING TO INSTALL MISSING LINE SUPPORT HARDWARE TO PREVENT CHAFING.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2005100400009	20051004	00009	EA  	2005	10	4	CA050824019      	2	20050807	G	7414	1016301010R	MAGNETO         			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								RL1362148C			(CAN) DURING A ROUTINE COMPANY FLIGHT, THE NR 1 ENGINE STARTED RUNNING ROUGH.  THE AIRCRAFT LANDED AND CALLED MAINTENANC	E.  UPON INSPECTION THE LT MAG WAS FOUND SEPARATED IN TWO, THE REAR HALF WAS STILL BOLTED TO THE ENGINE PAD AND THE FRON	T HALF WAS HANGING BY THE IGNITION LEADS.  THE MAG WAS REPLACED AND TIMED WITH THE AIRCRAFT AND RETURNED TO SERVICE.				1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA	 
2005091300145	20050913	00145	WP  	2005	9	13	CA050824020      	1	20050821	G	2697	356080765	WIRE            			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13H     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	NR 2 FIRE DETECT	SHORTED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT, NR 2 ENGINE ZONE 1 FIRE LIGHT ILLUMINATED AND BELL SOUNDED. THE ENGINE WAS E-HANDLED, NO OTHER IN	DICATION OF FIRE WAS EVIDENT. THE AIRCRAFT LANDED SAFELY. DURING INVESTIGATION BY MAINTENANCE STAFF THE FIRE ELEMENT P/N	 35608-0-765 WAS INDICATING A SHORT. THE ELEMENT WAS REPLACED AND THE SYSTEM TESTED SERVICEABLE. THE AIRCRAFT WAS RETURN	ED TO SERVICE.			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2005091300146	20050913	00146	EA  	2005	9	13	CA050825001      	2	20050817	G	8530	LW19047	RING            			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 3 CYLINDER	FAILED          	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								L2576651A			(CAN)  HEAVY OIL CONSUMPTION CYLINDER NR 3.  OIL RING NOT PERFORMING ITS WORK. REMOVED AND SENT FOR REPAIR.   REINSTALLE	D CYLINDER.					1	G	7	1 	3O	3	O		4H12    	1E10				 
2005091300147	20050913	00147		2005	9	13	CA050825002      	4	20050824	G	2330	50401100003	DISPLAY         			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON AUGUST 24, 2005 A/C WAS IN CRUISE WHEN THE CREW WAS ADVISED THAT THE VDU AT SEAT 17C HAD QUIT WORKING AND THE P	ASSENGER SMELLED SMOKE. THE IFE SYSTEM WAS TURNED OFF AT THIS POINT.  MAINTENANCE REPLACED THE VDU AND CHECKED THE SYSTE	M SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THI	S SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005091300148	20050913	00148	NM  	2005	9	13	CA050825003      	1	20050821	G	2760	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT IB SPOILER	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			12639								(CAN) AT LINE UP FOR TAKEOFF CREW OBSERVED NR 1 HYD SYSTEM AND IB ROLL SPOILER CAUTION LIGHTS ILLUMINATED.   AIRCRAFT RE	TURN TO BLOCKS.  INVESTIGATION REVEALED SIGNIFICANT HYDRAULIC LEAKAGE FROM THE AREA OF THE RT IB SPOILER ACTUATOR.  CLOS	ER INSPECTION OF THE SPOILER ACTUATOR REVEALED A METAL FATIGUE FAILURE OF THE SPOILER ACTUATOR BODY ALLOWING LIBERATION 	OF THE FLUID CONTENT OF THE NR 1 HYDRAULIC SYSTEM. THE FAILED SPOILER ACTUATOR WAS REPLACED AND FOLLOWING APPROPRIATE MA	INTENANCE CHECKS THE AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005091300149	20050913	00149	EA  	2005	9	13	CA050825004      	1	20050819	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT SIDE WINDOW CRACKED IN FLIGHT.  A/C LANDED.  A/C FERRIED FOR WINDOW REPLACMENT.  WINDOW REMOVED AND INSTALLED =	 P/N NP139322-12, S/N 05200H6110.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005100400010	20051004	00010	EU  	2005	10	4	CA050825005      	1	20050819	G	2913		DRIVE ASSY      			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	WORN            	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) HYD WARNING HORN AND LIGHT CAME ON IN FLIGHT.  PILOT FOLLOWED LOST HYD PROCEDURE AND RETURNED TO BASE AND SHUT DOW	N.  INVESTIGATION SHOWED THAT THE HYD PUMP DRIVE SPLINES WERE COMPLETLY WORN.  PUMP, COUPLING AND BEARING CHANGE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005100400011	20051004	00011	NE  	2005	10	4	CA050825006      	2	20050819	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								4432			(CAN) DURING INSPECTION, IGNITERS WERE FOUND TO HAVE BROKEN INSULATORS.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005091300150	20050913	00150	NE  	2005	9	13	CA050826001      	2	20050819	G	7311	702101600641	HEAT EXCHANGER  			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF34*       	 	NE  					FUEL/OIL	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING TROUBLESHOOTING TO FIND CAUSE FOR LOW OIL PRESSURE AT HIGH POWER IT WAS DISCOVERED THAT THE OIL HAD BECOME 	CONTAMINATED WITH FUEL AND SUBSEQUENTLY LOWERED IN VISCOSITY CAUSING LOW OIL PRESSURE READINGS. THE OIL TO FUEL HEAT EXC	HANGER, FUEL HEATER/OIL COOLER HAD FAILED INTERNALLY AND WAS ALLOWING HIGHER PRESSURE FUEL TO CONTAMINATE THE ENGINE OIL	 SYSTEM. THE UNIT WAS REPLACED, ENGINE OIL CHANGED AND THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2005091300151	20050913	00151	SO  	2005	9	13	CA050826002      	2	20050815	G	7414	M3114C120783	COIL            	SLICK       	4201        	CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	LT MAGNETO	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						4019238R					(CAN) RAN ROUGH SLIGHTLY MORE PROP THAN NORMAL.  MAG DROP, WEAK SPARK,  ABOUT .3333 OF NORMAL STRENGTH.  OVERHAULED MAG 	WAS INSTALLED, 900 HOUR PREVIOUSLY.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2005100400012	20051004	00012	NE  	2005	10	4	CA050826003      	2	20050825	G	8530		CYLINDER        			DOUG  	DC4   	C54GDC      	3021534	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								P106820			(CAN) NR 10 CYLINDER CRACKED AT THE EXHAUST VALVE SIDE AND MADE ENGINE RUN A LITTLE ROUGH.  ENGINE WAS SHUT DOWN PRECAUT	IONARY AND THE CYLINDER WAS REPLACED.					2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
2005091300152	20050913	00152		2005	9	13	CA050826004      	4	20050825	G	2330	50401100003	DISPLAY         			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON AUGUST 25, 2005 A/C WAS IN CRUISE WHEN THE CREW WAS ADVISED THAT THE VDU AT SEAT 22B WENT BLANK WITH THE SMELL 	OF SMOKE.  THE IFE SYSTEM WAS TURNED OFF.  MAINTENANCE REPLACED THE VDU AND THE SYSTEM TESTED SERVICEABLE.  THIS COMPONE	NT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE 	THAT INFORMATION IS AVAILABLE.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005100400013	20051004	00013	NE  	2005	10	4	CA050826005      	2	20050824	G	7322	189111	HMU             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ENGINE EXHIBITED VIBRATION AND LOUD BANGING NOISES ON COMMANDED POWER MODULATION.  ENGINE POWER 	WAS REDUCED TO FLIGHT, IDLE AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE HYDROMECHANICAL FUEL CONTROL UNIT WAS 	SUBSEQUENTLY REPLACED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2005100400014	20051004	00014	GL  	2005	10	4	CA050826007      	2	20050728	G	7320	23061824	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A GROUND RUN UP, AIRCRAFT STARTED HOT AND FUEL WAS LEAKING FROM A HOLE WITH IN THE FCU BODY.  THE FCU WAS R	EMOVED AND AIRCRAFT STARTED NORMALLY AND NO FURTHER ISSUES APPEARED.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005100400015	20051004	00015	GL  	2005	10	4	CA050826008      	2	20050818	G	7323	2549170	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					POWER TURBINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING POST INSPECTION GROUND RUNS, THE AIRCRAFT GOVERNOR WOULD NOT RECOVER FROM DROOPING OFF.  THE GOVENOR WAS RE	PLACED AND AIRCRAFT WAS RETURNED TO THE FLIGHTLINE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005100400016	20051004	00016	EA  	2005	10	4	CA050826009      	2	20050701	G	7320	324472110	FUEL CONTROL    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING POST INSPECTION RUN UP, THE NR 2 ENGINE WOULD NOT START.  THE AFCU WAS REPLACED AND FURTHER GROUND RUNS CAR	RIED OUT AND ENGINE STARTED WITH NO FURTHER PROBLEMS.  THE AIRCRAFT WAS RETURNED TO THE FLIGHT LINE.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005091300153	20050913	00153	CE  	2005	9	13	CA050829001      	1	20050825	G	5311	5042002847	DOUBLER         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21356								(CAN) DURING THE CONTINUING AIRWORTHINESS STRUCTURAL INSPECTION A CRACK WAS FOUND IN THE FLOOR LEVEL DOUBLER FOR THE LT 	FRAME AT FUSELAGE STATION 207.00, THE CRACK MOVED LATERALLY ACROSS THE DOUBLER FROM THE IB SIDE THOUGH 2 RIVET HOLES AND	 A BEND. THE PROBABLE CAUSE IS THAT THE DOUBLER HAD A PILOT HOLE THAT WAS DIRECTLY ADJACENT TO A RIVET HOLE WITH NO EDGE	 DISTANCE. THE CRACK WAS ABOUT 3.5 INCHES LONG.			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2005091300154	20050913	00154	EU  	2005	9	13	CA050829002      	1	20050825	G	5697	K61	WIRE            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	WINDSHIELD HEAT	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CO-PILOTS WINDSHIELD, NR 4 AREA, FAILED ON LOW SELECTION.  HIGH HEAT WAS SELECTED AND ELECTRICAL BURNED SMELL WAS 	DETECTED.  SYSTEM WAS SHUTOFF AND TRIP CONTINUED WITHOUT INCIDENT.  MAINTENANCE TROUBLESHOOTING FOUND THE PROBLEM TO BE 	RELAY K61 WHEN IT WAS LOCATED THE WIRE FROM RELAY TO WINDSHIELD WAS FOUND BURNED AND LOOSE ON THE RELAY.  THE WIRE WAS R	EPLACED AND SYSTEM TESTED AND RETURNED TO SERVICE.			1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
2005091300155	20050913	00155	CE  	2005	9	13	CA050829003      	1	20050825	G	5312		BULKHEAD        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21356								(CAN) DURING THE CONTINUING AIRWORTHINESS STRUCTURAL INSPECTION CHAFFING DAMAGE WAS FOUND ON THE AFT SIDE OF THE AFT PRE	SSURE BULKHEAD. THE LOWER CENTER AND THE LOWER RT INTERCOSTALS RUBBING ON THE BULKHEAD DURING PRESSURIZATION CAUSED THE 	DAMAGE. FURTHER INVESTIGATION (EDDY CURRENT) FOUND THAT THE BULKHEAD WAS CRACKED AT THE CENTER INTERCOSTAL LOCATION.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2005091300156	20050913	00156	EA  	2005	9	13	CA050829004      	2	20050823	G	8520		CRANKCASE       			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION, CHECKING FOR OIL LEAK, A CRACK IN THE CRANKCASE WAS FOUND. FRONT LT SIDE FORWARD OF NR 2 CYLINDER.						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
2005091300157	20050913	00157		2005	9	13	CA050829005      	4	20050824	G	2330	50401100003	DISPLAY         			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 4E	INOPERATIVE     	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AC WAS IN CRUISE WHEN THE CREW WAS ADVISED THAT THE VDU AT SEAT 4E SMOKED.  THE IFE SYSTEM WAS TURNED OFF.  MAINTE	NANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A	 COMPLETE TEARDOWN REPORT WILL BE REQUESTED.  THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005100400017	20051004	00017	EA  	2005	10	4	CA050830001      	2	20050826	G	8500		ENGINE          			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	NR 2	MAKING METAL    	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA								PC10234C			(CAN) DURING CRUISE ON FLIGHT, THE AIRCRAFT WAS APPROXIMATELY 90 MILES FROM BASE WHEN THE NR 2 ENGINE BEGAN BACKFIRING A	ND RUNNING ROUGH.  THE ENGINE WAS SHUT DOWN AND THE PROPELLER WAS FEATHERED.  THE AIRCRAFT RETURNED TO BASE AND LANDED U	NEVENTFULLY.  MAINTENANCE CREW FOUND METAL IN THE MAIN OIL SCREEN DURING INVESTIGATION.  THE ENGINE WAS REPLACED AND THE	 AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2005091300158	20050913	00158	SO  	2005	9	13	CA050830002      	1	20050823	G	5280	37722002	ROD END         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LINKAGE CRACK AT WELD JOINT AT LT MAIN LANDING DOOR ATTACHMENT.   PARTS REPLACED.  GEAR RETRACTION C/O.  NO PROBLE	M FOUND.					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2005100400018	20051004	00018	EA  	2005	10	4	CA050830003      	1	20050821	G	2700	601A913703	LINK            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					FLT CONTROLS	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING AIRCRAFT 1ST 12/24 MONTH INSPECTION, DISCOVERED RT AILERON CABLE FOUND INCORRECTLY ROUTED RESULTING IN CHAF	ING OF AUTOPILOT SYNCRO INPUT LINK.  CABLE INSPECTED NFF AND RE-ROUTED.  AREA LAST ACCESSED BY BOMBARDIER SERVICE CENTER	, FOR AILERON PCU CHANGE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005100400019	20051004	00019	EA  	2005	10	4	CA050830005      	2	20050830	G	7230		COMPRESSOR      			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								FA0085			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE ENGINE INL	ET AND LOW PRESSURE COMPRESSOR.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005100400020	20051004	00020	SW  	2005	10	4	CA050830006      	1	20050829	G	2910	2780322044	LINE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT CREW NOTICED HYD FLUID LEAKING FORM THE LEFT SIDE OF THE NACELLE.  MAINTENNACE INSPECTED LEAK AND FOUND UP 	GEAR HYD LINE FROM POWER PACK TO GEAR ACTUATORS LEAKING.  CRACKED IN 90 DEGREE BEND RADIUS.  LINE REPLACED,GEAR SWINGS C	ARRIED OUT AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
2005100400021	20051004	00021	EU  	2005	10	4	CA050830008      	1	20050830	G	3270	1090372231	SKID            			AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL	CORRODED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) TAIL SKID BROKEN DUE TO CORROSION.						1	G	7	2 	3U	3	U		H7EU    	E4CE				 
2005100400022	20051004	00022	EA  	2005	10	4	CA050831001      	2	20050829	G	7414	1051676TCM	CAPACITOR       			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O320  	O320A2B     	41508	EA  					MAGNETO	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED IGNITION PROBLEMS WHEN OPERATING ENGINE ON RIGHT HAND MAGNETO.  ALL IGNITION COMPONENTS INSPECTED A	ND TESTED INCLUDING CAPACITOR.  CAPACITOR ELECTRICALLY TESTED TO 0.358 MICRO FARADS.  THIS VALUE IS ABOVE THE MAINTENANC	E VALUE OF A 0.300 MICRO FARAD MINIMUM.  IGNITION SYSTEM RE-INSTALLED ON ENGINE.  DURING ENGINE RUN UP PROBLEMS PERSISTE	D. NO EVIDENCE OF A DEFECTIVE CAPACITOR WERE FOUND ON THE SURFACE CONDITION OF THE BREAKER POINTS. DUE TO EXPERIENCE WIT	H SIMILAR CIRCUMSTANCES, CAPACITOR REPLACED WITH NEW KELLY AEROSPACE CAPACITOR P/N 10-51676.  SUBSEQUENT RUN UP CONFIRME	D CAPACITOR TO HAVE BEEN SOURCE OF IGNITION TROUBLES.	1	H	7	1 	3O	3	O		A780    	E274				 
2005100400023	20051004	00023	WP  	2005	10	4	CA050831002      	1	20050803	G	6210	369D21100517	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20C     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PILOT'S POST FLIGHT INSPECTION A CRACK WAS DETECTED IN THE LOWER SKIN OF MAIN ROTOR BLADE NR 1.  THE CRACK 	IS LOCATED 11' FROM THE INBOARD END (ROOT FITTING) OF THE BLADE, AND 3' AFT OF THE LEADING EDGE.  THE CRACK WAS 3' LONG 	AND WITHIN 1' OF THE TRAILING EDGE.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005100400024	20051004	00024	GL  	2005	10	4	CA050831003      	2	20050829	G	7397	TLF816	CONNECTOR       			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) WHEN THE PILOT WAS CONDUCTING HIS PREFLIGHT CHECK HE NOTICED THAT THE THROTTLE LEVER FOR NR 2 ENGINE WAS ROUGH BET	WEEN SHUTOFF AND GROUND IDLE. UPON INVESTIGATION OF THE THROTTLE LINKAGE, IT WAS DISCOVERED THAT ONE OF THE LOCK TANGS O	N THE THROTTLE TELEFLEX CABLE QUICK DISCONNECT AT THE ENGINE FIREWALL WAS BROKEN OFF. THE PART WAS REPLACED AND THE AIRC	RAFT RETURNED TO SERVICE.			1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2005100400025	20051004	00025	EU  	2005	10	4	CA050831004      	1	20050715	G	2432	16061	BATTERY         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MASTER	OVERHEATED      	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) BATTERY OVERHEATED.  PILOT HAD AN OVERTEMP INDICATION ON HIS INSTRUMENT PANEL.  BATTERY REMOVED AND A NEW ONE INST	ALLED.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005100400026	20051004	00026	NE  	2005	10	4	CA050831005      	2	20050722	G	7230		BLADES          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR	DAMAGED         	W				C				ABORTED TAKEOFF         				C			F.O.D.                    			TO	TAKEOFF        	1			CA								PC0823			(CAN) THE ENGINE WAS REPORTED TO LOSE POWER DURING TAKEOFF AND THE AIRCRAFT CRASHED.  PRELIMINARY INVESTIGATION EVIDENCE	D FRACTURED COMPRESSOR AND POWER TURBINE BLADES.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETER	MINED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005100400027	20051004	00027	EA  	2005	10	4	CA050831006      	2	20050830	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 1	ODOR            	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA								FA0213			(CAN) AN OIL SMELL WERE DETECTED IN THE CABIN DURING FLIGHT.  BLEED AIR FROM THE NR 1 ENGINE WAS SHUT OFF AND THE SMELL 	REDUCED.  THE AIRCRAFT COMPLETED THE PLANNED FLIGHT.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETE	RMINED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005100400028	20051004	00028	EA  	2005	10	4	CA050831007      	2	20050826	G	7250		TURBINE BLADES  			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					POWER SECTION	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			C			F.O.D.                    			CR	CRUISE         	1			CA								42475			(CAN) DURING CRUISE, THE ENGINE WAS REPORTED TO SURGE AND EMIT LOUD NOISES.  THE PILOT SHUT THE ENGINE DOWN IN FLIGHT.  	A SUBSEQUENT RE-LIGHT ATTEMPT WAS UNSUCCESSFUL AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION R	EVEALED POWER TURBINE BLADE DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005100400029	20051004	00029	NE  	2005	10	4	CA050831008      	2	20050830	G	7321		HMU             			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING A TRAINING FLIGHT, ENGINE POWER WAS COMMANDED TO IDLE RESULTING IN A LOW FUEL PRESSURE WARNING AND AN UNCOM	MANDED ENGINE SHUT DOWN.  AN IN-FLIGHT RE-LIGHT WAS SUCCESSFULLY ACCOMPLISHED AND THE REMAINDER OF THE FLIGHT CARRIED OU	T WITHOUT FURTHER INCIDENT.  SUBSEQUENT TROUBLESHOOTING WAS UNABLE TO REPRODUCE THE PROBLEM AND THE ENGINE CONTROLS RIGG	ING WAS DETERMINED TO HAVE BEEN WITHIN DEFINED LIMITS.  THE HYDROMECHANICAL FUEL CONTROL WAS SUBSEQUENTLY REPLACED.  P&W	C WILL MONITOR INVESTIGATION OF THE FUEL CONTROL AND ADVISE OF ROOT CAUSE ONCE DETERMINED.		1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2005100400030	20051004	00030	NM  	2005	10	4	CA050901001      	1	20050831	G	5311	85310926101	FRAME           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	BS 136.80	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40486								(CAN) DURING A SCHEDULED DETAILED STRUCTURAL INSPECTION OF AIRCRAFT AT FRAME SPLICES AT STA 136.80 AND STR 15A, 5310/29C	.  CRACKING WAS FOUND ON FRAME SPLICES AND ADDITIONAL STRAPS AS PER MOD 8/0340, LT AND RT PROCEEDED WITH BOMBARDIERS RD-	8-53-3541FOR PERM REPAIR TO FRAME SPLICES AND STRAPS.  UPON REMOVAL OF LT FRAME SPLICE AN OTHER CRACK WAS DETECTED APPRO	XIMATELY ONE HALF INCH IN LENGTH, THUS SUBMITTED ADDITIONAL DAMAGE REPORT TO BOMBARDIER AND WAS ISSUED AN ADDITIONAL, RD	 8-53-8673.  REPAIRS WERE CARRIED OUT AND NO FURTHER INCIDENTS.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005100400031	20051004	00031	SW  	2005	10	4	CA050901002      	1	20050818	G	6310	206040206001	BEARING         	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FREEWHEEL UNINT	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						BMB10385					(CAN) DURING A 1500 HR FREEWHEEL INSP, THE AFT BEARING IN THE OUTER SHAFT WAS FOUND CORRODED ON THE INSIDE OF THE OUTER 	RACE.  BEARING WAS REMOVED AND RUST WAS PRESENT ON THE OUTER RACE.  BEARING HAD PREVIOUSLY OVERHAULED BY BII IN 1999BEAR	ING WAS REMOVED FROM SERVICE.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005100400032	20051004	00032	GL  	2005	10	4	CA050901003      	2	20050704	G	7310	5233592	SHROUD          			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL NOZZLE ASSY	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						AG75092					(CAN) DURING 100 HR ENGINE INSPECTION, FUEL NOZZLE WAS REMOVED FOR CLEANING.  AFTER CLEANING WAS COMPLETED, NOZZLE AIR S	HROUD WAS VISUALLY INSPECTED AND FOUND CRACKED ABOUT .250 LONG.  CRACK STARTED FROM CENTER HOLE THROUGH TWO OUTWARD HOLE	S.  FUEL NOZZLE WAS REMOVED FROM SERVICE.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005100400033	20051004	00033	SO  	2005	10	4	CA050901004      	2	20050901	G	8520		CONNECTING ROD  			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520J    	17040	SO  					CRANKSHAFT	BROKEN          	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) SUSPECT OIL STARVATION TO NR 3 CONNECTING ROD DUE TO MOVEMENT OF NR 2 INTERMEDIATE MAIN BEARING IN CRANKCASE.  ENG	INE NOT FULLY DISASSEMBLED AT THIS TIME.  ENGINE BOTTOM END BEYOND REPAIR.					1	L	7	2 	3O	3	O		3A25    	E8CE				 
2005110700187	20051107	00187	NE  	2005	11	7	CA050901005      	3	20050829	G	6197		WIRE HARNESS    			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	PROPELLER SYNC	SHORTED         	W				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CL	CLIMB          	1			CA											A/C DEPARTED YYC, DURING CLIMB-OUT LIGHTS FLICKERED LT GEN KICKED OFFLINE AND CREW LOST FMS SCREEN AND PROP SYNC CB POPP	ED.  AS DEPARTING MX BASES, ELECTED TO RETURN TO YYC.  PAX`S WHERE DISEMBARKED AND A/C RETURNED TO HANGAR.  GENERATOR CA	ME ON LINE DURING STARTUP AND TAXI BACK TO HANGAR ALTHOUGH FMS SCREEN AND PROP SYNC REMAINED INOP.  VISUAL CHECK OF STAR	T/GEN COMPLETED AND GROUND RUN AND FLT TEST COULD NOT DUPLICATE ANY ELECTRICAL FAULT IN GENERATOR.  FMS AND PROP SYNC WH	ERE DEFERRED AND FLIGHT CONTINUED.  ELECTRICAL SHORT OF PROP SYNC SYSTEM SUSPECTED OF INTERFERRING WITH START/GEN AND HA	RMING FMS SCREEN.  TROUBLESHOOTING OF PROP SYNC SHORT ONGOING.  WILL REPORT FINDINGS.	2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2005100400034	20051004	00034	CE  	2005	10	4	CA050902001      	1	20050831	G	2160	IN4005	DIODE           	BARBERCOL   		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TEMP CONTROL BOX	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						1412H					(CAN) FLIGHT FROM WAS DIVERTED DUE TO SMOKE IN THE CABIN.  MAINTENANCE WAS DISPATCHED AND FOUND THE CABIN TEMP CONTROL B	OX WAS BURNT FROM AND OVER HEATED DIODE.  THE SYSTEM DEFERRED UNDER MEL AND AIRCRAFT RETURNED.  THE TEMP CONTROL SYSTEM 	WAS TESTED, THE CONTROLLER REPLACED AND THE SYSTEM CHECK SERVICEABLE				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005100400035	20051004	00035	CE  	2005	10	4	CA050902002      	1	20050901	G	2160	IN4005	DIODE           	BARBERCOL   		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TEMP CONTROL BOX	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA						1371H					(CAN) AIRCRAFT DEPARTED, 30 KM OUT, REPORTED SMOKE IN THE CABIN.  THE SMOKE DISSIPATED AND THE FLIGHT LANDED.  MAINTENAN	CE FOUND THE CABIN TEMP CONTROL HAD A BURND DIODE IN IT.  THE CONTROLLER WAS REMOVED AND THE SYSTEM WAS DEFERRED IAW THE	 MEL.  AIRCRAFT THEN CONTINUED OPERATING UNDER THE MEL AND RETURNED TO BASE THAT EVENING.  OPEN DIODES IN THE CONNECTOR 	TO THE LT HEAT EXCHANGER BYPASS VALVE WERE REPLACED AS THE SUSPECT CAUSE OF THE DIODES OVERHEATING IN THE CABIN TEMP CON	TROLLER.  AIRCRAFT WAS RETURNED TO SERVICE AFTER CLEARING THE DMI.		1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005100400036	20051004	00036	EU  	2005	10	4	CA050904001      	1	20050831	G	7910	LTS101	RESERVOIR       			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE OIL	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOTS NOTICED THE MASTER CAUTION LIGHT FLICKER, FOLLOWED BY A STEADY MASTER CAUTION LIGHT.  ENGINE 2 OIL PRESSURE	 LIGHT ON THE CAUTION PANEL AND FALLING PRESSURE ON THE NR 2 ENGINE PRESSURE GAUGE.  AIRCRAFT DIVERTED TO A NEARBY AIRST	RIP FOR A PRECAUTIONARY LANDING.  PILOTS SHUT DOWN NR 2 ENGINE.  AFTER SHUT DOWN IT WAS DISCOVERED THAT THE NR 2 ENGINE 	OIL RESERVOIR WAS VIRTUALLY EMPTY.			1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2005100400037	20051004	00037	CE  	2005	10	4	CA050906001      	1	20050831	G	3710		SHAFT           			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	VACUUM PUMP	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								295142R			(CAN) DURING ROUTINE MAINTENANCE, SHAFT LOCATION CUTOUT OF RT PUMP HAD AN ODD LOOK TO IT.  TURNING PROPELLOR BY HAND VER	IFIED SUSPICION, SHAFT WAS SHEARED.  PUMP REPLACED.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2005100400038	20051004	00038	SW  	2005	10	4	CA050906002      	1	20050829	G	7334	42D208	PRESSURE SWITCH 			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J	H		WARNING INDICATION        	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											(CAN) FUEL FILTER LIGHT ON.  REPLACED PRESSURE SWITCH P/N 42D208.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005100400039	20051004	00039		2005	10	4	CA050906003      	1	20050804	G	1430	AS21910	BOLT            								RROYCE	TAY   	TAYMK6118   	 	NE  					TURBINE CASE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENG TAY 16916 AFTER TEST, HAD ABNORMAL NOISE DURING ROTATION OF LP SYS.  ENG WAS REJECTED AT DISPATCH AND MODULE 5	 (LP TURBINE ASSY) WAS DISMANTLED FOR INVESTIGATION.  DURING DISASSEMBLY IT WAS FOUND THAT 1 OFF BOLT AS21910 HAD FAILED	 IN 3 PIECES CAUSING SECONDARY DAMAGE TO HP AND LP SYS. FAILED BOLT, 1 OFF,  FULL ENG SET ARE 20), RETAIN ASSY OF LP TUR	BINESTAGE 1 AIR STATIC SEAL.  LAB ANALYSIS OF FAILED BOLT REVEALED CAUSE OF FAILURE WAS DUE TO CADMIUM PLATING APPLICATI	ON.  CADMIUM PLATING PENETRATE BY DIFFUSION AT HIGH TEMP AND LEADS TO CRACKING OF PARTS.  AS21910 FOR THAT ENGINE LOCATI	ON DOES NOT REQUIRES CADMIUM PLATING AND AN INVESTIGATION IS TAKING PLACE BY RRC TO FIND SOURCE OF CADMIUM APPLICATION. 						4	F			A25NE				 
2005100400040	20051004	00040	EA  	2005	10	4	CA050906004      	2	20050808	G	7322	229164	TUBE            	PREAIR      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					DISCHARGE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DT21656					(CAN) ACCELERATOR DISCHARGE TUBE CAME OUT OF THE CARB BOWL (NOT FOUND).  SECONDARY PROBLEM FOUND UPON DISASSEMBLY: ONE F	LOAT PONTOON PARTIALLY FILLED WITH FUEL.  NEW DISCHARGE TUBE INSTALLED AND FLOAT REPLACED.  CARB REASSEMBLED AND TESTED.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2005100400041	20051004	00041	NM  	2005	10	4	CA050907001      	1	20050823	G	3230		PIN             			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO YHM NLG DID NOT INDICATE DOWN AND LOCKED.  CONFIRMED DOWN BY VISUAL SCOPE, AIRCRAFT LANDED WITHOUT 	INCIDENT.  UPON INVESTIGATION IT WAS DETERMINED A PIN FOR THE LANDING GEAR ACCESSORY UNIT WAS 'PUSHED BACK'.  PIN REPAIR	ED AND INDICATION WORKED NORMAL.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005100400042	20051004	00042		2005	10	4	CA050907004      	4	20050902	G	2312	VHF251	RADIO           			CESSNA	206   	P206A       	2073308	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	VHF SYSTEM	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) UPON DEPARTURE FROM THE AIRPORT, THE PILOT SMELLED SMOKE IN THE COCKPIT.  RETURNED TO THE AIRFIELD AND HAD MAINTEN	ANCE INSPECT THE AIRCRAFT.  RADIO NR 2 HAD A BURNT SMELL TO IT.  RADIO WAS REMOVED AND DEFECT DEFERRED.  PILOT CONTINUED	 ON WITHOUT FURTHER INCIDENT.  AVIONICS SHOP FOUND A CAPACITOR THAT HAD FAILED.				1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P36EA	 
2005100400043	20051004	00043	NE  	2005	10	4	CA050908002      	1	20050902	G	3233		LINE            			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  					NLG ACTUATOR	OBSTRUCTED      	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) NOSE GEAR FAILED TO LOCK DOWN DUE TO A PLUGGED RETURN LINE ORIFACE, ACTUATOR REMOVED/DISASSEMBLED/CLEANED/REASSEMB	LED, REINSTALLED, HYDRAULIC SYSTEM FLUSHED, GEAR SWINGS COMPLETED.  NO FAULTS FOUND.					1	H	7	1 	3O	3	O		1A13    	1E10				 
2005100400044	20051004	00044	WP  	2005	10	4	CA050908003      	1	20050905	G	2750	7501113	COUPLING        			LKHEED	188   	188A        	5262602	WP  	ALLSN 	501D  	501D13      	03004	GL  					TE FLAP CONTROL	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE A/C HAD FINISHED IT'S THIRD DROP ON A FIRE BOMBING PRACTICE, FLAPS WOULD NOT RETRACT AND THE FLAP ASYMMETRIC L	IGHT WAS ON.  THE FLAP ASYMMETRY CHECKLIST WAS COMPLETED AND THE A/C RETURNED TO BASE.  MAINTENANCE FOUND A BROKEN TORQU	E TUBE COUPLING, THE COUPLING WAS REPLACED THE ASYMMETRY SYSTEM WAS RESET.  THE FLAPS WERE RUN THROUGH SEVERAL CYCLES AN	D THE A/C WAS RETURNED TO SERVICE.			2	L	7	4 	4T	4	T	RT	4A22    	E282				 
2005100400045	20051004	00045	GL  	2005	10	4	CA050908004      	2	20050813	G	7200		BEARING         			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					NR 4	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			M	Y	J	OVER TEMP                 	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA								CAE312071			(CAN) PILOT REPORTED RT ENGINE SHUTDOWN UNCOMMANDED, FLIGHT DIVERTED TO PIT.  ITT ROSE TO THE AMBER RANGE, PILOT RETARDE	D THROTTLE.  ITT CONTINUED TO RISE INTO THE RED AND THE E2 OUT MESSAGE APPEARED ON EICAS.  ENGINE SHUTDOWN UNCOMMANDED. 	 ENGINE CURRENTLY BEING DISMANTLED FOR INVESTIGATION.  EVIDENCE OF  NUMBER 4 BEARING FAILURE.  STRIP REPORT WILL BE SUBM	ITTED AT A LATER DATE.			2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2005100400046	20051004	00046	EU  	2005	10	4	CA050908005      	1	20050906	G	6123		WARNING LIGHT   			HWKSLY	DH125 	HS125600A   	4230158	EU  	RROYCE	DART  	DART5342    	 	EU  					PROP FEATHERING	FALSE INDICATION	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) BELOW FFPS INDICATOR LIGHT FOR NR 2 PROP INOP SYSTEM GROUND TEST NORMAL FERRY FLIGHT PERMIT ISSUED TO RETURN TO BA	SE FOR REPAIR.					2	L	7	2 	4J	4	T		A3EU    	A196				 
2005100400047	20051004	00047	EA  	2005	10	4	CA050909001      	1	20050901	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, CO-PILOT SIDE WINDOW CRACKED WHEN PASSING FL 110.						2	L	7	2 	4F			RT	A21EA   					 
2005100400048	20051004	00048	EA  	2005	10	4	CA050909002      	1	20050810	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) PILOT'S WINDSHIELD CRACKED AFTER LANDING.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005100400049	20051004	00049	NM  	2005	10	4	CA050909003      	1	20050909	G	2897		WIRE HARNESS    			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					FUEL SYSTEM	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) FAULT: FLT DEP.YYZ WITH LT FUEL DENSIOMETER UNDER MEL.  FLT CREW CONFIRMS LT IND DID BLANK OUT ON OCCASION DURING 	THE FLT AND HAD BEEN CALCULATING THE FUEL REMAINING THROUGHOUT THE FLT.  AT FL370 AND 50NM FROM TOP OF DESCENT, THE LT E	NG FLAMED OUT, ENG RELIT USING CROSSFEED FROM RT TANK.  LT FUEL TANK IND PLACED ON MEL WITH DRIP REQUIRED.  LEFT WING FU	EL QTY PROBE HARNESS REPLACED AS PER AMM NIL FIX.  LEFT WING DENSIOMETER AND DENSIOMETER EMITTER REPLACED AS PER AMM, NI	L FIX.  LT WING COMPENSATOR REPLACED TWICE NIL FIX.  REPLACED LT WING HI 'Z' HARNESS FOR A FIX.		2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005110700188	20051107	00188	SW  	2005	11	7	CA050909004      	1	20050908	G	5551		ATTACH BRACKET  			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ACCOMPLISHMENT OF A 200 HOUR INSPECTION, A CRACK WAS OBSERVED IN THE ATTACH BRACKET WELD THAT SECURED THE R	T UPPER AUX FINLET TO THE HORIZONTAL STABILIZER. THE FINLET WAS REMOVED FROM THE AIRCRAFT FOR REPAIR. UPON COMPLETION OF	 THE REPAIR THE FINLET WILL BE RE-INSTALLED ON THE AIRCRAFT.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2005100400050	20051004	00050	SW  	2005	10	4	CA050909005      	1	20050908	G	5280		DOOR            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DAMAGE FOUND ON THE LT NOSE GEAR DOOR 6 INCH AFT OF THE FORWARD HINGE.  GEAR SWINGS CARRIED OUT AND MAINT FOUND DO	OR TO JAM IN THERE TRACKED POSITION.  GEAR DOOR ADJUSTED AS PER THE AMM AND GEAR SWINGS CHECKED SERVICIBLE.  AIRCRAFT RE	LEASED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005100400051	20051004	00051	SW  	2005	10	4	CA050909006      	1	20050902	G	2910	2781032491	LINE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT LANDED AND FLIGHT CREW NOTICED HYD LEAK.  MAINTENANCE WAS CONTACTED.  FOUND A CRACKED FLAP UP LINE IN THE	 BELLY OF THE AIRCAFT.  TUBE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2005100400052	20051004	00052	EA  	2005	10	4	CA050909007      	2	20050909	G	8530	893741	CYLINDER        			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								PC10117C			(CAN) AN OIL LEAK WAS OBSERVED AT BASE OF CYLINDER NR 1.  SOME SLIGHT MOVEMENT WAS NOTED AT CYLINDER BASE.  UPON FURTHER	 INVESTIGATION, ALL CYLINDER BASE HOLD DOWN BOLTS ON THE AFFECTED CYLINDER WERE FINGER TIGHT.  THE LOCK PLATES WERE STIL	L INSTALLED.  CYLINDER WAS REMOVED AND THE CYLINDER BASE O-RING WAS BROKEN AND A MINOR AMOUNT OF WORKING WAS NOTED ON TH	E CYLINDER FLANGE.  THE ADJACENT CYLINDERS WERE INSPECTED AND FOUND BELOW THE REQUIRED TORQUE.  THE CYLINDER BASE HOLD D	OWN BOLTS WERE RETORQUED.  AIRCRAFT HAS BEEN REMOVED FROM SERVICE PENDING A COMPLETE TORQUE CHECK OF ALL CYLINDER BASE H	OLD DOWN BOLTS.  A RANDOM CHECK OF THE OTHER AIRCRAFT ON BASE WAS COMPLETED AND NO EVIDENCE OF LEAKS WERE NOTED.	2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2005110700189	20051107	00189	CE  	2005	11	7	CA050912001      	1	20050909	G	5520	1156100151	SUPPORT         	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TORQUE TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ACCOMPLISHMENT OF SB 2145 CRACK WAS DETECTED ON TORQUE TUBE ASSEMBLIES (P/N 115-610015-325).  FOUND AT IB S	UPPORT (P/N 115-610015-1).   TORQUE TUBE REPLACED.					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2005110700190	20051107	00190	SW  	2005	11	7	CA050912002      	1	20050831	G	6730	C4264145	BUSHING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRUNNION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						RH1058					(CAN) AFTER DISASSEMBLY THIS ITEM WAS SENT FOR NDT AND WAS RETURNED WITH CRACK INDICATIONS.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005101300051	20051013	00051	NM  	2005	10	13	CA050912003      	1	20050830	G	3246	3006191	WHEEL HALF      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27121								(CAN) DURING ROUTINE SERVICE CHECK, THE NR 4 MAIN WHEEL TIRE PRESSURE WAS FOUND TO BE 50 PSI WHEEL ASSY REPLACED AND ROU	TED TO YHZ WHEEL AND BRAKE SHOP. DURING INSPECTION PROCESS, NDT INSPECTION REVEALED A CRACK EMANATING FROM THE VALVE STE	M SEAT.  WHEEL HALF ASSY WAS ON BUILD NR 61.  WHEEL HALF SCRAPPED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005101300052	20051013	00052	EA  	2005	10	13	CA050912004      	1	20050909	G	7120	73507217	MOUNT           			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 1 ENGINE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, PILOT ENCOUNTERED PWR LEVER MISMATCH AS REDUCED TO CLIMB POWER. REPORTED  PROBLEM AND LANDED UNEVEN	TFULLY.  INVESTIGATION REVEALED THAT TOP ENGINE MOUNT ON NR 1 ENG HAD BROKEN AT A POINT BETWEEN FLANGE AND BASE.  THIS C	AUSED ENG TO SAG ENOUGH TO GIVE A PWR LEVER MISMATCH.  ALL 3 ENG MOUNT ASSY AND ATTACH BOLTS WERE REPLACED, NACELLE LONG	ERONS AND ASSOCIATED STRUCTURE WERE INSPECTED FOR DEFORMATION, AND AC RETURNED TO SERVICE.  ALTHOUGH THERE IS NO SPECIFI	C NDT REQUIRED ON THIS ITEM, A SHIP SET OF MPI INSPECTED MOUNTS HAS BEEN READIED FOR A FLEET CAMPAIGN AS THE AIRCRAFT AR	E SCHEDULED THROUGH MAINTENANCE.  TIME AND CYCLES ON THE FAILED PART ARE UNKNOWN.	1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005100500013	20051005	00013	WP  	2005	10	5	CA050912005      	1	20050910	G	7160	C328	AIR FILTER      			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2599340A			(CAN) DURING AN 100 HR INSPECTION, THE AIR FILTER WAS BEING REPLACED.  THE FILTER WAS FOUND DAMAGED AND REPLACED.  INVES	TIGATION REVEALED NO APPARENT REASON.  THE PILOT WAS ASKED IF A BACKFIRE CONDITION OCCURRED AND NONE WAS EXPERIENCED AT 	THE TIME.  THIS IS THE FIRST THATS BEEN SEEN OF THIS AND ONLY ASSUME AT THIS TIME.  HAVE SENT PICTURES TO ROBINSON HELI	COPTERS TO GET SOME FEED BACK.  ASSUME IT WAS DUE TO A CARB FIRE AND THE HEAT DISTORTED THE FILTER.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2005110700191	20051107	00191	CE  	2005	11	7	CA050912006      	1	20050908	G	2133	5038017027	PRESSURE VALVE  			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN PRESSURE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REMOVED LT PNEUMATIC CHECK VALVE TO INSPECT INTERNAL HINGE OPERATIONS. FOUND HINGE PIN DISLODGED (WORKED) TO ONE S	IDE, RESULTING IN OFFSET FLAPPER DOOR MOVEMENT, WEAR AND POOR OPERATION. A LONGER HINGE PIN OR STAKING THE ORIGINAL PIN 	MAY PREVENT THIS TYPE OF MALFUNCTION.				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2005100500014	20051005	00014	EA  	2005	10	5	CA050913001      	1	20050911	G	2130	GG67098001	CONTROL PANEL   			CNDAIR	CL600 	CL6002C10   	1390015	EA  										CABIN PRESSURE	SPARKS          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) THE CABIN PRESS CONTROL PANEL STARTED SMOKING AND SPARKING' WHILE A/C WAS TAKEN AT THE GATE.  THE CPCP WAS REPLACE	D IN ACCORDANCE WITH AMM.					2	L	7	2 	4F			RT	A21EA   					 
2005100500015	20051005	00015	EA  	2005	10	5	CA050913002      	1	20050912	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) THE LT WINDSHIELD CRACKED WHILE THE A/C WAS IN CLIMB.  THE A/C RETURNED TO GROUND FOR THE REPLACEMENT OF THE WINDS	HIELD.					2	L	7	2 	4F			RT	A21EA   					 
2005100500016	20051005	00016	EU  	2005	10	5	CA050913003      	1	20050912	G	5230		DOOR            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					CARGO BAY	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, DAMAGE FOUND TO LARGE FREIGHT DOOR FORWARD FORMER RING AND STRAP AT STA 126A BETWEEN STRINGERS 	7 AND 8.  DAMAGE WAS CAUSED BY INCORRECT FASTENER (SCREW TOO LONG) AT THE MOST FORWARD POSITION OF THE LARGE FREIGHT DOO	R UPPER SPIGOT FAIRING.  THE SCREW WAS ALLOWED TO FOWL WITH DOOR SURROUND WHEN OPENING AND CLOSING THE DOOR.				2	L	7	2 	3T	4	T		A24EU   	A196				 
2005110700179	20051107	00179	EU  	2005	11	7	CA050913004      	1	20050908	G	2910	365A75814012	TUBE            			UROCOP	EC155 	EC155B      	8681000	EU  										HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A POST FLIGHT WALK AROUND PILOT NOTICED HYDRAULIC FLUID DRIPPING FROM LT WHEEL WELL. FURTHER INVESTIAGTION 	FOUND FLUID ACTUALLY DRIPPING FROM ABOVE IN THE FORWARD LT BAGGAGE AREA WHERE THE HYDRAULIC SYSTEM PIPING RUNS. A SINGLE	 PIPE GOING INTO A MANIFOLD WAS FOUND CRACKED ABOUT .5 INCH FROM THE FITTING. FURTHER VISUAL INSPECTION FOUND A FLAT SPO	T ON THE PIPE WHERE THE CRACK WAS LOCATED. WHEN REMOVED IT WAS FOUND THAT THE PIPE WAS LOADED SLIGHTLY. A NEW PIPE WAS I	NSTALLED AND NO FURTHER PROBLEMS NOTED. PIPE HAS BEEN RETURNED TO FOR FURTHER INVESTIGATION.		1	G	7	2 	3U				H10EU   					 
2005100500017	20051005	00017	EA  	2005	10	5	CA050913005      	1	20050822	G	7110	MSZ698010	ISOLATION MOUNT 			DHAV  	DHC3  	DHC3        	2800202	EA  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  					COWL	SEPARATED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) FLOAT EQUIPPED AIRCRAFT IN CRUISE AT APPROXIMATELY 2,000 AGL, PILOT NOTED AN IRREGULAR SOUND FROM FRONT OF AIRCRAF	T.  NOISE CEASED AFTER WHICH THE PILOT CONTINUED TO A NEARBY LAKE AND LANDED.  6 OF 12 VIBRATION ISOLATORS HAD PULLED TH	RU THE BACK OF THE SECURING EYE BOLTS WHICH ATTACH THE RING ASSEMBLY TO THE CYLINDER HEADS.  RING RE-SECURED.  MINOR DAM	AGE TO LEADING EDGE OF TOP COWL AND FACE/TRAILING EDGE OF PROP.			1	H	7	1 	3R	3	R		A815    	E10NE				 
2005110700180	20051107	00180	SO  	2005	11	7	CA050913006      	1	20050831	G	2910	1776602	HOSE            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) PILOT NOTICE HYDRAULIC FLUID LEAKING FROM RT LOWER FUSELAGE TO WING FAIRING AFT MAIN SPAR.  AP ON INSPECTION, FOUN	D LANDING GEAR HOSE RUPTURED.  REPAIRED HOSE ASSY P/N 17766-02 BY REPLACING HOSE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005110700181	20051107	00181	SW  	2005	11	7	CA050913007      	1	20050909	G	6220	407310101101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					CENTER SUPPORT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING SHEARED FROM THE CENTER SUPPORT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005110700182	20051107	00182	SO  	2005	11	7	CA050913008      	1	20050901	G	3233	484706	O-RING          	PIPER       		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	MCAULY	3AF34C	3AF34C502   	GL  	ACTUATOR	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) PILOT REPORTED THAT LANDING GEAR FAILED TO RETRACT. AIRCRAFT PLACED ON JACKS,  LANDING GEAR SWUNG, FOUND NOSE GEAR	 ACTUATOR FAILED TO COMPLETELY RETRACT.  REMOVED NOSE GEAR ACTUATOR, DISASSEMBLED, FOUND PISTON ORING EXCESSIVELY WORN. 	INSTALLED NEW ORINGS P/N 484-706 AND BACK UP RING P/N 758-053 AND RE-ASSEMBLED. RE-INSTALLED NOSE GEAR ACTUATOR, SWUNG G	EAR WITH NO FAULT FOUND.			1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2005110800025	20051108	00025	WP  	2005	11	8	CA050913009      	1	20050901	G	2926	D2111	RESERVOIR       			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					HYDRAULIC SYS	INOPERATIVE     	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FLUID FOUND VENTING FROM CAP.  ALL FITTINGS AND LINES OF HYDRAULIC SYSTEM CHECKED.  NO DEFECTS FOUND.  G	ROUND RUN LEAK CHECK, AND STILL VENTING FROM CAP.  HYDRAULIC RESERVOIR ASSEMBLY REPLACED.  GROUND RUN AND LEAK CHECK, NO	 DEFECTS FOUND.				1	G	7	1 	3O	3	O		H11NM   	E295				 
2005121200110	20051212	00110	WP  	2005	12	12	CA050913010      	1	20050711	G	6220	369X795111	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ROD END	UNSERVICEABLE   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ROD END BEARING WORN BEYOND SERVICEABLE LIMITS PREMATURELY.  MANUFACTURER OF RODEND BEARING.  WARRANTY ON THIS BEA	RING AND PREVIOUS PREMATURELY WORN BEARINGS REJECTED.  SUSPECT SUBSTANDARD PARTS DUE TO HIGH WEAR RATE, CONFIRMED BY OTH	ER OPERATORS.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2005121900060	20051219	00060	WP  	2005	12	19	CA050913011      	1	20050911	G	6200	369X795111	BEARING         			HUGHES	369   	369D        	4470706	WP  										P/C ROD END	UNSERVICEABLE   	W				O				OTHER                   				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA											(CAN) ROD END BEARING WORN BEYOND SERVICEABLE LIMITS PREMATURELY.  MANUFACTURER OF RODND BEARING, WARRANTY ON THIS BEARI	NG AND PREVIOUS PREMATURELY WORN BEARINGS REJECTED.  SUSPECT SUBSTANDARD PARTS DUE TO HIGH WEAR RATE, CONFIRMED BY OTHER	 OPERATORS.				1	G	7	1 	3U				H3WE    					 
2005110700183	20051107	00183	EU  	2005	11	7	CA050914002      	1	20050903	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL BOOST	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL BOOST PUMP WAS INTERMITTENT DURING PRE-START CHECKS.  PUMP WAS REPLACED WITH AN OVERHUALED UNIT.  NO FURTHER 	DEFECTS.  PUMP INSTALLED 35.3 HOURS.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005110700184	20051107	00184	SW  	2005	11	7	CA050914003      	1	20050914	G	6420	047641175001	BEARING RACE    	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R HUB	BRINELLED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						JILG51007					(CAN) TAIL ROTOR HUB ASSY WAS REMOVED TO REPLACE TX BLADES.  TO ALLOW A PROPER STATIC BALANCE THE YOKE WAS TAKEN APART A	ND CLEANED.  ONE INNER RACE ON THE YOKE WAS SERVICEABLE, THE OTHER RACE WAS FOUND BADLY BRINELLED.  THE ASSEMBLY LOOKED 	TO BE PROPERLY GREASED AT TIME OF DISASSEMBLY, HOWEVER THE GREASE ON THE BRINELLED SIDE WAS SLIGHTLY REDDISH BROWN.  NO 	SIGN OF CORROSION IN THE ASSEMBLY.  BOTH INNER RACES WERE REPLACED AT THIS TIME.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005100500018	20051005	00018	SO  	2005	10	5	CA050915001      	2	20050730	G	7310		INJECTION SYSTEM			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE FUEL	OUT OF ADJUST   	W				D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			LD	LANDING        	1			CA								806496			AIRCRAFT ENGINE QUIT DURING LANDING AND HAD RESTART DIFFICULT.  A/C WAS FINALLY STARTED AND TAXIED BACK TO A MX HANGAR. 	 IT WAS NOTED THAT ENGINE RAN EXTREMELY ROUGH AT IDLE.  A SET OF CALIBRATED FUEL SET UP GAUGES WERE ATTACHED AND A FUEL 	SYSTEM CHECK CARRIED OUT PER TCM SID97-3C.  ADJUSTMENTS WERE CARRIED OUT AND A/C RELEASED CONDITIONAL TO SATISFACTORY TE	ST FLIGHT.  TEST FLIGHT WAS SATISFACTORY AND A/C RETURNED TO BASE.  DIAMOND AND TCM (TELEDYNE CONTINENTAL MOTORS) ARE AW	ARE OF THE FUEL SETUP PROBLEMS FUEL SYSTEM DRIFTING OUT OF ADJUSTMENT AND TO MY KNOWLEDGE HAVE BEEN CARRYING OUT FIELD T	EST WORKING CLOSELY WITH EMBRY RIDDLE.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2005100500019	20051005	00019		2005	10	5	CA050915002      	4	20050913	G	2330	50401100003	DISPLAY         			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ENTERTAIN SYS	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											A/C WAS ON THE GROUND TAXIING TO THE GATE, WHEN A BURNING ELECTRICAL SMELL WAS NOTICED AT ROW 10ABC.  THE IFE SYSTEM WAS	 DEACTIVATED.  MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO T	HE MANUFACTURER AND A COMPLETE TEAR DOWN REPORT WILL BE REQUESTED.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005100500020	20051005	00020	NM  	2005	10	5	CA050915003      	1	20050902	G	2913	570347	DRIVE SHAFT     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC PUMP	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB-OUT, THE NUMBER 1 ENGINE DRIVEN HYDRAULIC PUMP FAILED AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT.  THE NU	MBER 1 HYDRAULIC PUMP AND HYDRAULIC RETURN FILTER WERE REPLACED (SHAFT SHEARED ON PUMP) AND AIRCRAFT WAS RETURNED TO SER	VICE.  TIME SINCE LAST REPAIR 1380.1 HRS, 1388 CYCLES, SN MX-459161C.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005110700185	20051107	00185	CE  	2005	11	7	CA050915004      	1	20050915	G	3020	AN3H32A	BOLT            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	VANE	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) CREW ENTERED DEFECT IN JOURNEY LOGBOOK, (RT ANTI-ICE LIGHT ON.  VISUAL INSPECTION INDICATES BY-PASS DOOR FULLY DOW	N, DEFLECTOR DOOR HALF WAY DOWN).  MAINTENANCE CREW FOUND A BOKEN BOLT IN LINKAGE P/N AN3H-32A. (REFER TO IPC 30-20-02 P	AGE 0 ITEM 35) RT ENGINE COMPRESSOR CHECKED FOR FOD DAMAGE.  NO DEFECTS FOUND.  THE BOLT WAS REPLACED, SYSTEM CHECKED AN	D AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2005100500021	20051005	00021	EA  	2005	10	5	CA050915005      	1	20050915	G	2820	15J0408AE	FITTING         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					FS 636	LOOSE           	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA											(CAN) DURING SERVICING A STRONG ODOR OF JET FUEL WAS NOTICED IN THE AFT EQUIPMENT BAY.  AFTER INVESTIGATION, THE TRANSFE	R FUEL LINE FROM THE TAIL TANK TO THE FUSELAGE AUXILIARY TANK WAS FOUND TO BE LEAKING.  THE WIGGINS FITTING ON THE TRANS	FER ROTOR BURST FUEL LINE AT FS 636 WAS FOUND LOOSE.  WORK IN THE AREA WAS LAST PERFORMED ON MAY 14, 2005 WHEN ANOTHER A	MO REPLACED THE TRANSFER ROTOR BURST FUEL LINE IN QUESTION.  NEW SEALS WERE INSTALLED, THE WIGGINS FITTING WAS TIGHTENED	 AND LEAK CHECKED.  AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110700186	20051107	00186	EA  	2005	11	7	CA050916001      	2	20050915	G	7414	BL6006163	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE MAGNETO WAS REMOVED DUE TO FAILURE (NOT WORKING) UPON DISASSEMBLY THE BRUSH WAS BROKEN AND THE SPARK WAS NOT M	AKING IT OUT OF THE COIL TO THE DISTRIBUTOR.  ALSO, FOUND COIL CLAMP BROKEN THIS WILL BE REPAIRED HERE ALONG WITH A FRES	H 500 HR INSP.  DURING THE 500 HR INSPECTION THE COIL FAILED INTERNAL RESISTANCE CHECK. THE COIL IS ALSO BEING REPLACED.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2005110700170	20051107	00170	EA  	2005	11	7	CA050916002      	2	20050915	G	7414	1081806	BEARING         	CONT        		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					MAGNETO	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						I140017E					(CAN) MAGNETO WAS REMOVED FOR SCHEDULED 500 HOUR INSPECTION.  THE LOWER BEARING LOOKS AS THOUGH IT HAD BEEN SPINNING ON 	THE SHAFT.  THE SPACER WAS ALSO DAMAGED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2005110700192	20051107	00192	SW  	2005	11	7	CA050916003      	1	20050914	G	7920	500751	FILTER          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE OIL	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A PHYSICAL DIFFERENCE WAS NOTICED ON FILTERS 50-075-1.  A SCREEN HOLE PATTERN WAS FOUND TO BE OUT OF SPECIFICATION	.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005110700193	20051107	00193	SW  	2005	11	7	CA050916004      	1	20050914	G	6320	500751	FILTER          			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A PHYSICAL DIFFERENCE WAS NOTICED ON FILTERS 50-075-1.  A SCREEN HOLE PATTERN WAS FOUND TO BE OUT OF SPECIFICATION	.  ATTACHED PICTURE SHOWING DIFFERENCES BETWEEN ACCEPTABLE AND NON-CONFORMING PARTS.					1	G	7	1 	3U			NC	H2SW    					 
2005100500022	20051005	00022	NE  	2005	10	5	CA050916005      	2	20050913	G	8530		ENGINE          			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  						FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								21739			(CAN) FIVE MINUTES INTO CRUISE FLIGHT AT 1000FT, THE CAPTAIN REPORTED A LOUD BANG, FOLLOWED BY A CONSTANT VIBRATION.  TE	MPS AND PRESSURES WERE CHECKED NORMAL.  THE CAPTAIN ELECTED TO RETURN TO THE POINT OF DEPARTURE AND DECLARED AN EMERGENC	Y.  FOLLOWING AN UNEVENTFUL LANDING, MAINTENANCE INVESTIGATION REVEALED THAT NR 1 CYLINDER PISTON HAD BEEN DRIVEN INTO C	ONTACT WITH THE CYLINDER HEAD, TWO OTHER CYLINDERS HAD NO COMPRESSION, AND THE OIL SCREEN WAS FULL OF METAL.  A TEARDOWN	 REPORT WILL BE FORWARDED WHEN AVAILABLE.		1	H	7	1 	3R	3	R		A806    	5E1				 
2005100500023	20051005	00023	SO  	2005	10	5	CA050917001      	2	20050906	G	8530	AEC631397ST712B	CYLINDER HEAD   			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 CONTINENTAL ENGINE SB M91-	6, AND THE TEST FAILED FOR CYLINDER NR 2 DUE TO A LEAK FOUND BETWEEN FINS AT CYLINDER HEAD.  THE CYLINDER REPLACED AND A	IRCRAFT RETURN TO SERVICE AFTER THE INSPECTION.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2005110700194	20051107	00194		2005	11	7	CA050919001      	4	20050914	G	2562		G SWITCH        	POINTER     		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					ELT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						409022					(CAN) ELT WENT OFF DURING GROUND HANDLING.  THE ELT WAS REMOVED FOR FURTHER INVESTIGATION.  SUSPECT G-SWITCH.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2005110700195	20051107	00195	SW  	2005	11	7	CA050919002      	1	20050914	G	7920	500751	FILTER          			BELL  	407   	407         	1182206	SW  										TRANSMISSION	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A PHYSICAL DIFFERENCE WAS NOTICED ON FILTERS 50-075-1. A SCREEN HOLE PATTERN WAS FOUND TO BE OUT OF SPECIFICATION.	  PICTURE SHOWING DIFFERENCES BETWEEN ACCEPTABLE AND NON-CONFORMING PARTS.					1	G	7	1 	3U			O	H2SW    					 
2005110700196	20051107	00196	GL  	2005	11	7	CA050919003      	2	20050819	G	7323	25491701	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DROOPING NR, AND WOULD NOT RECOVER.  GOVERNOR REPLACED, NO FURTHER DEFECTS.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005110700197	20051107	00197		2005	11	7	CA050919004      	4	20050916	G	2312	069010320101	RADIO           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	VHF	ODOR            	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) 15 MINUTES INTO CLIMB TO ALTITUDE, PILOTS SAW AND SMELLED SMOKE EMANATING FROM LOWER PORTION OF COPILOT'S WINDSHIE	LD.  AIRCRAFT RETURNED TO BASE OF DEPARTURE, MEANWHILE CIRCUIT BREAKERS FOR WHAT APPEARED TO BE CAUSE OF SMOKE WERE PULL	ED. WINDSHIELD HEAT BREAKERS WERE PULLED.  INVESTIGATION ON GROUND REVEALED STRONG BURNED SMELL EMANATING FROM NR 1 VHF 	NAV/COMM ONCE REMOVED FROM INSTALLATION RACK.  BACK OF NAV/COMM IS LOCATED BELOW COPILOT'S WINDSHIELD AND THIS IS WHY SM	OKE WAS COMING FROM LOWER PORTION OF WINDSHIELD. NAV/COMM REPLACED WITH SERVICEABLE UNIT.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110700198	20051107	00198	SW  	2005	11	7	CA050919005      	1	20050818	G	6730	41103750017	SERVO           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC LEAK WAS NOTED DURING MAINTENANCE.  SERVO REPLACED, NO FURTHER DEFECTES NOTED.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005100500024	20051005	00024	WP  	2005	10	5	CA050919006      	2	20050831	G	7260	30730427	GEARSHAFT       			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					ENGINE	BROKEN          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) AS A/C WAS TAXIING FOR T/O, CREW LOST LT ENGINE OIL PRESSURE.  ENGINE WAS SHUTDOWN AND A/C WENT BACK TO GATE.  LT 	ENGINE OIL PUMP WAS FOUND DAMAGED.  PUMP WAS REPLACED BUT ENGINE COULD NOT START AS N1 FAN WAS NOT TURNING.  ENGINE WAS 	OPENED UP AND NR 1 BEARING OF PLANETARY GEARSHAFT ASSY WAS FOUND BROKEN.  PLANETARY GEARSHAFT ASSY WAS REPLACED AND ENGI	NE WAS FOUND SERVICEABLE.  AFTER THE INCIDENT, A/C CAME BACK TO MAIN BASE.  ENGINE OIL FILTER WAS CHECKED AND METAL PART	ICLES WAS FOUND.  THE ENGINE OIL FILTER WAS REPLACED AND WHILE DOING ENGINE RUNS AFTER THE FILTER REPLACEMENT AND OIL PR	ESSURE ADJUSTMENT, THE ENGINE OIL PUMP BROKE AGAIN.  THE ENGINE WAS REPLACED WITH A LOANER UNIT.	2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2005110700199	20051107	00199	EU  	2005	11	7	CA050919007      	1	20050914	G	6220	350A31033KIT2	SHOCK ABSORBER  	UROCOP      		SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					M/R HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M401					(CAN) REMOVED FROM AIRCRAFT FOR MANUFACTURER 2500 HOUR INSPECTION AND 2 COILS OF THE SAME PN WERE FOUND TO BE CRACKED.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005100500025	20051005	00025	WP  	2005	10	5	CA050919008      	2	20050914	G	7200		ENGINE          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  						UNKNOWN         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								P63311C			(CAN) ENGINE REMOVED AND SENT REPAIR STATION.  RESULTS TO FOLLOW.						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE				 
2005100500026	20051005	00026	EA  	2005	10	5	CA050920001      	1	20050916	G	4920	WE8007712	APU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  						DEFECTIVE       	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) FORWARD LAV SMOKE WARNING MESSAGE CAME ON DURING TAKEOFF ROLL.  ABORTED TAKEOFF.  MAINTENANCE SUSPECTED BLEED AIR 	SYSTEM CARRIED CONTAMINATED AIR COMING FROM THE APU BLEED.  APU OIL CONSUMPTION SUSPECTED, EVIDENCE AT DUPLEX BEARING GE	ARBOX DRAIN, EVIDENCE AT HOT SECTION, OIL LEVEL BELOW ADD LINE APU COLD.  APU REPLACED, AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005110700200	20051107	00200	EA  	2005	11	7	CA050920002      	1	20050920	G	3520	60144101	OXYGEN SYSTEM   			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MM DEPLOYMENT OF THE PASSENGER OXYGEN MASKS WAS ATTEMPTED. THE CONTROLLER WAS SWITCHED TO THE OVE	RRIDE POSITION BUT ALL OF THE PASSENGER OXYGEN MASKS FAILED TO DEPLOY. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT	 THERE WAS INSUFICIENT PRESSURE AT THE PASSENGER OXYGEN BOX SOLENOIDS TO DEPLOY THE MASKS. THE OXYGEN CONTROLLER WAS REP	LACED AND THE SYSTEM WAS TESTED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005100500027	20051005	00027	NM  	2005	10	5	CA050920003      	1	20050913	G	2910	AN81510D	FITTING         			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER LANDING GEAR HAD RETRACTED, THE PILOTS NOTICED A DROP IN HYDRAULIC QUANTITY AND PRESSURE.  AIRCRAFT RETURNED	 TO BASE.  INSPECTION FOUND A CRACKED FITTING ON THE NR 2 HYDRAULIC PRESSURE MANIFOLD.  EDP WAS REPLACED AS IT WAS RUN D	RY FOR MORE THAN 15 MINUTES SYD 8-29-002 REFERENCED.  THIS SYD ALLOWS THE REPLACEMENT OF THE AN815-10D FITTING FROM ALUM	INIUM TO STAINLESS STEEL FITTING.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005110700201	20051107	00201	NE  	2005	11	7	CA050920004      	2	20050913	G	7297		WIRE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30015	NE  					IDG	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA								0098RH			(CAN) POST FLIGHT INSPECTION REVEALED EVIDENCE OF OVERHEAT CONDITION FOUND AT 6 O'CLOCK POSITION AT THE COMBUSTOR SECTIO	N FWD FRAME WHEN COWLINGS OPENED TO INVESTIGATE IDG FAILURE.  MAINTENANCE PERSONNEL FOUND LOCALIZED AREA WITH OVERHEATED	 WIRE AND FUEL MANIFOLD INSULATION.  NO DAMAGE TO COWLINGS. ENGINE BEING REMOVED AND SENT FOR INVESTIGATION TO OVERHAUL 	FACILITY.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110700209	20051107	00209	SW  	2005	11	7	CA050920005      	1	20050915	G	2913	206076050	PUMP            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					HYDRAULIC SYS	WORN            	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA				10968							(CAN) PUMP SPLINES INSPECTED DURING ROUTINE 1200 HOUR INSPECTION AND FOUND SPLINE TEETH WORN. THERE IS NO SET INSPECTION	 TIME CALLED UP IN THE MFG MM AND REPORTS FROM OTHER OPERATORS INDICATE THAT THIS SPLINE SHOULD BE INSPECTED APROX. EVER	Y 600 HOURS.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005110700210	20051107	00210	SO  	2005	11	7	CA050920006      	1	20050818	G	7160	36320500	CONTROL CABLE   			MAULE 	M7    	M7235B      	5460109	SO  										CARB HEAT	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PILOT ACTUATED CARB HEAT AND HANDLE CAME UNSWAGED FROM CABLE.  AIRCRAFT HAD TO COME BACK TO BASE PREMATURELY.						1	H	7	1 	3O			NC	3A23    					 
2005110700211	20051107	00211	SO  	2005	11	7	CA050920007      	1	20050831	G	7820	M7235B	MUFFLER         			MAULE 	M7    	M7235B      	5460109	SO  										ENGINE	BURNED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT COMPLAINED OF ABNORMAL CARB HEAT OPERATION IN FLIGHT AND BACK AT BASE ON GROUND.  COWLS REMOVED ONLY TO DISC	OVER LARGE FIST SIZE BURN HOLE THROUGH LT MUFFLER AND HEAT MUFF SHROUD. CARB HEAT HOSE WAS TOTALLY BURNED OFF AND INDUCT	ION AIR BOX SUSTAINED MINOR DAMAGE BUT NOT TO AIR VALVE OR SEAL.  CAUSE WAS DETERMINED TO BE THAT THE INTERNAL BAFFLE HA	D BROKEN AWAY AT THE TOP TACK WELDS AND FALLEN DOWN CAUSING A HEAT SINK ON THE MUFFLER BOTTOM AND BURNING THROUGH.  NEW 	PARTS WHERE INSTALLED AND REPAIRS TO LOWER COWL CARRIED OUT AND AIRCRAFT RELEASED FOR RETURN TO SERVICE.		1	H	7	1 	3O			NC	3A23    					 
2005100500028	20051005	00028	EA  	2005	10	5	CA050920008      	2	20050809	G	8530	CLASSCN13	CYLINDER BORE   			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540D4A5   	41532	EA  					NR 4 CYLINDER	DAMAGED         	W				O				OTHER                   				M			OVER TEMP                 			CR	CRUISE         	1			CA								L2833248A			(CAN) PILOT NOTICED INCREASED CHT IN FLIGHT UTILIZING GEM (GRAPHIC ENGINE MONITOR) ON NR 4 CYLINDER AND RICHEN UP MIXTUR	E TO MAINTAIN COOLER CHT.  MAINTENANCE PERSONNEL DISCOVERED 0/80 DURING COMPRESSION TEST AND REMOVED AFFECTED CYLINDER O	NLY TO FIND THAT 408.0 AFTER TOP OVERHAUL AT ECI WHERE CYLINDER WAS RE-CHROMED THAT 80% OF THE CHROME HAD SHED OFF THE C	YLINDER WALLS AND DEPOSITED ITSELF THROUGHOUT THE ENGINE.  THE REMAINING CYLINDERS WERE REMOVED DUE TO SCORING AND REPLA	CED WITH SERVICEABLE CYLINDER ASSY'S.  THE ENGINE WAS DECONTAMINATED AN AFTER DUE DILIGENCE RETURNED TO SERVICE.  ENGINE	 TSO 1524.8	1	H	7	1 	3O	3	O		A7EA    	1E4				 
2005110700212	20051107	00212	CE  	2005	11	7	CA050921001      	1	20050916	G	5310	50430043BG5	DOOR FRAME      			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A DAILY INSPECTION 2 CRACKS WERE DETECTED ON EACH SIDE OF THE UPPER ATTACHMENT FOR THE REAR DOOR. THE PART 	WAS REPLACED.					1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005100500031	20051005	00031	NM  	2005	10	5	CA050921003      	1	20050921	G	2920	654468117	MODULE          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION OF THE STANDBY HYDRAULIC SYSTEM, BOEING TASK CARD B27-21-94-2A, FLUID WAS NOTED LEAKING FROM 	THE STANDBY HYDRAULIC MODULE.  ON INVESTIGATION THE UNIT WAS FOUND TO BE CRACKED.  THE UNIT WAS REPLACED WITH A SERVICEA	BLE UNIT.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005110700213	20051107	00213	NE  	2005	11	7	CA050922001      	2	20050921	G	7421	103815504	EXCITER         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	IGNITION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NN01322784					(CAN) ENGINE FAILED TO LIGHT AT REMOTE COMMUNITY AIRPORT.  IGNITION EXCITER BOX FOUND TO BE AT FAULT. FAILED UNIT HAD BE	EN REPLACED AT ENGINE CHANGE, 17.4 HRS PREVIOUS.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110700214	20051107	00214	EU  	2005	11	7	CA050922002      	1	20050915	G	7160	5302412151	STRUCTURE       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	INTAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRACES OF EXHAUST EMISSIONS WERE NOTICED COMING OUT OF EDGE OF INTAKE LIP.  PART WAS REMOVED FROM COWL AND WITH TH	E TAPE AND INSULATION REMOVED,  AN 8 INCH CRACK WAS REVEALED ON THE AFT SIDE OF THE EXHAUST CHAMBER PASSAGE. NEW INTAKE 	LIP KIT WAS FITTED, RETURNED TO SERVICE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110700215	20051107	00215	EU  	2005	11	7	CA050922003      	1	20050915	G	3020	978731530	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PARTICAL SEPARA	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) PARTICLE SEPARATOR ACTUATOR FAILED TO OPERATE.  UNIT REPLACED WITH SERVICEABLE UNIT, TESTS SATISFACTORY.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005101300117	20051013	00117	NM  	2005	10	13	CA050922004      	1	20050920	G	5420	311A106595	PANEL           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					NACELLE	DEPARTED        	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) WHEN DEPARTING, AC HAD A NR1 ENG NACELLE STRUT ACCESS PANEL DEPART FROM AC.  AC WAS INSPECTED FOR DAMAGE RESULTING	 FROM DEPARTURE OF THIS PANEL, AND FOR  POSSIBLE CAUSE.  REST OF PANELS WERE CHECKED FOR SECURITY. NO ADDITIONAL FAULTS 	FOUND. AC WAS RELEASED BACK INTO SERVICE UNDER CDL 54-20-1 AND PANEL WAS REPLACED THAT NIGHT. PANEL IS SECURED INTO PLAC	E USING ZEUS OR CAM-LOCK STYLE FASTENERS. COULD NOT FIND ACTION OR MAINT ACTIVITY THAT WOULD HAVE LED TO DEPARTURE OF TH	IS PANEL. THIS ONLY INCLUDED PANELS WITH SCREWS AS SCREWS WERE COMING LOOSE AND FALLING OUT. TECH INFO BULLETIN (TIB) TO	 ALL MAINT STAFF TO PROVIDE A REMINDER OF THE PROCESS FOR SECURING THESE PANELS AND THEIR FASTENERS.	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005110700216	20051107	00216	CE  	2005	11	7	CA050922005      	1	20050912	G	5522		SKIN            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE ELEVATOR IAW AD 2005-18-21 AND COMMUNIQUE NO. 261, SMOKING RIVETS WERE DISCOVERED IN THE 	LOWER SKIN OF BOTH ELEVATORS (2 IN THE LT, 4 IN THE RT).  REQUIRED REPAIRS WERE CARRIED OUT.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005110700217	20051107	00217	EA  	2005	11	7	CA050923001      	1	20050709	G	3234	555405	SELECTOR VALVE  	MESSIER     	555405      	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE 3A AND 3B HYD PUMPS WERE TURNED ON.  SHORTLY THEREAFTER THE SYSTEM 3 HIGH TEMP MSG CAME ON.  QRH F	OLLOWED AND TURNED OFF 3A PUMP TO ISOLATE PROBLEM.  THE HIGH TEMP WENT OUT.  ON SHORT FINAL THE CREW PUT GEAR DOWN, THE 	GEAR DISAGREE MSG CAME ON ASSOCIATED WITH THE NOSE GEAR.  THE CREW FOLLOWED QRH AND PULLED THE LANDING GEAR MANUAL RELEA	SE, THE NOSE GEAR CAME DOWN FINE.  MX REPLACED THE ACTUATOR AND THE SELECTOR VALVE, SWING CHECKS GOOD. PARTS REMOVED: AC	TUATOR, P/N 16520-101, VENDOR: MESSIER-DOWTY.  SELECTOR VALVE, P/N 55540-5, VENDOR: VICKERS.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110700218	20051107	00218	NE  	2005	11	7	CA050923002      	2	20050525	G	7200	6089T11G01	ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2	OVERHEATED      	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) MFG HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT.  THE FLIGHT CREW REJECTED TAKE-OFF WHEN THEY NOTICE	D THE AIRCRAFT VEERING TO THE RT ASSOCIATED WITH ENGINE NR 2 OIL PRESSURE AND ITT ABNORMALITIES.  TAKE-OFF WAS ABORTED A	T APPROXIMATELY 100 KNOTS.  RT ENGINE REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110700219	20051107	00219	EA  	2005	11	7	CA050923003      	1	20050804	G	7110	BLC3BC09SL5C	PIN             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COWL	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) FLIGHT CREW HAD TO SHUT DOWN THE LT ENGINE ON FINAL AS THE LT THROTTLE WOULD NOT RETARD BELOW 93 PERCENT.  THE THR	OTTLE WAS ABLE TO ADVANCE TO PROVIDE MORE POWER, BUT WOULD NOT RETARD BELOW 93 PERCENT.  FOUND THAT THE UPPER COWL PIN H	OLDING THE ROD HAD BROKEN WHICH LET UPPER CORE COWL SUPPORT ROD POSITION ITSELF AT THE THROTTLE MAIN FUEL CONTROL CONNEC	TION FROM THE THROTTLE CONTROL BOX.  THE PIN ITSELF WAS INTACT, BUT THE TWO SPRING LOADED BALLS AT THE END OF THE PIN HA	D COME APART ALLOWING THE PIN TO COME OUT.  CODE: V84256.(SEE ALSO: US 2005081600047)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005100500040	20051005	00040	SO  	2005	10	5	CA050923004      	2	20050922	G	8530	AEC65385	CYLINDER HEAD   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT CAME TO DOCK WITH A DISTINCT AIR LEAKAGE SOUND FROM THE ENGINE, FURTHER INVESTIGATION FOUND THE CRACKED C	YL HEAD.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2005110700220	20051107	00220	EU  	2005	11	7	CA050923005      	1	20050824	G	5554	9411412107	BUSHING         	PILATS      		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) DURING AN INSPECTION THE TOP RUDDER BUSHING WAS FOUND TO BE WORN BEYOND LIMITS. RUDDER WAS REMOVED AND RUDDER WAS 	REPAIRED IAW MFG TECH MEMO ECE -12-TM-02-327.  RUDDER REINSTALLED AND CHECKED FOR TRAVEL IAW MM.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110700221	20051107	00221	SO  	2005	11	7	CA050923006      	1	20050912	G	3260	487862	DOWNLOCK SWITCH 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT MLG	STUCK           	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA			12481								(CAN) ON APPROACH THE GEAR WAS LOWERED FOR LANDING AND THE RT GEAR DID NOT INDICATE DOWN AND LOCKED.  FIGHT CREW NOTIFIE	D FLIGHT SERVICES THAT THEY WOULD DO A FLY PASS SO MAINTENANCE CREWS COULD CHECK TO SEE IF THE GEAR WAS EXTENDED. THE GE	AR WAS DOWN AND APPEARED TO BE LOCKED SO THE AIRCRAFT LANDED WITH NO PROBLEM.  THE AIRCRAFT WAS TAKEN TO MAINTENANCE AND	 PLACED ON JACKS GEAR OPERATION WAS CHECKED AND IT WAS FOUND THE THE RT DOWN SWITCH WAS DIRTY AND STUCK.  ALL SWITCHES W	ERE CLEANED AND THE GEAR OPERATION CHECKED FOR 5 CYCLES. MAINTENANCE/FLIGHT CREWS WERE INFORMED OF THE PROBLEM.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005100500041	20051005	00041		2005	10	5	CA050923007      	4	20050913	G	3461	160E046X	GLIDE SLOPE     			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  					COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											GLIDESLOPE DEVIATION ON EHSI INVERTED.  GLIDESLOPE INFORMATION INTERFACED ON ARINC 429 DATA BUS.  EFIS MANUFACTURER ACKN	OWLEDGES PROBLEM IS SOFTWARE IN EHSI, AWAITING SOFTWARE FIX FROM MANUFACTURER.  DEFECT IS ALSO PRESENT IN EADI WHEN EADI	 IS IN FORCED COMPOSITE MODE (IE. EHSI FAILED).				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005100500042	20051005	00042	NM  	2005	10	5	CA050923008      	1	20050921	G	5420	315A1580507	VENT            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A SCHEDULED PHASE INSPECTION THIS VENT, WHICH IS ON THE ENGINE THRUST REVERSER COWL WAS FOUND TO HAVE A 2 INCH 	CRACK.  A SIMILIAR CRACK WAS FOUND ON A PHASE CHECK THE DAY BEFORE ON ANOTHER AIRCRAFT.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005100500043	20051005	00043	NM  	2005	10	5	CA050923009      	1	20050922	G	2740	6548244090	SEAL            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					RUDDER	FOD             	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) WHILE THIS A/C WAS IN HANGAR FOR A SCHEDULED PHASE CHECK, IT WAS NOTICED BY A MECHANIC THAT THERE APPEARED TO BE F	OREIGN MATERIAL STICKING OUT OF THE RUDDER BALANCE WEIGHT CUT-OUT SEAL.  ON CLOSER INSPECT IT WAS FOUND TO BE TWO BAGS O	F PNL ATTACHMENT HARDWARE AND A PARTS REMOVAL TAG SITTING ON WEB IN AREA OF BALANCE WEIGHT, MID-WAY UP VERTICAL STAB.  I	NSPECT OF AREA REVEALED NO DAMAGE.  THIS FOD WAS LEFT BEHIND DURING THE RECENT VISIT AT A MX FACILITY OUTSIDE OF CANADA.	 THIS IS SECOND FOD DISCOVERY ON A/C. SINCE THIS TIME WE HAVE INITIATED A FLEET CAMPAIGN TO CHECK BEHIND ALL FLT CONTROL	 ACCESS PANELS FOR FOD DURING THE NEXT OVERNIGHT VISITS TO OUR MX FACILITY.  IN ADDITION, ALL OTHER ACCESS PANELS WILL B	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005110700222	20051107	00222	WP  	2005	11	7	CA050923010      	1	20050921	G	2435	BC3151004	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START UP, THE STARTER WOULD NOT ENGAGE. THE STARTER WAS REMOVED AND REPLACED WITH ANOTHER UNIT AND THE  PRO	BLEM NO LONGER WAS EVIDENT. WE HAVE HAD SEVERAL STARTER PROBLEMS AND ROBINSON ARE TRYING TO SOLVE THE ISSUE.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2005120200052	20051202	00052	EU  	2005	12	2	CA050923011      	1	20050922	G	3212	2033931	FLOAT           		2033931     	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					EMERGENCY FLOATS	ACTIVATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0201					HAD JUST FINISHED TRACING, BALANCING AC, BEGAN REMOVING BALANCING EQUIP. A/C READY DEPARTURE, LT SIDE EMERGENCY FLOAT IN	FLATED.  AC HAD JUST COMPLETED TRANSMISSION CHANGE, ENGINE REMOVAL/REPAIR/REISTALLATION.  DURING MAINT, EMERGENCY FLOATS	 SAFETY PINS WERE INSTALLED. UPON COMPLETEING MAINT, PINS WERE REMOVED AND SYS ARMED.  IMPORTANT TO NOTE THAT SPACE TO I	NSERT,  REMOVE SYS SAFETY PINS IS SMALL. ACTUATION CABLE MAY HAVE BEEN BUMPED UPON REMOVAL. DUE TO THE DESIGN OF SYS, (B	UMP) WOULD USUALLY ACTUATE BOTTLE IMMEDIATELY.  FACTORY HAS BEEN NOTIFIED, WILL CHECK VALVE CAREFULLY. FLOAT BOTTLES/VAL	VES HAD 7 MONTHS TO GO BEFORE THEY WERE DUE FOR A 36 MONTH OH.  SYS IS PRESENTLY DISABLED PENDING REPORT.	1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005100500044	20051005	00044	NE  	2005	10	5	CA050924001      	2	20050921	G	7230	110036106	BLADE           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					COMPRESSOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) AS THE A/C WAS APPROACHING STAGING WITH A SLING LOAD, THE PILOT HEARD A LOUD BANG FOLLOWED BY A LOUD SCREECHING NO	ISE FROM THE ENGINE.  THE A/C LANDED IMMEDIATELY WITH POWER AND THE ENGINE SHUT DOWN.  UPON FURTHER INVESTIGATION, ONE O	F THE COMPRESSOR FIRST STAGE ROTOR BLADES WAS FOUND BROKEN AT THE ROOT AND MISSING.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2005100500045	20051005	00045	NM  	2005	10	5	CA050926001      	1	20050923	G	7740	C19190AB04	DISPLAY         			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					COCKPIT	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK-AROUND, DC PWR HAD BEEN APPLIED AND ONLY ENGINE DISPLAY AND NR 2 MFD HAD BEEN TURNED ON.  SHORTLY AFTE	R (AROUND 1MIN) BIG GREEN T FOR THE TESTING MODE FLASHED ON NR 1 MFD (NOTICE THAT THE SWITCH FOR THIS MFD WAS STILL OFF)	. A BURNED ODOR CAME FROM WAY BACK IN CABIN ACCOMP AGAIN WITH A THICK SMOG.  SMOKE CAME FROM FAULTY DISPLAY UNIT & SPREA	D INSIDE CABIN THRU INSTRUMENT COOLING DUCTS, WHICH ARE CONNECTED TO CABIN VENT SYS.  AFTER A SHORT INVESTIGATION, BREAK	ER FOR NR 1 MFD FOUND OUT.  NR 1 MFD FOUND TO BE INTERNALLY DEFECTIVE CAUSING BREAKER TO COME OUT & SMOKE & BURNED ODOR 	INSIDE CABIN. TROUBLESHOOTING SWITCH FOR FAULTY DISPLAY UNIT DID NOT HAVE TO BE ON TO CAUSE BREAKER TO COME OUT.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005110700305	20051107	00305	SO  	2005	11	7	CA050926002      	2	20050926	G	8530		ROCKER BOSS     			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	CYLINDER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION, BRASS AND ALUMINUM PARTICLES FOUND IN FILTER. ROCKER BOSSES AND BUSHINGS FOUND WORN. THIS SHOWS UP 	AT ABOUT 200 HRS IN SERVICE AND HAS HAPPENED TO ALL CYLINDERS THAT ARE FACTORY NEW IN THE LAST COUPLE OF YEARS.  ACCORDI	NG TO THE FACTORY WE ARE THE ONLY OPERATOR THAT THIS HAS HAPPENED TO, THEIR FIX IS TO BUSH THE BOSSES WHICH THEY WILL DO	 UNDER WARRANTY BUT THEY WILL NOT DO IT RT FROM THE FACTORY WHICH CAUSES A GREAT DEAL OF DOWN TIME COST.			1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2005110700223	20051107	00223		2005	11	7	CA050926003      	4	20050920	G	6122	8210212E	GOVERNOR        			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE RT PROPELLER RPM OCCASIONALLY FLUCTUATED 100 RPM WITH NO INPUT FROM THE CREW. THE DEFECT WAS CO	NFIRMED ON THE GROUND BY MAINTENANCE AND THE PROPELLER GOVERNOR WAS REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005100500046	20051005	00046		2005	10	5	CA050926004      	1	20050922	G	2435	M230881320	BRUSHES         	LUCAS       																STARTER GEN	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											BRUSHES FROM LOT  MC20987 BATCH  072905 APPEAR TO HAVE A HIGHER THAN NORMAL RESISTANCE.  THE NOTICEABLE SYMPTOMS ARE SUR	FACE BLUING OF THE ARMATURE COMMENTATOR, EXCESSIVE CURRENT DRAW AND INCREASED FIELD FRAME TEMPERATURE DURING BRUSH RUN I	N ON THE STARTER GENERATOR.  THESE BRUSHES HAVE BEEN RETURNED TO MIRAJ CORPORATION FOR EVALUATION OF THE CARBON GRADE PR	OPERTIES.  A FINDINGS REPORT HAS BEEN REQUESTED.																 
2005110700224	20051107	00224	CE  	2005	11	7	CA050926005      	1	20050926	G	3097	2601048200	CONNECTOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROP HEAT	MELTED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) APPROXIMATELY 5 TO 10 MIN BEFORE LANDING THE PILOT NOTICED A FAINT SMELL OF SMOKE OR SOMETHING BURNING. EVERYTHING	 WAS OPERATING NORMALLY AND HE LANDED WITHOUT MISHAP. UPON INSPECTION, THE PROP HEAT WIRE CONNECTOR BETWEEN THE CIRCUIT 	BREAKER AND PROP DE-ICE TIMER WAS FOUND TO BE MELTED AND BURNED. THE WIRE TERMINAL ENDS AND CONNECTOR WERE REPLACED AND 	THE PROP HEAT SYSTEM FUNCTION CHECKED SERVICEABLE.  THE CONNECTOR IS LOCATED ON THE LT SIDE OF THE COCKPIT JUST IN FRONT	 OF THE CIRCUIT BREAKER PANEL.		1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2005110700225	20051107	00225	SW  	2005	11	7	CA050927001      	1	20050922	G	2921	MS28775212	PACKING         	BELL        	212076007003	BELL  	412   	412EP       	1182205	SW  										ACCUMULATOR	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING FTP'S, MS28775-212 PACKING FAILED CAUSING LOSS OF HYDRAULIC FLUID FROM ACCUMULATOR ASSY, 212-076-007-003.						1	G	7	2 	4U				H4SW    					 
2005110700202	20051107	00202	SW  	2005	11	7	CA050927002      	1	20050927	G	2730	31072	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELEVATOR UP CONTROL CABLED FRAYED AT AFT PULLEY.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2005100500047	20051005	00047	NE  	2005	10	5	CA050927003      	2	20050923	G	8530		CYLINDER        			DOUG  	DC4   	C54ADC      	3021510	WP  	PWA   	R2000 	R20007M2    	52023	NE  					NR 8	CRACKED         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											THE NR 8 CYLINDER CRACKED AT THE EXHAUST VALVE CAUSING THE ENGINE TO SHAKE.						2	L	7	4 	4R	4	R		A762    	5E5				 
2005120200055	20051202	00055	EU  	2005	12	2	CA050927004      	1	20050920	G	3240		LOCK            			EMB   	ERJ170	ERJ170100   	       	EU  										MLG BRAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											IT IS OBVIOUS THAT THIS AC EXPERIENCED A LOCKED BRAKE CONDITION FOR WHATEVER REASON. A MEMBER OF THE SIDE STAY LOCKING A	RM IS BROKEN IN TWO. THERE IS NO PART MISSING, NORMALLY 2 PARTS SHOULD BE TOGETHER. PROXIMITY SENSOR IS ALSO VISIBLE. BR	AKING EVENT WOULD NOT HAVE RESULTED IN BREAKAGE OF THIS LINK, WHAT BROKE IT SEEMS TO BE APIECE OF TREAD FROM THE TIRE. A	 BLACK TIRE MARK IS VISIBLE ON PARTS NEXT TO RUPTURE.  TIRE TREAD FAILURE SHOULD NOT CAUSE RUPTURE OF A PRINCIPAL STRUCT	URAL ELEMENT OF A LANDING GEAR. IF TREAD FAILURE WOULD OCCUR ON TAKE-OFF, IT COULD RESULT IN A COLLAPSE OF LANDING GEAR 	AT HIGH SPEED WHICH MIGHT NOT BE JUST AN INCIDENT. HAVE BEEN TOLD THAT TREAD FAILURE IS NOT UNCOMMON ON THAT AIRCRAFT.	2	L	7	4 	4F			RT	A56NM   					 
2005110700203	20051107	00203	CE  	2005	11	7	CA050928001      	1	20050923	G	5312		BULKHEAD        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19662								(CAN) DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON ANOTHER AIRCRAFT, (SDR 20050829003) THE SAME TWO AREAS OF THE 	AFT PRESSURE BULKHEAD WERE FOUND CHAFED BY THE TWO INTERCOSTALS ADJACENT TO THE TAIL ACCESS DOOR. NDT WAS COMPLETED AND 	THERE WERE NO CRACKS FOUND. THE INTERCOSTALS WERE TRIMMED BACK TO MAINTAIN A CLEARANCE WHEN THE AIRCRAFT IS PRESSURIZED 	AND PREVENT FURTHER CHAFING AND POSSIBLE CRACKING. WE HAVE SET UP A FLEET CAMPAIGN TO INSPECT ALL OF OUR AIRCRAFT AS THE	Y COME DUE FOR THEIR NEXT PHASE INSPECTION.		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2005110700204	20051107	00204	EA  	2005	11	7	CA050928002      	1	20050927	G	5411	C6WM1712	LONGERON        			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT THE LOWER LONGERON INSPECTION IAW AD CF 81-07R4 AND SB 6/509, THE LT IB LONGERON ON THE RT NACE	LLE WAS FOUND CRACKED LATERALLY ACROSS THE WEB. THE CRACK WAS JUST AFT OF THE ENGINE MOUNT.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005110700205	20051107	00205	EA  	2005	11	7	CA050928003      	1	20050927	G	3246	L814710	BEARING RACE    	BFGOODRICH  		DHAV  	DHC7  	DHC71       	2802702	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	MAIN WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE VISUAL INSPECTION THE INNER BEARING RACE OF THE NR 4 MAIN WHEEL ASSY WAS FOUND CRACKED.						2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2005110700206	20051107	00206	NM  	2005	11	7	CA050929001      	1	20050928	G	7600	87620130101	SHAFT           	DHAV        		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	SPRING STRUT	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) DURING POST ENGINE CHANGE RIGGING NR 1 ENGINE SPRING STRUT ASSEMBLY WAS REMOVED DUE TO EXCESSIVE PLAY (SLOPPY AT L	OOSE).  AFTER DISASSEMBLY AND INSPECTION SHAFT P/N87620130 WAS BROKEN AT POINT RIVET P/N MS204170AD3. THE SIZE OF THE RI	VET LEAVES MINIMAL MATERIAL AROUND THE HOLE IN THE SHAFT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005110700207	20051107	00207	NE  	2005	11	7	CA050929002      	2	20050923	G	7261	30607493	CAP             			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					OIL TANK	LOOSE           	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA								113107			(CAN) AFTER TAKEOFF,LOSS OF LT ENGINE OIL PRESSURE. SHUT DOWN LT ENGINE, DECLARED EMERGENCY AND RETURNED TO BASE. ENGINE	 SHOWED SIGNS OF OIL LEAK ON LT COWL. INVESTIGATED OIL LEAK AND FOUND THE OB OIL CAP LOOSE. INSPECTED OIL CAP/DIP STICK 	O-RING AND LOCKING ASSY SERVICEABLE. CLEAN DOWN ENGINE OIL SPILLAGE AND SERVICED ENGINE WITH MOBIL 254. C/O GND RUNS AND	 ENGINE PERFORMED SERVICEABLE. NO APPARENT LEAKS ON ENGINE. AIRCRAFT RELEASED FOR RETURN TO SERVICE.			2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2005110700208	20051107	00208	WP  	2005	11	7	CA050929003      	1	20050926	G	6330	A6502	BOLT            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					XMSN MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRANSMISSION MOUNTING BOLT WAS REMOVED FOR 2200 HR AIRCRAFT OVERHAUL.  CRACK UNDER HEAD WAS FOUND DURING NDT.  THE	 CRACK CAN NOT BE SEEN WITH VISUAL INSPECTION. THE BOLT HAS ATLEAST 2200 HR.  AIRCRAFT HAS 6366.9 HRS.					1	G	7	1 	3O	3	O		H11NM   	E295				 
2005110700172	20051107	00172	EU  	2005	11	7	CA050930001      	1	20050920	G	3040	9714231705	TERMINAL BLOCK  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSHIELD HEAT	MELTED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) THE WINDSHIELDS DE-ICE SYSTEM WAS SNAGGED AS DEFECTIVE BY THE PILOTS. AFTER INSPECTION OF THE SYSTEM 3 TERMINAL BL	OCKS LOCATED IN THE COCKPIT ROOF PORTION WERE FOUND TO HAVE OVERHEATED. ALL (3) TERMINAL BLOCKS AND BOTH WINDSHIELDS HAV	E BEEN REPLACED. SYSTEM WAS TESTED AND FOUND SERVICEABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110700173	20051107	00173	NE  	2005	11	7	CA050930002      	1	20050921	G	6210	6117020221067	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					MAIN ROTOR	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) COCKPIT BIM INDICATOR ILLUMINATED ON TAKEOFF.  AIRCRAFT RETURNED TO RAMP. VISUAL INDICATION REVELED (BLUE) MAIN RO	TOR BLADE BIM INDICATOR IN THE BLACK.  MAIN ROTOR BLADE REPLACED.					2	G	7	2 	4U	4	U		1H15    	1E3				 
2005110700174	20051107	00174	SW  	2005	11	7	CA051001001      	1	20050930	G	3213	212321103	CROSSTUBE       			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA											(CAN) HIGH SKID GEAR.  UPON LANDING THE FRONT CROSS TUBE CRACKED IN THE MIDDLE OF THE TUBE, BETWEEN THE MOUNTING SADDLES	.  FROM THE INFORMATION WE HAVE AT THIS TIME, THE AIRCRAFT WAS NOT HARD LANDED.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2005110700287	20051107	00287	EA  	2005	11	7	CA051002001      	1	20050923	G	5610	601R33033177	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FLT LEVEL 370 CAPT WINDSHIELD CRAKED. THE AIRCRAFT DIVERTED AND LANDED WITHOUT INCIDENT.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005110700288	20051107	00288	CE  	2005	11	7	CA051002002      	1	20050922	G	5753	1457711	GIMBAL JOINT    			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FLAP ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						11651172					(CAN) FOUND LEADING EDGE OF LOWER PANEL COVERING OB FLAP ACTUATOR ON BOTH LT AND RT FLAPS DAMAGED. INVESTIGATION FOUND L	OWER PIN P/N 145680-1 AND SNAP RING P/N 9-INI7437A2-70 HAD COME OUT OF THE BOTTOM OF GIMBAL ASSY. P/N 145771-1. PART OF 	ACTUATOR P/N 6627503000-011. WHEN THE ABOVE PIN CAME LOOSE IF ALSO GOUGED THE LEADING EDGE OF THE FLAP ACTUATOR CUTOUT F	RAME. THE ACTUATOR HOUSING ALSO CONTACTED THE LEADING EDGE OF THE COVER PANEL. THE DAMAGED AREAS WERE BLENDED OUT AND TR	EATED IAW MFG ENGINEERING AND BOTH FLAP ACTUATORS REPLACED.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2005110700289	20051107	00289	NM  	2005	11	7	CA051003001      	1	20051001	G	5730	BACB30NN4K12	SCREW           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					RT WING	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING, AFTER THE AIRCRAFT WAS REFUELED, FUEL WAS OBSERVED COMING FROM THE RIGHT WING FORWARD OF THE IB FLA	P TRACK.  THE FUEL ACCESS PANEL DIRECTLY AFT OF THE RT WING NACELLE WAS FOUND LEAKING.  ON INVESTIGATION SEVERAL SCREWS 	WERE FOUND TO BE STRIPPED AND LOOSE.  AFTER RESEALING THE ANCHOR NUTS AND REPLACING THE SCREWS, THE TANK WAS LEAK CHECKE	D SERVICEABLE.  THE ACCESS PANEL HAD LAST BEEN REMOVED, DURING A PRE-LEASE C-CHECK.			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005110700290	20051107	00290	CE  	2005	11	7	CA051003002      	1	20050929	G	5610	10138402515	WINDSHIELD      			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	FRACTURED       	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE ON ROUTE, AT 23,000 FEET AT 12 NOON, OAT -25 C, WINDSHIELD HEAT ON. THE PILOTS (LT) INNER LAYER OF WINDSHIEL	D FRACTURED WITHOUT WARNING DURING FLIGHT. NO LOSS OF CABIN PRESSURE OR OTHER EFFECTS FROM WINDSHIELD DELAMINATING. EMER	GENCY WAS DECLARED AND THE AC WAS LANDED WITH OUT FURTHER INCIDENT.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2005110700291	20051107	00291	GL  	2005	11	7	CA051003003      	2	20050911	G	7532	23005367	BLEED VALVE     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						CAC70413					(CAN) TOT RUNNING TO WARM. BLEED VALVE STICKING OPEN. BLEED VALVE CHANGE PROBLEM GOES AWAY.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005110700292	20051107	00292	EA  	2005	11	7	CA051003004      	2	20050929	G	8530	05K21100	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER HEAD SEPARATED FROM CYLINDER BARREL WHILE IN FLIGHT.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061200434	20060612	00434	CE  	2006	6	12	CA051003005      	1	20050813	G	7334	10038901819	PRESSURE SWITCH 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					FUEL SYSTEM	NO INDICATION   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FUEL WARNING LIGHT WOULD NOT INDICATE WHEN A/C WAS SHUT DOWN, IT IS SUPPOSE TO UNDER NORMAL PROCEDURES.  SWITCH WAS REPL	ACED WITH SAME PART NUMBER AND CORRECT AS PER IPC.  NEW SWITCH ALSO WOULD NOT WORK.  A SECOND NEW SWITCH WAS TRIED, IT A	LSO DID NOT WORK.  AFTER CONVERSATIONS WITH BEECHCRAFT TECHNICAL REP, IT WAS DISCOVERED SWITCH HAS A VENT HOLE SHOULD BE	 OPEN TO ATMOSPHERE.  FAILING SWITCHES HAD METAL TAG THAT COVERED THE VENT HOLE.  SUSPECT SWITCHES HAD TAG REMOVED AND T	HE SWITCHES WERE TESTED AND FOUND SERVICEABLE.  INFORMATION WAS FORWARDED TO BEECHCRAFT AND THEY ARE INFORMING THE VENDO	R OF THIS ERROR.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005110700293	20051107	00293	NE  	2005	11	7	CA051003006      	2	20050913	G	7250	0292803080	TURBINE BLADES  			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	FAILED          	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT THE ALF INSPECTION, THE ENGINEER NOTICED THAT A PORTION OF A TURBINE BLADE WAS MISSING.  A THOR	OUGH INSPECTION WAS CARRIED OUT UPSTREAM OF THE MO4 UTILIZING A BORESCOPE, NO ANOMALIES WHERE NOTED.  ANOTHER S/N MO4 WA	S INSTALLED WITH NO FURTHER INDICATION OF PROBLEMS.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005110800056	20051108	00056	CE  	2005	11	8	CA051003007      	1	20050913	G	3230	481	MOTOR           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) UPON SELECTION OF GEAR DOWN, PILOT NOTICED THAT GEAR WOULD NOT EXTEND AND THAT THE CIRCUIT BREAKER HAD POPPED. HE 	RESET IT AND SELECTED GEAR DOWN AGAIN WITHOUT ANY SUCCESS. PILOT USED EMERGENCY EXTENSION AND LANDED WITHOUT INCIDENT. U	PON INSPECTION OF LANDING GEARPOWER PACK MOTOR BY ENGINEER, IT WAS FOUND TO BE SHORTED OUT. MOTOR WAS REPLACED AND EXTEN	SION/RETRACTION SYSTEM FUNCTIONALLY CHECKED SERVICEABLE.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005110800057	20051108	00057	GL  	2005	11	8	CA051003008      	2	20050527	G	7261	23038241	LABYRINTH SEAL  	ALLSN       	250C20B     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					RT EXHAUST	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			11637	11637		CAE831793					(CAN) SUBJECT ENGINE WAS REMOVED FROM A/C FOR EXCESSIVE OIL VENTING FROM EXHAUST. THE DIFFUSER VENT ORIFICE HAD BEEN PRE	VIOUSLY ADJUSTED TO REDUCE VENTING, BUT WAS UNSUCCESSFUL. THE ENGINE WAS SENT BACK TO ENGINE SHOP FOR REPAIR. THE TURBIN	E WAS DISMANTLED BY THE ENGINE SHOP, AND THE POWER TURBINE LABYRINTH SEALS WERE ADJUSTED AS REQUIRED. THEY ALSO REPAIRED	 CRACKS FOUND IN COMBUSTION SECTION, TO ALLEVIATE EXCESS VENTING. THE ENGINE WAS INSTALLED IN THE TEST CELL AND RUN UP. 	THE ENGINE SHOP REPORTED NO OIL VENTING FOUND DURING THE RUNUP. THE ENGINE WAS RETURNED AND REINSTALLED IN THE AIRCRAFT.	 THE AIRCRAFT WAS RUNUP AND RETURNED TO SERVICE.	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005110800058	20051108	00058	EU  	2005	11	8	CA051003009      	1	20050911	G	2435	230791281	BRUSHES         	LUCAS       	23079009    	BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	STARTER GEN	FRAYED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						6619					(CAN) FOUND WIRES NOT FASTENED TO STARTER GENERATOR BRUSHES, DUE TO RIVET BEING LOOSE,WHICH THEN CAUSED ARCING OF WIRE A	ND RIVET TO CAUSE THE TEMPOR OUT OF THE RIVET .					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2005121900061	20051219	00061	SW  	2005	12	19	CA051003010      	1	20050312	G	2435	23032018	STARTER GEN     			BELL  	206   	206B        	1181511	SW  										ENGINE	ARCED           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											THE SUBJECT STARTER/GENERATOR WAS REMOVED FOR EXCESS ARCING ON STARTUP.  THE STARTER/GENERATOR WAS SENT TO A REPAIR FACI	LITY TO BE INSPECTED AND REPAIRED AS NECESSARY.  IT WAS NOTED FROM THE REPAIR FACILITY THAT THE STARTER SHOWED SIGNS OF 	OIL CONTAMINATION, WHICH WOULD CAUSE THE FAILURE.  IT WAS NOTED THAT THIS STARTER/GENERATOR WAS REMOVED FROM AN AIRCRAFT	 THAT HAD A PROBLEM WITH EXCESSIVE OIL VENTING FROM THE ENGINE EXHAUST.  THIS IS WHAT WAS CONCLUDED AS THE SOURCE OF THE	 OILCONTAMINATION.  THE STARTER/GENERATOR WAS REPAIRED THE FACILITY AND RETURNED TOTHE CUSTOMER.		1	G	7	1 	3U				H2SW    					 
2005120200064	20051202	00064	GL  	2005	12	2	CA051003011      	2	20050916	G	7323		CLIP            	GENDESIGN   		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ACTUATOR ROD	DISCONNECTED    	W				A				UNSCHED LANDING         				R	O		PARTIAL RPM/PWR LOSS      	OTHER                     		DE	DESCENT        	1			CA						4728A					(CAN) DURING DESCENT, CNTRL N2 SPEED W/ACTUATOR TRIM SWITCH, PILOT (BEEPED) N2 SPEED DOWN. N2 SPEED REDUCED BELOW LIMITS	, APPROX 70 PERCENT. AT THIS N2 SPEED ENG IS UNABLE TO PRODUCE REQUIRED PWR FOR NML OPS. PILOT ATTEMPTED TO (BEEP) N2 SP	EED UP, GOV DID NOT RESPOND. LANDING WAS NML. NO DAMAGE WAS SUSTAINED TO AC OTHER THAN MINOR INDENTATIONS ON MAIN ROTOR 	BLADES.  EXAM OF N2 GOVERNOR, CONTROLS, LINEAR ACT ROD HAD EXTENDED BEYOND INTERNAL STOPS OF ACT, WHICH HAD SET THE N2 G	OV SPEED BELOW NML LIMITS, ROD HAD DISENGAGED FROM ACT INTERNAL DRV SYS, DIS-ENABLING TRIM (BEEP) CNTRL OF N2 GOV. EXAM 	OF LINEAR ACT, CIRCLIP ON EXTNL ROD WAS FOUND TO BE MISSING. NO RECORD OF LINEAR ACT HAVING BEEN REPLACED OR O/H.	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005110800059	20051108	00059	SO  	2005	11	8	CA051003012      	1	20050916	G	8120		TURBOCHARGER    		LW12689     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						HK028772					(CAN) SAW SMOKE DURING FLIGHT.  RETURN TO BASE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005110800060	20051108	00060	EU  	2005	11	8	CA051003013      	1	20050910	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAILING EDGE CRACKED. BLADES WHERE DESTROYED, ONLY HAD 125 HOURS REMAINING ON THEM. INSTALLED A NEW SET OF BLADES 	SAME PART NUMBER.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005110800061	20051108	00061	EU  	2005	11	8	CA051003014      	1	20050909	G	6220	704A33633208	SPHERICAL STOP  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND DELAMINATION ON 2 SPHERICAL BEARINGS, OUT OF LIMITS.  REPLACED BY 2 NEW ONES.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005110800062	20051108	00062	SW  	2005	11	8	CA051003015      	1	20050922	G	6230	269A21725	TUBE            			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 1) TUBE ASSEMBLY IS CRACKED ON THE MAST SIDE. 2) REPLACED TUBE ASSEMBLY, P/N 269A2172-5.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2005110800066	20051108	00066	GL  	2005	11	8	CA051003017      	1	20051003	G	7810	22022	NUT             	CIRRUS      	10353002    	CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	EXHAUST HEADER	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) SOUND OF BACK FIRE WAS HEARD ON LANDING APPROACH.  INSPECTION FOUND NR 2 CYLINDER EXHAUST HEADER PIPE HAD DROPS DO	WN .1875 DUE TO MISSING EXHAUST NUTS.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
2005110800067	20051108	00067	EA  	2005	11	8	CA051003018      	1	20051003	G	5280		DOOR            	BOMBDR      		CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					LT MLG	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA						10027					(CAN) DURING INSPECTION OF THE AC DURING TRANSIT STOP THE LT MLG DOOR HAS BEEN FOUND MISSING. REMAINS OF THE BOTH DOOR H	INGE FITTINGS AND THE CONNECTING LINK ARE STILL PRESENT ON THE AC.  PILOT REPORTED THAT THEY HAD STRONG TURBULENCE IN FL	IGHT.  THE SB HAS BEEN PERFORMED ON THE AIRCRAFT ON 03-DEC-2003. BOTH LT AND RT DOORS HAVE BEEN INSPECTED IAW TC AD CF-2	003-23R1 ON 26-SEP-2005 WITH NO FAULT FOUND. MLG DOOR P/N CC670-10520-951A NEW DOOR WILL BE INSTALLED.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005110800068	20051108	00068	GL  	2005	11	8	CA051004002      	2	20050927	G	7250		BLADE           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					TURBINE SECTION	FRACTURED       	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			X	T		ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   		CR	CRUISE         	1			CA											(CAN) DURING IN-CRUISE POWER CHECK OF NR 1 ENGINE, NO 2 ENGINE (CHIP LIGHT) CAME ON, SHORTLY FOLLOWED BY (ENGINE OUT) HO	RN.  THE ENGINE WAS BROUGHT BACK TO FLIGHT IDLE AND EMERGENCY LANDING WAS ACCOMPLISHED.  ENGINE WAS SHUTDOWN.  UPON PREL	IMINARY INSPECTION IT WAS FOUND THAT N1 SYSTEM ROTATED NORMALLY.  N2 SYSTEM WAS SEIZED AND PIECES OF 3RD STAGE TURBINE W	HEEL SHROUD WERE FOUND IN THE EXHAUST COLLECTOR.  DAMAGE TO THE 4TH STAGE TURBINE WHEEL AND EXHAUST COLLECTOR WAS ALSO E	VIDENT.  ENGINE WAS REPLACED AND A/C RETURNED TO SERVICE.		1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2005110800069	20051108	00069	EA  	2005	11	8	CA051004003      	2	20051001	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540B1A5   	41532	EA  					FUEL SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ENGINE DRIVEN FUEL PUMP REPLACED BECAUSE OF OIL LEAK.  SB548A HAD BEEN COMPLIED WITH.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2005110800070	20051108	00070	SW  	2005	11	8	CA051004004      	1	20050906	G	2432	SM20ACD200A21	CONTACTOR       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					BATTERY	BURNED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											(CAN) DURING CRUISE PORTION OF A SHORT (15 MIN) CREW TRANSFER FLIGHT, THE PILOT AND 2 PASSENGERS ABOARD SMELLED/SAW FUME	S/SMOKE IN COCKPIT. ELECTRICAL SYSTEMS WERE SHUTDOWN AND AN UNEVENTFUL LANDING WAS CARRIED OUT NEAR CAMP SITE. UPON INVE	STIGATI ON, IT WAS DISCOVERED THAT THE FORWARD BODY RETENTION SCREW AND INSERT HAD BECOME DISBONDED AND WORKED UP INTO C	ONTACTS SHORTING THE POSITIVE TERMINAL TO GROUND, VAPOURIZING THE INSERT AND PORTION OF SCREW AND BURNING THE SURROUNDIN	G AREA. BETTER INTERNAL BONDING AND/OR COVERING OF THE INSERT COULD HAVE PREVENTED SAID MALFUNCTION.		1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005110800071	20051108	00071	CE  	2005	11	8	CA051004005      	1	20050923	G	7120	05510171	MOUNT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 200 HOUR INSPECTION,  DISCOVERED THIS TUBE WAS BROKEN. A REPLACEMENT MOUNT WAS INSTALLED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005110800072	20051108	00072	CE  	2005	11	8	CA051004006      	1	20050926	G	2612	30215B	FIRE DETECTOR   			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ENGINE BAY	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AFTER TAKE OFF AN (ENGINE FIRE) INDICATION FOR THE RT ENGINE ILLUMINATED. PILOT SHUT DOWN THE ENGINE AND LANDED ON	 ONE ENGINE. AFTER INSPECTION OF THE SYSTEM, NO FAULT FOUND, SYSTEM NORMAL. AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005110800073	20051108	00073	GL  	2005	11	8	CA051004007      	2	20050908	G	7250	23053299	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TURBINE WHEEL	DAMAGED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AIRCRAFT LIFTED OFF STAGING AREA WITH SLING LOAD. LOUD NOISE HEARD 2 MINUTES INTO FLIGHT. NO CAUTION LIGHTS OR OTH	ER INDICATION OF PROBLEM OTHER THAN LOUD AND HIGH-PITCHED NOISE. AIRCRAFT TURNED BACK AND MADE A NORMAL LANDING AND SHUT	-DOWN. TURBINE WAS REMOVED AND SENT FOR INSPECTION.  ONE BLADE FOUND MISSING FROM FIRST STAGE TURBINE WHEEL. SUSPECT CAU	SED BY TIP RUB.  INFORMATION AND PHOTOS FORWARDED TO MFG.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2005110800074	20051108	00074	WP  	2005	11	8	CA051004008      	1	20051004	G	2435	BC3151004	DRIVE GEAR      		BC3151004   	ROBSIN	R44   	R44RAVENII  	7640122	WP  										STARTER	CHIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1104241120					(CAN) AIRCRAFT HAD BEEN HARD TO START.  UPON INVESTIGATION THE STARTER BENDIX DRIVE GEAR FOUND TO HAVE A CHIPPED TOOTH. 	 NO PROBLEMS NOTED WITH THE INSTALLATION OF THE STARTER.THERE IS NO SHIMMING PROCEDURE, OR ANY OTHER KIND OF ADJUSTMENT 	WITH THIS INSTALLATION.				1	G	7	1 	3O				H11NM   					 
2005110800004	20051108	00004	EA  	2005	11	8	CA051004009      	1	20050930	G	5720	2153003126	ANGLE           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT ANGLES FOUND CRACKED WHEN DOING SB 215-454R3 PART B.						2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2005110800005	20051108	00005	EA  	2005	11	8	CA051005001      	1	20051003	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) LT WINDOW CRACKED AT FL410.  NO PRESSURE PROBLEM. DIVERTED FLIGH. LT SIDE WINDOW REPLACED ACCORDING AMM. THERE IS 	NO POST/PRE SB FOR WINDOWS.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005110800006	20051108	00006	CE  	2005	11	8	CA051005002      	1	20051002	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENROUTE, WHEN THE AC EXPERIENCED A CRACKED WINDSHIELD AND THE CREW REQUESTED IMMEDIATE DESCENT TO COMPLY WITH INST	RUCTIONS IN THE PILOTS HANDBOOK P/N101-590010-5, PAGE 3-16. SITUATION DID NOT REQUIRE THE DECLARATION OF AN EMERGENCY.  	UPON ARRIVAL OF AIRCRAFT, MAINTENANCE PERSONNEL INSPECTED THE WINDOW AND FOUND THE INSIDE PANE OF THE LT WINDSHIELD TO B	E BROKEN. THE WINDOW WAS FOUND TO BE INSTALLED CORRECTLY USING THE CORRECT PARTS. ALSO NOTED WAS THAT THE WINDSHIELD HEA	T WAS WORKING CORRECTLY AT THE TIME OF THIS INCIDENT. THE WINDSHIELD WAS TH EN REPLACED IAW THE MFG MM. THE PN REMOVED W	AS 101-384025-21.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2005110800007	20051108	00007	EU  	2005	11	8	CA051005003      	1	20051003	G	2421	200322	GENERATOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					NR 2 A/C SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 30 MINUTES ENROUTE THE AIRCRAFT HAD NR 2 AC WILD FAULT INDICATION. THE AIRCRAFT RETURNED WHERE MAINT	ENANCE REPLACED THE UNIT AND RETURNED THE AIRCRAFT TO SERVICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005110800008	20051108	00008	SW  	2005	11	8	CA051005004      	1	20051004	G	5302	206031403005	FITTING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14753			AOKP00862					(CAN) CRACKED FITTING ON TAILBOOM PN 206-033-004-045 AFMA FITTING P/N 206-031-403-005						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005110800009	20051108	00009	EU  	2005	11	8	CA051005005      	1	20051003	G	2421	200322	GENERATOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2 A/C	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 30 MINUTES AFTER DEPARTING THE AIRCRAFT HAD A NR 2 AC WILD FAULT INDICATION. THE CREW RETURNED THE A	IRCRAFT, WHERE MAINTENANCE REPLACED THE NR 2 AC GENERATOR AND RETURNED THE AIRCRAFT TO SERVICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2005110800010	20051108	00010	EA  	2005	11	8	CA051005006      	1	20051005	G	3230	200811620	PIN             			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG UPLOCK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A WALK AROUND THE NLG UPLOCK ROLLER PIN WAS FOUND BROKEN AT THE COTTER PIN HOLE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110800011	20051108	00011	NE  	2005	11	8	CA051005008      	2	20050901	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								PS0003			(CAN) DURING FLIGHT, SMOKE CONTAMINATED CABIN AIR AND MAIN OIL PRESSURE DECREASED TO UNACCEPTABLE LEVELS.  THE ENGINE WA	S SHUTDOWN IN FLIGHT AND A SINGLE ENGINE LANDING CARRIED OUT.  WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE O	F ROOT CAUSE ONCE ESTABLISHED. (SEE ALSO: US #2005090900013)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005120200073	20051202	00073	EA  	2005	12	2	CA051005009      	2	20050928	G	8500	LT10540J2B	ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RIGHT	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		CL	CLIMB          	1			CA			2518 								(CAN) DURING CLIMB OUT, RT ENG HAD UNCONTROLLABLE PROP FLUCTUATIONS. ENG WAS FEATHERED, AC LANDED WITHOUT INCIDENT. RUN-	UP ENG FOR TROUBLESHOOTING. NOTICED LOW OIL PRESS ON RT ENG. PULLED OIL FILTER, FOUND IT WAS FULL OF METAL CONTAMINATION	.  CREW REPLACED RT ENG, COMPLETED ENG CHANGE.  AC HAS NOW HAS BEEN RETURNED TO SERVICE. ENG WAS SENT OUT FOR EXAM FROM 	OUR ENG SHOP. WHEN ENG TEARDOWN COMES BACK AND REASON FOR FAILURE IS FOUND, WAS ON ON-CONDITION PROGRAM. IT HAD COMPLETE	D AN EVENT INSP 200 HR VALVE INSP,  ON-CONDITION INSP AND ALL WAS FOUND SATISFACTORY. OIL CONSUMPTION WAS GOOD AND WELL 	WITHIN LIMITS. THE ENGINE WAS RUNNING PERFECT AND HAD NO REPORTED PROBLEMS, SO THE SUDDEN FAILURE WAS UNEXPECTED.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005110800026	20051108	00026	NE  	2005	11	8	CA051005010      	2	20050903	G	7200		ENGINE          			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA								120942			(CAN) IN DESCENT THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND A SINGLE	 ENGINE LANDING ACCOMPLISHED AT POINT OF DESTINATION.  THE ENGINE FUEL CONTROL WAS SUBSEQUENTY REPLACED.  MFG WILL MONIT	OR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005110800027	20051108	00027	EA  	2005	11	8	CA051005011      	2	20050829	G	7200		ENGINE          			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  						FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								PE0182			(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED INCREASE IN TORQUE AND TEMPERATURE AND WAS SHUTDOWN IN FLIGHT.	  A SUBSEQUENT RESTART ATTEMPT WAS UNSUCCESSFUL AND A SINGLE ENGINE LANDING WAS ACCOMPLISHED AT POINT OF DESTINATION.  W	ILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	2 	3T	4	T		3A20    	E4EA				 
2005110800028	20051108	00028	EA  	2005	11	8	CA051005012      	2	20051004	G	8530	LW13447	CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA								L18561			(CAN) LT ENGINE SPRUNG HUGE OIL LEAK, WAS SHUTDOWN IN FLIGHT. ENGINE FEATHERED. A/C WAS EN-ROUTE. A/C MAINTAINED ALTITUD	E, CONTINUED AND LANDED SAFELY. LT ENGINE NR 6 CYLINDER WAS PULLED AND FOUND HAVE ALMOST CRACKED IN HALF AROUND BASE OF 	CYLINDER. CYLINDER WAS REPLACED WITH NEW CYLINDER.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005110800030	20051108	00030	NE  	2005	11	8	CA051006002      	2	20050907	G	7230		COMPRESSOR      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  					ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA								121290			(CAN) DURING CLIMB, SMOKE BECAME EVIDENT IN THE CABIN AIR ACCOMPANIED BY AN DECREASE IN ENGINE OIL PRESSURE AND AN INCRE	ASE IN TEMPERATURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSP	ECTION REVEALED SEIZURE OF THE PROP SHAFT AND OIL LEAKING FROM THE COMPRESSOR SECTION.  MFG WILL MONITOR INVESTIGATION O	F THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABISHED.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005110800031	20051108	00031	NE  	2005	11	8	CA051006003      	2	20050905	G	7200		ENGINE          			AYRES 	S2    	S2RT660     	0970112	SO  	PWA   	PT6   	PT6A65AG    	52043	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA								PN0061			(CAN) THE ENGINE WAS REPORTED TO HAVE FLAMED OUT ON FINAL APPROACH RESULTING IN THE AIRCRAFT LANDING SHORT OF THE RUNWAY	.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	L	7	1 	  	4	T		        	E4EA				 
2005110800032	20051108	00032	NE  	2005	11	8	CA051006004      	2	20050907	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								124484			(CAN) DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED DECREASE IN TORQUE ACCOMPANIED BY AN INCREASE IN TEMPERATURE. 	 THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL MONITOR INVESTIGA	TION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2005110800033	20051108	00033	EU  	2005	11	8	CA051006005      	1	20050901	G	7714		PACKING         			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					N1 PROBE	FAILED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI, CABIN AIR BECAME CONTAMINATED WITH SMOKE.  SUBSEQUENT INSPECTION REVEALED A HARDENED AND BROKEN N1 PROBE 	O-RING PACKING.					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2005110800034	20051108	00034	EA  	2005	11	8	CA051006006      	2	20050908	G	7230		COMPRESSOR      			DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  					ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								86127			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK TO IDLE IN CRUISE, AND WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT I	NSPECTION REVEALED DAMAGE TO THE 1ST STAGE COMPRESSOR BLADES.  WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF 	ROOT CAUSE, ONCE ESTABLISHED.				2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
2005120200079	20051202	00079	NE  	2005	12	2	CA051006007      	2	20051003	G	7250	311899101	BLADES          								PWA   	PT6   	PT6A67D     	 	NE  					TURBINE SECTION	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA								PCEPS0165			(CAN) ENG REQUIRED REPLACEMENT OF CT DISK DUE TO EXCESS CT TIP CLEARANCES AND BURNED CT BLADES TIPS.  NEW CT DISK ASSY, 	WITH QTY 8 NEW & QTY 35 OH CT BLADES WERE INSTALLED. 8 NEW BLADES NOTED TO HAVE A BLADE STEP AT  INTERFACE BETWEEN CT BL	ADE PLATFORM & FIR TREE ROOT.  CT DISK ASSY INSTALLED IAW MM, USUAL FIELD MAINT PERFORMED & ENG REASSEMBLED. GROUND RUN 	PERFORMANCE INDICATED ENG PERFORMANCE NOT AS EXPECTED. UPON SPLITTING ENG, RUB CONTACT BETWEEN CT DISK & CT AIR BAFFLE D	ISCOVERED. CT DISK REMOVED FOR INSP AND NOTED A SEVERE RUB OCCURRED ON L/E OF CT DISK PLATFORM FACE TO CT STATOR AIR SEA	L.  RUB ORIGINATED AT POSITION OF QTY 4 OF 8 NEW CT BLADES, INSTALLED IN DISK ASSY AT BUILD.						4	T			E26NE				 
2005110800075	20051108	00075	NE  	2005	11	8	CA051006008      	2	20050913	G	7200		ENGINE          			BRAERO	DH125 	HS125700A   	4230170	EU  	PWA   	305   	PW305B      	52128	NE  						LEAKING         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CABIN AIR BECAME CONTAMINATED WITH SMOKE.  ECS WAS SELECTED OFF AND AN EMERGENCY DECLARED.  SUBS	EQUENT INSPECTION FOUND EXTERNAL ENGINE OIL LEAKAGE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE, ONCE D	ETERMINED.				2	L	7	2 	4F	4	F		A3EU    	E35NE				 
2005110800077	20051108	00077	EA  	2005	11	8	CA051006009      	2	20050914	G	7320		FADAC           	PWC         	PW150A      	BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA						FA0039					(CAN) AFTER TAKE-OFF THE ENGINE (FADEC FAIL) WARNING ANNUNCIATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DI	VERTED TO POINT OF DEPARTURE.  INSPECTION REVEALED FAULT CODES ON BOTH FADEC CHANNELS.  THE FADEC, FUEL CONTROL UNIT AND	 BLEED VALVES WERE SUBSEQUENTLY REMOVED FOR INVESTIGATION.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE, 	ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005110800078	20051108	00078	NE  	2005	11	8	CA051006010      	2	20050912	G	7311		COOLER          			BAG   	ATP   	ATP         	       	EU  	PWA   	PW120 	PW126A      	 	NE  	HAMSTD	5500	65500F1     	NE  	FUEL/OIL	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVE	ALED THE PRESENCE OF FUEL IN THE ENGINE OIL TANK.  THE ENGINE FCOC WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A27NM   	E2ONE	6	C	P13NE	 
2005110800079	20051108	00079	SW  	2005	11	8	CA051006011      	1	20051004	G	5302	205032813041	PANEL           	BELL        	212030100067	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DEBONDED BEYOND LIMITS ON LT SIDE BETWEEN STATION 241.22 AND 324.51.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005110800080	20051108	00080	EU  	2005	11	8	CA051006012      	1	20050919	G	7712	30005000044	TSCU            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  					ENGINE	UNSERVICEABLE   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) FOLLOWING TAKE-OFF, THE ENGINE EXPERIENCED AN UNCOMMANDED TORQUE REDUCTION ACCOMPANIED BY A REDUCTION IN PROPELLER	 SPEED.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVE	ALED AN UNSERVICEABLE TORQUE SIGNAL CONTROL UNIT (TSCU).				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2005110800081	20051108	00081		2005	11	8	CA051006013      	4	20050923	G	8300		GEARBOX         			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  					ACCESSORY	SEIZED          	W				E				ENGINE SHUTDOWN         				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY FLAMES FROM THE EXHAUST AND VIBRATION.  THE ENGINE W	AS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED THE ACCESSORY GEARBOX TO BE SEIZED.  MFG WILL INVESTIGATE THE INC	IDENT AND WILL ADVISE OF ROOT CAUSE, ONCE ESTABLISHED.				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA				 
2005110800082	20051108	00082	NE  	2005	11	8	CA051006014      	2	20050922	G	7532		BLEED VALVE     			PILATS	PC7   	PC7         	7090401	EU  	PWA   	PT6   	PT6A25      	52043	NE  					COMPRESSOR	OUT OF LIMITS   	W				C				ABORTED TAKEOFF         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ON TAKE-OFF ROLL, THE ENGINE SURGED, ACCOMPANIED BY FLAMES EMITTED FROM THE EXHAUST.  SUBSEQUENT INVESTIGATION DET	ERMINED THE COMPRESSOR BLEED VALVE CLOSING POINT TO BE OUT OF LIMITS.  THE BOV WAS REPLACED.					1	L	7	1 	3T	3	T	RT	A50EU   	E4EA				 
2005110800083	20051108	00083	NE  	2005	11	8	CA051006015      	2	20050921	G	7321	806304101	FCU             	WOODWARD    	806304101   	PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						12069535					(CAN) IN FLIGHT, THE CREW REPORTED A LOUD NOISE ACCOMPANIED BY AN ENGINE SURGE.  ENGINE POWER ROLLED BACK AND RECOVERED 	WITHOUT PILOT INPUT.  THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REMOVED F	OR INVESTIGATION.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110800084	20051108	00084	SO  	2005	11	8	CA051006016      	1	20050624	G	5751	62102000	SUPPORT         	PIPER       	66600       	PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320*       	41508	EA  	SNSNCH	74DM	M74DM       	EA  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON BELLCRANK SUPPORT ASSEMBLY WAS CRACKED AT THE FORWARD ATTACH BOLT HOLE. THE CRACKS WERE APP 1 INCH LONG. P	ART HAS NOW BEEN REPLACED NEW.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2005120200086	20051202	00086	NE  	2005	12	2	CA051007001      	2	20050919	G	7200		ENGINE          			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					NR 1	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			12458					13205			AC DIVERTED AND LANDED. IN CRUISE, AUTO THROTTLES BEGAN MOVING BACK FORTH AS NR 1 ENG APPARENTLY WAS LOSING PWR,  NR 2 E	NG WAS INCREASING PWR TO COMPENSATE, A GROWLING NOISE IN NR 1 ENGINE, ENG SURGED 3 TO 5 TIMES, SMELL OF SMOKE WAS NOTICE	D IN CABIN, OIL PRESSURE DROPPED TO 2 OR 3 PSI AND AN ALERT (RED BOX AROUND OIL PRESSURE) WAS OBSERVED. PILOT REDUCED NR	 1 ENG TO IDLE AND SHUTOFF FUEL TO ENG, N1 AND N2 SPUN DOWN NORMALLY AND AC LANDED. MTC REPORTED LPT ROTATES NORMALLY, N	O OIL LEAKS IN TAILPIPE OR ON ENG WERE NOTICED, OIL QUANTITY LOW, BUT STILL IN TANK SIGHT GLASS, MCD OBSERVED WITH FUZZ 	ON IT. MECHANICS ARRIVED TO CHECK OIL FILTER, OIL LEAKS, POP OUT INDICATOR, T/C 449 CHECKS OF EEC FAULTS, BOROSCOPE, HPC	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2005110900147	20051109	00147		2005	11	9	CA051007002      	1	20050930	G	6100		MANUAL          																	MAINTENANCE	INACCURATE      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AFTER REVIEWING PRODUCTION FLT TEST PROCEDURE, IT WAS FOUND THAT NO MENTION OF PROP BOLTS TQ CHECK AFTER FIRST FLT AS RE	COMMENDED BY MT PROPELLER DOCUMENT.  AFTER REVIEWING MM , IT WAS FOUND THAT PROP BOLTS TQ CHECK AFTER FIRST 25HRS OF OP 	AS RECOMMENDED BY MT PROPELLER WAS MISSING IN SPECIAL INSPECT SECTION.  AS PRECAUTIONARY MEASURE OWNERS OF MDL SA160 S/N	 S-0001, S-0002, S-0003,S-0004S-0005, S-0006 WERE CONTACTED BY PHONE AND ADVISED TO CARRY OUT PROP BOLTS TQ CHECK AS PER	 MT PROP, BEFORE NEXT FLT IF A/C HAD ACCUMULATED LESS THAN 100 HRS ON TACH IND SINCE DELIVERY, FOR A/C THAT HAD ACCUMULA	TED MORE THAN 100 HRS, RE-TQ SHOULD HAVE BEEN CARRIED OUT AS PER ANNUAL/100 HRS INSPECTION AS INCORPORATED IN MM INSPECT														 
2005110800016	20051108	00016	NM  	2005	11	8	CA051007003      	1	20051004	G	2750	65C308461	BELLCRANK       			BOEING	737   	737500*     	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE DAILY CHECK,IT WAS NOTED THAT THE LT OB T/E FLAP HAD EXCESSIVE PLAY WHEN HAND FORCE WAS APPLIED T	O THE TRAILING EDGE FLAP.  UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE CLEVIS BOLT AND THE BELLCRANK WERE WORN	 AND CORRODED.  BELLCRANK AND CLEVIS REPLACED.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005110800017	20051108	00017	EA  	2005	11	8	CA051007004      	2	20050928	G	7322	1060301	CARBURETOR      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN)  AIRCRAFT HAVE LOW POWER IN FLIGHT.   REPLACED CARBURATOR.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2005110800018	20051108	00018	CE  	2005	11	8	CA051007005      	1	20051006	G	2150	651532629	SEGMENT         	CESSNA      	651532636   	CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					COOLING SYSTEM	COLLAPSED       	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT THE PILOTS HEARD A POP AND THE CABIN ALTITUDE BEGAN TO CLIMB BECAUSE OF LOSS OF PRESSURIZATION.  T	HEY COMMENCED AN EMERGENCY DESCENT AND LANDED SAFELY.  ON INVESTIGATION, FOUND THAT THE INLET END OF THE WYE ASSEMBLY OF	 THE FLOOD COOLING SYSTEM HAD DETERIORATED OVER TIME AND HAD COLLAPSED ENOUGH TO ALL OW THE END TO BE BLOWN OUT OF THE C	LAMP.  THE WYE ASSEMBLY WAS REPAIRED AND THE SYSTEM REASSEMBLED.  THE AIRCRAFT WAS TEST FLOWN AND FUNCTION PERFECTLY.			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2005110800019	20051108	00019		2005	11	8	CA051007006      	4	20051006	G	2330	50401100003	DISPLAY         	BOEING      		BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 13B, VDU	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA						3393042					(CAN) A/C WAS ON THE GROUND WHEN A BURNING ELECTRICAL SMELL WAS NOTICED AT ROW 13.  SEAT 13B WAS DEACTIVATED. MAINTENANC	E REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMP	LETE TEAR DOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005110800020	20051108	00020		2005	11	8	CA051007007      	4	20051006	G	6122		SHAFT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP GOVERNOR	SHEARED         	W				E	B			ENGINE SHUTDOWN         	EMER. DESCENT           			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LT ENGINE LOSS OF FUEL PRESSURE IN FLIGHT. ENGINE SHUTDOWN AND FEATHER COMPLETED. IN CRUISE, ENGINE HAD PARTIAL PO	WER LOSS. ENGINE WAS FEATHERED AND A/C LANDED SAFELY. TRIED GROUND START, ENGINE WOULD NOT COME OUT OF FEATHER. ENGINEER	 FOUND FAILED PROP GOVERNOR. ENGINE DID WHAT IT SHOULD GOING TO FEATHER. SERVICEABLE PROP GOVERNOR INSTALLED. ENGINE IS 	NOW BACK TO SERVICE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005110800022	20051108	00022	GL  	2005	11	8	CA051007008      	3	20051006	G	6114		HUB             	MCAULY      		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	PROPELLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						762789					(CAN) DURING AN ROUTINE INSPECTION, THE PROPELLER WAS FOUND LEAKING. PART OF THE INSPECTION CALLS OUT TO ENSURE THERE IS	 NO RED DYE LEAKING FROM THE PROP HUB ASSEMBLY. THE PROP HAS BEEN REMOVED FROM THE AIRCRAFT AND SENT TO THE OVERHAUL FAC	ILITY.  THIS IS THE SECOND TIME THE PROPELLER HAS LEAKED.  HAVE ASKED FOR THE HUB ASSEMBLY TO BE NDT TO ENSURE THERE IS 	NO CRACKS.   INSTALLED A LOANED PROP AND THE AIRCRAFT RETURNED TO THE FLIGHT LINE.			1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
2005110800049	20051108	00049	CE  	2005	11	8	CA051009001      	1	20051002	G	5610	1013840252	WINDSHIELD      	PPG         	1013840252  	BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						92317H9918					(CAN) ON CLIMB OUT, THE CREW HEARD A LOUD BANG AND  THE PILOTS WINDSHIELD INNER PANE HAD BROKEN. THE CREW RETURNED WITHO	UT A PROBLEM.					2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2005110800050	20051108	00050	EA  	2005	11	8	CA051011001      	1	20051007	G	2497		RELAY           	HARTMAN     	D7GRZ       	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RELAY/CONTACTOR	MELTED          	W				D				RETURN TO BLOCK         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		TX	TAXI/GRND HDL  	1			CA											(CAN) THE FLIGHT CREW WAS ON THE GROUND WITH THE APU ON (NO PASSENGERS ON BOARD).  JUST AFTER TRANSFERING FROM APU TO EX	TERNAL POWER, SMOKE STARTED TO FILL THE COCKPIT.  POWER WAS REMOVED FROM THE AIRCRAFT.  THE MECHANICS DETERMINED THAT TH	E SOURCE OF THE SMOKE WAS THE AVIONICS BAY.  THE MECHANICS FOUND THAT RELAY (AC SERVICE CONTACTOR) HAD MELTED.  IT IS AL	SO REPORTED THAT SOME WIRES HAVE SUSTAINED HEAT DAMAGE. THERE WAS NO EVIDENCE OF A WATER LEAK IN THE AREA.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110800051	20051108	00051	EA  	2005	11	8	CA051011002      	1	20051005	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) RT COCKPIT SIDE WINDOW CRACKED ON APPROACH.  WINDOW REPLACED IAW AMM, AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005110800052	20051108	00052	EA  	2005	11	8	CA051011003      	1	20050808	G	3230		LANDING GEAR    	MESSIER     	16040       	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NOSE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) UPON SELECTING THE LDG DOWN, THE NLG DID NOT COME DOWN AND A (GEAR DISAGREE) MESSAGE FOLLOWED.  QRH FOLLOWED, NLG 	FINALLY EXTENDED.  AN UNEVENTFUL LANDING FOLLOWED.  NUMEROUS TROUBLESHOOTING STEPS WERE PERFORMED DURING THE TROUBLESHOO	TING PERIOD THAT FOLLOWED, HOWEVER THE FINAL FINDINGS HAVE STILL NOT BEEN DETERMINED. STILL INVESTIGATING/ANALYSING THE 	EVENT.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110900148	20051109	00148		2005	11	9	CA051011004      	4	20050929	G	3497		WIRE HARNESS    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NAVIGATION SYS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12893								THE MODE C FUNCTION OF ENCODING ALTIMETER FAILED, AS WELL THERE WERE INTERMITTENT FAULTS OF THE RADAR ALTIMETER AND OTHE	R AVIONICS SYSTEMS.  DURING TROUBLESHOOTING, THE MAIN WIRE BUNDLE ATTACHED TO THE FORWARD FIREWALL/PRESSURE BULKHEAD BEH	IND THE INSTRUMENT PANEL WAS FOUND TO BE CHAFED THROUGH BY THE COOLING/BLAST TUBE FOR THE KLN 90B GPS.  BOTH THE WIRE BU	NDLE AND BLAST TUBE WERE WELL SECURED BUT IN THE AREA OF THE DAMAGE THERE WAS CONTACT BETWEEN THE TWO.  THE DAMAGED WIRI	NG WAS REPAIRED AND SPIRAL WRAP WAS APPLIED TO THE WIRE BUNDLE TO PREVENT FURTHER DAMAGE BY THE COOLING HOSE.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2005110800053	20051108	00053	EU  	2005	11	8	CA051011005      	1	20050921	G	2434	230790069	GENERATOR       			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	DC SYSTEM	SEPARATED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) GENERATOR WENT OFF LINE IN CLIMB OUT. AIRCRAFT RETURNED TO BASE. GENERATOR REPLACED WITH OVERHAULED UNIT. SYSTEM T	ESTED SATISFACTORY.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2005110900149	20051109	00149	EA  	2005	11	9	CA051011006      	2	20051005	G	7314	02532310103	DRIVE ASSY      			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					EDP	SHEARED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PCE57185			IN CRUISE FLT AT 7000 FEET, NR 1 ENGINE LOST POWER.  FLT CREW SECURED NR 1 ENGINE IAW APPLICABLE FLT MANUAL PROCEDURES A	ND LANDED A/C AT NEAREST AIRPORT.  UPON INVESTIGATION, MX FOUND THAT CAUSE OF ENG FAILURE WAS DUE TO ENG DRIVEN FUEL PUM	P.  WHEN FUEL PUMP WAS REMOVED IT WAS FOUND THAT SPLINES HAD SHEARED OFF OF DRIVE AS A RESULT OF INTERNAL PUMP FAILURE. 	 THE ACCESSORY DRIVE SECTION, ON THE ENGINE, WAS INSPECTED AND FOUND TO BE DEFECT FREE.  THE ENGINE DRIVEN FUEL PUMP ALO	NG WITH THE FUEL CONTROL UNIT WERE BOTH REPLACED AND THE ENGINE WAS GROUND RUN WHERE ALL PARAMETERS WERE FOUND TO BE NOR	MAL.  THE AIRCRAFT WAS THEN RETURNED TO SERVICE.  THE FUEL PUMP HAS BEEN SENT OUT FOR TEAR DOWN AND A STRIP REPORT.	1	L	7	2 	4T	4	T		A21SO   	E4EA				 
2005110900150	20051109	00150	CE  	2005	11	9	CA051011007      	1	20051004	G	5753	052300710	SKIN            			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11258								SEVERAL CRACKS IN SKIN THROUGH RIVET HOLES IN TRAILING EDGE.  THIS SKIN IS IN THE FLAP BAY.  SUSPECT FAILURE IS DUE TO F	LEXING OF TRAILING EDGE, CAUSED BY TURBULENCE IN SLOW FLIGHT WITH FLAPS LOWERED.  AIRCRAFT IS USED SOLELY FOR FLIGHT TRA	INING.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005110900151	20051109	00151	CE  	2005	11	9	CA051011008      	1	20051007	G	2720		SUPPORT BRACKET 			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RUDDER	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			14079								PILOT REPORTED THAT WHEN BRAKES WERE APPLIED FROM CAPTS POSITION, THE CO-PILOTS INSTRUMENTS LIGHTS WOULD GO OUT.  MAINTE	NANCE WAS ABLE TO DUPLICATE THE SNAG.  INVESTIGATION REVEALED CAPTS RUDDER SUPPORT BRACKET CRACKED AND BROKEN AT TOP AND	 BOTTOM ATTACH CHANNELS.  THREE CHANNELS BEING REPLACED (P/N'S 5565609-6, 5565609-7, 5565609-14).  CO-PILOTS LIGHTS AFFE	CTED DUE TO THE POSITIONING OF A RHEOSTAT LOCATED IMMEDIATELY ABOVE RUDDER SUPPORT.  WHEN BRAKES WERE APPLIED, FLEXING I	N THE SUPPORT ALLOWED IT TO COME INTO CONTACT WITH THE RHEOSTAT.  A FLEET WIDE CAMPAIGN WAS CARRIED OUT WITH NO OTHER DE	FECTS OF THIS TYPE NOTED	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005110900152	20051109	00152	SO  	2005	11	9	CA051011009      	1	20050929	G	3250	AN37A	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG STEERING SYS	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT COMPLAINED OF NO NOSE WHEEL STEERING WITH RUDDER INPUT.  MX FOUND 2 OF 3 BOLTS SHEARED ON STEERING LINKAGE O	N TOP OF NLG TRUNNION.  MX DRY ASSEMBLED STEERING LINKAGE AND DISCOVERED BOLT GRIP LENGTH INSUFFICIENT.  FOUND THAT 12 L	ENGTH WAS CORRECT LENGTH FOR THE 7 BOLT INDICATED IN IPC.  BOLTS WERE FOUND SHEARED WHERE GRIP MEETS THE THREADS.  ALL T	HREE BOLTS REPLACED WITH NEW HARDWARE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005110900116	20051109	00116	CE  	2005	11	9	CA051011010      	1	20051006	G	7830	202001551	LONGERON        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					THRUST REVERSER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11389								DURING SCHEDULED INSPECTION, MAINTENANCE FOUND A CRACK ON THE LT THRUST REVERSER LT INNER UPPER LONGERON TAB.  THE CRACK	 STARTED IN FASTENER HOLE AND PROPAGATED TO THE EDGE OF THE TAB.  THE CRACK WAS REPAIRED BY FABRICATING AND INSTALLING R	EPAIR DOUBLER IAW NORDAM STANDARD REPAIR PROCEDURE.  MAJOR MOD/REPAIR REPORT FILED WITH T.C.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2005110900117	20051109	00117	EA  	2005	11	9	CA051011011      	2	20051007	G	7314	6617302	SHAFT           	PARKERHANFIN		BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 OIL PUMP	SHEARED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA						K0238					AIRCRAFT SUFFERED A NR 2 EDP FAILURE DURING APPROACH.  ON INVESTIGATION, THE QUILL DRIVE WAS FOUND SHEARED AND THE CASE 	DRAIN DPI HAD ACTIVATED, THE FILTER WAS FULL OF BRASS.  NR 2 EDP REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005110900154	20051109	00154	NM  	2005	11	9	CA051012001      	1	20051004	G	3244	314353	TIRE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											DURING TAXI FOR TAKEOFF, A LOUD NOISE CAME FROM THE LEFT SIDE.  THE AIRCRAFT STOPPED AND AFTER INSPECTION THE LEFT MAIN 	TIRE WAS FOUND DEFLATED.  MAINTENANCE INSPECTION FOUND THE LT MLG INNER TIRE FOUND DEFLATED AND DAMAGED.  ALSO FROM INNE	R SIDE A LARGE METAL PIECE OF WHEEL WAS FOUND MISSING.  AFTER DV, INSPECTION OF MLG NOTHING ABNORMAL OBSERVED. THE MLG W	HEELS ASSY'S REPLACED BY SERVICEABLE ONES.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005110900155	20051109	00155	SO  	2005	11	9	CA051012002      	1	20051006	G	2913	8000420	PUMP            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					HYD SYSTEM	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			20241								THE FLIGHT CREW REPORTED THAT THE LANDING GEAR WAS SLOW TO RETRACT/EXTEND.  UPON INSPECTION, A RETURN (SUCTION) LINE FOR	 THE LEFT HYDRAULIC PUMP WAS FOUND CHAFED AND PIERCED INSIDE THE LEFT WING LEADING EDGE.  THE HOLE IN THE LINE WAS CAUSE	D BY THE VOLTAGE REGULATOR WIRE (PF16A), WHICH WAS BARE AND ARCING AGAINST THE PIPE.				1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2005110900156	20051109	00156	SO  	2005	11	9	CA051012003      	1	20051008	G	2731		CABLE           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TAB	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											THE FLIGHT CREW REPORTED THAT THE ELEVATOR TRIM WAS JAMMED IN THE FORWARD POSITION.  UPON INSPECTION, A LOOSE RIVET TAIL	 WAS FOUND LODGED ON TOP OF THE LEFT ELEVATOR TRIM DRUM AT THE CABLE STOP BOLT.					1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2005110900157	20051109	00157	SO  	2005	11	9	CA051012004      	1	20051011	G	3230	42042002	ARM             			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE COMPLYING WITH PIPER SL1092, INSPECTION/REPLACEMENT OF MAIN LANDING GEAR RETRACTION ARMS, THE LEFT ARM WAS FOUND C	RACKED AT THE INSIDE RADIUS.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA	6	C	P15EA	 
2005110900158	20051109	00158	EA  	2005	11	9	CA051012005      	1	20051006	G	5730		SKIN            	DHAV        		DHAV  	DHC6  	DHC6300     	2802606	EA  										WING BOX	DEBONDED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			28305			250082					FOUND LT AND RT WING DISBONDING OF THE UPPER WING SKIN, INBOARD AND OUTBOARD OF NACELLES FROM YW 60 TP YW 150.  BOMBARDI	ER IS IN THE PROCESS OF ISSUING A SB TO COVER INSPECTION OF THE UPPER WING SKINS.  DARK AREAS ON THE SKETCHES INDICATE D	ISBONDING.  MODEL P/N C6W1001-25 L/H, S/N 250082, L/H P/N C6W1001-27 R/H, S/N 270083 R/H.				1	H	7	2 	3T			RT	A9EA    					 
2005110900159	20051109	00159	EA  	2005	11	9	CA051012006      	1	20051010	G	7603	1600980005	CONTROL CABLE   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					THROTTLE	SEVERED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22229								WHEN BOTH ENGINES WERE REMOVED FOR INSPECTION ACCESS DURING A HEAVY MAINTENANCE VISIT, THE LT ENGINE AUTO THROTTLE RETAR	D CABLE (ITEM 220 IN FIGURE 2 ON CANADAIR IPC CHAPTER 76-10-00) WAS FOUND SEVERED BETWEEN THE DRILLED JAM NUT (ITEM 125)	 AND NUT (ITEM 165) AFT OF THE BELLCRANK (ITEM 85).				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110900160	20051109	00160	SW  	2005	11	9	CA051012007      	1	20050927	G	5244	206033111023	HINGE           			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					BATTERY DOOR	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											ON APPROACH WITH A SLING LOAD THE BATTERY DOOR OPEN AT A SPEED OF 60 MPH AND THE DOOR HINGE BROKE.  THE DOOR STAYED ATTA	CH TO THE AIRCRAFT BY THE SPRING P/N 206-031-155-005.  NO OTHER DAMAGES HAVE BEEN FOUND ON THE AIRCRAFT.  AFTER INVESTIG	ATION, THE HINGE P/N 206-033-111-023 HAVE BEEN FOUND THAT IT WAS PARTIALLY BROKEN BEFORE THE INCIDENT.  ALSO, THE D2U5 F	ASTENER USED TO KEEP THE DOOR IN CLOSE POSITION WHERE A DASH TOO LONG WITH THE RESULT THAT YOU COULD CLOSE THEM TO FAR O	UT OF THE LOCK POSITION IN A WAY THAT IT NEEDED JUST A WEAK FORCE TO MOVE THEM IN THE OPEN POSITION.  AFTER HINGE REPLAC	EMENT THE USE OF PROPER D2U5 LENGTH ALONG WITH RED LINE FOR LOCK POSITION FOR PREVENTION.	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006061200435	20060612	00435		2006	6	12	CA051012008      	4	20051011	G	2562		BATTERY         	AMERIKING   		STBROS	SC7   	SC72        	8100510	EU  	ALIDSG	TPE331	TPE331201A  	0517	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ELT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						455455					ELT WAS LEAKING ACID FROM THE "D" CELL BATTERIES INSTALLED IN THE UNIT.  THIS WAS FOUND DURING ROUTINE INSPECTION.  ACID	 WAS NEUTRALIZED ON AIRFRAME, AND UNIT.  AIRFRAME WAS REPRIMED.  ELT WAS INSPECTED/CLEANED/NEUTRALIZED.  NEW BATTERIES I	NSTALLED, AND FUNCTION TESTED NORMAL.				1	H	7	2 	3T	3	T		A15EU   	AEXJ STC	6	C	P15EA	 
2005110900163	20051109	00163	EU  	2005	11	9	CA051012009      	1	20051002	G	5220		SKIN            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					EMERGENCY DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING SERVICE CHECK, 13 INCH CRACK DISCOVERED ON EXTERNAL SKIN OF FWD SERVICE/EMERGENCY DOOR.  NO REPLACEMENT DOOR WAS 	IN STOCK.  REPAIRS WERE COMPLETED AS PER STRUCTURAL REPAIR MANUAL.  THIS AREA IS COVERED BY STRUCTURAL INSPECT PROGRAM W	HICH IS COMPLETED EVERY 2000 CYCLES AND WAS DUE WITHIN 70 CYCLES.  FOKKER SERVICES HAVE BEEN CONTACTED FOR THEIR RECOMME	NDATION REGARDING INSPECTION LVL AND FREQ.  ALL INITIAL FINDINGS ON SIP-1 ITEM 52-40-01 ARE FOUND WELL ABOVE INITIAL INS	PECT AT 18700 CYCLES.  IN MAJORITY OF FINDINGS, CRACK SIZE IS IN BETWEEN 8 AND 11 INCH.  CRACK GROWTH CALCULATIONS (50 M	M - 250 MM) DO SHOW A RAPID GROWTH.  HOWEVER, TAKING INTO ACCOUNT A SCATTER FACTOR OF 3, 3200 CYCLE INTERVAL SHOULD COVE	2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2005110900164	20051109	00164	EU  	2005	11	9	CA051012011      	1	20051006	G	2910	MS2771923	SWITCH          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ON COLLECTIVE	INTERMITTENT    	W				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											PILOT WAS CARRYING OUT THE HYDRAULIC TEST OF THE ACCUMULATORS AND THE HORN WOULD NOT ACTIVATE.  THE A/C WAS SHUT DOWN AN	D AN ENGINEER STARTED TO TROUBLESHOOT.  IT WAS DISCOVERED THAT THE HYDRAULIC CUT-OFF SWITCH WAS OPERATING INTERMITTENTLY	.  DUE TO HYDRAULIC PROBLEMS IN THE AS350 WORLD A/C GROUNDED UNTIL SERVICEABLE PART ARRIVED.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005110900165	20051109	00165	EA  	2005	11	9	CA051013001      	1	20051013	G	5312		BULKHEAD        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					BS 621	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FOUND NUMEROUS CRACKS AT PRESSURE BULKHEAD MARKED BY BLACK MARKING REF 53-61-153 PAGE 9.  PRESSURE BULKHEAD CRACKS AT ST	N 621 REPAIRED IAW REO 601R53-61-1230 AND PROD PERM CRJ-53-21664.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110900166	20051109	00166	EA  	2005	11	9	CA051013002      	1	20051013	G	5312		BULKHEAD        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					BS 621	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											REAR PRESS BULKHEAD CRACKED AT LBL 27.5, WL97.5, FS 621.11.  REPAIRED PER: REO 601R-53-61-1285.  INTEL FITTING, REPAIRED	 PER REO 601R-53-61-1230 UPPER OF TRACK: AS PER REO 601R-53-61-1458.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110900167	20051109	00167	EA  	2005	11	9	CA051013003      	1	20051012	G	5410	NAS6204L11	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT PYLON	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22229								WHILE CARRYING OUT CANADAIR SB601R-53-061 PART C, BOLT P/N NAS6204L11ON THE RT SIDE ENGINE PYLON WAS FOUND SEPARATED IN 	TWO PARTS.  FRACTURE OCCURRED UNDER THE HEAD OF BOLT.  BOTH THE HEAD AND SHANK OF THE BOLT LOCATED ARE IN OUR POSSESSION	.  WILL BE DOING A DETAILED INSPECTION OF THE AREA USING NDT METHOD, SB 601R-54 -005 WHICH WAS NOT PREVIOUSLY DONE WILL 	BE INCORPORATED  IN CONJUNCTION WITH SB601R-53-061.  THE ENGINE PYLON BOLTS WILL BE REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005120200094	20051202	00094	NE  	2005	12	2	CA051013004      	1	20050923	G	6320	MS173204	CLAMP           	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					NR 2 GENERATOR	MISINSTALLED    	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA						A6104					(CAN) DURING GROUND RUN PHASE OF MAIN GB REPLACEMENT,  NR 2 GEN VESPAL DRIVE SPLINE ADAPT STRIPPED OUT CAUSING GEN TO FA	LL OFF LINE. GEN WAS REMOVED FROM ACCY GB, DRIVE SPLINE ADAPTOR WAS REPLACED, GEN WAS REINSTALLED, FUNCTION TESTED. AC W	AS RETURNED TO SERVICE, APPROX 10 TO 15 MIN INTO AC'S FIRST LOGGING CYCLE, NR 2 GEN FELL OFF LINE.  MAINT DISCOVERED NR2	 GEN LAYING ON UPPER DECK ATTACHED ONLY BY ELEC WIRES. INSPECT REVEALED NO DAMAGE CAUSED BY GEN DETACHING FROM MNT, DROP	PING TO DECK. WITH NO MNTING EQUIP FAILURE, CLAMP THAT SECURES GEN MNTING FLANGE TO ITS MATING ADAPTOR FLANGE ON GB WAS 	INSTALLED WITHOUT ENSURING COMPLETE ENGAGEMENT WITH BOTH MATING FLANGES. GEN WAS REINSTALLED, AC RETURNED TO SERVICE.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2005110900168	20051109	00168	EA  	2005	11	9	CA051013005      	1	20051012	G	7830	3012525	BRACKET         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  					THRUST REVERSER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			33912	10027							UPON VISUAL INSPECTION, TOP PLATE OF AFT REVERSING TELEFLEX BRACKET WAS FOUND CRACKED 70 PERCENT THROUGH.  TOTAL FAILURE	 OF THIS BRACKET WOULD ALLOW THE REVERSING TELEFLEX TO MOVE FORE AND AFT CAUSING DIFFICULTIES IN ENGINE CONTROL DURING R	EVERSE OPERATIONS.  DEFECTIVE PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005110900169	20051109	00169	SW  	2005	11	9	CA051013006      	1	20051004	G	2150	20475546	COOLING TURBINE 			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	WING ROOT	LEAKING         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											CREW COMPLAINED OF A SLIGHT OIL SMELL IN CABIN IN ALL FLIGHT STAGES.  MAINTENANCE REPLACED LT COOLING TURBINE AND RELEAS	ED AIRCRAFT TO SERVICE.  DURING MAINTENANCE GROUND RUN PRIOR TO REPLACEMENT COOLING TURBINE FAILED AND FILLED CABIN WITH	 SMOKE AND A STRONG SMELL OF OIL.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2005110900170	20051109	00170	CE  	2005	11	9	CA051013007      	1	20051012	G	5312		BULKHEAD        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18819								DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON TWO OTHER AIRCRAFT, (SDR 20050829003 AND 20050928001) AFT PRESSURE B	ULKHEAD WAS FOUND CHAFFED BY THE CENTER INTERCOSTALS ADJACENT TO THE TAIL ACCESS DOOR.  NDT WAS COMPLETED AND A CRACK FO	UND.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005110900121	20051109	00121	WP  	2005	11	9	CA051013008      	2	20051012	G	7200		ENGINE          			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE33125D   	01514	WP  					RIGHT	POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								P39225			RT ENGINE WAS REMOVED FOR LOW TORQUE INDICATION AND SENT OUT FOR REPAIR AFTER TESTING PROVED AN INTERNAL PROBLEM.  THE E	NGINE WAS RE-INSTALLED FROM REPAIR WITH A NEW TORSION SHAFT SN 05P15649 AND TORQUE SENSOR P/N 3101726 AND NTS TEST FLIGH	T WAS CARRIED OUT AND FUNCTIONED NORMALLY.  THE AIRCRAFT ACCUMULATED LESS THAN 8 HOURS TIS AND SHOWED SIGNS OF TORQUE LO	SS. GROUND TESTS WERE CARRIED OUT AND SYSTEMS WERE FUNCTIONING NORMAL, AND NTS TEST FLIGHT WAS THEN CARRIED OUT AND FAIL	ED.  ENGINE HAS SINCE BEEN REMOVED AND WILL BE SENT BACK TO THE OVERHAUL SHOP FOR RE-EVALUATION.		2	H	7	2 	4T	3	T	RT	A16EU   	E2WE				 
2005110900188	20051109	00188	CE  	2005	11	9	CA051013009      	1	20051011	G	3233	ADI79990033	ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											ON DESCENT, CREW WAS UNABLE TO GET THE NOSE GEAR DOWN INDICATION.  EMERGENCY EXTENSION WAS COMPLETED AND A/C LANDED SAFE	LY.  FERRY PERMIT WAS ISSUED AND A/C RETURNED TO YYC MAINTENANCE BASE WITH GEAR DOWN.  RT MAIN GEAR ACTUATOR FOUND TO HA	VE THE SEAL FOR THE PISTON ROD FAIL, CAUSING THE LOSS OF HYDRAULIC FLUID.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005110900189	20051109	00189	EU  	2005	11	9	CA051014002      	2	20051012	G	7230		BLADES          			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					ENGINE	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			CA								9804			GII SERIAL 236 IN NR 1 POSITION HAS EXPERIENCED FOD DAMAGE.  THE DAMAGE HAS BEEN FOUND TO THE LPC5 BLADES AND HPC1 BLADE	S.  THE REST OF THE HP COMPRESSOR HAS YET TO BE INSPECTED.  THE DAMAGE HAS BEEN CAUSED BY THE RELEASE OF ONE LP OGV INNE	R BOLT WASHER AND NUT.				2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2005110900190	20051109	00190	CE  	2005	11	9	CA051014003      	1	20051013	G	3250	S14505H12063	WASHER          			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MLG SCISSORS	MISSING         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											AFTER LANDING, THE A/C SUDDENLY VEERED OFF THE RUNWAY.  THE RT MAIN LANDING GEAR SCISSORS CAME APART AT THE CENTER.  THE	 WHEEL THEN TURNED AND PULLED THE AIRCRAFT OFF THE RUNWAY.  ON EACH SIDE OF THE CENTER BOLT HOLDING THE SCISSORS TOGETHE	R TWO P/N S1450-5H12-063 WASHERS WERE MISSING.  AN WASHERS WERE USED IN THEIR PLACE.  THE PROPER WASHERS WERE INSTALLED 	AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2005110900191	20051109	00191	EU  	2005	11	9	CA051017001      	1	20051011	G	2434	1030032	SENSOR          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	HALL EFFECT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											THE NR 2 DC GENERATING SYSTEM WENT OFF LINE AFTER DEPARTING YFB.  THE AIRCAFT RETURNED TO POINT OF DEPARTURE WHERE MAINT	ENANCE DETERMINED THE NR 2 HALL EFFECT SENSOR HAD FAILED.  THE SENSOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2005110900192	20051109	00192	NM  	2005	11	9	CA051017002      	1	20051007	G	7931	1030032	PRESSURE SWITCH 		312242902   	BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 ENGINE OIL	DEFECTIVE       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											IN-FLIGHT SHUTDOWN OF THE NR 2 ENGINE DUE TO LOW OIL PRESSURE CAUTION LIGHT, OIL PRESSURE INDICATION WAS NORMAL.  PILOTS	 INITIATED CHECKLIST AND PERFORMED SHUTDOWN AND RETURNED TO BASE.  ENGINE IS A MODIFIED CIS ENGINE.  THE PROBLEM WAS FOU	ND TO BE A DEFECTIVE LOW OIL PRESSURE SWITCH.  THE OIL WAS A NORMAL COLOR AND PROPER QUANTITY, THE FILTERS WERE CLEAR.  	LOW OIL PRESSURE SWITCH REPLACED, SYSTEMS CHECKED, A/C RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005120200095	20051202	00095	EU  	2005	12	2	CA051017003      	1	20051009	G	2120	F50B721508A3	EXHAUST DUCT    			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					ECU	FAILED          	W				F				ACTIVATE FIRE EXT.      				M	J		OVER TEMP                 	WARNING INDICATION        		AP	APPROACH       	1			CA			10678								(CAN) CREW RECEIVED LT WARM BATT IND, FOLLOWED BY LT BATT HOT IND. ALSO, RT BATT IND WARM THEN HOT. SELECTED BOTH BATTER	IES OFF, HAD AN AFT EQUIP BAY FIRE IND.  RAN PHASE DRILL INCLUDING ACT OF FIRE EXTING.  AFT EQUIP FIRE WARNING WENT OUT 	FOLLOWING, REDUCING BATT TEMPS.  NORMAL LANDING FOLLOWED. NO VISUAL IND OF FIRE.  AFTER INSP, DETERMINED, INSULATION ARO	UND ECU EXHAUST DUCT HAD FAILED, RIPPED OPEN ALLOWING BLEED AIR INTO AFT COMPT CAUSING MAIN BATT TO HEAT UP, GIVE HOT BA	TT WARNING AS WELL AS FIRE WARN AS BLEED AIR WAS DIRECTED AT FIRE DETECT LOOP. EFFECTED FIRE BOTTLES, SQUIBS WERE REPLAC	ED, REPAIRED ECU DUCT, SLEEVE WERE INSTALLED. SYS WERE OPS AND LEAK CHECKED.  NO FAULTS WERE NOTED AND AC WAS RELEASED.	2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2005110900193	20051109	00193	EA  	2005	11	9	CA051017004      	1	20051017	G	2432		THERMAL BARRIER 			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					BATTERY	FAILED          	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA						109802					DURING FINAL TOP CHARGE CELL NR 19 WENT INTO THERMAL BARRIER BREAKDOWN.  HIGH TEMPERATURE LIMIT WAS REACHED AND THE CELL	 HOUSING MELTED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005110900201	20051109	00201	EA  	2005	11	9	CA051017005      	1	20051014	G	2731	AA112911002	SERVO           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											RIGHT ELEVATOR SERVO TAB FOUND CRACKED DURING ROUTINE INSPECTION.						1	H	7	1 	3R	4	T		A815    	E4EA				 
2005110900202	20051109	00202	EU  	2005	11	9	CA051017006      	1	20050918	G	2913	350A35013100	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYDRAULIC SYS	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22087								WHILE REPLACING THE PUMP DRIVE ASSEMBLY FOR THE 1200 HOUR INSPECTION, FOUND THE SPLINES ON THE DRIVE WORN OUT.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005110900203	20051109	00203	GL  	2005	11	9	CA051017007      	2	20050901	G	7323	252476914	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			11533								NR WAS REPORTED AS SURGING WITH EVERY COLLECTIVE MOVEMENT.  LINEAR ACTUATOR DISCONNECTED FROM GOVERNOR LEVER AND LEVER W	AS FOUND TO BE VERY DIFFICULT TO ROTATE.  WHEN FORCED TO ROTATE THE ARM WOULD RELEASE AND BIND INTERMITTENTLY.  GOVERNOR	 REPLACED AND A/C RETURNED TO SERVICE.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005110900204	20051109	00204	SW  	2005	11	9	CA051017008      	1	20050830	G	5342		FITTING         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STABILIZER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											RT HORIZONTAL STABILIZER MOUNT FITTING FOUND CRACKED.  THE STABILIZER SPAR WAS FOUND DAMAGED AS A RESULT OF THE FITTING 	DAMAGE AND WAS REPLACED ALONG WITH THE STABILIZER.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005110900205	20051109	00205	SW  	2005	11	9	CA051017009      	1	20050909	G	7312	10544E	FUEL HEATER     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 2 ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											NR 2 ENGINE FUEL HEATER FOUND TOO HOT TO TOUCH FOLLOWING SHUTDOWN.  HEATER REPLACED AND A/C RETURNED TO SERVICE.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005111000030	20051110	00030	GL  	2005	11	10	CA051017010      	2	20050929	G	7261	6845867	IDLER GEAR      	ALLSN       							ALLSN 	250C  	250C20B     	03013	GL  					SCAVENGE PUMP	FRACTURED       	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											AIRCRAFT NOTED AS SMOKING ON TAXI BY TOWER.  TAKEOFF WAS ABORTED AND INSUFFICIENT OIL PUMP SCAVENGE NOTED AS SOURCE OF T	URBINE SMOKING PROBLEM.  WHEN DISMANTLED FOR REPAIR AND INSPECTION, FOUND ONE SCAVENGE ELEMENT GEAR HAD A BROKEN TOOTH. 	 PART IS 3812.7 HOURS SINCE LAST NDT INSPECTION.  OEM NOTIFIED OF PROBLEM AND PROVIDED PICTURES OF NONCONFORMANCE.									3	U			E4CE				 
2005120200102	20051202	00102	NE  	2005	12	2	CA051017011      	2	20051017	G	7230	310784501	BEARING         								PWA   	PW120 	PW124B      	 	NE  					NR 2	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								124458			(CAN) SEE REPORT ATTACHED											4	T			E2ONE				 
2005121900062	20051219	00062	EU  	2005	12	19	CA051017012      	1	20051017	G	2435	150SG100920XL2	BRUSHES         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER GEN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						6505XL					UPON BRUSH INSPECTION IT WAS FOUND THAT ONE OF THE BRUSHES HAD A BROKEN RIVET.  THE RIVET HOLDS THE WIRE BRAIDING TO THE	 BRUSH.  WHEN THE BRUSH WAS PULLED OUT, THE RIVET FELL OUT ALONG WITH THE METAL TANG.  UP TO THIS POINT THE STARTER GENE	RATOR HAD BEEN WORKING NORMALLY.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005121900063	20051219	00063	EU  	2005	12	19	CA051017013      	1	20051016	G	6310	19E2268A	COUPLING        			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					ENG/ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AFTER LAST FLIGHT OF THE DAY, ENGINEERING REVIEWED THE HUMS DATA AND NOTICED A SPIKE IN THE SHAFT INFORMATION.  THE A/C 	ENGINE WAS REMOVED THE SHAFT REMOVED FROM THE ENGINE AND INSPECTED, AND A CRACK WAS DISCOVERED IN BETWEEN THE TWO FRANGI	BLE DISCS.  ANOTHER SHAFT WAS INSTALLED AND ALL NECESSARY GROUND RUNS AND VIBRATION CHECK WERE CARRIED OUT SATISFACTORY.	  A/C WAS RETURNED TO SERVICE.			2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2005111000031	20051110	00031	CE  	2005	11	10	CA051018001      	1	20051017	G	2710	MS21251B5S	TURNBUCKLE      			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					AILERON CONTROL	CHAFED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											DURING PHASE 1-5 INSPECTION ON AIRCRAFT, TECHNICIANS DISCOVERED THAT THE LT AND RT AILERON CABLES WERE FOULING.  THE RES	ULT WAS THAT THE LT TURNBUCKLE WAS CHAFED AND THE RT SIDE THE SAFETY CLIP WAS GONE AND THE TURNBUCKLE WAS ALSO CHAFED.					2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2005111000032	20051110	00032		2005	11	10	CA051018002      	4	20051016	G	2562	PS400010	G SWITCH        	POINTER     		ROBSIN	R44   	R44RAVENII  	7640122	WP  										ELT	WEAK            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA						409107					DURING CRUISE FLIGHT PAST AIRPORT, THE ELT WENT OFF IN FLIGHT.  NO UNUSUAL FLIGHT CONDITIONS AT THE TIME OF THE INCIDENT	.  FSS WAS CONTACTED.					1	G	7	1 	3O				H11NM   					 
2005111000033	20051110	00033	EA  	2005	11	10	CA051018003      	1	20051010	G	5311	C6FSM2528S12	FRAME           			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING SCHEDULED INSPECTION FOR SB 6/521 AND CF 95-12, A SINGLE CRACK WAS SUSPECTED IN THE WEB AREA OF THE AFT SECTION O	F THE RT SIDE FRAME.  AN EDDY CURRENT INSPECTION CONFIRMED THE CRACK AS WELL AS SMALLER CRACKS EMANATING FROM THREE ADJA	CENT RIVETS.  THE LARGER CRACK WAS ESTIMATED AT 3/8 INCH IN LENGTH AND ORIGINATED FROM A RIVET HOLE.  THERE IS NO RECORD	 OF THIS PARTICULAR SECTION OF THE SIDE FRAME HAVING BEEN CHANGED PREVOUSLY.  THE A/C REMAINS GROUNDED PENDING DELIVERY 	OF A SIDEFRAME FROM THE MANUFACTURER.		1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005111000034	20051110	00034	EU  	2005	11	10	CA051018005      	1	20051017	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											SERVO WAS REMOVED FROM AIRCRAFT TO REPAIR A LEAK.  THE PART WAS SHIPPED TO EUROCOPTER FOR REPAIR.  EUROCOPTER HAS CONTAC	TED US SAYING THAT THE PISTON HAD BEEN PREVIOUSLY DRESSED FOR DAMAGE, AND WAS FOUND TO BE BENT APPROX 0.032					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005111000035	20051110	00035	SW  	2005	11	10	CA051018006      	1	20051012	G	6330	206033506101	RESTRAINT       	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					XMSN MOUNT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BMC45012					DELAMINATION FOUND ON AFT TRANSMISSIN MOUNT ELASTOMERIC.  MOUNT CHANGED.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2005111000036	20051110	00036	EA  	2005	11	10	CA051019000      	1	20051017	G	7810	2285018124	EXHAUST PIPE    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	DETACHED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											EN ROUTE LOST THE LT ENGINE EXHAUST NOZZLE DURING CRUISE.  THE FLIGHT CREW REPORTED A SLIGHT YAW WHEN THE EXHAUST NOZZLE	 DETACHED, AND THE FLIGHT ATTENDANT REPORTED A CHANGE IN ENGINE NOISE.  THE EXHAUST NOZZLE HAS NOT BEEN RECOVERED.  SHOR	TS BROTHERS SERVICE BULLETIN CF34-78-NAC-024 IS APPLICABLE TO THIS AIRCRAFT/ENGINE, NO EVIDENCE WHERE FOUND THAT SHOWED 	THAT THE SHORTS SB HAD BEEN PERFORMED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005111000037	20051110	00037	EA  	2005	11	10	CA051019001      	1	20051007	G	2740	70744	MCU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					HORIZONTAL STAB	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											IN CRUISE FLIGHT 36000 FT, THE MASTER CAUTION ALERT CAME ON WITH STAB TRIM AND MACH TRIM MESSAGES.  FOLLOWED QRH AND DEC	LARED AN EMERGENCY.  LANDED WITHOUT INCIDENT.  ACCOMPLISHED TROUBLESHOOTING AND REPLACED THE HORIZONTAL STABILIZER MOTOR	 CONTROL UNIT.  THE VENDOR OF THE HORIZ STAB MCU IS SAGEM, VENDOR CODE: VF6151. NOTE 2: AS STATED IN BOMBARDIER AOM 254.	  AIRCRAFT EQUIPPED WITH SPOILER STAB CONTROL UNIT (SSCU) P/N C13045BA03 ARE MORE SUSCEPTIBLE TO STAB TRIM CAUTION MESSA	GES IN CERTAIN CONDITIONS.  THIS AIRCRAFT WAS EQUIPPED WITH SSCU P/N C13045BA03 AT THE TIME OF THE EVENT.  VENDOR OF THE	 SSCU IS THALES AVIONICS, VENDOR CODE: VF9111.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005111000038	20051110	00038	NE  	2005	11	10	CA051019002      	2	20050902	G	7421	CH34745	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOOSE CENTER ELECTRODE, REMOVED FOR FEAR OF FODDING ENGINE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005111000039	20051110	00039	NE  	2005	11	10	CA051019003      	2	20050902	G	7421	CH34745	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOOSE CENTER ELECTRODE, REMOVED FOR FEAR OF FODDING ENGINE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2005111000040	20051110	00040	CE  	2005	11	10	CA051019004      	1	20051017	G	2721	96630000335	TRIM TAB        	BEECH       		BEECH 	100   	B100        	1152919	CE  										RUDDER	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						UK					(CAN) DURING COMPLIANCE WITH RAYTHEON S/B 55-2365 REV.2 ISS. OCT 2005 MAINTENANCE FOUND THE RUDDER TAB DISBONDED ON LOWE	R END.  MAINTENANCE REPLACED THE RUDDER TAB AND RELEASED THE AIRCRAFT.  RESEARCH ON THIS AIRCRAFT DISCOVERED THAT RAYTHE	ON S/B 2 365R1 (A/D 92-07-05) HAD BEEN COMPLIED WITH IN 1992.  THIS AREA IS CALLED UP IN THE MAINTENANCE SCHEDULE TO BE 	INSPECTED EVERY PHASE 2 AND 4.  SUGGEST ALL OPERATORS INSPECT THIS AREA CLOSELY FOR DISBONDING NOT JUST THE DRAIN HOLE I	TSELF.		1	L	7	2 	4T				A14CE   					 
2005120200103	20051202	00103		2005	12	2	CA051020001      	4	20051019	G	2330	50401100003	DISPLAY         			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 22F	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) SEAT VDU 22F WENT BLANK AND SEEMED HOTTER THAN OTHER SCREENS. A HINT OF BURNING WIRE SMELL WAS NOTICED. SMELL DISS	IPATED.  MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MFR 	AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005120200107	20051202	00107	EA  	2005	12	2	CA051020002      	1	20051019	G	3252	412321	NUT             			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF34*       	 	NE  					RT TORQUE LINK	LOOSE           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) CREW REPORTED MAINWHEEL SHIMMY ON LANDING. MAINTENANCE FOUND BOLT (ITEM 45)FROM THE RT MLG TORQUE LINK TO THE SHIM	MY DAMPER HAD BACKED OUT AND THE TORQUE LINKS SEPARATED 1.2500 INCHES. THE SAFTEY BOLT (ITEM 35) AND LOCKING PLATE (ITEM	 60) WERE FOUND LAYING IN THE SHIMMY DAMPER DUST CAP AND THE LOCK WIRE BROKEN.  AFTER REMOVING THE SAFTEY BOLT, THE BOLT	 NUT (ITEM 55) WAS FOUND HAND TIGHT (NORMAL TORQUE IS 130-160 FT. LBS).   NUT WAS RETORQUED, THE SAFTEY BOLT REPLACED, T	ORQUED AND LOCKWIRED IAW AMM 32-11-39. IPC REF 32-11-37 FIG 01-AA1, 32-11-42 FIG 01-AA1. A FLEET CAMPAIGN IS BEING DEVEL	OPED TO CHECK ALL AIRCRAFT TYPE FOR SECURITY AND TORQUE OF SAFTEY BOLT, LOCKING PLATE, AND NUT.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2005120200108	20051202	00108	WP  	2005	12	2	CA051020003      	2	20051020	G	7310	8975131	FILTER          	HONEYWELL   		AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					FUEL PUMP	UNKNOWN         	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) THE INDICATORS ON THE PUMP ASSEMBLIES ARE SHOWING A BYPASS CONDITION. WHEN EXAMINED THE FILTERS ARE CLEAN. THESE F	ILTERS CAN BE LEFT IN SERVICE UP TO 600 HR. BUT ARE NOW TRIPPING THE INDICATOR ANY WHERE FROM 5 TO 500 HRS. WITH THE TYP	ICAL TIME BEING LESS THAN 100 HRS. THERE WAS NO PROBLEM IN THIS AREA UNTIL JANUARY 2005.  ALL 3 INDICATOR ASSEMBLIES HAV	E BEEN TESTED OK. THE TANKS AND TANK SCREENS HAVE BEEN INSPECTED AND FOUND CLEAN. THIS IS A KNOWN PROBLEM AS MFG ISSUED 	SB TFE731-73-3149 ON SEPT. 12, 2005 BUT AS YET THE NEW FILTERS ARE NOT AVAILABLE.		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2005121900064	20051219	00064	CE  	2005	12	19	CA051021001      	1	20051019	G	2131	13034611	CONTROLLER      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN PRESSURE	FAILED          	W				G				O2 MASK DEPLOYED        				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											FLIGHT CREW REPORTED THAT WHILE IN CRUISE AT F/L 200 CABIN ALTITUDE CLIMBED TO 14000 FEET WITH ASSOCIATED WARNINGS AND M	ASKS AUTOMATICALLY DEPLOYING.  AIRCRAFT RETURNED TO BASE WHERE MAINTENANCE CHANGED LT FLOW PACK, AND THE PRESSURIZATION 	CONTROLLER.  GROUND RUNS WERE CARRIED OUT WITH NO FURTHER DEFECTS NOTED.  AIRCRAFT WAS FLOWN FOR OPERATIONAL CHECK OF PR	ESSURIZATION SYSTEM WITH NO DEFECTS NOTED.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005120200109	20051202	00109	NM  	2005	12	2	CA051021002      	1	20051018	G	3220		SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG CENTERING	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE LANDING GEAR WAS NOT RETRACTABLE. EMERGENCY CHECKLIST FOR LANDING GEAR MALFUNCTION AND UNEVENTF	UL RELANDING PERFORMED. THE FAULT WAS CAUSED BY AN A UNSERVICEABLE NLG CENTERING SENSOR.  NOSE WHEEL CENTERING SENSOR RE	PLACED ACCORDING AMM 32-61-00. THE AIRCRAFT IS POST SB84-32-33.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006061200437	20060612	00437	NM  	2006	6	12	CA051021003      	1	20051021	G	5697	35108	TERMINAL        			BOEING	757   	757200      	1384950	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					CCT BREAKER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING VISUAL INSPECTION, NOTICED DISCOLORATION ON FASTON TERMINAL AND INSULATION ON WIRE NR W1272-2001R-12 AT CIRCUIT B	REAKER C-0392, TERMINAL B2.  R1 WINDOW HEAT CIRCUIT BREAKER, NO FAULTS WERE REPORTED ON THE FUNCTIONING OF WINDOW HEAT. 	 TERMINAL REPLACED IAW BOEING SWPM 20-30-11, AND WINDOW HEAT FUNCTION TESTED IAW AMM 30-41-00.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2005121900065	20051219	00065	NE  	2005	12	19	CA051022001      	1	20051020	G	5610	S6120612272	WINDSHIELD      			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					COCKPIT	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											CORNER WINDOW FAILED AFTER LOSING ITS SEAL AND SECURITY OF ATTACHMENT AT THE OVERLAP TO THE GLASS WINDSHIELD.  THIS WAS 	LIKELY CAUSED BY THE SEAL BEING DISRUPTED TWO DAYS EARLIER WITH THE REPLACEMENT OF THE ADJACENT GLASS WINDSHIELD (DUE TO	 AN OVERHEAT PROBLEM).  IT WAS NOTED THAT THE REPLACEMENT CORNER WINDOW HAD A MUCH GREATER OVERLAP WHICH WOULD PROVIDE B	ETTER SECURITY OF ATTACHMENT.			2	G	7	2 	4U	4	U		1H15    	1E3				 
2005120200110	20051202	00110	EA  	2005	12	2	CA051022002      	1	20051008	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					SIDE WINDOW	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) THE LT SIDE WINDOW CRACKED WHILE IN APPROACH. THE WINDOW IS THE OLDER GENERATION OF WINDOW. THE WINDOW WAS REPLACE	D IAW THE AMM.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2005120200111	20051202	00111	EA  	2005	12	2	CA051022003      	1	20051020	G	5280	CC67010520951	DOOR            	BOMBDR      		CNDAIR	CL600 	CL6002C10   	1390015	EA  										LT MLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LT MAIN LANDING GEAR DOOR WAS FOUND MISSING. DAMAGE WAS FOUND ON THE LT OB BRAKE LINE, AFT FUSELAGE FAIRING AN	D AFT WHEEL WELL FLANGE. A NEW DOOR WAS INSTALLED. (SEE ALSO: US #2005102700042)					2	L	7	2 	4F			RT	A21EA   					 
2005121900093	20051219	00093	NM  	2005	12	19	CA051024001      	1	20051013	G	3220	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER T/O, L/G WAS SELECTED UP, BUT NLG DID NOT RETRACT (MAINS OK).  NLG AMBER CAUTION LIGHT WAS ILLUMINATED, CREW SELEC	TED THE GEAR BACK DOWN AND NLG THEN INDICATED A RED UNSAFE LIGHT.  CREW CARRIED OUT THEIR EMERGENCY CHECK LIST, ALT EXTE	NSION ON BOTH GEARS, WITH ALL GEARS THE INDICATING DOWN AND LOCKED.  A/C THEN MADE A SAFE LANDING.  INITIAL CHECKS OFF P	SEU SHOWED NO ABNORMAL FAULTS, WITH THE NLG PROX SENSORS IMPEDANCE AND RESISTANCE CHECKS OK.  A/C WAS TAKEN TO MX HANGAR	 FOR JACKING AND LANDING GEAR RETRACTIONS TESTS/TROUBLE SHOOTING.  FAULT WAS REPRODUCED WITH A/C ON JACKS, WITH FAULT BE	ING TRACED TO THE NLG DOOR SOLENOID SEQUENCE VALVE.  NLG DOOR SOLENOID SEQUENCE VALVE WAS REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005121900095	20051219	00095	NM  	2005	12	19	CA051024002      	1	20051019	G	3260	1061226216	CIRCUIT CARD    			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					PROX SWITCH	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											AIRCRAFT ENCOUNTERED A NOSE GEAR 'DISAGREE' LIGHT ON DESCENT.  THE AIRCRAFT LANDED UNEVENTFULLY.  MAINTENANCE FOUND THE 	NLG LOCK PROXIMITY SWITCH CIRCUIT CARD TO BE AT FAULT.  CARD REPLACED AND GEAR SWING ACCOMPLISHED SUCCESFULLY.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005121900096	20051219	00096	NM  	2005	12	19	CA051024003      	1	20051016	G	2797	R123	RELAY           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											DURING APPROACH, AIRCRAFT ENCOUNTERED FLAP ASYMMETRY.  THE AIRCRAFT LANDED UNEVENTFULLY.  MAINTENANCE CARRIED OUT TROUBL	ESHOOTING AND SUSPECTED THE FLAP ASYMMETRY SHUT OFF RELAY TO BE AT FAULT.  THE RELAY WAS REPLACED AND THE FLAPS CYCLED N	UMEROUS TIMES WITHOUT FAULT.  THE AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006010500011	20060105	00011	GL  	2006	1	5	CA051024004      	1	20051021	G	2400	RB215	GROMMET         	DIAMON      	227521860   	DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE BAFFLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC WAS SNAGGED WITH GEN LIGHT NOT ILLUMINATING WITH BATTERY AND GENERATOR SWITCHES ON. DURING TROUBLESHOOTING IT W	AS FOUND THAT WHERE  ALTERNATOR CONTROL AND BATTERY WIRES PASS THROUGH GROMMET OF ENGINE BAFFLE, WIRES HAD CHAFFED THROU	GH PLASTIC INSULATOR OF WIRE. WEAR WAS CAUSED BY CHAFFING OF GROMMET, WIRES. SNAG WAS CONFIRMED WHEN ONE OF CONTROL WIRE	S AT ALTERNATOR PLUG WAS FOUND BROKEN AT SPADE TERMINAL. ALTHOUGH UNRELATED TO SNAG, WIRE CHAFING WAS SECOND AC FOUND WI	TH SIMILAR WIRE DAMAGE. WIRES WERE REPAIRED AND AIRCRAFT RELEASED. MFG HAS BEEN ADVISED.		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2005122100144	20051221	00144	NM  	2005	12	21	CA051024005      	1	20051023	G	2910		HYDRAULIC SYSTEM			BOEING	757   	757232      	1384965	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					LEFT	WARNING LIGHT   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											AIRCRAFT EN ROUTE HNL - YVR, LOST LT HYDRAULIC SYSTEM APPROX 2 HOURS FROM YVR.  ORIGINALLY PLANNED NORMAL LANDING UTILIZ	ING ALTERNATE SYSTEM BUT DURING LANDING PHASE, FLIGHT ENCOUNTERED FURTHER INDICATION OF HYDRAULIC LOSS AND DECLARED AN E	MERGENCY AND WAS MET BY FIRE EQUIPMENT.  FLIGHT LANDED SUCCESSFULLY AND WITHOUT INCIDENT, BUT HAD TO BE TOWED TO GATE.  	THERE WERE 9J AND 144Y PASSENGERS ONBOARD.  DEFECT IS CURRENTLY UNDER INVESTIGATION AND SDR WILL BE UPDATED AS INFORMATI	ON RECEIVED.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2006010500012	20060105	00012		2006	1	5	CA051024006      	4	20051023	G	2230		AUTOTHROTTLE SYS			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COCKPIT	MALFUNCTIONED   	W				L				ABORTED APPROACH        				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) ON APPROACH, NR 2 THRUST LEVER WOULD NOT GO BACK TO IDLE. AUTO THROTTLE WAS ENGAGED AT TIME AND NR 2 LEVER STOPPED	 1 TO 1.5 FROM IDLE (58 PERCENT N1) AUTO THROTTLE DISENGAGED CORRECTLY BUT STILL NO MANUAL MOVEMENT OF THRUST LEVER AFT.	  AUTO THROTTLE WAS ENGAGED AGAIN AND DISENGAGED.  SYSTEM RETURNED TO NORMAL AT THAT TIME.  CREW ELECTED TO RETURN.  THE	 SYSTEM COULD NOT BE FAULTED BY MAINTENANCE, NOR WAS THERE ANY EVIDENCE OF SOMETHING BLOCKING THE CONTROLS.  THE AUTOPIL	OT COMPUTER SHOWED NO FAULTS.  THE SYSTEM WAS CHECKED SERVICEABLE.		2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006010500013	20060105	00013	CE  	2006	1	5	CA051024007      	1	20051021	G	5320	504200337	BEAM            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20891	20891							(CAN) DURING ROUTINE INSPECTION THE RUDDER SUPPORT BEAM UNDER THE PILOTS RUDDER PEDALS WERE FOUND CRACKED. PART WAS REPL	ACED.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2005122100145	20051221	00145	EA  	2005	12	21	CA051024009      	1	20051024	G	2730	C6TE102627	RIB             			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3T*      	GL  	ELEVATOR	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											PART NOT TO LIMITS PROVIDED BY MANUFACTURER.  ANGLE AND DIMENSIONS NOT TO THE SPECS ON THE MYLAR.  MATERIAL TYPE AND THI	CKNESS ARE CORRECT.					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2005120200112	20051202	00112	NE  	2005	12	2	CA051025001      	2	20051024	G	8520	32983	ROD BEARING     			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								13149			(CAN) DURING INSPECTION PROGRAM OF PULLING A CYLINDER AND PERFORMING AN INTERNAL VISUAL (REPETITIVE 500 HRS), A MECHANIC	 NOTICED IMPACT MARKS ON THE PISTON SKIRT, ELSEWHERE INSIDE CASE. NOTICED A CHUNK OF METAL IN BOTTOM OF THE CASE APPROX 	2INCHES BY .2500 INCH WITH A PARTIA L P/N 2983 STILL LEGIBLE. AFTER CONSULTING THE PARTS CATALOG WE ARE REASONABLY CERTA	IN IT IS A P/N 32983 MASTER ROD CRANKPIN BEARING ALTHOUGH THIS WILL HAVE TO BE CONFIRMED AT TEARDOWN. THERE WERE NO SIGN	IFICANT METAL PARTICLES FOUND IN SUMP OR SCREEN. ENGINE O/H AGENCY HAS BEEN CONTACTED. THE ENGINE HAS BEEN PULLED AND WI	LL BE SENT FOR REPAIR. AT THE TIME OF THE ROUTINE INSPECT ION THE ENGINE HAD BEEN RUNNING FINE WITH NO REPORTED DEFECTS.	1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2005122100146	20051221	00146	CE  	2005	12	21	CA051025002      	1	20051024	G	7931	973840091	INDICATOR       			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					OIL PRESSURE	STUCK           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								PCE50078			ON CLIMB OUT, CO-PILOT NOTICED THE OIL PRESSURE INDICATOR FOR THE RIGHT HAND ENGINE DROP TO 10PSI AND STAY THERE.  ALL O	THER INDICATIONS WERE NORMAL.  THE AIRCRAFT RETURNED TO BASE AND LANDED SAFELY.  THE INDICATOR WAS REPAIRED AND RE-INSTA	LLED.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2005122100148	20051221	00148	NE  	2005	12	21	CA051025003      	2	20050906	G	7210		GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1 RGB	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											FOUND A BOLT LOCKTAB IN NR 1 RGB CHIP DETECTOR HOUSING WHEN INVESTIGATING AN ENGINE CHIP LIGHT.  ON FURTHER INVESTIGATIO	N A SECOND LOCKTAB WAS FOUND IN THE VICINITY OF THE CHIP DETECTOR HOUSING.  POWER SECTION WAS SEPARATED FROM THE C/BOX T	O TROUBLESHOOT THE SOURCE OF THE LOCKTABS AND ONCE DONE TWO BOLT HEADS WERE FOUND INTHE C/BOX.  A P&WC REP WAS ON HAND T	O HELP DETERMINE THE SOURCE, AFTER A BOROS COPE INSPECTION AND P/N ON THE BOLT HEADS, IT WAS DETERMINED THAT THE FAULT W	AS IN THE C/BOX.  SERVICEABLE C/BOX INSTALLED AND A/C RETURNED TO SERVICE.		1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2005122100152	20051221	00152	CE  	2005	12	21	CA051025004      	1	20051024	G	5312		BULKHEAD        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20447								DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON THREE OTHER AIRCRAFT, (SDR 20050829003, 20050928001 AND 20051013007)	 THE AFT PRESSURE BULKHEAD WAS FOUND CHAFFED BY THE CENTER INTERCOSTAL ADJACENT TO THE TAIL ACCESS DOOR.  NDT WAS COMPLE	TED AND A CRACKS FOUND.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2005120200113	20051202	00113	GL  	2005	12	2	CA051025005      	2	20051023	G	7240	6870992J	COMBUSTION CASE 			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			18096								(CAN) AIRCRAFT TOT WAS RUNNING HIGH, N1 WAS ABOUT 91 PERCENT.  BARFIELDED GAUGE, FOUND TO BE CORRECT.  CHECKED THERMOCOU	PLE RESISTANCE, ALSO FOUND TO BE WITH IN LIMITS. CHECKED ARM PIT'S WITH FINGER, FELT OKAY. CHECKED WITH MIRROR, FOUND CR	ACK THROUGH MESH ON LT SIDE ARM PIT. COMBUSTION LINER WAS FOUND CRACKED WITHIN LIMITS, BUT WAS CHANGED DUE TO BEING VERY	 TIGHT ONTO NOZZLE SHIELD.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006010500207	20060105	00207		2006	1	5	CA051025006      	4	20051018	G	2300	GMA340	AUDIO PANEL     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	INTERNAL	FAILED          	W				O				OTHER                   				Z	H		SIGNIFICANT FAILURE REPORT	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			CA							317652086				(CAN) AIRCRAFT EXPERIENCED A COMPLETE COMM FAILURE IN CLIMB STAGE OF FLIGHT.  CREW WAS ABLE TO CONTACT ATC VIA A CELL PH	ONE AND RECEIVE INSTRUCTIONS AND CLEARANCES.  ALL AVIONICS WERE TESTED AND REPORTED TO BE FUNCTIONING FINE.  WIRING ON A	IRCRAFT WAS CHECKED AND AIRCRAFT BATTERY WAS REPLACED.  NEXT DAY AFTER A HALF HOUR FLIGHT, THE PROBLEM RECCURRED. ALTHOU	GH THERE WAS NO SIGN OF PROBLEMS WITH THE AUDIO PANEL IT WAS THE COMMON DENOMINATOR, WHEN THE FAILURE OCCURED IT TOOK OU	T BOTH PILOT AND CO-PILOT COMM SYSTEMS AS WELL AS THE COCKPIT INTERCOM.  THE INTERCOM IS PART OF THE AUDIO PANEL.  SINCE	 THE REPLACEMENT OF THE PANEL THERE HAVE BEEN NO FURTHER FAILURES.  THE AUDIO PANEL WAS NEW IN AUGUST.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2005122100155	20051221	00155	CE  	2005	12	21	CA051025007      	1	20051024	G	3246	50820042601	BARREL          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					NLG WHEEL	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											FLIGHT CREW REPORTED LOSS OF NOSE WHEEL STEERING DURING TAXI.  MAINTENANCE FOUND THE NOSE WHEEL BARREL ASSY BROKEN.  SLO	TS WHICH HOLD IN SPRING RETAINER FOUND BROKEN ALLOWING SPRING TO LOSE TENSION.  MX REPLACED THE ASSY AND RELEASED AIRCRA	FT FOR RETURN TO SERVICE.				1	L	7	2 	4T	4	T		A14CE   	E2WE				 
2005122100157	20051221	00157	NM  	2005	12	21	CA051026001      	1	20051026	G	3230	5114904	PTU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											AFTER TAKEOFF, CREW SELECTED GEAR UP, THE LANDING GEAR DID NOT RETRACT.  AFTER ABOUT ONE MINUTE THE LANDING GEAR RETRACT	ED. IMMEDIATELY FOLLOWING THE RETRACTION THE HYD PRESS 2 CAUTION LIGHT ILLUMINATED, THE NR 2 HYDRAULIC FLUID QUANTITY WA	S RAPIDLY DECREASING AND HYDRAULIC PRESSURE WENT TO ZERO. THE CREW THEN CARRIED OUT AN ALTERNATE GEAR EXTENSION AND RETU	RNED BACK TO BASE, WHERE A NORMAL LANDING WAS MADE.  INITIAL INVESTIGATION OF THE AIRCRAFT FOUND A LARGE HYDRAULIC LEAK 	COMING FROM THE RT WING ROOT AREA.  THE SOURCE OF THE LEAK WAS TRACED TO THE SEPARATION OF THE PTU.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2005122100158	20051221	00158		2005	12	21	CA051026002      	4	20051023	G	2330	50401100003	VIDEO DISPLAY   			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 16C	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											A/C WAS IN LEVEL FLIGHT WHEN SMOKE WAS NOTICED COMING FROM SEAT 16C VDU.  THE IFE SYSTEM WAS DEACTIVATED.  MAINTENANCE R	EPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLE	TE TEAR DOWN REPORT WILL BE REQUESTED.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005122100160	20051221	00160		2005	12	21	CA051026005      	4	20051025	G	2562	E0103E0102	CASE            	ACK         	E01         	CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  					ELT BATTERY	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						027395					AT 12 MONTH CERTIFICATION OF ELT THE UNIT WAS INSPECTED AND FOUND THE BATTERIES LEAKING AND BATTERY CONTACTS ON THE ELT 	BATTERY CASE CORRODED.  BATTERIES HAD A DATE CODE OF MAR 2010 AND MAR 2009.  BATTERIES AND BATTERY CASE REPLACED AND UNI	TTESTED SEVICEABLE.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2005122100162	20051221	00162	GL  	2005	12	21	CA051026006      	1	20050623	G	5740		ATTACH ANGLE    			NAMER 	T6    	HARVARD4    	6400430	GL  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CRACK DETECTION INSPECTION AT WING ATTACHMENT ANGLES ON BOTH WINGS PER AD CF-2005-19.  NO CRACK INDICATION WERE DISCOVER	ED ON THE WING ATTACHMENT ANGLES					1	L	7	1 	3R				EXPA1L71					 
2005122100164	20051221	00164	CE  	2005	12	21	CA051026007      	1	20051020	G	8011	231697	CONTACT         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	STARTER RELAY	MELTED          	W				O				OTHER                   				L	B		NO TEST                   	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA											ENGINE STARTER RELAY ARCING, CAUSED THE CONTACTS TO WELD TOGETHER SOLID.  WHICH IN TURN CAUSED STARTER TO RUN CONTINOUSL	Y UNTIL IT OVERHEATED AND BURNED. POTENTIAL FOR ELECTRICAL FIRE IN ENGINE/WING ROOT.					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
2005120200114	20051202	00114	EA  	2005	12	2	CA051026008      	1	20051011	G	6120		BETA RING       			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									BUA29133		(CAN) IT WAS FOUND THAT THE CIRCLIP SECURING THE BETA BUSHING HAD PULLED AWAY FROM ITS SLOT. THIS WAS DUE TO IMPROPER AD	JUSTMENT OF THE BETA RODS. IT IS RECOMMENDED TO FOLLOW THE INSTRUCTIONS FROM MFG PROPELLER MM P/N 118F PG.7-58 FIG. 7-27	, REV.11 OCT 01.				1	H	7	1 	3R	4	T		A806    	E4EA	6	C	P15EA	 
2006022300045	20060223	00045	CE  	2006	2	23	CA051026009      	1	20050722	G	8011	111138D	CONTACTOR       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					STARTER	SEIZED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) RECURRING DEFECT, STARTER CONTACTOR COILS FUSED TOGETHER DUE TO EXCESSIVE HEAT WHICH RESULTED IN STARTER GETTING S	TUCK (ON).   AFTER 9 ATTEMPTS, AFTER BEING MISLED BY MFG THAT THEY HAD FAULTY CONTACTORS, FOUND MAIN POWER WIRE FROM CON	TACTOR TO STARTER HAD CORRODED TERMINALS WHERE CRIMPED TO WIRE.  THIS WAS NOT VISIBLE UNTIL CUT OPEN.  THE CORROSION LED	 TO A HIGHER CURRENT DRAW THAN NORMAL PASSING ACROSS THE CONTACTOR WHICH MELTED THE COIL WIRED IN THE CONTACTOR.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2005112800165	20051128	00165	SW  	2005	11	28	CA051027001      	1	20051013	G	7920	3108081	LINE            	GARRTT      	TPE33112UHR 	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NR 1 ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						P70196C					(CAN) ENROUTE, FLIGHT CREW OBSERVED A LOW OIL PRESSURE INDICATION ON NR 1 ENG. CONFIRMED LOW OIL PRESS ON GAUGE AND COND	UCTED AN IN-FLIGHT SHUTDOWN PROCEDURE. SINGLE ENG FLIGHT CONTINUED TO DESTINATION. CREW CARRIED OUT LANDING, WITH ERS ST	ANDING BY, WITHOUT FURTHER INCIDENT. MAINT INSPECT FOUND CRACK ON RIGID OIL LINE, APPROX 0.125 INCHES AFT OF ONE FLARED 	END AND CONTINUING HALF WAY AROUND DIAMETER OF LINE.  LINE WAS REPLACED WITH NEW LINE, 5.5 QUARTS OF OIL WAS ADDED, MAG 	PLUG INSPECTED, FOUND TO BE CLEAN, OIL FILTER INSPECTED, NO METAL PARTICLES NOTED. AC WAS GROUND RUN FOR LEAK CHECKS AND	 TAKE OFF PERFORMANCE VERIFIED, AC WAS RETURNED TO BASE, SPECTRO-GRAPHIC OIL ANALYSIS SAMPLES (S.O.A.P.) WASTAKEN.	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2006010500017	20060105	00017	EU  	2006	1	5	CA051027002      	1	20051003	G	5524	5552012186	STOP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ELEVATOR	MISSING         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THIS IS THE SECOND PC-12 IN WHICH THE COMPANY HAS DISCOVERED THIS ELEVATOR STOP TO BE MISSING. THE MISSING STOP WA	S DISCOVERED WHEN REMOVING FLIGHT CONTROLS TO PAINT THE AIRCRAFT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006010500020	20060105	00020	EU  	2006	1	5	CA051027003      	1	20050207	G	5524	5552012186	STOP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ELEVATOR	MISSING         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THIS IS THE SECOND PC-12 THAT THE COMPANY HAS DISCOVERED THIS PART TO BE MISSING. OBSERVATION NOTED WHEN REMOVING 	FLIGHT CONTROLS FOR PAINT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006020300106	20060203	00106	NM  	2006	2	3	CA051027004      	1	20051021	G	3240	BACB30MT10HT13	BOLT            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE WHEEL CHANGE, IT WAS FOUND THAT 2 OF THE 3 BRAKE RETAINING BOLT HEADS HAD SHEARED. THE BROKEN BOL	T HEADS HAD BECOME TRAPPED BETWEEN THE BRAKE AND WHEEL INNER HALF CAUSING SCORING DAMAGE TO THE WHEEL.  IT IS SUSPECTED 	THAT THE COUNTERSUNK WASHERS MAY NOT HAVE BEEN INSTALLED CORRECTLY OR NOT INSTALLED AT ALL UNDER THE BOLT HEAD DURING IN	STALLATION OF THE BRAKE. THIS POSSIBLY CAUSING OVERSTRESSING OF THE BOLT WHEN TORQUED. THIS IS DIFFICULT TO PROVE DUE TO	 LOSS OF THE WASHERS. THE BRAKE WAS INSTALLED IN JUNE 2005.  THE BRAKE CHANGE TASK CARD DOES CONTAIN A WARNING NOTE REGA	RDING THE CORRECT INSTALLATION OF THE WASHERS.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2005112800166	20051128	00166	SO  	2005	11	28	CA051027005      	2	20051014	G	7420	IO8216743	IGNITION LEAD   	BENDIX      	S6LSG25T    	CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	MAGNETO CAP	DETERIORATED    	W				E				ENGINE SHUTDOWN         				E	R	G	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	MULTIPLE FAILURE          	IN	INSP/MAINT     	1			CA						D03GA258R					(CAN) ON GROUND RUN, LT MAGNETO ON FRONT ENGINE HAD A 200 RPM DROP. DURING TROUBLESHOOTING FOUND NR 4 CYLINDER TOP LEAD 	SHORTING FROM INNER COIL THROUGH INSULATOR TO CAP. LEAD REPAIRED, AIRCRAFT RELEASED INTO SERVICE. AFTER A FEW HOURS OF F	LIGHT, THE PROBLEM RE-OCCURRED ON RT MAGNETO FRONT ENGINE. REPLACED IGNITION HARNESSES WITH NEW. MAGNETO RT  PN S6LSG-25	T,  SN D03GA258R, LT P/N S6LSG-25, SN D03GA179R.			1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2006020300107	20060203	00107	EA  	2006	2	3	CA051027006      	1	20051007	G	5610	06422	WINDSHIELD      			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O	M		OTHER                     	OVER TEMP                 		CR	CRUISE         	1			CA			23321								(CAN) AC, WHILE IN LIGHT ICING CONDITIONS, ENCOUNTERED A MALFUNCTION OF CAPTAIN'S (LT SIDE) WINDSHIELD. ENTERING ICING C	ONDITIONS, NORMAL MODE WAS SELECTED. CAPTAIN NOTICED DISCOLORATION IN LWR PORTION OF WINDSHIELD, VERBALIZED IT TO F/O. C	APTAIN OBSERVED DISCOLORATION SPREADING AND SELECTED WINDSHIELD HEAT SWITCH TO WARMUP, THEN TO OFF TO SUSPEND DISCOLORAT	ION GROWTH. AT THE SAME TIME, CRACKS WERE OBSERVED DEVELOPING ALONG AND AROUND DISCOLORED AREA. CREW THEN CHANGED COURSE	. UNEVENTFUL LANDING WAS EXECUTED AND MAINTENANCE STAFF PROCEEDED TO WORK ON THE AIRCRAFT. AT THIS TIME, SPARE PART PROC	UREMENT AND TROUBLESHOOTING ARE ONGOING AND THE AIRCRAFT IS EXPECTED TO RETURN TO SERVICE.	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006010500024	20060105	00024	CE  	2006	1	5	CA051027007      	1	20051016	G	2731	50524161606	ACTUATOR        			BEECH 	90    	C90         	1152913	CE  										ELEVATOR TAB	CONTAMINATED    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AFTER REACHING CRUISE ALTITUDE ELEVATOR TRIM FAILED TO MOVE ANY FURTHER. NOSE DOWN AIRCRAFT RETURNED TO BASE AND A	N ELEVATOR TRIM SYSTEM INSPECTION WAS CARRIED OUT. NO DISCREPANCIES COULD BE FOUND IN THE SYSTEM, BUT WATER WAS FOUND ON	 THE TAB ACTUATOR SCREW. IT IS BELIEVED THAT THIS WATER FROZE AT ALTITUDE ALLOWING NOSEUP TRIM BUT NOT NOSE DOWN. THE WA	TER WAS REMOVED, ACTUATORS GREASED AND A TEST FLIGHT CARRIED OUT. THE PROBLEM COULD NOT BE DUPLICATED IN THE HANGAR OR O	N THE TEST FLIGHT. THE AIRCRAFT WAS RETURNED TO SERVICE.		1	L	7	2 	3T				3A20    					 
2006010400102	20060104	00102	SW  	2006	1	4	CA051027008      	1	20051024	G	6320	206040010103	PLANETARY GEAR  			BELL  	206   	206B1       	1181503	SW  	ALLSN 	250C  	250C20      	03013	GL  					GEARBOX	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A820					(CAN) PLANETARY GEAR FLANKS SURFACE FINISH EXCEED THE ENGINEERING DRAWING REQUIREMENT OF (RMS 8 RA).4 GEARS IAW XMSN IAW	 206B.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006010500026	20060105	00026	SW  	2006	1	5	CA051027009      	1	20051025	G	5320	272008478	WEB             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24654								(CAN) DURING INSPECTION, MAINTENANCE FOUND SEVERAL FATIGUE CRACKS IN THE CENTER AISLE FLOORBOARD WEBS AND FLOOR FRAMES B	ETWEEN STATIONS 174 AND 427. THESE CRACKS WERE FOUND ON BOTH THE LT AND RT SIDES OF THE AISLE.  BOTH WEBS WERE REPLACED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2006010500035	20060105	00035	EA  	2006	1	5	CA051028001      	1	20051016	G	3213		TORQUE LINK     		492009      	CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					LT MLG	DISCONNECTED    	W				K				NONE                    				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		LD	LANDING        	1			CA						SPP0042					(CAN) HVY VIBRATION AFTER TD UNTIL TAXI SPEED IS REACHED. INDEPENDENT FROM BRAKE APPLICATION.  AC WAS SMOOTH DURING TAXI	 AND TAKEOFF ROLL. ON ARRIVAL FOUND LT MLG TORQUE LINK DISCONNECTED. WHEEL NR 2 DESTROYED. SHIMMY DAMPER TORN OFF. VARIO	US DAMAGE ON BRAKE NR2, UPPER AND LOWER LINK, HYD LINE AND HARNESS FIXTURE. ALMOST ALL PARTS COLLECTED ON RWY. SUSPECT D	ISCONNECT WAS CAUSED BY INCOMPLETE OR MISSING ASSY OF TORQUE LINK CONNECTING PIN SAFETY BOLT IPC REF 32-11-42 ITEM 35, N	OT FOUND ON RUNWAY. NOTICED INITIAL OIL LEAKAGE FROM LT MLG SHOCK STRUT. LT MLG REPLACED. LT SIDE STAY REPLACED. DVI OF 	STRUCTURE SURROUNDING GEAR ATTACHMENT PERFORMED, NO FINDING. FDR DOWNLOAD PERFORMED. NO ACTION REQUIRED AFTER ANALYSIS.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006010500042	20060105	00042	NE  	2006	1	5	CA051028002      	2	20051024	G	7310	4120T03P04	ACTUATOR        			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					LT ENGINE	LEAKING         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FOUND FUEL LEAKING FROM LT ENGINE VG ACTUATOR (SECONDARY).						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006010500208	20060105	00208	EU  	2006	1	5	CA051028003      	1	20051010	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD SYS	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21038								(CAN) DURING A 100-HR INSPECTION THE HYDRAULIC PUMP SPLINES AND HYD PUMP DRIVE SPLINES WERE INSPECTED IAW FORM AS350B-IN	S-100.  BOTH THE HYDRAULIC PUMP AND HYDRAULIC PUMP SPLINES WERE FOUND TO BE WORN IN EXCESS OF THE .3333 ALLOWED.  THE LU	BRICATION WAS INSUFFICIENT IN THAT THE HYDRAULIC PUMP DRIVE CAVITY WAS DRY.  THE SPLINES APPEARED TO BE DRY.  THE LITTLE	 REMAINING GREASE WAS BROWN OR RUSTY IN COLOR.  BOTH THE HYDRAULIC PUMP AND HYDRAULIC PUMP DRIVE HAD TO BE REPLACED.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006020300110	20060203	00110	NE  	2006	2	3	CA051028004      	2	20051026	G	7250	311074102	SEGMENT         	PWA         	PT6A114A    						PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE	DISTORTED       	W				E				ENGINE SHUTDOWN         				E	W		VIBRATION/BUFFET          	INADEQUATE Q C            		CR	CRUISE         	1			CA						96A443					(CAN) REPAIR DUE TO SHIFTING OF CT SHROUD SEGMENTS, HEAVY RUB ON CT BLADES/SEG. EXCESS GAP BETWEEN CT SHRD SEG, CT SHRD 	HSG MATING SURFACES WERE NOTED. CT SHRD SEG-RETAIN RING WAS OF POST SB, CT SHRD SEG WERE PRE SB 1628. RUB SPOTS WERE NOT	ED ON ALL (QTY 9) CT SHRD SEG, CT BLADES. CT SHRD SEG-RETAIN RING WAS FOUND DISTORTED, COMPLETELY DISENGAGED FROM RETAIN	 GROOVE OF CT SHRD HSG. CMM INSP OF CT SHRD HSG WAS DONE, ROUNDNESS OF ALL CRITICAL DIA NOTED WITHIN MM LIMIT.  CT SHROU	D SEG RETAINING RING WAS FOUND DISTORTED, COMPLETELY DISENGAGED FROM CT SHROUD HSG RETAINING GROOVE. PROBLEM DUE TO PREM	ATURE FAILURE OF CT SHROUD SEG RETAINING RING.  NEW CONFIGURATION PARTS INTENDED TO PREVENT THIS PROBLEM.						3	T			E4EA				 
2006010500209	20060105	00209	EU  	2006	1	5	CA051028005      	1	20051025	G	2752	9787320309	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FLAP SYSTEM	BINDING         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) ON FLAP RETRACTION AFTER TAKEOFF, FLAP WARNING LIGHT CAME ON.  AIRCRAFT RETURNED TO AIRPORT AND CARRIED OUT A SUCC	ESSFUL FLAP RESET.  AIRCRAFT DEPARTED, AND ON FLAP RETRACTION, FLAP WARNING CAME ON WITH FLAPS STOPPING BETWEEN 0 AND 15	 DEGREES.  AIRCRAFT RETURNED TO BASE.  FLAP FAULT CHECK WAS CARRIED OUT AND FAULTS INDICATED A STIFFNESS IN THE SYSTEM. 	 FOUR FLAP CYCLES WERE CARRIED OUT AND FLAP ACTUATORS CHECKED.THE RT IB ACTUATOR WAS FOUND EXTREMELY HOT.  ACTUATOR WAS 	CHANGED AND AIRCRAFT RETURNED TO SERVICE.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006010500048	20060105	00048	NM  	2006	1	5	CA051031001      	1	20051028	G	3246	LM29700LA902A1	BEARING         	BFGOODRICH  	31574       	BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI TO GATE AFTER ARRIVAL TO BASE, AIRCRAFT STOPPED DUE TO DIFFICULTY TO USE NLG STEERING. CREW FOUND LT N	LG AXLE DAMAGED, DUE TO BEARING FAILURE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006010500210	20060105	00210	NM  	2006	1	5	CA051031002      	1	20051029	G	5241	AR47013	STRIKER         			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					COCKPIT DOOR	BURNED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) FAULT:  STRONG RUBBER BURNING SMELL FIRST NOTICED IN FWD GALLEY THEN IN COCKPIT.  AUTH  NR175945 FOUND FLT DECK DO	OR ELEC LOCK ACT BURNNED.  LOCK ACT ELECT CONNECTORS REMOVED AND STOWED, C/B PULLED AND COLLARED.  (RUNOUT DATE10/31/200	5).				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006020300111	20060203	00111	SO  	2006	2	3	CA051031003      	2	20051021	G	8530		CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) 7 HOURS ON OH ENG, MTCE WAS NOTIFIED VIA RADIO RELAY THAT AC WAS HAVING ENG TROUBLE. JUST ABLE TO MAINT ALTITUDE, 	AROUND 2500 FT, ENG WAS SURGING, SPUTTERING. NOTHING PILOT DID RECTIFIED PROBLEM. CONFIRMING FUEL, PUMPS MADE NO DIFFERE	NCE, MTCE, OPS INSTRUCTED PILOT TO MAKE IMMEDIATE LANDING.  2 ENGINEERS FOUND NR 6 CYL W/ NO COMPRESSION, BENT PUSH RODS	.  CYL, PUSH RODS WERE SENT NEXT DAY, UPON REMOVAL OF CYL IT WAS FOUND EXHAUST VALVE HAD BUSTED ON STEM, HAMMERED ITSELF	 INTO VALVE SEAT, PISTON.  SERV CYL PISTON, RODS INSTALLED,  AC WAS FLOWN BACK TO BASE, ON APPROACH ENG BEGAN TO RUN ROU	GH W/ UNEVENTFUL LANDING. IT WAS FOUND THAT RODS HAD BENT AGAIN W/ NO DAMAGE TO CYL OR VALVES. ENG REMOVED FROM SERV.	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2006010500055	20060105	00055	EU  	2006	1	5	CA051031004      	1	20051014	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYDRAULIC SYS	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FILTER INDICATOR POPPED, FILTER DIRTY AND REPLAYED.  METAL CHIPS FOUND ON CHIP PLUG.  TECH REP SUGGESTED	 CHANGING HYD PUMP.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006010400090	20060104	00090	EU  	2006	1	4	CA051101001      	1	20051030	G	3020	F10A5P202413	TUBE            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					BYPASS DUCT	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE NACELLE HEAT WOULD NOT TEST PROPERLY ON GROUND.  FURTHER TROUBLESHOOTING REVEALED THAT THE BLEED SUPPLY PIP	E WAS RUPTERED IN THE BYPASS DUCT AREA.  PIPE WAS REPLACED AND SYSTEM WAS GROUND CHECK WITH NO FURTHER FAULTS FOUND.					2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2006010400119	20060104	00119	SW  	2006	1	4	CA051101002      	1	20051029	G	6320	205040229003	SUN GEAR        			BELL  	412   	412EP       	1182205	SW  										M/R TRANSMISSION	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) 412 MAIN TRNASMISSION SUN GEAR 205-040-229-003 MANUFACTURED WITH WRONG TYPE MATERIAL.						1	G	7	2 	4U				H4SW    					 
2006010600027	20060106	00027	EA  	2006	1	6	CA051101003      	2	20051017	G	8520	74968	CRANKSHAFT      	LYC         	0360C2E     	BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						L3376336A					(CAN) ENGINE WAS REMOVED FROM THE AIRCRAFT AND SENT TO AN OVERHAUL FACILITY FOR AN INSPECTION DUE TO A PROP STRIKE. DURI	NG THE INSPECTION OF THE CRANKSHAFT, IT WAS NOTICED THAT THE URETHANE INTERNAL COATING (PID) WAS BLISTERING. FURTHER INS	PECTION OF THE AREA REVEALED CORROSION, WHICH WAS BEYOND LIMITS, AND THE CRANKSHAFT WAS TAKEN OUT OF SERVICE.  THE ENGIN	E WAS A FACTORY EXCHANGE WITH 4 YEARS AND 776.0-HRS ON IT.  THE CRANKSHAFT WAS MARKED PID AND DID NOT REQUIRE ANY INTERN	AL INSPECTIONS UNTIL OVERHAUL AT 2000-HRS (REF AD 98-02- 08, SB 530B, SB 505B).		1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006010600028	20060106	00028	EU  	2006	1	6	CA051101004      	1	20051021	G	2742	47172	ACTUATOR        			AIRBUS	330   	A300*       	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HORIZ STAB	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNMODIFIED LOWER CLAW STOP FITTED WHICH IS NOT IN COMPLIANCE WITH DGAC AD NR. F2002-414R3 REF. TRW SB 47172-27-03 	PARAGRAPH D (4). UNIT WAS REPAIRED AND SCREW SHAFT ASSY WAS REPLACED BY RETRO-FITTED ONE ON WHICH THE CLAW HAD NOT BEEN 	TO THE LATEST STANDARD.				2	L	7	2 	4F	4	F	RT	A26NM   	E39NE				 
2006020300112	20060203	00112	WP  	2006	2	3	CA051101005      	1	20051025	G	2822	B8187B	PUMP            	WELDON      	D7431       	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					ELEC FUEL PUMP	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						105489					(CAN) PUMP WAS NOT PROVIDING ENOUGH FUEL TO PRIME THE ENGINE.  ELECTRIC PUMP ASSEMBLY REPLACED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006020300113	20060203	00113	CE  	2006	2	3	CA051101006      	1	20050809	G	2434	DOFF1300J	ALTERNATOR      			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REMOVED ALTERNATOR S/N D120708 SEPARATED AT 545.2 TSO AND 12 MONTHS LATER INSTALLED S/N 032530 AT 9 AUG. 05 AND RE	MOVED IT 11 SEPT.05 156.6 HOURS SINCE REBUILD, SEPERATED AGAIN AND GOT WARRANTY ON IT. THIS PROBLEM IS MORE COMMON THAN 	NOT IN THE INDUSTRY.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2006010500061	20060105	00061		2006	1	5	CA051101007      	4	20051011	G	2565	4A40302	SLIDE           			EMB   	ERJ170	ERJ170100LR 	       	EU  	GE    	CF34  	CF348E5A1   	30015	NE  					L1 DOOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) L1 DOOR ESCAPE SLIDE PARTIALLY DEPLOYED WHEN DOOR OPENED FROM OUTSIDE.  L1 DOOR DEACTIVATED IAW MEL 52-00-00. SLID	E REMOVED,  DID NOT INFLATE AND BOTTLE DEACTIVATED.					2	L	7	4 	4F	4	F	RT	A56NM   	E00063EN				 
2006010500064	20060105	00064	NM  	2006	1	5	CA051101008      	1	20050731	G	5347	6562157505	FITTING         			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CORROSION TASK C53-107-01-01.7 IS INSPECTING THE CABIN SEAT TRACKS. THE CORROSION WAS FOUND ON THE UPPER DECK 	CARGO G NET FITTING P/N 65-62157-505. THE FOLLOWING INSPECTIONS OF THIS FITTING HAVE BEEN INCORPORATED IN THE  MAINTENAN	CE PROGRAM 1) ADDITION OF WORK CARD 3039 CLEANING AND INSPECT COMPLETED 18 MONTHS OR 4000HRS 2) AMENDMENT OF WORK CARD 3	031 TO INCLUDE CARGO NET FITTING CORROSION INSPECTION COMPLETED 8 YEARS.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006010500065	20060105	00065	NM  	2006	1	5	CA051101009      	1	20050731	G	5260	65593416	HINGE FITTING   	BOEING      	65593416    	BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					AFT AIRSTAIR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NO CPCP CORROSION TASK COVERS THIS AREA, BUT DUE TO THE FINDINGS THE MAINTENANCEPROGRAM IS BEING AMENDED TO REDUCE	S THE CORROSION FINDINGS IN THIS AREA. THE CO RROSION WAS FOUND ON THE AFT AIRSTAIRS UPPER HINGE FITTING ON THE LOWER FO	LDING SECTION. THE FOLLOWING INSPECTIONS OF THIS FITTING HAVE BEEN INCORPORATED,1) AMENDMENT OF WORK CARD 40118 FOR THE 	FWD AND AFT AIRSTAIR. 2) AMENDMENT OF WORK CARD 40116 FOR THE FWD AIRSTAIR. 3) AMENDMENT OF WORK CARD 41220 FOR THE AFT 	AIRSTAIR.		2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006010600032	20060106	00032	GL  	2006	1	6	CA051102001      	1	20050421	G	5551	MS932013	WASHER          	DIAMON      	225510000   	DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	HORIZ STAB	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE FOLLOWING SUBMISSION WAS FOUND MISSED DURING OUR MOST RECENT INTERNAL AUDIT.  DURING THE 1000HR INSPECTION IS 	REQUIRED THAT THE HORIZONTAL STABILIZER BE REMOVED FROM THE AIRCRAFT WHICH REQUIRES THE 4 BOLTS OF BRACKET ATTACHING THE	 REAR HORIZONTAL STABILIZER SPAR TO THE VERTICAL TAIL FIN RIB REMOVED. PRIOR TO REMOVAL IT WAS NOTED THAT THE 4 WASHERS 	ON THE NUT SIDE SEEMED TO BE OFF CENTER AND ONCE REMOVED IT BECAME APPARENT. THE 4 WASHERS WERE MS9320-13 AND NOT MS9320	-12 AS CALLED OUT IN THE IPC, MAKING THE INSIDE DIAMETER OF THE WASHER ONE SIZE LARGER THAN THE AN6-16A BOLT USED IN THE	 ASSEMBLY. WASHERS WERE REPLACED AND AIRCRAFT RELEASED.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006020300114	20060203	00114	NE  	2006	2	3	CA051102002      	2	20051027	G	7321		FUEL CONTROL    	PWA         		SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					NR 2 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) PILOT ELECTED TO BACK AC OUT AWAY FROM LOG LANDING. AS AC STARTED ITS REARWARD DESCENT DOWN TO LOGGING BLOCK, PILO	T HEARD WHOOSH SOUND FOLLOWED BY AN ENG LOW RPM AUDIO WARN HORN. NR 2 ENG WAS IN ROLLBACK CONDITION W/DECREASING N1 SPEE	D, INCREASING T5 TEMP. AFTER VERIFICATION FROM COMMAND PILOT, CO-PILOT EXECUTED SHUTDOWN OF NR 2 ENG.  IT IS TO BE NOTED	 THAT T5 TEMP LIMITS WERE NOT EXCEEDED. WITH ENG MOTORING PROCED COMPLETE, AC RETURNED, MADE SINGLE ENG LANDING.  FOLLOW	ING AN ENG ROLL, FCU AND FUEL PRESSURIZING AND DUMP (PD) VALVE WERE REPLACED, RETURNED FOR INTERNAL EVAL.  A REPLACEMENT	 FCU AND PD VALVE WERE INSTALLED AND AFTER A COMPLETE GROUND CK OF ENG, AC WAS RETURNED TO SERVICE.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006022200073	20060222	00073	NE  	2006	2	22	CA051102003      	2	20051029	G	7321		ENGINE          			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					NR 1	FAILED          	W				E				ENGINE SHUTDOWN         				N	J		FALSE WARNING             	WARNING INDICATION        		DE	DESCENT        	1			CA								672549			(CAN) AFTER SLIGHT REDUCTION IN PWR SETTING PILOT HEARD A WHOOSH SOUND FOLLOWED BY N1 LOW RPM AUDIO WARNING HORN. CO-PIL	OT IDENTIFIED NR1 ENG IN A ROLLBACK CONDITION WITH A DECREASING N1 SPEED AND AN INCREASING T5 TEMP. AFTER VERIFICATION, 	 EXECUTED A SHUTDOWN OF NR 1 ENG. FOLLOWED BY ENGAGEMENT OF ENG STARTER TO MOTOR ENG IN ORDER TO COOL DOWN T5 OVER-TEMP 	CONDITION OF 805 DEGREES C. WITH ENG TEMP IN AN ACCEPTABLE RANGE, MOTORING PROCEDURES DISCONTINUED, AC RETURNED, MADE A 	SINGLE ENG LANDING. A REPLACEMENT ENG, FREE TURBINE, FCU AND P&D VALVE WERE INSTALLED. ENG WAS GROUND TESTED AND AC WAS 	RETURNED TO SERVICE. AS A RESULT OF HAVING 2 ENGINE ROLL BACKS, FUEL SAMPLES WERE TAKEN FROM AC AND SENT FOR ANALYSIS.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006010500066	20060105	00066	NM  	2006	1	5	CA051102004      	1	20051030	G	5610	80260008	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA											(CAN) CREW REPORTED CO-PILOT'S WINDSHIELD CRACKED AFTER THE AIRCRAFT LANDED.  MECHANICS ADVISED THAT CO-PILOT'S WINDSHIE	LD HAS A CRACK ABOUT 50 CM ON THE OUTER PLY.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006010600034	20060106	00034	EU  	2006	1	6	CA051102005      	3	20051101	G	6112	697070212	BUSS BAR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLER	SHORTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CRUISE, RT DC GEN HOT CAUTION LIGHT STARTED FLICK. QRH CONSULTED, FC SWITCHED OFF DC GEN NR2.  AC WENT INTO ICING 	COND, FC SWITCHED ON PROP DEICE. AFTER PROP DEICE CAUTION WENT ON AND OFF. MADE AC GEN NR1, NR2 OFF LINE. WITH ONLY DC G	EN NR1 ON LINE FC DECIDED TO DIVERT.  DC GEN NR2 HOT LIGHT WAS STILL FLICKERING. CKD DC GEN TEMP, FOUND NOT HOT.  CIRCUI	T FROM P1 AT DC GEN TO CAUTION WARN PNL CKD W/O FINDINGS.  DC GEN NR2 REPLACED, TEST RUN.  TROUBLESHOOTING ON PROP DEICE	 FOUND THAT BUS-BAR ON BACK OF SLIP-RING WAS BURNED, ONE END WAS BENT AWAY FROM SLIP-RING. TMCU FAIL CODES SHOWED PHASE 	2 SHORTED, HAS CAUSED OVERLOAD IN AC SYS, DISCONNECTED BOTH AC GEN NR1, NR2. BUS-BAR REPLACED, SYS TESTED W/O REMARK.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006010400092	20060104	00092	CE  	2006	1	4	CA051102007      	1	20051101	G	5753	0523914	SKIN            	CESSNA      		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RT TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14730								(CAN) OPENED LEADING EDGE OF RT FLAP SKIN FOR REPAIR. VISUALLY NOTICED CRACKED CENTER LEADING EDGE RIB AT BOLT HOLE FOR 	FLAP ACUATING PUSH ROD BRACKET ATTACHMENT. OUTER LEADING EDGE SKIN NOT DAMAGED AT THIS LOCATION.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006010500067	20060105	00067	EA  	2006	1	5	CA051102008      	1	20051102	G	5312		BULKHEAD        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	BWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHERE THE JANITROL CABIN HEATER MOUNTS TO THE FORWARD CABIN ENTRANCE BULKHEAD FS234.5, A 4 INCH CRACK WAS DISCOVER	ED DURING A 6 YEAR C-CHECK INSPECTION. THE CRACK RUNS PARALLEL TO THE HEATER MOUNTING FLANGE.  THE 5 OTHER AIRCRAFT OF T	HE FLEET ARE TO BE INSPECTED BEFORE UPCOMING FIRE SEASON. FINDINGS WILL BE RECORDED.				2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2006010500068	20060105	00068	NM  	2006	1	5	CA051103001      	1	20051101	G	3230	471515	SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. A/C RETURN TO BASE. THE FAULT WAS CAUSED BY A UNSERVICEABLE NLG CENT	ERING SENSOR.  NOSE WHEEL CENTERING SENSOR REPLACED IAW AMM 32-61-00. AIRCRAFT RTS.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006020300115	20060203	00115	CE  	2006	2	3	CA051103003      	1	20051101	G	5312		BULKHEAD        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	AFT PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17205								(CAN) DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON 4 OTHER AIRCRAFT, (SDR 20050829003, 20050928001, 20051013007 A	ND 20051025004) THE AFT PRESSURE BULKHEAD WAS FOUND CHAFFED BY BOTH THE CENTER INTERCOSTAL AND THE OB INTERCOSTAL ADJACE	NT TO THE TAIL ACCESS DOOR. NDT WAS COMPLETED AND A CRACK FOUND AT THE OB LOCATION.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2006010500073	20060105	00073	CE  	2006	1	5	CA051103004      	1	20051011	G	5320	9744001967	WEB             			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) WEB CRACKED HORIZONTALLY APPROX. 10 INCHES. CRACK COINCIDES WITH FLANGE OF UNDERLYING Z CHANNEL. PROBLEM APPEARS T	O BE RELATED TO POOR MANUFACTURING PRACTICES.  PRC SEALANT BEAD APPLIED TO Z CHANNEL FLANGE CURED BEFORE RIVETING. THE R	ESULT WAS THAT THE SEALANT BEAD CAUSED A STRESS RISER COMPOUNDED BY PRESSURIZATION LOADS ACCELERATING THE FATIGUE. THIS 	CONCLUSION WAS ARRIVED AT BY OBSERVING THAT THE CRACK EXACTLY CO-INSIDES WITH THE PATH OF THE SEALANT BEAD.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006010500078	20060105	00078		2006	1	5	CA051103005      	4	20051029	G	2210	065001640100	ADAPTER         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AUTOPILOT SYS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) AUTO PILOT TRIPPED OFF LINE.  RED TRIM ANNUNCIATOR ILLUMINATED ON MODE CONTROLLER.  FLIGHT DIRECTOR WAS FUNCTIONIN	G NORMAL.  ALL ELECTRIC TRIMS FUNCTIONING NORMAL.  AUTO PILOT WOULD NOT TEST, THEREFORE NOT ENGAGE. PITCH TRIM ADAPTER F	OUND AT FAULT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006010500082	20060105	00082		2006	1	5	CA051103006      	4	20051031	G	3425	066031252500	ADI             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	FAULTY          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EADI ON COPILOTS SIDE WOULD GO (FUZZY) INTERMITTENTLY.  PART REPLACED WITH SERVICEABLE UNIT. THIS SEEMS TO BE A RE	CURRING DEFECT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006010500094	20060105	00094		2006	1	5	CA051103007      	4	20051031	G	6122	8210137	GOVERNOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE PHASE 4 INSPECTION, METALLIC POWDER WAS DISCOVERED TRAPPED IN THE ENGINE MAIN OIL FILTER. SOURCE 	OF CONTAMINATION WAS CONFIRMED TO BE THE PROPELLER GOVERNOR AS SOME NON-METALLIC DEBRIS WAS FOUND IN THE OVERSPEED GOVER	NOR GASKET SCREEN.  ONCE REMOVED, THE CSU SPLINED SHAFT CAN ONLY BE ROTATED IN ONE DIRECTION AND FEELS (ROUGH).  CSU REP	LACED. O/S GOVERNOR INSPECTED BY APPROVED SHOP, REINSTALLED. MFG AND PC12 MANUALS CONSULTED FOR PROPER FLUSHING ETC.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006010500100	20060105	00100	NE  	2006	1	5	CA051103008      	2	20051021	G	7250	500310401	TURBINE BLADES  			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					NR 1 ENGINE	MISSING         	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			20240								(CAN) IN CRUISE, LOST EGT INDICATION UPON DESCENDING AND POWER REDUCTION NR1 ENGINE RESULTED IN VIBRATION REQUIRING NR1 	ENGINE TO BE SHUTDOWN. INITIAL INSPECTION INDICATED SOME VISIBLE T4 BLADE DAMAGE WHEN VIEWED THROUGH TAILPIPE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006010400123	20060104	00123	CE  	2006	1	4	CA051103009      	1	20051031	G	3233	24170161	ACTUATOR        			LEAR  	55    	55LEAR      	5170702	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					UPLOCK	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER T/O AND UPON GEAR RETRACTION, NOSE GEAR UNSAFE LIGHT REMAINED ILLUMINATED. MULTIPLE GEAR SELECTIONS HAD NO E	FFECT.  CREW ELECTED TO CIRCLE FOR ABOUT AN HOUR TO BURN OFF FUEL BEFORE RETURNING TO BASE.  MAINT WAS ABLE TO CONFIRM S	NAG, RECTIFY BY BLEEDING HYDRAULICS.  PREVIOUS TO THIS OCCURRENCE ALL HYDRAULIC HOSES IN NOSE BAY WERE CHANGED AND SYSTE	M BLED IAW MM PROCEDURES. AIRPLANE THEN SAT FOR 7 DAYS. THERE IS NO SPECIFIC TEST CALLED OUT IN THE MM. FOR BLEEDING THE	 LANDING GEAR HYDRAULIC LINES AFTER REPLACEMENT. IN THE PROCEDURES FOR REPLACING THE NOSE GEAR ACTUATOR, THERE IS MENTIO	N TO PRESSURIZE AND BLEED THE SYSTEM, BUT IS NOT SPECIFIC ABOUT WHAT SHOULD BE DONE.	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006010500104	20060105	00104	SO  	2006	1	5	CA051103010      	1	20051016	G	3340	6367400	SCREW           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	LANDING LIGHT	BACKED OUT      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12700								(CAN) THE THUMB SCREW HOLDING THE AIR FILTER/LANDING LIGHT ASSY BACKED OFF AND THE ASSY CAME OFF DURING RUNUP.  NO OTHER	 DAMAGE WAS INCURRED.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006010500109	20060105	00109	EA  	2006	1	5	CA051103011      	1	20051102	G	3234	574205A	SELECTOR VALVE  			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LANDING GEAR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			35595								(CAN) WHEN SELECTING GEAR DOWN FOR ARRIVAL , RECEIVED 3 RED GEAR INDICATION AND NO GEAR EXTENSION.  ALTERNATE GEAR EXTEN	SION USED. AIRCRAFT LANDED NORMALLY.  MAINTENANCE REPLACED LANDING GEAR SELECTOR VALVE. GEAR FUNCTION TESTED.  AIRCRAFT 	RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061200438	20060612	00438	SO  	2006	6	12	CA051103012      	1	20051028	G	2130	4624500	EVAPORATOR      			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3T*      	GL  	CABIN CONTROLLER	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											DURING DESCENT, PILOT ADJUSTED CABIN CONTROLLER AND VERY SHORTLY AFTER HEARD A BANG FOLLOWED BY A DECOMPRESSION.  DROPPE	D DOWN TO THEIR CLEARED ALTITUDE AND LANDED UNEVENTFULLY.  UPON FURTHER INSPECTION IT WAS DISCOVERED THAT THE FRESH AIR 	DISTRIBUTION HOSE ON THE EVAPORATOR SLIPPED OFF.				1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2006010500112	20060105	00112	EA  	2006	1	5	CA051104001      	2	20051005	G	7314	025332310103	SPLINE          		3031709     	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL PUMP	DAMAGED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA						12698					(CAN) DURING CRUISE THE ENGINE WAS REPORTED TO HAVE LOST POWER AND THE CREW SHUTDOWN THE ENGINE IN FLIGHT.  SUBSEQUENT I	NSPECTION REVEALED A DAMAGED FUEL PUMP DRIVE SPLINE.					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006010500115	20060105	00115	NE  	2006	1	5	CA051104002      	2	20051015	G	7200		ENGINE          	PWA         	PW123C      	DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			TO	TAKEOFF        	1			CA						AE0090					(CAN) DURING TAKE-OFF AND CLIMB THE ENGINE WAS REPORTED TO SURGE AND LOSE POWER.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND 	THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED METALIC DEBRIS ON THE TURBOMACHINE CHIP DET	ECTOR .  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006010500117	20060105	00117	NM  	2006	1	5	CA051104003      	1	20051007	G	7931	312249	PRESSURE SWITCH 			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	OIL SYSTEM	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE CREW SHUT THE ENGINE DOWN IN FLIGHT.  SUBSEQUENT INSPECTIO	N REVEALED NO EVIDENSE OF OIL LOSS AND THE LOW OIL PRESSURE SWITCH WAS REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006010400108	20060104	00108	NE  	2006	1	4	CA051104004      	2	20051018	G	7200	PT6A114A	ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE (FAILED) IN FLIGHT AND AN EMERGENCY LANDING WAS CARRIED OUT.  THE AIRCRAFT CONTACT	ED POWER LINES AND SUBSEQUENTLY CRASHED INTO A HOUSE.  PRELIMINARY EVALUATION OF THE ENGINE REVEALED NO ANOMALIES. MFG W	ILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006010500124	20060105	00124	NE  	2006	1	5	CA051104005      	2	20051007	G	7200		ENGINE          	PWC         	PT6A11      	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A11      	52043	NE  					ENGINE	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA						E10323					(CAN) IN FLIGHT, COMPRESSOR SPEED DECREASED UNCOMMANDED ACCOMPANIED BY AN INCREASE IN TURBINE TEMPERATURE.  THE ENGINE W	AS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS	 IN THE ENGINE OIL AND DIFFICULTY IN ROTATING THE COMPRESSOR SECTION.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT	 CAUSE ONCE ESTABLISHED.			1	L	7	2 	3T	3	T		A8EA    	E4EA				 
2006010500129	20060105	00129	NE  	2006	1	5	CA051104006      	2	20051023	G	7200	PW120	ENGINE          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					ENGINE	OVERHEATED      	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, ENGINE TEMPERATURE INCREASED ACCOMPANIED BY AN UNCOMMANDED DECREASE IN ENGINE TORQUE.  THE ENGINE WA	S SHUT DOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006010400130	20060104	00130	NE  	2006	1	4	CA051104007      	2	20051023	G	7200	PW305A	ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE FLAMED OUT DURING DESCENT.  A SUCCESSFUL IN-FLIGHT RE-LIGHT WAS ACCOMPLISHED.  MFG WILL INVESTIGATE THE	 EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006010400091	20060104	00091	CE  	2006	1	4	CA051104008      	1	20051007	G	5100		WASHER          			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	INTAKE TUBE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PARTIAL POWER LOSS IN-FLIGHT.  UPON INSPECTION, CONTRACT AMO FOUND A WASHER LODGED UNDER AN INTAKE AND EXHAUST VAL	VE, CAUSING ZERO COMPRESSION. ON DISASSEMBLY, SCREW FOUND IN SCAT HOSE LEADING FROM CARB HEAT INTAKE PORT TO HEAT MUFF. 	LIKELY SCREW AND WASHER VIBRATED LOOSE FROM COWLING AND/OR WINTER KIT FELL ONTO BAFFLE AND ROLLED INTO CARB HEAT INTAKE 	PORT. WASHER OBVIOUSLY PASSED THROUGH HEAT MUFF, AIRBOX, CARB INTAKE TUBE AND LODGED IN CYLINDER INFLIGHT. SCREW REMAINE	D IN SCAT TUBE. COUNTERMEASURE; SCREEN CARB HEAT INTAKE PORT.		1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006010400118	20060104	00118	EA  	2006	1	4	CA051104009      	2	20051024	G	7310		TUBE            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE FLAMED OUT IN FLIGHT RESULTING IN AN UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION R	EVEALED AN ENGINE FUEL DELIVERY TUBE LEAK.  THE ENGINE EXHAUST DUCT WAS ALSO FOUND CRACKED.					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2006010500132	20060105	00132	NE  	2006	1	5	CA051104010      	2	20051025	G	7261	PW123	ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  						LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAF	T DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A LARGE OIL LEAK NEAR THE PROP CONTROL UNIT AND INPUT 	DRIVE HOUSING.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006010500140	20060105	00140	NE  	2006	1	5	CA051104011      	2	20051022	G	7200	PW305B	ENGINE          			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305B      	52128	NE  						POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA											(CAN) DURING A TRAINING TOUCH-AND-GO MANEUVER, THE ENGINE ROLLED BACK IN POWER AND THE LOW OIL PRESSURE WARNING ANNUNCIA	TED.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND AN UNSCHEDULED LANDING CARRIED OUT.  MFG WILL INVESTIGATE THE INCIDENT AND 	ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2006010400093	20060104	00093	EA  	2006	1	4	CA051104012      	2	20051025	G	7200	PT6A65B	ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  		SHUTDOWN        	W				E				ENGINE SHUTDOWN         				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE WAS REPORTED TO EMIT A LOUD (BANG) FOLLOWED BY SEVERE VIBRATION.THE ENGINE WAS SHUTDOWN 	IN FLIGHT AND A SINGLE ENGINE LANDING ACCOMPLISHED.  MFG WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONC	E DETERMINED.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P44GL	 
2006010500142	20060105	00142	EA  	2006	1	5	CA051104013      	2	20051025	G	7200	PT6A34	ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK ON TAKE-OFF.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRC	RAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE COMPRESSOR AND ENGINE INLET AREA.  MF	G WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2006010400131	20060104	00131	CE  	2006	1	4	CA051104014      	1	20051028	G	7714	30B615004	SENSOR          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE RPM	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE FLAMEDOUT ON DESCENT FOLLOWING A COMMANDED REDUCTION TO IDLE POWER. AN IN-FLIGHT RE-LIGHT WAS SUCCESSFU	LLY CARRIED OUT.  THE ENGINE N1 SPEED SENSOR S WERE SUBSEQUENTLY REPLACED.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006010500148	20060105	00148	EA  	2006	1	5	CA051104015      	2	20051027	G	8520	50153813	STUD            	LYC         	IO360C1C    	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	CRANKCASE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA						L955551A					(CAN) 7 OF THE 8 STUDS ON NR 2 CYL BROKE ALLOWING THE CYL TO SHIFT CAUSING A VIBRATION.  5 MIN AFTER TAKEOFF THE PILOT N	OTED A VIBRATION AND RETURNED FOR A NORMAL LANDING. INSPECTION OF THE LOG BOOK IT WAS NOTED THAT NR2 CYL HAD BEEN REMOVE	D 375 HRS PRIOR BY THE PREVIOUS OWNER.				1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P25EA	 
2006010500152	20060105	00152	EA  	2006	1	5	CA051104016      	1	20051020	G	5101	4426X212	RADOME          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	FUSELAGE	BIRD STRIKE     	W				K				NONE                    				C			F.O.D.                    			DE	DESCENT        	1			CA			31466	31466							(CAN) DURING DESCENT, IMPACT WITH GOOSE. AIRCRAFT LANDED NORMALLY. MAINTENANCE FOUND RADOME BADLY DAMAGED AND ALSO DAMAG	E TO BULKHEAD AT STATION X-7.0.  RADOME ASSEMBLY REPLACED AND FACTORY REPAIR DRAWING CARRIED OUT TO REPAIR UPPER RT CORN	ER OF RADOME BULKHEAD AT STATION X-7.0				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006010500155	20060105	00155	EA  	2006	1	5	CA051104017      	1	20051020	G	5101	60012112	SKIN PANEL      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT WING	DAMAGED         	W				K				NONE                    				C			F.O.D.                    			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, AIRCRAFT HIT GOOSE.  AIRCRAFT LANDED NORMALLY. DAMAGE FOUND ON IB RT LE (DENT .7500 INCH DEEP 4.5 	INCH WIDE AND 8.5 INCH LONG).  MFG AUTHORIZED FERRY FLIGHT WITH THIS DAMAGE TO MAINTENANCE BASE.  MAINTENANCE REMOVED LE	ADING EDGE FOR INSPECTION. MAINTENANCE REPLACED DAMAGED SKIN PANEL , DAMAGED RIB BETWEEN WING STATIONS WS 50.54 - WS66.2	0 AND ALSO FOUND DENT ON WING PICCOLO (ANTI-ICE) TUBE. WING PICCOLO TUBE ALSO REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006010500158	20060105	00158	EU  	2006	1	5	CA051104018      	1	20051103	G	3233	AR03404	ACTUATOR        			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					LANDING GEAR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A MAIN LANDING GEAR ACTUATOR REPLACEMENT, THE NOSE LANDING GEAR WOULD NOT FREE FALL ON SYSTEM NR1 DURING TES	T PROCEDURE. SYSTEM WAS OK ON SYSTEM NR2. THE FREE FALL ACTUATOR ASSEMBLY WAS REPLACED AND SYSTEM FOUND SERVICEABLE. THE	 FREE FALL ACTUATOR WAS SENT TO THE REPAIR SHOP FOR A STRIP REPORT.				1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2006061900153	20060619	00153	EA  	2006	6	19	CA051104019      	2	20050803	G	7532		BLEED VALVE     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	STUCK           	W				E	B	A		ENGINE SHUTDOWN         	EMER. DESCENT           	UNSCHED LANDING         		E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											COMPRESSOR STALL CAUSED OSCILLATIONS IN AIRFRAME.  ENGINE POWER REDUCED TO IDLE.  A SINGLE ENGINE LANDING CARRIED OUT IN	 NEAR BY FIELD.  ENGINE REPLACED WITH SERVICEABLE UNIT.  IT WAS FOUND TO BE A STUCK CLOSED, BLEEDVALVE AND 3RD STAGE COM	PRESSOR BLADE DAMAGE.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006010500165	20060105	00165	EU  	2006	1	5	CA051107001      	1	20051106	G	6420		BUSHING         	UROCOP      	350A33214501	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						S5635					(CAN) UPON VISUAL INSPECTION, THERE WAS CORROSION FOUND ON THE INSIDE DIAMETER OF THE INNER STEEL BUSHING.  THE CORROSIO	N WAS REMOVED AND THE CRACKS WERE THEN VISIBLE.  THE CRACKS WERE FOUND RUNNING AXIALLY. THE PITCH LINK WAS REPAIRED IN 2	003, AND HAS 804.4 HOURS SINCE REPAIR.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006061900154	20060619	00154	CE  	2006	6	19	CA051107002      	1	20051104	G	3250	50820189	LINK            			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG STEERING SYS	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											ONCE LANDED , FLT CREW PROCEEDED TO STEER A/C OFF RUNWAY, WERE UNABLE.  BY APPLYING THE BRAKES AND DIFFERENTIAL ENGINE P	OWER SETTINGS, ABLE TO MANEUVER A/C OFF RUNWAY AND OVER TO MX HANGAR.  MX PERSONNEL FOUND STEERING LINK SEVERED IN HALF 	APPROX MID SPAN AND HANGING DOWN.  UPON FURTHER INVESTIGATION, FOUND STEERING BUNGEE (P/N 50-820034-3) WAS JAMMED NOT AL	LOWING SPRING TO COMPRESS IN ONE DIRECTION.  THIS JAMMED BUNGEE CAUSED STEERING LINK TO BREAK ONCE STEERING PRESSURE WAS	 APPLIED TO RUDDER PEDALS.  WHEN  MX PERSONNEL DISASSEMBLED THE BUNGEE MECHANISM, FOUND THREE LARGE INTERNAL WASHERS BEN	T OVER AND CRUMPLED WITHIN MECHANISM.  THE REASON FOR THIS TYPE OF FAILURE IS UNKNOWN.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006010500174	20060105	00174	NM  	2006	1	5	CA051107003      	1	20051107	G	5711	85713502	SPAR            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REPLACEMENT OF LT WING IB LEADING EDGE, AN APPROX 12-INCH CRACK IN LOWER SPAR FLANGE WAS DISCLOSED. THE CRA	CKED SPAR FLANGE PIECE FOLLOWED THE LEADING EDGE DURING REMOVAL. LOCATION, YW 136.30 TO YW 157.875. THE CRACKED SPAR FLA	NGE PIECE IS BEING RETURNED TO MFG FOR EVALUATION.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006061900155	20060619	00155	CE  	2006	6	19	CA051107004      	1	20051101	G	2424	EA85098	RESISTOR        	BENDIX      		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	VOLT REGULATOR	OPEN            	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA						R52253					LT GEN FAIL ANNUNCIATOR LIGHT ILLUMINATED IN CRUISE.  ATTEMPED RESET BY SWITCHING LT GEN OFF, WAITED 10 SECONDS, THEN SW	ITCHED BACK ON.  RESULT WAS BRIEF SMALL PUFF OF SMOKE FROM INSTRUMENT PANEL, SUBSEQUENTLY FOUND TO BE BURN OF GPS ANNUNC	IATOR BRT/DIM/TEST MODULE P/N 3423-P14 C/B, THEN PILOT SIDE ALT C/B TRIPPED.  ATC WAS ADVISED AND IMMEDIATE RETURN TO AE	RODROME OF DEPARTURE REQUESTED.  LANDED WITHOUT FURTHER INCIDENT.  AMO INVESTIGATION REVEALED LT GENERATOR HAD FAILED DU	E TO AN OPEN CIRCUIT RESISTOR IN THE VOLTAGE REGULATOR, AND THAT RESETTING CAUSED A VOLTAGE SPIKE WHICH BURNED OUT GPS M	ODULE C/B DESCRIBED ABOVE, AND ALSO DAMAGED ALT SELECTOR P/N 065-0053-00 AND TRIPPED PILOT SIDE ALT C/B.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2006010500175	20060105	00175	NE  	2006	1	5	CA051108001      	2	20051105	G	7261		SHAFT           	ROMEC       	LR37940J    	AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					OIL PUMP	SHEARED         	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			14037			B779					(CAN) DURING NORMAL ENGINE START AFTER PUSHBACK, NR 1 ENGINE ECAM WARNING INDICATED, LOW OIL PRESSURE. CREW ABORTED ENGI	NE START.  T/S CARRIED OUT, FOUND NR 1 ENGINE OIL PUMP ASSY INPUT SHAFT SHEARED.  PUMP WAS REPLACED AND AIRCRAFT WAS RET	URNED TO SERVICE. A/C HAD BEEN PARKED FOR APPROX. 36 HOURS. TEMPERATURE AT DEPARTURE WAS 2 DEG C.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2006061900156	20060619	00156	GL  	2006	6	19	CA051108002      	1	20051108	G	7160	AN334	BOLT            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	AIR BOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			190  								INDUCTION AIR BOX SUPPORT MOUNTING BOLT (AN3-34 BOLT) IS WORN PREMATURELY BY SUPPORT BRACKET 15671-002.  THE SAME BOLT A	LSO IS WEARING AT CONTACT AREA FROM ALTERNATE AIR DOOR SUPPORT BEARING P/N 50200-101.  THIS BOLT SUPPORTS THE INDUCTION 	AIR BOX ONTO THE CRANKCASE AND ACTS AS THE HINGE FOR THE ALTERNATE INDUCTION AIR DOOR.  TO INSPECT THIS DAMAGE, THE AIR 	BOX HAS TO BE REMOVED AND DISASSEMBLE.			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2006061900158	20060619	00158	GL  	2006	6	19	CA051108003      	1	20051104	G	7810	51381001	SPRING          			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	EXHAUST PIPE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			105  								DURING FIRST 100 HOUR INSPECTION, FOUND LEFT EXHAUST TAIL PIPE SUPPORT SPRING END LOOP WORN ABOUT 80 PERCENT AT CONTACT 	AREA TO MOUNTING BRACKET.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2006010500176	20060105	00176	EA  	2006	1	5	CA051108004      	1	20051104	G	3411	PH506L	PITOT HEAD      			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PITOT/STATIC SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			37908								(CAN) THE CAPTAIN REPORTED A 10 - 15 KTS SPLIT ON AIRSPEED INDICATIONS BETWEEN PILOT-F/O INDICATORS.  MAINTENANCE INVEST	IGATION REVEALED THAT THE CAPTAINS (LT) PITOT HEAD WAS RESTRICTED SLIGHTLY. FURTHER INVESTIGATION REVEALED THAT THE AIR 	TUBE HAD BEGUN TO EXFOLIATE INTERNALLY AT THE 90 DEGREE BEND IN THE PITOT HEAD.  THE HEAD WAS REPLACED AND THE AIRCRAFT 	WAS RETURNED TO SERVICE. THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT.			1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006061900159	20060619	00159	SO  	2006	6	19	CA051108005      	1	20051107	G	3211	4028600	FITTING         			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											PART NUMBER 43286-02 (2 OF) WERE REMOVED FROM STOCK FOR INSTALLATION ON PA42-720 AS REQUIRED BY A/C MX SCHEDULE REPLACEM	ENT INTERVAL.  CLOSE INSPECTION PRIOR TO INSTALLATION REVEALED BOTH FITTINGS (PART NUMBER 40286-00) WERE CRACKED WHERE T	HEY MATE WITH THE PIVOT SHAFT.  BOTH UNITS IDENTIFIED AS UNSERVICEABLE AND WILL BE RETURNED TO THE MANUFACTURER.				1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2006010500177	20060105	00177	SO  	2006	1	5	CA051108008      	2	20050915	G	7313		INJECTOR        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	NR 5	CONTAMINATED    	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) FULL POWER NOT AVAILABLE FOR TAKEOFF.  STATIC RPM 150 RPM LOW.   ENGINE SLIGHTLY ROUGH.  REMOVED INJECTORS AND FOU	ND UNIDENTIFIED PARTICLE IN NR5 INJECTOR.   REMOVED PARTICLE AND ENGINE RAN NORMALLY.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006010400113	20060104	00113	CE  	2006	1	4	CA051108010      	1	20051028	G	3297	S13605	CIRCUIT BREAKER 			CESSNA	337   	337C        	2075712	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C307  	GL  	MLG	ARCED           	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH FLIGHT, PILOT SELECTED LANDING GEAR DOWN.  LANDING GEAR CONTROL CIRCUIT BREAKER POPPED AND WOULD N	OT RESET.  PILOT WAS INSTRUCTED TO CARRY OUT AN EMERGENCY GEAR EXTENSION AND FOLLOW LANDING PROCEDURES IN PILOT'S OPERAT	ING HANDBOOK.  UPON INVESTIGATION, THE CONNECTION TO LANDING GEAR C/B WAS LOOSE AND ARCHING.  THE CONNECTION WAS CLEARED	 AND SECURED.  NO OTHER FAULTS WERE FOUND. SUBSEQUENT GEAR SWING AND TEST FLIGHT C/O.  SERVICEABLE.			1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2006061900161	20060619	00161	GL  	2006	6	19	CA051109001      	2	20051029	G	7230		COMPRESSOR      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2706 				CAC34068			FOLLOWING A REPORT OF HIGHER THAN NORMAL TOT ON NR 2 ENGINE A POWER CHECK WAS CONDUCTED AND TROUBLESHOOTING LED TO SPLIT	TING THE COMPRESSOR FOR INSPECTION.  SUBSTANTIAL DAMAGE WAS FOUND ON THE 5TH AND 6TH ROW STATOR VANES AND 6TH STAGE ROTO	R BLADES.  NO DAMAGE WAS EVIDENT FORWARD OF THE FIFTH COMPRESSOR STAGE.  TWO STATOR BLADES WERE MISSING LEADING THE OPER	ATOR TO BELIEVE THAT A BLADE SEPARATION HAD CAUSED THE DAMAGE.			1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006061900162	20060619	00162	CE  	2006	6	19	CA051109002      	1	20051107	G	5313		STRINGER        			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	NR 10	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8030 								DURING AN INSPECTION OF THE ELEVATOR CABLES, AFT OF THE REAR PRESSURE BULKHEAD, THE ENGINEER DISCOVERED A CRACK IN THE N	R 10 STRINGER OF THE AFT PRESSURE BULKHEAD.  THIS AIRCRAFT HAS A CVR INSTALLED IAW STC 'SA-02-26' AND THE MOUNTING TRAY 	FOR THE CVR TIES INTO THE NR 10 STRINGER.  THE CRACK IS APPROX 2" LONG AND LOCATED ON THE LT OUTBOARD SIDE.				1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2006010400120	20060104	00120	SW  	2006	1	4	CA051109003      	1	20051107	G	2820	222366687101	CHECK VALVE     			BELL  	430   	430         	1182150	SW  										FUEL SYSTEM	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WE HAVE RECEIVED A REPORT CONCERNING A PROBLEM WITH THE FUEL SYSTEM.   THE FUEL CHECK VALVE P/N: 222-366-687-101 W	AS FOUND COMING APART.  THEY FOUND THAT THE NUT HAD COME OFF OF THE POPPET ASSEMBLY AND CONTAMINATING THE FUEL FILTER, T	HE FUEL PUMP AND THE HMU.				1	G	7	2 	3U			RT	H9SW    					 
2006010500179	20060105	00179	GL  	2006	1	5	CA051109005      	1	20051031	G	5101		LEAD            			NAMER 	T6    	HARVARD4    	6400430	GL  	PWA   	R1340 	S3H1        	52016	NE  	HAMSTD	12D	12D40       	NE  		UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT TTSN 5412.7 HOURS.  AD CF-2005-10 C/W SEPT 12/05. NO FAULT FOUND.						1	L	7	1 	3R	3	R		EXPA1L71	E143	5	C	P257	 
2006062700026	20060627	00026	CE  	2006	6	27	CA051109006      	1	20051011	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA				2454 							DURING CLIMB-OUT, THE PILOT NOTICED THAT SUDDENLY THE INNER PLY OF THE CAPTAINS HEATED WINDSHIELD SHATTERED.  THERE WAS 	NO INDICATION OF IMPACT, OR ANY OTHER APPARENT REASON, THAT MAY HAVE CAUSED THIS.  THE AIRCRAFT RETURNED TO THE DEPARTUR	E AERODROME WITHOUT FURTHER INCIDENT WHERE MAINTENANCE PERSONNEL INSPECTED THE WINDSHIELD.  A FERRY PERMIT WAS OBTAINED 	TO FERRY THE AEROPLANE TO THE COMPANY'S MAINTENANCE BASE WHERE THE WINDSHIELD WAS REPLACED.  DURING THE REPLACEMENT PROC	ESS NOTHING WAS FOUND THAT MAY HAVE EXPLAINED WHY THE WINDSHIELD SHATTERED IN THE FIRST PLACE.		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE	 
2006020200169	20060202	00169	NE  	2006	2	2	CA051109007      	2	20051107	G	7200	PT6A36	ENGINE          			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING	FLUCTUATES      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) INFLIGHT SHUTDOWN FROM TORQUE FLUCTUATIONS INDICATED IN CONJUNCTION WITH OIL PRESSURE FLUCTUATIONS. NO CHIP DETECT	ER LIGHT, NO OIL PRESSURE LIGHT.  ENGINE SECURED BEFORE LOSS OF OIL PRESSURE MAINTENANCE CHECKED CHIP DETECTER, CLEAN.  	MAINTENANCE CHECKED MAIN OIL SCREEN, METAL (FUZZ), NONE MAGNETIC.  ENGINE REMOVED FROM A/C FOR FURTHER INVESTIGATION.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006020300116	20060203	00116	EU  	2006	2	3	CA051110001      	1	20051108	G	3250	503028533	CABLE           			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					NLG	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE NLG SERVICING THE FRAYED CABLE WAS NOTICED BETWEEN 2 PULLEYS.  ONLY A FEW STRANDS REMAINED INTACT A	ND THE PROBLEM HAS BEEN THERE FOR QUITE SOMETIME IAW THE PART CONDITION.  THE CREW HAD REPORTED THAT THE PLANE HAD A SLI	GHT TENDANCY TO GO TO THE LT ON LANDING AND THOUGHT IT MAY HAVE BEEN TIRE PRESSURE RELATED.  TT ON CABLE UNKNOWN.				2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2006020300117	20060203	00117	NE  	2006	2	3	CA051110002      	2	20051110	G	7220	JT8D15AQM	ENGINE          			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TOP AFT FUSELAGE	SURGES          	W				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			CA			39801								(CAN) AIRCRAFT EXPERIENCED NR 2 ENGINE SURGE DURING TAKEOFF ROLL. SEVERE CROSSWINDS WERE EXPERIENCED WHICH WILL CAUSE TH	IS ENGINE SURGE.  DUE TO THE CROSSWINDS AND THEN INTERRUPTION OR DISTURBANCE OF AIRFLOW THRU THE AIR INTAKE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006020300118	20060203	00118	EA  	2006	2	3	CA051110003      	1	20051110	G	3246	F343240	LUG             			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540D4A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	LT FUSELAGE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK-AROUND, LT REAR FLOAT FLY-WIRE WAS FOUND LOOSE. FURTHER INSPECTION REVEALED THE LT, AFT FLY-WIRE ATTAC	H LUG HAD FAILED APPROX 1/4 INCH FROM THE REAR FUSELAGE ATTACH POINT. REMAINING 3 FLY-WIRE ATTACH LUGS INSPECTED, NO FAU	LT FOUND. BROKEN SECTION OF THE LUG WAS INSPECTED, FAILURE APPEARED TO HAVE STARTED AT THE LUG TO FUSELAGE WELD.				1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA	 
2006022300041	20060223	00041	NE  	2006	2	23	CA051111001      	2	20051111	G	7230		ENGINE          			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					NR 2	BIRD INGESTION  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								41192			(CAN) EVIDENCE OF BIRD STRIKE AT FAN BLADES. NO SIGNS OF BIRD REMAINS OR DAMAGE ON CORE OF ENG FAN BLADES, LP/IP SPLITTE	R FAIRING, OGV'S AOHE AIR INLET IDG OIL COOLER INLET INSPECTED. (A) DUE TO ENG SURGE OUT OF AIRPORT ON 01/09/2005. BOROS	COPE INSPECTION CARRIED OUT IAW MM 71-00-00-200-808.  SOME DAMAGED BLADES FOUND AT HP COMPRESSOR STAGE 3 TIP CURL, BENDS	 AND TEAR.   COMPRESSOR SURGE MARGIN TEST CARRIED OUT. NR2 ENG STALL FOLLOWED BY ENG 2 FAIL. POWER BEING ADVANCED FROM 1	.03 EPR AT 1.05 EPR. ENG INSPECTED WITH NO FAULT FOUND IAW AMM 71-00-00-200-808, ENG RUN CARRIED OUT WITH NIL FAULT: ON 	TAXI IN, ENG ANTI ICE SELECTED OFF, ENG 2 FAILED, THRUST AT IDLE. NR 2 ENG REPLACED IAW J/C 9-371A.	1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2006020300120	20060203	00120		2006	2	3	CA051111002      	4	20051111	G	2310	6225272001	RADIO           			BOEING	767   	767383      	1385214	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					HF RADIOS	INTERMITTENT    	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FAULT: WHEN ATTEMPTING TO TUNE NR 1 HF (LT) STRONG ACRID ODOR/HEATING SMELL RT HF INTERMITTENT FOR TRANSMITTING BO	TH HF'S SELECTED OFF C/B'S FOR BOTH HF'S PULLED SMELL DISSIPATED FLT OP ADVISED ACTION:  LT HF T/R REPLACED IAW AMM 23-1	1-03-406 RT HF T/R REPLACED IAW AMM23-11-03-406				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006020300121	20060203	00121	SO  	2006	2	3	CA051111003      	2	20051111	G	8530	TIST760CA	CYLINDER        	CONT        	IO550F      	CESSNA	207   	207         	2073602	CE  	CONT  	O550  	IO550F      	17042	SO  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA						284933R					(CAN) CYLINDER NR 4 HAD LARGE CRACK ACROSS CYLINDER, BELOW TOP SPARK PLUG HOLE. A CYLINDER DIFFERENTIAL CHECK CONFIRMED 	CYLINDERS 2, 6, AND 3 TO HAVE CRACKS IN THE SAME GENERAL LOCATION.  ALL 6 CYLINDER ASSEMBLIES WHERE REMOVED.  6 NEW CYLI	NDER ASSEMBLIES P/N 655471A4.  NOTE: THIS MAKES 16 I0-520 AND I0-550 CYLINDER ASSEMBLIES REPLACED DUE TO THE SAME PROBLE	M SINCE MAY 2005 ON A FLEET OF 6 AC OPERATED BY 2 INDEPENDENT COMPANYS.			1	H	7	1 	3O	3	O		A16CE   	E3SO				 
2006020300122	20060203	00122	EA  	2006	2	3	CA051112001      	1	20051111	G	5610	601R3303311	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CAPT SIDE WINDOW	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAINS SIDE WINDOW CRACKED, WINDOW REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006020300123	20060203	00123	EA  	2006	2	3	CA051112002      	1	20051102	G	7830		THRUST REVERSER 	GE          		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	BROKEN          	W				O				OTHER                   				D	Y		INFLIGHT SEPARATION       	ENGINE STOPPAGE           		AP	APPROACH       	1			CA						GEE873650					(CAN) AC WAS BEING FERRIED SOUTH TO BASE WITH MISSING BLOCKER DOOR, WITH T/R BEING DEFERRED IAW MEL IN ORDER TO BE REPAI	RED, DIDN'T HAVE BLOCKER DOOR IN STOCK. ON ITS WAY TO DESTINATION, CREW HEARD A LOUD BANG DURING DESCENT, RT ENGINE FLAM	ED OUT ON ITS OWN.  CREW RAN QRH PROCEDURES FOR SINGLE ENGINE LANDING AND LANDED AT DESTINATION W/O ANY INCIDENT. IN BAS	E HANGAR, FIRST LOOK AT THIS ENGINE SHOWED THAT THERE WERE AT LEAST 1 OR 2 STAGE 2 GUIDE VANES, LEVER ARMS THAT GOT LOOS	E OR DISCONNECTED FROM ACTUATING RING AND THEN GOT SWALLOWED BY ENGINE, ALONG WITH VANES. FURTHER INSP ALSO REVEALED THA	T STAGE 9 WAS COMPLETELY GONE. ENGINE WAS REMOVED AND REPLACED, AC IS BACK IN SERVICE. (SEE ALSO: US #2005110900025)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006020300124	20060203	00124	NM  	2006	2	3	CA051114001      	1	20051112	G	2742	03994001011	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PITCH TRIM ACTOR	UNKNOWN         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, PITCH TRIM CAUTION LIGHT, AUTO TRIM FAIL MESSAGE ILLUMINATED.  PITCH TRIM INDICATOR SHOWED FULL NOSE	 UP POSITION. FLIGHT CREW ELECTED TO RETURN TO DEPARTURE AIRPORT.  MAINTENANCE: FCECU PRESENT FAULTS FOUND 63, 67, E3, A	ND E7.  RESET FCECU CIRCUIT BREAKERS THEN THE CAUTION LIGHT CLEARED AND OPERATION CHECK NORMAL. REPLACED PITCH TRIM ACTU	ATOR AS PRECAUTION.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006020300125	20060203	00125		2006	2	3	CA051114002      	4	20051101	G	6113		PLATE           	HARTZL      		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	PROP BACK PLATE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						HU132					(CAN) PART INSTALLED DEC 03, FOUND CRACKED AT REMOVAL FOR ENGINE CHANGE.						1	H	7	1 	3R	3	R		A806    	5E1	5	C	P28EA	 
2006020300129	20060203	00129	SO  	2006	2	3	CA051114003      	1	20051128	G	5280	46357000	CHANNEL         	PIPER       	4752933     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	IO540M1A5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	WING	CRACKED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE A CRACK WAS NOTICED EXTENDING FROM THE BOLT HOLE. THIS IS THE BRACKET THAT IS RIVETED T	O THE WING AND THE DOOR ACTUATOR ATTACH POINT.  SUSPECT THAT THE FLAW WAS A RESULT OF THE DOOR BEING RIGGED TOO TIGHT FO	R SOMETIME. THE BRACKET HAD A PATCH FROM A PREVIOUS REPAIR. TT ON PART APPEARS TO BE 6465 HOURS.				1	L	7	2 	3O	3	O		A20SO   	1E4	5	C	P9EA	 
2006062700027	20060627	00027	SO  	2006	6	27	CA051114004      	1	20051114	G	5280	46357000	BRACKET         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	IO540M1A5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6465 								PREVIOUSLY REPAIRED BRACKET DISCOVERED CRACKED AT BOLT HOLE.  THIS PART IS RIVETED TO THE TOP OF THE WING IN THE WHEEL W	ELL.  SUSPECTED CAUSE OF THE DEFECT IS TOO MUCH STRAIN ON THE PART OVER TIME DUE TO AN IMPROPERLY RIGGED LANDING GEAR DO	OR ACTUATOR.				1	L	7	2 	3O	3	O		A20SO   	1E4	5	C	P9EA	 
2006020300130	20060203	00130	CE  	2006	2	3	CA051114005      	1	20051113	G	8011		DRIVE GEAR      		MZ6222      	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						E043495					(CAN) STARTER DRIVE GEAR FAILED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006020300131	20060203	00131	EU  	2006	2	3	CA051114006      	1	20051109	G	2742	065001640100	ADAPTER         	BENDIX      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITCH TRIM ADAPT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						ADAPTER1277					(CAN) RED (PITCH TRIM) ANNUNCIATOR WOULD ILLUMINATE INTERMITTENTLY WHEN DESCENT COMMANDED. THIS WOULD SOMETIMES OCCUR AS	 THE AUTO PILOT WOULD ATTEMPT TO TRIM. AUTO PILOT WOULD NOT DISENGAGE. PITCH TRIM ADAPTER REPLACED 31.4 HRS PREVIOUS DUE	 TO A DIFFERENT DEFECT. ANOTHER TRIM ADAPTER WAS INSTALLED, PROBLEM RECTIFIED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062200092	20060622	00092	CE  	2006	6	22	CA051114007      	1	20051019	G	3233	9981004311	LINK            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER SELECTION OF GEAR UP ON DEPART, GEAR STOPPED PART WAY THROUGH ITS TRAVEL AND HAD TO BE EXTENDED BY MEANS OF ALT EX	TENSION SYSTEM.  A/C LANDED UNEVENTFUL WITH 3 GREEN, DOWN AND LOCKED.  INSPECTION OF A/C INITIALLY INDICATED A BROKEN LT	 INBOARD MAIN GEAR DOOR SWIVEL LINK.  THE GEAR CONTROL C/B WAS ALSO TRIPPED.  AFTER RESETTING BREAKER, GEAR WAS CYCLED F	OR INVESTIGATION AND IT WAS NOTED THAT LEFT MAIN GEAR ACT EXHIBITED AN ABNORMAL NOISE DURING CYCLE AND APPEARED SLOWER. 	 ACTUATOR REMOVED FOR INSPECTION AND FOUND TO HAVE AN AREA OF TRAVEL WHICH WAS ROUGH AND STIFF TO EXTEND AND RETRACT WHE	N ROTATED BY HAND.  ACTUATOR WAS REPLACED ALONG WITH THE SWIVEL LINK AND GEAR DOOR BRACKETS.  ALL GEAR DOOR LINKAGES WER	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006020300132	20060203	00132	NM  	2006	2	3	CA051115001      	1	20051109	G	2910	DSC252B40124	FLEX LINE       			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG ACTUATOR	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			30628								(CAN) CREW REPORTED NR 2 HYDRAULIC (HYD ISOL VALVE) ILLUMINATED IN CRUISE.  AIRCRAFT RETURNED TO BASE. ON ARRIVAL, MAINT	ENANCE DISCOVERED A FLUID TRAIL AFT FROM THE NOSE LANDING GEAR WHEEL WELL.  FURTHER INVESTIGATION DETERMINED THAT ONE OF	 THE NOSE LANDING GEAR ACTUATOR FLEXIBLE HYDRAULIC LINES HAD RUPTURED.  THE LINE WAS REMOVED AND A SERVICEABLE LINE WAS 	FITTED AND TESTED IAW THE APPLICABLE AIRCRAFT MM. THE AIRCRAFT WAS RETURNED TO SERVICE.  THIS ISSUE IS RELATED TO SERVIC	E DIFFICULTY ALERT AL-2003-11.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006020300133	20060203	00133	CE  	2006	2	3	CA051115002      	1	20051107	G	8011	643259A18	CLUTCH          	CONT        	IO520L13B   	CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	STARTER	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						29374					(CAN) WHILE ATTEMPTING FIRST START OF DAY, PROP ROTATED THEN STOPPED.  ON SUBSEQUENT ATTEMPTS THE PROPELLOR FAILED TO RO	TATE.  IT WAS DETERMINED THAT THE STARTER ADAPTER CLUTCH FAILED.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2006020300134	20060203	00134	NM  	2006	2	3	CA051115003      	1	20051114	G	6120	699018002	ECU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROP ECU	OVERSPEED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AN AIRCRAFT EXPERIENCED A NR1 ENGINE OVERSPEED NP, COMMANDED INFLIGHT SHUTDOWN.  ENGINE OVERSPEED NP IN FLIGHT (FA	ULT CODE 161) FOUND. PROPELLER ELECTRONIC CONTROL UNIT REPLACED. AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006061900282	20060619	00282	EU  	2006	6	19	CA051115004      	1	20050701	G	6210	355A11002009	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING A BFF INSPECTION, A LARGE CHORDWISE CRACK (130MM LONG) WAS DISCOVERED ON THE UPPER SURFACE OF A M/R BLADE APPROX 	1150MM FROM BLADE ROOT (AREA C).  A/C WAS GROUNDED AND REPLACEMENT BLADE WAS ORDERED.					1	G	7	1 	3U				H9EU    					 
2006020300135	20060203	00135	WP  	2006	2	3	CA051115007      	2	20051113	G	7200		ENGINE          			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	RT WING	UNKNOWN         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN) RT ENG DID AN UNCOMMANDED INFLIGHT SHUTDOWN.  TROUBLESHOOTING IN PROGRESS . WILL UPDATE FURTHER .						2	H	7	2 	4T	3	T	RT	A16EU   	E2WE	6	C	P40EA	 
2006020300136	20060203	00136	NM  	2006	2	3	CA051116001      	1	20051116	G	3297		HARNESS         	BFGOODRICH  		BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	INOPERATIVE     	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						339730002					(CAN) AFTER TAKEOFF, THE LANDING GEAR DID NOT RETRACT AFTER GEAR UP SELECTION, AIRCRAFT RETURNED TO BASE AND MADE A NORM	AL LANDING.  A CHECK OF THE PSEU SHOWED THAT THE PROX SENSOR FOR NWCENT WAS INDICATING DASHES. HARNESS ASSY (P/N: 47151-	5) REPLACED IAW AMM 32-61-00. AIRCRAFT RTS.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006020300137	20060203	00137	NM  	2006	2	3	CA051116002      	1	20051101	G	2916	3811208102	RELIEF VALVE    	VICKERS     	3810040103  	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD RESERVOIR	STICKING        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						0027					(CAN) HYDRAULIC QUANTITY NR 1 READ ZERO. OVERFOW CAN FULL. THIRD REOCCURANCE.  FOUND RESERVOIR LOW PRESSURE RELIEF VALVE	 STICKING OPEN WHEN RELIEF. ABLE TO DUPLICATE BY TRANSFERRING HYDRAULIC FLUID FROM SYSTEM 2 TO SYSTEM 1 WITH BRAKE AND P	ARK BRAKE. RESERVOIR EMPTIED IN LESS THAN 5 SEC. HYDRAULIC RESERVOIR REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062200094	20060622	00094	CE  	2006	6	22	CA051116003      	1	20051113	G	3010	SMR504108	BOOT            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	DE-ICE SYS	TORN            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			76   								IN CRUISE FLIGHT, A THUMPING NOISE WAS DETECTED ON THE RIGHT SIDE OF AIRCRAFT.  AFTER LANDING IT WAS FOUND THAT A NEWLY 	INSTALLED RIGHT INBOARD WING BOOT LOWER HALF HAD TORE LOOSE FROM THE GLUE, AND WAS TRAILING BEHIND THE AIRCRAFT ABOUT 8 	FEET HITTING THE LOWER PORTION OF THE WING AND THE RIGHT SIDE OF THE BAGGAGE POD.  IT APPEARS THE GLUE UNDER THE BOOT DI	D NOT HOLD, MAY BE DUE TO THE GLUE FREEZING DURING SHIPPING.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006062200095	20060622	00095	SO  	2006	6	22	CA051116004      	1	20051103	G	3220	21890	ARM             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					NLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											DURING FLIGHT TRAINING, GEAR RETRACTION CAUSED UNUSUAL NOISE AND GEAR FAILED TO RETRACT.  ON SELECTING GEAR DOWN, 3 GREE	N LIGHTS WERE NOTED BUT VISUAL INSPECTION OF NOSE GEAR IN MIRROR SHOWED NOSE WHEEL RANTED 5-10" TO LEFT.  A LANDING AT A	IRPORT WAS CARRIED OUT WITH LANDING NORMAL BUT GROUND STEERING WAS NOT NORMAL.  THE AIRCRAFT WAS TAXIED TO A HANGAR RAMP	 WHEN  INSPECTION REVEALED THE STEERING ARM ON TOP OF NOSE STRUT WAS DISLOCATED DUE TO ATTACHMENT BOLTS BEING SHEARED OF	F.  THIS WAS PROBABLY CAUSED BY NOSE GEAR STEERING LIMITS BEING EXCEEDED BY GROUND TOWING OPERATIONS.		1	L	7	2 	3O	3	O		A1EA    	1E12				 
2006020300128	20060203	00128	SO  	2006	2	3	CA051116006      	2	20051014	G	7321	6297032	FCU             	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						828227R					(CAN) ON THE INSPECTION THE FUEL CONTROL ASSY WAS FOUND LEAKING.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2006020300138	20060203	00138	EA  	2006	2	3	CA051116007      	1	20051106	G	2916	C6HF10571	RESERVOIR       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FILLER NECK	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLUID WAS DRIPPING FROM THE HYD AREA.OPON INSPECTION IT WAS NOTICED THAT THE TANK WAS CRACKED ALONG THE FILLER NEC	K.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006022200074	20060222	00074	EA  	2006	2	22	CA051116008      	2	20051031	G	7200	3031200	ENGINE          			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 3	FAILED          	W				E				ENGINE SHUTDOWN         				E	E		VIBRATION/BUFFET          	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA			11569					PS86585			(CAN) ON OCTOBER 31, 05, THE PILOTS WHEN APPROACHING, WERE TOLD TO RETURN TO DEPARTURE, BECAUSE THE AIRPORT WAS CLOSED. 	UPON LANDING AFTER SLOWING THE AIRCRAFT, THE PILOT TRIED TO BRING THE POWER LEVERS TO FLT IDLE, BUT THE NR 3 ENGINE WOUL	D NOT MOVE.  MAINTENANCE WAS CALLED TO INSPECT THE CAUSE OF POWER LEVER ON NR 3 ENGINE JAMMED. IT WAS CONFIRMED BY THE A	ME THAT THE POWER LEVER CONNECTION ON THE ENGINE WAS JAMMED, AND THE ENGINE NEEDS TO BE REPLACED.  THE AIRCRAFT INSPECTE	D IAW FERRY FLIGHT PERMIT AUTHORIZATION PROCEDURES, AND AIRCRAFT FLIGH T MANUAL PROCEDURES.		2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006020300139	20060203	00139	NE  	2006	2	3	CA051116009      	2	20051111	G	7200	TRENT772B60	ENGINE          	RROYCE      		AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					LT WING	SHUTDOWN        	W				D				RETURN TO BLOCK         				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		TO	TAKEOFF        	1			CA						41228					(CAN) AFTER APPLYING TO POWER AND STARTING TO ROLL (APPROX 35KTS), NR 1 ENGINE SHUTDOWN WITH RELATED ECAM MESSAGE ENGINE	 FAIL . AIRCRAFT CAME BACK TO THE GATE. THERE WAS NO OBVIOUS DAMAGE TO THE ENGINE INTAKE AND EXHAUST. THE EEC WAS INTERR	OGATED AND MCDU AND REPORTED NO FAULT. ATTEMPTED ENGINE RUN BUT ENGINE NEVER REACHES IDLE. DURING START CYCLE IT RAPIDLY	 WENT FROM 7 PERCENT TO 63 PERCENT (APPROX 2 SEC.) WITH ECAM MESSAGE ENG CONT. FAULT AND ENGINE SHUTDOWN PROCEDURES. PER	SONNEL ON GROUND REPORTED A BIG OIL LEAK FROM ENGINE COWLING AND C DUCT AREA. TROUBLESHOOTING INSPECTION REVEALED METAL 	PARTICLES IN OIL FILTER AND MCD. ENGINE WAS REPLACED.	2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2006020300140	20060203	00140	EU  	2006	2	3	CA051116010      	1	20051114	G	2750	952D1005	PDU             	PILATS      	952D1005    	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FLAP SYSTEM	DEFECTIVE       	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA						188					(CAN) FLAP PDU FOUND U/S NEW PDU INSTALLED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062100181	20060621	00181	SO  	2006	6	21	CA051116011      	1	20051103	G	3230	40336000	LINK ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ACTUATOR ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9062 								WHEN CARRYING OUT SL1088 CRACKS WERE FOUND AT THE ACTUATOR LUGS ON THE LINK ASSY.  IAW SERVICE LETTER.  NEW LINK ASSY IN	STALLED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062100184	20060621	00184	SO  	2006	6	21	CA051116012      	1	20051110	G	3231	40336000	LINK ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17680								THE ACTUATOR ATTACH LUGS ON THE LINK ASSY WERE FOUND TO BE CRACKED IAW THE SERVICE LETTER.  NEW LINK ASSY INSTALLED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062200096	20060622	00096	NE  	2006	6	22	CA051116013      	2	20051114	G	7320	0164548660R	FUEL CONTROL    			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA			2396 	25   				4266			DURING FINAL STAGE OF RECON OF CONFINED AREA, THE ROTOR OVERSPEED (POSSIBLE ENGINE OVER SPEED) MORE THAN 450 RPM, NEEDLE	 PEGGED AT MAX READING.  EMERGENCY PROCEDURES WERE CARRIED OUT THROUGH RAISING COLLECTIVE AND THROTTLE RETARDING BUT THE	SE ATTEMPTS WERE NOT SUCCESSFUL.  AIRCRAFT SETTLED IN TO 60 FT POPLAR TREES, AIRCRAFT WAS SUBSTANTIALLY DAMAGED WITH NO 	PERSONAL INJURIES.  ACCIDENT IS CURRENTLY UNDER TSB INVESTIGATION AND THIS SDR IS CONSIDERED OPEN PENDING SYSTEM, COMPON	ENT TESTING AND TSB FINDINGS.  HOWEVER, THE FCU IS SUSPECT AT THIS POINT IN TIME.		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006020300141	20060203	00141	EA  	2006	2	3	CA051117001      	1	20051115	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COPLT WINDSHIELD	CRACKED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) AT 33000 FT DURING DESCENT, THE COPILOT'S WINDSHIELD SHATTERED.  THE LANDING WAS UNEVENTFUL.  MAINTENANCE WAS DISP	ATCHED TO REPLACE THE WINDSHIELD AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006020300142	20060203	00142	EU  	2006	2	3	CA051117003      	1	20051115	G	5347	TAAI233PE01	SEAT            			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					CAPT SEAT ASSY	UNSECURE        	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CAPTAIN SEAT WILL NOT LOCK INTO PLACE.						2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2006070500141	20060705	00141	WP  	2006	7	5	CA051117004      	1	20051117	G	7921	369D2562611	MOUNT BRACKET   			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					OIL COOLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED 300 HOUR AIRFRAME INSPECTION, A CRACK WAS FOUND IN THE COOLING FAN MOUNT.  PART WAS REMOVED AND N	EW PART WAS ORDERED ON MHI PO NR 204119. UNSERVICEABLE PART IS AVAILABLE IF REQUIRED. (TC 20051117004)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006070500142	20060705	00142	EU  	2006	7	5	CA051117005      	1	20051117	G	2741	W83420	CONTROL CABLE   			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	JACK SCREW	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			301  								(CAN) AC DEPARTED, WHEN STAB TRIM STARTED TO RUN AWAY TO NOSE UP POSITION.  PILOT HAD TO HOLD WHEEL TO KEEP IN POSITION 	ON CLIMB.  AC LANDED AT MAINT BASE TO GET CHECKED OUT. CABLE TENSION WAS BROUGHT UP TO MAX TENSION IAW MM.  WHEN TENSION	 WAS CHECKED ON 17TH IT WAS 2 POUNDS LESS. TEMPERATURE CHANGE. WHEN ATTEMPTING TO BRING TENSION BACK UP TO MAX, TRIM CAB	LE SNAPED NEAR FWD DRUM.  IN APRIL AND MAY OF 2005 TRIM SYS WAS DOING A SIMILAR THING, MFG SUPPLIED US WITH NEW SCREW JA	CK, CABLE ASSY WHICH CURRED PROBLEM UNTIL NOW. TRIM CABLE HAS A TENSION OF 15 + OR - 5 WHICH SEEMS HIGH FOR A .0625 CABL	E BUT HAS TO BE TO KEEPING TRIM SYS IN PLACE AS THERE IS NO FRICTION LOCK OR RATCHET SYS. (TC NR 20051117005)	1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2006070500143	20060705	00143	WP  	2006	7	5	CA051117006      	1	20050721	G	6210	369D2110052	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2681 								(CAN) DURING TRAINING FOR TORQUE EVENT INSPECTION (AWD2003-24-01) A POSSIBLE CRACK WAS FOUND.  THE M/R BLADE WAS REMOVED	 FOR A BETTER VISUAL LOOK WITH THE 10X GLASS.  THE BLADE WAS ALSO INSPECTED BY COUGAR NDE LTD. AND CONFIRMED THE CRACK. 	 MHI PO NR 20385.  THE CRACK WAS 4 INCHES LONG ACROSS THE DOUBLER. (TC NR 20051117006)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006020300143	20060203	00143	EA  	2006	2	3	CA051117007      	2	20051116	G	7414		DISTRIBUTOR GEAR	CONT        	S4LN1209    	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAGNETO	BROKEN          	W				O				OTHER                   				L	O		NO TEST                   	OTHER                     		IN	INSP/MAINT     	1			CA						F01EA170R					(CAN) MAGNETO FAILED SHORTLY AFTER TBO. (80 HOURS), DAMAGING THE DISTRIBUTOR GEAR.						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
2006062200097	20060622	00097	EU  	2006	6	22	CA051117008      	1	20051115	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			1105 								RT WHEEL ASSY WAS FOUND U/S AFTER INSPECTION.  FOUND THAT THE INNER WHEEL WAS CRACKED AND THE WHEEL ASSY WAS REPLACED WI	TH A SERVICEABLE UNIT.					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2006062100186	20060621	00186	SO  	2006	6	21	CA051117009      	1	20051113	G	2130	46129002	CONTROL CABLE   			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					CONTROL LEVER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21316	21316							UPON WALK AROUND, OUTSIDE RECIRCULATED, PRESSURIZED CONTROL LEVERS FOUND WITHOUT ANY TENSION.  CONTROL LEVER CONTROL CAB	LE REPLACED.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2006020200151	20060202	00151	NM  	2006	2	2	CA051118001      	1	20051108	G	4920	38403031	TURBINE BLADES  		1319B       	BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					APU	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA						P6654					(CAN) APU AUTO SHUTDOWN WITH LOSS OF OIL OUT DRAIN MAST REFERENCE ADDITIONAL WORKSHEET ITEM NR2 AND NR3. C/B CLOSED AT P	91.  APU REPLACED IAW AMM 49-11-00 THIS CLEARS MEL 49-1 AND MDDR 3227. PLACARD REMOVED. OFF APU PN 3800702-1SN P-6654 UN	IT WAS ORIGINAL INSTALLATION FROM AIRCRAFT MFG.  TSN IN APU OPERATING HOURS = 2256:30APU START CYCLES CSN = 2923 DAYS SI	NCE NEW = 562FOUR ADDITIONAL APU REMOVALS HAVE OCCURRED YEAR TO DATE ATTRIBUTED TO THE SAME CAUSE OF TURBINE BLADE WALKI	NG.  OEM SB131-49-7860 REFERS.  ADDITIONAL OEM DEVELOPMENT IN PROGRESS FOR LONG TERM CORRECTIVE ACTION PLAN.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062200098	20060622	00098	NE  	2006	6	22	CA051118002      	1	20050117	G	6220	S611221010082	CLEVIS          		S611020003  	SKRSKY	S61   	S61N        	8142104	NE  										M/R HEAD	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THE LOCKING CHANNEL FOR THE KEY IS NOT COMPLETELY MACHINED WHICH RESULTS IN NOT BEING ABLE TO FULLY ADJUST THE PITCH ROD	 ASSY.  SEE ATTACHED PHOTOGRAPHS NR 2 IS A CORRECTLY MACHINED CHANNEL AND NR 1 IS THE FAULTY PART IN QUESTION.  THE PART	 WAS RETURNED TO THE OEM WITH A CORRECTIVE ACTION REPORT WITH A FOLLOW UP E-MAIL DATED THE 10TH NOVEMBER 2005.  NO REPLY	 TO THE ROOT CAUSE TO DATE.			2	G	7	2 	4U				1H15    					 
2006020200152	20060202	00152	EA  	2006	2	2	CA051121001      	1	20051121	G	7312	5023T57P02	FUEL HEATER     	GE          	CF343A      	CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					FUEL HEATER SYS.	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						350232					(CAN) FUEL LEAK AS BEEN FOUND ON SEVEN DAYS INSPECTION, TECHNICIAN HAS FOUND A CRACK IN A SOLDERED JOINT ON FUEL HEATER.	 THE FUEL HEATER HAS BEEN REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006062200100	20060622	00100	NE  	2006	6	22	CA051121002      	1	20050616	G	6310	SB2158102	BEARING RACE    			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					FREEWHEEL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPON VISUAL INSPECTION BEFORE INSTALLATION IT WAS NOTED THAT THE BEARING HAD MULTIPLE AXIAL SCORING MARKS ON THE INNER R	ACE SURFACE.  THESE MARKS WERE DETECTABLE WITH A SCRIBE AND WERE BEYOND ALLOWABLE LIMITS AS PER THE OVERHAUL MANUAL.  TH	E BEARING WAS RETURNED TO THE OEM WHO SUPPLIED A NEW BEARING BUT DID NOT REPLY WITH A CAUSE AND ANALYSIS TO THE PROBLEM.	  A FOLLOW UP E-MAIL REQUESTING THE RESULTS OF THEIR FINDINGS WAS SENT 10-NOV-05.			2	G	7	2 	4U	4	U		1H15    	1E3				 
2006062200101	20060622	00101	NE  	2006	6	22	CA051121003      	1	20050606	G	6320	SB3615102	BEARING CAGE    			SKRSKY	S76   	S76C        	8143008	NE  										M/R GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											BEARING CAGE SHAKE TEST EXCEEDED THE ALLOWABLE TOLERANCE OF 0.025" THE AVERAGE RECORDED ON THIS BEARING WAS 0.051".  THE	 BEARING WAS RETURNED TO THE OEM AND A REPLACEMENT RECEIVED.  NO CAUSE AND ANALYSIS HAS BEEN PROVIDED.  A FOLLOW UP E MA	IL WAS SENT 10-NOV-05.				1	G	7	2 	3U			NC	H1NE    					 
2006020200153	20060202	00153	NE  	2006	2	2	CA051121004      	2	20051117	G	8530	153084	CYLINDER        	PWA         	R2007M2     	DOUG  	DC4   	C54ADC      	3021510	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	NR 2 ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA						P106106					(CAN) NR 2 ENGINE WAS PRECAUTIONARILY SHUTDOWN DUE TO SHAKE.  IT WAS DISCOVERED THAT NR 10 CYLINDER WAS CRACKED AT THE E	XHAUST EAR.  THE CYLINDER ASSY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
2006062200102	20060622	00102	CE  	2006	6	22	CA051122001      	1	20051121	G	5700	817911018	NUT             			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					WING	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THE CREW WENT TO INSTALL A WING BOLT RETAINING NUT ON THE AIRCRAFT.  IT WAS NOTICED THAT THE NUT WAS MISSING ONE OF THE 	TWO PLASTIC LOCKING DEVICES.  IT APPEARS THE PLASTIC WAS NEVER INSTALLED IN ONE HOLE.  THIS IS THE SECOND NUT THAT WAS F	OUND WITH PROBLEMS.  PREVIOUSLY ANOTHER NUT HAD BAD THREADS IN IT EVEN THOUGH IT WAS NEW.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006062200103	20060622	00103	SW  	2006	6	22	CA051122002      	1	20051026	G	5320	206333110	WEB             			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE PERFORMING A 1200 HR INSPECTION ON THE VERTICAL TUNNEL AND BOXBEAM A CRACK WAS NOTICED ON THE RIGHT VERTICAL WEB\S	KIN AND THE VERTICAL ANGLE STIFFENER INSIDE THE TUNNEL.  THIS AREA HAD BEEN REPAIRED PREVIOUSLY IN 1996 BY ANOTHER REPAI	R STATION.  THIS AREA IS KNOWN FOR CRACKS AND IS ALREADY ADDRESSED IN THE STRUCTURAL REPAIR MANUAL.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006062200104	20060622	00104	CE  	2006	6	22	CA051122003      	1	20051119	G	2422		INVERTER        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					AC SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											THE PILOT IN COMMAND REPORTED THE NR 2 INVERTER CIRCUIT BREAKER POPPED.  ON INVESTIGATION, THE NR 2 INVERTER AND ASSOCIA	TED RELAY WIRING SHOWED SIGNS OF OVERHEATING.  THE WIRING FOR THE RELAY OVERHEATED TO THE POINT THAT ONE OF THE WIRES SE	PARATED FROM THE POLE OF THE RELAY.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006062200105	20060622	00105	NE  	2006	6	22	CA051123001      	1	20050810	G	6320	RF981213	ADAPTER         			SKRSKY	S76   	S76A        	8143006	NE  										M/R GBOX FILTER	WORN            	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						A08100225					COMPLETE LOSS OF MAIN GEARBOX OIL AND OIL PRESSURE AS A RESULT OF MGB OIL FILTER OUTLET FLUID ADAPTER ASSEMBLY SEPARATIO	N FROM HOUSING DURING FLIGHT.  CAUSE OF FITTING DISENGAGEMENT UNDER INVESTIGATION.  FOR ADDITIONAL DETAILS CONTACT CHC H	ELICOPTERS INTERNATIONAL.				1	G	7	2 	3U				H1NE    					 
2006020200154	20060202	00154	EA  	2006	2	2	CA051123002      	2	20051123	G	7414	M3006	BEARING         		4371        	CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	MAGNETO	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						05012636					(CAN) ROTOR BEARINGS ROUGH AND SHAFT HARD TO TURN. MAGNETO WOULD NOT TURN FAST ENOUGH TO START ENGINE.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2006062200106	20060622	00106	EU  	2006	6	22	CA051123003      	1	20051122	G	6420	330A33316620	BUSHING         		332A33000106	SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					TAIL ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1403 	313  		M538					DURING THE DAILY INSPECTION, IT WAS NOTICED BLACK T/R BLADE FLAPPING HINGE HADE A LITTLE MORE RESISTANCE, (SIDE TO SIDE 	MOTION) THAN THE OTHER BLADES.  AFTER FURTHER INVESTIGATION IT WAS FOUND THAT THE BUSHING HAD SOME BRINELLING, WHEN THE 	BUSHING WAS REMOVED FOR REPLACEMENT, A CRACK WAS FOUND ALONG THE LENGTH OF THE BUSHING.  IT WAS UPON REMOVAL OF THIS BUS	HING THAT IT WAS NOTICED THAT THREE OF THE NEEDLE BEARINGS WERE DAMAGED AS WELL.  ALL ASSOCIATED PARTS WERE THEN INSPECT	ED, WORN AND DAMAGED PARTS WERE REPLACED, VIBE CHECKS CARRIED OUT AND CHECKED SATISFACTORY.		2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2006020200155	20060202	00155		2006	2	2	CA051123004      	4	20051123	G	3414	C6610640237	INDICATOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	AIRSPEED IND	STUCK           	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT WAS DEPARTING RUNWAY AND THE PILOT NOTICED ON TAKEOFF ROLL THAT THE RT AIRSPEED INDICATOR HAS STUCK AT TH	E 50KT INDICATION. THE PILOT DECIDED TO ABORT THE TAKEOFF AND RETURNED TO THE RAMP. MAINTENANCE INSPECTED THE SYSTEM AND	 MEL THE SYSTEM IAW MFG C208 MEL. FLIGHT CONTINUED WITHOUT ANY FURTHER PROBLEMS.  NOTE: NO OTHER PITOT OR STATIC INSTUME	NTS WERE EFFECTED BY THIS FAULT. INDICATOR TO BE REPLACED WHEN THE AIRCRAFT RETURNS.			1	H	7	1 	3T	3	T		A37CE   	E2NE	5	C	P60GL	 
2006062200107	20060622	00107	NE  	2006	6	22	CA051123005      	1	20051120	G	6320	MS8005K280P	HOSE            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					M/R GEARBOX	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											WHILE GROUND RUNNING AIRCRAFT, OIL HOSE BURST AND DRAINED MGB OIL OVERBOARD.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006062600021	20060626	00021	WP  	2006	6	26	CA051123006      	1	20050814	G	6710		TIP CAP         	HUGHES      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	DAMAGED         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			8    								(CAN) A/C HAD A BLADE REPLACED DUE TO A CRACK.  NEW BLADE WAS VERY DIFFICULT TO BALANCE, SEEMED HEAVIER THAN THE OTHERS.	 BALANCING OF BLADES MET CRITERIA AND IT WAS RELEASED FOR SERVICE. SWEEPING OF BLADES WAS USELESS IN ACHIEVING BALANCE. 	SECOUND DAY OF THE JOB PILOT STARTED AC AND WAS ROLLING UP TO IDLE WHEN AC WENT INTO MODERATE M/R INBALANCE. ENGINE WAS 	SHUTDOWN. CREW MEMBER NOTICED A WHITE MIST COMING OUT OF TIP CAP. ON SHUTDOWN, PILOT NOTICED THAT TRAILING TIP CAP WAS M	ISSING OFF END OF ONE BLADE, THAT THERE SEEM TO BE A SLIGHT DEFORMATION IN SKIN TOP AND BOTTOM APPROX. 8 IN. FROM TIP.  	BLADE WAS RETURNED TO THE MFG FOR EVALUATION. (TC NR20051123006)	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006020200156	20060202	00156	SO  	2006	2	2	CA051123007      	2	20051115	G	8530	AEC631397	CYLINDER        	CONT        	TSIO520E    	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						176696R					(CAN) AT THE 50 HRS INSPECTION OF THE AIRCRAFT, AT CYLINDER COMPRESSION TEST, MFG ENGINE SB M91-6, AND THE TEST FAILED F	OR CYLINDER NR 4 DUE TO A LEAK FOUND BETWEEN FINS AT CYLINDER HEAD (THE SIDE OF THE EXHAUST EXIT).  THE CYLINDER REPLACE	D AND AIRCRAFT RETURN TO SERVICE AFTER THE INSPECTION.				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006020200165	20060202	00165	SO  	2006	2	2	CA051123008      	2	20051117	G	8530	AEC631397	CYLINDER        	CONT        	TSIO520E    	CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	NR 4 CYL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						514517					(CAN) AT THE 200 HRS INSPECTION OF THE AIRCRAFT, AT ENGINE CYLINDER COMPRESSION TEST, MFG SB M91-6, AND THE TEST FAILED 	FOR CYLINDER NR 4 DUE TO LEAK FOUND BETWEEN FINS AT CYLINDER HEAD. THE CYLINDER REPLACED AND AIRCRAFT RETURN TO SERVICE 	AFTER THE INSPECTION.				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006020200166	20060202	00166	NM  	2006	2	2	CA051123009      	1	20051118	G	2797	W32200518	WIRE            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					SPOILER SYS	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, CIRCUIT BREAKER FOR THE SPOILER SHUTOFF VALVES POPPED.  AFTER LANDING, MAINTENANCE COULD NOT DUPLIC	ATE THE SNAG.  BOTH A AND B SYSTEMS WERE FUNCTION CHECKED SERVICEABLE. ON THE NEXT FLIGHT, THE CB POPPED AGAIN.  THE AIR	CRAFT WAS OPERATED ON A FERRY PERMIT TO RETURN FOR FURTHER MAINTENANCE.  THE WIRE, W322-00 5-18 WAS FOUND SHORTED TO GRO	UND FROM CONNECTOR D758 TO CONNECTOR D4842P.  THE WIRE WAS REPAIRED IAW STANDARD WIRING PRACTICES MANUAL.			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006012400125	20060124	00125	EA  	2006	1	24	CA051124001      	2	20051112	G	7323	697072003	GOVERNOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	OVERSPEED	LOOSE           	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AN AC CARRIED OUT AN INFLIGHT SHUTDOWN OF THE NR 1 ENGINE DUE TO LOSS OF OIL PRESSURE. AFTER LANDING THE CREW NOTI	CED OIL STREAKED DOWN BOTH SIDES OF COWLING AND A SIGNIFICANT AMOUNT DRIPPING FROM DRAIN VENTS.  MAINTENANCE FOUND ON TH	E NR 1 ENGINE, THE OVERSPEED GOVERNOR HAD AN EXCESSIVE OIL LEAK. THE BOLTS ON THE FLANGE THAT SECURES THE SPRING CASING 	SUB ASSY TO THE MAIN BODY OF THE OVERSPEED GOVERNOR WERE LOOSE ENOUGH TO BE ROTATED BY HAND. OVERSPEED GOVERNOR REPLACED	 IAW AMM 61-20-26-000-801 AND 61-20-26-400-801.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005122000307	20051220	00307	CE  	2005	12	20	CA051124002      	1	20051121	G	5521	26340141	SPAR            	CESSNA      	263400045   	CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELEVATOR	CORRODED        	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						208341					(CAN) SEVERE CORROSION ON FACE OF SPAR UNDER BALANCE WEIGHT. AIRCRAFT IS A FLOAT PLANE.						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2006062200108	20060622	00108	SW  	2006	6	22	CA051124003      	1	20050920	G	6320	RSS9	BEARING         			BELL  	212   	212         	1181420	SW  											UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											NEW SPHERICAL BEARING RECEIVED WITH EXCESSIVE AXIAL PLAY.  AXIAL PLAY OF THE INNER RACE TO OUTER RACE WAS MEASURES AT 0.	032" THE BHT-ALL-SPM LIMIT FOR A USED BEARING IS 0.030".  THE BEARING HAS BEEN RETURNED TO BHT FOR WARRANTY WITH A BHT M	MIR.				1	G	7	1 	4U				H4SW    					 
2006062200109	20060622	00109	WP  	2006	6	22	CA051124004      	1	20051124	G	5340	C3485	ANCHOR          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					SEAT BELT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6399 	2200 							DURING AIRCRAFT, OVERHAUL THE PILOT/COPILOT SEAT BELT ATTACH POINTS WERE FOUND CRACKED.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2005122700201	20051227	00201	EA  	2005	12	27	CA051124005      	1	20051121	G	5230	MS2125006020	BOLT            			DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  					DOOR FITTING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17496								(CAN) DURING C CHECK, BOLT ON FWD CARGO DOOR FITTING WAS CORRODED TO THE EXTENT THAT BOLT HEAD SEPARATED AT LIGHT FINGER	 TOUCH. 6 FITTINGS ARE BOLTED TO THE SILL STRUCTURE BY 2 BOLTS EACH. THEY SECURE THE DOOR IN THE CLOSED POSITION. THE MO	ST FWD BOLT OF THE 12 WAS THE ONE AFFECTED. VISUAL INSPECTION OF THE AREA DID NOT INDICATE ANY CORROSION PROBLEMS. THERE	 IS NO REQUIREMENT TO DISASSEMBLE THE BOLTS FOR INSPECTION AND THEY HAVE PROBABLY BEEN THERE SINCE THE A/C WAS NEW. THE 	REMAINING 11 BOLTS WERE DISASSEMBLED AND VARYING DEGREES OF CORROSION WAS FOUND. ALL 12 BOLTS HAVE BEEN REPLACED.		2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
2005122700202	20051227	00202	EA  	2005	12	27	CA051124006      	1	20051121	G	2750	C6W104632	ADAPTER         			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27856								(CAN) DURING MAINTENANCE CHECK, A CRACK WAS FOUND ON THE AFT END FLANGE OF THE ADAPTER. THE ADAPTER WAS REPLACED IAW RD6	-57-266 BUT IT WAS FOUND THAT THE LOCK FASTENER COULD NOT BE INSTALLED AT 1 LOCATION DUE TO INTERFERENCE WITH INTERNAL S	TRUCTURE. OTHER FASTENER PROBLEMS THEN AROSE. A REPAIR SCHEME IS BEING PREPARED TO SOLVE THE FASTENER PROBLEM.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2005122700203	20051227	00203	NE  	2005	12	27	CA051124007      	2	20051116	G	7200	CT79B	ENGINE          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	NR 2	OVERHEATED      	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			M	J		OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AS THE POWER LEVERS WERE ADVANCED TO 80 PERCENT THE FLIGHT CREW HEARD POPPING NOISES AND THE TAKEOFF WAS REJECTED.	 THE NR 2 ENGINE OVERHEAT LIGHT WAS ILLUMINATED AND THE ENGINE WAS SHUTDOWN. THIS ENGINE HAS BEEN REMOVED AND RETURNED T	O MANUFACTURER FOR EVALUATION AND REPAIR. CAUSE OF OVERHEAT NOT READILY APPARENT.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2005122700204	20051227	00204	EA  	2005	12	27	CA051124008      	1	20051121	G	5753	C6W12104546	RIB             			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27856								(CAN) DURING MAINTENANCE CHECK THE RIB WAS FOUND TO BE CRACKED IAW ATTACHMENT. RIB WAS REPLACED.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006062200110	20060622	00110	NM  	2006	6	22	CA051124009      	1	20051122	G	4920	38403031	TURBINE BLADES  	HONEYWELL   		BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					APU	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			2501 			P6621					ITEM/ISSUE IS NON SDR REPORTABLE REQUIREMENT.  PMI REQUESTED ITEM TO BE FILED TO BRING VISIBILITY TO ISSUE.  APU INOP DU	E TO AUTOSHUT DOWN, TURBINE SCAVENGE RETURN LINE BROKEN RESOLUTION NOTES:  DUE BROKEN OIL SCAVENGE RETURN LINE.  TURBINE	 AREA INSPECTED AS PER HONEYWELL SIL APU-91.  NO BLADE SHIFT NOTED (NO RUBBING OR TIP CURL).  APU CENTER BODY CAP APPEAR	S TO BE CRACKED BETWEEN UPPER SUPPORT STRUTS, SOME OIL STAINING NOTED ON BOTTOM OF BODYCAP.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2005122700205	20051227	00205		2005	12	27	CA051125001      	4	20051125	G	2565		SLIDE           			EMB   	ERJ170	ERJ170100   	       	EU  	GE    	CF34  	CF348E5A1   	30015	NE  					L2 DOOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FAULT: L2 DOOR IN DISARMED MODE, ARMING/DISARMING HANDLE DOES NOT MOVE UP FULLY AS COMPARED TO OTHER DOORS HANDLES	.  INDICATOR SHOWS (DISARMED) BUT NOT IN CENTER OF INDICATION WINDOW.  ALSO COVER DOES NOT CLOSE FLUSH IN BOTH MODES.  F	MR WAS ISSUED TO VERIFY THE MECHANISM OF THE DOOR, AND FOUND SLIDE HANDLE DOES NOT MOVE UPWARDS TO DISARM WHEN VENT IS O	PEN, USING THE OUTSIDE HANDLE.			2	L	7	4 	4F	4	F	RT	A56NM   	E00063EN				 
2006062200111	20060622	00111	SW  	2006	6	22	CA051125002      	1	20051109	G	6720	430001007101	CONTROL TUBE    			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					TAIL ROTOR	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											T/R CONTROL TUBE 430-001-007-101, FOUND WITH CHAFING MARKS.  TUBE WAS REPLACED WITH NEW -105.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2006062200112	20060622	00112	SW  	2006	6	22	CA051125003      	1	20051109	G	6720		CONTROL TUBE    			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					TAIL ROTOR	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											T/R CONTROL TUBE 430-001-007-101 FOUND WITH CHAFING MARKS.  TUBE WAS REPLACED WITH NEW -105.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2005122700206	20051227	00206	GL  	2005	12	27	CA051125004      	2	20051021	G	7250	23073795	TURBINE BLADES  			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA								CAE31206			(CAN) DURING A FLIGHT THE ENGINE EXPERIENCED AN ITT OVERTEMP OF 1045 DEGREES C FOR 36 SECONDS. THIS RESULTED IN AN UN-CO	MMANDED IN FLIGHT SHUTDOWN. ENGINE DISASSEMBLY AT MFG REVEALED AN  HPT1  BLADE FAILURE FROM THE ROOT.					2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2005122700207	20051227	00207	NM  	2005	12	27	CA051125005      	1	20051124	G	5100		CLAMP           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					UNKNOWN	UNSECURE        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE PHASE CHECK A CLAMP WAS FOUND UNSECURED IN THE EE BAY JUST ABOVE THE SHIP BATTERY.  CLAMP REMOVED	.  A FLEET CAMPAIGN IS IN PROGRESS TO CHECK FOR FOD IN THE EE BAY.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005122700208	20051227	00208	CE  	2005	12	27	CA051125006      	1	20051123	G	2497		WIRE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ALTERNATOR	SHORTED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA						F062719					(CAN) MAIN BATTERY WIRE AT ALTERNATOR, SHORTED TO GROUND AT FRONT BAFFLE, THEREFORE CAUSING CIRCUIT BREAKER TO TRIP.  AC	U WAS ALSO DAMAGED DUE TO SHORT.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2005122700210	20051227	00210	NM  	2005	12	27	CA051125007      	1	20051125	G	2530	4110001145	COFFEEMAKER     			BOEING	767   	767383      	1385214	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					GALLEY	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FAULT: IN CRZ VENTRE GALLEY COFFEE MAKER GAVE A FLASH AND ASH DEPOSITED ALL AROUND, ELECTRIC FUMES SMELT BY F/AS, 	ALL CB'S IN AREA PULLED UNTIL BUSSES DEPOWERED.  DIVERTED YYT FOR MTCE/SAFETY CHECK. FOUND LOWER C/M MID GALLEY HEATING 	ELEMENT INSULATION BLOWN OUT WITH POWDER EVIDENT AND C/B POPPED ON UNIT. COFFEE MAKER REMOVED AND ALL MID GALLEY CB`S PU	LLED AND COLLARED, WATER SUPPLY ALSO S/OFF FOR EXTRA PRECAUTION.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2005122700218	20051227	00218	EU  	2005	12	27	CA051125008      	1	20051121	G	3232	5D11580	CONNECTING ROD  			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING, IT WAS FOUND THAT THE NOSE U/C LT DOOR HAD COME OPEN IN FLIGHT. THE CONNECTING ROD WAS FOUND TO BE 	SHEARED. DURING INSPECTION NO DISTRESS OR DETERIORATION COULD BE FOUND TO ACCOUNT FOR THE SHEARED ROD. LOCAL DAMAGE TO T	HE LT U/C DOOR HINGE IS ATTRIBUTED TO BEING OPEN IN FLIGHT. NO SECONDARY DAMAGE TO THE AIRCRAFT STRUCTURE WAS FOUND. THE	 DOOR AND CONNECTING ROD WERE CHANGED AND THE SYSTEM FUNCTIONED CORRECTLY DURING RETRACTION TESTS.			2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005122700219	20051227	00219	CE  	2005	12	27	CA051125009      	1	20051125	G	3246	D30256	HUB             	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE WHEEL IS THE OLDER THREE-PIECE TYPE. SEVERAL CRACKS WERE FOUND IN THE ALUMINUM CASTING AT THE FLANGE RETAINING	 BOLT HOLES, WITH SOME HOLES HAVING CRACKS THROUGH TO THE OUTER CIRCUMFERENCE OF THE HUB AS WELL AS ALONG THE SPOKE. ALL	 CRACKS WERE APPROXIMATELY ALIGNED WITH THE BOLT AXIS.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062200113	20060622	00113	EU  	2006	6	22	CA051125010      	1	20051124	G	6210	704A33633211	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					M/R BLADES	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			53   								WHILE DOING A 500 HOUR (T)INSPECTION IT WAS NOTED THAT THE RUBBER WAS DELAMINATING ON TWO OUT OF THE THREE SPHERICAL THR	UST BEARINGS.  CRACKING APPEARS TO BE BETWEEN THE RUBBER AND THE METAL PIECE INBOARD SIDE OF SPHERICAL STOP.  THE RUBBER	 APPEARED WET ALL THE TIME SO AS PER MM INSPECTION CRITERIA IT WAS FOUND THAT THE DELAMINATION WAS BEYOND LIMITS.  WITH 	ONLY 52.7 HOURS ON THE UNITS IT WAS DISCOURAGING.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006012400131	20060124	00131	NE  	2006	1	24	CA051128001      	2	20051125	G	7230	4020T51P02	TURNBUCKLE      								GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	FRACTURED       	W				O				OTHER                   				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			CA											(CAN) TO DATE, (3) CF34-3B1 STAGE 2 HPC TURNBUCKLES AFFECTING 2 ENG HAVE FAILED DURING SERVICE. SEPARATION OF VG SHAFT S	IDE TURNBUCKLE ROD END.  SEPARATION POINT ON ROD END OCCURRED IN THREADED PORTION WHERE IT MEETS JAM NUT ON TURNBUCKLE A	SSY. CAUSE CONFIRMED TO BE LOW CYCLE FATIGUE RESULTING FROM IDLE LOAD INDUCED BY INTERFERENCE OF  TURNBUCKLE ASSY WITH T	ORQUE SHAFT CLEVIS. ONE OF 2 ENG FOUND WITH THE BROKEN TURNBUCKLE CONDITION EXPERIENCED AN INFLIGHT SHUTDOWN DUE TO BOTH	 TURNBUCKLES FAILING, NOT ALLOWING STAGE 2 VANES TO TRACK PROPERLY. OTHER ENG WAS FOUND WITH ONE BROKEN TURNBUCKLE.  VG 	SYS CAN WORK PROPERLY FOR AMOUNT OF TIME ON ONE TURNBUCKLE.						4	F			E15NE				 
2005122700220	20051227	00220	EU  	2005	12	27	CA051128002      	1	20051124	G	3234		HANDLE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	MLG	ICED            	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF FOR FIRST FLIGHT OF THE DAY, THE CREW WHERE UNABLE TO MOVE THE LANDING GEAR SELECTOR HANDLE TO THE G	EAR UP POSITION. THE AIRCRAFT RETURNED TO THE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. UPON INVESTIGATION BY MAINTEN	ANCE, IT WAS FOUND THAT THERE WAS ICE ACCUMULATION IN THE LANDING GEAR SELECTOR LINKAGE LOCATED IN THE NOSE WHEEL WELL.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2005121200002	20051212	00002	GL  	2005	12	12	CA051128005      	1	20051101	G	5740		ATTACH FITTING  			NAMER 	T6    	HARVARD*    	6400426	GL  										WING	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLY WITH CF 2005-19, NO CRACKS FOUND.  REFER TO FILE FOR COPY OF EMAIL INDICATING COMPLIANCE BY AIRCRAFT OWNER.						1	L	7	1 	3R				EXPA1L71					 
2005121200003	20051212	00003	EU  	2005	12	12	CA051128006      	1	20051101	G	5740		ATTACH FITTING  			NOORDN	AT16  	AT16HARVARD 	       	EU  	PWA   	R1340 	R1340AN1    	52016	NE  					WING	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLY WITH CF 2005-19, NO CRACKS FOUND.  REFER TO FILE FOR COPY OF EMAIL INDICATING COMPLIANCE BY AIRCRAFT OWNER.						1	L	7	1 	3R	3	R		AR11    	5E2				 
2005121200010	20051212	00010	WP  	2005	12	12	CA051128007      	1	20051101	G	5740		ATTACH FITTING  			NAMER 	A36   	A36AEDMONDSN	6400102	WP  										WING	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLY WITH CF 2005-19, NO CRACKS FOUND.  REFER TO FILE FOR COPY OF EMAIL INDICATING COMPLIANCE BY AIRCRAFT OWNER.						1	L	7	1 	4V				L152    					 
2005121200011	20051212	00011	EU  	2005	12	12	CA051128008      	1	20051101	G	5740		ATTACH FITTING  			NOORDN	AT16  	AT16HARVARD 	       	EU  										WING	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLY WITH CF 2005-19, NO CRACKS FOUND.  REFER TO FILE FOR COPY OF EMAIL INDICATING COMPLIANCE BY AIRCRAFT OWNER.						1	L	7	1 	3R				AR11    					 
2005122800225	20051228	00225	NM  	2005	12	28	CA051128009      	1	20051122	G	2910	BACH8A04NM0274T	FLEX LINE       			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					HYD SYSTEM	KINKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE SUBJECT AIRCRAFT HAD INTERMITTENT HISTORY ASSOCIATED WITH NOSE GEAR EXTENSION/RETRACTION ANOAMLIES. DURING A R	ECENT HEAVY CHECK THIS ISSUE WAS FURTHER INVESTIGATED.THE TEFLON LINED HYDRAULIC FLEX LINE WAS FOUND TO HAVE KINKED.IT I	S BELIEVED THAT THIS FINDING CONTRIBUTED TO THE EXTENSION/RETRACTION ANOMALIES BY RESTRICTING THE FLOW THE NOSE GEAR SKI	 ACTUATOR.THE AIRCRAFT IS BEING MONITORED AS PART OF THE RELIABILITY PROGRAM REVIEW.			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005122800226	20051228	00226	WP  	2005	12	28	CA051128010      	1	20051124	G	5412	AN8324D	FITTING         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	BULKHEAD	CRACKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, IT WAS OBSERVED THAT THE DIRECT READING OIL PRESS GAUGE WAS AT ZERO ON RT ENGINE. AUTO SYN PRESSURE	 GAUGE, TEMPS, OIL WARNING LIGHT ALL INDICATED ENG WAS FINE. IT WAS THEN FOUND A LEAK ON RT ENG DURING VISUAL CONFIRMATI	ON. ENG WAS SHUTDOWN AND PROP FEATHERED. FLT LANDED WITHOUT FURTHER INCIDENT. UP ON INSP IT WAS FOUND THAT A BULKHEAD FI	TTING ON FIREWALL FOR DIRECT OIL PRESS GAUGE HAD BROKEN COMPLETELY OFF. FITTING WAS REPLACED WITH STEEL FITTING, AC RETU	RNED TO SERVICE. THIS TYPE OF FAILURE HAD NEVER BEEN SEEN BEFORE, A SERIES OF NDT ON SAME TYPE AND MAKE OF FITTINGS RESU	LTED IN NO FAILURE OF THIS KIND. IT WAS DETERMINED THAT THIS WAS A ISOLATED INCIDENT.	2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603	 
2006062200114	20060622	00114	WP  	2006	6	22	CA051128011      	1	20051128	G	6320	C2641	GEARBOX         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			805  								AIRCRAFT WAS DOWN FOR OTHER MAINTENANCE.  WHEN THE FUEL TANK WAS REMOVED THE C729-14 PITOT LINE WAS FOUND WEARING INTO T	RANSMISSION HOUSING.  THE WEAR IS ON THE CURVE, AND IS APPROX. 0.045" TO 0.050" DEEP.  THIS AREA HAD NOT BEEN ACCESSED S	INCE THE AIRCRAFT WAS NEW.  CONTACTING ROBINSON HELICOPTERS TO FIND OUT WHAT TYPE OF DAMAGE LIMITS ARE ALLOWED, AND WHAT	 FURTHER ACTION WILL BE REQUIRED.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062200115	20060622	00115	EU  	2006	6	22	CA051128012      	1	20051028	G	7931	704A37642043	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL PRESSURE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA				118  							A RESISTANCE CHECK OF THE TRANSMITTER WAS CARRIED OUT. IT REVEALED AN OPEN CIRCUIT.  TX ORDERED AOG.  PREVIOUS LOG ENTRY	 REVEALED THIS TRANSMITTER WAS JUST INSTALLED AUG 30 05.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2005122800227	20051228	00227	EU  	2005	12	28	CA051129001      	2	20051128	G	7310		LINE            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					ENGINE FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING WALKAROUND, FUEL WAS COMING FROM NR 2 ENGINE COWL.  DISCOVERED LINE BETWEEN FUEL PUMP AND FIREWALL LEAKING 	FROM B-NUT AT FIREWALL.  B-NUT TIGHTENED AND LEAK CHECKED. FLEET CAMPAIGN INITIATED TO CHECK TORQUE OF B-NUTS AND TORQUE	 SEALANT WILL BE APPLIED AND CHECKED ON PHASE CHECKS.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006062200117	20060622	00117	CE  	2006	6	22	CA051129002      	1	20051114	G	2710	1295240051	SPRING          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					AILERONS	FRACTURED       	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			14632	14632							DURING TAXI, THE FLIGHT CREW NOTICED A FULL LEFT BIAS DEFLECTION IN THE AILERON SYSTEM.  MAINTENANCE FOUND ONE OF THE AI	LERON INTERCONNECT SPRINGS HAD FRACTURED AT THE END RING THAT PROVIDES CONNECTION TO THE BRIDLE.  IT IS FELT THAT THE IS	SUE MAY HAVE BEEN INDUCED DURING PHASE INSPECTION REQUIREMENTS TO REMOVE THE SPRINGS DURING TENSIONING PROCEDURES AND TH	AT TOOL MARKS FROM PLIERS OR OTHER MECHANICAL MEANS MAY HAVE SCORED THE SPRING PROVIDING AREAS FOR STRESS RISERS TO DEVE	LOP.  A COMPANY SUPPLEMENTAL INSPECTION HAS BEEN INSERTED INTO OUR PROCESS CONTROL FOR THIS ISSUE.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2005122800228	20051228	00228	EA  	2005	12	28	CA051129003      	1	20051106	G	4920	5490000	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU BAY	FAILED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) WHILE AT THE GATE AND PRIOR TO DEPARTURE, THE FLIGHT CREW HAD AN APU FIRE WARNING INDICATION. THE CREW FOLLOWED TH	E QRH PROCEDURE AND DICHARGED THE APU FIRE BOTTLE. LINE MAINTENANCE INSPECTED THE APU AND FOUND NO EVIDENCE OF FIRE. THE	Y ALSO FOUND THE FUEL AND OIL FILTERS IN BYPASS MODE AND THAT THE FAN MODULE WAS EXTREMELY HARD TO TURN BY HAND. THE APU	 (P/N 5490000 S/N P-1247) HAS BEEN REMOVED AND HAS BEEN SENT TO MFG FOR ANALYSIS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062200118	20060622	00118	CE  	2006	6	22	CA051129004      	1	20051118	G	5710	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	STABILIZER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12468								DURING INSPECTION OF AD 80-11-04, BRACKET P/N 0432001-9 FOUND CRACKED AT THE SAME TIME, REAR SPAR P/N 0432001-56 AND REI	NFORCEMENT P/N 0432001-15 FOUND ALSO CRACKED.  ALL THOSE 3 PARTS REPLACED WITH NEW.  AVAILABLE FROM CESSNA.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2006062200119	20060622	00119	SW  	2006	6	22	CA051129005      	1	20051025	G	3260	713058503	UPLOCK          			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	LT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA				287  							FAILED TO DISENGAGE.  SECOND EXTENSION WORKED FINE.						1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2006062200120	20060622	00120		2006	6	22	CA051129006      	4	20051128	G	3418	9754423104	COMPUTER        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STICK PUSHER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			4526 								PILOT RETURNED TO RAMP FOLLOWING NORMAL DEPARTURE AND REPORTED THAT SHORTLY AFTER TAKEOFF THE "STICK SHAKER" WAS OPERATI	NG AND OPERATED MOST OF THE WAY THROUGH THE CIRCUIT TO RETURN TO RUNWAY AND THE RAMP.  AIRCRAFT WAS BROUGHT INTO HANGAR 	AND A "CHECK" OF THE STICK PUSHER SYSTEM WAS PERFORMED.  IT WAS DISCOVERED THAT LT AOA TRANSMITTER WAS INITIATING A SHAK	E AT 10 DEGREES INSTEAD OF THE NORMAL PER CHECK 32 DEGREES.  RT AOA TRANSMITTER WAS ALSO TESTED AND SHAKE WAS AT NORMAL 	32 DEGREES.  A SERVICEABLE SPARE STICK SHAKER COMPUTER WAS INSTALLED AND A COMPLETE "FUNCTION TEST" PERFORMED.  ALL SYST	EMS NORMAL.  A PRECAUTIONARY TEST FLIGHT PERFORMED ALL SYSTEM FUNCTIONING NORMAL.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062200121	20060622	00121	NE  	2006	6	22	CA051129007      	2	20051028	G	7200		ENGINE          			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											DURING CLIMB, THE ENGINE FLAMED OUT.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC WILL MONITOR INVESTIGATION OF T	HE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062200122	20060622	00122	NE  	2006	6	22	CA051129008      	2	20051102	G	7200		ENGINE          								PWA   	PT6   	PT6A68      	 	NE  						FIRE            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AB	AEROBATIC      	1			CA											DURING AEROBATIC MANEUVERS (RAYTHEON T-6A) SMOKE AND FUMES BECAME EVIDENT IN THE COCKPIT.  P&WC WILL MONITOR INVESTIGATI	ON OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.										4	T			E26NE				 
2006062200123	20060622	00123	NE  	2006	6	22	CA051129009      	2	20051108	G	7200		TOWERSHAFT      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											THE ENGINE FLAMED OUT DURING CLIMB.  AN EMERGENCY WAS DECLARED AND THE FLIGHT DIVERTED.  SUBSEQUENT INVESTIGATION REVEAL	ED A FRACTURED TOWERSHAFT.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062100187	20060621	00187	EA  	2006	6	21	CA051129010      	2	20051108	G	7200		ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  						FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								56942			ON CLIMB, THE ENGINE WAS REPORTED TO HAVE EMITTED A NOISE ACCOMPANIED BY A LOSS OF POWER.  THE AIRCRAFT DIVERTED TO DEPA	RTURE AND SUBSEQUENTLY CRASHED.  MFG WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2006062200124	20060622	00124	NE  	2006	6	22	CA051129011      	2	20051108	G	7200		ENGINE          			AMD   	FALC50	FALCON2000  	2730170	NM  	PWA   	306   	PW306B      	 	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE AND SHUT DOWN UNCOMMANDED.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE T	URBOMACHINE.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	K	7	2 	4F	4	F	RT	A50NM   	E35NE				 
2006062200125	20060622	00125	NE  	2006	6	22	CA051129012      	2	20051110	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	JT15  	JT15D5      	52112	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								500072			DURING TAKEOFF, THE ENGINE FLAMED OUT.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE INCIDENT	 AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006062200126	20060622	00126	NE  	2006	6	22	CA051129013      	2	20051110	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						SMOKE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								DD0012			DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED ACCOMPANIED BY OIL SMOKE AND ODOR IN THE CABIN AIR.  THE 	ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING.  P&WC WILL INVESTIGATE THE INCIDENT	 AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006062200127	20060622	00127	NE  	2006	6	22	CA051129014      	2	20051102	G	7261		HOUSING         			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  					OIL FILLER	LEAKING         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPE	CTION REVEALED THE OIL TANK OIL FILTER HOUSING TO BE LEAKING.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062200128	20060622	00128	EU  	2006	6	22	CA051129015      	1	20051113	G	7712		CONNECTOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					TORQUE SENSOR	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			AP	APPROACH       	1			CA											ON APPROACH, ENGINE TORQUE COULD NOT BE REDUCED BELOW 40 PERCENT.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INVES	TIGATION REVEALED A CONTAMINATED TORQUE SENSOR CONNECTOR.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062200129	20060622	00129	EA  	2006	6	22	CA051129016      	2	20051105	G	7314		DRIVE SHAFT     			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL PUMP	FRACTURED       	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			2437 								DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION AND WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION	 REVEALED A FRACTURED FUEL PUMP DRIVE SHAFT.					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006062200130	20060622	00130	NE  	2006	6	22	CA051129017      	2	20051108	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PC1199			DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED AND UNRECOVERABLE REDUCTION IN POWER ACCOMPANIED BY A REDUCTION IN 	FUEL FLOW AND COMPRESSOR SPEED.  THE FLIGHT DIVERTED.  P&WC WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE 	OF ROOT CAUSE ONCE ESTABLISHED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006062200131	20060622	00131	NE  	2006	6	22	CA051129018      	2	20051122	G	7200		ENGINE          			MRCHTI	S205  	S20522R     	8120412	EU  	PWA   	JT15  	JT15*       	52060	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								98034			DURING A TRAINING FLIGHT, THE ENGINE FLAMED OUT WHEN THE POWER LEVEL WAS RETARDED TO IDLE POSITION.  A SUCCESSFUL IN-FLI	GHT RE-LIGHT WAS ACCOMPLISHED.  P&WC WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETER	MINED.				1	L	7	1 	3O	4	T		A9EU    	E1NE				 
2006062200132	20060622	00132	EU  	2006	6	22	CA051130001      	1	20051128	G	2750		FLAP SYSTEM     			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	MALFUNCTIONED   	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											DURING APPROACH, ECAM MESSAGE CAME ON FLAP SYSTEM 1 AND 2 FAULT AT POSITION 15/20.  RETURNED FLAP TO 0 THE SAME THING HA	PPENED ON SECOND ATTEMPT.  DURING INSPECTION, FOUND THE RIGHT TORQUE LIMITER FLAP GEAR BOX NR 1 INDICATOR TRIPPED.  INDI	CATOR RESET AND OIL LEVEL CHECKED ON NR 1, 2 AND 3 GEARBOXES.  ALL FOUND NORMAL.  SYSTEM OPERATED SEVERAL TIMES.  UNABLE	 TO DUPLICATE PROBLEM.  AD F2005-174 COMPLETED AND SYSTEM FOUND SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006062200133	20060622	00133	CE  	2006	6	22	CA051130002      	1	20051119	G	2421	DOFF10300BR	ALTERNATOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  		FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA				257  							ALTERNATOR SYSTEM FAILURE IN FLIGHT.  ALL ELECTRICS WENT OFF LINE.  UNKNOWN CAUSE.  BOTH ALTERNATOR AND VOLTAGE REGULATO	R FOUND UNSERVICEABLE.  ALTERNATOR POSITIVE LEAD TO BUS BAR, CONNECTORS AT BOTH ENDS FOUND DISCOLORED FROM HEAT AND/OR A	RCING.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2006062200134	20060622	00134		2006	6	22	CA051130003      	4	20051121	G	2312		RADIO           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  		MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											HUGH STATIC OVER VOICE WHEN TRANSMITTING.  RECEIVING 5/5.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2005122800229	20051228	00229	CE  	2005	12	28	CA051130004      	1	20051122	G	2612	302158	FIRE DETECTOR   			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	LT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) WHEN THE INDICATOR (LT ENGINE FIRE) ILLUMINATED, THE ENGINE WAS SHUTDOWN BY THE PILOT, AND PUT INTO FEATHER. AN EM	ERGENCY WAS DECLARED. THE AIRCRAFT RETURNEDTO BASE. AFTER VERIFICATION, NO ENGINE FIRE WAS EVIDENT. THE INDICATORS WERE 	VERIFIED AND THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2005122800230	20051228	00230	EA  	2005	12	28	CA051130005      	2	20051125	G	7200		ENGINE          			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 1	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) NR1 ENGINE THE AUTO FEATHER SYSTEM WAS ARMED FOR TAKEOFF.  SHORTLY AFTER TAKEOFF THE PILOT DISARMED THAT AUTO FEAT	HER SYSTEM. THE AIRCRAFT CONTINUED TO CLIMB OUT. THE PILOT NOTICED PROPELLER RPM SLOWLY DROPPING OFF (SUCH AS PROPELLERS	 OUT OF SYNC). THE PILOT ADVANCED THE POWER LEVER FOR NR1 ENGINE (LT). THERE WAS NO NOTICEABLE CHANGE TO ENGINE OUT PUT.	  THE PILOT PROCEEDED TO FEATHER THE PROPELLER AND SHUTDOWN THE ENGINE. ATC WAS CONTACTED. THE AIRCRAFT RETURNED TO THE 	POINT OF DEPARTURE WITHOUT INCIDENT. UNDER INVESTIGAITON AT THIS TIME.		1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2006062200135	20060622	00135	EA  	2006	6	22	CA051130006      	2	20051130	G	7414	M3100	IMPULSE COUPLING			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			852  			04051072					AS A RESULT OF PREVIOUS MAGNETO FAILURES, IMPLEMENTED A 100 HR INSPECTION OF ALL IMPULSE COUPLED MAGNETOS ON ALL ZLIN 24	2L AIRCRAFT.  DURING ONE OF THESE INSPECTIONS ONE OF THE IMPULSE COUPLING PAWLS HAD A SPRING MISSING.  THIS SPRING ALLOW	S THE PAWL TO ENGAGE TO THE PIN ON THE MAGNETO HOUSING FOR STARTING.  IN THIS CONDITION THE MAGNETO WOULD ONLY FIRE EVER	Y SECOND ROTATION DURING THE STARTING PROCESS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2006062200136	20060622	00136	EA  	2006	6	22	CA051130007      	1	20051129	G	3220		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NOSE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			2791 	2791 							AFTER TAKEOFF DURING GEAR RETRACTION, RECEIVED THE FOLLOWING WARNING MESSAGES: NOSE DOOR OPEN, GEAR DISAGREE.  AIRCRAFT 	HAD DEPARTED FROM CONTAMINATED RUNWAY.  AIRCRAFT CONTINUED TO DESTINATION AND USED ALTERNATE EXTENSION TO LOWER GEAR.  A	IRCRAFT LANDED NORMALLY.  MAINTENANCE FOUND ACCUMULATION OF SLUSH ON MLG AND NLG OLEOS AND SWITCHES.  SLUSH REMOVED, GEA	R SWINGS CARRIED OUT, GEAR FUNCTIONED NORMALLY.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062200137	20060622	00137	CE  	2006	6	22	CA051130008      	1	20051130	G	2435	23078019	STARTER GEN     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				697  				PS0287			ATTEMPTED TO START THE LEFT ENGINE BUT NO SUCCESS.  MAINTENANCE WAS NOTIFIED AND AIRCRAFT BROUGHT BACK INTO HANGAR.  SYS	TEM INSPECTED AND FOUND THAT STARTER GENERATOR AT FAULT.  REPLACED STARTER GENERATOR AND ENGINE RUN PERFORMED.  SYSTEM C	HECKED SATISFACTORY AND NO LEAKS PRESENT.  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006062200138	20060622	00138	EU  	2006	6	22	CA051130009      	1	20051123	G	3297		WIRE HARNESS    			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											ON APPROACH WHEN GEAR SELECTED DOWN, GEAR UNSAFE LIGHT CAME ON, GEAR IN TRANSIT.  GOT ALL (3) GREENS LEFT, RIGHT AND NOS	E, BUT NOSE UNSAFE LIGHT REMAINED ON.  DID FLY BY, TOWER REPORTED NOSE GEAR APPEARS TO BE DOWN.  PILOTS CONFIRMED (3) GR	EENS FOR GEAR, IT WAS DETERMINED THAT NOSE GEAR DOORS ON NOSE MAY NOT BE CLOSING AFTER THE GEAR WAS DOWN AND LOCKED.  LA	NDING WAS MADE WITH NO FURTHER PROBLEMS.  ON INVESTIGATION FOUND BOTH WIRES TO MICROSWITCH ON STRUT BROKEN AT THE HARNES	S CLAMPING.  REPAIRED BROKEN WIRES ON HARNESS.  C/O GEAR FUNCTIONAL AS PER RAYTHEON MM SERVICEABLE.  ADJUSTED CLAMPING O	N STRUT MICROSWITCH HARNESS.  CHECKED ON GEAR SWINGS OK.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006062200139	20060622	00139	EU  	2006	6	22	CA051130010      	1	20051123	G	5740	1407000130001	BRACKET         			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					LT WING TE FLAP	UNSERVICEABLE   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											ON APPROACH WITH FLAPS SELECTED TO 15 DEG STALL IDENT LIGHT CAME ON THE ANNUNCIATOR PANEL.  ON INVESTIGATION FOUND FLAP 	OUTBD MICROSWITCH OFF THE CAM FROM SWITCH ASSY.  FURTHER INVESTIGATION WAS CARRIED OUT AND FOUND THE OUTBD BRACKET BROKE	N FOR SWT SUPPORT.  REPLACED OUTBD BRACKET P/N 140-700013-0001 WITH NEW UNIT.  C/O RIGGING AND FUNCTIONALS AS PER RAYTHE	ON MM CH.27-33-23-501.  C/O FUNCTIONALS ON STALL IDENT SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006062200140	20060622	00140	EA  	2006	6	22	CA051130011      	2	20051125	G	7314		DRIVE ASSY      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	FUEL PUMP	SHEARED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			155  			HKN047FP					IN CRUISE, WHEN LT ENGINE LOST POWER.  CREW RETARDED THROTTLE AND CALLED ATC.  DURING THIS TIME, DISCOVERED NO FUEL PRES	SURE INDICATED ON LT ENGINE AND SELECTED BOOST PUMP ON.  REGAINED FULL POWER AND LANDED AT THE CLOSEST PRACTICAL AIRPORT	.  INVESTIGATION REVEALED PUMP DRIVE ON AFFECTED FUEL PUMP TO BE SHEARED OFF IN THE SHEAR AREA, ALTHOUGH THE PUMP APPEAR	S UNDAMAGED AND TURNS NORMALLY.  ENGINE WAS INSPECTED, PUMP REPLACED WITH A SERVICEABLE PUMP, AND THE AIRCRAFT RETURNED 	TO SERVICE.  DUE TO THE FACT THAT THIS PUMP IS ONLY 155.1 HOURS SINCE NEW, IT IS SCHEDULED TO BE SENT TO KELLY AEROSPACE	 FOR FURTHER INVESTIGATION.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062200141	20060622	00141	EA  	2006	6	22	CA051130012      	1	20051125	G	3320	BR6314101	LIGHT           			DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  					CABIN LIGHTS	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											DURING PRESTART CHECKS BOTH THE PAX AND CREW NOTICED A BURNING ODOR AND THE FLIGHT WAS ABORTED.  MAINTENANCE INSPECTION 	REVEALED A CHARRED RECEPTACLE FOR THE FLUORESCENT TUBE IN THE WINDOW LIGHT.  FURTHER INVESTIGATION HAS SHOWN THAT BOTH T	HE RECEPTACLE AND THE BALLAST MAY HAVE BEEN AT FAULT.  A CURRENT AD CF-2004-26R1 IS OUT FOR THE DASH-8 THAT USES THE SAM	E FLUORESCENT LIGHTING SYSTEM.			2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
2006062200143	20060622	00143	CE  	2006	6	22	CA051201001      	1	20051130	G	3213	08411066	IDLER ASSY      			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	BELLCRANK GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6473 								DURING ROUTINE INSPECTION OF THE RIGHT MAIN LANDING GEAR, A SMALL CRACK IN PAINT HAS BEEN FOUND ON THE UPPER RADIUS OF T	HE BELLCRANK GEAR IDLER DOOR ARM.  NON DESTRUCTIVE TEST CONFIRMED THE CRACK AND THE PART HAS BEEN REPLACED.					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2006062100188	20060621	00188	CE  	2006	6	21	CA051202001      	1	20051124	G	3297	G13A22	WIRE            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	LOOSE           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											WIRE G13A22 CAME OFF AT V3-1 EMERGENCY EXTENSION HANDLE SAFETY SWITCH.  THIS CAUSED THE GEAR TO NOT RETRACT WHEN SELECTE	D TO THE UP POSITION.  POSSIBLE CAUSE OF LOOSE WIRE, MAY BE THAT THE WIRE WAS MOVED DURING FUSELAGE INSPECTION, WHICH MA	Y HAVE LOOSENED ATTACHING HARDWARE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006062200144	20060622	00144	SW  	2006	6	22	CA051202002      	1	20051123	G	5302	206033001003	TAIL BOOM       			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					BS 45	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING THE CLEANING OF THE TAIL BOOM, A CRACK WAS FOUND AT BOOM STATION 45".  THE CRACK ORIGINATED FROM A RIVET THE TOP 	LEFT SLIP (FOR THE CAMLOC FITTING).  THE CRACK MEASURED 3.5" AND RUNS ON AN 80 DEGREES ANGLE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062200145	20060622	00145	CE  	2006	6	22	CA051202003      	1	20051125	G	3310		CONTROL PANEL   			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					TRIM INDICATOR	BURNED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											A BURNT ODOR WAS NOTICED FOLLOWED BY SMOKE IN THE COCKPIT, COMING FROM THE TRIM INDICATOR LIGHT PANEL.  THE PILOT CLOSED	 THE RHEOSTAT AND RETURNED TO BASE.  AFTER INSPECTION OF THE LIGHT PANEL, HUMIDITY WAS FOUND UNDER THE PANEL, WHICH CAUS	ED A SHORT CIRCUIT.  THE PANEL WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	4T	4	T		A14CE   	E2WE				 
2006062200146	20060622	00146	SO  	2006	6	22	CA051202004      	2	20051201	G	8520		CRANKCASE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1238 	1238 				357431			MULTIPLE CRACKS FOUND ON RIGHT CRANKCASE THRU BOLT BOSS JUST UNDER THE UPPER REAR HOLE OF THE NR 1 ALTERNATOR MOUNTING B	RACKET.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2006062700030	20060627	00030	EU  	2006	6	27	CA051202005      	1	20051129	G	3250	C24780003	STEERING SYS    			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211*      	54555	NE  					NLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING LEVELING A/C FOR WEIGHT AND BALANCE PURPOSES, GREEN SYS ELECT HYD PUMP WAS TURNED ON TO POSITION HORIZ STAB, A/C 	WAS BEING LEVELED USING 5 LANDING GEAR AXLE JACK POINTS, N/G STEERING SWITCH WAS SELECTED OFF AND N/G STEERING BY-PASS P	IN INSTALLED.  AT THE MOMENT OF SYSTEM PRESSURIZATION NOSE LANDING IMMEDIATELY SWUNG 90 DEG.  T/S CARRIED OUT USING BITE	 INFO; AIRBUS INDUSTRIES WAS ALSO SOLICITED FOR ASSIST.  AN EXISTING TFU 32.51.00.020 DETAILS A SIMILAR PROBLEM.  A RECO	MMENDATION WAS RECEIVED FROM AIRBUS TO REPLACE THE SELECTOR VALVE (FIN 5113GC) PRIOR TO NEXT FLT, WHICH WAS ACCOMP AND S	ENT UNIT OUT FOR ANALYSIS.  ADDITIONAL T/S RELATED TO A CLASS 3 FAULT THAT MAY BE RELATED REMAINS TO BE INVESTIGATED.	2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006062700031	20060627	00031	CE  	2006	6	27	CA051202006      	1	20051128	G	2820	05011874	LINE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL DIST	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			9394 								FUEL PIPE BETWEEN STAINER AND UNION WORN ALMOST THROUGH BY NOSE STEERING ROD.  PART REPLACED WITH CLEARANCE TO ROD.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062700033	20060627	00033	EA  	2006	6	27	CA051202007      	2	20051121	G	7322	105217	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3026 							CARBURETOR BOWL TO BODY WAS FOUND TO BE LOOSE.  ATTACHMENT SCREWS LOCK TABS WERE IN PLACE, HOWEVER DUE TO HIGH TIME (ON 	CONDITION ENGINE) THE ASSY HAD BECOME LOOSE ASSUMABLY DUE TO AGE AND VIBRATION.  AN OVERHAULED CARB WAS INSTALLED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062700034	20060627	00034	CE  	2006	6	27	CA051202008      	1	20051109	G	5210	504300431329	ANGLE           			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	CABIN DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5684 								WHEN COMPLYING WITH SPECIAL INSPECTION ON CABIN DOOR, DISCOVERED CRACKED CABIN DOOR SILL ANGLE AT TOP OF DOOR.  ADVISED 	TO HAVE A SPARE PART ON HAND BEFORE DOING INSPECTION.  PART WAS CRACKED ALONG WIDTH OF THE ANGLE  RUNNING FORE AND AFT F	ROM AFT END OF THE DOOR.  APPROX LENGTH WAS 8" ALONG THE ATTACHMENT RIVETS.  THIS A/C IS CONTRACTED TO DO AIR AMBULANCE 	7 DAYS/WEEK AND HAD ACCRUED APPROX 2000 HOURS IN THIS TYPE OF USE BY TWO OPERATORS.  PREVIOUS INSPECTION DETECTED NO PRO	BLEM 1000 CYCLES PREVIOUS.  THE PART WAS ALSO INADVERTENTLY THROWN OUT AFTERWARDS SO IT IS NOT AVAILABLE.  INCREASED OUR	 INSPECTION FREQUENCY IN THIS AREA DUE TO HEAVY USE IT IS SUBJECTED TO.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006062700035	20060627	00035	NM  	2006	6	27	CA051205001      	1	20051130	G	3220	DSC252B40124	HOSE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG	RUPTURED        	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											AT T/O WHEN L/G WAS SELECTED 'UP', ABNORMAL IND LIGHTS WERE OBSERVED ON THE GEAR SELECTOR ANNUNCIATOR PANEL.  IN ADDITIO	N NR 2 OUTBOARD SPOILER CAUTION LIGHTS ILLUMINATED WITH NR 2 HYD SYSTEM IND GAUGES BOTH AT ZERO.  FOLLOWING A MANUAL GEA	R EXTENSION, A/C RETURNED TO BASE WHERE A LANDING WAS CARRIED OUT W/O INCIDENT.  ENGINEERING INVESTIGATION REVEALED THAT	 A PRESSURE FLEXIBLE HOSE TO THE NLG DRAG STRUT RETRACTION ACTUATOR HAD RUPTURED LIBERATING THE HYDRAULIC FLUID CONTENT 	FROM THE NR 2 HYDRAULIC SYSTEM.  BOTH NLG RETRACTION ACTUATOR FLEXIBLE HOSES WERE REPLACED, NR2 HYD SYSTEM CONTENT REPLE	NISHED AND THE SYSTEM BLEED IAW MM REQUIREMENTS.  RELATED TO SERVICE DIFFICULTY ALERT AL-2003-11.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062700037	20060627	00037	WP  	2006	6	27	CA051205002      	2	20051203	G	7200		ENGINE          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					LEFT	BIRD INGESTION  	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			C	E	J	F.O.D.                    	VIBRATION/BUFFET          	WARNING INDICATION        	TO	TAKEOFF        	1			CA											ON TAKEOFF ROLL, A BIRD WAS INJESTED THROUGH THE LT ENGINE.  THE CREW ABORTED TAKEOFF AND SHUTDOWN.  THE ENGINE AND ENGI	NE INLET WILL BE REPLACED AND SENT FOR REPAIR.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062700039	20060627	00039	NE  	2006	6	27	CA051205003      	2	20051129	G	7250		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  		FOD             	W				O				OTHER                   				C			F.O.D.                    			CR	CRUISE         	1			CA			2781 					PC0693			DURING CRUISE, THE PILOT HEARD A LOUD WHINING SOUND FROM THE ENGINE.  MX FOUND THE WHINING STARTED AT 850 PROP RPM.  THE	 RGB CHIP AND THE MAIN OIL FILTER WAS EXAMINED AND CLASS 3 UNACCEPTABLE DEBRIS IAW MM CHAP 79 WAS FOUND.  THIS COUPLED W	ITH THE NOISE FROM THE ENGINE RESULTED IN THE ENGINE BEING REMOVED AND SENT TO AN APPROVED MAINTENANCE FACILITY.  NO RES	ULTS FROM THE INVESTIGATION ARE YET AVAILABLE.			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006062700040	20060627	00040	EU  	2006	6	27	CA051205004      	1	20051130	G	3110	27E462	MODULE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					INSTRUMENT PANEL	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											CORROSION WAS FOUND ON A RELAY SOCKET AND ASSOCIATED WIRING CAUSING SYSTEM FAILURE.  MOISTURE HAD MIGRATED INTO THE NOSE	 COMPARTMENT CAUSING CORROSION ON THE DIMMING MODULE COMPONENTS.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006062700041	20060627	00041	NE  	2006	6	27	CA051205005      	2	20051205	G	7200		ENGINE          			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					NR 1	MAKING METAL    	W				E				ENGINE SHUTDOWN         				C			F.O.D.                    			CR	CRUISE         	1			CA			19575					41193			PRELIMINARY INVESTIGATION AND TROUBLESHOOTING HAS NOTED UNUSUALLY HIGH N3 INDICATION DURING A GROUND START ATTEMPT, WHIC	H SUGGESTS THAT THE ACCESSORY GEARBOX MAY HAVE LOST COUPLING TO THE N3 ROTOR.  AS FURTHER SUPPORTING EVIDENCE, THE MASTE	R CHIP DETECTOR WAS FOUND WITH SIGNIFICANT CONTAMINATION.  THE TROUBLESHOOTING FINDINGS ARE CONSISTENT WITH OTHER INDUST	RY OCCURRENCES THAT ARE CURRENTLY UNDER INVESTIGATION BY ROLLS ROYCE, WHERE THE ACCESSORY GEARBOX LOST MECHANICAL DRIVE 	FROM N3 ROTOR.  REFERENCE ROLLS ROYCE WORLD WIDE COMMUNICATION WW10379/1 AND WW10345.  WILL BE REQUESTING A FULL INVESTI	GATION AT ENGINE TEAR DOWN.	2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006062700043	20060627	00043	EA  	2006	6	27	CA051205006      	2	20051107	G	7310	AS3209010012	MANIFOLD        								PWC   	150   	PW150A      	 	EA  					FUEL SYSTEM	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								FA0093			SEVERAL PACKINGS P/N AS3209-010 AND AS3209-012 WERE NOT INSTALLED DURING ASSY OF FUEL MANIFOLDS TO FLOW DIVIDER.  ASSEMB	LER SUBSEQUENTLY REALIZED OMITTED ONE OF TWO O-RINGS AT FUEL MANIFOLD LOCATION OF ONE ENG.  ENG TECH MADE RESEARCHES TO 	TRACK ENG SERIAL NUMBER.  P&WC REQUESTED THAT THE CUSTOMER LANDS HIS A/C TO CHECK ENGINE AND CONFIRM THE MISSING O-RING.	  PREVENTIVE ACTION WAS ALSO REQUESTED TO PREVENT ANY FUTURE OCCURRENCE.  ASSEMBLY INSTRUCTION WAS AMENDED TO CLEARLY SH	OW WERE THE TWO PARALLEL O-RINGS MUST BE INSTALLED PRIOR TO SLIDING THE FUEL MANIFOLD INTO THE FLOW DIVIDER.  THE INVEST	IGATION SHOWED THAT THIS WAS AN ISOLATED CASE.						4	T			E00062EN				 
2006071900041	20060719	00041	EA  	2006	7	19	CA051205007      	2	20051201	G	8520	74965	CRANKSHAFT      			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1442 				L1884836A			(CAN) THE CRANKSHAFT OF THIS AIRCRAFT WAS INSPECTED DUE TO A FAILURE OF A CRANKSHAFT OF ANOTHER AIRCRAFT IN THE FLEET (I	NTERNAL CORROSION). UPON REMOVAL OF THE FRONT CRANK PLUG AND CLEANING OF THE CRANKSHAFT. IT WAS DISCOVERED THAT THE URET	HABOND COATING WAS PEELING AND IT SUBSEQUENTLY PEELED COMPLETELY AWAY FROM THE CRANK.  FURTHER INSPECTION FOUND CORROSIO	N ON THE FIRST INCH OF THE CRANKSHAFT. THIS CRANKSHAFT HAD NOT BEEN RE-WORKED IN THE PAST SO THERE WAS ENOUGH MATERIAL T	O CLEAN THE CRANK AND RETURN IT TO SERVICE.  ENGINE WAS OVERHAULED ON 3 MAR 99 AND WAS MARKED PID NOT REQUIRING ANY INTE	RNAL INSPECTIONS UNTIL 2000-HRS. (TC NR20051205007)	1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006062700044	20060627	00044	SW  	2006	6	27	CA051205008      	1	20051205	G	6220	206011160101	STOP            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1164 		MDLM07376					DURING OVERHAUL OF MAIN ROTOR HUB, NDT OF THE STATIC STOPS FOUND CRACKS IN CORNERS.  THE ASSEMBLY HAS TWO STOPS, AND BOT	H WERE CRACKED.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062700045	20060627	00045	WP  	2006	6	27	CA051205009      	1	20051201	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					PILOT VALVE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			414  								TWO SERVOS REMOVED.  BOTH INSTALLED NEW AT THE FACTORY WITH THE SAME TIME ON THEM.  BOTH SERVOS LEAKING HYDRAULIC FLUID 	FROM THE PILOT VALVE.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062700046	20060627	00046	WP  	2006	6	27	CA051205010      	1	20051201	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			414  								HYD SERVO WAS REMOVED FOR HYD LEAK.  WHEN THE UPPER ROD-END WAS REMOVED, WATER WAS FOUND IN THE SHAFT OF THE SERVO.  NO 	SIGNS OF CORROSION WERE NOTED.  SERVOS IN THE R44 ARE MOUNTED VERTICALLY, AND UNLIKE OTHER HELICOPTERS WITH VERTICAL SER	VOS, THE UPPER ROD ENDS DO NOT GET SEALED WITH PRO-SEAL.  THE END OF THE SHAFT HAS TWO TANGS FOR A LOCK ASSEMBLY.  WHEN 	FULLY ASSEMBLED IT IS POSSIBLE THAT WATER COULD ENTER AT THAT POINT.  THE PICTURES ATTACHED ARE NOT OF THE SERVO IN QUES	TION.		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062700047	20060627	00047	NM  	2006	6	27	CA051206001      	1	20051206	G	2530	3510004403	COFFEEMAKER     			BOEING	767   	767300      	1385204	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					CTR GALLEY	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											IN CRZ VENTRE GALLEY COFFEE MAKER GAVE A FLASH AND ASH WAS DEPOSITED ALL AROUND, ELEC FUMES SMELT BY F/A`S, ALL CBS IN A	REA PULLED, UTIL BUSSES DEPOWERED.  DIVERTED YYT FOR MTCE/SAFETY CK.  FOUND LOWER C/M MID GALLEY HEATING ELEMENT INSULAT	ION BLOWN OUT WITH POWDER EVIDENT AND CB POPPED ON UNIT C/M REMOVER AND ALL MID GALLEY CBS PULLED AND COLLARED, WATER SU	PPLY ALSO SHUTOFF FOR EXTRA PRECAUTION.  NEW C/MKR INSTALLED, OPERATION CHKS SERV.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006062700049	20060627	00049	NM  	2006	6	27	CA051206002      	1	20051206	G	2121	EVT3454H	FAN             			AIRBUS	A319  	A319114     	3930350	NM  										AVIONICS BAY	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											VENT EXTRACT FAULT.  BURNING ODOR NOTICED PRIOR TO MESSAGE.  EXTRACT FAN SET TO OVRD.  ODOR DISAPPEARED.  EXTRACT BLOWER	 REPLACED AS PER AMM 21-26-51.  OPERATIONAL TEST C/O THROUGH CFDS, NO FAULT.					2	L	7	2 	4F			RT	A28NM   					 
2006062700052	20060627	00052	EA  	2006	6	27	CA051206003      	1	20050921	G	5270	601R38593	FITTING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PROX SWITCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING SCHEDULED MAINTENANCE, SLIDER FITTING FOR PROXIMITY SWITCH PS17MB ON SERVICE DOOR WAS FOUND CRACKED.  UPON FURTHE	R INSPECTION EXTENSIVE CORROSION WAS FOUND ON PART.  SLIDER FITTING WAS REPLACED AND PROXIMITY SWITCH RERIGGED.  PART TI	MES AND CYCLES UNKNOWN.  AIRCRAFT TOTAL TIME AND CYCLES: 21277:48 HOURS, 17532 CYCLES.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062700057	20060627	00057	CE  	2006	6	27	CA051206004      	1	20051201	G	5312		INTERCOSTAL     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19409								DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON OTHER AIRCRAFT, THE AFT PRESSURE BULKHEAD WAS FOUND CHAFED BY BOTH T	HE CENTER INTERCOSTAL AND THE OUTBOARD INTERCOSTAL ADJACENT TO THE TAIL ACCESS DOOR.  NDT WAS COMPLETED AND A CRACK FOUN	D AT THE OUTBOARD LOCATION.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2006062700058	20060627	00058	GL  	2006	6	27	CA051206005      	2	20051201	G	7250	6870832	COUPLING        								ALLSN 	250C  	250C20      	03013	GL  					TURBINE ASSY	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A CONVERSATION BETWEEN  ESSENTIAL TURBINES INC (ETI) PROCUREMENT MANAGER, AND CENTRAL ROMANA CORPORATION LTD., LA	 ROMANA, DOMINICAN REPUBLIC (T.809-723-1372, 809-523-8232, 809-813-9350 FAX 305-574-7873), A QUERY WAS ABOUT PARTS THAT 	(ETI) WAS ASSUMED TO HAVE SUPPLIED.  ETI REQUESTED THE CERTIFICATION COPIES AND RECEIVED FAA 8130.3 WITH ESSENTIAL TURBI	NES INC ON IT AND AMO18-09 DATED 11/10/2005.  CERTIFICATES ARE IDENTIFIED WITH 68708324 & 6898977-H PN RESPECTIVELY. ETI	, Q.A.  MANAGER HAS SENT ETI TRANSPORT CANADA AMO37-94 & EASA 145.7117 CERTS TO THE COMPLAINANT.							3	U			E4CE				 
2006062700059	20060627	00059	EA  	2006	6	27	CA051206006      	2	20051101	G	8520	13B27123	CRANKSHAFT      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2198 								ENGINE WAS IN FOR OVERHAUL.  CRACK FOUND IN CRANKSHAFT WITH MPI.  NO RECORD OF BLADE STRIKE.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2006062700077	20060627	00077	WP  	2006	6	27	CA051206007      	1	20051129	G	8011	3151031	ACTUATOR        		BC3151002   	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					STARTER	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						0990000906					STARTER WAS REMOVED SLOW TO CRANK.  OVERHAUL SHOP FOUND MOTOR BEARINGS FAILED/SEIZED.  LINEAR ACTUATOR REMOVED WAS AN AF	TER-MARKET AUTOMOTIVE PART, MADE BY UNIPOINT OF TAIWAN.  THIS ACTUATOR  (SOLENOID) DIFFERS FROM THE OEM PART: (1) ALIGNM	ENT OF MOUNTING HOLES TO ELECTRICAL TERMINALS IS ROTATED 90; AND (2) THE TWO MAIN CONTACTOR TERMINALS ARE REVERSED.  TH	IS COULD CAUSE CONFUSION WHEN CONNECTING POWER LEADS.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062700079	20060627	00079	EA  	2006	6	27	CA051206008      	1	20051206	G	3222	713321	STRUT           			DHAV  	DHC6  	DHC6300     	2802606	EA  										NLG	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											FLIGHT CREW REPORTED A CONSTANT LOSS OF FLUID AND PRESSURE OF NOSE STRUT ASSEMBLY.  NOSE STRUT DISASSEMBLED TO BE RE-SEA	LED.  THE RETAINING SCREW THAT HOLDS THE PISTON NUT SECURE WAS NOT WOUND IN PROPERLY/COMPLETELY.  THIS PROTRUDING SCREW 	HEAD THEN MADE REPEATED CONTACT WITH THE INSIDE OF THE FLOATING PISTON, CREATING DEEP GOUGES IN THE PISTON INTERNAL SURF	ACE.  THIS CAUSED SHAVINGS OF ALUMINUM FROM PISTON TO BE DISPERSED THROUGHOUT STRUT AND TORE UP THE INTERNAL O-RINGS CAU	SING LEAKAGE.		1	H	7	2 	3T			RT	A9EA    					 
2006062700080	20060627	00080	CE  	2006	6	27	CA051206009      	1	20051123	G	2435	03600923	BEARING         	LUCAS       		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	STARTER GEN	WRONG PART      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1100 		3085					STARTER-GEN SUFFERED A BEARING FAILURE THAT TOOK THE GENERATOR OFF-LINE.  THE ANTI-DRIVE END (ADE) BEARING FAILED, CAUSI	NG THE ARMATURE TO DESTROY ITSELF BY RUBBING ON THE STATOR POLES.  ON DISASSEMBLY BY OVERHAUL SHOP, THE BEARING WAS FOUN	D TO BE P/N 03-6009-23, WHICH IS NOT APPROVED IN THE 23085-001 ST-GEN.  THE CORRECT BEARING IS P/N 03-6009-18.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006062700082	20060627	00082	CE  	2006	6	27	CA051206010      	1	20051201	G	3260		DOWNLOCK SWITCH 			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											ON APPROACH, CREW DID NOT GET A NOSE GEAR DOWN INDICATION ON SELECTION.  EMERG PROCEDURES COMPLETED WITH NO INDICATION. 	 FLY BY VISUAL SHOWED NOSE GEAR DOWN, INDICATION ILLUMINATED ON TOUCH DOWN.  MAINTENANCE FOUND NOSE GEAR ACTUATOR INTERN	AL DOWN LOCK SWITCH TO BE INTERMITTENT.  ACTUATOR REPLACED.				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006062700029	20060627	00029	WP  	2006	6	27	CA051207001      	1	20051201	G	6320		HOUSING         	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TRANSMISSION	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			414  			2513					PITOT LINE WAS FOUND WEARING INTO TRANSMISSION HOUSING.  THE WEAR IS ON THE CURVE OF THE HOUSING.  THE COMPANY HAS START	ED AN INSPECTION OF THIS AREA FOR ALL R44II IN THE FLEET.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006060600224	20060606	00224	WP  	2006	6	6	CA051207002      	1	20051204	G	6320	C2641	HOUSING         	ROBSIN      	C0065       	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					TRANSMISSION	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			492  			2067					PITOT LINE WAS FOUND WEARING INTO TRANSMISSION HOUSING.  THE WEAR IS ON THE CURVE OF THE HOUSING.  THE COMPANY HAS START	ED AN INSPECTION OF THIS AREA FOR ALL R44II IN THE FLEET.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006060600229	20060606	00229	EA  	2006	6	6	CA051207003      	2	20051201	G	7314	200F5002	PUMP            	CONAER      	200F5002    	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					RT ENGINE	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			CA			576  			HDN076FP					PILOT NOTICED LOW FUEL PRESSURE ON APPROACH.  UPON FURTHER INVESTIGATION, MAINTENANCE DETERMINED THAT THERE WAS FUEL LEA	KING PAST THE RELIEF VALVE WHICH AT A LOW ENGINE RPM WOULD GIVE LOW FUEL PRESSURE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060600230	20060606	00230	CE  	2006	6	6	CA051207005      	1	20051206	G	3260	H111541	UPLOCK SWITCH   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LG RETRACT SYS	INTERMITTENT    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											ON CLIMB WHEN GEAR WAS SELECTED UP, THE INTRANSIT LIGHT IN GEAR HANDLE STAYED ILLUMINATED.  PILOT CYCLED GEAR AND DOWNLO	CK GREEN LIGHTS GOOD BUT HANDLE ALWAYS RED IN GEAR UP POSITION.  ELECTED TO RETURN TO MAINTENANCE BASE.  THE GEAR WAS GO	OD IN THE DOWN AND LOCKED POSITION, EMERG SERVICES WHERE ON STANDBY AND AN UNEVENTFUL LANDING WAS DONE.  MAINTENANCE FOU	ND THAT THE LT LANDING GEAR UPLOCK SWITCH WAS INTERMITTENT AND WAS REPLACED.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006060600231	20060606	00231	EA  	2006	6	6	CA051207006      	1	20051204	G	5610	NP13932211	WINDSHIELD      	PPG         	NP13932211  	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			CA			11959	11959		99238H6783					DURING APPROACH, LT COCKPIT SIDE WINDSHIELD SHATTERED.  NO LOSS OF PRESSURIZATION.  MAINTENANCE REPLACED LT SIDE WINDSHI	ELD, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006060600232	20060606	00232	EU  	2006	6	6	CA051208001      	1	20051208	G	3244	300828	TIRE            	MESSIER     		AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					MLG	BLOWN           	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			CA											AFTER T/O FROM YYC, A LARGE PIECE OF TIRE RUBBER WAS FOUND ON RUNWAY, NO UNUSUAL INDICATIONS IN COCKPIT.  LANDED IN LHR 	WITH EMERG SERVICES IN STANDBY, TIRE IS SHREDDED.  ACCOMPLISHED INSPECTION AFTER TIRE BLOWN AS PER AMM 05-51-12, REF L40	44129 FOR FINDINGS.  REPLACED NR 6 TIRE DUE BLOWN AND MATING TIRE NR 5 AS PER AMM 32-41-11-400-801.				2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006060600233	20060606	00233	GL  	2006	6	6	CA051208003      	1	20051112	G	1430	AN6A	BOLT            	DHAV        	C2FS3203A   	DHAV  	DHC2  	DHC2MKI     	2801830	GL  										LANDING GEAR	WRONG PART      	W				A	C			UNSCHED LANDING         	ABORTED TAKEOFF         			E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			288  								WRONG BOLTS INSTALLED AT LOWER FUSELAGE STRUT TO BIRDCAGE STRUCTURE.  AN6-A INSTALLED, SHOULD BE AN176-13A CLOSE TOLERAN	CE BOLTS, AS PER DEHAVILLAND DRAWING C2FS5123A.					1	H	7	1 	3R			RC	A806    					 
2006061900171	20060619	00171	EU  	2006	6	19	CA051208004      	1	20051130	G	2910	809510	O-RING          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					FILTER SHROUD	DEFORMED        	W				E				ENGINE SHUTDOWN         				K	O		FLUID LOSS                	OTHER                     		NR	NOT REPORTED   	1			CA			222  								(CAN) PRIOR TO THE SECOND FLIGHT OF THE DAY THE PILOT NOTICED HYDRAULIC FLUID ON THE SIDE OF THE FUSELAGE.  FURTHER INSP	ECTION REVEALED LEAK ORIGINATED FROM THE HYDRAULIC COMPACT UNIT.  THE O-RING ON THE FILTER SHROUD HAD FAILED. O-RING REP	LACED. AIRCRAFT GROUND RUN FOR LEAK CHECK AND RETURNED TO SERVICE. (TC NR 20051208004)				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2006060600234	20060606	00234	SO  	2006	6	6	CA051208005      	1	20051202	G	2130		PIPE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					CABIN	LOOSE           	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											CABIN DEPRESSURIZED AT 13000 FEET, CABIN RATE OF CHANGE SPIKED +6500 FEET AND DIFF TO ZERO.  FRESH AIR PIPE DISCONNECTED	 IN FLIGHT.  PIPE REPOSITIONED, CLAMP TIGHTENED AND CHECKED OK.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2006060600235	20060606	00235	SW  	2006	6	6	CA051208006      	1	20051128	G	5330	206033003161	SKIN            	BELL        	BELL407     	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5160 			53130					SKIN FOUND TO BE CRACKED DURING ROUTINE INSPECTION.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006061900173	20060619	00173	EU  	2006	6	19	CA051208007      	1	20051111	G	2911	366A541088	B-NUT           	UROCOP      		SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ACCUMULATOR	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DECREASED OF 15 RPM OBSERVED IN FLIGHT. LEAK CHECK COMPLETE AND LEAK FOUND ON ACCUMULATOR P/N : 366A54-1088.  ACCU	MULATOR B-NUT TIGHT AND LEAK CHECK COMPLETED, LEAK FOUND ACCUMULATOR REMOVED FROM AC AND FOUND CRACK AND FALL IN 2 PIECE	S  REPLACED WITH NEW ACCUMULATOR.   AC SENT BACK TO SERVICED. (TC NR 20051208007)				1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2006060600236	20060606	00236	CE  	2006	6	6	CA051208008      	1	20051202	G	5312		BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE TROUBLESHOOTING A PRESSURIZATION SNAG ON THE AIRCRAFT UNDERGOING MAINTENANCE AT OUR FACILITY, DISCOVERED AN APPROX	IMATELY 3.5 LONG CRACK IN A SECTION OF THE BULKHEAD LOWER FLANGE ATTACHED AT THE REAR SPAR AT FS 227.  THE CRACK WAS CAU	SING A MAJOR PRESSURIZATION LEAK THAT COULD BE FELT OUTSIDE OF THE AFT SPAR BOX ON THE EXTERIOR OF THE AIRCRAFT.  NO SPE	CIFIC REPAIR INSTRUCTIONS ARE PROVIDED IN THE MAINTENANCE MANUAL FOR THIS DAMAGE.  A CANADIAN DAR WAS CONTRACTED TO PROV	IDE A REPAIR DESIGN FOR THE ABOVE AND REPAIRS WERE COMPLETED AS PER APPROVAL.  UPON COMPLETION OF REPAIRS A PRESSURIZATI	ON TEST WAS COMPLETED.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060800223	20060608	00223	CE  	2006	6	8	CA051208009      	1	20051202	G	5310		STRUCTURE       			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT6A41      	52043	EA  						PULLED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											AFT STRAKES RIVETS PULLED THROUGH ON THE TAIL TO FUSELAGE JOINT.  ADVISED ENGINEERING AND GAINED INSTRUCTIONS FOR REPAIR	 AND COMPLETED, AIRCRAFT RETURNED TO SERVICE.  CAUSE OF THE RIVETS PULLING THROUGH IS UNKNOWN AT THIS TIME.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060800230	20060608	00230	EA  	2006	6	8	CA051208010      	1	20051208	G	5420	601370038182	ANGLE           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FS 640	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21506								WHILE REPLACING THE ENGINE PYLON BOLTS AS PER THE SB601R-54-005, THE AME WORKING IN THE AREA NOTICED THAT BOTH THE LT AN	D RT SIDE FORMED ANGLES INSIDE ENGINE PYLON AT STA FS 640, STRINGER 10 WERE CRACKED.  BOTH ANGLES P/N 601-37003-81 FOR T	HE LHS AND ANGLE P/N 601-37003-82 FOR THE RHS WERE REMOVED AND REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006060800231	20060608	00231	NM  	2006	6	8	CA051208011      	1	20050923	G	2760	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILER	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			24310	24310							15 MINUTES AFTER DEPARTURE, CREW REPORTED THAT THE NR 1 HYDRAULIC SYSTEM FLUID QUANTITY DROPPED TO LESS THAT ONE US QUAR	T, AND PRESSURE WENT TO ZERO.  THE AIRCRAFT RETURNED TO BASE UPON WHICH MAINTENANCE DISCOVERED THAT THE RT INBOARD FLIGH	T SPOILER ACTUATOR HOUSING HAD CRACKED ON THE BODY SURROUNDING THE FORWARD END OF THE ACTUATOR SLEEVE.  A BROKEN PIECE O	F THE ACTUATOR BODY WAS DISLODGED AND FELL INTO THE AFT SECTION OF THE REAR SPAR ON THE RT WING.  MAINTENANCE REPLACED T	HE SPOILER ACTUATOR AND FUNCTION CHECKED IT PER AMM 27-14-05.  SYSTEM WAS BLED AND LEAK CHECKED SERVICEABLE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060800232	20060608	00232	WP  	2006	6	8	CA051208012      	1	20051205	G	6320	A6502	BOLT            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2200 							BOLT WAS SENT FOR NDT AS PART OF THE 2200HR AIRCRAFT OVERHAUL.  THE CRACK WAS FOUND ON THE MOUNTING TANGS THAT ARE PART 	OF THE BOLT HEAD.  THIS CRACK COULD NOT BE SEEN BY A NORMAL VISUAL INSPECTION.  THIS IS NOT THE FIRST TIME THIS BOLT HAS	 BEEN FOUND CRACKED DURING THE 2200 HR OVERHAUL.				1	G	7	1 	3O	3	O		H11NM   	E295				 
2006060800233	20060608	00233	CE  	2006	6	8	CA051209001      	1	20051208	G	5630	1014301833	WINDOW          	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					EMERGENCY DOOR	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											LEVELING OFF AT 19000 FT, CREW HEARD FAINT CRUNCH SOUND WITHIN CABIN.  PAX SITTING AT EMERG EXIT NOTIFIED FLT CREW OF LO	UD GUNSHOT TYPE NOISE.  THEN NOTICED OUTER WINDOW PANE FOR EMERG EXIT CRACKED.  CREW PROMPTLY REDUCED THEIR ALT TO 11000	 FT AND DIALED CABIN UP TO OBTAIN CABIN PRESS DIFF OF APPROX 1.0 PSI.   SAFELY CONTINUED TO DESTINATION.   RETURN FLT WA	S CONDUCTED UNPRESSURIZED.  MX INSPECTED OUTER SURFACE OF WINDOW AND FOUND IT DELAMINATED AND THE CRACK IN A MOON SHAPE 	FROM TOP TO BOTTOM FACING FWD.  CRACKED PORTION PROTRUDING SLIGHTLY OUTWARDS.  ONCE REMOVED, INNER SURFACE OF WINDOW FOU	ND TO BE INTACT.  NO DAMAGE FOUND ON OUTER SURFACE OF WINDOW THAT MIGHT INDICATE WHERE CRACK MIGHT HAVE ORIGINATED.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061900180	20060619	00180	EU  	2006	6	19	CA051209002      	1	20051208	G	7500	350A72100509	PIPE            			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					BLEED AIR	MISLOCATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BLEED AIR HEATER PIPE WAS DISCOVERED LOOSE DURING A WINTER TEAR DOWN INSPECTION.  THE CRIMPED COLLAR CAME LOOS	E AND ALLOWED THE PIPE TO SLIDE OUT OF THE B-NUT. (TC NR 20051209002)					1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2006061900182	20060619	00182	GL  	2006	6	19	CA051209003      	2	20051203	G	7200		ENGINE          	ALLSN       							ALLSN 	AE300 	AE3007A     	 	GL  					LEFT	MALFUNCTIONED   	W				B				EMER. DESCENT           				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			14400					CAE310011			(CAN) A/C WAS IN ROUTE TO DESTINATION, WHEN 20 MINUTES INTO THE FLIGHT, THE CAPTAIN NOTICED THAT EICAS INDICATIONS FLICK	ERED OFF THEN ON.  LT ENGINE THEN SHUTDOWN UNCOMMANDED AND CREW RECEIVED NUMEROUS EICAS MESSAGES. (TC NR 20051209003)										4	F			TE6CH				 
2006060800234	20060608	00234	EU  	2006	6	8	CA051209004      	1	20051130	G	2913	4005303	PUMP            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HYDRAULIC SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				330  							HYD NR 1 ANNUNCIATOR ILLUMINATED AFTER TAKEOFF.  HYDRAULIC PRESSURE WAS LOST ON SYSTEM 1.  QUANTITY WAS SUFFICIENT AND S	TANDBY SYSTEM WORKED NORMALLY.  HYD NR 1 SYSTEM PRESSURE PUMP HAS BEEN REPLACED, P/N 40053-03, S/NOFF AH-16041A, S/NON A	H-16086A.  FILTER INSPECTED AND GROUND TEST CARRIED OUT OK.				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2006061900183	20060619	00183	SW  	2006	6	19	CA051209005      	1	20051201	G	2750	510003357	BRACKET         			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	FLAP PULLEY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8569 								(CAN) LT FLAP PULLEY ASSY UPPER BRACKET FOUND CRACKED AT FORWARD IB LOWER CORNER RELIEF.  A SECOND AC IN COMPANY FLEET O	F 6 FOUND CRACKED IN SAME LOCATION. (TC NR 20051209005)					1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
2006061900184	20060619	00184	SW  	2006	6	19	CA051209006      	1	20051209	G	5210	2330270501	ANGLE           			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3804 								(CAN) REENFORCING ANGLES ON INSIDE OF DOOR AT UPPER AND LOWER HINGES FOUND CRACKED. (TC NR 20051209006)						1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
2006061200268	20060612	00268	GL  	2006	6	12	CA051211001      	2	20051122	G	7321	23034702	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA				1865 				CAE822633			PILOT LANDED ON REMOTE LEASE SITE AND UPON LOWERING THE COLLECTIVE THE ENGINE DID AN UNCOMMANDED DECEL TO 75 PERCENT.  P	ILOT ROLLED THROTTLE BACK TO IDLE AND TRIED TO ROLL THROTTLE BACK TO 100 PERCENT.  ENGINE WOULD NOT RETURN PAST 75 PERCE	NT.  MAINTENANCE WAS CALLED AND FUEL CONTROL WAS REPLACED.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006060800235	20060608	00235	CE  	2006	6	8	CA051211002      	1	20051021	G	2720	04115262	BAR             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7299 								DURING A 100 HR INSPECTION OF THE CESSNA 152, THE REAR RUDDER BAR WAS FOUND TO HAVE A HOLE WORN THROUGH IT ON THE CO-PIL	OT SIDE.  THE PLASTIC CENTER CONSOLE IS ATTACHED TO THE RUDDER PEDAL COVERS WITH SCREWS.  IF THE SCREWS ARE TOO LONG, TH	EY WILL WEAR INTO THE RUDDER BAR OVER TIME.  THIS COULD EVENTUALLY CAUSE THE RUDDER BAR TO FAIL CAUSING THE LOSS OF RUDD	ER CONTROL.  THIS WAS THE SECOND OF TWO IDENTICAL FINDINGS ON TWO DIFFERENT 152 AIRPLANES WITH APPROX 7300 AIRFRAME HOUR	S.		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006060800288	20060608	00288	EA  	2006	6	8	CA051212001      	1	20051208	G	2400	D1822A	RELAY           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						OVERHEATED      	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											AT FL230, ALL THE TUBES EICAS AND PFD'S WENT BLANK THEN FLASHED ON AND OFF. NEXT AC BUS1 CAUTION MESSAGE. LEFT AUTO TRAN	SFER FAIL AND GENERATOR 1 OFF CAUTION.  COCKPIT HAD ELECTRICAL OVERHEATING SMELL.  NO SMOKE VISIBLE IN COCKPIT OR CABIN.	  COMPLETED THE QRH FOR PREVIOUS MESSAGES ALSO STAB TRIM AND MACH TRIM CAUTION MESSAGES APPEARED AND CLEARED BY FOLLOWIN	G QRH.  EFIS COMP MON WITH IAS YELLOW ON AIRSPEED.  AUTOPILOT NOSE UP TRIM CAUTION AND WOULD NOT CLEAR PER QRH.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006060800379	20060608	00379	WP  	2006	6	8	CA051212002      	1	20050814	G	6210	2253110104	BLADE           			HILLER	UH12  	UH12D       	4360118	WP  										MAIN ROTOR	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA			6594 	544  							A SEVERE VERT VIBRATION OCCURRED WHEN HELICOPTER ENTERED A SPRAY RUN.  VIBRATION CEASED JUST BEFORE LANDING ON A NEARBY 	ROAD.  ROTOR HEAD WAS REMOVED AND NDT'D FOR CRACKS, NONE FOUND.  HELICOPTER WAS RE-ASSEMBLED, ALL FLT CONTROLS WERE CHEC	KED FOR DAMAGE AND SECURITY, AND TEST FLOWN OK UNTIL AUTO-ROTATION WAS ENTERED.  VERT VIBRATION RE-OCCURRED, BUT DISAPPE	ARED WHEN POWER APPLIED.  MAIN ROTOR BLADES WERE CHECKED AND ADJUSTED FOR TRACK AND BALANCE AND NEXT FLT, VERT VIBRATION	 DEVELOPED WHILE UNDER PWR, AT APPROX 40 KNOTS IAS.  HELICOPTER  IMMEDIATELY LANDED ON THE ROAD BELOW, WITH A TAILROTOR 	STRIKE RESULTING.  HIGH TIME MAIN ROTOR BLADES HAVE BEEN RETIRED AND TAILROTOR SUDDEN STOPPAGE INSPECT IN PROGRESS.	1	G	7	1 	3O				4H10    					 
2006060800289	20060608	00289	WP  	2006	6	8	CA051212003      	1	20051211	G	2510	PS400010	ELT             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					CABIN	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			400  								AIRCRAFT WAS IN A TURN WHEN THE ELT WENT OFF.  THE PILOT STATED THE TURN WAS NOT OUTSIDE OF A NORMAL MANOUVER.  ELT WAS 	RESET BY REMOTE SWITCH IN THE COCKPIT.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062100008	20060621	00008		2006	6	21	CA051212004      	2	20051204	G	7261		ENGINE          			BOMBDR	BD700 	BD7001A10   	1390006	GL  											CONTAMINATED    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			1675 	1675 							(CAN) APPROX 20 MINUTES INTO THE FLIGHT, DURING CRUISE AT FL450, THE CREW REPORTED THAT A RED EICAS (L ENG OIL PRESS LOW	) MESSAGE POSTED ALONG WITH THE LT OIL PRESSURE INDICATION TURNING RED AND READING 26 PSI. THE CREW FOLLOWED THE AFM CHE	CKLIST AND SHUTDOWN THE LT ENGINE AND RETURNED TO THE AIRPORT.  A BORESCOPE INSPECTION WAS SUBSEQUENTLY PERFORMED, AND N	UMEROUS FIBERS SIMILAR IN APPEARANCE TO A SHOP RAG WERE FOUND LODGED IN SEVERAL SCAVENGE SCREENS. THE ENGINE WAS REMOVED	 AND REPLACED WITH A LOANER AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20051212004)		2	L	7	2 	4F			RT	T00003NY					 
2006060800380	20060608	00380	WP  	2006	6	8	CA051212005      	1	20051212	G	6510	C04111	BEARING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					TAIL ROTOR	SPUN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			180  								DURING INSPECTION, THE TAIL ROTOR DRIVESHAFT DAMPER BEARING WAS NOTED TO HAVE MOVED ON THE TAIL ROTOR DRIVE SHAFT.  THE 	WITNESS MARKS WERE MOVED ABOUT .250".  THE BEARING FEELS FINE, AND THERE DOES NOT APPEAR TO BE ANY OTHER PROBLEMS.  ROBI	NSON HELICOPTERS DOES NOT ALLOW ANY MOVEMENT BETWEEN THE BEARING AND THE DRIVE SHAFT.  THE ASSEMBLY IS BEING REMOVED AND	 RETURNED TO THE FACTORY.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061200270	20060612	00270	GL  	2006	6	12	CA051213002      	1	20051209	G	3244	382K032	TIRE            			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											A/C DEPARTED, NR 2 TIRE BLOW OUT ON LANDING.  SHORTLY AFTER LANDING, CREW REPORTED LOST NR 2/3 HYD SYSTEMS.  AS A RESULT	 OF THIS, LOST ALL BRAKING AND STEERING AND RT T/R WAS STUCK IN DEPLOYED POSITION.  A/C DRIFTED TO RT AND EXITED RUNWAY 	INITIALLY ONTO A HIGH SPEED TAXIWAY, THEN ON TO GRASS, A/C CAME TO A STOP ON GRASS SEVERAL YARDS FROM RUNWAY.  AFTER EXI	TING A/C, CREW FOUND NR 2 TIRE BLOWN,  HYD LINES AND ELECTRICAL HARNESS SEVERED.  THE INBD FLAP ACT BROKEN IN TWO AND DA	MAGE TO AFT W/W AREA.		2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2006060800381	20060608	00381	NE  	2006	6	8	CA051213003      	1	20051017	G	7921	W200PP	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					OIL COOLER	SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M			OVER TEMP                 			AP	APPROACH       	1			CA											NR 2 ENGINE OIL OVER TEMPERATURE WAS OBSERVED BY CREW DURING ROUTINE FLIGHT.  SINGLE ENGINE LANDING WAS EXECUTED AT NEAR	EST AIRPORT.  UPON INSPECTION IT WAS APPARENT THAT NR 2 ENGINE OIL COOLER BLOWER FAILED.  THE REAR BEARING SEIZED, BLOWE	R SHAFT SHEARED NEAR THE FRONT BEARING.  IT WAS ALSO APPARENT THAT A SLEEVE REPAIR OF REAR BEARING CAGE FAILED (SLEEVE V	ISIBLE ON OUTER RACE OF THE BEARING).  NR 2 ENGINE AND OIL COOLER BLOWER REPLACED, A/C RETURNED TO SERVICE.  THE BLOWER 	ASSEMBLY TSO=727.7, BEARING TSN=UKN.		1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006061200271	20060612	00271	NE  	2006	6	12	CA051213004      	2	20050715	G	8530	126741	CYLINDER        			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	SEPARATED       	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA				84   							ON DAILY INSPECTION, FOUND OIL SPATTERING ON SIDE OF NR 5 CYLINDER AND EXCESSIVE STAINING AT BARREL TO SLEEVE JUNCTION O	F NR 6 CYLINDER.  NOTICED EXCESSIVE CLEARANCE BETWEEN COOLING FIN ON BARREL AND CYLINDER HEAD OF NR 6 CYLINDER, INDICATI	NG THAT CYLINDER HEAD WAS SEPARATING FROM THE BARREL. REMOVED NR 6 CYLINDER AND INSTALLED SERVICEABLE REPLACEMENT CYLIND	ER.  CYLINDER S/N 25997 RETURNED TO O/H AGENCY, AWAITING REPORT.			1	L	7	2 	3R	3	R		A765    	5E1				 
2006060800382	20060608	00382	EA  	2006	6	8	CA051213005      	2	20051211	G	8530	75184	CYLINDER HEAD   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	CRACKED         	W				D				RETURN TO BLOCK         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA			1952 	1952 							CRACKED FROM TOP SPARK PLUG TO BOTTOM SPARK PLUG.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006060800383	20060608	00383	CE  	2006	6	8	CA051213006      	1	20051213	G	3080	1013800159	HOSE            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LT BRAKE DEICE	BURST           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2099 								DURING DAILY INSPECTION, THE AME FOUND THE LT BRAKE DEICE HOSE (P/N 101-380015-9) BURST NEAR UNION (P/N 832-12D).						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006060800384	20060608	00384	SW  	2006	6	8	CA051213007      	1	20051208	G	2435	23079010	STARTER GEN     			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				225  							GENERATOR DROPPED OFF LINE, GENERATOR RESET AND WAS FINE FOR REMAINDER OF LEG.  UPON LANDING GENERATOR DROPPED OFF LINE 	AND AGAIN WAS RESET WITH NO FURTHER PROBLEMS.  UPON FURTHER INVESTIGATION MAINTENANCE FOUND WHAT HAD THE APPEARANCE OF R	EMNANTS OF A BEARING CAGE AS WELL AS BRUSH PIECES.  STARTER GENERATOR WAS REMOVED AND SERVICEABLE STARTER GENERATOR INST	ALLED.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2006060800385	20060608	00385	NM  	2006	6	8	CA051213008      	1	20051213	G	3230	38805	VALVE           			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					GND SPOILER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			9993 								A/C HAD AN AIR TURNBACK AFTER TAKEOFF FROM YYZ. PIREP A43921 READS "LANDING GEAR DOES NOT RETRACT WHEN LANDING GEAR LEVE	R MOVED TO UP POSITION".  MAINTENANCE FOUND THE GROUND SPOILER INTERLOCK VALVE RIGGED TO IT'S FAR LIMIT.  THE INTERLOCK 	VALVE WAS RIGGED IAW AMM 26-62-61, GEAR SWINGS WERE CARRIED OUT WITH NO FAULTS FOUND AND THE AIRCRAFT WAS RETURNED TO SE	RVICE.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006061200312	20060612	00312	CE  	2006	6	12	CA051213009      	1	20051209	G	3260	1003810061	UPLOCK SWITCH   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	NLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											A/C SCHEDULED DEPARTURE AND DESTINATION.  AFTER T/O CREW SELECTED GEAR UP AND THEY HAD THE INTRANSIT LIGHT STAY ON (GEAR	 HANDLE LIGHT).  CREW CALLED MX FROM THE AIR AND CYCLED GEAR.  CYCLING OF GEAR DID NOT MATTER.  MX AND CREW DECIDED IT W	OULD BE BEST TO RETURN TO ITS MAIN MX BASE. CREW DID HAVE ALL THREE GREEN WITH GEAR DOWN THEREFORE KNEW IT WAS NOT A PRO	BLEM WITH AN UNSAFE LANDING.  CREW OFF LOADED PAX`S AND RETURNED A/C TO HANGAR.  MX JACKED A/C AND T/S SYSTEM.  T/S REVE	ALED THAT CONTACTS WITHIN THE UPLOCK SWITCH WERE CLOSED RESULTING IN THE IN TRANSIT LIGHT STAYING ON.  MX REPLACED N/G U	PLOCK SWITCH AND CARRIED OUT OP CHECKS.  ALL CHECKED OK. A/C WAS RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006061900208	20060619	00208	EU  	2006	6	19	CA051214001      	1	20051213	G	2424	51539002B	GENERATOR       			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	AC REGULATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) IAW AMM 24-30-00 501 DC GENERATION-ADJUSTMENT/TEST.  GENERATOR VOLTAGE MUST BE WITHIN 0.3 VOLTS OF EACH OTHER.  WH	EN REPLACING COMPONENTS IN THE GENERATOR SYSTEM, A CHECK OF THE GCU'S VOLTAGE IS RECOMMENDED AS NUMEROUS HOURS OF TROUBL	ESHOOTING AND PARTS REPLACEMENT WILL OCCUR.  (TC NR 20051214001)				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2006061300014	20060613	00014	EA  	2006	6	13	CA051214002      	2	20051207	G	8520	13F17785	CRANKSHAFT      			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  					RT ENGINE	BROKEN          	W				A				UNSCHED LANDING         				G	Y		MULTIPLE FAILURE          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA				966  				RL352361A			DURING LAST LEG OF THE DAY, 10 MINUTES FROM LANDING, A WOOSHING NOISE WAS HEARD FROM THE RT ENGINE, OIL PRESSURE, RPM, F	UEL FLOW AND VACUUM INDICATIONS FOR THE RT ENGINE WENT TO ZERO.  MANIFOLD PRESSURE WENT TO 39".  THE ENGINE WAS SHUT DOW	N AND PROP FEATHERED.  THE FLIGHT FINISHED ITS FINAL AND LANDED UNEVENTFUL.  ON THE GROUND, THE PROP COULD BE MOVED WITH	OUT RESISTANCE, SPARK PLUGS REMOVED AND A VISUAL OF THE PISTONS NOT MOVING WITH THE PROP TURNING.  ENGINE WAS REMOVED AN	D SENT TO OVERHAUL AT AVIATION TECH CONSULTING FOR FURTHER TEAR DOWN.		1	L	7	2 	3O	3	O		A12SW   	E14EA				 
2006061300015	20060613	00015	NM  	2006	6	13	CA051214003      	1	20051207	G	2910	82970410119	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	CHAFED          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											THE NR 2 HYDRAULIC INDICATION WAS SHOWING "0"  WHILE THE QUANTITY DECREASING.  AN ALTERNATE GEAR EXTENSION WAS PERFORMED	 AND THE AIRCRAFT HAD LANDED SAFELY WITHOUT INCIDENT.  MAINTENANCE FOUND THAT THE EDP PRESSURE LINE WAS LEAKING IN THE N	ACELLE DUE TO CHAFFING.  THE LINE WAS REPLACED.  ALSO, THE ENGINE DRIVEN PUMP WAS REPLACED AS A PRECAUTION.  THE AIRFRAM	E HOURS WERE 45227:27, THE AIRFRAME CYCLES WERE 54992.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300016	20060613	00016	CE  	2006	6	13	CA051215001      	1	20051206	G	3233	99810057651	ACTUATOR        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER T/O, GEAR WAS SELECTED UP AND CLUNK WAS HEARD, T/O CONTINUED TO SAFE ALT AND WAS VISUALLY CONFIRMED THAT RT GEAR H	AD NOT RETRACTED.  THE GEAR WAS RECYCLED DOWN 3 GREEN LIGHTS CONFIRMED ALL GEAR DOWN AND LOCKED.  A/C RETURNED TO AIRPOR	T AND LANDED W/O FURTHER INCIDENT.  FURTHER INVESTIGATION BY MX REVEALED THAT RT GEAR ACTUATOR HAD FAILED INTERNALLY.  A	CTUATOR WAS REPLACED AND A/C RETURNED TO SERVICE.  FAILED ACTUATOR IS BEING RETURNED TO THE OVERHAUL FACILITY FOR FURTHE	R INVESTIGATION, AT OUR REQUEST, THE FAA WILL BE SUPERVISING THE DISASSEMBLY OF THE ACTUATOR.  THIS ACTUATOR HAD 2339 LA	NDING SINCE OVERHAUL.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061300017	20060613	00017	GL  	2006	6	13	CA051215002      	1	20051212	G	2752		SEAL            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					FLAP ACTUATOR	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			858  								PILOT REPORTED FLAPS WOULD NOT RETRACT.  INSPECTION FOUND SEAL MIGRATED INTO FLAP SWITCHES.  RE-GLUED PER DIAMOND INSTRU	CTIONS.  THIS UNIT HAD BEEN RE-GLUED TWICE BEFORE.  DIAMOND IS LOOKING INTO A MECHANICAL SEAL RETENTION SOLUTION, AND HA	S OFFERED TO CONTINUE TO REPLACE THE UNITS UNDER WARRANTY.  NEW UNITS HAVE BEEN INSTALLED IN THE PAST AND STILL FAIL.  O	CCURRENCES SEEM TO BE CONCENTRATED BETWEEN NOVEMBER AND MARCH, THIS WOULD INDICATE A COLD WEATHER OPERATION PROBLEM.			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006061300019	20060613	00019	WP  	2006	6	13	CA051216001      	1	20051212	G	2910	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  						LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			805  								HYDRAULIC LEAKS ON VARIOUS COMPONENTS IN THE SYSTEM.  3 SERVOS WERE REPLACED DUE TO LEAKING AROUND PILOT VALVES.  HYDRAU	LIC PUMP D500-1 (TSN 805.3) WAS ALSO REPLACED BECAUSE OF LEAKING.  DUE TO THE HYDRAULIC LEAKS ON THE FORWARD SERVOS, THE	 RUBBER TRANSMISSION WERE REPLACED.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061300020	20060613	00020	NE  	2006	6	13	CA051216002      	1	20051215	G	6320	7635109105068	NOZZLE          			SKRSKY	S76   	S76A        	8143006	NE  										M/R GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THESE TWO OIL JET ASSEMBLIES WERE RECEIVED NEW AND CHECKED FOR CORRECT ORIENTATION OF THE OIL DELIVERY HOLE. BOTH UNITS 	FAILED WHEN COMPARED TO A USED ASSEMBLY.  THIS OIL JET SPRAYS ON TO THE GEAR MESH OF THE INPUT BEVEL PINION P/N 76351-09	132-102 AND BEVEL GEAR P/N 76351-09011-105 AND -106.  THERE ARE 2 NOZZLE ASSEMBLIES IN EACH MAIN GEARBOX P/N 76351-09500	-043/044.			1	G	7	2 	3U				H1NE    					 
2006061300021	20060613	00021	CE  	2006	6	13	CA051216003      	1	20051215	G	3320	2K40D10	RESISTOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					CABIN LIGHTS	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA											DURING ROUTINE INSPECTION, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED.  INSULATION ABOVE THE RESISTOR WAS SCOR	CHED AND BURNED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006080400001	20060804	00001	NM  	2006	8	4	CA051219001      	1	20051212	G	5411	C5WM126238	FRAME           			DHAV  	DHC5  	DHC5A       	2803018	NM  										NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11986								(CAN) DURING NOV 26/04 SB 5/316 INSPECTION 4 CRACKS WERE FOUND, 1 CRACK RT OB, 2 CRACKS LT OB AND 1 CRACK LT IB FRAMES A	T STA 123.10 IN THE NACELLE.  RD5-54-017 WAS INCORPORATED TO ALL 3 AFFECTED AREAS.  DURING DEC 11/05 SB 5/316 INSPECTION	 THE NR OF CRACKS HAD RISEN TO 11 WITH 2 CRACKS RT IB, 2 CRACKS RT OB, 5 CRACKS LT IB AND 2 CRACKS LT OB.  RD5-54-017 HA	S NOT BEEN INCORPORATED INTO THE NEW CRACKED AREA YET. WE ARE ATTEMPTING TO GATHER INFORMATION AS TO HOW MANY CRACKS ARE	 ALLOWABLE BEFORE THE FRAMES MUST BE CHANGED OUT. (TC NR 20051219001)		2	H	7	2 	4T			RT	        					 
2006061300024	20060613	00024	NM  	2006	6	13	CA051219002      	1	20051212	G	3231	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					RT MLG DOOR	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											RT MLG FAILED TO RETRACT.  MLG SELECTOR LEVER SWITCHED TO THE UP POSITION, GEAR RETRACTED NORM, BUT ON RT MLG DOOR STAYE	D OPEN.  WHEN MLG SELECTOR LEVER IS SWITCHED BACK TO DOWN POSITION, RT MLG DOOR CLOSE AND STAYED IN THIS POSITION.  NLG 	AND LEFT MLG EXTENDED NORMAL.  RIGHT MLG STAYED IN UP AND LOCKED POSITION.  EXTENDED RIGHT MLG WITH THE ALTERNATE SYSTEM	 DOOR OPENED NORMAL AND GEAR FELL DOWN.  AFTER APPROX 5-10 SECONDS, DOORS START TO CLOSE.  BOTH MLG DOOR WERE HIT HARD B	Y MLG.  MLG DOORS WERE DAMAGED.  FOR INFO, INHIBIT SWITCHED WAS SET TO INHIBIT, BOTH ALTERNATE RELEASE DOORS WERE OPENED	.  RT MLG DOOR SOLENOID SEQUENCE VALVE REPLACED.  AIRCRAFT RETURNED TO SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006061300059	20060613	00059		2006	6	13	CA051219004      	4	20051122	G	2300	5190601	CIRCUIT CARD    			EMB   	120   	EMB120ER    	3260203	SO  	PWA   	118   	PW118       	 	NE  	HAMSTD	14RF	14RF9       	NE  	AUDIO CONTROL	CORRODED        	W				O				OTHER                   				O		O	OTHER                     		OTHER                     	AP	APPROACH       	1			CA			6913 	2572 		321					ON APPROACH, A LOAD SIDE TONE WAS HEARD IN THE HEADSETS.  PILOTS WERE UNABLE TO ESTABLISH COMMUNICATION WITH ATC DUE FOR	 FEEDBACK HUM NOISE GENERATED IN AUDIO SYSTEM, AND ALSO EMERG SELECTION IN AUDIO CONTROL PANEL WAS INOP.  TROUBLESHOOTIN	G FOUND THE AUDIO REMOTE ELECTRONIC UNIT (REU) CIRCUIT CARD NR 1 (P/N 5190-60-1) CONNECTORS CONTACT TO MAIN MOTHERBOARD 	WAS HEAVY CORRODED DUE THE PROTECTIVE COATING AT CIRCUIT BOARD WAS NOT APPLIED AS PER MIL 1-46058 AS STATED IN COMPONENT	 MM, THUS SHORTING OUT ALL SIGNALS AND INDUCING FEED BACK NOISES.  THIS REPAIRED UNIT WAS RECEIVED FROM THE FAA REPAIR S	TATION AVTECH CORPORATION NR IG6R621N ON DECEMBER 2003 AND INSTALLED ON THE AIRCRAFT WITHIN THE SAME MONTH.	2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2006061300075	20060613	00075		2006	6	13	CA051219005      	4	20051204	G	3457	KLN90B	GPS             			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  	HARTZL	HCC3Y	HCC3YN      	GL  	COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											THE GPS SYSTEM WENT THROUGH NORMAL SELF-TEST AND DID NOT FLAG AS INOP.  HOWEVER, THE TRACKS DISPLAYED BETWEEN WAYPOINTS 	WERE INCORRECT.  UPON FURTHER INVESTIGATION THE SYSTEM DATE WAS DISPLAYED AS APR 20, 1986 AND COULD NOT BE CORRECTED ON 	ANY SYSTEM OR START-UP PAGE WHILE IN FLIGHT.  POST-FLIGHT DISCUSSION WITH THE MANUFACTURER REVEALED THAT THIS PROBLEM WA	S DUE TO THE 1024 WEEK DATE ROLLOVER OF GPS SYSTEMS.			1	L	7	2 	3O	3	O		A8EA    	E19EA	5	C	P25EA	 
2006061300080	20060613	00080	CE  	2006	6	13	CA051220001      	1	20051219	G	3246	15802101	SEAL            	PARKERHANFIN		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BEARING CAP	LEAKING         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			143  			1474					ON LANDING, OBSERVED NO BRAKING ACTION EVEN THOUGH BRAKE PEDALS HARD.  EMERG BRAKING UTILIZED & A/C CLEAR OF RUNWAY, NOR	MAL BRAKING ACTION RETURNED.   NO FAULT LIGHTS INDICATING  ANTI-SKID FAILURE.  MX NOTICED UPON REMOVING LT WHEEL BEARING	 CAP, ANTI-SKID DRIVE COUPLING TANGS SHEARED OFF.  WATER WAS ALSO OBSERVED DRAINING OUT OF WHEEL SPEED TRANSDUCER HOUSIN	G.   CLEAR THAT WATER IN AXLE HOUSING FROZE WOULD NOT ALLOW WHEEL SPEED TRANSDUCER TO ROTATE. THIS WOULD SHOW ANTI-SKID 	SYSTEM THAT LT WHEEL WAS IN A SKID AND SYSTEM WOULD NOT ALLOW BRAKE PRESSURE TO BE APPLIED TO RT BRAKE.  A NEW TRANSDUCE	R WAS INSTALLED ON LT WHEEL, COMPANY CONVENIENCE.  RT AXLE HOUSING FOUND FREE OF WATER.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006061300083	20060613	00083	SW  	2006	6	13	CA051220002      	1	20051216	G	5532		SKIN            		407023801109	BELL  	407   	407         	1182206	SW  										VERTICAL STAB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A SCHEDULED DESTRUCTIVE TEST, FOUND SOME STABILIZER SKINS DAMAGED WITH TOOL MARKS AT SOME INSERT HOLES.						1	G	7	1 	3U			O	H2SW    					 
2006061300084	20060613	00084	SW  	2006	6	13	CA051220003      	1	20051216	G	5532		SKIN            			BELL  	206   	206L4       	1182110	SW  										VERTICAL STAB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A SCHEDULED DESTRUCTIVE TEST, FOUND SOME STABILIZER SKINS DAMAGED WITH TOOL MARKS AT SOME INSERT HOLES.						1	G	7	1 	3U			NC	H2SW    					 
2006061300085	20060613	00085	CE  	2006	6	13	CA051220004      	1	20051212	G	7120	05510171	MOUNT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9933 								DURING INSPECTION (ANNUAL), CRACK FOUND ON ENGINE MOUNT.  MOUNT REMOVED FOR REPAIR AND RE-INSTALLED FOLLOWING REPAIR.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006061300086	20060613	00086	CE  	2006	6	13	CA051220005      	1	20051202	G	2720	07436082	ROD             			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	RUDDER PEDAL	BROKEN          	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											DURING TAXI (AFTER HARDWIND DURING THE DAY WITH THE AIRCRAFT PARKED WITH TAIL TO THE WIND), AT THE END OF THE DAY THE PI	LOT HAD NO CONTROL ON PEDALS FOR TAXIING.  THE PILOT SIDE RT PEDAL WAS JAMMED IN PLACE.  AFTER EVALUATION OF PROBLEM, FO	UND A BROKEN ROD END FROM ROD ASSEMBLY 0743608-2 ON SKIN UNDER FLOOR, PILOT SIDE RT PEDAL ATTACHMENT TO RUDDER CABLE AND	 STEERING CONTROL BELLCRANK.  THE BROKEN ROD WAS FOUND STOCKED BETWEEN RIB AND PEDAL.			1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2006061900211	20060619	00211	EU  	2006	6	19	CA051220006      	1	20051206	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					MAIN ROTOR	INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			HO	HOVERING       	1			CA			5445 	1691 							(CAN) PILOT REPORTED STIFF RAPID LT MOVEMENT AND COLLECTIVE STICK RISING. AIRCRAFT TESTED ON HYDRAULIC BENCH AND WE FOUN	D THAT LT SERVO WAS SLOWER TO RETRACT.  THE AIRCRAFT WAS OPERATING CORRECTLY AFTER AFFECTED SERVO WAS REPLACED.  THIS PR	OBLEM WAS IMPOSSIBLE TO CREATE UNDER NORMAL FLIGHT CONDITIONS. PILOT REPORTED THE FAULT DURING LANDING IN SNOW, DOING RA	PID UP-DOWN MOTION TO STABILIZE THE AIRCRAFT.  THE AFFECTED SERVO HAD 110 HOURS REMAINING FOR ITS SCHEDULED OVERHAUL.  (	TC NR 20051220006)		1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2006061300088	20060613	00088	CE  	2006	6	13	CA051220007      	1	20051207	G	3231	08411066	BELLCRANK       			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	MLG DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			9696 	9696 							AIRCRAFT LAND GEAR EXTENSION CARRIED OUT AS NORMAL ON AIRPORT APPROACH.  ON THE GROUND, THE PILOT NOTICED THAT THE RIGHT	 MAIN GEAR INBOARD DOOR WAS NOT CLOSED.  UPON FURTHER INSPECTION BY AN AME, RT GEAR DOOR RETRACTION SYSTEM BELLCRANK P/N	 0841106-6 WAS FOUND TO HAVE FAILED COMPLETELY AND HAD BROKEN IN TWO.  A NEW BELLCRANK HAS BEEN INSTALLED AND THE GEAR S	YSTEM HAS BEEN CHECKED FOR SIGNS OF STRESS, RUBBING OR INTERFERENCE.  ALL WITH NO FAULTS FOUND.  SEVERAL GEAR RETRACTION	 TEST HAVE BEEN CARRIED OUT.  THE LEFT GEAR DOOR MATCHING BELLCRANK HAS BEEN CHECKED FOR CRACKS USING  MAGNAFLUX FLUORES	CENT PENETRANT.  THE FAILED BELLCRANK DID SHOW SIGNS OF A WORKING FATIGUE CRACK AND CONSEQUENT FAILURE.	1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
2006061300089	20060613	00089	CE  	2006	6	13	CA051220008      	1	20051220	G	3245	302039402	TUBE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG TIRE	CUT             	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			34   								WHEEL ASSY P/N 101-8002-3 ASSEMBLED USING GOODYEAR TIRE P/N 301-392-641 AND TUBE P/N 302-039-402.  AFTER 34 HRS TO 250 H	RS OF OPERATION, TUBES WOULD FAIL. PERIODIC AIR PRESSURE TESTING WOULD REVEAL A TIRE PRESSURE LOSS OF 10 LBS.  THE TUBE 	WAS REMOVED AND CUTS WERE EVIDENT.  THIS IS THE 7TH TIME THIS HAS HAPPENED IN 6 WEEKS PRIOR.  THE AREA THAT THE TUBES AR	E CUT ARE ADJACENT TO A MANUFACTURES STICKER ON THE INSIDE OF THE TIRE.			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061300090	20060613	00090	EA  	2006	6	13	CA051220009      	2	20051220	G	7414	10400075	HOUSING         	CONT        		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			492  			E03LA035					MAGNETO WAS REMOVED FROM THE AIRCRAFT FOR ROUTINE INSPECTION.  MOUNTING LUG FOUND CRACKED DURING 500HR MAGNETO INSPECTIO	N.  POSSIBLE BAD CASTING, OR OVERTORQUE ON HOLD DOWN NUT DURING INSTALLATION OF MAGNETO AT THE FACTORY.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061300169	20060613	00169	EA  	2006	6	13	CA051220010      	2	20051212	G	8530		PISTON RING     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CYLINDER	WORN            	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			1583 	1583 							IN CRUISE, PILOT NOTICED DROP IN OIL PRESSURE AND CLIMB IN OIL TEMPERATURE ON THE LEFT ENGINE.  A TRACE OF OIL APPEARED 	ON THE COWLING.  THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE DETERMINED THAT THREE C	YLINDERS REQUIRED REPLACING DUE TO EXCESSIVE LEAKAGE PAST THE RINGS.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061300179	20060613	00179	SW  	2006	6	13	CA051220011      	1	20051213	G	6410	206016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										TAIL ROTOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			703  								AS THE ENGINEER WAS CONDUCTING A DAILY CHECK WITH THE PILOTS, IT WAS NOTED UNUSUAL AMOUNT OF MOVEMENT OF THE T/R BLADE T	O THE HUB ASSEMBLY.  FURTHER INVESTIGATION IT WAS REVEALED THAT THE STAKED SLEEVE ONTO THE T/R BLADE AND THE SPHERICAL F	EATHERING BEARING WAS LOOSE.  THE LOOSENESS WAS BETWEEN THE SLEEVE AND THE T/R BLADE.  THE SPHERICAL BEARING WAS A OLDER	 P/N BEARING THE BLADE WAS SENT AWAY FOR REPAIR.			1	G	7	1 	3U				H2SW    					 
2006061300180	20060613	00180	CE  	2006	6	13	CA051221001      	1	20051215	G	2520		HINGE           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	SEAT BACK	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											UPON INSPECTION, MAINTENANCE PERSONNEL DISCOVERED SEVERAL PLACES WHERE NAILS AND LOCK PINS WERE USED IN PLACE OF THE PRO	PER NAS561 PINS.  SAFETYING METHOD WAS "BENT OVER" INSTEAD OF LOCK WIRE.  LOCATIONS WERE TRIM WHEEL, SEAT BACK HINGE POI	NTS AND SEAT LOCK MECHANISM.  HAVE PICTURE OF UNAPPROVED PARTS TO ATTACH TO FILE.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P21EA	 
2006061300181	20060613	00181	SO  	2006	6	13	CA051221002      	1	20051208	G	5740		ATTACH BRACKET  			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											REINFORCEMENT STRAP AT REAR SPREADER BAR ATTACHMENT LUG; INTERGRANULAR CORROSION DESTROYED PART FROM INSIDE OUT RESULTIN	G IN LOOSE FASTENER.					1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
2006061300182	20060613	00182	SO  	2006	6	13	CA051221003      	1	20051202	G	5313		LONGERON        			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	MCAULY	1A175	1A175GM     	GL  	FUSELAGE	ROTTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPPER RT LONGERON AT TAIL WAS ROTTED.  TUBING WAS REPLACED AS REQUIRED.						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P857	 
2006061300183	20060613	00183	EA  	2006	6	13	CA051221004      	2	20051206	G	8520	13F17760	CRANKSHAFT      								LYC   	O540  	TIO540R2AD  	41532	EA  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA				966  							CRANKSHAFT FAILED AT THROW BETWEEN NR 2 MAIN JOURNAL (AS NUMBERED BACK TO FRONT) AND NR 4 CRANK PIN.  CRACK STARTED AT R	ADIUS OF MAIN JOURNAL AND PROPAGATED APPROX 70% THROUGH THROW BEFORE SEPARATING.  AFTER SEPARATION, THROW BETWEEN NR 3 R	OD AND NR 3 MAIN FRACTURED THROUGH FROM OVERLOAD.  APPEARS TO HAVE BEEN INITIATED BY STRESS RISER CREATED BY SLIGHT STEP	 IN RADIUS.  (POSSIBLY CREATED FROM BEING TOUCHED ACCIDENTALLY BY GRINDING WHEEL WHEN CRANKSHAFT WAS REWORKED.)  CRANKSH	AFT WAS (TC# 20051221004).							3	O			E14EA				 
2006061300184	20060613	00184	NM  	2006	6	13	CA051221005      	1	20051130	G	3260	82455025303	DOWNLOCK SENSOR 			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT MLG	MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			11474								DURING GEARS RETRACTION TESTS FOR TASK 3230/09 ITEM 100, FOUND LT MAIN LANDING GEAR ALTERNATE DOWN LOCK INDICATION INDIC	ATING "DOWN AND LOCKED " WHILE THE GEAR WAS STILL RETRACTED.  MOST PROBABLE CAUSE, FAILURE OF LIGHT SENSITIVE DIODE IN C	ABLE ASSY.  LT MLG ALTERNATE DOWN INDICATION CABLE REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300185	20060613	00185	NM  	2006	6	13	CA051221006      	1	20051221	G	2121	732591A	COOLING FAN     			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					E/E BAY	SEIZED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						0608					CREW REPORTED SLIGHT SMOKE AND PLASTIC BURNING ODOR IN COCKPIT.  ACFT DIVERTED TO SNN.  MX CARRIED OUT INSPECTION, FOUND	 EQUIP COOL EXHAUST FAN FAILED AND TRIPPED THE CB, AREA INSP.  NO FURTHER DAMAGE FOUND, FAN PLACED ON MEL ACFT DISPATCHE	D.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006061300186	20060613	00186	CE  	2006	6	13	CA051221007      	1	20051123	G	5511	053200198	SPAR            			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300D       	17022	SO  					STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2277 								THE STABILIZER FORWARD SPAR WAS CRACKED AND BUCKLED AT THE CENTER LIGHTENING HOLE.  THERE WERE 2 SMALL CRACKS RADIATING 	OUTWARD.  STABILIZER WAS REPAIRED AS PER CESSNA SEB94-8.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2006061300187	20060613	00187	EA  	2006	6	13	CA051222001      	1	20051214	G	2497		CONTACTOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					AVOINIC BAY	BURNED          	W				O				OTHER                   				G			MULTIPLE FAILURE          			DE	DESCENT        	1			CA											PILOT EXPLAINED THAT AT ABOUT 24,000 FEET BEGAN EXPERIENCING ELECTRICAL FAILURES AND LOST AC BUS 2 AND GEN 2.  DURING AT	TEMPT TO RESET GEN 2 AND BUS 2 HE BEGAN LOSING GEN 1 AND BUS 1 AT THIS TIME PROBABLY AFTER LOSING ESSENTIAL BUS ADG DEPL	OYED.  AFTER TALKING WITH MAINT CONTROL WAS ABLE TO RESET GEN 2 AND REGAIN AC BUS 2 WAS NOT ABLE TO RESET GEN 1 OR AC BU	S 1 AND DID NOT ATTEMPT TO START THE APU.  UPON INSPECTION ON THE GRD, DID NOT FIND ANY IRREGULARITIES WITH EITHER OF TH	E ENGINE GENERATORS.  DURING AN INSPECTION OF THE AVIONICS BAY THE CONTACTORS ON THE LEFT SIDE OF THE AVIONICS BAY WERE 	DAMAGED BEYOND RECOGNITION AND THERE WAS HEAVY SMOKE AND SOME HEAT DAMAGE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061300188	20060613	00188	NE  	2006	6	13	CA051222002      	2	20051215	G	7320		FUEL CONTROL    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA			11736								DURING FLT, DURING DESCENT, RT THRUST LEVER ON RT ENG WAS UNRESPONSIVE AND THAT IND REMAINED AT 40% EVEN AFTER CREW EXER	CISED BOTH THRUST LEVER'S POSITION TO CONFIRM THAT RT ENGINE WAS NON-RESPONSIVE.  CREW THEN FOLLOWED QRH PROCEDURES, SHU	T DOWN RT ENGINE, DECLARED EMERGENCY AND DID A SINGLE ENGINE LANDING WITHOUT FURTHER INCIDENT.  PLEASE NOTE THAT RT ENG 	ON A/C WAS NOT ORIG ENG INSTALLED AT THE FACTORY.  ORIGINAL RT ENG WAS ROBBED A COUPLE WEEKS AGO OR SO FOR A/C 7588 THAT	 DID AN IFSD ON 29-NOV-05 IN SOUTH BEND. THE OTHER RT ENG THAT WAS THEN INSTALLED ON A/C 8024 AFTER ROBBING ORIG ENG CAM	E FROM KNOXVILLE AND WAS S/N 872699, FLEET LEADER IN TIME SHOWING 11,736 FLT HRS & 10, 899 FLT CYCLES.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061300189	20060613	00189	NE  	2006	6	13	CA051222003      	2	20051219	G	7230		BLADES          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			C	E	J	F.O.D.                    	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			CA			11936					872874			RT ENG IFSD WHEN AT FLT LVL 30,000 FT, CREW REPORTED EXCESSIVE VIBRATION ON RT ENG WAS FELT AND THEN SHUT DOWN ON ITS OW	N.  CREW THEN FOLLOWED QRH, DECLARED EMERGENCY AND DID A SINGLE ENGINE LANDING WITH NO FURTHER INCIDENT.  A LOT OF BLADE	S DAMAGED INSIDE INLET/INTAKE.  ALMOST, ALL BLADES ARE DAMAGED AND AT LEAST 3 HAVE HUGE CHUNK OF BLADES BROKEN OFF AND M	ISSING.  WHEN INSPECTING INTAKE, ONE CHUNK OF BLADE WAS STUCK IN AND WENT PARTIALLY THROUGH INLET CASE.  ANOTHER PIECE O	F BLADE DID A SERIOUS DENT AND ALMOST WENT COMPLETELY THROUGH THE KEVLAR CONTAINMENT RING WHILE TAIL PIPE HAS A WARBLE S	HAPE AT BACK END.  CHIP DETECTOR LIGHT FOR RT ENG WAS ON AND WOULD NOT RESET.  BASED ON THE VISUAL DAMAGE, PINNACLE DECI	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061300212	20060613	00212	CE  	2006	6	13	CA051222004      	1	20051209	G	5711	10111007315	SPAR            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9736 								A/C IN FOR 5 YR WING BOLT REPLACEMENT AND MAIN SPAR LWR FITTING VISUAL INSPECT.  LWR FWD LT WING BOLT DIFFICULT TO REMOV	E AND UPON REMOVAL MODERATE CORROSION WAS OBSERVED IN BOLT BORES.  LOOKING AT BOLT BORES FROM FRONT, GREATEST CORROSION 	APPEARED TO BE AFT AIRFRAME LUG AND AFT WING LUG.  MILD CORROSION NOTED IN FWD AIRFRAME LUG.  NDT WAS CARRIED OUT ON LUG	 W/NO CRACKS FOUND.  ALL OTHER BOLTS WERE SERVICEABLE.  RAYTHEON WAS CONTACTED FOR ASSESSMENT OF DAMAGE FOUND AND FOLLOW	ING SEVERAL DELAYS APPROVED A/C FOR LIMITED RETURN TO SERV UNDER REPAIR ORDER NUMBER FR-KA-01836 REV 1.  THIS TEMP REPAI	R WAS APPROVED FOR 250 HRS OR NINE WEEKS AT WHICH POINT A PERMANENT REPAIR MUST BE CARRIED OUT.  PERMANENT REPAIR ENTAIL	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006061300213	20060613	00213	CE  	2006	6	13	CA051222005      	1	20051219	G	2421	633661	SHAFT           	CONT        	633661      	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ALTERNATOR	BROKEN          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			CA				250  		F140102					ELECTRICAL FAILURE ALTERNATOR REMOVED SHAFT FOUND BROKEN ALTERNATOR STILL TURNS NOT SEIZED.  DRIVE GEAR AND CAM GEAR FOU	ND WORN DUE TO DRIVE GEAR BEING NOT ATTACHED TO THE ALTERNATOR.  ALTERNATOR REPLACED CAM AND DRIVE GEAR, RETAINER AND BU	SHINGS REPLACED.				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006061300214	20060613	00214	CE  	2006	6	13	CA051222006      	1	20051220	G	3397	2K40D10	RESISTOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LIGHTS	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE CARRYING OUT COMPANY CAMPAIGN 681-33-21-018, RESISTOR R145 FOR FLUORESCENT LIGHT CIRCUIT FOUND SHOWING SIGNS OF OV	ERHEATING.  SYSTEM DISABLED AND DEFERRED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006061300216	20060613	00216	CE  	2006	6	13	CA051222007      	1	20051220	G	3320	2K40D10	RESISTOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN LIGHTS	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											RESISTOR R145 FOR FLUORESCENT LIGHT CIRCUIT FOUND SHOWING SIGNS OF OVERHEATING WHILE CARRYING OUT COMPANY CAMPAIGN 681-3	3-21-018.  SYSTEM DISABLED AND DEFFERED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006061300217	20060613	00217	NM  	2006	6	13	CA051222008      	1	20051221	G	5753	BACB30LE8DK83	BOLT            			BOEING	737   	7378Q8      	13844BX	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FLAP FAIRING	MIGRATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17857	58   							DURING GROUND INSPECTION IT WAS DISCOVERED THAT AFT ATTACHMENT BOLT OF THE NR 3 FLAP FAIRING HAD MIGRATED INBOARD AND PU	NCTURED A HOLE THROUGH THE COMPOSITE FAIRING.  THE AIRCRAFT WAS REMOVED FROM SERVICE FOR REPAIRS.  UPON FURTHER INVESTIG	ATION, THREE(3) OF THE FAIRING AFT ATTACHMENT BOLTS WERE FOUND WITHOUT COTTER PINS INSTALLED, TWO NUTS HAD BACKED OFF AN	D THE THIRD HAD SEPARATED COMPLETELY ALLOWING THE BOLT TO MIGRATE.  THIS AIRCRAFT HAD RECENTLY HAD A BASE VISIT DURING W	HICH THE FAIRING WAS REMOVED FOR ACCESS.  AN INVESTIGATION IS UNDERWAY WITH THE MRO THAT PERFORMED THE WORK.		2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006061300218	20060613	00218	CE  	2006	6	13	CA051222009      	1	20051222	G	3320	2K40D10	RESISTOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN LIGHTS	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											VISUAL INSPECTION CARRIED OUT AS PER CAMPAIGN NOTICE 681-33-21-018.  RESISTOR VISUAL INSPECTED OKAY.  SCORCHING FOUND ON	 INSULATION BLANKET.  SYSTEM CB PULLED AND PLACARDED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006061300219	20060613	00219	NE  	2006	6	13	CA051223001      	2	20051128	G	7200		ENGINE          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING CRUISE AT 38K FEET, BOTH ENGINES FLAMED-OUT.  IN-FLIGHT RELIGHT ATTEMPTS WERE UNSUCCESSFUL AND THE AIRCRAFT DIVER	TED FOR A DEAD-STICK LANDING.  P&WC WILL PARTICIPATE IN THE INVESTIGATION OF THIS INCIDENT AND WILL ADVISE OF ROOT CAUSE	 ONCE ESTABLISHED.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006061300220	20060613	00220	SW  	2006	6	13	CA051223002      	1	20051115	G	6310	209340265103	SEAL            			BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	DISLODGED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											THE AFT SEAL OF THE FREEWHEEL UNIT CAME OUT FROM THE AFT CAP WHILE THE ENGINE WAS RUNNING.						1	G	7	1 	3U			O	H2SW    					 
2006061300222	20060613	00222	NE  	2006	6	13	CA051223003      	2	20051129	G	7200		ENGINE          			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  						OVERTEMP        	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA								RK0150			DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN INDICATED ITT OVER-TEMPERATURE.  THE PILOT SHUT THE ENGI	NE DOWN IN FLIGHT AND DIVERTED TO POINT OF ORIGIN.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  PWC 	WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2006061300223	20060613	00223	SW  	2006	6	13	CA051223004      	1	20051212	G	6310	406040506101	CLUTCH          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FREEWHEELING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4627 	2127 							4 FATIGUE CRACKS WERE FOUND AROUND TWO LOWER ENGINE ATTACHMENT BOLT HOLES.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006061300224	20060613	00224	NE  	2006	6	13	CA051223005      	2	20051114	G	7230		COMPRESSOR      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	E	J	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          	WARNING INDICATION        	NR	NOT REPORTED   	1			CA								62511			DURING A MAINTENANCE CHECK FLIGHT, THE ENGINE EMITTED A LOUND NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION.  THE 	ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE COMPRESSOR AND INLET AREA.  P&WC WILL INVE	STIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006061300262	20060613	00262	NE  	2006	6	13	CA051223006      	2	20051130	G	7200		WARNING LIGHT   								PWA   	PT6   	PT6A68      	 	NE  					ENGINE	ILLUMINATED     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											DURING SPIN RECOVERY MANEUVERS THE ENGINE CHIP DETECTOR WARNING ANNUNCIATED ACCOMPANIED BY VIBRATION.  THE AIRCRAFT DIVE	RTED FOR AN UNSCHEDULED LANDING.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.										4	T			E26NE				 
2006061400020	20060614	00020	NM  	2006	6	14	CA051223007      	1	20051128	G	7712		TORQUE SENSOR   			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	REDUCTION GBOX	FAULTY          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											DURING CLIMB, THE ENGINE PROPELLER FEATHERED UNCOMMANDED ACCOMPANIED BY AN ENGINE OVER-TORQUE.  THE ENGINE WAS SHUT DOWN	 IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A FAULTY ENGINE TORQUE SENSO	R.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400021	20060614	00021	EU  	2006	6	14	CA051223008      	1	20051030	G	6123		CIRCUIT BOARD   			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  					AUTOFEATHER	CRACKED         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						MN1334					DURING CLIMB, THE ENGINE EXPERIENCED UNCOMMANDED TORQUE FLUCTUATIONS AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT	 INSPECTION REVEALED AN INTERMITTENTLY FAULTY AUTOFEATHER UNIT DUE TO A CRACKED INTERNAL CIRCUIT BOARD.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006061400023	20060614	00023	NE  	2006	6	14	CA051223009      	2	20051203	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW121 	PW121       	52124	NE  						SHUTDOWN        	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA								120257			ON APPROACH, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE ENGINE WAS SHUT DOWN	 IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS AT THE ENGINE CHIP DETECTORS AND FILTERS.  P&WC WILL INVESTIGAT	E THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006061400024	20060614	00024	EA  	2006	6	14	CA051223010      	2	20051207	G	7261	3032098	CSU             			PIPER 	PA28  	PA28140     	7102802	SO  	PWA   	PT6   	PT6A61      	52043	EA  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING CRUISE, THE ENGINE LOST OIL PRESSURE AND WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A LEAK AT THE C	SU PITCH LOCK SOLENOID.					1	L	7	1 	3O	4	T		2A13    	E4EA				 
2006061400026	20060614	00026	NE  	2006	6	14	CA051223011      	2	20051216	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  						VIBRATION       	W				E				ENGINE SHUTDOWN         				B	R	E	SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          	NR	NOT REPORTED   	1			CA								AE0053			IN FLIGHT, ODORS WERE DETECTED IN THE CABIN.  SUBSEQUENTLY ENGINE VIBRATIONS OCCURRED ACCOMPANIED BY AN INDICATED LOSS O	F TORQUE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  INSPECTION REVEALED NOISES INTERNAL TO THE ENGINE ON ROTATING THE PROPELL	ER.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006061400028	20060614	00028	NE  	2006	6	14	CA051223012      	2	20051216	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  						VIBRATION       	W				O				OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	DE	DESCENT        	1			CA								PJ0203			ON DESCENT, THE ENGINE WAS REPORTED TO VIBRATE ACCOMPANIED BY AN UNCOMMANDED POWER ROLL-BACK AND SHUT DOWN.  A SUCCESSFU	L IN-FLIGHT RELIGHT WAS ACCOMPLISHED.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061400040	20060614	00040	NE  	2006	6	14	CA051223013      	2	20051221	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								123250			DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED ACCOMPANIED BY OIL PRESSURE FLUCTUATIONS.  THE ENGINE WAS	 SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS ON TH	E TURBOMACHINE CHIP DETECTOR AND AN OIL LEAK AT THE TORQUE-SHAFT COVER.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF R	OOT CAUSE ONCE DETERMINED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006061400051	20060614	00051	EA  	2006	6	14	CA051223014      	2	20051221	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						MAKING METAL    	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0124			DURING FLIGHT, SMOKE WAS DETECTED IN THE CABIN AIR ACCOMPANIED BY A REDUCTION IN ENGINE OIL PRESSURE.  THE AIRCRAFT DIVE	RTED FOR A UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL SYSTEM.  P&WC WILL INVEST	IGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006061400053	20060614	00053	SO  	2006	6	14	CA051223015      	1	20051220	G	7603	3011587	ROD END         			PIPER 	PA28  	PA28140     	7102802	SO  	PWA   	PT6   	PT6A34      	52043	EA  					POWER LEVER	STIFF           	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			250  								ON POWER REDUCTION FOR DESCENT, THE ENGINE DID NOT RESPOND TO THROTTLE LEVER INPUT.  THE ENGINE WAS SHUTDOWN ON FINAL AP	PROACH AND A DEAD-STICK LANDING ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED THE FUEL CONTROL INTER-CONNECT ROD END TO 	BE STIFF AND LIMITED IN MOVEMENT DUE TO A SEIZED ROD-END BALL SWIVEL.				1	L	7	1 	3O	4	T		2A13    	E4EA				 
2006061400055	20060614	00055	NM  	2006	6	14	CA051223016      	1	20051108	G	3010	29S7D524008	BOOT            			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	RT HORIZ. STAB	SPLIT           	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			5150 								CREW REPORTED A FAIL INDICATION FOR THE RT HORIZONTAL STAB DEICE BOOT.  UPON INSPECTION BY MAINTENANCE THE BOOT HAD A 12	 INCH SPLIT AND WAS REPLACED.  NO IN FLIGHT HANDLING PROBLEMS WHERE REPORTED.)					2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2006061400057	20060614	00057	EA  	2006	6	14	CA051228001      	1	20051219	G	5311	21531062882	FRAME           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	BS 388 RBL 51	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2436 								WHILE PERFORMING AD 1997-07R2 A HORIZONTAL CRACK WAS DISCOVERED ON THE RT FORWARD OUTBOARD FUSELAGE FRAME ANGLE FS 388.0	0 RBL 51.00.  THE CRACK WAS LOCATED APPROXIMATELY IN LINE WITH THE BOTTOM WING SKIN.  THE FRAME ANGLE WAS COMPLETELY CRA	CKED OFF AND COULD BE SEEN QUITE PLAINLY WITH THE NAKED EYE.  BOMBARDIER WAS CONTACTED AND A REQUEST FOR AN ENGINEERING 	REPAIR ORDER WAS MADE.			2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2006061400058	20060614	00058	CE  	2006	6	14	CA051228002      	1	20051226	G	2435	6608458005	STARTER GEN     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA				803  							CLIMBING THRU 30000 FT, THE CREW FELT A VIBRATION IN AIRFRAME.  SHORTLY AFTER LT ENGINE GENERATOR FAILED.  THE CREW THEN	 DIVERTED TO AN ALTERNATE AIRPORT WITH APPROPRIATE FACILITIES TO FIX THE PROBLEM.  THOUGH BEFORE THEY ARRIVED THEY AGAIN	 FELT THE SAME VIBRATION THIS TIME COMING FROM THE RT SIDE. CONTINUED TO MAKE 28VDC UNTIL SHUTDOWN. UPON INSPECTING RT S	TARTER GENERATOR IT AS WELL WAS ON ITS WAY OUT (MAKING METAL)AND WILL ALSO BE REPLACED. ITS P/N IS 6608458-005 S/N 99103	9 WITH A TSO OF ONLY 153 HOURS. BOTH OF THESE S/G'S HAVE HAD THE SB TO GO 1200 HOURS INBETWEEN OVERHAULS.  OBVIOUSLY THE	SE DID NOT MAKE IT.  PERHAPS THE INCREASED LOAD (NOT MORE THAN 190 AMPS) CAUSED THE SECOND S/G TO PACK IT IN.	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006061400062	20060614	00062	EA  	2006	6	14	CA051228003      	1	20051227	G	3411	6670658	PITOT HEAD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						BENT            	W				O				OTHER                   				C			F.O.D.                    			DE	DESCENT        	1			CA			2784 	2784 							BIRD STRIKE DURING FLIGHT.  MAINTENANCE INSPECTION AFTER LANDING FOUND 2 SMALL DENTS ON THE RT WING LEADING EDGE AT WS89	.34 AND RT PITOT HEAD DAMAGED/BENT.  LEADING EDGE DENTS ALLOWABLE FOR CONTINUED SERVICE, RT PITOT HEAD REPLACED.  AIRCRA	FT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061400063	20060614	00063	NM  	2006	6	14	CA051229001      	1	20051224	G	5350	BACC2C3D00525EG	CONTROL CABLE   			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					NLG STEERING SYS	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A SEVEN DAY CHECK OF AIRCRAFT C-FCGF, THE NOSE WHEEL STEERING CABLE WAS FOUND TO BE ROUTED AROUND AN AFT ATTACHME	NT BOLT FOR THE NOSE WHEEL METERING VALVE ASSEMBLY.  THE CABLE HAD BEEN RIGGED AND TENSIONED IN THAT POSITION.  THE CABL	E WAS DISENGAGED FROM THE BOLT, INSPECTED AND RE-RIGGED.  THE BOLT ALSO HAD TO BE REPLACED DUE TO WEAR FROM THE CABLE.  	 A RECORDS SEARCH SHOWS THAT THE LAST TIME THE CABLES HAD BEEN DISCONNECTED AND RE-RIGGED WAS AT TIMCO IN LAKE CITY FL D	URING A C CHECK DATED 20 NOV 2004.		2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061400065	20060614	00065	NM  	2006	6	14	CA051229002      	1	20051226	G	7333	FFG052AC	GOVERNOR        			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					FUEL FLOW	UNSERVICEABLE   	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				7922 							DURING FLIGHT FROM YYC TO PVR, NR 2 ENGINE LOST PARTIAL POWER.  FLIGHT CONTINUED WITHOUT INCIDENT.  MAINTENANCE INVESTIG	ATION DETERMINED THE FUEL FLOW GOVERNOR TO BE AT FAULT.  THE GOVERNOR WAS REPLACED, POWER PERFORMANCE RUNS CARRIED OUT S	ATISFACTORY AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2006061400067	20060614	00067	NM  	2006	6	14	CA051230002      	1	20051109	G	2797	2210P12210P2	WIRE HARNESS    	HONEYWELL   		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FLT GUIDANCE	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						85070177					YAW DAMPER AND AUTOPILOT FAILED ON BOTH SIDES DURING CRUISE.  FLT CONTINUED WITH NO PROBLEMS.  BOTH FGCS WERE FOUND TO 	BE U/S.  2 NEW FGCS AND A KNOWN SERVICEABLE SERVO WERE INSTALLED RESULTING IN 2 MORE U/S FGCS UPON FURTHER INVESTIGATI	ON, FOUND A FAULT WITH CLUTCH POS CIRCUIT.  PULLED CONNECTOR AT PRESS DOME AND FOUND PIN F AT 2210-P2 GROUNDED, THEN WEN	T TO 2210-P1 WHEN THAT CONNECTOR WAS PULLED PIN F WAS NOW OPEN BUT SHORTED TO PIN N.  COMPLETED A FULL INSPECTION BETWEE	N BOTH CONNECTORS AND FOUND NO VISUAL FAULTS.  STARTED AT FRONT MOVING WIRE BUNDLES AND FOUND FACTORY SPLICE FOR SHIELDI	NG ON PIN N HAD CHAFFED INTO WIRE ON PIN F WIRE NUMBER 2210-5K20-2. WHEN FUNCTION TESTING THE A/P WHEN THERE IS A SNAG, 	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400068	20060614	00068	EA  	2006	6	14	CA051230003      	2	20051203	G	8520	KO509	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			5669 	361  				L1058961A			OIL LEAK REAR OIL ACCESS DOOR LT ENGINE.  UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT CRANKCASE WAS CRACKED BETWEE	N NR 4 AND NR 6 CYLINDERS.  THIS ENGINE ONLY HAD 361.2 TSO.  THE CRANKCASE HAD APPROX 5669 HRS SINCE NEW.  THIS ENG WAS 	INSTALLED MAY 03/2005 REPLACING AN ENGINE WITH THE EXACT SAME CRACK IN THE EXACT SAME LOCATION, THAT ENGINE WAS AT 1749.	4 TSO.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061400069	20060614	00069	SO  	2006	6	14	CA051230004      	1	20051230	G	5711		SPAR            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WING MAIN SPAR EXTRUSION CRACKED AT MAIN LANDING GEAR SIDESTAY SUPPORT BRACKETS, LT AND RT SIDES.  CRACKS RUN SPANWISE I	N FILLET RADIUS AND IN WEB.  TWO CRACKS VISIBLE IN EACH SIDE, LONGEST CRACK IS ABOUT 1.25" LONG.  CRACKS EXTEND THROUGH 	FULL THICKNESS OF THE SPAR WEB.  INITIALLY DETECTED THROUGH INSPECTION HOLE LOOKING AT FORWARD SIDE OF SPAR WEB, CONFIRM	ED BY REMOVAL OF SIDESTAY SUPPORTS AND INSPECTION FROM AFT SIDE.  THE SIDESTAY BRACKETS ARE SUBJECT OF AD 97-01-01 R1.  	NO AD ADDRESSES THIS DEFECT.  WINGS ARE NOT ORIGINAL TO THIS AIRCRAFT SO TSN CANNOT BE READILY DETERMINED.		1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
2006061400071	20060614	00071	EA  	2006	6	14	CA060103002      	1	20051214	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			11022								FOUND LEFT WINDSHIELD CRACKED.  LEFT WINDSHIELD REMOVED AND REPLACED ACCORDING AMM PROCEDURE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061400172	20060614	00172	EA  	2006	6	14	CA060103003      	1	20051230	G	2497	1K4XD	CONTACT         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											"UPON POWER UP, GOT AC UTIL 1 OFF + MAIN BATT CHGR MESSAGES".   MAINTENANCE DISCOVERED HEAT DAMAGE TO CONTACTOR 1K4XD.  	 CONTACTOR REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061500021	20060615	00021	EA  	2006	6	15	CA060104000      	1	20051221	G	3397		WIRE            			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF34*       	 	NE  					FLOOD LIGHT	BURNED          	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA			4887 								FLT 5046 CLT-RTF, WHEN THE FOS SIDE FLOOD LIGHT WIRING CAUGHT FIRE.  A/C LANDED WITHOUT INCIDENT AND THE CREW HAD EXTIN	GUISHED FIRE IN APPROX 4 SECONDS PER THE CAPTAIN.  A/C IMPOUNDED BY NTSB AND WAS RELEASED BACK TO MX UPON OUR RECEIPT OF	 DIGITAL PICTURES OF DAMAGE.  UPON INITIAL INVESTIGATION MX INSPECTED LIGHT, REMOVED COVER AND FOUND A SMALL AMOUNT OF M	OISTURE.  THIS FIRE ALSO BURNED THROUGH THE FLOOD LIGHT WIRING AND MELTED SOME OF THE LIGHT ASSEMBLY.  MX REMOVED AND RE	PLACED THE LIGHT ASSY.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061500023	20060615	00023	CE  	2006	6	15	CA060104001      	1	20051120	G	7120	05510171	MOUNT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5365 								CRACK ON ENGINE MOUNT CROSS BRACE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061500024	20060615	00024	EA  	2006	6	15	CA060104002      	2	20051211	G	7322	105217	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA				1293 							CARBURETOR FAILED TO SHUT ENGINE DOWN WHEN MIXTURE PULLED OUT TO IDLE CUTOFF POSITION.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061500026	20060615	00026	WP  	2006	6	15	CA060104003      	1	20051001	G	7600	D2782	CONTROLLER      			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					GOVERNOR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			56   								GOVERNOR FAILED TO CONTROL ENGINE RPM.  WHEN THROTTLE INCREASED TO 100% ROTOR SPEED.  GOVERNOR CONTROL ASSEMBLY REPLACED	 WITH NEW.  AIRCRAFT GROUND RUN AND TEST FLIGHT SATISFACTORY.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061500178	20060615	00178	NE  	2006	6	15	CA060104006      	2	20051228	G	7261	9196M44G01	MANIFOLD        								GE    	CF6   	CF650E2     	30018	NE  					SUMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											OPERATOR REPORTED N1 VIBRATION AND METAL CONTAMINATION OF A SUMP SCAVENGE SCREEN AND MASTER CHIP DETECTOR.  THE ENGINE W	AS REMOVED FOR FURTHER INVESTIGATION.  DURING INITIAL TROUBLESHOOTING, LOOSE MATERIAL WAS HEARD TUMBLING IN THE SPINNER 	CONE AND EVIDENCE OF OIL LEAKAGE FROM UNDER THE SPINNER WAS OBSERVED.  THE SPINNER CONE WAS REMOVED FOR INVESTIGATION.  	OBSERVED CATASTROPHIC FAILURE OF THE A SUMP MANIFOLD ASSEMBLY.  SIX OF THE TEN MOUNTING BOLTS WERE FOUND SHEARED.  ENG H	AS BEEN SCHEDULED FOR DISASSEMBLY AND FURTHER INVESTIGATION IN EARLY JANUARY.  THE OEM WILL BE ADVISED AND WILL ASSIST W	ITH THE INVESTIGATION. FURTHER DETAILS WILL BE FORWARDED TO THE TCCA WHEN AVAILABLE.						4	F			E23EA				 
2006061500186	20060615	00186	SW  	2006	6	15	CA060105003      	1	20051208	G	6230	206040014105	MAST            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			6524 	1525 							M/R MAST WAS REPLACED 4 HOURS PREVIOUSLY.  PILOT HAD A TRANSMISSION CHIP LIGHT AND NOTIFIED TOWER OF LANDING DUE TO A MX	 PROBLEM.  ENGINEER INSPECTED F/W, TRANSMISSION, AND MAST CHIP DETECTORS.  FOUND HAIR LIKE SLIVER ON THE UPPER MAST BRG 	CHIP DETECTOR AND ON THE TRANSMISSION OIL MONITOR, AS PER BELL 206L-1 CHIP DETECTOR GUIDE C/O INSPECTION AS REQUIRED, C/	O OPERATIONAL CHECK AND 20 MIN GROUND RUN AS PER BELL 206L-1 MM.  CHECK CHIP DETECTORS, OIL REPLACED, FILTER INSPECTED A	ND REPLACED AND ANOTHER OPERATIONAL CHECK C/O.  SLIVERS MAY HAVE BEEN FROM MAST INSPECTION OR OIL CANS?  SOURCE UNKNOWN.	  AIRCRAFT RETURNED TO SERVICE WITH A SATISFACTORY TEST FLIGHT.	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006061600050	20060616	00050	EA  	2006	6	16	CA060106002      	2	20051220	G	7200		ENGINE          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LEFT	FAILED          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA								PCE25598			WHILE IN FINAL DESCENT, THE FLIGHT CREW DISCOVERED THAT THEY DID NOT HAVE FULL AUTHORITY OVER THE LEFT ENGINE.  THE LEFT	 ENGINE COULD NOT BE REDUCED BELOW 800 LBS TORQUE. ENGINE CONTROL WAS STILL AVAILABLE IN A RANGE FROM 800 LBS TO MAX TOR	QUE. FLIGHT CREW OPTED TO SECURE LEFT ENGINE AND CARRY OUT A SINGLE ENGINE LANDING IN FREDERICTON WITH CFR STANDBY.  ENG	INE SHUTDOWN AND FEATHERING OF PROP WAS NORMAL.  INITIAL INSPECTION SHOWS ALL LINKAGE NORMAL.  FURTHER DIAGNOSIS BEING C	ONDUCTED.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006061600058	20060616	00058	EA  	2006	6	16	CA060109003      	1	20050130	G	3251	7117717	COLLAR          			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					NLG STEERING	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											THE STEERING COLLAR WAS ASSEMBLED AT THE FACTORY INCORRECTLY.  THERE ARE TWO DISCS WHICH ARE ATTACHED TO THE COLLAR. ONE	 DISC IS BARE METAL AND IS SUPPOSED TO BE AT THE SIDE THAT IS FACING THE STRUT TOUCHING THE FRICTION DISC (WHICH IS GLUE	D TO THE STRUT ITSELF).  THE OTHER DISC IS A SPECIAL DISC WITH A SPECIAL COATING WHICH FACES THE PLASTIC DISC POINTING T	OWARDS THE LOCKNUT.  THIS DISC HAS A SMALLER DIAMETER AND CAN NOT BE INSTALLED TOWARDS THE STRUT.  CUSTOMER CORRECTED TH	E SITUATION HIMSELF AND HEROUX HAS BEEN CONTACTED.		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006061900074	20060619	00074	CE  	2006	6	19	CA060112008      	1	20051215	G	5340		INTERCOSTAL     			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	RUDDER PEDAL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CAPTAINS OUTBOARD RUDDER PEDAL MOUNT BLOCK INTERCOSTAL AT STN 118.55, REPAIRED DUE TO CRACKED.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006061900247	20060619	00247	EA  	2006	6	19	CA060112012      	1	20051229	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			4900 								ON LANDING, THE CAPTAINS WINDSHIELD SHATTERED.  MAINTENANCE REPLACED WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062100080	20060621	00080	SW  	2006	6	21	CA060117006      	1	20051122	G	6720	206928110	PIN             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THREADED PORTION OF EXPANDABLE PIN FOUND SHEARED OFF, REPLACED WITH SERVICEABLE ASSEMBLY.  ASSEMBLY WAS FOUND TO BE BROK	EN DURING A GROUND RUN. THIS PIN IS PART OF THE QUICK DISCONNECT PEDAL SYSTEM.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062100085	20060621	00085	EA  	2006	6	21	CA060118004      	2	20051212	G	8530	72257	PUSHROD         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER BAFFLE TIE ROD P/N 71562-03 WAS FOUND WITH A SECURING INTER CYLINDER BAFFLE, ADEL CLAMP MISSING. THIS HAD	 ALLOWED THE BAFFLE TIE ROD TO RAISE UP TO THE POINT WHERE IT CAME INTO CONTACT WITH THE LOWER SIDE OF THE NR 4 CYLINDER	 EXHAUST PUSH ROD TUBE.  IT IS SUGGESTED THAT ALL MAINTENANCE PERSONNEL ENSURE THAT THESE ADEL CLAMPS ARE IN PLACE AS TH	EY HOLD THE TIE ROD AWAY FROM THE UNDERSIDE OF THE PUSH ROD TUBES. (TC NR 20060118004)			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006062100086	20060621	00086	SO  	2006	6	21	CA060119001      	1	20050909	G	6100		GEAR            			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  	HARTZL	HCC3Y	HCC3YN      	GL  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON SHUTDOWN, PILOT HEARD A REPETITIVE SOUND, FROM THE LT ENGINE. INVESTIGATION SHOWED THE PROP GEAR HAD TEETH MISS	ING.   EVIDENCE, METAL TEETH PIECES IN OIL SCREEN.  NO RESISTANCE IN PROP ROTATION FOR ABOUT 10 DEGREES.  ENGINE REPLACE	D, AIRCRAFT RETURNED TO SERVICE.  (TC 20060119001)				1	L	7	2 	3O	3	O		A8EA    	E19EA	5	C	P25EA	 
2006062200070	20060622	00070	EA  	2006	6	22	CA060119002      	2	20051012	G	8520		CASE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA				688  				RL151561			IN FLIGHT AT LOW CRUISE SETTING, PILOT REPORTED HEARING A BANG, FELT A "SHUTTER", AND EXPERIENCED A LOSS OF POWER IN THE	 LEFT ENGINE.  ENGINE WAS SHUT DOWN, PROP FEATHERED, AND AIRCRAFT LANDED SAFELY.  THE ENGINE CASE WAS FOUND CRACKED.  TH	E ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  ENGINE IS CURRENTLY BEING STORED.  NO DISASSEMBLY OR INVEST	IGATION HAS TAKEN PLACE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062300209	20060623	00209	EA  	2006	6	23	CA060127008      	1	20051214	G	7120	CSP28229	BOLT            			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENG MOUNT	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON SCHEDULED REMOVAL OF LOANER ENGINE FOR RETURN TO MFG, 2 OF THE TOP MOUNT BOLTS WERE DISCOVERED TO BE SEIZED I	N PLACE. ENGINE WAS RETURNED TO MFG WITH MOUNT IN PLACE FOR THEM TO REMOVE. THIS IS THE SECOND OCCURANCE OF THIS PROBLEM	 WITHIN OUR COMPANY, THE FIRST WAS DURING AN ENGINE CHANGE. UPON DISCUSSION WITH OTHER OPERATORS UTILIZING THESE BOLTS, 	DETERMINED THAT THE PROBLEM IS NOT ISOLATED TO US. (TC NR 20060127008)			1	H	7	1 	3T	4	T		A806    	E4EA	6	C	P15EA	 
2006062700021	20060627	00021	NM  	2006	6	27	CA060127009      	1	20051228	G	2611	473054	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CARGO BAY	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA			34809	430  							EN ROUTE CAPT CONTACTED MX TO ADVISE BAGG SMOKE DETECT LIGHT FLICKERED A COUPLE OF TIMES.  A FEW MINS LATER CAPT CONTACT	ED FLT DISPATCH AGAIN TO ADVISE LIGHT WAS NOW ON CONSTANT, DECLARED EMERG DIVERTING TO YYY.  COMMUNICATION WAS LOST WITH	 FLT AND A CALL WAS MADE TO MONTREAL ATC TO OBTAIN FURTHER INFO.  ATC ADVISED FULL EMERG WAS DECLARED, FLT CREW ON OXYGE	N, SMOKE IN COCKPIT.  FLT LANDED, PAX DEPLANED UNDER NORMAL CONDITIONS.  AT NO TIME WAS SMOKE IN COCKPIT.  REPLACED SMOK	E DETECTORS IN CARGO AREA AND TESTED SYS.  RELEASED A/C INTO SERVICE. A/C HAS CONTINUED IN SERV TO DATE WITH NO FURTHER 	INCIDENCES.  ONE OF DETECTORS WAS FOUND IN 2 PREVIOUS EVENTS, DETERMINED IT WAS COST EFFECTIVE TO SCRAP UNIT OUT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300213	20060623	00213	NE  	2006	6	23	CA060129003      	2	20051116	G	7321		FUEL CONTROL    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	CONTAMINATED    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CLIMB THE ENGINE LOST POWER AND THE PROPELLER AUTOFEATHERED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIR	CRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED SOOT CONTAMINATION OF THE FUEL CONTROL PY ORIFICE.	 (TC NR 20060129003)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006062600080	20060626	00080	NE  	2006	6	26	CA060129009      	2	20051225	G	7321	381850012	FUEL CONTROL    			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			49   								(CAN) ON APPROACH, THE ENGINE DID NOT RESPOND TO THROTTLE INPUT.  AN EMERGENCY WAS DECLARED AND A LANDING ACCOMPLISHED W	ITH THE THROTTLE IN THE IDLE DETENT.  SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT.  MFG WILL INVESTIGATE T	HE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129009)				1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2006062600089	20060626	00089	NE  	2006	6	26	CA060129016      	2	20051213	G	7230		CASE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMPRESSOR	FRACTURED       	W				E				ENGINE SHUTDOWN         				R	E	J	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) DURING APPROACH, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY NOISE AND VIBRATION.  THE EN	GINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT ISPECTION REVEALED A FRACTURED INLET CASE STRUT. (TC NR 20060129016)					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006070300016	20060703	00016	CE  	2006	7	3	CA060129017      	1	20051225	G	2820		LINE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					FUEL EJECTOR	FRACTURED       	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											FUEL WAS FOUND LEAKING FROM THE ENGINE NACELLE FOLLOWING LANDING AND TAXI.  INSPECTION REVEALED A FRACTURED ENGINE FUEL 	EJECTOR TUBE.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006070300049	20060703	00049	EA  	2006	7	3	CA060129018      	2	20051228	G	7250		TURBINE BLADES  			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  					GAS GENERATOR	FRACTURED       	W				E				ENGINE SHUTDOWN         				R	Z		PARTIAL RPM/PWR LOSS      	SIGNIFICANT FAILURE REPORT		CR	CRUISE         	1			CA											DURING CRUISE, ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY NOISE.  ENGINE WAS SHUT DOWN IN FLIGHT. 	 SUBSEQUENT INSPECTION  REVEALED FRACTURED COMPRESSOR TURBINE BLADES.					1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2006070500034	20060705	00034	EU  	2006	7	5	CA060131006      	1	20051011	G	6220	704A33633208	SPHERICAL STOP  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2986 								THIRD SPHERICAL STOP FOUND DELAMINATED SHORTLY AFTER REPLACEMENT OF 2 PREVIOUSLY, SEPT 9,2005.  UNIT OUT OF LIMITS.  REP	LACED WITH NEW PART.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006070500035	20060705	00035	EU  	2006	7	5	CA060131007      	1	20051104	G	7931	704A37642043	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL PRESSURE	FAILED          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			CA											OIL PRESSURE INDICATION FAILED ON FERRY FLIGHT.  TROUBLESHOOTING REVEALED PRESSURE TRANSMITTER INDICATES AND OPEN CIRCUI	T WHEN ENGINE IS RUNNING.  REMOVED TRANSMITTER AND INSTALLED PN 60310-01 SN N/K WITH NO SUCCESS.  INSTALLED -043  AND A/	C INDICATES OIL PRESSURE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006070500131	20060705	00131	GL  	2006	7	5	CA060208005      	2	20050918	G	7230	230765593	COUPLING        	ALLSN       	6890550     						ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEFECTIVE       	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA			191  			CAC33575					SAGS WAS REPLACED DUE TO PITTING AND SPALLING DURING THIS SHOP VISIT.  ON JUNE 29, 2005, NEW SAGS, 2  BEARING AND RETAI	NING RING WERE SENT TO CUSTOMER FOR REPLACEMENT DUE TO SAGS DAMAGE.  AFTER 191.4 HOURS USAGE, ON SEP 18, 2005, CAC-33575	 WAS SENT IN AGAIN FOR SAGS WARRANTY CLAIM (MAKING METAL).  COMPRESSOR WAS DISASSEMBLED AND COMPLETE INSPECTION WAS DONE	.  IT WAS FOUND THE RETAINING RING WAS BROKEN, 2  BEARING WAS MISPLACED AND SAGS WAS WORN OUT.  THE FURTHER INVESTIGATI	ON SHOWED THAT THE NON-CONFORMANCE OF ADAPTER COUPLING MIGHT CAUSE THIS PROBLEM.							3	U			E4CE				 
2006070500287	20060705	00287	EA  	2006	7	5	CA060208012      	1	20051019	G	7120	PK73507217	MOUNT           			DHAV  	DHC6  	DHC6300     	2802606	EA  										RT ENGINE	BROKEN          	W				A				UNSCHED LANDING         				R	F	J	PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         	WARNING INDICATION        	CL	CLIMB          	1			CA			46252								(CAN) ON TAKE-OFF THERE WAS A NOISE AND THE AC NOSE HAD AN UNCONTROLLED PITCH UP, AND IT YAWED TO THE RT AND THE TORQUE 	PRESSURE FELL TO 80 PERCENT.  THE TAKE-OFF WAS ABORTED AND THE AC RETURNED TO THE DOCK. IT WAS THAN DISCOVERED THAT THE 	RT ENGINE MOUNT WAS BROKEN. (TC NR 20060208012)				1	H	7	2 	3T			RT	A9EA    					 
2006071100135	20060711	00135	EA  	2006	7	11	CA060208013      	1	20050228	G	7120	73512562	MOUNT           			DHAV  	DHC6  	DHC6300     	2802606	EA  										LT ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			37781								AFTER A SMOOTH LANDING, THE A/C HIT AN ABNORMALLY LARGE WAVE, WHICH CAUSED THE A/C TO GET AIRBORNE THAN CAME DOWN HARD O	N A SMALLER WAVE, WHICH RESULTED IN A LARGE JOLT TO THE A/C.  IT WAS THEN NOTICED THAT THE LT ENGINE AND POWER LEVERS HA	D SHIFTED FORWARD.  IT WAS ALSO NOTICED THAT THE LT ENGINE HAD DROPPED A BIT.				1	H	7	2 	3T			RT	A9EA    					 
2006071100150	20060711	00150	EA  	2006	7	11	CA060208014      	1	20051019	G	7120	73512562	MOUNT           			DHAV  	DHC6  	DHC6300     	2802606	EA  										ENGINE	BROKEN          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			1604 								(CAN) AFTER LANDING IT WAS NOTICED NO REVERSE ON THE RT ENGINE AND THE THERE WAS STIFFNESS IN THE OPERATION OF THE POWER	 LEVERS THAN IT ULTIMATLLY GOT STUCK. MAINTENANCE IDENTIFIED THE PROBLEM AS A BROKEN ENGINE MOUNT.  (TC NR20060208014)					1	H	7	2 	3T			RT	A9EA    					 
2006071100199	20060711	00199	NE  	2006	7	11	CA060211003      	2	20051012	G	7230		TURNBUCKLE      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLES	SEPARATED       	W				E				ENGINE SHUTDOWN         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN)   WHEN STARTING APPROACH, THROTTLES WERE PULLED BACK, A LOUD BANG WAS WITNESSED AND FELT IN A/C. ENG NR 1 STARTED 	TO LOSE POWER IMMEDIATELY, FOLLOWED BY LOW OIL PRESSURE WARNING. ITT ROSE UP TO 1230 DEG CELSIUS AND HIGH ENGINE VIBRATI	ON WERE FELT. ENG WAS SHUTDOWN BY CREW.  SINGLE ENG APPROACH AND LANDING, UNEVENTFUL LANDING.  DURING INSP, MAINT FOUND 	BOTH TURNBUCKLES STG 2 OF VG LINKAGE WERE FOUND SEPARATED FROM VG SHAFT.  SOME DAMAGED COMPRESSOR BLADES OF LAST FOUR ST	AGES WERE OBSERVED.   CAUSE FOR STAGE 2 TURNBUCKLE PROBLEMS IS (MOST LIKELY)INTERFERENCE BETWEEN VG SHAFT CLEVIS AND TUR	NBUCKLE JAM NUT ITSELF. BRG ROD END SHEARED CLOSE TO THE NUT.  (TC NR 20060211003)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071100200	20060711	00200	NE  	2006	7	11	CA060211004      	2	20051011	G	7230		BLADES          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COMPRESSOR	DAMAGED         	W				E				ENGINE SHUTDOWN         				Y	E		ENGINE STOPPAGE           	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN)  FLIGHT CREW REPORTED SEEING HIGH NR 1 ENGINE ITT > 900 DEG CELSIUS, TOGETHER WITH ENGINE VIBRATION. N1 STARTED TO	 SPOOL DOWN AND FLUCTUATING N2 WAS SEEN. CREW SHUTDOWN THE ENGINE AND RETURNED TO DEPARTURE. SUCCESSFUL SINGLE ENGINE LA	NDING WAS PERFORMED. FAN AND TURBINE LOOKED NORMAL AND TURNED NORMALLY. GEARBOX TURNED AND ALSO SEEMS NORMAL. CHIP DETEC	TOR FOUND CLEAN. OIL FILTER SHOWED A SMALL AMOUNT OF CHIPS. OIL IN GEARBOX LOOKED NORMAL.  FOUND IN EXHAUST A LOT OF MET	AL CHIPS. BORESCOPE INSPECTION OF THE AIRFLOW SECTION SHOWED DAMAGED COMPRESSOR ROTOR BLADES STAGE 10 THROUGH 14. (TC NR	 20060211004)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071900035	20060719	00035	EA  	2006	7	19	CA060213005      	2	20051220	G	7414	LW14227	BEARING         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1005 								(CAN) SMALL METAL FRAGMENT DISCOVERED WHILE CHANGING ENGINE OIL. FOUND TO BE PART OF A BEARING KEEPER IN RT MAGNETO ADAP	TER BEARINGS. THIS IS THE SECOND TIME THIS PROBLEM HAS OCCURRED ON THIS AIRCRAFT.  (TC NR 20060213005)					1	G	7	1 	3O	3	O	O	4H12    	E286				 
2006060700249	20060607	00249	EA  	2006	6	7	CA060216007      	1	20051225	G	7120	73512562	MOUNT           	BARRYCTRLS  	73512562    	DHAV  	DHC6  	DHC6300     	2802606	EA  										ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING EDDY CURRENT INSPECTION PER MULDIVES AD CAD/2005/1, A CRACK INDICATION WAS FOUND IN THE RADIUS OF THE TOP ENGINE 	VIBRATION ISOLATOR MOUNT.					1	H	7	2 	3T			RT	A9EA    					 
2006060700250	20060607	00250	EA  	2006	6	7	CA060216008      	1	20051005	G	7120	73512562	MOUNT           	BARRYCTRLS  	73507217    	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TOP, ENGINE VIBRATION ISOLATOR MOUNT (RIGHT ENGINE) WAS FOUND CRACKED DURING INSPECTION.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006060800203	20060608	00203	NM  	2006	6	8	CA060219002      	1	20050908	G	3010	38962E	REGULATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DE ICE SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											NR 2 ENGINE FORWARD DE-ICE VALVE P/N 28E96-2D WAS FOUND DAMAGED DURING 3 MONTH LUMP INSPECTION WHILE PERFORMING ZONAL TA	SK CARD 422 (PANEL 422DT) THERE DC FEED CABLES WERE POSITIONED WRONG AND HAD CHAFED THROUGH RUBBER COATING OF TERMINAL A	ND HAD SHORTED AGAINST FORWARD DE-ICE VALVE, THERE WAS SUBSTANTIAL DAMAGE TO THE VALVE, RESULTING IN AN UNRESTRICTED BLE	ED AIR LEAK FROM THE BOTTOM OF THE VALVE.  VALVE WAS REMOVED, THE CABLES WERE INSPECTED WITH NO DAMAGE NOTED THEN REPOSI	TIONED AND THE TERMINAL COVERS WERE REPLACED.  THE SURROUNDING AREA WAS ALSO INSPECTED WITH NO DAMAGED NOTED.  THE VALVE	 WAS REPLACED, LEAK AND FUNCTION CHECKED SERVICEABLE, PANEL 422DT WAS RESEALED WITH PRC 1422 B1/2.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061500192	20060615	00192	SO  	2006	6	15	CA060228010      	2	20050621	G	7414	BL3493108	MAGNETO         			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			171  								ROUGHNESS ON STARTUP OF LT MAGNETO.						1	H	7	1 	3O	3	O		3A21    	3E1				 
2006061500193	20060615	00193	SO  	2006	6	15	CA060228011      	2	20051205	G	7414	BL3493108	MAGNETO         			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			134  								NR 1 CYLINDER NOT FIRING.  TRACED BACK TO INTERNAL PROBLEM WITH MAGNETO, RETURNED FOR WARRANTY.						1	H	7	1 	3O	3	O		3A21    	3E1				 
2006061500194	20060615	00194	CE  	2006	6	15	CA060228012      	1	20050702	G	7921	654593	OIL COOLER      			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGINE OIL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			211  								OIL LEAK FROM OIL COOLER.						1	H	7	1 	3O	3	O		3A21    	3E1				 
2006061600039	20060616	00039	NE  	2006	6	16	CA060228020      	2	20051028	G	7314	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1346 								DURING START UP PILOT COULD NOT PRIME AIRCRAFT.  FURTHER INVESTIGATION FOUND PUMP HAD FAILED.  PUMP REPLACED AND NO FURT	HER DEFECTS WERE NOTED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600041	20060616	00041	NE  	2006	6	16	CA060228022      	2	20050422	G	7314	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1190 								DURING AN ATTEMPTED START, THE AUX FUEL PUMP LIGHT ILLUMINATED.  SYSTEM WOULD NOT FUNCTION.  FURTHER INVESTIGATION FOUND	 PUMP SEIZED.  PUMP REPLACED AND NO FURTHER DEFECTS WERE NOTED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600042	20060616	00042	CE  	2006	6	16	CA060301001      	1	20050225	G	2435	S24431	CONTACTOR       	CONT        		CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	STARTER ENG	ARCED           	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA			789  			0179					DURING TAXI TO POSITION, PILOT HEARD UNUSUAL STATIC ON HEADSET AND A LARGER THAN NORMAL AMPS DRAW.  RETURNED TO CHOCKS; 	WHILE STILL RUNNING CHECKED SYSTEM AND SUDDENLY ALL APPEARED NORMAL.  ENGINE WAS SHUT DOWN, MAINTENANCE WAS CONTACTED.  	A RESTART WAS TRIED BUT NO STARTER ENGAGEMENT.  STARTER AND CONTACTOR WAS CHANGED.  UPON INVESTIGATION, APPEARS STARTER 	REMAINED ENERGIZED DUE TO FAULTY CONTACTOR. THIS FRIED THE STARTER.			1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2006061900097	20060619	00097	CE  	2006	6	19	CA060303004      	1	20050531	G	3243	211111	SHUTTLE VALVE   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					BRAKE ASSEMBLY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											BRAKE SHUTTLE VALVE LEAKING HYDRAULIC FLUID (SKYDROL) INTO PNEUMATIC EMERGENCY BRAKE CONTROL SYSTEM NECESSITATING THE RE	PLACEMENT OF THE EMERGENCY BRAKE CONTROL VALVE P/N 895232-0875.  SHUTTLE VALVE REPLACED SYSTEM CHECK SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006061900150	20060619	00150	WP  	2006	6	19	CA060303016      	1	20051125	G	2842		VALVE           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FUEL SYSTEM	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FUEL SYSTEM SENDER INCORRECT VALVE.  REPLACED SENDER.						1	G	7	1 	3O	3	O		4H12    	1E10				 
2006062100072	20060621	00072	GL  	2006	6	21	CA060303017      	2	20050604	G	7421	CH34168	IGNITER         			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											NO IGNITION.  REPLACED IGNITER.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062100073	20060621	00073	SW  	2006	6	21	CA060303018      	1	20050719	G	2424	206075447007	VOLT REGULATOR  			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  						FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											AT START UP NO CHARGE.  REPLACED VOLTAGE REGULATOR.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062100136	20060621	00136	WP  	2006	6	21	CA060306001      	1	20051001	G	2740	C0559	MOTOR           			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					LATERAL TRIM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			HO	HOVERING       	1			CA											(CAN) TRIM MOTOR NOT OPERATING.  REPLACED TRIM.  (TC NR 20060306001)						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062100137	20060621	00137	WP  	2006	6	21	CA060306002      	1	20051015	G	2740	D1402	CONTROL BOX     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TRIM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			HO	HOVERING       	1			CA											(CAN)  LONGITUDINAL TRIM NOT WORKING. REPLACED TRIM BOX.   (TC NR 20060306002)						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062100138	20060621	00138	WP  	2006	6	21	CA060306003      	1	20051121	G	7810	C1692	SHROUD          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					EXHAUST PIPE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WORN AT END OVER ENGINE EXHAUST PIPE DUE TO LOOSENESS.  REPLACED PART.  (TC NR 20060306003)						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062300165	20060623	00165	EU  	2006	6	23	CA060306010      	1	20050629	G	7931	704A37642043	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL PRESSURE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NO OIL PRESSURE INDICATION.  REPLACED PRESSURE GENDER.  (TC NR 20060306010)						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006062300167	20060623	00167	EU  	2006	6	23	CA060306011      	1	20051014	G	2435		ARMATURE        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				401  		53570					(CAN) START UP SPARK/SMOKE FROM STARTER.  REPLACED STARTER.  (TC NR 20060306011)						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006062300168	20060623	00168	SW  	2006	6	23	CA060306012      	1	20051118	G	5320	269A8598	BRACKET         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRACKET CRACKED.  REPLACED BRACKET.  (TC NR 20060306012)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2006062300170	20060623	00170		2006	6	23	CA060306014      	4	20051028	G	2340	B2272	SWITCH          			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					INTERCOM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRIM INTERMITTENT.  REPLACED SWITCH. (TC NR 20060306014)						1	G	7	1 	3O	3	O		H10WE   	E274				 
2006062300171	20060623	00171	SW  	2006	6	23	CA060306015      	1	20051021	G	2424	15891F	VOLT REGULATOR  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NO CHARGE.  REPLACED VOLTAGE REGULATOR.  (TC NR 20060306015)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062300189	20060623	00189	SW  	2006	6	23	CA060306016      	1	20051028	G	6240	D22A690	TACHOMETER      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	FAILED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN)  NO ROTOR TACH INDICATION. REPLACED TACH.  (TC NR 20060306016)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006070500096	20060705	00096	CE  	2006	7	5	CA060317005      	1	20050907	G	2422		CIRCUIT BOARD   			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	STATIC INVERTER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STATIC INVERTER BOARD CRACKED AND MOISTURE SHORTED BOARD. (TC NR 20060317005)						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006070500209	20060705	00209	EA  	2006	7	5	CA060321010      	2	20050920	G	7322	S123017	CONTROL CABLE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CARB HEAT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2249 								(CAN) THIS REPORT HAS BEEN RESUBMITTED.  THE INTERNAL PART OF THE BOUDEN CABLE WAS FOUND TO BE EXCESSIVELY WORN DURING I	NSPECTION.  SEE ATTACHED PHOTO (TC NR 20060321010)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006070500150	20060705	00150	EA  	2006	7	5	CA060321015      	1	20051215	G	2810	C3PT315	FUEL CELL       			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					WING	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			23509								ALL OF THE BLADDER STYLE FUEL CELLS REQUIRED EXTENSIVE WORK OR REPLACEMENT, PN# C3PT31-5, C3PT32-5, C3PT33-5, C3PT34-5 T	HE FUEL CELLS WERE REPLACED AS REQUIRED.  THE AVERAGE DATE OF THE TANK MANUFACTURE WAS NOTED TO BE 1956.					1	H	7	1 	3R	3	R		A815    	5E2				 
2006070500173	20060705	00173	GL  	2006	7	5	CA060322005      	2	20050810	G	7314	1132431	SPLINE          	CHNDLREVANS 	11331002A1  	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL PUMP	WORN            	W				R	A			AUTOROTATION            	UNSCHED LANDING         			X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA			1288 			J6AKW0079					THE ENGINE LOST POWER BECAUSE THE ENGINE DRIVEN FUEL PUMP FAILED.  THE CAUSE OF THE PUMP FAILURE WAS DISENGAGEMENT OF TH	E DRIVE SHAFT SPLINES FROM THE DRIVER GEAR SPLINES DUE TO EXCESSIVE WEAR.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2006062600099	20060626	00099	SO  	2006	6	26	CA060328003      	1	20051015	G	5730	40659002	SKIN            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11280								ON DE-ICER BOOT REPLACEMENT DUE TO WEAR AND CONDITION FOUND LT WING AND LT HORIZONTAL STAB LEADING EDGE SKINS CORRODED. 	 THERE WERE HOLES THROUGH THE METAL.  SKINS WERE BEYOND REPAIR AND HAD TO BE REPLACED.  RT SIDE WAS FOUND OK.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2006062600104	20060626	00104	SW  	2006	6	26	CA060329003      	1	20050730	G	6320	204040353023	CASE            	BELL        	212040001123	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TRANSMISSION	BROKEN          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA						ABW270					WHILE IN CRUISE, A LOUD BANG WAS HEARD AND AC SHUDDERED.  AC SETTLED OUT AND CREW DIVERTED TO AIRPORT.  INSPECTION OF AC	 REVEALED MAIN TRANSMISSIOM SUPPORT CASE BROKEN AT DRAG LINK ATTACHMENT POINT.  AC GROUNDED AND MAIN TRANSMISSION REPLAC	ED.  AC RELEASED BACK TO SERVICE.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062600106	20060626	00106	EA  	2006	6	26	CA060329005      	2	20050801	G	7230		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 2	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			3971 					CPPS61680			WHILE IN CRUISE, A LOUD BANG WAS HEARD FOLLOWED BY AIRFRAME SHUDDER.  AN EMERGENCY WAS DECLARED AND AIRCRAFT STARTED LAN	DING PROCEDURES.  NR 2 ENGINE INDICATING FAILURE AND ROLLED BACK.  AIRCRAFT SUCCESSFULLY LANDED IN A FIELD.  POWER RECOV	ERY OF NR 2 ENGINE ABORTED DUE TO COMPRESSOR STALL.  AC WAS SHUTDOWN AND GROUNDED UNTIL POWER SECTION COULD BE REPLACED.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062600122	20060626	00122	SO  	2006	6	26	CA060405007      	1	20051125	G	2133	7331802	OUTFLOW VALVE   			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3T*      	GL  	CABIN PRESSURE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						0161					DURING AN EVENT, NR 2 INSPECTION OF THE EMERGENCY PRESSURIZATION SYSTEM, VALVE ASSY (BY-PASS) P/N 73318-00-1) WAS REMOVE	D FROM RT WING ROOT AREA, FURTHER INSPECTION FOUND EXTENSIVE CORROSION IN THIS VALVE AND REDUCER P/N: 584-124 (A55-16-12	).  SYSTEM CLEANED.  BENCH TESTED VALVE, FOUND U/S.  SUSPECT MOISTURE RESTING IN VALVE AND REDUCER OVER A LONG PERIOD OF	 TIME CAUSED VALVE FAILURE.			1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2006061300291	20060613	00291	SW  	2006	6	13	CA060407009      	1	20050427	G	5210	2720063907	RECEPTACLE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	ROTOL	R321	R321482F8   	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29489								WHEN COMPLYING WITH SERVICE LETTER 226-SL-027, WHICH DEALS WITH INSPECTION OF THE DOOR CLICK CLACK RECEPTACLES, TWO WERE	 FOUND CRACKED ON THE PASSENGER DOOR.  THIS IS THE FIRST TWO PASSENGER DOOR RECEPTACLES THIS OPERATOR HAS FOUND CRACKED.	  ONE WAS BROKEN IN HALF WHEN IT WAS REMOVED.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006062600064	20060626	00064	NM  	2006	6	26	CA060502007      	1	20050506	G	7830		HEAT SHIELD     			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					THRUST REVERSER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 1 ENG RT THRUST REVERSER COWL AFT HEAT SHIELD DAMAGED (DISBONDED).  REPAIR FOR HEATSHIELD IN OEM MANUAL. (TC NR	 20060502007)					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2006071100117	20060711	00117	WP  	2006	7	11	CA060503005      	2	20051220	G	7230	8939735	PLENUM          			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE3316     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA		CFTWO						P20362C			(CAN) AC TOOK OFF, AC CRASHED, POST-CRASH FIRE OCCURRED. AC WAS DESTROYED. BOTH PILOTS FATALLY INJURED. DURING TEAR-DOWN	 OF RT ENG (WHICH WAS FOUND TO BE OPERATING AT HIGH POWER ON IMPACT) P3, BLEED AIR BOSS WELDS WERE EXAMINED BY FPI USING	 A 2X POWER MAGNIFYING GLASS WITH NO CRACKS NOTED. LOCATION BETWEEN P3, BLEED AIR BOSSES WAS THEN SECTIONED. A SMALL CRA	CK ABOUT .5 MM DEEP AND 3.5 MM LONG WAS VISUALLY DETECTED ALONG TOE OF P3 BOSS WELD. CRACK OPENED FOLLOWING RELEASE OF R	ESIDUAL STRESSES WHEN CUT. CRACK WAS EXAMINED, FOUND TO BE FATIGUE IN NATURE, ORIGINATING FROM OUTER SURFACE. NO FLUORES	CENT PENETRANT RESIDUE WAS NOTED ON SURFACES OF CRACK, INDICATING PENETRANT HAD NOT PENETRATED CRACK.	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P15EA	 
2006071900014	20060719	00014	WP  	2006	7	19	CA060503006      	2	20051220	G	7230	8939735	PLENUM          			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE3316     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								P20190C			(CAN) AIRCRAFT TOOK OFF FROM AIRPORT RUNWAY 15 OR A COURIER FLIGHT. THE AIRCRAFT CRASHED ABOUT 500 METERS EAST OF, AND A	PPROXIMATELY ABEAM, THE SOUTH END OF RUNWAY 15, ABOUT 300 METERS BEYOND THE AIRPORT PERIMETER. A POST-CRASH FIRE OCCURRE	D. THE AIRCRAFT WAS DESTROYED. THE TWO PILOTS WERE FATALLY INJURED.  A TEAR-DOWN OF THE TWO ENGINES HAS DETERMINED THAT 	THE LT ENGINE FAILED AS A RESULT OF THE COMBUSTION CASE ASSEMBLY (PLENUM) RUPTURING ALONG ITS ENTIRE LENGTH AND MUCH OF 	ITS CIRCUMFERENCE. THE ORIGIN OF THE RUPTURE WAS FOUND TO BE A FATIGUE CRACK IN A REINFORCING WELD BETWEEN THE P3 AND BL	EED AIR BOSSES.  (TC NR 20060503006)	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P15EA	 
2006070500222	20060705	00222	CE  	2006	7	5	CA060509005      	1	20050517	G	2910	105932B	POWERPACK       			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	HYD SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) LANDING GEAR FAILED TO EXTEND.  CREW ACTIVATED EMERGENCY EXTENSION.  STILL NO INDICATION ON RT GEAR POSITION.  SWI	TCHED BULBS ON GEAR INDICATOR AND DISCOVERED ONE BULB U/S.  LANDING CARRIED OUT NORMALLY.  FOUND HYDRAULIC POWER PUMP MO	TOR BRUSHES WORN.  REPLACED WITH OVERHAULED UNIT, REPLACED CONTROL RELAY AS  WELL.  RECORDS RESEARCH DISCOVERED AVERAGE 	LIFE IS APPROX. 1700 HOURS BETWEEN FAILURES, WE HAVE ELECTED TO PLACE THIS PART ON A 1500 HOUR REPLACEMENT. (TC NR 20060	509005)		1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2006091300052	20060913	00052	GL  	2006	9	13	CA060803002      	2	20050811	G	7261	03807205	FILTER          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SCAVENGE OIL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A SCAVENGE OIL FILTER REPLACEMENT IAW INSPECTION PROGRAM IT WAS NOTED THAT THE FILTER WAS DIFFE	RENT THAN THE REPLACEMENT FILTER. THE CORRECT FILTER FOR THE SCAVENGE OIL FILTER IS P/N 038088-08, WHAT WAS FOUND IN THE	 SCAVENGE OIL FILTER HOUSING WAS AN P/N 038072-05 FILTER. WE ARE INVESTIGATING HOW THIS OCCURRED.  (TC NR 20060803002)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120800056	20061208	00056	WP  	2006	12	8	CA061002008      	1	20050915	G	6320	369D25146	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TRANSMISSION	SPALLED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				3097 		1810					(CAN) M/R TRANSMISSION CHIP DETECTOR FOUND TO HAVE A LARGE AMOUNT OF METAL.  SOURCE FOUND TO BE THE T/R O/P PINION ROLLE	R BEARING INNER RACE.  THE INNER RACE WAS FOUND TO HAVE HEAVY SPALLING IN A LARGE AREA.  (APPROXIMATELY .550 INCH X .200	 INCH) (TC NR 20061002008)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006120800075	20061208	00075	EU  	2006	12	8	CA061004002      	1	20051028	G	5620	M1052330115	WINDOW          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					DOOR	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAD DEPARTED FROM HELICOPTER PAD AND WAS TRANSITING TO WEST COAST.  SHORTLY AFTER TAKE-OFF AND ALMOST IN 	CRUISE, THE PASSENGER SITTING IN THE LT CREW SEAT HEARD A NOISE.  AT THAT TIME HE NOTICED THAT THE WIND DEFLECTOR HAD BE	COME SEPARATED AT THE LOWER POINT OF THE WINDOW.  THE PASSENGER MANAGED TO OPEN THE SLIDING WINDOW AND SECURE THE REMAIN	ING PORTION OF THE DEFLECTOR IN HIS HAND.  THE PILOT AT THAT POINT ELECTED TO RETURN THE AIRCRAFT TO THE POINT OF DEPART	URE.  UPON ARRIVAL BACK AT POINT OF DEPARTURE, THE REMAINING PORTION OF THE WIND DEFLECTOR WAS REMOVED, AIRCRAFT INSPECT	ED FOR ANY DAMAGE CAUSED BY FOD, AND THEN RETURNED TO SERVICE. (TC NR 20061004002)	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006120800104	20061208	00104	NM  	2006	12	8	CA061005008      	1	20051021	G	5610	8SC0043007	WINDSHIELD      			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 53 MINUTES INTO FLIGHT, SOON AFTER LEAVING FL 190, CREW HEARD A LONG (BANG) FOLLOWED BY THE OBSERVAT	ION OF THE CAPTAINS MAIN WINDSHIELD SHATTERING, CREW CONTINUED DESCENT TO FL 100 AT RESTRICTED AIRSPEED OF 188 KNOTS AN	D MAINTAINED A CABIN DIFFERENTIAL OF 2.6PSI IAW QRH. ENGINEERING CHANGED THE AIRCRAFT WINDSHIELD IAW MM 56-10-11.  AIRCR	AFT RETURNED TO SERVICE.  (TC NR 20061005008)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006121100365	20061211	00365		2006	12	11	CA061107006      	4	20051215	G	8300	311433701	GEARBOX         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A6       	52043	EA  					ENGINE	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				937  							(CAN) THE ENGINE LOST OIL PRESSURE IN FLIGHT RESULTING IN LOSS OF THE AIRCRAFT.  SUBSEQUENT INVESTIGATION REVEALED THAT 	A PROTECTIVE COATING HAD BEEN IMPROPERLY APPLIED TO THE AGB HOUSING AT THE PRIOR ENGINE OVERHAUL.  THE COATING DEBONDED 	AND BLOCKED THE OIL PUMP INLET RESULTING IN LOSS OF OIL PRESSURE. IT WAS FURTHER DETERMINED THAT RECOMMENDED PERIODIC VI	SUAL INSPECTIONS OF THE PUMP INLET HAD NOT BEEN PERFORMED BY THE OPERATOR. (TC NR 20061107006)			1	L	7	1 	3T	3	T	RT	A78EU   	E4EA				 
2006121300081	20061213	00081	EA  	2006	12	13	CA061201005      	1	20051228	G	5521	C6TE1064	RIB             	DHAV        		DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AD CF-82-21 R1 USING A BORESCOPE, CRACKS WERE FOUND AT THE ATTACHMENT POINT OF THE TORQUE TUBE TO	 THE ELEVATOR RIB. SEE PHOTOS AND DAMAGE REPORT. (TC NR 20061201005)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007050700119	20070507	00119	SO  	2007	5	7	CA061219008      	1	20051212	G	7714		INDICATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE RPM	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) TACH CABLE FAILED WHILE ON TAXI CAUSING NO RPM INDICATION.  (TC NR 20061219008)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007080800139	20070808	00139	CE  	2007	8	8	CA070214003      	1	20051118	G	5511	043200156	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION, VERIFICATION OF AD 80-11-04, THE TECHNICIAN FOUND A CRACKED BRACKET.  CLOSER INSPECTIO	N INDICATED THAT THE SPAR WAS ALSO CRACKED.  (TC NR 20070214003)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2005062200039	20050622	00039	CE  	2005	6	22	CAR110           	1	20050604	G	2130	310112	MIXING VALVE    			RKWELL	NA265 	NA26560     	7630106	CE  										E/E BAY	NOT BONDED      	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CE	03	XCJDC					306145				HOT AIR MIXING VALVE WAS OVERHAULED BY ROCKER, 1-25-05, REF WO 56559.  INSTALLED IN AIRCRAFT FROM STOCK ON 6-4-05.  DURI	NG FUNCTIONAL TEST FLIGHT FOR PRESSURIZATION PROBLEM, THE UP STREAM FLANGE SEPARATED FROM VALVE HOUSING.  RELEASING BLEE	D AIR INTO AFT EQUIPMENT BAY.  AFT FUSELAGE HOT LIGHTS ILLUMINATED.  FLIGHT ABORTED.  RED RUBBERIZED INSULATION MELTED/B	URNED AWAY NEAR LEAK.  POST FLIGHT EVALUATION REVEALED FLANGE NOT WELDED/BRAZED TO HOUSING.			2	L	7	2 	4J			RT	A2WE    					 
2005030800276	20050308	00276	WP  	2005	3	8	COOSDR05003      	1	20050125	G	5310		DOOR FRAME      			DOUG  	DC9   	DC915F      	3022037	WP  	PWA   	JT8   	JT8D*       	 	NE  					FUSELAGE	CRACKED         	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	785TW					47015				FWD CARGO COMPARTMENT, DOOR JAMB, STUB BEAM, PN 5921718-1, SHORT FLANGES CRACKED.  (K)						2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2006031500036	20060315	00036	CE  	2006	3	15	CQWR20005006     	1	20050805	G	2820	651631155	LINE            			CESSNA	500   	560CESSNA   	2076750	CE  										FUEL SYSTEM	DAMAGED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	808Q	2048 				5600619				DURING PHASE 1 THRU 5 INSPECTION, FOUND REFUEL/DEFUEL FLOW LINE ASSY (P/N 6516311-55) SAWED BY THE FORWARD FLAP CROSS-OV	ER CABLE.  THIS LINE ASSY HAD BEEN DAMAGED MORE THAN 50 PERCENT OF THE WALL THICKNESS, AND IS LOCATED IN THE LEFT WING R	OOT DRY BAY AREA FORWARD OF THE FLAP WELL.  THE LINE ASSY IS SUPPORTED BY TWO ADEL CLAMPS.  A DESCRIPTION OF THIS REPORT	 AND PICTURES HAVE BEEN SUBMIT TO CESSNA/CIATION VIA SERVICE CONDITION REPORT NR 200470.			2	L	7	2 	4F			RT	A22CE   					 
2005041100025	20050411	00025	CE  	2005	4	11	CWQR20050001     	1	20050126	G	3010	66212812930	HEAT SHIELD     			CESSNA	560   	560XL       	2076702	CE  										WINGS	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	697QS	3352 				5605197				DURING INSPECTION FOUND THE LEADING EDGE HEAT SHIELD FLANGE CRACKED ON BOTH LEFT AND RIGHT WINGS.  SUBMITTED CESSNS/CITA	TION SERVICE CONDITION REPORT 181187 WITH PICTURES.					2	L	7	2 	4F			RT	A22CE   					 
2005041100026	20050411	00026	CE  	2005	4	11	CWQR20050002     	1	20050128	G	2731	MS21044N3	NUT             			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	WRONG PART      	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	688Q					5605188				PILOT FOUND ELEVATOR TRIM OUT OF RIG.  TECHICIAN FOUND EXCESSIVE PLAY IN TRIM WHEEL, ALLOWING TRIM INDICATOR POINTER TO 	JUMP GROOVE IN TRIM WHEEL.  FOUND TRIM WHEEL BOLT (P/N AN3-57) NOT TO HAVE NUT (P/N MS21044N3) INSTALLED.  NUT WAS FOUND	 IN AIRCRAFT BELLY.  BOLT IS DRILLED FOR COTTER PIN, AND FIBER LOCK NUT WAS INSTALLED.  CHECKED IPC, FOUND PROPER HARDWA	RE WAS INSTALLED.  SUGGEST CASTELLATED NUT BE INSTALLED.  SUBMITTED CITATION SERVICE CONDITION REPORT 181391.			2	L	7	2 	4F			RT	A22CE   					 
2005041100024	20050411	00024	CE  	2005	4	11	CWQR20050003     	1	20050406	G	2842	99144272	SENSOR          			CESSNA	560   	560XL       	2076702	CE  										LOW FUEL	ARCED           	B			DXTA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	05	671Q	4538 				5605071				DURING INSPECTION FOUND LOW LEVEL FUEL SWITCH INOP AND THE APPEARANCE OF MISSING MATERIAL AND ARCING BETWEEN FLOAT AND S	WITCH BODY WHEN FLOAT WAS IN THE UP POSITION.  THIS SWITCH HAS BEEN SENT TO CESSNA FOR EVALUATION AND SUBMITTED CITATION	 SERVICE CONDITION REPORT 187403.				2	L	7	2 	4F			RT	A22CE   					 
2005050300276	20050503	00276	CE  	2005	5	3	CWQR20050004     	1	20050411	G	7830	64ND784093	SUPPORT BRACKET 			CESSNA	560   	560XL       	2076702	CE  										THRUST REVERSER	MISINSTALLED    	B			DXTA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	626QS	4261 				5605293				DURING PHASE 1-4 INSPECTION FOUND LOWER OUTBOARD BARREL SUPPORT BRACKETS INSTALLED INCORRECTLY DURING MANUFACTURE.						2	L	7	2 	4F			RT	A22CE   					 
2005071100068	20050711	00068	CE  	2005	7	11	CWQR2005005      	1	20050622	G	2810	68C48	DRAIN           			CESSNA	560   	560XL       	2076702	CE  										FUEL SYS	POPPED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	609QS	566  				5605522				FORWARD RT FUSELAGE STATIC DRAIN VALVE NOT FLUSH.  NEW UNIT ORDERED AND INSTALLED, LEAK CHECKED.  DURING REMOVAL OF SUSP	ECTED BAD PART, ENTIRE CORE POPPED OUT, CONDITION WOULD HAVE DIRECTLY OPENED STATIC SYSTEM.  CORE OF UNIT APPEARS TO BE 	PRESSED AND GLUED INTO PLACE, VERY LITTLE GLUE RESIDUE APPEARED ON CORE OR BASE. THIS IS A RVSM A/C. ALSO, THE VERBIAGE 	IN THE IPC REFERS TO IT AS A FUEL DRAIN NOT A STATIC DRAIN.			2	L	7	2 	4F			RT	A22CE   					 
	20081128		NM  	2008	11	28	DL757081592      	1	20051027	G	5210		SKIN            			BOEING	757   	757232      	1384965	NM  										L1 DOOR	CRACKED         	C			DALA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	27	610DL					22817				SUPPLEMENTAL SDR FUSELAGE/SKIN L-1 DOOR CUTOUT/UPPER FWD CORNER-CRACK IAW ERA 090914-14.  C/W ERA 090914-14.						2	L	7	2 	4F			RT	A2NM    					 
2005071200063	20050712	00063	NM  	2005	7	12	DU4R00507139     	1	20050701	G	5754		SKIN            			BOEING	737   	737522      	138449F	NM  										NR 4 SLAT	GOUGED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA					26739				RIGHT WING NR 4 SLAT HAS SKIN CHAFED THRU AT T/E LOWER INBOARD SKIN SURFACE.						2	L	7	2 	4F			RT	A16WE   					 
2005062400050	20050624	00050	NM  	2005	6	24	DU4R0506031      	1	20050603	G	5321		FLOORBOARD      			DOUG  	MD88  	MD88        	3023688	NM  										CABIN	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				PAX CABIN FLOORBOARD BETWEEN L/S SEAT TRACK AT FS 389 - 465 HAS A VERY SOFT AND VOIDED AREA.						2	L	7	2 	4F			RT	A6WE    					 
2005062700042	20050627	00042	NM  	2005	6	27	DU4R05060310     	1	20050603	G	5300		PANEL           			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	PUNCTURED       	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				RT CABIN STA 693 PANEL D9 IS PUNCTURED.						2	L	7	2 	4F			RT	A6WE    					 
2005062700043	20050627	00043	NM  	2005	6	27	DU4R05060311     	1	20050603	G	5300		PANEL           			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	PUNCTURED       	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				RT CABIN STA 350.5 PANEL D2 IS PUNCTURED.						2	L	7	2 	4F			RT	A6WE    					 
2005062700044	20050627	00044	NM  	2005	6	27	DU4R05060312     	1	20050603	G	5300		PANEL           			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	PUNCTURED       	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				R/H CABIN STA. 335 PANEL B2 IS PUNCTURED.						2	L	7	2 	4F			RT	A6WE    					 
2005062700045	20050627	00045	NM  	2005	6	27	DU4R05060313     	1	20050603	G	5300		PANEL           			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	PUNCTURED       	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				RT CABIN STA. 655 AND 674 PANEL B8 HAS PUNCTURES.						2	L	7	2 	4F			RT	A6WE    					 
2005062400051	20050624	00051	NM  	2005	6	24	DU4R0506032      	1	20050603	G	5347		SEAT TRACK      			DOUG  	MD88  	MD88        	3023688	NM  										FWD CABIN	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				FWD CABIN 256 LBL 24 SEAT TRACK LOWER LEG IS CORRODED.						2	L	7	2 	4F			RT	A6WE    					 
2005062400057	20050624	00057	NM  	2005	6	24	DU4R0506033      	1	20050603	G	5321		FLOOR PANEL     			DOUG  	MD88  	MD88        	3023688	NM  										CABIN	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				CABIN FLOOR PANEL AT FS 875 - 864 HAS A SOFT SPOT LT OVER FUEL ACCESS PANEL.						2	L	7	2 	4F			RT	A6WE    					 
2005062400061	20050624	00061	NM  	2005	6	24	DU4R0506034      	1	20050603	G	5321		FLOORBOARD      			DOUG  	MD88  	MD88        	3023688	NM  										CABIN	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				FLOORBOARD AT R/S SEAT TRACK STA 1193-1250 HAS SOFT SPOTS.						2	L	7	2 	4F			RT	A6WE    					 
2005062400062	20050624	00062	NM  	2005	6	24	DU4R0506035      	1	20050603	G	5321		FLOOR PANEL     			DOUG  	MD88  	MD88        	3023688	NM  										CABIN	DELAMINATED     	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				LT FLOOR PANEL FS 866 BL 44.5 TO 24.5 DELAMINATED AND SOFT SPOTS.						2	L	7	2 	4F			RT	A6WE    					 
2005062400063	20050624	00063	NM  	2005	6	24	DU4R0506036      	1	20050603	G	5320		THRESHOLD       			DOUG  	MD88  	MD88        	3023688	NM  										AFT CARGO BAY	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				AFT CARGO DOOR THRESHOLD HAS CORROSION AROUND FASTENER HOLES AT L-28R.						2	L	7	2 	4F			RT	A6WE    					 
2005062400064	20050624	00064	NM  	2005	6	24	DU4R0506037      	1	20050603	G	5320		FLOOR SUPPORT   			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				CENTER FLOORBOARD AT FS 807 TO 886 HAS CRACKED SUPPORT ANGLE.						2	L	7	2 	4F			RT	A6WE    					 
2005062400065	20050624	00065	NM  	2005	6	24	DU4R0506038      	1	20050603	G	5330		SKIN            			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				FUSELAGE SKIN AT FS 224 L-19L 1.2 BY 1.9 IN. DENT 0.043 IN. DEPTH D/X 27.9.						2	L	7	2 	4F			RT	A6WE    					 
2005062700041	20050627	00041	NM  	2005	6	27	DU4R0506039      	1	20050603	G	5330		SKIN            			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	12FQ					49766				DENT AT FS 237 LEFT LONGERON 17 AND 18L .021 BY .750 IN D/X 35.7.						2	L	7	2 	4F			RT	A6WE    					 
2005070700014	20050707	00014	NM  	2005	7	7	DU4R0507002      	1	20050701	G	5754		SKIN            			BOEING	737   	737522      	138449F	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NR 3 SLAT	CHAFED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA					26739				LT WING NR 3 SLAT HAS SKIN CHAFED THRU AT T/E LOWER IB SKIN SURFACE.  S/O 269008, OPS NR 24936						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005070700020	20050707	00020	NM  	2005	7	7	DU4R0507003      	1	20050630	G	5330		SKIN            			BOEING	737   	737         	UTILSYS	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	387UA					24662				DENT AND CREASE IN LOWER FUSELAGE SKIN AT BS 907 BETWEEN S-25R - S-26R.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005071200086	20050712	00086	NM  	2005	7	12	DU4R0507126      	1	20050630	G	5313		STRINGER        			BOEING	737   	737522      	138449F	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	387UA					24662				CABIN S-15L CRACKED, ALSO END FITTING.						2	L	7	2 	4F			RT	A16WE   					 
2005070700022	20050707	00022	NM  	2005	7	7	DU4R0507128      	1	20050630	G	5330		SKIN            			BOEING	737   	737         	UTILSYS	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	387UA					24662				DL/H UPPER FUSELAGE SKIN S-7L HAS 1 EA. CHERRY MAX RIVET FS 420.  S/O NR 134005, OPS NR 20347.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2005071200069	20050712	00069	NM  	2005	7	12	DU4R0507133      	1	20050630	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				DENT IN LEFT FUSELAGE EXTERIOR SKIN BS 935 S-26L.						2	L	7	2 	4F			RT	A16WE   					 
2005071200070	20050712	00070	NM  	2005	7	12	DU4R0507134      	1	20050630	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				CREASES IN DENTS AND ON TOP OF STRINGER 27R AT BS 951 - 952 A/Y = 24.7 A/Y 1.875 X .076.						2	L	7	2 	4F			RT	A16WE   					 
2005071100177	20050711	00177	NM  	2005	7	11	DU4R0507135      	1	20050630	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				CREASE IN DENT AT BS 971 BETWEEN S-24L-25L 2 INCHES X .86 A/Y = 23.3.  S/O NR 109002, OPS NR 25863.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071200087	20050712	00087	NM  	2005	7	12	DU4R0507137      	1	20050701	G	5330		SKIN            			BOEING	737   	737500      	138449E	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA									FOUND DENT WITH OLD YELLOW DOTS 20 INCHES AFT OF DOOR 2L.						2	L	7	2 	4F			RT	A16WE   					 
2005071200064	20050712	00064	NM  	2005	7	12	DU4R0507141      	1	20050701	G	5753		SKIN            			BOEING	737   	737522      	138449F	NM  										TE FLAP	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA					26739				RIGHT WING INBOARD FORE FLAP LOWER SKIN SURFACE HAS NUMEROUS DENTS.						2	L	7	2 	4F			RT	A16WE   					 
2005071200065	20050712	00065	NM  	2005	7	12	DU4R0507143      	1	20050701	G	5753		SKIN            			BOEING	737   	737522      	138449F	NM  										TE FLAP	DELAMINATED     	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	954UA					26739				RIGHT WING INBOARD MID FLAP WEDGE LOWER T/E SKIN SURFACE DELAMINATED AND DENTED.						2	L	7	2 	4F			RT	A16WE   					 
2005071100157	20050711	00157	NM  	2005	7	11	DU4R0507144      	1	20050706	G	5311		FRAME           			BOEING	737   	7373S1      	138447S	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					BULKHEAD	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				BS 178 BULKHEAD RT SIDE AFT SIDE FRAME HAS EVIDENCE OF CRACK ABOVE AND BELOW WL 207.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071100154	20050711	00154	NM  	2005	7	11	DU4R0507145      	1	20050706	G	5312		BULKHEAD        			BOEING	737   	7373S1      	138447S	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				CRACK APPROX. 5.5 INCHES BELOW WL 207 IB SIDE LBL 5.7 APPROX. 1.2 INCH IN LENGTH AT BS 178 BULKHEAD.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071500021	20050715	00021	NM  	2005	7	15	DU4R0507146      	1	20050706	G	5312		BULKHEAD        			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				CRACK APPROX 8 IN BELOW WL 207 INBD SIDE RBL 5.7 APPROX 1.5" IN LENGTH AT BS 178 BULKHEAD.						2	L	7	2 	4F			RT	A16WE   					 
2005071500022	20050715	00022	NM  	2005	7	15	DU4R0507147      	1	20050706	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				DENT 3 IN DIAMETER, DEPTH .015 INCHES FUSELAGE S 1070 S-14L FRONTIER DENT TALLY ITEM NR 3.						2	L	7	2 	4F			RT	A16WE   					 
2005071100155	20050711	00155	NM  	2005	7	11	DU4R0507148      	1	20050706	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				DENT AT RT EXTERNAL FUSELAGE SKIN AT BS 391.5 BETWEEN S-22R AND S-23R.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071500023	20050715	00023	NM  	2005	7	15	DU4R0507149      	1	20050706	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				DENT AT LT EXTERNAL FUSELAGE SKIN AT BS 997.5 BETWEEN S-13L AND S-14L.						2	L	7	2 	4F			RT	A16WE   					 
2005071500029	20050715	00029	NM  	2005	7	15	DU4R0507150      	1	20050706	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				DENT AT RT EXTERNAL FUSELAGE SKIN AT BS 876 S-21R AND S-22R.						2	L	7	2 	4F			RT	A16WE   					 
2005071100140	20050711	00140	NM  	2005	7	11	DU4R0507153      	1	20050707	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				FUSELAGE SKIN HAS DENT AT BS 480 S-26R - S-28R.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2005071400009	20050714	00009	NM  	2005	7	14	DU4R0507155      	1	20050707	G	5313		STRINGER        			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				STRINGER 27R CRACKED.						2	L	7	2 	4F			RT	A16WE   					 
2005071400010	20050714	00010	NM  	2005	7	14	DU4R0507156      	1	20050707	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				FUSELAGE EXTERNAL SKIN CRACKED AT S-24R BETWEEN BS 727D - 727E.						2	L	7	2 	4F			RT	A16WE   					 
2005071400011	20050714	00011	NM  	2005	7	14	DU4R0507157      	1	20050707	G	5330		SKIN            			BOEING	737   	7373S1      	138447S	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311FL					24856				DENT AT RT EXTERNAL FUSELAGE AT BS 871 BETWEEN S-22R AND S-23R.						2	L	7	2 	4F			RT	A16WE   					 
2005072900045	20050729	00045	NM  	2005	7	29	DU4R0507159      	1	20050728	G	5311		FRAME           			BOEING	757   	757232      	1384965	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				AFT CARGO BAY LT BS 1340 AT S-25L MAIN FRAME HAS DENT.						2	L	7	2 	4F			RT	A2NM    					 
2005072900046	20050729	00046	NM  	2005	7	29	DU4R0507160      	1	20050728	G	5311		FRAME           			BOEING	757   	757232      	1384965	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				AFT CARGO BAY LT BS 1480 AT S-25L MAIN FRAME HAS DENTS.						2	L	7	2 	4F			RT	A2NM    					 
2005072900067	20050729	00067	NM  	2005	7	29	DU4R0507161      	1	20050728	G	5311		FRAME           			BOEING	757   	757232      	1384965	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				AFT BAG PIT LT BS 1500 AT S-26L MAIN FRAME HAS DENT/CRACK.						2	L	7	2 	4F			RT	A2NM    					 
2005072900051	20050729	00051	NM  	2005	7	29	DU4R0507165      	1	20050728	G	5320		SHEAR WEB       			BOEING	757   	757232      	1384965	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				CORROSION IN SHEAR WEB SURFACE FROM BS 1681.8 - 1720 BL 0 - BL 60R INCLUDING FASTENERS.						2	L	7	2 	4F			RT	A2NM    					 
2005072900065	20050729	00065	NM  	2005	7	29	DU4R0507166      	1	20050728	G	5310		CREASE BEAM     			BOEING	757   	757232      	1384965	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				CORROSION ON CREASE BEAM AT 364 - 371 RBL 65.						2	L	7	2 	4F			RT	A2NM    					 
2005072900072	20050729	00072	NM  	2005	7	29	DU4R0507168      	1	20050728	G	5320		SUPPORT         			BOEING	757   	757232      	1384965	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				CRACKED/TORN METAL SUPPORT IN CABIN FUSELAGE AT BS 1040 - 1060 JUST AFT OF FLOORBOARD 1020A.						2	L	7	2 	4F			RT	A2NM    					 
2005072900106	20050729	00106	NM  	2005	7	29	DU4R0507170      	1	20050728	G	5210		DOOR FRAME      			BOEING	757   	757232      	1384965	NM  										PAX DOOR	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				RT NR 2 DOOR ON FRAME 27 IS CRACKED.						2	L	7	2 	4F			RT	A2NM    					 
2005072900074	20050729	00074	NM  	2005	7	29	DU4R0507171      	1	20050728	G	5210		DOOR            			BOEING	757   	757232      	1384965	NM  										R4	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	624DL					22914				R-4 DOOR IS DENTED ON THE LOWER AFT CORNER.						2	L	7	2 	4F			RT	A2NM    					 
2005051700195	20050517	00195	NM  	2005	5	17	DU4R20050428     	1	20050428	G	5320		FLOOR SUPPORT   			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	312FL					24569				CORROSION AT FLOORBOARD ANGLE SUPPORT FROM BS 947 - 1000 LBL 68.						2	L	7	2 	4F			RT	A16WE   					 
2005042000066	20050420	00066	SO  	2005	4	20	DUKESPUMPMPG     	2	20050405	G	7314	41400015RX	PUMP            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					FUEL SYSTEM	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	21	PKMPG		321  			U20606585				PUMP IS LEAKING AT THE SEAL AT THE BASE OF THE PUMP, NEAR DRAIN PIPE.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2005042000065	20050420	00065	SO  	2005	4	20	DUKESPUMPPKMP    	2	20050405	G	7314	41400015RX	PUMP            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					FUEL SYSTEM	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	PKMPG		321  			U20606585				PUMP IS LEAKING AT THE SEAL AT THE BASE OF THE PUMP-NEAR/AT DRAIN PIPE.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2005072600314	20050726	00314	CE  	2005	7	26	DYCR200532202    	1	20050726	G	3240	90C897001	BRAKE ASSY      			CESSNA	500   	550         	2076604	CE  										ZONE 700	DAMAGED         	B			DYCR	C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	07	550KA	171  				5500279				BRAKE IS PART OF MTOW STC BY NEWFLIGHT. BRAKE AND WHEEL ASSEMBLY FIT FINE, HOWEVER AFTER SEVERAL FLIGHT HOURS THE BRAKE 	LUGS ON THE INNER WHEEL HALF RUB THE PIN IN THE LOWER TORQUE LINK DAMAGING THE WHEEL HALF AND THE TORQUE LINK. AXLE NUT 	IS TORQUED AT INITIAL INTALL, BUT IT WAS NOTED UPON THIS DISCREPANCY THAT THE NUT WAS NOW ONLY FINGER TIGHT. LOCK SCREWS	 AND SAFETY WIRE WERE STILL IN PLACE.			1	L	7	2 	4F				A22CE   					 
2005042600010	20050426	00010	GL  	2005	4	26	EAHR200500001    	1	20050308	G	6520	28135079	SPACER          	ENSTRM      		ENSTRM	F28   	280FX       	3300506	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					T/R GEARBOX	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		1200 	1200 		2551794T	2079				CRACK ON ID OF SPACER OF TAIL ROTOR GEARBOX.						1	G	7	1 	3O	3	O		H1CE    	1E10				 
2005102400170	20051024	00170	GL  	2005	10	24	EAHR200500002    	1	20050930	G	8120	037360115	ADAPTER         			ENSTRM	F28   	F28F        	3300412	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					TURBOCHARGER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	8095	4039 	10   			754	L2516051A			WELD BROKEN AT TURBO-CHARGER FLANGE.						1	G	7	1 	3O	3	O		H1CE    	1E10				 
2005110700168	20051107	00168	GL  	2005	11	7	EAHR200500003    	1	20051101	G	2430	VR152811B	GCU             			ENSTRM	F28   	ENSTROM480  	       	GL  	ALLSN 	250C  	250C20      	03013	GL  					DC SYSTEM	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		735  				5025	CAE845049			GENERATOR CONTROL UNIT CAUSES GENERATOR RELAY TO CYCLE ON AND OFF.						1	G	7	1 	3O	3	U	NC	H1CE    	E4CE				 
2006010500268	20060105	00268	SO  	2006	1	5	EC3R20050001     	1	20051121	G	3230		LANDING GEAR    	AID         		GULSTM	GV    	GULFSTREAMGV	3980116	SO  										RT MLG	MALFUNCTIONED   	B			EC3R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	09	225GV					672				RT MAIN LANDING GEAR STUCK IN TRANSIT.  WOULD NOT FULLY RETRACT OR EXTEND.  EVENTUALLY WAS ABLE TO GET GEAR DOWN AND LOC	KED,  UNEVENTFUL LANDING.					2	L	7	2 	4F			RT	A12EA   					 
2005072000116	20050720	00116	CE  	2005	7	20	ERYR682D         	1	20050715	G	2750	45A6103511	CABLE           			BEECH 	MU300 	400A        	1155402	CE  										ZONE 500	BROKEN          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	11	746TA	6580 				RK146				FLAP FOLLOW-UP CABLE WAS DISCOVERED CORRODED AND BROKEN IN HALF DURING AN INSPECTION.						2	H	7	2 	4F			RT	A16SW   					 
2005102800047	20051028	00047	GL  	2005	10	28	EY2R77637        	3	20051011	G	6114	2A34C203	HUB             	MCAULY      	2A34C203    	CESSNA	172   	R172K       	2072431	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03					776084			776084		PITTING CORROSION ON INTERNAL SURFACES OF PROPELLER HUB.						1	H	7	1 	3O				3A17    		5	C	P3EA	 
2005062800150	20050628	00150	SO  	2005	6	28	F8ZR871Y         	1	20050606	G	8011		MOUNT           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					STARTER	CRACKED         	B			F8ZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	429PA				E101996	2843487				MOUNTING PLATE STRESSED CRACKED.  IDENTICAL TO OTHER FAILURES.  CRACKS ON BOTH UNITS WERE 2 INCHES LONG.  (K)						1	L	7	1 	3O	3	O		2A13    	E286				 
2005071800222	20050718	00222	CE  	2005	7	18	FAA0507001       	1	20050707	G	3213	2500404511	STRUT           			HELIO 	H250  	H250        	4300302	CE  										MLG	FAILED          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	05		7004 				2530				RIGHT LANDING GEAR FAILED DURING TAXI.						1	H	7	1 	3O				1A8     					 
2005060100021	20050601	00021		2005	6	1	FAAAL01002       	1	20050512	G	2710		TURNBUCKLE      																	AILERON	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01										FSDO SENT INFO LETTER TO ALL IA`S IN DISTRICT REGARDING TURNBUCKLES CRACKING AT ENDS THUS LOOSING STRUCTURAL INTEGRITY O	F TURNBUCKLE ON PRIMARY FLT CONTROLS AS A RESULT OF SURVEILIANCE CONDUCTED IN DISTRICT, DISCOVERING PROBLEM.  AS A RESUL	T OF LETTER MECHANIC GAVE OFFICE AFTER OFFICE SENT OUT LETTER REGARDING TURNBUCKLES AND AFTER AC WAS INSPECTED. TURNBUCK	LE WAS INSTALLED ON AN AILERON CONTROL CABLE.  THIS TURNBUCKLE HAS NO V NOTCH ALLOWING FOR CLIPS TO BE USED.  RECOMMEND 	AD BE IMPLEMENTED MANDATING REPLACEMENT OF ALL TURNBUCKLES THAT DO NOT HAVE A DATE ON THEM.  DOCUMENT RECOMMENDS THE ACT	ION OF NOT REUSING TURNBUCKLES W/DATE OF 1978 OR PRIOR.  MS21251M AND PHOTO OF TURNBUCKLE MFG IN APPROX 1952.(K)														 
2005092600081	20050926	00081	CE  	2005	9	26	FCPR200500020    	1	20050812	G	3250	50820042601	BARREL          			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					NLG STEERING	BROKEN          	B			FCPR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	09	544PS	8140 				FA90				SHARP TAXI TURN, NOSE WHEEL STEERING BARREL BROKE AT RETAINER AREA.  C/W SB 220 TO PREVENT RECURRENCE.  (K)						2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2005080200138	20050802	00138	EU  	2005	8	2	GQRR082005       	1	20050802	G	3232	D52177	HOLDER          	MESSIER     		AMD   	FALC20	FALCON200   	2730150	EU  										ACTUATOR PACKING	BROKEN          	B			GQRA	O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			SW	05					064					THE PACKING HOLDER P/N D52177 INSIDE OF THE MAIN GEAR ACTUATOR BROKE APART IN TWO PIECES.THIS CAUSED LOSS OF HYDRAULIC F	LUID TO THE AIRCRAFT. THIS PART HAD NOT BEEN MODIFIED IAW SB TO PREVENT THIS PART FROM BREAKING.  THIS IS THE 3RD PACKIN	G HOLDER FOUND TO BE CRACKED OR BROKEN, WHERE MODIFIED OR NOT.				2	L	7	2 	4F			RT	A7EU    					 
2005050500088	20050505	00088	EU  	2005	5	5	HDS0315051       	1	20050316	G	5531	109037301	FRAME           			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					VERT STABILIZER	CRACKED         	B			VK1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	521RC					14019				THIS IS TO REPORT CRACKS IN THE FRAMES ON THE VERTICAL FIN, IN THE AREAS AT WL 2145.0 AND 2520.0.  THESE CRACKS ARE OCCU	RRING APPROXIMATELY BETWEEN FS 9350.0 TO 9850.0.    (SW19200508005) (K)					1	G	7	2 	3U	3	T		H7EU    	E2NE				 
2005050400034	20050504	00034	EU  	2005	5	4	HE89099847       	1	20050317	G	2435	150SG117Q	STARTER GEN     			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					ENGINE	UNSERVICEABLE   	Z				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	03	ZKHDG					5212	CAE840557			STARTER WOULDN'T START ENGINE						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
2005072600265	20050726	00265	SO  	2005	7	26	IAD05LA064       	1	20050726	G	7820	6690602	MUFFLER         			PIPER 	PA28  	PA28140     	7102802	SO  										EXHAUST	BLOCKED         	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			EA	17	55165					287325336				MUFFLER INTERNAL BAFFLE CAME LOOSE.   TAILPIPE SAFETY RODS DID NOT PROTRUDE FAR ENOUGH INTO MUFFER TO PREVENT BLOCKAGE.						1	L	7	1 	3O				2A13    					 
2005102600219	20051026	00219	CE  	2005	10	26	IGL1520050080    	1	20050915	G	7820	15006	MUFFLER         			CESSNA	175   	175         	2072502	CE  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2Y*      	GL  	EXHAUST	DETERIORATED    	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			GL	15	7219M	800  	7    			55519	L1881136A	CH13441		EXHAUST MUFFLER CRACKED AND DETERIORATED AND WAS NOT DETECTED DUE TO LOCATION UNDER HEAT SHROUD.  MUFFLER IS PART OF ENG	INE CONVERSION STC NR SA777CE, KIT  NR 740.					1	H	7	1 	3O	3	O	NT	3A17    	E286	5	C	P920	 
2005072600198	20050726	00198	CE  	2005	7	26	IS4R200500002    	1	20050513	G	2140	45C40	TUBE            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					COMBUSTION	CRACKED         	B			IS4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	560X				7650187	TC968				HEATER COR RECEIVED FROM CUSTOMER.  COMBUSTION TUBE FOUND CRACKED AT CROSSOVER PART WHICH CONNECTS THE INNER COMBUSTION 	TUBE TO THE OUTER COMBUSTION TUBE.  MALFUNCTION FOUND USING A PRESSURE DECAY TEST, EVEN THOUGH THIS TEST IS NOT REQUIRED	 ON THE D83A28 HEATER ASSY.  THE SERIAL NUMBER ON THE COMBUSION TUBE INDICATES IT WAS MFG IN AUG 1995.  RECOMMEND PRESSU	RE DECAY TESTS ON THESES HEATER ASSEMBLIES.  AD DOES NOT APPLY TO THESE HEATERS.  (K)			1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2005072600160	20050726	00160	CE  	2005	7	26	IS4R200500003    	1	20050513	G	2140	51A45	COMBUSTION HEAD 			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					HEATER	WORN            	B			IS4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	560X				7650187	TC968				HEATER CORE RECEIVED FROM CUSTOMER.  UPON TEARDOWN, FOUND INTERIOR OF THE COMBUSTION HEAD SEVERELY WORN FROM FLAME EROSI	ON.  PREVIOUS INSPECTIONS BY THIS REPAIR STATION HAVE FOUND SMALL HOLES APPEARING IN THE WALL OF THE COMBUSTION HEAD.  F	ROM THE OUTSIDE, THE COMBUSION HEAD APPEARS GOOD INTERNALLY, THIS COMBUSTION HEAD IS UNAIRWORTHY.  BY FOLLOWING THE MFG 	AND MM THESE CONDITIONS WOULD HAVE BEEN FOUND EARLIER.  TBO TIME IS EVERY 500 HOURS OF HEATER OPERATION OR EVERY ENGINE 	OVERHAUL, WHICHEVER OCCURS FIRST.  (K)		1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2005050600089	20050506	00089		2005	5	6	JGVR2005P7YFA    	4	20050415	G	3420	2300626020	MOTOR           	COLLINS     	ADI85A      															ADI	INTERMITTENT    	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09					822					INTERMITTENT MOTOR CAUSED STICKING FLIGHT DIRECTOR COMMAND FUNCTION.  THIS CAUSED THE COMMAND FLAG TO BE INTERMITTENTLY 	DISPLAYED.  INSPECTION REVEALED THE MOTOR TO HAVE HIGH RESISTANCE.  THIS MOTOR WAS INSTALLED NEW IN AUGUST 2004.  DATE C	ODE ON THE MOTOR IS 0424.																	 
2006012400202	20060124	00202	CE  	2006	1	24	JK1205           	1	20050820	G	7920	AE7013002H0194	LINE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					OIL SYSTEM	LEAKING         	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J	Y	FLUID LOSS                	WARNING INDICATION        	ENGINE STOPPAGE           	CR	CRUISE         	1			NM	07	441DD					4410341	P77719			THE ENGINE OIL LINE SUPPLYING OIL TO THE OIL COOLER BEGAN TO LEAK RAPIDLY INFLIGHT.  OIL PRESSURE WAS LOST, THE ENGINE W	AS SHUTDOWN AND AN UNSCHEDULED LANDING WAS ACCOMPLISHED WITHOUT DAMAGE.  INSPECTION REVEALED THAT THE LOSS WAS FROM THE 	P/N AE7013002H0194 OIL HOSE, THE INTERNAL LINING APPEARED TO HAVE BEEN SOFTENED AND RIPPED SUCH AS POSSIBLY A COMPOUND T	HAT WAS NOT COMPATIBLE WITH THE 2380 ENGINE OIL.			1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006010400121	20060104	00121	WP  	2006	1	4	JKWS1205         	2	20050820	G	7261	AE7013002H0194	HOSE            			CESSNA	441   	441         	2076020	CE  	ALIDSG	TPE331	TPE331201A  	0517	WP  					ZONE 400	LEAKING         	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			NM	07	441DD					4410341	P77719			THE ENGINE OIL LINE SUPPLYING OIL TO THE OIL COOLER BEGAN TO LEAK RAPIDLY IN-FLIGHT.  OIL PRESSURE WAS LOST, THE ENGINE 	WAS SHUTDOWN AND AN UNSCHEDULED LANDING WAS ACCOMPLISHED WITHOUT DAMAGE.  INSPECTION REVEALED THAT THE LOSS WAS FROM THE	 P/N AE7013002H0194 OIL HOSE, THE INTERNAL LINING APPEARED TO HAVE BEEN SOFTENED AND RIPPED SUCH AS POSSIBLY A COMPOUND 	THAT WAS NOT COMPATIBLE WITH THE 2380 ENGINE OIL.  FAILURE OCCURRED.			1	L	7	2 	3T	3	T	RT	A28CE   	AEXJ STC				 
2005032800075	20050328	00075	SO  	2005	3	28	KBUY5052         	1	20050216	G	3220	36742016	SWITCH          			PIPER 	PA32  	PA32R301    	7103218	SO  										NLG	OPEN            	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	05	61KD	3336 	175  			3213065				PILOT REPORTED UNSAFE NLG ON FINAL. CYCLED AND INDICATION WAS SAFE. JACKED AC, RAN GEAR THROUGH RIG AND OPS CK. FOUND NL	G DOWN LIMIT SWITCH WOULD NOT ACTIVATE PUMP IF IT WAS NOT DOWN AND LOCKED. REPLACED SWITCH AND OPS CK SYSTEM THROUGH 5 N	ORMAL AND 3 EMERGENCY CYCLES. AC RETURNED TO SERVICE. BENCH CHECK OF SWITCH REVEALED OPEN CONDITION WHEN IT SHOULD BE CL	OSED.			1	L	7	1 	3O				A3SO    					 
2005082200057	20050822	00057	GL  	2005	8	22	KESE0508001      	2	20050816	G	7314		PUMP            								AMTR  	SUBURU	SUBURU      	 	GL  					FUEL SYS	SEIZED          	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			EA	23	18GK	226  								ELECTRIC FUEL PUMP FAILED UPON THROTTLE RETARDATION WHILE TURNING BASE LEG TO FINAL FOR LANDING.  ENGINE SHUT OFF AND SU	CCESSFUL DEAD STICK APPROACH AND LANDING EXECUTED.  NO DAMAGE OR INJURIES.  PUMP PISTON FOUND TO BE SIEZED AND WAS BROKE	N FREE WITH FORCE.  CORROSION EVIDENT ON BARREL WHICH LOOKED TO BE BRASS. THIS INSTALLATION HAS NO ENGINE DRIVEN FUEL PU	MP AND FAILED UNIT IS RELIED UPON AT LOW POWER SETTINGS.  SUGGEST ROUTINE LUBRICATION AND REPLACEMENT.								3	O			EXPE3O				 
2005120200089	20051202	00089		2005	12	2	L3WSA            	4	20051118	G	2216	6565001197	CONTROL CABLE   	HONEYWELL   		CESSNA	500   	550         	2076604	CE  										AUTOPILOT SERVO	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	2663Y	7495 				5500602				WE HAVE FOUND THE ELEVATOR AUTOPILOT SERVO LT CABLE WITH BROKEN STRANDS ON 3 SUCCESSIVE AIRCRAFT THAT WERE UNDERGOING A 	PHASE 5 INSPECTION. ON CABLE HAD 50 PERCENT FRAYING. THE FRAYING WAS FOUND WHERE THE CABLE PASSES THROUGH A DOUBLE CABLE	 JOGGLE AT FUSELAGE STA 428.50 AND CAN BE DIFFICULT TO DETECT. THE 3 SUBJECT AIRCRAFT HAD 7495, 8856 AND 13393 HOURS TOT	AL TIME. THE IPC REFERENCE FOR THE CABLE IS 22-10-00, FIGURE 1, PAGE 3, ITEM 85.			1	L	7	2 	4F				A22CE   					 
2005041400106	20050414	00106	WP  	2005	4	14	LCQ20050120      	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 85 HAS HALF SECTION CRACKED OUT.  S/O 152051, OPS 29532, ZONE 6C-127.						2	L	7	2 	4F				A6WE    					 
2005041400107	20050414	00107	WP  	2005	4	14	LCQ20050120A     	1	20050120	G	5320		CHANNEL         			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				LT CENTER FS 606 TO 680 HAS SURFACE CORROSION ON CHANNELS, CRACKED OUT ON ENDS AND CENTER AREAS.  S/O 152051, OPS 29568,	 ZONE 6C-145.					2	L	7	2 	4F				A6WE    					 
2005031500034	20050315	00034	WP  	2005	3	15	LCQ29            	1	20050119	G	5330		SKIN            			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				SKIN CRACKED AT FS 996 STRINGER 23L.  S/O 152051, OPS 29033, ZONE 1A-16.						2	L	7	2 	4F				A6WE    					 
2005031100037	20050311	00037	WP  	2005	3	11	LCQ30            	1	20050119	G	5330		SKIN            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	LIGHTNING STRIKE	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				AIRCRAFT NOSE RT STA 69,  APPROX. 15 INCHES ABOVE FLOOR REFERENCE PLANE HAS A LIGHTNING STRIKE. S/O 152051, OPS 29036, Z	ONE 1A-18					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005031500038	20050315	00038	WP  	2005	3	15	LCQ31            	1	20050119	G	5330		SKIN            			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	LIGHTNING STRIKE	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				FOUND LIGHTNING STRIKE INDICATION AT L-4R BS 659.  S/O 152051, OPS 29677, ZONE 1A-54.						2	L	7	2 	4F				A6WE    					 
2005031500039	20050315	00039	WP  	2005	3	15	LCQ32            	1	20050119	G	5330		SKIN            			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				FS 64.150 SKIN IS CRACKED AROUND FASTENER, 10TH FASTENER DOWN FROM CUSP LINE.  S/O 152051, OPS 29845, ZONE 1A-67.						2	L	7	2 	4F				A6WE    					 
2005031500040	20050315	00040	WP  	2005	3	15	LCQ33            	1	20050119	G	5330		SKIN            			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				SKIN CRACKED ON RT SIDE OF FUSELAGE CANTED FRAME STA 1155.225 MID WAY BETWEEN RIVETS 2 INCH LENGTH.  S/O 152051, OPS 298	66, ZONE 1A-69.					2	L	7	2 	4F				A6WE    					 
2005031500041	20050315	00041	WP  	2005	3	15	LCQ34            	1	20050119	G	5313		LONGERON        			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				L-23L CRACKED AT FRAME ATTACH FASTENERS FS 200 E&E COMPARTMENT.  S/O 152051, OPS 29808, ZONE 1C-16.						2	L	7	2 	4F				A6WE    					 
2005031500042	20050315	00042	WP  	2005	3	15	LCQ35            	1	20050119	G	5313		LONGERON        			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				L-25L CRACKED AT FRAME ATTACH FASTENER (UPPER AND LOWER FASTENERS) FS 160 E&E COMPARTMENT.  S/O 152051, OPS 29807, ZONE 	1C-17.					2	L	7	2 	4F				A6WE    					 
2005031500043	20050315	00043	WP  	2005	3	15	LCQ36            	1	20050119	G	5514		FITTING         			DOUG  	DC9   	DC932       	3022066	WP  										HORIZ STAB	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				HORIZONTAL STABILIZER LT MOUNT LUG FITTING FOR PIVOT BEARING O/B FACE HAS CORROSION.  S/O 152051, OPS 29688, ZONE 2A-24.						2	L	7	2 	4F				A6WE    					 
2005031100061	20050311	00061	WP  	2005	3	11	LCQ37            	1	20050119	G	5310		DOOR FRAME      			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				STA. 908.5, AFT CARGO DOOR FRAME WEB HAS CORROSION ON VERTICAL SUPPORT, FOUR CORNERS FWD SIDE. S/O 152051, OPS 29258, ZO	NE 1E-3					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005031500044	20050315	00044	WP  	2005	3	15	LCQ39            	1	20050119	G	5543		DOUBLER         			DOUG  	DC9   	DC932       	3022066	WP  										RUDDER TAB	DEBONDED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				RUDDER TRIM TAB REPAIR DOUBLER DISBONDED ON RT SIDE.  S/O 152051, OPS 29865, ZONE 2B-3.						2	L	7	2 	4F				A6WE    					 
2005031500045	20050315	00045	WP  	2005	3	15	LCQ40            	1	20050119	G	5347		SEAT TRACK      			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	BROKEN          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				CAPTAIN'S O/B SEAT TRACK HAS THE END PIECE BROKEN OFF.  S/O 152051, OPS 29443, ZONE 6A-24.						2	L	7	2 	4F				A6WE    					 
2005031500046	20050315	00046	WP  	2005	3	15	LCQ41            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 7 HAS SURFACE CORROSION THRU OUT TOP AND BOTTOM.  S/O 152051, OPS 29210, ZONE 6C-24.						2	L	7	2 	4F				A6WE    					 
2005031500049	20050315	00049	WP  	2005	3	15	LCQ42            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 4 HAS SURFACE CORROSION THROUGH OUT TOP AND BOTTOM.  S/O 152051, OPS 29208, ZONE 6C-26.						2	L	7	2 	4F				A6WE    					 
2005031500050	20050315	00050	WP  	2005	3	15	LCQ43            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL 2A IS CORRODED.  S/O 152051, OPS 29207, ZONE 6C-27.						2	L	7	2 	4F				A6WE    					 
2005031500053	20050315	00053	WP  	2005	3	15	LCQ44            	1	20050119	G	5320		PAN             			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CHAFED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				CABIN FLOOR PAN HAS CHAFED THRU AREA STA 237 RBL 3 FROM THE CENTER.  S/O 152051, OPS 29425, ZONE 6C-85.						2	L	7	2 	4F				A6WE    					 
2005031500058	20050315	00058	WP  	2005	3	15	LCQ45            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				CABIN FLOOR PANEL HAS GOUGE AND CRACK FWD OF FS 237 I/B OF LEFT O/B SEAT TRACK.  S/O 152051, OPS 29423, ZONE 6C-87.						2	L	7	2 	4F				A6WE    					 
2005031500060	20050315	00060	WP  	2005	3	15	LCQ46            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				CABIN FLOOR PANEL HAS 3 EACH AREAS WORN AND CRACKED AT FS 237 LBL 7 FROM CENTER.  S/O 152051, OPS 29422, ZONE 6C-88.						2	L	7	2 	4F				A6WE    					 
2005031500062	20050315	00062	WP  	2005	3	15	LCQ47            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				CABIN FLOOR PANEL 73 LT CENTER HAS HOLES ON THE EDGE TORN OUT.  S/O 152051, OPS 29524, ZONE 6C-119.						2	L	7	2 	4F				A6WE    					 
2005031500066	20050315	00066	WP  	2005	3	15	LCQ48            	1	20050119	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL FS 120 - 160 HAS CRACKS ON TOP SKIN AND CORROSION.  TOP AND BOTTOM SIDE HAS HOLES DRILLED IN HALF	 SECTION.  S/O 152051, OPS 29528, ZONE 6C-123.					2	L	7	2 	4F				A6WE    					 
2005031100032	20050311	00032	WP  	2005	3	11	LCQ49            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					MAIN CABIN	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 83 HAS SURFACE CORROSION AND A PUNCTURE.  S/O 152051, OPS 29530, ZONE 6C-125						2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005020100003	20050201	00003	WP  	2005	2	1	LCQ50            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 80 HAS SECTION CRACKED OUT IN THE CENTER AND TOP SKIN CRACKED OUT ON EDGES.  S/O 152051, OPS 2	9531, ZONE 6C-126.					2	L	7	2 	4F				A6WE    					 
2005020100009	20050201	00009	WP  	2005	2	1	LCQ52            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 92 HAS CORNERS BROKEN OUT OF TOP SKIN, HALF SECTION IS CRACKED AND HAS SURFACE CORROSION.  S/O	 152051, OPS 29535, ZONE 6C-130.					2	L	7	2 	4F				A6WE    					 
2005020100010	20050201	00010	WP  	2005	2	1	LCQ53            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 95 HAS SKIN TORN ON END AND SURFACE CORROSION ON BOTTOM CHANNELS.  S/O 152051, OPS 29564, ZONE	 6C-141.					2	L	7	2 	4F				A6WE    					 
2005031100003	20050311	00003	WP  	2005	3	11	LCQ54            	1	20050120	G	5320		PANEL           			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					CABIN	ELONGATED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN PANEL E5-3 HAS ELONGATED HOLES ON THE END OF PANEL.  S/O 152051, OPS 29566, ZONE 6C-143						2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005031100034	20050311	00034	WP  	2005	3	11	LCQ56            	1	20050120	G	5320		CHANNEL         			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN PANEL NR 75 HAS CHANNELS CRACKED OUT AND SURFACE CORROSION.  S/O 152051, OPS 29569, ZONE 6C-146						2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005031100012	20050311	00012	WP  	2005	3	11	LCQ57            	1	20050120	G	5320		CHANNEL         			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN PANEL, NR A53 HAS CHANNELS CRACKED.  S/O 152051, OPS 29572, ZONE 6C-149						2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005031100035	20050311	00035	WP  	2005	3	11	LCQ61            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 76 RT CENTER FS 680 - 760 IB HAS HOLES BROKEN OUT ON THE END.  S/O 152051, OPS NR 29576, ZONE 	6C-153					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005031100036	20050311	00036	WP  	2005	3	11	LCQ62            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 81 HAS CRACKS AROUND RIVETS, 2 EACH PUNCTURES AND SURFACE CORROSION.  S/O 152051, OPS NR 29583	, ZONE 6C-156					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2005021700137	20050217	00137	WP  	2005	2	17	LCQ63            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				MAIN CABIN FLOOR PANEL NR 83 HAS CORROSION.  S/O 152051, OPS 29582, ZONE 6C-157.						2	L	7	2 	4F				A6WE    					 
2005020100001	20050201	00001	WP  	2005	2	1	LCQ66            	1	20050120	G	5320		FLOOR SUPPORT   			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				CABIN LT FLOORBOARD OB SUPPORT CRACKED FS 617 TO 658 ABOVE FLOOR WEB.  S/O 152051,OPS NR 29661, ZONE 6C-180.						2	L	7	2 	4F				A6WE    					 
2005020100013	20050201	00013	WP  	2005	2	1	LCQ67            	1	20050120	G	5320		FLOOR SUPPORT   			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	MISLOCATED      	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	867AT					47170				CABIN FLOOR AREA FS 680 FLOORBOARD SUPPORT MISDRILLED 36 INCHES RT OF CENTER.  S/O 152051, OPS NR 29665, ZONE 6C-183.						2	L	7	2 	4F				A6WE    					 
2005031500074	20050315	00074	WP  	2005	3	15	LCQ68            	1	20050120	G	5321		FLOOR PANEL     			DOUG  	DC9   	DC932       	3022066	WP  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				L-1 FLOOR PANEL COVER HAS CORROSION UPPER AND LOWER SURFACE.  S/O 152051, OPS 29737, ZONE 6C-201.						2	L	7	2 	4F				A6WE    					 
2005031500075	20050315	00075	WP  	2005	3	15	LCQ69            	1	20050120	G	5240		PAN             			DOUG  	DC9   	DC932       	3022066	WP  										SERVICE DOOR	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	867AT					47170				RIGHT SERVICE DOOR PAN CRACKED IN 4 EA PLACES AND INNER STRAP CRACKED AT FWD LOWER CORNER.  S/O 152051, OPS 29879, ZONE 	6C-206.					2	L	7	2 	4F				A6WE    					 
2005031500147	20050315	00147	NM  	2005	3	15	LCQ73            	1	20050224	G	5543		TAB             			BOEING	737   	737522      	138449F	NM  										RUDDER	BROKEN          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	948UA					26691				COMPOSITE TAB ON L/E SPAR OF RUDDER BROKEN OFF.  S/O 269004, N/R 24993.						2	L	7	2 	4F			RT	A16WE   					 
2005031500148	20050315	00148	NM  	2005	3	15	LCQ74            	1	20050224	G	5330		SKIN            			BOEING	737   	737522      	138449F	NM  										FUSELAGE	GOUGED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	948UA					26691				GOUGE BETWEEN S-27L - S-28L BS 420.  S/O 269004, N/R 24710.						2	L	7	2 	4F			RT	A16WE   					 
2005031500149	20050315	00149	NM  	2005	3	15	LCQ75            	1	20050224	G	5330		SKIN            			BOEING	737   	737522      	138449F	NM  										FUSELAGE	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	948UA					26691				DENT IN EXTERIOR FUSELAGE SKIN AT FS 412 S-18R.  S/O 269004, N/R 24964.						2	L	7	2 	4F			RT	A16WE   					 
2005041500127	20050415	00127	EU  	2005	4	15	LEGR200500001    	1	20050218	G	5280	25W261201452	DOOR            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										ZONE 700	CRACKED         	B			LEGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	108C					108				DURING ACCOMPLISHMENT OF AD 2004-13-18 FOUND RT MLG DOOR TO BE CRACKED AFTER REMOVAL OF DOOR HINGE.  DOOR HINGE IS NOT R	EQUIRED TO BE REMOVED UNLESS THE AFT DOOR GAP IS LESS THAN 0.25 INCH PER AD AND REFERENCED SERVICE BULLETIN.					2	L	7	2 	4F			RT	A16NM   					 
2005052500116	20050525	00116	GL  	2005	5	25	LU4R12482        	3	20050421	G	6110	B5020	SPRING          			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	STRETCHED       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	208JB					20800362		020561		SPRING ASSY STRETCHED TOO LARGE.  (K)						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
2005091200031	20050912	00031	SO  	2005	9	12	M1555            	2	20050902	G	7261		BRACKET         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					OIL FILTER	SPLIT           	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	763C					0431				DURING SCHEDULED ENGINE OIL CHANGE, FOUND BRACKET INDUCTION AIR FILTER SPLIT AT MANUFACTURED SEAM.  SUSPECT ADHESIVE USE	D AT MANUFACTURE OF THE FOAM TYPE FILTER IS INADEQUATE FOR THE TASK.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2005042000060	20050420	00060	CE  	2005	4	20	MAFALT1          	1	20050404	G	2430	DOFF10300BR	ALTERNATOR      			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	OPEN            	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	21		575  								OPEN FIELD WINDING.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2005042000061	20050420	00061	CE  	2005	4	20	MAFALT2          	1	20050404	G	2430	DOFF10300BR	ALTERNATOR      			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	OPEN            	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	21		279  								OPEN FIELD WINDING AT SLIP RING (WIRE BROKEN AT SOLDER JOINT).						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2005042000062	20050420	00062	CE  	2005	4	20	MAFALT3          	1	20050404	G	2497		WIRE            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	OPEN            	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	21		327  			ES4145					OPEN FIELD WINDING AT SLIP RING (WIRE BROKEN AT SOLDER JOINT).						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2005091200086	20050912	00086	CE  	2005	9	12	MAFALT4          	1	20050902	G	2420	C6FF10335B	ROTOR           	ELECTROSYS  		CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ALTERNATOR	FAILED          	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			WP	21		188  			B110413					ELECTROSYSTEM WOES CONTINUE, WITH ANOTHER ROTOR GOING BAD.  DETAILS: M/N DOFF10300BR S/N B110413 WITH A TS0 :1095.1 ON T	HE ALTERNATOR.  THE ROTOR WAS CHANGED 3 DIFFERENT TIMES ON THIS ALTERNATOR AND IT RAN ON FOUR DIFFERENT A/C IN IT'S LIFE	 HERE.  THIS LAST ROTOR RAN FOR 188.1 HRS.  TIS, AND PREVIOUS ROTORS ONLY RAN 18.9HRS AND 1 HR.  MORE IN-DEPTH INSPECTIO	N OF THE ALTERNATOR FOR A REOCURRING FAULT HAS TURN UP NOTHING, AS TO A CAUSE FOR ROTORS CONTINUING TO FAIL.  SINCE A RE	CENT RASH OF ROTOR FAILURES ON OTHER ALTERNATORS, POSSIBLY AN ISSUE WITH THE MANUFACTURE, ELECTORSYSTEMS AND THE QUALITY	 OF ROTORS.	1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2005110800311	20051108	00311	SW  	2005	11	8	MDR01KH2005      	1	20051010	G	6220	200571045D	BOLT            			BELL  	222   	222         	1182122	SW  										M/R CONTROLS	SHEARED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	29KH					47053				UPON INSPECTION AND MAINTENANCE OF MAIN ROTOR CONTROLS, INSPECTION REVEALED SHEARED BOLT (PN 20-057-10-45D) AT BOLT HEAD	 AT THE M/R SWASH PLATE COLLECTIVE LEVER IDLER LINK.  (ATTACH BOLTS)  MFG A- NR 28 BOLT, MFG U-NR 28 BOLT.  THIS CONDITI	ON HAS BEEN REPORTED TO MFG FOR INVESTIGATION ADN ANALYSIS OF CAUSE.  ALL REMAINING COMPANY HELICOPTERS HAVE BEEN INSPEC	TED FOR LIKE CONDITION AND FOUND AIRWORTHY.  (K)			1	G	7	2 	3U				H9SW    					 
2005110800285	20051108	00285		2005	11	8	MDR02BO2005      	1	20050110	G	6220	10514104119	NUT             																	MAIN ROTOR HEAD	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25		674  			2033					UPON INSPECTION AND MAINTENANCE OF MAIN ROTOR HEAD ASSY, SUBCOMPONENT (UPPER QUAD NUT) WAS SENT TO VENDOR FOR MAG PARTIC	LE INSPECTION AND SUBSEQUENTLY WAS REJECTED.  THIS CONDITION HAS BEEN REPORTED TO MFG FOR INVESTIGATION AND ANALYSIS OF 	CAUSE.  (K)																	 
2005081700163	20050817	00163	EU  	2005	8	17	MFSDR0501        	1	20050811	G	7797	AWG22TG2	WIRE            			EXTRA 	EA400 	EA400       	7021804	EU  	CONT  	O550  	TSIOL550C   	 	SO  						BURNED          	B				K				NONE                    				P			NO WARNING INDICATION     			UK	UNKNOWN        	1			SW	99	400YY	159  				019	603272			TACHOMETER FULL SCALE DEFLECTION ON ANALOG NEEDLE WHEN POWER SELECTED AND LOW ANALOG READING ON EGT. PROBLEM TRACED TO R	OUTING OF BOTH CABLES THROUGH A FIRESLEEVE OVER THE TURBOCHARGER. THE FIRESLEEVE HAS BUNED AWAY, LOSING ITS FIRE RESISTA	NT QUALITIES AND CAUSING BOTH TACHO AND EGT CABLES TO MELT. PROBABLY SATISFACORY ON AN AIR COOLED ENGINE, BUT NOT ON A C	LOSE COWLED, WATER COOLED ENGINE.			1	H	7	1 	3O	3	O	RT	A43CE   	E4SO				 
2005032400150	20050324	00150	SO  	2005	3	24	MN3525           	2	20050224	G	8500	IO520F	ENGINE          			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  		MAKING METAL    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9938Z	2508 	872  			U20606757	112700R	010968		DURING AIRCRAFT 50 HOUR INSPECTION, FOUND METAL IN THE OIL FILTER.  TOOK OIL SAMPLE DURING ENGINE OIL CHANGE.  RECOMMEND	ED TO OWNER TO CHANGE ENGINE.  REPLACED ENGINE AFTER OWNER APPROVAL.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2006010400107	20060104	00107	CE  	2006	1	4	MPFACTUATOR1     	1	20051213	G	2750	99105863RX	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					TE FLAPS	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	PK-MP	885  	507  			208B0989	PCEPC1004			BOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS INOPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT 	BREAKER TO OPEN.  DISASSASEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2005062300130	20050623	00130	NM  	2005	6	23	MTF2351          	1	20050616	G	3340	65445543	MOUNT BRACKET   			BOEING	727   	727223      	1384074	NM  										STROBE LIGHT	DETERIORATED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	289MT	53426	1463 			22467				STROBELIGHT MOUNT BRACKET, SHOCK MOUNTS DETERIORED AND UNIT HELD IN PLACE BY ONE SHOCK MOUNT, ALL SHOCK MOUNT ATTACH HOL	ES IN BRACKET WORN/ELONGATED, SO MOUNTS WERE NOT ABLE TO REMAIN ATTACHED.  INSPECTION OF THIS AREA WAS BY REMOVING ACCES	S PANEL 9715 PREVIOUS LISTED IN BOEING 727 MPD D6-8766-2 REV H DATED 3/78, PER -D- CHECK 6-55-12.  D-CHECK REQUIREMENT. 	 REQUIREMENT REVISED TO C-CHECK LEVEL PER REVISION TO MPD D6-8766-2 REV K DATED 4/80 OF BOEING 727 AND ACCESS PANEL 9715	 REQUIREMENT TO REMOVE HAS BEEN DELETED THEREFORE NOT PRESENTING AVAILABILITY TO INSPECT MOUNT/BRACKET ATTACHMENT.		2	L	7	3 	4F				A3WE    					 
2005052000061	20050520	00061	EA  	2005	5	20	MYNR748KA        	2	20050105	G	8530		EXHAUST VALVE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NR 3 CYLINDER	STUCK           	B			MYNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4190P	350  				17280620	L2779651A			NR 3 CYLINDER EXHAUST VALVE STUCK AT 300.1 HRS.  NR 2 CYLINDER EXHAUST VALVE STUCK AT 351.1 HRS.  REMOVED NR 1 AND NR 4 	FOR EVALUATION, CYLINDER SHOP FOUND PROBLEMS WITH THERE EXHAUST VALVES.  THESE WERE NEW SUPERIOR MILLENNIUM CYLINDER ASS	EMBLIES INSTALLED AT ENGINE OVERHAUL 351.0 TSMOH. (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005081700125	20050817	00125	SO  	2005	8	17	NEFSDO03         	1	20050711	G	3210		ROLL PIN        			PIPER 	PA24  	PA24260     	7102406	SO  	RROYCE	RB211 	RB211535E4  	54555	NE  					LT MLG	MISSING         	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	03	9167P					244655				APPROXIMATELY 2149 Z PILOT ADVISED HE BELIEVED THE AIRCRAFT LT MAIN GEAR COLLAPSED. THE SAFETY DEVICE (ROLL PIN) WAS NOT	 INSTALLED. THIS ALLOWED THE NUT TO ROTATE ALLOWING THE STUD TO BACK OUT OF THE CASTING. THIS CAUSED THE LT MAIN LANDING	 GEAR TO COLLAPSE.  AD97-01-01R1 TO PREVENT MAIN LANDING GEAR (MLG) COLLAPSE CAUSED BY MAIN GEAR SIDE BRACE STUD CRACKED	.  ANNUAL INSPECTION C/W FEB 1, 2005.			1	L	7	1 	3O	4	F		1A15    	E12EU				 
2006042700217	20060427	00217	CE  	2006	4	27	OMKR200600001    	1	20050425	G	5511	45A21104642	RIB             			BEECH 	MU300 	400A        	1155402	CE  										HORIZ STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	743TA					RK271				ROLLER RIB AT INBOARD END CRACKED (ASSY P/N 45A21104-642) IN THREE PLACES.  RIB, AND BOTH CLIPS.  CRACKING IS FROM RIB M	ATERIAL BEING TOO THIN, IMPROPER RIGGING, OR EXCESSIVE WEAR OF HORIZONTAL STABILIZER HINGE POINTS.  SUSPECT RIB MATERIAL	 IS JUST TOO THIN TO CARRY LOAD FROM ROLLER BRACKET.				2	H	7	2 	4F			RT	A16SW   					 
2006051000234	20060510	00234	CE  	2006	5	10	PAI5200503774    	1	20051019	G	3231	354100779	BRACKET         	BEECH       		BEECH 	36    	A36         	1151604	CE  										ZONE 700	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4489S	6516 				E706				DURING ANNUAL INSPECTION, FOUND LT NOSE GEAR DOOR RETRACT BRACKET CRACKED COMPLETELY THROUGH ON ONE SIDE.  NOSE GEAR RET	RACT ROD ATTACHES TO THIS BRACKET, WHICH IS RIVETED TO THE NOSE GEAR DOOR.					1	L	7	1 	3O				3A15    					 
2005102500026	20051025	00026	EU  	2005	10	25	PAZR200550249    	1	20051017	G	3320		CIRCUIT BOARD   			AMD   	FALC50	FALCON50MYST	2730106	EU  										CABIN LIGHTS	BURNED          	B			PAZR	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	03	980S				29939408	249				PASSENGER NOTICED A SPARK AND SMOKE IN THE UPPER FWD AREA OF THE CABIN HEADLINER. PILOT WAS NOTIFIED AND PILOT DISENGAGE	D CIRCUIT BREAKER FOR THE LIGHTS. AIRCRAFT LANDED WITHOUT INCIDENT. UPON REMOVAL OF HEADLINER AND LIGHT STRIPS, VISUALLY	 INSPECTED AND FOUND LIGHT STRIP CIRCUIT BOARD WAS BURNED AND CHARRED DUE TO EXCESSIVE HEAT, LIGHT TRACK WAS DEFORMED, T	HERMAL PLASTIC AT ENDS OF LIGHTS WERE MELTED, AND ONE OF THE 28VDC POWER LEAD WIRES WAS PULLED OUT OF THE CIRCUIT BOARD.			2	L	7	3 	4F				A46EU   					 
2005092100060	20050921	00060	NE  	2005	9	21	R017794          	3	20050920	G	6110	D7745	BEARING         	HARTZL      	HCE4A3J     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER HUB	BROKEN          	B			SJ3R	K				NONE                    				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			GL	05	SJ3R	3791 			HJ1634			HJ1634		PROP WAS REMOVED FOR LOOSE BLADE. PROP WAS OVERHAULED BY MFG SERVICE CENTER ON 10/7/03 AND INSTALLED NEW D-7745 BEARINGS	 AT THAT TIME.  HUB SIDE BEARINGS ON BLADES 2 AND 3 ARE CRACKED CIRCUMFERENTIALLY. HUB SIDE BEARING ON BLADE 4 IS BROKEN	.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2005080900070	20050809	00070	EU  	2005	8	9	RX8R2005002      	1	20050802	G	2120	050143	MOTOR           		35000031HP  	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					BLOWER	INOPERATIVE     	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	578AE	401  	401  			3716	22318			AIR CONDITIONING CONDENSER BLOWER FAILED AFTER 401.4 OPERATING HOURS.						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005080900059	20050809	00059	EU  	2005	8	9	RX8R2005003      	1	20050803	G	2120	050085	MOTOR           		35000031HP  	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					A/C BLOWER	INOPERATIVE     	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	578AE	2    	2    			3716	22318			AIR CONDITIONING CONDENSER BLOWER FAILED AFTER 2 OPERATING HOURS.						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2005061700137	20050617	00137	CE  	2005	6	17	S002368          	1	20050608	G	2435	6762751R	STARTER         			BEECH 	58    	58          	1152740	CE  										ENGINE	SEIZED          	D				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	06	3101B					TH1901				THIS STARTER SIEZED DURING START CAUSING SIEZURE AND SEVERE DAMAGE TO THE ENGINE ACCESSORY GEARBOX STATER ADAPTER.						1	L	7	2 	3O				3A16    					 
2005083000149	20050830	00149	CE  	2005	8	30	S3692            	1	20050825	G	3246	C1630040102	WHEEL           			CESSNA	210   	210M        	2073450	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG	SEPARATED       	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	05	761K	5265 				21062316				TWO BOLTS IN RT MAIN WHEEL INNER FLANGE, BROKE ON LANDING, CAUSING WHEEL INNER FLANGE AND BRAKE DISC TO PARTIALLY SEPARA	TE FROM WHEEL HUB AND RUB INTO MAIN GEAR AXLE FITTING.  MOUNTING BOLT HOLES IN BRAKE DISC SHOW SOME ELONGATION, POSSIBLY	 DUE TO LOOSE BOLTS BEFORE BOLT FAILURE.  REPLACED WHEELS AND BRAKES WITH CONVERSION KIT, AND REPLACED RT MAIN GEAR AXLE	 FITTING.			1	H	7	1 	3O	3	T		3A21    	E2NE				 
2005060900089	20050609	00089	SO  	2005	6	9	SO11200516386    	1	20050428	G	3250	485615	ARM             			PIPER 	PA20  	PA20        	7102002	SO  	LYC   	O290  	O290*       	41506	EA  					TAIL STEERING	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	11	7053K	1632 	6    			20160				UPON LANDING, PILOT REPORTED NO CONTROL OF TAIL WHEEL STEERING AND SUBSEQUENT LOSS OF CONTROL.  VISUAL INSPECTION REVEAL	ED RUDDER TO TAIL WHEEL STEERING ARM HAD BROKEN JUST OB OF A PREVIOUS WELD/BRAZE REPAIR.					1	H	7	1 	3O	3	O		1A4     	E229				 
2005040700302	20050407	00302	NM  	2005	4	7	SROM200500001    	1	20050119	G	3350	21131A	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										CABIN	DISCHARGED      	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		11   			23466				AFT GALLEY DOOR EMERGENCY LIGHT INOP.  REMOVED AND REPLACED BATTERY PACK IAW B737 NN 3351-71, OPS CHECKED GOOD.						2	L	7	2 	4F			RT	A16WE   					 
2005041400115	20050414	00115	NM  	2005	4	14	SROM200500002    	1	20050129	G	3397	58791	POWER CABLE     			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	OPEN            	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				FLOOR PROXIMITY EMERGENCY ESCAPE PATH LIGHTING INOP BETWEEN ROWS 9 TO 15.  TROUBLESHOT, REMOVED AND REPLACED FLOOR PROXI	MITY ESCAPE PATH LIGHTING CABLE LEAD ASSEMBLY IAW B737 MM 33-51-191, OPS CHECK GOOD.					2	L	7	2 	4F			RT	A16WE   					 
2005041400116	20050414	00116	NM  	2005	4	14	SROM200500003    	1	20050128	G	3350	582212	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				EMERGENCY ESCAPE FLOOR LIGHTING FROM ROWS 16 TO 19 INOP AND L2 DOOR INTERIOR EMERGENCY EXIT LIGHTS INOP.  CLEANED CONNEC	TOR ON EMERGENCY ESCAPE FLOOR LIGHT STRIP AT ROW 18 AND REMOVED AND REPLACED R2 DOOR EMERGENCY EXIT LIGHTS BATTERY PACK 	IAW B737MM 33-51-191, OPS CHECK GOOD.				2	L	7	2 	4F			RT	A16WE   					 
2005041500044	20050415	00044	NM  	2005	4	15	SROM200500004    	1	20050203	G	3397	58791	WIRE            			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	BROKEN          	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				FWD SECTION EMERGENCY FLOOR LIGHTS INOPERATIVE ROWS 1 - 3.  REPLACED BROKEN FLOOR LIGHT STRIP IAW MM 33-51-191.  OPS CHE	CK NORMAL.					2	L	7	2 	4F			RT	A16WE   					 
2005041500045	20050415	00045	NM  	2005	4	15	SROM200500005    	1	20050204	G	3350	582212	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		32   			23466				EMERGENCY ESCAPE FLOOR LIGHTING INOP FROM ROWS 15 TO 18.  REPLACED BATTERY PACK, ESCAPE LIGHTING OPS CHECK GOOD IAW CPA 	AMM SUPPLEMENT 33-51-191.					2	L	7	2 	4F			RT	A16WE   					 
2005042000047	20050420	00047	NM  	2005	4	20	SROM200500006    	1	20050310	G	3350	582212	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				EMERGENCY EGRESS AFT FLOOR LIGHTING VERY DIM, THEN WENT INOP ON OPS CHECK.  REMOVED AND REPLACED EMERGENCY EGRESS AFT BA	TTERY PACK IAW B737MM 33-51-93, OPS CHECK GOOD.					2	L	7	2 	4F			RT	A16WE   					 
2005071500184	20050715	00184	NM  	2005	7	15	SROM200500008    	1	20050710	G	3350	582212	POWER SUPPLY    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHTS	DISCHARGED      	C			SROM	O				OTHER                   				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA					23466				RT FLOOR LEVEL EMERGENCY EXIT DOOR LIGHT INOP. REMOVED AND REPLACED RT EMERGENCY EXIT POWER SUPPLY P/N 5822-12, CABLE LE	AD AND 1 EL LAMP STRIP.  OPS CHECKED GOOD PER AMM 33-51-191.					2	L	7	2 	4F			RT	A16WE   					 
2005081000224	20050810	00224	NM  	2005	8	10	SROM200500011    	1	20050729	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					STA910,STR16	GOUGED          	I			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING 24 MONTH INSPECTION FOUND GOUGE IN SKIN AT STA 910, STR 16 TO BE OUT OF LIMITS DUE TO SKIN THICKNESS AFTER BLENDI	NG.  REPAIRED GOUGE IN SKIN AT STA 910, STR 16 IAW B737 SRM 53-30-3  FIG. 18.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2005081000225	20050810	00225	NM  	2005	8	10	SROM200500012    	1	20050802	G	5320		FLOOR SUPPORT   			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					STA797,STR 8R	DAMAGED         	A			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING 24 MONTH INSPECTION FOUND DAMAGE TO CARGO FLOOR SUPPORT STRUCTURE AT STA 797 STR 8R.  ALLOWABLE DAMAGE .090 IAW S	RM 63-10-1 FIG 5, DAMAGE - .340.  REPAIRED DAMAGE IAW SRM 53-10-5, FIG 6.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2005082300060	20050823	00060	NM  	2005	8	23	SROM200500013    	1	20050815	G	3230		SENSOR          			BOEING	737   	737205      	1384456	NM  										MLG	OUT OF ADJUST   	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	736BP		5    			23465				AFTER TAKEOFF THE LANDING GEAR LEVER WOULD NOT MOVE TO THE GEAR UP POSITION.  GEAR WAS LEFT DOWN AND AIRCRAFT RETURNED T	O DEPARTURE AIRPORT AND MADE A UNEVENTFUL OVERWEIGHT LANDING.  TROUBLE SHOOTING FOUND NO FAULTS WITH THE WIRING HARNESS 	ASSOCIATED WITH THE LANDING GEAR CONTROL SYSTEM.  FOUND GROUND SAFETY SENSOR ACTUATOR GAP OUT OF ADJUSTMENT.  ADJUSTED G	AP, GROUND SPOILER INTERLOCK. OPS CHECKED SAFETY SENSOR, GROUND SPOILER AND LANDING GEAR EXTENSION & RETRACTION SYSTEMS 	IAW B737 AMM.		2	L	7	2 	4F			RT	A16WE   					 
2005082500115	20050825	00115	NM  	2005	8	25	SROM200500014    	1	20050821	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BS1036,STR8L	GOUGED          	I			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US					22751				DURING ROUTINE INSPECTION FOUND A GOUGE IN THE SKIN AT BS 1036.5, STR 8L.  REPAIRED IAW MFG MESSAGE 1-115922448-4 AND SR	M 53-30-3, FIG. 50.  BLENDED, REMOVED DAMAGE, EDDY CURRENT INSPECTED FOR CRACKS AND INSTALLED AN EXTERNAL DOUBLER IAW ME	SSAGE AND SRM REFERENCED.				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005101800168	20051018	00168	NM  	2005	10	18	SROM200500015    	1	20050926	G	3230	69355004	ACTUATOR        			BOEING	737   	737205      	1384456	NM  										LT MLG UPLOCK	BYPASSING       	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	736BP					23465				AFTER TAKE-OFF FROM ANC, GEAR WAS SELECTED UP, LT MAIN WOULD NOT INDICATE UP AND LOCKED.  AIRCRAFT RETURNED FOR AN UNEVE	NTFUL LANDING. DETERMINED LT UPLOCK ACTUATOR WAS BYPASSING FLUID. REPLACED UPLOCK ACTUATOR. SUBSEQUENT GEAR SWING AND FL	IGHT CHECK WERE SATISFACTORY.				2	L	7	2 	4F			RT	A16WE   					 
2006010600074	20060106	00074	NM  	2006	1	6	SROM200500016    	1	20051212	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	A			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US					22751				DURING ROUTINE MAINTENANCE FOUND A 3 INCH CRACK IN THE FUSELAGE SKIN AT BS 973, STR 21L.  INSTALLED TEMPORARY REPAIR DOU	BLER IAW 8110-3 APPROVED REPAIR, REFERENCE DWG 33-05565-1.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006010600077	20060106	00077	NM  	2006	1	6	SROM200500017    	1	20051212	G	5753	654648175	SPINDLE         			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FLAP CARRIAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		9319 			22751				DURING ROUTINE NDT INSPECTION OF OB FLAP SPINDLE IAW AD 2003-24-08 AND SB 737-57A1277 FOUND A FLAP CARRIAGE SPINDLE CRAC	KED 40 PERCENT AT THE RADIUS OF THE YOKE TO THE FIRST BEARING LAND.  FLAP CARRIAGE ASSEMBLY REPLACED WITH A NEW UNIT. RE	CORDS INDICATE 5221 CYCLES SINCE OVERHAUL.				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2005071800218	20050718	00218	NM  	2005	7	18	SROM20050009     	1	20050712	G	3350	362624	LIGHT           			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHTS	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	736BP					23465				EMERGENCY TRACK LIGHTING AT ROW 17 AFT AND L2 GROUND LEVEL EXIT LIGHT INOP.  REMOVED AND REPLACED ILLUMINATION AISLE STR	IP AT ROW 19 IAW 33-51-191.  OPERATIONAL CHECK GOOD.					2	L	7	2 	4F			RT	A16WE   					 
2005071800217	20050718	00217	NM  	2005	7	18	SROM20050010     	1	20050713	G	3350	582039	LIGHT           			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHTS	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA					23466				AFT EMERGENCY EXIT LIGHT UNDER AFT F/A SEAT INOP.  REMOVED AND REPLACED EMERGENCY EXIT LIGHT ASSEMBLY IAW B737MM 33-51-1	91.					2	L	7	2 	4F			RT	A16WE   					 
2005062900089	20050629	00089	NE  	2005	6	29	T48R20050013     	2	20050621	G	7250	798404	BLADE           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ENGINE	FRACTURED       	B			GTIA	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			T			ENGINE CASE PENETRATION   			CR	CRUISE         	1			GL	09	834NK	4500 	4500 			49847	718055			ENGINE WAS REMOVED FROM N834NK NR 2 POSITION FOR IN FLIGHT SHUTDOWN.  VISUAL INSPECTION REVEALED THE T-4 BLADES FRACTURE	D/MISSING AT THE BASE OF THE BLADE ROOT WITH PENETRATION OF THE CONTAINMENT AND OUTER ENGINE CASINGS.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2005052500068	20050525	00068	GL  	2005	5	25	T7419            	3	20050509	G	6114	D7582	BULKHEAD        			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	TSIO550B    	17043	SO  	MCAULY	2A34C	2A34C201    	GL  	PROPELLOR	CRACKED         	B				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			GL	11	1016C	145  				290297	685018	00296		SPINNER BULKHEAD CRACKING AT 50HRS TKS WAS INSTALLED BY AIRCRAFT FACTORY.  1ST BULKHEAD REPLACED AT 104 HRS, 2CD BULKHEA	D REPLACED AT 249.5 HRS.  COULD NOT DETERMINE IF THE PROPELLER EVER HAD A PROP BALANCE.  FOUND OIL COOLER MOUNTING ANGLE	 CRACKED ALSO AT 249.5 HRS				1	L	7	1 	3O	3	O	RT	2A3     	E5SO	5	C	P3EA	 
2005032800046	20050328	00046	SO  	2005	3	28	TCMMAQ1          	2	20050125	G	7414	103493504	MAGNETO         			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	DEFORMED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21	PKMAB	509  				U20606806	532226			COIL WEDGES OVERDRIVEN TO THE POINT OF CONTACT WITH COIL, CRACKING THE INSULATION.						1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2005032800047	20050328	00047	SO  	2005	3	28	TCMMAQ2          	2	20050125	G	7414	103493505	MAGNETO         			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	DEFORMED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21	PKMAB	509  				U20606806	532226			COIL WEDGES OVERDRIVEN TO THE POINT OF CONTACT WITH COIL, CRACKING THE INSULATION.						1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2005020100012	20050201	00012	EU  	2005	2	1	TL9R200500001    	1	20050120	G	3242	C200601004	BRAKE           			AIRBUS	330   	A300*       	       	EU  										MLG	MAKING METAL    	B			TL9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										OUR REPAIR SHOP REPORTS THAT THE ROTORS IN THIS BRAKE PN HAVE A HISTORY OF FALLING APART.  WHEN THIS HAPPENS, DAMAGE TO 	THE TORQUE TUBE CAN OCCUR WHICH WILL SEVERELY DEGRADE THE PERFORMANCE OF THE BRAKE.					2	L	7	2 	4F			RT	A26NM   					 
2005020100011	20050201	00011	EU  	2005	2	1	TL9R200500002    	1	20050120	G	3242	C200601004	BRAKE           			AIRBUS	330   	A300*       	       	EU  										MLG	MAKING METAL    	B			TL9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										OUR REPAIR SHOP REPORTS THAT THE ROTORS IN THIS BRAKE PN HAVE A HISTORY OF FALLING APART.  WHEN THIS HAPPENS, DAMAGE TO 	THE TORQUE TUBE CAN OCCUR WHICH WILL SEVERELY DEGRADE THE PERFORMANCE OF THE BRAKE.					2	L	7	2 	4F			RT	A26NM   					 
2005031400008	20050314	00008	EU  	2005	3	14	TXER099315       	1	20050120	G	2400	51455Y2	RELAY           			UROCOP	EC155 	EC155B      	8681000	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					UNKNOWN	FAILED          	B			TXER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	155EW					6660				RELAY FAILED.						1	G	7	2 	3U	3	U		H10EU   	E00054EN				 
2005062200220	20050622	00220	NE  	2005	6	22	UIA0506          	2	20050614	G	7320	ST3367009WE	PACKING         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					NR 1 ENGINE	BROKEN          	Z				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			TW	00	15225					405	123131			TRANSIT CHECK FOUND FUEL LEAKING FROM NR 1 ENG.  DETAILED INSPECTION FOUND FUEL MANIFOLD PACKING BROKEN IAW AMM 71-01-40	.  REPLACED NEW ONE AND IAW AMM 71-00-00 ENG RUNUP CHECK CONDITION NORMAL, NO FUEL LEAK FIND.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005072000166	20050720	00166	EA  	2005	7	20	UIA0507001       	1	20050704	G	3231	83232013003	BELLCRANK       			DHAV  	DHC8  	DHC8311     	1386006	EA  										NLG DOOR	BROKEN          	Z				O				OTHER                   				S			AFFECT SYSTEMS            			AP	APPROACH       	1			TW	00	15233					402				NOSE LANDING GEAR DOOR MAFUNCTION IN FLIGHT,AFTER LANDING CHECK FOUND NOSE LANDING GEAR FRONT DOOR BELLCRANK BOLT HOLE B	ROKEN.IAW AMM32-20-26 REPLACED NEW BELLCRANK ASSY AND BOLT.AND IAW AMM FUNCTION CHECK CONDCTION NORMAL.					2	H	7	2 	4T			RT	A13NM   					 
2005102800080	20051028	00080	NE  	2005	10	28	UIA200509        	2	20051025	G	7200		ENGINE          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					LEFT	MAKING METAL    	Z				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	99	15227	18273	5118 			406	123250			AC LT ENGINE LOW OIL PRESS WARNING LIGHT ON, PILOT SHUT DOWN LT ENGINE IN-FLIGHT, THEN SINGLE ENGINE LANDING.  GROUND IN	SPECTION RESULTS, FOUND ENGINE CONDITION PANEL TOTAL 7 FLAG, ONLY OIL TANK, RED FLAG SHOW ON, REMOVED OIL TANK CHIP DETE	CTOR FOUND MINOR METAL CHIP, FOUND OIL WETTING ON EXTERNAL AREA, OIL QTY DROP TO LOWER LEVEL.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2005041500084	20050415	00084		2005	4	15	VW3R20050004     	4	20050208	G	2565	D29601103	GIRT BAR        	AIRCRUISERS 		AIRBUS	330   	A300*       	       	EU  										ESCAPE SLIDE	DEFECTIVE       	B			VW3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	09	ALL				0412	ALL				GIRT EXTENSION DOES NOT FIT PROPERLY ON GIRT BAR.  GIRT EXTENSION PADS RIDE UP ON CAVITY RIDGE OF GIRT BAR.  PLEASE NOTE	 THIS EVACUATION SLIDE IS ALSO USED ON A310 AIRCRAFT.					2	L	7	2 	4F			RT	A26NM   					 
2006020300119	20060203	00119		2006	2	3	YHLR200500001    	4	20051123	G	3457	0100013911	GPS             			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					COCKPIT	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2668Q					287790414				CUSTOMER STATED THAT THE GNS-430 DISPLAY WAS NO LONGER WORKING AND THAT THE CDI WAS PEGGED LT AT ALL TIMES. SENT UNIT OU	T FOR REPAIR. ALSO FOUND UPON INSPECTION OF THE GNS-430 INSTALLATION, IT WAS NOTED THAT REPAIR STATION HAD NOT INSTALLED	 AN AVIONICS COOLING FAN IAW THE INSTALLATION MANUAL. AN AVIONICS COOLING FAN WAS INSTALLED UPON RECEIVING THE GNS-430 B	ACK FROM REPAIR. THE PROBLEM WITH THE GNS-430 WOULD HAVE BEEN PREVENTED IF AN AVIONICS FAN HAD BEEN INSTALLED IAW THE RE	QUIREMENTS FOR COOLING AS STATED IN THE INSTALLATION MANUAL.		1	L	7	1 	3O	3	O		2A13    	E286				 
2006022100160	20060221	00160	SW  	2006	2	21	YTRR106607       	1	20051104	G	6710	412310400105	BEARING         			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	4125C	760  				33103				BEARING WORN.  REPLACED ROD-END BEARING ASSEMBLY.						1	G	7	2 	4U				H4SW    					 
2006022100161	20060221	00161	SW  	2006	2	21	YTRR106608       	1	20051101	G	6710	412310400103	BEARING         			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	4125C	760  				33103				BEARING FOUND WORN.  REPLACED ROD END ASSY.						1	G	7	2 	4U				H4SW    					 
2006022100162	20060221	00162	SW  	2006	2	21	YTRR106609       	1	20051101	G	6710	412310400103	BEARING         			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	4125C	760  				33103				ROD END BEARING FOUND WORN.  REPLACED ASSEMBLY.						1	G	7	2 	4U				H4SW    					 
2006022100163	20060221	00163	SW  	2006	2	21	YTRR106610       	1	20051101	G	6710	412310400103	BEARING         			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	4125C	760  				33103				ROD END BEARING FOUND WORN.  REPLACED ASSEMBLY.						1	G	7	2 	4U				H4SW    					 
2006022100164	20060221	00164	SW  	2006	2	21	YTRR106621       	1	20050916	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										UNIVERSAL JOINT	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	407HX	259  			RXFS8590	53092				UNIVERSAL BEARING ASSEMBLY FOUND WORN.  REPLACED BEARING ASSY.						1	G	7	1 	3U			O	H2SW    					 
2006022100165	20060221	00165	SW  	2006	2	21	YTRR106622       	1	20050916	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										UNIVERSAL JOINT	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	407HX	259  			RXFS8058	53092				UNIVERSAL BEARING ASSEMBLY FOUND WORN.  REPLACED BEARING ASSY.						1	G	7	1 	3U			O	H2SW    					 
2006022100166	20060221	00166	SW  	2006	2	21	YTRR106624       	1	20051014	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										UNIVERSAL JOINT	WORN            	B			YTRR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	595RL	856  			RXFS9719	53595				UNIVERSAL BEARING ASSEMBLY FOUND WORN.  REPLACED PART.						1	G	7	1 	3U			O	H2SW    					 
2006022100167	20060221	00167	SW  	2006	2	21	YTRR106625       	1	20051015	G	6710	406310405101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	B			YTRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	594RL	1031 				53594				M/R PC LINK BEARING AXIAL AND RADIAL MOVEMENT BEYOND LIMITS						1	G	7	1 	3U			O	H2SW    					 
2006022100168	20060221	00168	SW  	2006	2	21	YTRR106626       	1	20051006	G	5302	206031417007005	SUPPORT FITTING 			BELL  	206   	206B3       	1181506	SW  										VERTICAL FIN	BROKEN          	B			YTRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2043B					3355				FOUND BOTH SUPPORTS FOR VERTICAL FIN ASSEMBLY BROKEN THROUGH LOWER MOUNTING HOLES.						1	G	7	1 	3U				H2SW    					 
2006022100169	20060221	00169	GL  	2006	2	21	YTRR106627       	2	20051103	G	7320	23057344	FUEL CONTROL    			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	HOT START       	B			YTRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2043B	203  				3355				FUEL CONTROL FAILED TO HIGH-SIDE DURING LIGHT OFF. REPLACED FUEL CONTROL ASSEMBLY.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005051100221	20050511	00221	SO  	2005	5	11	ZB0R200500001    	1	20050418	G	2720		TRIM SYSTEM     			PIPER 	PA28  	PA28180     	7102808	SO  										ZONE 300	OUT OF RIG      	B			ZB0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	643MT	4902 	45   			285646				FOUND RUDDER CONTROL AND RUDDER TRIM CONTROL SYSTEMS OUT OF RIG.  CABLES WERE LOOSE AND IMPROPERLY ADJUSTED.  RIGGED RUD	DER AND RUDDER TRIM SYSTEM PER PA28-180 SERVICE MANUAL.					1	L	7	1 	3O				2A13    					 
2005051600100	20050516	00100	SO  	2005	5	16	ZB0R200500002    	1	20050425	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					ENGINE	BROKEN          	B			ZB0R	E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	05	15143	140  	140  			28R7335027	L958451A			ON START, PILOT HEARD GRINDING NOISE. ABORTED START PROCEDURE AND PERFORMED VISUAL INSP OF VISIBLE STARTER COMPONENTS. F	OUND STARTER BENDIX SEVERELY DAMAGED. MAINT INSPECTION REVEALED DAMAGE TO STARTER RING GEAR. BOTH COMPONENTS (GEAR AND S	TARTER) REPLACED. NO FURTHER PROBLEMS DETECTED.				1	L	7	1 	3O	3	O		2A13    	1E10				 
2005071100167	20050711	00167	CE  	2005	7	11	ZB0R200500003    	1	20050706	G	3340	CM358910	CIRCUIT BREAKER 			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LANDING LIGHT	SHORTED         	B			ZB0R	H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	05	963AC	2735 	2    			172S8259				DURING TRAINING FLIGHT, INSTRUCTOR AND STUDENT NOTICED SMOKE COMING FROM LANDING LIGHT SWITCH. INSTRUCTOR IMMEDIATELY TU	RNED MASTER SWITCH OFF AND PROCEEDED BACK TO BASE. INSPECTION IN MAINTENANCE REVEALED LANDING LIGHT BREAKER SWITCH INOPE	RATIVE. REPLACED WITH NEW P/N CM3589-10. SYSTEM OPS CK OK. NO EXTERNAL OR WIRING DAMAGE.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2005071100166	20050711	00166	SO  	2005	7	11	ZB0R200500004    	1	20050701	G	2731	481640	PULLEY          			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					STABILIZER	BROKEN          	B			ZB0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	15143		99   			28R7335027				DURING ANNUAL INSPECTION, FOUND STABILIZER TRIM AFT CABLE UPPER RT PULLEY, P/N 481-640, BROKEN IN HALF. REPLACED WITH NE	W PART. RIG AND OPS CKS OK.					1	L	7	1 	3O	3	O		2A13    	1E10				 
2005071100168	20050711	00168	SO  	2005	7	11	ZB0R200500005    	1	20050701	G	3110	67435002	POTENTIOMETER   			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					PANEL LIGHTS	MALFUNCTIONED   	B			ZB0R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	05	15143		99   			28R7335027				DURING ANNUAL INSPECTION, FOUND PANEL LIGHTS POTENTIOMETER DIMMING INOP. SWITCH WILL COME ON BRIGHT, BUT WILL NOT DIM. A	LSO, LANDING GEAR LIGHTING WILL NOT DIM CORRECTLY WHEN POTENTIOMETER IS ON. REPLACED WITH NEW P/N 67435-002. OPS CK OK.					1	L	7	1 	3O	3	O		2A13    	1E10				 
2005081600216	20050816	00216	SO  	2005	8	16	ZB0R200500006    	1	20050811	G	3210	67031002	FITTING         			PIPER 	PA28  	PA28R200    	7102811	SO  										MLG	CRACKED         	B			ZB0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	41331		56   			28R7435169				DURING REPAIR OF LT MLG DRAG BRACE KNEE JOINT, WE FOUND THE RETRACT FITTING CRACKED. REPLACED WITH NEW LIKE PART.						1	L	7	1 	3O				2A13    					 
2005120200098	20051202	00098	EU  	2005	12	2	ZN3R030M         	1	20051122	G	7921	1601562	OIL COOLER      			AMD   	FALC20	FALCON      	2720302	EU  	GARRTT	ATF3  	ATF36A4     	29002	WP  					ENGINE	MISREPAIRED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	ZN3R	5177 					P21108			OIL COOLER 160156-2, SN 23-610C SERIES 2 HAS POSSIBLE UNAPPROVED REPAIR CONSISTING OF A PLUG WELD IN THE MIDDLE OF THE O	IL COOLER FINS AND WALL COMPLETELY THRU.  CHIEF INSPECTOR NOTIFIED AT REPAIR STATION AND REQUESTED SUP TO BE COMPLETED O	N 11/22/05.				2	L	7	2 	4F	4	F		A7EU    	E7WE				 
2005052300321	20050523	00321	WP  	2005	5	23	ZN3R425038       	2	20050401	G	7200	30729202	BEARING         			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					ENGINE	FRACTURED       	B			ZN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07			1052 				P77111C			ENGINE RETURNED TO SERVICE CENTER FOLLOWING COMMANDED SHUTDOWN IN FLIGHT DUE TO LOW OIL PRESSURE.  DURING INSPECTION A F	RACTURED CAGE AND OUTER RACE WAS FOUND ON A FORWARD PLANETARY ROLLER BEARING.					2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2005072200056	20050722	00056	WP  	2005	7	22	ZN3R475888       	2	20050719	G	7250	30607881	TURBINE BLADES  			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  						SEPARATED       	B			ZN3R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	07		959  				N864QS	P107672			ENGINE RETURNED TO SERVICE CENTER FOLLOWING COMMANDED SHUTDOWN IN FLIGHT DUE TO EXCESSIVE VIBRATION.  DURING INSPECTION,	 SEPARATED 3RD LPT BLADES (QTY. 3) WERE FOUND.  SEPARATED BLADES WERE RETURNED TO ENGINE OEM (HONEYWELL) FOR EVALUATION.	  CAUSE OF BLADE SEPARATION IS UNKNOWN AT THIS TIME.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE